th

29 AAS/AIAA Space Flight
Mechanics Meeting,January 13-17
Ka’anapali, HI
AAS General Chair
Dr. Matthew Wilkins
L3 Advanced Defense Solutions

AIAA General Chair
Dr. Renato Zanetti
The University of Texas at Austin

AAS Technical Chair
Images courtesy: John Hopkins APL

Dr. Francesco Topputo
Politecnico di Milano

AIAA Technical Chair
Dr. Andrew Sinclair
Air Force Research Laboratory1/6/2019

FINAL PROGRAM

29TH AAS/AIAA SPACE FLIGHT MECHANICS MEETINGCONFERENCE INFORMATIONGENERAL INFORMATION
Welcome to the 29th Space Flight Mechanics Meeting, hosted by the American Astronautical Society (AAS)
and co-hosted by the American Institute of Aeronautics and Astronautics (AIAA), January 13 – 17, 2018.
This meeting is organized by the AAS Space Flight Mechanics Committee and the AIAA Astrodynamics
Technical Committee, and held at the Sheraton Maui Resort and Spa, 2605 Ka’anapali, Maui, HI, (808)-6610031, https://www.marriott.com/hotels/travel/hnmsi-sheraton-maui-resort-and-spa/.

REGISTRATION
Registration Site ( https://www.xcdsystem.com/aas/attendee/index.cfm?ID=zP55GsC )In order to encourage early registration, we have implemented the following conference registration rate
structure: Register by November 30, 2018 and save $70!
Category

Early Registration(through Nov 30, 2018)

Registration (beginning
Dec 1, 2018)

Walk-up Registration(beginning Jan 1, 2019)

Full - AAS or AIAA
Member

$600

$670

$770

Full - Non-member

$700

$770

$870

Retired or Student* Member

$250

$320

$420

$370 / $365

$470 / $465

Retired / Student* - Non- $300 / $295
member*does not include proceedings CD

Refunds will be issued until December 31, 2018. A 10% fee will be assessed for all refunds issued after thatdate and until 8:00 am EST January 13, 2018. No refunds will be issued after 8:00 am EST January 13, 2018.
Please note that only the first 279 to register and/or purchase a guest ticket will be guaranteed a ticket foradmission to the Tuesday evening Old Lahina Luau. After 279 Luau ticketes are issues additional tickets will
be only available contingent on the venue’s seating availabiligy. The Old Lahina Luau usually sells out weeks
in advance. Register Early! Bus transportation is provided from the conference hotel to the luau and back.
Guest tickets for the luau may be purchased for $120. More information about the luau is included below.
All registrants and guests are invited to the welcome reception on Sunday evening for food and drinks.
A conference registration and check-in table will be located near the session rooms of the Sheraton Maui
Resort and will be staffed according to the following schedule:ØØØPage 1

Sunday Januray 13: 3pm – 6pm
Monday Januray 14: 7:30am – 2pm
Tuesday Januray 15: 8am – 2pm

Ø Wednesday Januray 16: 8am – 2pm
Ø Thursday January 17: 8am – 10 am

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We will accept registration and payment on-site for those who have not pre-registered online, but we strongly
recommend online registration before the conference in order to avoid delays (see URL above). Preregistration also gives you free access to pre-print technical papers. On-site payment by credit card will be
only through the AAS website using a computer at the registration table. Any checks should be made payable
to the “American Astronautical Society.”

SCHEDULE OF EVENTS

Start

End

Function

Room

3pm

6pm

Registration

Foyer/Kihei

6pm

9pm

Early Bird Reception (Food and Hosted Bar)

Anuemue Lawn

7:30am2pm

Registration

8am

12pm

Session 1: Orbit determination & space,surveillance-tracking

Kapalua

8am

12pm

Session 2: Orbital dynamics, perturbations, andstability I

Napili

8am

12pm

Session 3: Attitude dynamics and control I

Kula

8am

12pm

Session 4: Trajectory Design & Optimization I

Hana

10am

10:20amMorning BreakNoon

1:30pmJoint Technical Committee Lunch

Kihei

1:30pm

5:30pmSession 5: Artificial intelligence in astrodynamics

Kapalua

1:30pm

5:30pmSession 6: Asteroid & non-Earth orbiting missions I

Napili

1:30pm

5:30pmSession 7: Attitude dynamics and control II

Kula

1:30pm

5:30pmSession 8: Trajectory Design & Optimization II

Hana

3:30pm

3:50pmAfternoon Break

5:30pm

6:30pmConference Administration Subcommittee

Kapalua

5:30pm

6:30pmTechnical Administration Subcommittee

NapiliPage 214 January

Monday13
JanuaryDay
SundayTechnical sessions begin on Monday, 14 January, at 8 am. The last technical sessions end at 12:20 pm on
Thursday, 17 February. Presentations are limited to 15 minutes with an additional 5 minutes for questions andanswers. Each session has a 20-minute morning or afternoon break. Authors are required to be in their
session room 30 minutes prior to the start of their sessions. No speakers’ breakfast will be served.

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Maui, Hawai’i

1/6/201915 January

TuesdayDay

FINAL PROGRAM
5:30pm

6:30pmWebsite Administration Subcommittee

Kula

Start

End

Function

Room

8am

2pm

Registration

8am

12pm

Session 9: Orbital debris and space environment

Kapalua

8am

12pm

Session 10: Orbital dynamics, perturbations, andstability II

Napili

8am

12pm

Session 11: Atmospheric re-entry & Satellite
constellations

Kula

8am

12pm

Session 12: Trajectory Design & Optimization III

Hana

10am

10:20amMorning BreakNoon

1:30pmAIAA Technical Committee Lunch

Coral Reef

1:30pm

4:30pmSession 13: Large space structures and tethers

Kapalua

1:30pm

4:30pmSession 14: Dynamical systems theory

Napili

1:30pm

4:30pmSession 15: Mars InSight (Special session)

Kula

1:30pm

4:30pmSession 16: Mars sample return (Special session)Hana

3:10pm

3:30pmAfternoon Break

5:15pm8:15pmOffsite Event: Old Lahina Luau

Page 316 January

WednesdayBuses depart the Sheraton Maui at 5:00pm
8am

2pm

Registration

8am

12pm

Session 17: SSA & Conjunction analysis

Kapalua

8am

12pm

Session 18: Asteroid and non-Earth orbiting
missions II

Napili

8am

12pm

Session 19: Proximity missions, and formation
flying I

Kula

8am

12pm

Session 20: Trajectory Design & Optimization IV

Hana

10am

10:20amMorning Break

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Maui, Hawai’i16 January
17 January

ThursdayWednesday

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FINAL PROGRAM
Noon

1:30pmAAS Technical Committee Lunch

Coral Reef

1:30pm

5:30pmSession 21: SSA & Flight dynamics operations

Kapalua

1:30pm

5:30pmSession 22: Guidance, navigation and control I

Napili

1:30pm

5:30pmSession 23: Proximity missions and formation flying KulaII

1:30pm

5:30pmSession 24: Trajectory Design & Optimization V

3:30pm

3:50pmAfternoon Break

6:00pm

9:00pmAwards Reception

8am

10am

Registration

8am

12pm

Session 25: Spacecraft guidance, navigation andcontrol II

Kapalua

8am

12pm

Session 26: Astrodynamics

Napili

8am

12pm

Session 27: Proximity missions and formation flying Kula
III

8am

12pm

Session 28: Trajectory Design & Optimization VI

10am

10:20amMorning Break

Hana

Ocean Lawn

Hana

A map of the Sheraton Maui Resort and Spa and the relevant meeting rooms appears on the next page.

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29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Maui, Hawai’i

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SPECIAL EVENTSEARLY BIRD RECEPTION
Sunday, 13 January

6:00 – 9:00 pm

Location:

Anuenue Lawn

AWARDS RECEPTION
Wednesday, 16 January

6:00 – 9:00 pm

Location:

Ocean Lawn

Presentation of the 2018 AIAA/AAS Space-Flight Mechanics Meeting Best Paper Award to:
Costantinos Zagaris and Marcello Romano, for paper “Applied Reachability Analysis for Spacecraft
Rendezvous and Docking with a Tumbling Object”
Presentation of the 2019 Space-Flight Mechanics Breakwell Student Travel Award to:
Ahmed Atallah, San Diego State University, for paper “Analytical Radial Adaptive Method for Spherical
Harmonics Gravity Models”
Francisco Franquiz, Embry Riddle University, for paper “Optimal Range Observability Maneuvers for
Angles-Only Navigation in Elliptic Orbits”
Lauren Schlenker, Massachusetts Institute of Technology, for paper “Simultaneous Localization and Mapping
for Satellite Rendezvous and Proximity Operations Using Random Finite Sets”
Justin Mansell, Purdue University, for paper “Swarm Optimization of Lunar Transfers from Earth Orbit with
Radiation Dose Constraints”

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OLD LAHINA LUAU – TRADITIONAL HULA & FEAST
Tuesday, 15 January

5:00 pm (Buses Depart Sheraton Maui Resort for Old Lahina Luau)
5:15 – 8:15 pm (Dinner and Entertainment)

Location

Old Lahina Luau Grounds

The Old Lahaina Lu’au takes great pride in presenting an authentic Hawaiian Lu’au. An evening of traditional
Hawaiian cuisine, music, cultural dances and demonstrations. Guests will appreciate a genuine reflection of
Hawaii’s rich history while enjoying an ocean view and sunset.
Currently we have half of the luau grounds reserved and can accommodate the first 279 guests that register
and/or purchase a guest ticket. Both full and reduced registrants will receive a luau ticket until our reserved
block is full. After that, the General Chairs (GCs) will work with the luau upon space availability toaccommodate additional attendees. The Old Lahaina Luau is famous and known to sell out. The sooner you
register the more likely we can accommodate additional guests. Guest tickets are $120 and sales of guest
tickets will be discontinued after we reach our maximum attendance.
The Old Lahaina Luau menu is included in this program (subject to change) and the Ingredients List can befound in the conference website. All ingredients for menu items are listed. If you feel that there are not menu
options available to you for dietary reasons, please let the GCs know and we will do our best to accommodateyou.

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Luau Menu

Pua’a Kalua Pork roasted in our beachside Imu; the Hawaiian underground oven
Laulau – Lu’au leaf wrapped pork Succulent bundles of pork wrapped in taro leaf and cooked until tender.
I’a - Maui Style Fish Chef’s Special Preparation with fresh seasonal ingredients
Pipi Ko’ala Grilled Beef Steak
Chicken Long Rice Shredded Chicken, Maui onions, ginger and rice bean noodles in broth
Moa – Island Style Chicken Chicken marinated with guava sauce garnished with fresh pineapples andtoasted sesame seeds
Mea’ai Ola Pono Taro, Sweet Potato, and Tofu Patty served with a side of Pineapple Salsa and Garlic Chili
Vinaigrette (Vegetarian / Vegan / Gluten Free)
Stir Fry Vegetables Zucchini, Maui onions, carrots, broccoli, and sugar snap peas
Local-Style Fried Rice Fried rice with green onions, peas, and sesame oil‘Uala - Sweet Potato Warm sliced Big Island sweet potatoes
Island Crab Salad Crab, shrimp and water chestnuts
Lu’au Kalo – Taro Leaf Stew Taro and Lu’au leaf combined with creamy coconut milk for an authentic
island favorite.
Pohole Salad Fern shoots, Maui onions and tomatoes served in a vinaigrette sauce
LomiLomi Salmon Local tomatoes, Maui onions, and salted salmon – Lomilomi or “massaged” together
with Aloha
Poke ‘Ahi Fresh raw ahi (yellow fin tuna) with green onions and Maui onions
Poke He’e Marinated cooked octopus/tako
Poi Made from boiling and mashing the root of the taro plant
Fresh Island Fruit & Banana Bread Fresh seasonal fruits and banana bread
Assorted Island Desserts Passion Fruit Cake, Upcountry Lavender Lemon Shortbread Cookies, Hawaiian
Chocolate Chili Pepper Brownie, and Haupia
Open Bar

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CONFERENCE LOCATIONSHERATON MAUI RESORT AND SPA
2605 Kaanapali Parkway
Lahaina, Maui, HI, 96761
808-661-0031 (voice)888-627-8114 (toll-free)

A room block with the Government Per Diem Rate (currently $259/night) was secured and available for
conference attendees until soldout. We encourage all conference attendees to make your hotel reservation
early!
Group Reservation Page:
https://www.marriott.com/event-reservations/reservationlink.mi?id=1808157216&key=36F014CA&app=resvlink
A deposit equal to two (2) nights is required to hold each guest's reservation. Deposits are refundable if notice
is received by Hotel at least thirty (30) days prior to arrival and a cancellation number is obtained. An early
departure charge of one (1) night room plus tax will apply if a Customer attendee checks out prior to theconfirmed checkout date.
All rates quoted are single or double occupancy. The current rate for a third person in the room is $80.00, plus
tax per night. Children seventeen (17) years of age and younger are free of charge when sharing the sameroom as parent(s), maximum of four (4) persons to a room. Third person charge subject to change.

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Rates do not include applicable state and local taxes, currently 13.4166% or the mandatory Resort Charge of$20.00 plus tax of 4.166% per day, per room (Originally at $25.00) No automatic or mandatory charges aretips, gratuities, or services charges for employees, unless otherwise expressly stated. Resort charge, taxes andresort charge inclusions are subject to change.
Dally Resort Charge Service Inclusions (inclusions subject to change without notice):•

Unlimited wireless high-speed internet access in guest rooms•

Unlimited wireless high-speed internet access in lobby, pool bars, and Hoku Rotunda•

Valet parking on the day of arrival (first night only)•

Unlimited local telephone calls (on-island)•

Credit card and 800# access telephone calls up to 60 minutes•

Starwood Maui scheduled shuttle service to Westin Maui Resort and Spa, Westin Ka'anapali Ocean
Resort Villas, and historic Lahaina town•

Adult Pool Floats•

Professional resort photo session and keepsake 4 x 8 photo•

Signature logo Hawaiian tote bag

Daily self-parking charge, starting on the 2nd night, will be $20.00 plus tax with arrival night complimentary
valet parking included in the daily resort charge.

HOTEL SERVICES AND AMENITIES
Located on 23 lush oceanfront acres at legendary Pu‘u Keka‘a on Ka‘anapali Beach, Sheraton Maui Resort &Spa invites travelers to experience adventure, romance and family fun on the island of Maui. Relax at theresort’s 142-yard lagoon style pool, taste fresh island cuisine, learn indigenous Hawaiian cultural activities
and play at the white sandy beach. Eighty-three percent of the resort’s 508 rooms and suites feature
breathtaking views of the Pacific, and sister islands Lanai and Molokai. At sunset, the resort showcases its
iconic cliff dive ceremony, a tradition since the resort first opened in 1963. Make lasting memories as you
unwind during sunset, snorkel with tropical fish and honu (green sea turtles), learn ukulele with family, or
rejuvenate at The Spa at Black Rock.
Hotel Dining Options
ROCKsalt (INTERNATIONAL) Craveable, eclectic share plates with a global flair. For more information,
check us out on Instagram @rocksaltmaui! Open for breakfast and dinner Phone: +1 808-921-4600
Mai Tai Bar (AMERICAN) Located steps away from of Kaanapali Beach, Mai Tai Bar is an ideal setting forsipping on your favorite umbrella drink and savoring tasty poolside bites. Open for lunch and dinner
Teppan-yaki Dan (JAPANESE) At Teppan-yaki Dan, skilled chefs expertly prepare fresh lobster, steak, andmore, right before your eyes. Sakes and fine wines are the perfect complement. Reservations required, open
for dinner.
Cliff Dive Grill (AMERICAN) This open-air hot spot serves tasty grilled fare plus a range of tempting
beverages, right on Kaanapali Beach. Take in the nightly torch lighting and cliff dive ceremony, and enjoy
hula dancing and live music. Open for lunch and dinner
Hank's Haute Dogs (AMERICAN) Inventive hot dogs, French fries and dips served poolside. Open for lunch

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OTHER HOTEL OPTIONS
Although conference rates cannot be guaranteed, suggestions for other hotel options in the area are listed
below. Further information is available on VRBO and Airbnb.
•
•
•
•
•
•
•
•

The Westin Maui Resort and Spa
Kaanapali Alii Resort
Hyatt Regency Maui Resort
Royal Lahaina Resort
Honua Kai Resort and Spa
The Westin Kaanapali Ocean Resort Villas
The Ritz-Carlton Kapalua
Marriott's Maui Ocean Club Lahaina

TRANSPORTATION INFO
All flights to the conference should arrive at Kahului Airport (OGG). http://airports.hawaii.gov/ogg/
Hawaii has strict import/export rules for fresh food products, animals, meats, and plants. Please follow thefollowing directions for travel to Hawaii:
US Mainland to Hawaii:
http://hdoa.hawaii.gov/pi/pq/travel-shipping-information/traveling-from-the-u-s-mainland-tohawai%CA%BBi/
International Travel to Hawaii:
http://hdoa.hawaii.gov/pi/pq/travel-shipping-information/traveling-to-and-from-foreign-countries/

Several car rental companies are available at OGG. Alternatively, the following services are available:
Airport shuttle service via Roberts Hawaii, $34 each way or $68 round trip (plus tax and possible baggagefees). The booking link is: Http://www.robertshawaii.com/mauiexpress Reservations: 808-439-8800
Mercedes shuttles between OGG and the Sheraton Maui via SpeediShuttle, $35.40 one way, $67.26 round trip
(10% discount on return when booked together) and includes airport greeter service. Registrants withprearranged arrival reservations will be greeted in the baggage claim area then directed to their waiting
shuttles. Vehicle amenities include complimentary WiFi, 6’1” clearance, three point seat restraints.
www.speedishuttle.com Phone: 808-268-2094

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MAUI WEATHER
For more information on Maui weather, go here: https://www.mauiinformationguide.com/hawaii-weather.php

December, January, February
These months have the lowest temperatures for the year. Keep in mind that it's still plenty warm in many
areas. With regular showers, these winter months are home to the wettest Maui weather of the year. In
January, tradewinds only blow half as much as they do in the summer. Throughout the winter, generally from
November to March, large North Swells create big surf on our North and Northwest facing beaches. The
ocean temperature is approximately 75 F, and the air temperature averages between 65-80 degrees F
depending on which area you're in. For Ka'anapali, the average temperature is closer to a high of 79 degrees F
during the day and overnight lows of 64 degrees F with about 6 rainy days per month on average.

Maui Weather Cycle

From the crater at Haleakala's summit, you can watch Maui weather being made. On a typically warm day,trade winds carry moisture-laden air up the northeast slopes of Haleakala. As the moisture rises, it cools andcondenses into the cloud layer that frequently rings the mountain. Rising warm air often pushes the clouds up
through Ko'olau Gap and Kaupo Gap. As the evening air colls, the clouds drain out of the valley and the cycle
begins again. Haleakala influences weather all around the volcano. Average annual rainfall varies from about
400 inches (1,000m) in the high-elevation rain forest above Hana to 10 inches (25 cm) in Kihei, only about 15
minutes apart. Because temperatures drop about 3.2F (1.3C) every 1,000 feet (305m), the summit of
Haleakala is roughly 32F (13C) cooler than the beaches.

BUSINESS LUNCH OPTIONS WITHIN FIVE MILES
Hula Grill Kaanapali$$ American (New), Hawaiian, Seafood
2435 Kaanapali Pkwy
Lahaina, HI(808) 667-6636
Leilani’s$$ Seafood, American (New), Hawaiian
2435 Kaanapali Pkwy
Lahaina, HI(808) 661-4495
Monkeypod Kitchen$$ American (New), Cocktail Bars, Hawaiian
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2435 Kaanapali Pkwy
Lahaina, HI(808) 878-6763
Teppanyaki 2 Go By 808 Afternoons$$ Teppanyaki, Food Trucks, Seafood(808) 866-4025
Java Jazz & Soup Nutz$$ Coffee & Tea, Breakfast & Brunch, American (New)3350 Lower Honoapiilani Rd
Lahaina, HI(808) 667-0787
C J’s Deli & Diner$$ Delis, Breakfast & Brunch
2580 Kekaa Dr
Lahaina, HI(808) 667-0968
Relish Burger Bistro$$ American (New), Breakfast & Brunch, Burgers
2365 Ka'anapali Pkwy
Lahaina, HI(808) 667-2525
The Fish Market Maui$$ Seafood, Hawaiian
3600 Lower Honoapiilani Rd
Lahaina, HI(808) 665-9895
Ka’anapali Grille and Tap Room$$ American (Traditional), Breweries
100 Nohea Kai Dr
Lahaina, HI(808) 667-7733
Cafe Roseanne$ Coffee & Tea, Shaved Ice, Breakfast & Brunch
2661 Kekaa Dr
Lahaina, HI(808) 667-4215
Nikki’s Pizza$ Pizza, Italian
2435 Kaanapali Pkwy
Lahaina, HI(808) 667-0333
Roy’s Kaanapali
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FINAL PROGRAM$$$ Hawaiian, Asian Fusion, Seafood
2290 Kaanapali Pkwy
Lahaina, HI(808) 669-6999
Castaway Cafe$$ American (Traditional), Diners, Breakfast & Brunch
45 Kai Ala Dr
Lahaina, HI(808) 661-9091
Duke’s Beach House$$ Breakfast & Brunch, Hawaiian
130 Kai Malina Pkwy
Lahaina, HI(808) 662-2900
Pizza Paradiso Mediterranean Grill$$ Mediterranean, Middle Eastern, Greek
3350 Lower Honoapiilani Rd
Lahaina, HI(808) 667-2929
Slappy Cakes$$ Breakfast & Brunch
3350 Honoapiilani Rd
Lahaina, HI(808) 419-6600
L&L Hawaiian BBQ Honokowai$ Hawaiian, Barbeque, Seafood
3350 Lower Honoapiilani Rd
Lahaina, HI(808) 667-7788

ADDITIONAL INFORMATIONSPEAKER ORIENTATION
Authors should have submitted a brief (approximately 50 words or 3 sentences) speaker’s bio with theirabstract submission. Author presentations (preferably in PDF format) will be submitted through a web-based
system and are due by Friday January 11th, 2019, 23:59:59 Eastern Time. Authors are required to be in
their session room 30 minutes prior to the start of their sessions. No speakers’ breakfast will be served.
Authors are reminded that the deadline to upload pre-prints to the https://www.xcdsystem.com/aas/ website is
before Friday January 4th, 2019, 23:59:59 Eastern Time.

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FINAL PROGRAMVOLUNTEERS
Volunteers that would like to staff the registration table may sign up at the registration table.

PRESENTATIONSEach presentation is limited to 15 minutes. An additional five minutes is allotted between presentations foraudience participation and transition. Session chairs shall maintain the posted schedule to allow attendees theoption of joining a parallel session. Each room is equipped with a laser pointer, an electrical outlet, and avideo projector that can be driven by a computer. Presenters shall coordinate with their Session Chairs
regarding the computing equipment, software, and media requirements for the session; however, eachpresenter is ultimately responsible for having the necessary computer and software available to drive thepresentation. Microsoft PowerPoint and PDF are the most common formats.
"No-Paper, No-Podium" Policy Completed manuscripts shall be electronically uploaded to the submission
site before the conference, limited to 20 pages in length, and conform to the AAS conference paper format. If
the completed manuscript is not contributed on time, it will not be presented at the conference. If there is noconference presentation by an author, the contributed manuscript shall be withdrawn.
Each author is also acknowledges that he or she is releasing technical information to the general public andthat respective papers and presentations have been cleared for public release. If any author of a paper is a US
person (citizen or permanent resident), he or she acknowledges that the release of these data and content of
the paper and presentation conforms to ITAR and are not on the USML. The information contained in these
documents is neither classified, SBU, FOUO, nor proprietary to any sponsoring organization.

PREPRINTED MANUSCRIPTS
Physical copies of preprinted manuscripts are no longer available or required for the Space Flight Mechanics
Meetings or the Astrodynamics Specialist Conferences. Electronic preprints are available for download atleast 72 hours before the conference at https://www.xcdsystem.com/aas/ for registrants who use the online
registration system. The hotel provides conference guests with complimentary wireless internet access inguest rooms and the conference meeting space. Registrants without an internet-capable portable computer, or
those desiring traditional paper copies should download and print preprint manuscripts before arriving at theconference.

CONFERENCE PROCEEDINGSAll full registrants will receive a CD of the proceedings mailed to them after the conference (extra copies areavailable for $60 during the conference). However, the hardbound volume of Advances in the Astronautical
Sciences covering this conference will be available to attendees at a reduced pre-publication cost, if ordered at
the registration desk. After the conference, the hardbound proceedings will more than double in price,although authors will still receive a special 50% discount off the post-conference rate even if they delay theirorder until after the conference. Cost of Proceedings:
ØØØConference Rate
$290 domestic ($380 international)
Post-Conference Rate
$600 (approx.)
Authors (post-conference) $300 (approx.)

Although the availability of hardcopy proceedings enhances the longevity of your work and elevates theimportance of your conference contribution, please note that conference proceedings are not considered anPage 15

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archival publication. Authors are encouraged to submit their manuscripts after the meeting to one of therelevant journals, such as:
Journal of the Astronautical Sciences
Editor-in-Chief: Dr. Kathleen C. Howell, Purdue University
Manuscripts can be submitted via: https://www.editorialmanager.com/jass
Journal of Guidance, Control and Dynamics
Editor-in-Chief: Dr. Ping Lu, San Diego State University
Manuscripts can be submitted via: https://mc.manuscriptcentral.com/aiaa
Journal of Spacecraft and Rockets
Editor-in-Chief: Dr. Hanspeter Schaub, University of Colorado Boulder
Manuscripts can be submitted via: https://mc.manuscriptcentral.com/aiaa

SATISFACTION SURVEY
Registrants are highly encouraged to record their level of satisfaction and conference preferences in ananonymous survey taken throughout the time of the conference. Please return the survey form given to you
when you check in at the registration table to the registration table before departing from the conference.

COMMITTEE MEETINGS
Committee seating is limited to committee members and invited guests. Committee and subcommittee
meetings will be held according to the schedule at the beginning of the program.

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Conference Technical Session Schedule
Last Update: 6 January 2019
The most up-to-date full schedule is at https://www.xcdsystem.com/aas/program/zKjDgfX/index.cfm

Monday, January 14
Session 1: Orbit Determination & Space-Surveillance Tracking
Monday, Kapulua
Chair: Brandon Jones, University of Texas at Austin
8:00

AAS Analyzing Feasibility of Optical Communication Observables for Navigation
19-220 Sarah Elizabeth McCandless, Jet Propulsion Laboratory; Tomas Martin-Mur, NASA/JPL;
Reza Karimi
Future deep-space missions are intending to utilize optical communications and thereby takeadvantage of superior data delivery rates. The same laser-based links could also be used forinterplanetary navigation. Two main optical tracking types could be used for this purpose: opticalranging and optical astrometry. These data types offer similar capabilities to the radiometrictechniques currently used. This paper discusses the formulation of the data types and their success inmeeting mission requirements for a variety of mission scenarios.

8:20

AAS Navigation Accuracy at Jupiter and Saturn using Optical Observations of Planetary
19-231 Satellites
Nicholas Bradley, CalTech / Jet Propulsion Laboratory; Shyam Bhaskaran, Jet Propulsion
Laboratory; Zubin Olikara, NASA Jet Propulsion Laboratory; Stephen Broschart, NASA /Caltech JPL
Optical-based deep-space autonomous navigation (AutoNav) on board a spacecraft has the potential
to significantly reduce reliance on ground-based assets for navigation purposes. Continuing an
investigation of AutoNav across the solar system, we assess optical-only navigation performance forJuno and Europa Clipper at Jupiter, and Cassini at Saturn, using simulated optical observations of
natural satellites. We show that the use of AutoNav at these planets is feasible within current
technological capabilities. Spacecraft position uncertainty can be as low as single kilometers, andstatistical fuel allocation for injection and maneuvers can be quite low, depending on camera
specifications.

8:40

AAS ORBIT DETERMINATION SENSITIVITY ANALYSIS FOR THE EUROPA
19-271 CLIPPER MISSION TOUR
Zahi Tarzi, Jet Propulsion Laboratory; Sumita Nandi, NASA / Caltech JPL; Dylan Boone,
NASA / Caltech JPL; Brian Young, Jet Propulsion Laboratory, California Institute ofTechnology.
The Europa Clipper mission will orbit Jupiter and investigate Europa’s habitability utilizing a set offive remote sensing and five in-situ instruments. The tour phase of the current mission plan consistsof forty-six low altitude Europa science flybys. Sufficiently accurate predicted and reconstructed
spacecraft orbit determination (OD) is needed to support spacecraft pointing, measurement planningand interpretation of measurements. After briefly discussing expected OD capability, this paper will

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assess the sensitivity of OD delivery and knowledge performance for the current Europa Mission
trajectory through parametric variation of a baseline tour navigation strategy.

9:00

AAS RECURSIVE POLYNOMIAL MINIMUM MEAN SQUARE ERROR ESTIMATION
19-445 WITH APPLICATIONS TO ORBIT DETERMINATION
Simone Servadio, University of Texas at Austin; Renato Zanetti, University of Texas atAustinThis paper presents a systematic generalization of the linear update structure associated withthe extended Kalman filtering for high order polynomial estimation of nonlinear dynamicalsystems. A minimum variance criterion is used as a cost functional to determine theoptimal gains required for the estimation process. The high order series representation is
implemented effectively using Differential Algebra techniques.

9:20

AAS INDENTIFYING SPACECRAFT CONFIGURATION USING DEEP NEURAL
19-518 NETWORKS FOR PRECISE ORBIT ESTIMATION
Madhur Tiwari, Embry-Riddle Aeronautical University; David Zuehlke, Embry-Riddle
Aeronautical University; Troy Henderson, Embry-Riddle Aeronautical University
This paper proposes a method for classifying the configuration of a satellite using semantic
segmentation in Deep Neural Networks. A semantic segmentation network is created and trainedusing MATLAB’s Neural Net Toolbox based on upsampling and downsampling. The resulting
network identifies features of a satellite (Panel and Bus). Images are taken with a ground based
telescope, processed, then segmented before applying angles-only orbit determination (AIOD)
methods with covariance. AIOD results with covariance are analyzed for centroid data of a full
extended object vs. a feature of interest (i.e. central Bus). Results are shown for passes of theInternational Space Station.

10:00

Morning Break

10:20

AAS GEOSTATIONARY SATELLITE ORBIT ACCURACY ANALYSIS FOR
19-507 MANEVEUR EFFICIENCY CALIBRATION
Yoola Hwang, ETRI; Byoung-Sun Lee, ETRI
Geostationary satellite keeps the position within the control box in order to conduct its missions. As
geostationary satellites increase, the control box is restricted into small area. Thus the position
evaluation for the maneuver becomes important factor for the next operation. In this research, we
analyze the orbit determination (OD) uncertainty using covariance propagation and measurement
residuals for the maneuver efficiency calibration. Both covariance error and measurement
residuals depend on measurements noises. The maneuver efficiency is calibrated from the the delta
velocityof the principal axis between the thruster telemetry information and the estimated OD.

10:40

AAS Extended Kalman Filtering in Regularized Coordinates for Orbit Determination
19-513 David Ciliberto, Pennsylvania State University; Puneet Singla, Pennsylvania State
University; Manoranjan Majji, Texas A&M University, College Station

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The linear error theory used in our previous work developing an extended Kalman filter (EKF)
formulation in Burdet regularized coordinates is applied to the Kustaanheimo-Stiefel (KS)regularization for the purpose of estimating the unperturbed two-body motion of Earth-orbiting
satellites. Challenges encountered in the development of the Burdet EKF, including the addition oferror associated with the discrepancy between the regularized independent variable and time-tagged
measurement data, are addressed. Similar strategies for dealing with these challenges are applied tothe development of the KS EKF. Simulated orbit determination is conducted in the two regularized
spaces and using a traditional Cartesian EKF.

11:00

AAS INITIAL RELATIVE ORBIT DETERMINATION SOLUTIONS USING
19-515 POLYNOMIAL SYSTEMS
Troy Henderson, Embry-Riddle Aeronautical University; Alex Sizemore, NRC; David
Zuehlke, Embry-Riddle Aeronautical University; Kenneth Horneman, Emergent SpaceTechnologies, Inc.; Alan Lovell, Air Force Research Laboratory
This paper presents a solution method for the initial relative orbit determination
problem using a system of polynomials as measurement equations derived fromthe line-of-sight measurement problem. The measurements equations are cast as aset of six quadratic polynomials with the six initial conditions as variables. Solving
for the roots of the polynomial equations is performed using three methods. Improved
conditioning, through variable and equation
scaling, is shown to increase
the likelihood of finding correct solutions.

Session 2: Orbital Dynamics, Perturbations, and Stability I
Monday, Napili
Chair: Richard Linares, Massachusetts Institute of Technology
8:00

AAS Stability and Targeting in Dawn's Final Orbit
19-254 Daniel Grebow, NASA / Caltech JPL; Nicholas Bradley, Jet Propulsion Laboratory; Brian
Kennedy, Jet Propulsion Laboratory
The Dawn spacecraft conducted two extended missions at Ceres following the completion of the
primary mission in June 2016. The final orbit of the second extended mission was designed to havea 35-km periapsis altitude for 10x higher-resolution science. The mission ends in this orbit when
the spacecraft runs out of attitude control propellant. In this paper, we describe the final orbit anddiscuss the challenges of flying this low at Ceres. We also include our stability analysis showing
the spacecraft will remain in orbit for more than 20 years, as stipulated by the Planetary Protection
requirements.

8:20

AAS Design and Control of Repeat Ground Track Orbit in High Fidelity Dynamical Model
19-270 via High Order Poincaré Mapping
Roberto Armellin, University of Surrey; Yanchao He; Ming Xu, Beihang University
The aim of this work is to introduce a new semi-analytical technique for both the design and controlof repeat ground-track (RGT) orbit in a high fidelity dynamical model, including non conservative
forces and highly accurate Earth orientation parameters. The idea is based on the use of high-order
expansion of Poincaré maps to propagate regions of the phase space forward in time for one, orPage 1929th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

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more, repeating cycles. This tool provides the means to efficiently study the effect that a Δv appliedat the Poincaré crossing produces on the ground-track pattern, thus enabling highly accurate designand control.

8:40

AAS Capture an asteroid to the Earth-Moon system via triangular libration points
19-277 Yuying Liang; Jinjun Shan, York University; Ming Xu; Shijie Xu
This paper is devoted to the development of a new capture strategy via triangular libration
points. First, the entire family of long- and short-period stable orbits at the triangular libration points
will be obtained numerically by continuation. The transfer segments connecting parabolic orbits andparking orbits will then constructed by the stable manifolds of the unstable periodic orbits of L4/5,
while the parking orbits are chosen from the stable members by hyper-Poincaré sections. To
quantify the propellant cost and time of flight under such a control strategy, an interpolation
algorithm will be implemented to provide a global view of these two key indicators. Finally,
the sample capture trajectories using impulsive thrust

9:00

AAS DROMO propagator for highly perturbed problems
19-310 Virginia Raposo-Pulido; Hodei Urrutxua, Universidad Rey Juan Carlos; Jesus Pelaez,
Technical University of Madrid (UPM)
DROMO is an orbital propagator developed in 2000 by the Space Dynamics Group at the Technical
University of Madrid. This special perturbation method is characterized by eight ODE's. A new
extension of DROMO for highly perturbed problems has been developed by introducing a new sets
of variables. The formulation proposed is compared with the schemes proposed by Cowell,
Kustaanheimo-Stiefel (KS) and Palacios et al. 1996 in double and quadruple precision. The results
confirm the stability and reliability of the new formulation, showing a significant improvement withrespect to the classic version of DROMO when the perturbation is close to unity.

9:20

AAS Dedicated Mission to the Sun-Earth Saddle Point: A Feasibility Assessment
19-322 Carmine Giordano, Politecnico di Milano; Francesco Topputo, Politecnico di Milano;
Christian Trenkel
In this paper, periodic orbits through the Sun–Earth Saddle Point are sought. The periodic orbits
survey is made using a systematic approach, firstly addressing it in the circular restricted three-bodyproblem with the Sun and the Earth as main bodies: first attempt trajectories are sought through agrid search and then refined using a simple shooting, differential correction scheme. Stability isevaluated and a classification is made. Restricted four body problem adding the Moon is used as
middle complexity model in order to find quasi-periodic orbits. These are refined in a full ephemeris
high-fidelity n-body model. Preliminary results show different possible solutions with diverse
characteristics and properties.

10:00

10:20

Page 20Morning BreakAAS Sensitivity Analysis of Regularised Orbit Formulations with Interval Arithmetic
19-328 Hodei Urrutxua, Universidad Rey Juan Carlos; Youssef Souied, Universidad Politécnica de29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

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Madrid; Jesus Pelaez, Technical University of Madrid (UPM)
Regularised formulations provide a highly accurate description of the orbit as a geometric element,
while the dynamical instabilities concentrate in the integration of the physical time. However, inhighly perturbed problems, the geometric variables may also exhibit an important accumulation of
propagation errors, where different formulations display distinctive error build-up patterns. To
understand the error growth in each of the variables, in this paper interval arithmetic is used toperform a sensitivity analysis of the propagation error for various orbital formulations. The study
considers a variety of orbital scenarios and conclusions are drawn based on the performed numericaltests.

10:40

AAS Attitude Dependent Evolution of Orbits about Active Comets
19-375 Mark Moretto, University of Colorado Boulder; Jay McMahon, CCAR (Colorado Center
for Astrodynamics Research)
Spacecraft orbiting active comets are perturbed by gas drag from the coma. These gasses expand
radially at about 0.5 km/s, much faster than orbital velocities that are on the order of meters per
second. The resulting drag accelerations can be similar in magnitude to that of gravity and are thus
important to model. Here we present an orbit averaging analysis of spacecraft motion about anactive comet. The spacecraft will be modeled as a flat plate. This results in out-of-plane forces,
enabling the use of natural dynamics for maneuvering. These dynamics can be leveraged for
mission planning, operations, and science.

11:00

AAS Stability and spin-orbit resonance analysis of low altitude Martian orbits
19-379 Andres Dono, NASA Ames Research Center; Laura Plice, Metis Technology Solutions
The increasing interest in Mars orbiters brings the question of the likelihood of natural decay in low
altitude regimes. This paper studies the change in shape of low altitude Mars orbits by carrying out
large sets of numerical high fidelity simulations. Results showed that various configurations of theorbital elements gave perturbations that re- sulted in unstable orbits. The paper also studies thepotential causes of the observed unstable regions. First by taking a close look at zonal and tesseral
harmonics to find the implications of Mars mass concentrations, and second by computing
theoretical spin-orbit resonances.

Session 3: Attitude Dynamics & Control I
Monday, Kula
Chair: Marcello Romano, Naval Postgraduate School
8:00

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AAS Lunar Reconnaissance Orbiter Operations Without a Gyro
19-202 Julie Halverson, NASA GSFC; Oscar Hsu; Philip Calhoun
The Lunar Reconnaissance Orbiter, launched in 2009, has made groundbreaking discoveries of themoon. Star trackers and a miniature inertial measurement unit (MIMU) estimate attitude and bias inan extended Kalman filter (EKF). The MIMU, powered off in early 2018, is currently only used formomentum unloads; science slews are suspended, and the EKF is disabled. This paper presents acomplementary filter applied to differentiated quaternions and angular acceleration derived from theattitude control torque to estimate a rate to replace the MIMU in the EKF, resulting in minimalflight software changes. Results from simulations and in-flight performance are included.
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8:20

AAS CONFIGURATION OPTIMAZATION OF 0-1 SUN SENSORS FOR SUN VECTOR
19-240 DETERMINATION
Shijie Zhang; Botian Zhou; Shiqiang Wang
Sun vector is vital for the determination of satellite attitude, which can be coarsely estimatedutilizing 0-1 sun sensors. However, the configuration of sun sensors varied from one to another andthere is no standard theory for designing the configuration. Therefore, in this paper, the optimization
model of the configuration of 0-1 sun sensors was first established, where the reliability, cost, andthe precision of sun vector determination were in consideration. Then the configuration was
optimized and the optimized results were presented. Finally, the sun vector determination error andits distribution were analyzed and the robustness was verified.

8:40

AAS Rotations, Transformations, Left Quaternions, Right Quaternions?
19-296 Renato Zanetti, University of Texas at Austin
This paper surveys the two fundamental possible choices in representing the attitude of an aerospacevehicle: active and passive rotations. The consequences of the choice between the two are detailed
for the two most common attitude parameterizations, a three-by-three orthogonal matrix and thequaternion. Successive rotations are also reviewed in this context and the choices as well as theattitude kinematic equations.

9:00

AAS UNCERTAINTY QUANTIFICATION AND ANALYSIS OF INVARIANTS OF
19-368 RIGID BODY ATTITUDE DYNAMICS
Anant Joshi, Indian Institute of Technology, Bombay; Kamesh Subbarao, University ofTexas at Arlington
This paper considers uncertainty quantification in systems perturbed by stochastic disturbances, inparticular, Gaussian white noise. The main focus of this work is on describing the time evolution of
statistical moments of certain invariants (for instance total energy and magnitude of angularmomentum of a spring-mass or mass-pendulum) for such systems. A case study for the attitude
dynamics of a rigid body is presented where it is shown that these techniques offer a closed form
representation of the evolution of the first and second moments of the states of the resulting
stochastic dynamical system.

9:20

AAS Fault Points Detection for Large Solar Panel Based on Photogrammetry
19-399 Hongwen Wang, Beihang University; Rui Zhong; Li Pengjie, Beihang University, Beijing,
China
Modal analysis for a large solar panel is performed in this paper and a combined method of opticalmeasuring points is designed with modal information. When the model is excited by pulse input,
collect vibration displacement information to simulate the results from photogrammetry and add
white noise to responses to correspond with real vision measurement results. When the vibration
information of points is contaminated or one optical point is missing, this paper utilizes PCA todetect fault points with the statistic SPE. This research may help to modify the existing scheme of
optical measuring points and identify modal parameters intelligently.

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Morning Break

10:20

AAS Removing Rate Un-observability in Sun Heading Filters Without Rate Gyros
19-460 Thibaud Teil, University of Colorado, Boulder ; Hanspeter Schaub, University ofColorado; Scott Piggott, Laboratory for Atmospheric and Space Physics
A novel sun-heading filter is derived which estimates only the observable components of the rate
vector. By switching between kinematic formulations, it provides not only better sun-heading
estimates, but also a body rate that can be used for rate validation or control. One of the ratecomponents will always remain unobservable, and therefore must be measured otherwise.
Nevertheless, when using coarse sun sensors alone, this filter provides a minimal, fully observable,
and non-singular state.

10:40

AAS Heading and Angular Velocity Correlation Using Polynomial Chaos
19-473 Christine Schmid; Kyle DeMars, Missouri University of Science and Technology
Polynomial chaos expresses a probability density function (pdf) as a linear combination of basis
polynomials. If the density and basis polynomials are over the same field, any set of basis
polynomials can describe the pdf; however, the most logical choice of polynomials is the family thatis orthogonal with respect to the pdf. This problem is well-studied over the field of real numbers,
and has been shown to be valid for the complex unit circle in one dimension. The current framework
for circular polynomial chaos is extended to multiple angular dimensions with the inclusion ofcorrelation terms.

11:00

AAS Control of an Earth-Based Satellite Test Platform through Vision Based Position
19-503 Measurement
Sital Khatiwada, University of New Hampshire Mechanical Engineering; Andrew Masters,
University of New Hampshire; Aaron Cantara, University of New Hampshire MechanicalEngineering; Michael Goulet, University of New Hampshire Computer Science; May-Win
Thein, University of New HampshireIn this paper, the authors propose using multirotor Unmanned Aerial Vehicles (UAVs) as an
economical option of testing and evaluating satellite control processes on an Earth-based platform.
To improve a multi-rotor's capacity to mimic satellites, a robust control scheme is designed andtested to assess its capabilities. An in-house vision system will be fabricated for state monitoring.
The system will be integrated with the multirotor platform and evaluated for its accuracy andprecision. It is expected that numerical and experimental results will provide meaningful qualitative
data, granting insight on methods to improve multirotor capabilities to serve as low-cost spacecraft
testbeds.

11:20

AAS SPACECRAFT RADIATION PRESSURE USING COMPLEX BIDIRECTIONAL
19-531 REFLECTANCE DISTRIBUTION FUNCTIONS ON GRAPHICS PROCESSINGUNIT
Patrick Kenneally; Hanspeter Schaub, University of Colorado
A description of a method for computing on the graphics processing unit the force and torque on a
spacecraft due to solar radiation pressure. The method employs ray-tracing techniques, developed inPage 2329th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

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the graphics rendering discipline, to resolve spacecraft self-shadowing, self-reflections and complex
surface material optical characteristics at faster than real-time computation speed. The primaryalgorithmic components of the ray-tracing process which contribute to the method's computational
efficiency are described. Complex bidirectional reflectance distribution functions (BRDF) models
are described. The modeling approach process is implemented using C++ and OpenCL and executedon a consumer grade graphics processing unit.

11:40

AAS Attitude Control and Orbit Determination of a Crewed Spacecraft With a Lander in
19-545 Near Rectilinear Halo Orbit
Clark Newman, a.i. solutions, Inc.; Diane Davis, a.i. solutions, Inc.; Ryan Whitley, NASA;
Ryan Sieling, CACI NSS, INC.
NASA's Gateway program will place a crew-tended spacecraft in cislunar Near Rectilinear Halo
Orbit (NRHO). The outpost will support crew arrival in the Orion spacecraft and the undocking andreturn of a crewed lunar lander. The impact on Gateway attitude control with the addition of a lunar
lander is investigated. Perturbations from Orion and a lander's docking and undocking to the
Gateway are considered. Deep Space Network (DSN) tracking is supplemented with remote
Gateway measurements to lunar north pole craters to analyze the benefit in solution accuracy and/or
DSN scheduling relief.

Session 4: Trajectory Design & Optimization I
Monday, Hana
Chair: Martin Ozimek, The Johns Hopkins University Applied Physics Laboratory
8:00

AAS INDIRECT OPTIMIZATION OF LOW-THRUST TRAJECTORIES USING
19-201 HOMOTOPY
Bradley Wall, Embry-Riddle Aeronautical University
In this work a homotopic approach is used to start with a simple indirect low-thrust trajectory
solution and alter the boundary conditions slowly until the desired trajectory problem is solved. It isshown that the user can change the inclination, semimajor axis, eccentricity, and true anomaly of thetarget body as well as the transfer time of the trajectory. As previously shown in other works, thethrust acceleration of the spacecraft can then be changed to yield optimal bang-bang control
trajectories.

8:20

AAS Mars 2020 Mission Design and Navigation Overview
19-203 Fernando Abilleira, NASA Jet Propulsion Laboratory/Caltech; Seth Aaron, NASA Jet
Propulsion Laboratory/Caltech; Chuck Baker, NASA Jet Propulsion Laboratory/Caltech;
P. Daniel Burkhart, NASA / Caltech JPL; Gerhard Kruizinga, NASA / Caltech JPL; Julie
Kangas, JPL; Mark Jesick, Jet Propulsion Laboratory; Robert Lange, NASA Jet Propulsion
Laboratory/Caltech; Sarah Elizabeth McCandless, Jet Propulsion Laboratory; Mark Ryne,
NASA / Caltech JPL; Jill Seubert, NASA / Caltech JPL; Sean Wagner, Jet Propulsion
Laboratory; Mau C. Wong, JPL
Following the exceptionally successful Mars Science Laboratory mission which placed the Curiosity
rover in the interior of Gale Crater in August 2012, NASA will launch the next rover in the 2020
Earth to Mars opportunity arriving to the Red Planet in February 2021 to explore areas suspected ofPage 2429th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

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former habitability and look for evidence of past life. This paper details the mission and navigation
requirements set by the Project and how the final mission design and navigation plan satisfy thoserequirements.

8:40

AAS AL YAH 3 ORBIT TRANSFER RECOVERY DESIGN
19-206 Chris Ranieri, The Aerospace Corporation; Marc DiPrinzio, The Aerospace Corporation;Peter Edelman, The Aerospace Corporation; Gregory Fruth, Aerospace Corporation; Jose
Guzman, The Aerospace Corporation; James Gearhart, Northrop Grumman Innovation
Services; John Hartmann; Rosemary Huang, The Aerospace Corporation; Demyan
Lantukh, The Aerospace Corporation; Robert Markin
After an Ariane 5 ECA launch anomaly, the Al Yah 3 spacecraft required significantly more fuel toreach its desired GEO mission orbit slot. Northrop Grumman Innovation Systems and The
Aerospace Corporation partnered to design an orbit transfer recovery sequence that maximized theachievable mission life. Using specialized trajectory optimization tools, a recovery sequence wasfound that maximized the performance of three different propulsion systems. The use of a tool to
optimize the end-to-end transfer was critical and will be highlighted with comparisons to recovery
options designed using experience and intuition. A mission life of >8 years was salvaged.

9:00

AAS Hybrid Transportation System Integrated Trajectory Design and Optimization for
19-226 Mars Landing Site Accessibility
Patrick Chai, NASA Langley Research Center; Min Qu, AMA; Raymond Merrill, NASA
Langley Research Center; Kaila Pfrang, Massachusetts Institute of Technology
This paper demonstrates the capability of the new integrated trajectory design and optimization
method as it applies to the landing site accessibility problem for the Hybrid transportationarchitecture. A full system level analysis shows the limitations of the current basis of comparison
designed vehicle in reaching higher latitudes. Sensitivity of the system mass to increased landingsite accessibility across the full Earth-Mars synodic cycle is presented to show the additional
performance requirements on the system given the current constraint of system power.

9:20

AAS Optimization of Variable-Specific-Impulse Gravity-Assist Trajectories
19-236 Zhemin Chi, Politecnico di Milano; Di Wu, Tsinghua University; Fanghua Jiang; Junfeng
Li
This paper presents a series of optimization methods for finding fuel-optimal gravity-assist
trajectories that utilize the practical solar electric propulsion with variable specific impulse. An
optimization method combining the particle swarm optimization and the indirect method is
proposed to optimize the variable-specific-impulse gravity-assist low-thrust trajectories.
Additionally, the modified logarithmic homotopy function is applied to serve as a gateway invariable-specific-impulse case. The algorithm for optimization multiple-gravity-assist trajectories isalso presented in this paper. Moreover, the experimental data of NASA’s Evolutionary Xenon
Thruster is employed in numerical simulations. Main-belt asteroids missions are given to
substantiate the feasibility of the proposed methods.

10:00

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10:20

AAS On Alighting Daintily at Jupiter: Innovative Methods for Efficiently Achieving Jovian
19-242 Orbit
Tim McElrath, JPL/Caltech; Stefano Campagnola, Jet Propulsion Laboratory; Anastassios
Petropoulos, NASA / Caltech JPL; Amanda Haapala , Johns Hopkins University Applied
Physics Laboratory; Fazle Siddique, The Johns Hopkins University Applied Physics
Laboratory
Spacecraft bound for Jupiter orbit typically spend the majority of their delta-V in the capture
process. The Galilean satellites provide myriad opportunities to use flybys to assist the capture
process. In addition, the low solar range (compared to the other outer planets) and absence ofsignificant rings add to the option space. Starting with typical single-flyby and Jupiter Orbit
Insertion (JOI) maneuver sequences, the paper will walk through a range of capture options,
including longer post-capture tours, double flybys (and their constraints), combined with solarelectric propulsion (SEP) usage, and concluding with the potential benefits of retrograde orbit
insertion.

10:40

AAS High Performance Interpolation of Chebyshev Ephemerides
19-245 Juan Arrieta, Nabla Zero Labs
We present the design and implementation of a software library used for high-performanceinterpolation of planetary and satellite ephemerides for the important case when such ephemerides
are provided as Chebyshev polynomials. The need for such ephemerides arises when mission
analysts and designers need to rely on ephemerides provided by SPICE (e.g., DE430 and JUP310),
but need to significantly speed up the interpolation stage without sacrificing correctness. Our
implementation relies on the exact same SPICE files but can deliver performance improvement
between 10x and 100x.

11:00

AAS Transfer between planar and three-dimensional Quasi Satellit Orbits in the vicinity of
19-248 Phobos
Elisabet Canalias, CNES; Laurence Lorda; Enne Hekma, Thales Services (for CNES)
The peculiar dynamics of the Mars-Phobos couple results in the lack of keplerian orbits around thismoon. Quasi Satellite Orbits are a type of Mars centered orbits, allowing to orbit Phobos in thesense of formation flying. JAXA's MMX probe intends to fly several different QSO trajectories toaccomplish its scientific objectives in the Phobos proximity face. This paper presents the work
performed at CNES concerning transfers between planar and 3D QSOs, in the frame of thecooperation with JAXA. The transfer strategy developed by the authors is described and applied toparticular cases. A sensitivity analysis with respect to navigation and DV execution errors is alsopresented.

11:20

AAS The Implementation of Maximum Likelihood Estimation in Space Launch System
19-249 Vehicle Design
William Stein, Jacobs Technology/Jacobs ESSCA Group; Anthony Craig; Seth Thompson,
Troy 7; Tamara Statham, Jacobs Space Exploration GroupThe Space Launch System (SLS) uses a Maximum Likelihood Estimation (MLE) process inconjunction with Design of Experiments to develop statistically representative vehicles for the
Block-1 and Block-1B configurations. These vehicles are the used to estimate maximum load

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conditions for simulating stressing cases in other simulations. This paper discusses the MLE
modeling process and how SLS captures manufacturing uncertainty in the launch vehicle design. It
also provides an overview of the differences between Block-1 and Block-1B statisticalrepresentations. This paper also discusses proper DOE grid choice as well as which uncertainties
drive the vehicle design.

11:40

AAS Tube Stochastic Optimal Control For Nonlinear Constrained Trajectory Optimization
19-255 Problems
Naoya Ozaki, ISAS, JAXA; Stefano Campagnola, Jet Propulsion Laboratory; Ryu Funase,
The University of Tokyo
This paper presents a new algorithm to solve stochastic optimal control problems with nonlinear
systems and constraints. The proposed algorithm uses the unscented transform to transcribe astochastic optimal control problem into a deterministic problem, which is then solved by trajectory
optimization methods such as differential dynamic programming. A numerical example that applies the
proposed method to low-thrust trajectory design illustrates that it automatically introduces margins
that improve robustness. Finally, Monte-Carlo simulations are used to evaluate the robustness andoptimality of the solution.

Session 5: Artificial Intelligence in Astrodynamics
Monday, Kapulua
Chair: Roberto Furfaro, The University of Arizona
13:30

AAS An Interactive Reinforcement Learning Approach to Real-Time Optimal Control for
19-304 Celestial Landing Problems
Lin Cheng, Tsinghua University; Fanghua Jiang; Zhenbo Wang, University of Tennessee
An interactive reinforcement learning approach is proposed for real-time optimal control of celestiallanding systems with irregular gravitational attraction, wherein an approximate indirect method withhigh computational efficiency is presented to generate the optimal control instructions for actor
learning, and the trained actor returns good initial guesses to improve the success probability of theindirect method in finding optimal solutions. On this basis, a new control paradigm is developed toachieve the real-time optimal control for the celestial landing. Two examples of fuel-optimal landing
problems respectively to the Moon and Eros are given to substantiate the effectiveness of thesetechniques.

13:50

AAS Actor-Critic Reinforcement Learning Approach to Relative Motion Guidance in Near19-441 Rectilinear Orbit
Andrea Scorsoglio, Politechnico di Milano; Roberto Furfaro, The University of Arizona;
RICHARD LINARES, Massachusetts Institute of Technology; Mauro Massari, Politecnico
di Milano
In this paper, we develop a novel feedback guidance algorithm for docking maneuvers in thecislunar environment. In particular, the aim is to create a guidance algorithm that is lightweight andclosed-loop, suitable for on-board implementation. The problem has been solved starting from thewell know Zero-Effort-Miss/Zero-Effort-Velocity (ZEM/ZEV) feedback algorithm using machinelearning to improve its capabilities and widen its field of applicability.

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14:10

AAS Spacecraft Decision-Making Autonomy using Deep Reinforcement Learning
19-447 Andrew Harris, University of Colorado Boulder; Thibaud Teil, University of Colorado,
Boulder ; Hanspeter Schaub, University of Colorado
The high cost of space mission operations has motivated several space agencies to prioritize thedevelopment of autonomous spacecraft control techniques. Learning agents present one manner inwhich autonomous spacecraft can adapt to changing hardware capabilities, environmental
parameters, or mission objectives while minimizing dependence on ground intervention. This work
considers the frameworks and tools of Deep Reinforcement Learning to address high-level mission
planning and decision-making problems for autonomous spacecraft, under the assumption that subproblems have been addressed through design. Simulated results show that learning agents canimprove science return substantially over baseline policies.

14:30

AAS SPACECRAFT RENDEZVOUS GUIDANCE IN CLUTTERED ENVIRONMENTS
19-462 VIA REINFORCEMENT LEARNING
Jacob Broida, Massachusetts Institute of Technology; RICHARD LINARES, Massachusetts
Institute of Technology
This paper investigates the use of Reinforcement Learning for controlling satellite rendezvous
missions. We implement and evaluate two different reinforcement learning approaches for thisproblem: Proximal Policy Optimization (PPO) and Asynchronous Advantage-Actor Critic (A3C).
Both of these methods use data sampled from repeated simulation to perform gradient descent on aparameterize policy. After sufficient training, we evaluate the performance of A3C and PPO
developed policies and compare against traditional optimal control approaches. Our experimental
results show that these RL approaches achieve comparable results to optimal control methods withminimal computational requirements, as well as prove effective in solving nonlinear problems.

14:50

AAS INVESTIGATION OF DIFFERENT NEURAL NETWORK ARCHITECTURES
19-479 FOR DYNAMIC SYSTEM IDENTIFICATION: APPLICATIONS TO ORBITALMECHANICS
Damien GUEHO, The Pennsylvania State University; Puneet Singla, Pennsylvania State
University; Robert G. Melton, Pennsylvania State University
Previous work investigated the learning capabilities of feed-forward neural networks based on theconservative unperturbed Keplerian two-body problem. It has been found that rich data set
combined with a penalty term in loss function formulation corresponding to violation of constants ofthe motion during the training provide a good accuracy, close to integration tolerances. In this paper,
we considerably improve previous work by considering brand new structures of neuralnetworks such as Residual Neural Networks (ResNet) or Recurrent Neural Network (RNN). We also
implement a new kind of optimizer to take into account hard constraints during the training phase.

15:10

AAS ADAPTIVE CONTROL BY REINFORCEMENT LEARNING FOR SPACECRAFT
19-537 ATTITUDE CONTROL
Mohammad Ramadan, San Diego State University; Ahmad Bani Younes, San Diego State
University
A direct Neural Dynamic Programming (direct NDP) is utilized to develop an adaptive model-freecontroller using Temporal Difference (TD) methods. The Approximate Dynamic Programming

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avoid the so-called curse of dimensionality. A new algorithm is proposed in this paper to thelearning scheme. The proposed algorithm takes the advantage of the properties of the exponentialfunction and its derivatives. From the preliminary results, our approach can provide a good on-line
learning rate for a given dynamical system allowing sufficient time to train both critic and action

15:30

Afternoon Break

15:50

AAS Low-Thrust Optimal Control via Reinforcement Learning
19-560 Daniel Miller, Massachusetts Institute of Technology; RICHARD LINARES, Massachusetts
Institute of Technology
This paper investigates a Reinforcement Learning (RL) based approach for real-time optimal control
applied to the problem of finding solutions to the low-thrust cis-lunar problem. The Proximal Policy
Optimization (PPO) method is used for developing complex policies by training neural network
controllers to solve optimal control problems. Simulation demonstrations are shown which compare
the proposed approach to "open-loop" optimal control methods. These include transfers to and from
Near Rectilinear Halo Orbits, which have been identified as a possible orbit type for NASA’s future
Lunar Orbital Platform-Gateway.

16:10

AAS COLLISION PREDICTION WITHIN A CUBESAT SWARM USING MACHINE
19-566 LEARNING
Patrick Doran; Navid Nakhjiri, California State Polytechnic University Pomona
This paper presents an algorithm of predicting collisions in a swarm of small satellites in orbit. The
paper studies a case of dozen CubeSats in a relaxed-formation flying in low Earth orbits. A machinelearning method based on classification is trained from hundreds of training sets made fromsimulations to predict the collision. The training sets are created from a simulation of the dozen
CubeSats orbiting till a collision or completion of five orbits. The trained algorithm could predict a
collision two orbits before and which satellites are involved.

16:30

AAS TRAINING SET DATA OPTIMIZATION FOR ARTIFICIAL NEURAL
19-573 NETWORKS FOR ORBITAL STATE SPACE TRAJECTORY PREDICTIONS
Zachary Reinke, Western Michigan University
Demand on earth orbiting object surveillance systems is increasing as more equipment is put in toorbit. These systems rely on predictive techniques to periodically track objects. The demand onthese systems may be reduced if object trajectories could be predicted farther into the future. The
goal of this research is to develop techniques to analyze orbital state trajectory data to develop
optimal training data sets used for teaching artificial neural networks (ANN) used for trajectory
predictions. These methods use multi-variable statistics to analyze data energy content providing the
ANN with scaled, information dense, training data.

16:50

AAS Deep neural networks of Optimal Low-Thrust Orbit Raising19-336 Haiyang Li, Politecnico di Milano; Tsinghua University; Francesco Topputo, Politecnico di

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Milano; Hexi Baoyin, Tsinghua University
Geostationary Earth orbit (GEO) satellites are of great significance in the space market. Low-thrust
propulsion has been highly developed in the last decades because it is fuel saving. Therefore, thedesign of GEO satellites is rapidly changing from classic high-thrust propulsion more and more
toward low-thrust propulsion. However, the transfer time will be quite long using low-thrust
propulsion. It will be very expensive if the ground supports the whole orbit raising. Autonomous
orbit raising is necessary. Deep neural networks are trained to learn the optimal control. Results
show that DNNs can be utilized for future low-thrust orbit raising missions

17:10

AAS Fast Estimation of Gravitational Field of Irregular Asteroids Based on Deep Learning
19-397 and Its Applications
Yu Song, Tsinghua University; Lin Cheng, Tsinghua University; Shengping Gong, Tsinghua
University
In this study, a novel approach is proposed to fast estimate the gravitational field of the irregular
asteroid by the deep neural network (DNN), and the related orbital dynamics problems around theasteroid are studied based on the obtained gravitational field. A DNN architecture will beestablished and trained off-line to learn the gravitational field of irregular asteroids, and the gradientestimation of the gravitational field based on the DNN will be derived. Numerical examples are used
to verify the effectiveness of the proposed approach.

Session 6: Asteroid & Non-Earth Orbiting Missions I
Monday, Napili
Chair: Donghoon Kim, Mississippi State University
13:30

AAS Deployment analysis and trajectory reconstruction of MINERVA-II rovers on
19-243 asteroid Ryugu
Stefaan Van Wal, Japan Aerospace Exploration Agency; Yuichi Tsuda, Japan Aerospace
Exploration Agency; Kent Yoshikawa, Japan Aerospace Exploration Agency
In September 2018, the Hayabusa2 asteroid explorer deployed the small MINERVA-II-1A/B rovers
to asteroid Ryugu. They contain small instruments and can hop across the asteroid surface. The
mission geometry restricts all Hayabusa2 descent operations to a narrow region around the asteroid
equator. Given the rovers’ chaotic bouncing dynamics, it was challenging to design theirdeployment while complying with requirements from the other Hayabusa2 operations. We present
the process applied to generate candidates for, and select the final, rover landing site. Using imagery
from Hayabusa2, we attempt to reconstruct the rover trajectory and constrain Ryugu's mechanicalsurface properties.

13:50

AAS Initial Orbit Determination about Small Bodies Using Flash LIDAR and Rigid
19-253 Transform Invariants
Benjamin Bercovici, University of Colorado Boulder, Colorado Center for Astrodynamics
Research (CCAR); Jay McMahon, CCAR (Colorado Center for Astrodynamics Research)
This paper proposes a novel approach based on the registration of 3D point clouds acquired bymeans of a LIDAR instrument to perform initial orbit determination in the vicinity of a small body.
Specifically, the proposed methods provide position, velocity and standard gravitational parameter

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estimates along with their consistent uncertainties. Besides the knowledge of the instrument inertial
pointing, no a-priori information is required for the filter to function. Initial results featuring a pointmass gravity model and normally distributed Iterated Closest Point registration errors demonstrate
the ability of the filter to quickly characterize the spacecraft orbit.

14:10

AAS Multilayer Clustered Sampling Technique (MLCS) for Near-Earth Asteroid Impact
19-260 Hazard Assessment
Javier Roa, NASA / Caltech JPL; Davide Farnocchia
Because of planetary encounters, the motion of near-Earth asteroids is chaotic and small differencesin the initial conditions tend to diverge exponentially. Linear approximations for propagating theorbital uncertainty can lead to inaccurate estimates of the probability of an Earth collision. We
present a novel fully nonlinear strategy for estimating the probability of an asteroid impact using
sequential Monte Carlo layers. The method first explores low-resolution layers to locate potentiallyrelevant regions. Then, we conduct localized searches on deeper layers with higher resolution. The
method retains the accuracy of Monte Carlo sampling while significantly reducing thecomputational cost.

14:30

AAS Science Orbit Design with Frozen Beta angle: Theory and Application to Psyche
19-269 mission
Kenshiro Oguri, University of Colorado Boulder; Gregory Lantoine, NASA / Caltech JPL;
William Hart, NASA / Caltech JPL; Jay McMahon, CCAR (Colorado Center for
Astrodynamics Research)
Beta angle, an angle formed by the sunlight and a spacecraft orbital plane, is an important parameterfor science orbit design at primitive bodies. This angle defines lighting conditions and eclipse
occurrences, and is then used for science observation planning. Investigating evolution of the beta
angle is therefore critical for science orbit design. This paper presents beta frozen solutions under
the J2-perturbed dynamics using the averaged Lagrange Planetary Equations, and extends them toinitially-frozen solutions for more flexible mission design. The analytical work is applied to scienceorbit design of the Psyche mission, a recently selected mission of the NASA's Discovery Program.

14:50

AAS Curvilinear Surface-Based Gravity Model for Evolutionary Trajectory Optimization
19-339 around Bennu
Jason Pearl, University of Vermont; David Hinckley, University of Vermont; WilliamLouisos, University of Vermont; Darren Hitt, University of Vermont
Trajectory optimization around small bodies presents interesting challenges due to their irregularshape. Often several competing objectives must simultaneously be considered in a high dimensional
optimization landscape. As such population based optimization techniques have been applied. In thepresent study, a gravity model using numerical quadrature and a curvilinear surface mesh isdeveloped to meet the requirements of a differential evolution trajectory optimization problem
around Bennu.

15:30

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15:50

AAS Lagrange – Mission Analysis for the European Space Agency’s Space Weather
19-385 Mission to the Sun-Earth Libration Point L5
Florian Renk, European Space Agency; Michael Khan, European Space Agency; Mehdi
Scoubeau, European Space Agency
In the frame of the European Space Agency’s Space Situational Awareness Programme a space
weather mission is currently being studied. For this mission the satellite is envisioned to be placed at
the Sun-Earth Libration Point L5. Observations from the L5 point extend our view of the Sun by
about 33% and would allow to see Sun activities not yet visible from Earth. The paper covers the 14
as well as the 26 months transfer options and dicusses the impact of the orbit size about L5 on the
DeltaV budget. The stability under normal perturbations is investigated.

16:10

AAS Trajectory design for LUMIO CubeSat in the cislunar space
19-387 Diogene Alessandro Dei Tos, Politecnico di Milano; Francesco Topputo, Politecnico di
Milano
The Lunar Meteoroid Impacts Observer, or LUMIO, is a CubeSat mission concept awarded exaequo winner of ESA's SysNova Competition "Lunar CubeSats for Exploration" that shall observe,
quantify, and characterize the meteoroid impacts by detecting their flashes on the lunar farside.
After a study at the ESA/ESTEC concurrent design facility, LUMIO is now under consideration for
future implementation by the Agency. In this paper, we propose the implementation of a
sophisticated orbit design, concept of operations, and station-keeping strategy: LUMIO is placed ona quasi-halo orbit about Earth-Moon L2. The baseline solution is presented with evidence to support
the orbit design.

16:30

AAS Mascot: flight dynamics activities in support of an asteroid landing mission
19-411 Elisabet Canalias, CNES; Laurence Lorda; Romain Garmier; Thierry Martin, Centre
National d'Etudes Spatiales; Jens Biele, DLR; Aurélie Moussi, Centre National d'Etudes
Spatiales
MASCOT is a German-French small lander that travelled onboard of the Japanese spacecraft
Hayabusa2 to the C-type asteroid called Ryugu. The probe arrived at Ryugu in June 2018. Then,
Hayabusa2 scientific teams started generating asteroid models that allowed for the selection of thelanding sites of its passengers (Minerva-II and MASCOT landers), as well as the touchdown sites of
the S/C itself. This paper describes the mission analysis and flight dynamics activities performed at
CNES since the early stages of MASCOT development and until after the lander release, withspecial emphasis on the operational process implemented for its landing site

16:50

AAS A new environment to simulate the dynamics in the close proximity of rubble-pile
19-412 asteroids
Fabio Ferrari, NASA Jet Propulsion Laboratory
This paper presents a new environment to simulate close-proximity dynamics around rubble-pile
asteroids. The code provides methods for modeling the asteroid's gravity field and surface throughgranular dynamics. It implements state-of-the-art techniques to model both gravity and contact
interaction between particles: 1) mutual gravity as either direct N2 or Barnes-Hut GPU-paralleloctree and 2) contact dynamics with a soft-body (force-based, smooth dynamics), hard-body(constraint-based, non-smooth dynamics), or hybrid (constraint-based with compliance anddamping) approach. A very relevant feature of the code is its ability to handle complex-shaped rigid

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bodies and their full 6D motion. Examples of spacecraft close-proximity scenarios and theirnumerical simulations are shown.

Session 7: Attitude Dynamics & Control II
Monday, Kula
Chair: Marco Ciarcia, South Dakota State University
13:30

AAS Spacecraft Attitude Motion Planning on SO(3) using Gradient-based Optimization
19-210 Fabio Celani, Sapienza University of Rome - School of Aerospace Engineering; Dennis
Lucarelli, American University - Department of Physics
The purpose of the present work is to perform spacecraft attitude motion planning so that a rest-torest rotation while satisfying pointing constraints is achieved. Attitude is represented on the group of
three dimensional rotations SO(3). The motion planning is executed in two steps. In the first step,
path-planning is performed by searching for a time behavior for the angular rates through theformulation of an optimal control problem solved with a gradient-based algorithm. In the second
step, the actual input torque is simply determined by the use of inverse attitude dynamics. A
numerical example is included to show the effectiveness of the method.

13:50

AAS Innovative Guidance and Control Design of the Versatile Orbit Transfer Space
19-257 Vehicle of the Epsilon Rocket
Yasuhiro Morita, Japan Aerospace Exploration Agency
This paper deals with the innovative guidance and control design of the versatile orbit transfer spacevehicle. The vehicle acts as the upper stage vehicle of the Epsilon rocket and its objective is to place
multiple small satellites into different orbits at significantly high accuracy. The primary issue is thehigh accuracy guidance and control under the relatively low thrust acceleration (long burn time). A
novel guidance strategy, the extended long-time velocity increment cut-off guidance law (LVIC), isutilized to tackle this challenge.

14:10

AAS HIGH PRECISION ATTITUDE CONTROL OF SPACECRAFT BASED ON
19-275 ELECTRIC THRUSTER AND FLYWHEEL
Ting Jin; Jian Cai
A new output torque strategy is proposed for attitude control actuators composed of electric
thrusters and flywheels. At the initial time, the large-angle and fast attitude maneuver is realized by
flywheels. When the attitude control is stable, the flywheels rotate at a constant speed without
output torque, and the electric thrusters generate control torque. If the control torque exceeds theoutput range of electric thrusters, the flywheels output constant torque over a period of time, and theelectric thrusters generate the residual control torque. Simulation results verify the feasibility of highprecision attitude control based on electric thrusters and flywheels.

14:30

AAS WAYPOINT FOLLOWING DYNAMICS OF A QUATERNION ERROR
19-283 FEEDBACK ATTITUDE CONTROL SYSTEMMark Karpenko, Naval Postgraduate School; Julie Halverson, NASA GSFC; Rebecca
Besser, KBRwyle

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Closed-loop attitude steering can be used to implement a non-standard attitude maneuver by using a
conventional attitude control system to track a profile of downsampled attitude commands(waypoints) stored in a spacecraft's command buffer. In this paper, we explore the waypoint
following dynamics of a quaternion error feedback control system. It is shown that using
downsampled commands induces a ripple between samples that causes the satellite angular rate tosignificantly overshoot the desired limit. Analysis in the z-domain is carried out in order tounderstand the phenomenon. NASA’s Lunar Reconnaissance Orbiter is used to illustrate thebehavior of a practical attitude control system.

14:50

15:30

AAS Attitude Maneuver Design for Planar Space Solar Power Satellites
19-287 Michael Marshall, Graduate Aerospace Laboratories, California Institute of Technology;
Ashish Goel, Jet Propulsion Laboratory; Sergio Pellegrino, Graduate Aerospace
Laboratories, California Institute of Technology
This paper investigates the attitude dynamics of planar space solar power satellites (SSPSs) byformulating the power-optimal guidance problem as a nonlinear optimal control problem. The
power-optimal guidance problem determines the attitude maneuvers that maximize the powertransmitted to Earth. This transmitted power depends on the relative geometry between the SSPS,
Sun, and receiving station. Hence, it is inherently coupled to the SSPS’s attitude. We solve thepower-optimal guidance problem to obtain attitude maneuver designs for various orbits. By
quantifying control and propellant requirements for various orbits, we emphasize how maneuver
dynamics play an important role in SSPS design.

Afternoon Break15:50

AAS Predicting Time-Optimal Slews Across Multiple Spacecraft with Inertia Ratios and19-319 the Agility Envelope
Jeffery King, U.S. Naval Academy; Yash Khatavkar, U.S. Naval Academy
This paper expands the prior findings by using a normalized satellite inertia tensor anddemonstrating a direct relationship between the agility envelope and the time benefit of using
optimal control maneuvering. This relationship was validated by analyzing 5184 maneuvers across4π steradian for each satellite configuration. Since the agilitoid is defined by the physicalconfiguration (reaction wheel and spacecraft inertia), it can be easily calculated without resorting toextensive simulation. This method achieves a simple and effective estimation of the benefit of
optimal control maneuvering for any spacecraft.

16:10

AAS NUMERICAL RESULTS ON THE GENERAL TIME-OPTIMAL REST-TO-REST
19-374 THREE-AXISREORIENTATION
OF
A
RIGID
SPACECRAFT
Marcello Romano, Naval Postgraduate School; Alanna Sharp, Naval Postgraduate School
The time optimal results to the rest-to-rest three-axis reorientation of a rigid spacecraft are presented
as a stereographic projection with respect to the eigenvector sphere for all possible rest-to-rest
reorientation maneuvers of a given slew angle. The pseudospectral method is used to obtain the
numerical results over a selec- tion of azimuths and elevations within the first octant of theeigenvector sphere. The stereographic projection method used in cartography then translates the

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three dimensional eigenvector coordinates to a two dimensional plane at the equator of theeigenvector sphere. These projections are applicable to inertially symmetric, axisymmetric, andasymmetic spacecraft.

16:30

AAS Discrete-Time Iterative Learning Control for Nonlinear Systems by Feedback
19-490 Linearization
Bing Song, Columbia University; Minh Phan, Dartmouth College; Richard Longman,
Columbia University
Iterative learning control (ILC) learns to track a pre-defined maneuver with high accuracy throughpractice. It aims to approach the hardware reproducibility error level, beyond the accuracy of thesystem model used in the learning process. ILC can be used in spacecraft fine pointing sensors
doing repeated scanning maneuvers. This paper is one of a series that extends ILC to classes ofnonlinear systems, besides linearization/bilinearization-based ILC algorithms. Feedback
linearization is another alternative that offers the possibility to apply linear ILC for learning in
nonlinear systems. Numerical examples demonstrate the comparison of these ILC methods fornonlinear systems.

16:50

AAS ON THE USE OF SINGULAR VALUE DECOMPOSITION BASIS FUNCTIONS TO
19-572 PREVENT ERROR SIGNAL ACCUMULATION IN ITERATIVE LEARNINGCONTROL
Bowen Wang, Columbia University; Richard Longman, Columbia University
Iterative Learning Control (ILC) aims to achieve zero error when performing the same finite-timetask repeatedly. The learning during transients are of importance for ILC to achieve zero tracking
error in a finite time, particularly when the desired trajectory is short compared to the systemsettling time. Using basis functions can not only decrease the computation burden, but also provides
solution to obtain a bounded control action sequence. Basis functions based on system Toeplitz
matrix are developed, which can prevent the accumulation of errors outside the span of output basis
functions that are produced during learning processes.

Session 8: Trajectory Design & Optimization II
Monday, Hana
Chair: Sonia Hernandez, Jet Propulsion Laboratory
13:30

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AAS DESIGNING LOW-ENERGY TRANSFERS FROM LOW-EARTH ORBIT TO A
19-259 TEMPORARILY-CAPTURED ORBITER
Kanta Yanagida; Naoya Ozaki, ISAS, JAXA; Ryu Funase, The University of Tokyo
Temporarily-Captured Orbiters (TCOs) are a new population of asteroids that are captured
by Earth’s gravity. Due to its proximity to the Earth, short-term exploration with small delta-V is
expected possible. This study aims to construct low-energy transfers to 2006 RH120, one of the
TCOs, from Low-Earth Orbit using an analogy with the lunar transfers. The initial guess was soughtby back-propagating perturbed TCO trajectories, which was then optimized through the direct
multiple shooting method. The result shows that various transfers are possible with rendezvous
delta-V even below 100 m/s, and that they form family structures.

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13:50

AAS A TITAN GRAVITY-ASSIST TECHNIQUE FOR BALLISTIC TOURS SKIMMING
19-265 OVER THE RINGS OF SATURNMar Vaquero, Jet Propulsion Laboratory; Juan Senent, Jet Propulsion Laboratory;
Matthew Tiscareno, Carl Sagan Center for the Study of Life in the Universe, SETI InstituteA novel type of Titan-flyby orbits featuring passes of the Saturn rings at close range has been
recently discovered. The purpose of this study is to explore the trajectory design space and assess
the applicability of such orbits to the design of a Saturn Ring Tour mission concept. A set of initialconditions required to start a tour is first determined, and a ∆V sequence to maximize the science
time over desired ring regions in terms of range distance, relative velocity and duration is thenselected. To demonstrate the potential of this technique, two sample ballistic ring tours are detailed.

14:10

AAS Robust Optimisation of Low-Thrust Interplanetary Transfers using Evidence Theory
19-285 Marilena Di Carlo, University of Strathclyde; Massimiliano Vasile, University ofStrathclyde; Cristian Greco, University of Strathclyde; Richard Epenoy, Centre Nationald'Etudes Spatiales
This work presents the formulation and solution of optimal control problems under epistemic
uncertainty, when the uncertainty is modelled with Dempster-Shaffer theory of evidence. The
application is to the design of low-thrust interplanetary transfers with epistemic uncertainty in theperformance of the propulsion system and initial launch mass. The problem is solved bytransforming the exact formulation, that uses discontinuous Belief functions, into an inexact
formulation that uses a new continuous statistical function that approximates the value of the Belief
function. The method is applied to the design of optimal low-thrust transfers from the Earth toasteroid Apophis.

14:30

AAS CHARTING A COURSE TO THE SUN: FLIGHT PATH CONTROL FOR PARKER
19-294 SOLAR PROBE
Powtawche Valerino, NASA / Caltech JPL; Paul Frank Thompson, Jet Propulson
Laboratory; Drew Jones, Jet Propulsion Laboratory, Caltech; Troy Goodson, NASA /Caltech JPL; Robert Haw, NASA / Caltech JPL; Eunice Lau, NASA / Caltech JPL; Neil
Mottinger, NASA / Caltech JPL; Mark Ryne, NASA / Caltech JPL
The successful launch of the Parker Solar Probe (PSP) during the early morning of August 12, 2018
on a Delta IV rocket and Star 48BV third stage has placed the spacecraft on a 7-year trajectory to
study the Sun. The goals of PSP are to better characterize the solar environment by collecting data
as close as 9.86 solar radii. This paper documents the analysis of 42 planned trajectory correction
maneuvers in preparation for the achieved launch date, along with the post-launch maneuver
activities. Since the previous paper, two design cycles were completed; they included the analysisof refined inputs for 24 reference trajectories.

14:50

AAS MARS GRAVITY ASSIST OPTIONS TO REDUCE MISSION ΔV FOR EUROPA
19-295 LANDER
Amanda Haapala , Johns Hopkins University Applied Physics Laboratory; Tim McElrath,
JPL/Caltech; Fazle Siddique, The Johns Hopkins University Applied Physics Laboratory
For the Europa Lander concept, a Carrier spacecraft transports a Lander to Jupiter’s moon, Europa,
to perform in-situ science aimed at detecting bio-signatures. Launch is planned for 2026 using the
SLS Block-1B to accommodate the mass of the Carrier and Lander. A 2026 baseline launch offers

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the opportunity for a unique set of Mars gravity assists (MGA) for both baseline and backup launch
options. By exploiting MGAs during interplanetary cruise, total mission ΔV is reduced from 2.3 to
1.7 km/s, and the spacecraft wet mass is correspondingly reduced.

15:10

15:30

AAS A Survey of the Methods Available for the Design of Many-Revolution Low-Thrust
19-297 Planetocentric Trajectories
Pradipto Ghosh, Analytical Graphics, Inc.
The mission use of electric propulsion (EP) systems providing continuous, low thrust has steadily
increased over the past several years. As EP technology continues to mature, the upward trend in its
efficient utilization is expected to persist. A particularly challenging and long-studied low-thrust
trajectory design problem is Electric Orbit Raising, i.e. the design of many-revolution, long durationtransfers in the planetocentric space. Numerous methods, both analytical and numerical, optimal andsub-optimal, open-and-closed-loop, and involving models of various degrees of complexity, havebeen proposed. This paper attempts to characterize and classify the more popular of these methods
and their variants.

Afternoon Break15:50

AAS Julia Language 1.0 Ephemeris and Physical Constants Reader for Solar System
19-298 Bodies
Kaela Martin, Embry-Riddle Aeronautical University (ERAU); Julia Mihaylov, EmbryRiddle Aeronautical University (ERAU); Renee Spear, Embry-Riddle Aeronautical
University (ERAU); Damon Landau, NASA / JPL
An ephemeris reader in the Julia Language that includes small bodies, asteroid shape modeling, andhigher order spherical harmonics is presented here. The second generation of this ephemeris reader
introduces shape models of known asteroids as well as spherical harmonics capabilities to support
gravitational potential models. This version of the ephemeris reader is also compatible with Julia 1.0
which was released in August of 2018. This second-generation version continues to support theobtainment of critical information needed for mission and trajectory design.

16:10

AAS Multi-step Optimization of Orbit Raising Trajectories for All-electric Propulsion
19-299 Geostationary Satellites
Kentaro Nishi, Japan Aerospace Exploration Agency (JAXA); Satoru Ozawa, Japan
Aerospace Exploration Agency (JAXA); Saburo Matunaga
An all-electric propulsion satellite has become a major system architecture for geostationary
communication satellites. To mitigate drawbacks caused by its low-thrust such as long stay in severeradiation environment, minimum-time transfer is necessary. In this paper, we propose a multi-step
optimization of orbit raising trajectories for the all-electric propulsion satellites. This method splits
the problem into multiple steps and optimizes thrust-vector direction in each step. It lightens thecomputational load and requires no initial guess. This paper describes detail of the method andevaluates optimality of the method. It also provides numerical results and a comparison with anexisting method.

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16:30

AAS Reachable Domain of Continuous Low-Thrust Trajectories with Linearized Dynamic
19-306 Model
Zhaowei Wang, Tsinghua University; Fanghua Jiang
An analytical method is improved for reachable domain of noncircular orbit propelled by low thrust
within fixed allowable transfer time, using the linearized differential equations of relative motion.
The projection of the relative reachable domain for noncircular and non-coplanar orbits can beobtained by numerical calculation of the derived analytical expressions. A geometrical construction
technique based on the envelope theory of family of surfaces is developed to determine the envelopeof the reachable domain. Two numerical examples demonstrate the usefulness of the proposed
method and show that the reachable domains consist well with the ones obtained by indirect
method.

16:50

AAS Optimal Hyperbolic Rendezvous Trajectories for Cycler Missions
19-308 Mauro Pontani, Sapienza University of Rome
Cycler mission architectures consider the use of a large space vehicle that cycles continuously
between Earth and Mars. While this large spacecraft, termed the cycler, is employed in theinterplanetary arc, taxi vehicles of reduced size are sufficient for the connection between each planet
and the cycler. This research provides a comprehensive analysis on optimal hyperbolic rendezvous
trajectories, with reference to two classes of rendezvous problems: (i) multiple-velocity-impulse
paths and (ii) low-thrust trajectories. Optimal high-thrust rendezvous trajectories include up to four
velocity changes. Moreover, low-thrust propulsion is proven to possess the potentiality ofoutperforming high-thrust in the future.

17:10

AAS Adjoint Estimation Method for Low-thrust Many-revolution Trajectory Optimization
19-311 Di Wu, Tsinghua University; Hexi Baoyin, Tsinghua University; Junfeng Li
This paper presents an adjoint estimation method for many revolution transfers. First the manyrevolution transfer problem is formulated as a multi-rendezvous problem with the same boundary
conditions. The initial guess of adjoint variables are obtained by the shape-based path technique. A
transforming method of the adjoint variables is then developed to get the results of the manyrevolution transfer. Then, based on the optimality analysis, an iterative optimization algorithm is
proposed to ensure that the nominal trajectories approach the optimum. In this way, the initial guess
is obtained by solving linearized equations analytically. Two scenarios are conducted as examples.

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Tuesday, January 15
Session 9: Orbital Debris & Space Environment
Tuesday, Kapulua
Chair: Simone D'Amico, Stanford University
8:00

AAS Conjunction Assessment and Risk Mitigation Automation (CARMA)
19-229 Mark Vincent, Raytheon
The Conjunction Assessment and Risk Mitigation Automation (CARMA) process at the Jet
Propulsion Laboratory was a natural response to the devolution strategy of the NASA Conjunction
Assessment Risk Analysis (CARA) institution. The progress in the implementation of the
distributed CARA software, any enhancements made, and preliminary test results will be described.
CARMA research includes matching the NASA lifetime risk criteria to the Probability of Collision(Pc) thresholds used in operations. A new tool produces Predicted Maneuver Trade Space plots,
which give a range of Pc values for a chosen maneuver given a model of future uncertainties fromnew observations.

8:20

AAS Resident Space Object Proper Orbital Elements
19-557 Aaron J. Rosengren, University of Arizona; Davide Amato, Technical University of Madrid(UPM); Claudio Bombardelli, Technical University of Madrid (UPM); Moriba K. Jah,
University of Texas at Austin
Proper elements are obtained as a result of the elimination of short and long periodic perturbations
from their instantaneous, osculating counterparts, and therefore represent a kind of averagecharacteristic of motion. Projected into proper element space, asteroids tend to cluster around
special values of the orbital elements leading to their classification into dynamical families. Proper
elements thus appear to have application to a number of underpinning areas of SSA in terms
taxonomy of RSOs and the associated of debris from breakup into its parent satellite. Here, we will
work out the theory of proper orbital elements in the circumterrestrial context.

8:40

AAS Mass Estimation Through Fusion of Astrometric and Photometric Data Collection
19-268 with Applications to Orbital Debris Characterization
Matthew Richardson, L3 Applied Defense Solutions; Thomas Kelecy, Applied Defense
Solutions; Jason Stauch, Applied Defense Solutions; Jack Wetterer, Integrity Applications
Incorporated; Channing Chow, Pacific Defense Solutions, LLC
A formulation is presented for estimating the mass of a space object from the fusion of astrometricand photometric data processed through a particle filter. The application for such a tool is tocharacterize the mass of an unknown debris object and quantify the mass uncertainty through theestimation method. This will facilitate understanding of unknown debris objects when characterizing
such objects with quantifiable uncertainty. Observability, in conjunction with consider analysis of
the states, was incorporated and shown to be a good indicator of when mass, size and attitude can be
estimated.

9:00

AAS Interpolation and Integration of Phase Space Density for Estimation of Fragmentation
19-320 Cloud Distribution
Stefan Frey, Politecnico di Milano; Camilla Colombo, Politecnico di Milano; Stijn

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Lemmens, European Space Agency
On-orbit fragmentations potentially produce hundreds of thousands of debris. The evolution of afragmentation cloud is modelled to estimate the consequences such events have on the spaceenvironment. Propagating the characteristics of the continuum equation can accurately estimate thedensity given any generic force model. However, interpolation and integration from point clouds ischallenging. Here, a method is presented to estimate the underlying distribution through Delaunay
triangulation. Alpha shapes are used to manage non-convex distributions. Integration is performed
on individual simplexes to give consistent marginals independent of bin sizes. The method is shownto outperform others based on representative objects.

9:20

AAS Data-driven investigation of thermospheric variations
19-438 Piyush Mehta, West Virginia University; RICHARD LINARES, Massachusetts Institute ofTechnology
This paper presents a methodology for data-driven investigation of thermospheric variations thatuses modal decomposition to extract high-dimensional basis for the correlated variation of theneutral thermospheric species and temperature. The extracted basis functions are combined withCHAMP and GRACE mass density measurements using a non-linear least squares solver. We
demonstrate the methodology using the MSIS model to derive high-dimensional basis functions. We
use the methodology to investigate oxygen-to-helium transition through variations of the individual
species as both species have a direct impact on drag and orbit prediction through gas-surface
interactions and mass density.

9:40

AAS On deriving Self-Consistent, High-accuracy Mass Density Measurements
19-439 Piyush Mehta, West Virginia University
High-accuracy thermospheric mass densities derived from measurements of orbital drag on-board
the CHAMP and GRACE satellites have been the workhorse of upper atmospheric research formore than a decade. These estimates use drag coefficients ($C_D$) computed with neutral species
composition from some empirical model that provides global estimates by combining diffusive
equilibrium profiles with lower boundary number density estimates that can contain errors. Recent
work on self-consistent calibration of empirical models provide insight into the errors in lower
boundary estimates and temperature profiles and this paper investigates its impact on the derivationof the measurements used to calibrate them.

10:00

10:20

Page 40Morning BreakAAS Robustness of Targeting Regions of Chaos In the GNSS Regime
19-465 Marielle Pellegrino, University of Colorado Boulder; Daniel Scheeres, University ofColorado at Boulder
This paper investigates the sensitivity of resonant and chaotic orbital dynamics proximate to GNSS
satellites. These regions are caused by luni-solar resonances and are defined by the semimajor axis,
eccentricity, and inclination. However, they are dependent on the position of the sun, moon, andother orbital parameters. This work will describe how sensitive the system is based on the different
orbital parameters in an effort to determine the feasibility of targeting these regions for debris
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disposal.

10:40

AAS Koopman Operator Theory for Thermospheric Density Modeling19-502 RICHARD LINARES, Massachusetts Institute of Technology; Piyush Mehta, West Virginia
University; Humberto C. Godinez, Los Alamos National Laboratory; David Gondelach,
University of Surrey, UK
Low-Earth orbiting (LEO) satellites are heavily influenced by atmospheric drag, which is very
difficult to model accurately. This paper demonstrates the Koopman Operator (KO)-theory applied
to the TIE-GCM model. The goal of this work is to use a physics-based atmospheric density modelfor obtaining a Reduced-Order Model (ROM) for density forecasting. It is shown that
Koopman/Extended Dynamic Model Decomposition (DMD) approach can reduce propagation error
while using fewer modes as compared to the DMD approach which assumes a linear model.

11:00

AAS A density-based approach to the propagation of re-entry uncertainties
19-409 Mirko Trisolini, Politecnico di Milano; Camilla Colombo, Politecnico di Milano
The proposed study aims at implementing a density-based approach for the propagation of
uncertainties in the initial conditions and parameters for the analysis and prediction of spacecraft reentries. Using the continuity equation together with the re-entry dynamics, the joint probability
distribution function of the uncertainties is propagated and the final uncertainties in the re-entry
corridor, impact location, and casualty area are quantified. The paper considers uncertainties in theinitial conditions at re-entry and in the ballistic coefficient of the satellite for different types of reentry scenarios, studying the effects that such uncertainties have on the impact location and entry
corridor.

11:20

AAS Large Constellation De-Orbiting with Low-Thrust Propulsion
19-480 Simeng Huang, Politecnico di Milano; Camilla Colombo, Politecnico di Milano; Elisa
Maria Alessi, IFAC-CNR; Zhili Hou, Tsinghua univercity
This paper deals with the de-orbiting of large constellations using low-thrust propulsion. The
objective is to de-orbit all satellites without any inner-constellation collision. Two de-orbit strategies
are considered — the first is lowering the perigee and the second is reaching a natural de-orbiting
highway. The research will be conducted via two layers — the first layer is designing the
trajectories for a single satellite and the second layer is minimizing the risk of inner-constellation
collision. For the first layer, three different control methods are investigated; the orbital averaging
technique and the direct apporach are used.

Session 10: Orbital Dynamics, Perturbations, and Stability II
Tuesday, Napili
Chair: Thomas Kelecy, L3 - Applied Defense Solutions
8:00

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AAS SECULAR ORBITAL ELEMENT VARIATIONS DUE TO CONTINUOUS LOW19-390 THRUST CONTROL AND THIRD-BODY PERTURBATIONS
Xiaoyu Liu, University of Glasgow; Colin McInnes, University of Glasgow; Matteo Ceriotti,
University of Glasgow
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An analytical method is investigated to evaluate the orbital element variations of a massless particle
in orbit about a central body, under the influence of continuous low-thrust control and third-body
perturbations. The third-body disturbing function is expanded in the form of Legendre polynomials
and truncated up to the second-order term. The components of continuous low-thrust control arethen represented as Fourier series in eccentric anomaly. Finally, the variational equations for theparticle orbital elements are averaged over the period of the particle to yield the secular effects.
Numerical simulation verifies the efficiency of the methodology.

8:20

AAS Trajectory Design in the Circular Restricted Three-body Problem Using Artificial
19-396 Invariant Manifolds
Yuki Oshima; Mai Bando, Kyushu University; Shinji Hokamoto, Kyushu University
This paper generalizes invariant manifolds of unstable libration point orbits through the applicationof constant thrust acceleration. First, artificial periodic orbits and their associated invariant
manifolds are introduced. It is shown that heteroclinic connections between an artificial periodic
orbit and an unforced periodic orbit with the same Jacobi constant are realized by detecting
intersections of manifolds on the Poincare section. Second, new Jacobi constant incorporating theconstant acceleration is defined. By utilizing the new Jacobi constant, zero-velocity curves for the
motion under constant thrust are shown and revealed that there exist transit orbits which connect
different regions in the CRTBP.

8:40

AAS VERY LONG ARC TIMING COEFFICIENT AND SOLAR LUNAR PLANETARY
19-401 EPHEMERIS FILES AND APPLICATIONS
Zachary Folcik, MIT Lincoln Laboratory; Paul J. Cefola, University at Buffalo (SUNY)
Precision orbit determination programs require time difference, polar motion parameter, solar, lunar,and planetary (SLP) ephemeris, and rotation matrix data. A single set of Timing Coefficient and
SLP files valid from 1973 to 2169 is developed. The start date is dictated by the IERS data. The end
date is dictated by the DE 200 file. DE 200 provides information referred to the dynamical equatorand equinox of 2000. The 196 year Timing Coefficient file requires consideration of the transition
from observed to extrapolated data. Cumulative Distribution Function (CDF) plots are given. The
performance of the 196 year files is explored.

9:00

AAS A HIGH ORDER ANALYTIC CONTINUATION TECHNIQUE FOR THE
19-512 PERTURBED TWO-BODY PROBLEM STATE TRANSITION MATRIXTahsinul Haque Tasif, University of Central Florida; Tarek Elgohary, University of Central
FloridaIn this work, the analytic continuation technique is used to derive the State Transition Matrix for the
perturbed two body problem resulting in a fast, high precision solution that outperforms state of theart numerical methods. Analytic Continuation is a Taylor series based technique where two scalar
Lagrange like invariants are defined and differentiated to an arbitrary order by using Leibniz productrule. These derivatives are used in the Taylor series expansion to obtain the solution. Previously,
this method has been applied to several trajectory calculations, which gave high precision
solutions with a comparatively lower computational cost.

9:20

AAS Identification of Families of Periodic Orbits Above/Below the Solar Sail Earth-Moon
19-470 Libration Points

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Jules Simo, University of Central Lancashire
This paper addresses the problem of finding periodic solutions in the circular restricted three- bodyproblem (CRTBP) with the Earth and Moon as the two primaries and the third massless body a solar
sail. Based upon the first-order approximation, an analytical formulation of the periodic orbits at
linear order is presented. The approximate analytical solutions found are utilized in a numericalsearch to determine displaced periodic orbits in the full nonlinear model. In order to illustrate thenear term and possible future orbits that can be achieved, we have generated the results for several
values of the characteristic acceleration.

9:40

10:00

AAS Feasibility study of near-frozen, near-circular, near-polar and extremely low altitude
19-510 lunar orbits
Sandeep Singh, Texas A&M University; Robyn Woollands, Jet Propulsion Laboratory;
John L. Junkins, Texas A&M University
Designing long duration lunar orbiter missions is challenging due to Moon's nonlinear gravity field
and third body perturbations. The absence of a lunar atmosphere, has encouraged mission designers
to search for extremely low altitude, stable lunar orbits as they present an opportunity for uniquescientific studies such as high resolution imaging of polar ice deposits in deep craters. Inaccuracy
in gravity models severely impacted duration of several past lunar orbiters. In this paper, we
perform a station keeping feasibility study for near-frozen, near-circular, near-polar and extrememly
low altitude orbits around the Moon. We study the trade-space between mission duration andcorrective impulses.

Morning Break

10:20

AAS ANALYSIS OF DISTURBANCE ANOMALY OF INTERPLANETARY MICRO19-526 SPACECRAFT PROCYON
Satoshi Ikari, The University of Tokyo; Takaya Inamori, Nagoya University; Takahiro Ito,
Japan Aerospace Eploration Agency; Ryu Funase, The University of Tokyo
Drugin the operation of the first 50-kg class interplanetary micro-spacecraft PROCYON,it's gradientof the angular momentum on Z-axis was suddenly changed without any external torque generationfrom propulsion system and attitude maneuver. In other words, disturbances acting on the spacecraft
was suddenly increased by 10-8 Nm oder at the point. In order to reveal the cause of the disturbanceanomaly, we investigated accurate solar radiation pressure, thermal radiation pressure,interplanetary magnetic field torque, and collision with proton particle. These detailed investigationsof minor disturbances with real flight data will contribute for future accurate navigation ofinterplanetary spacecraft.

10:40

AAS Analytical Radial Adaptive Method for Spherical Harmonics Gravity Models
19-544 Ahmed Atallah, San Diego State University; Robyn Woollands, Jet Propulsion Laboratory;
Ahmad Bani Younes, San Diego State University; John L. Junkins, Texas A&M University
High precision propagation for satellites orbiting the Earth require accurate computation of thegravitational acceleration at each integration step. This is a computationally expensive operation that
depends on the orbit geometry and the accuracy to which the solution is required. High accuracy

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solutions require a large degree and order in the spherical harmonic series which increases thecomputation time. In this paper we present an analytic method for which the degree of the sphericalharmonic series is automatically selected based on the desired solution accuracy and the radial
distance of the satellite from the Earth.

11:00

AAS Retrograde Teardrop Orbits about Asteroids: Application to the Hayabusa2 Mission
19-554 Shota Kikuchi, Japan Aerospace Exploration Agency; Yusuke Oki, The University of Tokyo;
Takanao Saiki, JAXA / ISAS; Yuto Takei; Hiroshi Takeuchi, Japan Aerospace Exploration
Agency; Go Ono, Japan Aerospace Exploration Agency; Hitoshi Ikeda, Japan Aerospace
Exploration Agency; Yuichi Tsuda, Japan Aerospace Exploration Agency
This research investigates retrograde teardrop orbits (RTOs) about asteroids subject to strong solar
radiation pressure (SRP). RTOs are closed orbits that are made periodic by introducing adeterministic impulsive delta-V within each period. This type of artificial periodic orbit provides
high flexibility in the orbit design compared with natural periodic orbits. RTOs are promising
options for asteroid missions because of their stability and small delta-V values (on the order of 10
cm/s or less). This paper presents the dynamical theories of RTOs and possible applications for the
Hayabusa2 mission.

11:20

AAS ANALYTIC PROBABILITY DENSITY MODEL OF SATELLITE SWARMS
19-564 Yupeng Gong
A probability density model is developed to calculate the spatial distribution and coverage
performance of satellite swarms on various orbits. Probability density function describes theprobably location of the satellites and considers the evolution under the effect of gravitational
perturbations, solar radiation pressure and drag. Since the satellite quantities can be represented by
the distribution of the sum of satellite probability density functions, the coverage property ofswarms can be calculated. Remarkably, the probability distribution of coverage property can becalculated by interval and distribution of orbit elements without need for precise orbital parameters.

Session 11: Atmospheric Re-entry & Satellite Constellations
Tuesday, Kula
Chair: Kamesh Subbarao, University of Texas at Arlington
8:00

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AAS Investigation of Direct Force Control for Planetary Aerocapture at Neptune
19-212 Rohan Deshmukh, Purdue University; Soumyo Dutta, NASA Langley Research Center;
David A. Spencer, Purdue University
In this work, a direct force control (DFC) numerical predictor-corrector guidance architecture isdeveloped to enable Neptune aerocapture using low-L/D blunt body aeroshells. Optimal control
theory is applied to obtain the angle of attack and side-slip angle guidance laws for a Mars Science
Laboratory-derived aeroshell. Robustness testing and performance analysis are performed in a
Monte Carlo setting using the Program to Optimize Simulated Trajectories II. The simulated
trajectories are demonstrated to be both robust to the modeled dispersions and at a low total delta-v
cost. DFC guidance is shown to be an enabling and enhancing technology for low-L/D planetary
aerocapture.

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8:20

AAS Autopilot for Near-Space Hypersonic Vehicle Controlled by Aerodynamic Lift and19-301 Divert Thrusters with Off-Centered Seeker Window
Penglei Zhao; Wanchun Chen; Wenbin Yu
This paper presents the design of an autopilot of the near-space hypersonic vehicle that is controlled
by aerodynamic lift and divert thrusters and has an off-centered seeker window. To decouple thecontrol of attitude and trajectory, a command allocation algorithm following the aerodynamicdivert-first principle is proposed to coordinate the divert and attitude control systems. Thereafter, ahigh-order sliding mode controller using nonlinear dynamic sliding manifold technique is designed
for the control of the attitude control system, and a pulse-width pulse-frequency modulator isdesigned for the control of the divert control system. Simulations demonstrate the effectiveness androbustness of the autopilot.

8:40

AAS PARKING ORBIT SELECTION FOR MARS AEROCAPTURE-ENTRY SYSTEMS
19-463 Evan Zinner, University of Illinois at Urbana-Champaign; Zachary Putnam, University of
Illinois at Urbana-Champaign
This study explores parking orbit selection for an aerocapture-entry system at Mars and assesses theimpact on vehicle design. This study explores the effect of parking orbit selection on the total entry
system mass. The effect of non-virgin thermal protection system during entry, descent, and landing
is considered. The analysis finds that the mass from the thermal protection system does not varysignificantly depending on orbit selection. The larger driver of entry system mass is the propellant
needed to stabilize the parking orbit. This leads to longer period parking orbits having less entry
system mass

9:00

AAS STOCHASTIC REACHABILITY ANALYSIS FOR THE HYPERSONIC RE19-468 ENTRY PROBLEM
Amit Jain, Penn State University; Damien GUEHO, The Pennsylvania State University;
Puneet Singla, Pennsylvania State University; Maruthi R. Akella, University of Texas atAustinIn this paper, a computationally efficient approach will be presented to enable on- board
computation of reachability sets for the hypersonic re-entry problem. The main idea of the presented
approach is to consider the bounded control variables as random variables and represent thereachability sets as the level sets of the state probability density function. A main advantage of suchan approach is that it provide not only the boundary of the reachability set but it also characterizes
the probability distribution of state variable due to variation in control input. The computation ofstate density function due to variation in

9:20

AAS Mid-Lift-to-Drag ratio Rigid Vehicle 6-DoF EDL Performance Using Tunable Apollo
19-499 Powered Guidance
Breanna Johnson, NASA; Ping Lu, San Diego State University; Christopher Cerimele,
NASA Johnson Space Center
The Mid-Lift-to-Drag ratio Rigid Vehicle (MRV) is a candidate in the NASA multi-center effort todetermine the most cost effective vehicle to deliver a large-mass payload to the surface of Mars for ahuman mission. Products of this effort include six-degree-of-freedom (6DoF) entry-to-descent
trajectory performance studies for each candidate vehicle. These high fidelity analyses help
determine the best guidance and control (G&C) strategies for a feasible, robust trajectory. This

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paper presents an analysis of the MRV’s G&C design by applying common entry and descentassociated uncertainties using a Fully Numerical Predictor-corrector Entry Guidance (FNPEG) andtunable Apollo powered descent guidance.

10:00

Morning Break

10:20

AAS Neural Network Trained Controller for Atmospheric Entry in Mars Missions
19-491 Hao Wang, University of Central Florida; Dillon Martin, University of Central Florida;
Tarek Elgohary, University of Central Florida
We will present a new method to design the controller of Mars capsule atmospheric entry usingneural networks. Compared to Apollo controller as a baseline, the simulation of neural network
controller reproduced the classical Apollo results over a wide variation of initial conditions andsystem parameters, e.g. atmospheric drag. This leads to the potential of achieving requirements offuture manned Mars missions. The data from Earth and Mars models are used for neural networks
training. The neural network for Earth reentry is evaluated with Apollo real data and then adapted
for the Mars environment.

10:40

AAS Guidance and Control System Design for Mars Aerocapture
19-508 Larissa Balestrero Machado, Florida Institute of Technology; Brian Kaplinger, Florida
Institute of Technology; Markus Wilde, Florida Institute of Technology; Robert Moses,
NASA Langley Research Center
This paper presents a control system and guidance algorithm for an aerocapture maneuver to transfer
a Crew Transfer Vehicle (CTV) from an Earth-Mars Cycler into a Low Mars Orbit (LMO). The
guidance algorithm guides the spacecraft through the Martian atmosphere targeting the atmospheric
exit conditions necessary for the vehicle to reach the desired post-aerocapture orbit apoapsis. The
reference trajectory is also optimized such that the maximum deceleration and heat loads tolerable
by the crew and vehicle are not violated.

11:00

AAS DESIGN OF A RESILIENT RIDESHARE-BASED SMALL SATELLITE
19-402 CONSTELLATION USING A GENETIC ALGORITHM
Katherine Mott, Virginia Tech; Jonathan Black
Responsive and resilient space-based systems are needed to satisfy changing mission requirements
and react to unforeseen challenges. This paper studies the ability of a constellation constructed fromcommercial-off-the-shelf parts and launched using rideshare to provide imaging coverage over asmall region in the event of a disaster, such as an outbreak of wildfires. A genetic algorithm is used
to evaluate rideshare constellations through coverage metrics in both the nominal case and the casein which some satellites have failed. Novel methods for determining reachability between two orbits
and for determining revisit metrics for degraded constellations are presented.

11:20

AAS Differential Lift and Drag Based Constellation Control Using Trimmed Attitude
19-431 Andrew Harris, University of Colorado Boulder; Hanspeter Schaub, University ofColorado

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Spacecraft operating in Low Earth Orbit can leverage atmospheric forces to reduce fuelconsumption and improve robustness to hardware failure. This work extends prior work in
differential-drag formation flight to the constellation domain through the use of differential orbital
elements. Additionally, a gas-surface interaction model is incorporated into the control dynamics toenable out-of-plane maneuvers using atmospheric lift Small variations to attitude about a reference
attitude–referred to as “trimmed attitude” in this work–are considered as the control input, allowing
for the construction of a system that is affine in control.

Session 12: Trajectory Design & Optimization III
Tuesday, Hana
Chair: Ryan Russell, The University of Texas at Austin
8:00

AAS Low-Energy Trajectories as Staging Points for Landing on the Secondary Body in the
19-316 CR3BP
Luke Bury, University of Colorado Boulder; Jay McMahon, CCAR (Colorado Center for
Astrodynamics Research)
Many scientifically interesting moons orbit the gas giants, but without atmospheres to soften thelanding (excluding Titan), sending a lander to the surface becomes a very difficult problem forwhich a low-energy trajectory is required. In this paper, a grid-search is utilized to study all possible
landing regions for given Jacobi constants in the CR3BP, and various systems are compared. Impact
angles and location of Lagrange-point-neck crossings are carefully observed. Additionally, zonal
harmonics are included to study whether they allow new surface regions to be reached when
accounted for.

8:20

AAS Modeling and Optimization of Aero-Ballistic Capture
19-323 Carmine Giordano, Politecnico di Milano; Francesco Topputo, Politecnico di Milano
In this paper a novel paradigm for Mars missions is modeled and optimized. This concept consists ina maneuver that combines aerocapture and ballistic capture upon Mars arrival, and is labelled aeroballistic capture. The idea is reducing the final mass by exploiting the interaction with the planet
atmosphere as well as the Sun--Mars gravitational field. The aero-ballistic capture paradigm isformulated. Then the problem is stated by using optimal control theory, and optimal solutions aresought. An assessment of aero-ballistic capture shows the superiority compared to classicalmaneuvers when medium-to-high final orbits are wanted.

8:40

AAS A Two-Level Differential Corrections Algorithm for Low-Thrust Spacecraft
19-356 Trajectory Targeting
Collin York, Purdue University; Kathleen C. Howell, Purdue University
Applications of low-thrust propulsion to spaceflight in multi-body environments require a targetingalgorithm to produce suitable trajectories on the ground and on board spacecraft. The two-leveltargeter with low thrust (TLT-LT) provides a framework to implement differential corrections inboth computationally-limited autonomous spacecraft applications and the larger design space of premission planning. Extending existing two-level corrections algorithms, applications of the TLT-LT
to spacecraft with a range of propulsive capabilities, from nearly-impulsive to low-thrust, areexplored. The process of determining partial derivatives is generalized, allowing for reduced logicalPage 47

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complexity and increased flexibility in designing sequences of thrusting and ballistic segments.

9:00

AAS Europa Lander trajectory design: case studies for the Direct-To-Earth architecture
19-327 Stefano Campagnola, Jet Propulsion Laboratory; Tim McElrath, JPL/Caltech; Aline K.
Zimmer, Jet Propulsion Laboratory; Damon Landau, NASA / JPLThis paper presents two interesting phasing problems that came up in support of design studies for apotential Europa Lander mission. Recent system trades were performed after the Mission Concept
Review in fall 2017, when the NASA board recommended the Europa Lander project design a
Direct-to-Earth architecture. In the first study, which considered a bi-propellant system for thelander, we designed an ultra-low-radiation endgame with separate Europa orbit insertion and deorbiting maneuvers for the Descent Vehicle, and a ballistic Ganymede-impact transfer for the
carrier. In the second study, we analyzed trajectories to use Clipper as a data-relay spacecraft during
landing.

9:20

AAS Trajectory Design Using Quasi-Periodic Orbits in the Multi-Body Problem
19-329 Brian McCarthy, Purdue University; Kathleen C. Howell, Purdue University
Incorporating quasi-periodic orbits (QPOs) into the preliminary design process offers a wider range
of options to meet mission constraints and address the challenges in a complex trade space. In thisinvestigation, QPO stability and alternative QPO family continuation schemes are examined to meetvarious types of trajectory constraints. Additionally, trajectory arcs from QPOs can be exploited togenerate transfers between periodic orbits. By leveraging the natural dynamical structures associatedwith QPOs, novel low cost transfers may emerge.

9:40

AAS Mission Design for the Lunar Pallet Lander
19-330 Anthony Craig; James Holt; Mike Hannan; Juan Orphee
Marshall Space Flight Center is developing a small lunar lander capable of delivering up to 300 kg
of payload to the lunar surface near the North or South Pole. Originally designed as a lander forsmall rover, the Lunar Pallet Lander, has seen several design iterations over the last couple of years.
This paper will cover how the vehicle and mission design evolved from starting as a Space Launch
System co-manifested payload up to the current design that could be launched with an EELV classvehicle.

10:00

10:20

Page 48Morning BreakAAS NASA Exploration Mission 2 Mission Design19-331 Anthony Craig; Christopher Berry, NASA; Eric Christiansen; Gerald Condon, NASA;
Adam Harden; Christopher Foster; Jeffery Little; Trey Perryman; Seth Thompson, Troy 7;
Michael D. Bjorkman, Jacobs Technology
Exploration Mission 2 (EM-2) will be NASA’s first manned flight on the Space Launch System(SLS) and Orion Spacecraft. The mission has been changed from an SLS Block 1B configuration to
Block 1. This change has necessitated a reexamination of the flight profile to determine whatchanges must be made in order to accommodate the reduced launch vehicle performance on the
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Block 1. Launch availability and Orbital Debris risk will be traded to find the best flight profile forboth SLS and Orion.

10:40

AAS Fuel-Optimal Convex Trajectory Optimization of Rendezvous on Elliptical Orbits
19-333 Mauro Massari, Politecnico di Milano; Paolo Massioni, Laboratoire Ampere, INSA Lyon,
Universitè de Lyon
In this paper a new approach to constrained low-thrust trajectory optimization for rendezvous on
elliptical orbits is presented. The approach is derived from a technique developed in the control
engineering community, known as Sum Of Squares. Approximating the solution as a polynomialwith respect to time, the constraints are reduced to bounds on polynomials. The polynomial
bounding problem is then formulated as a convex optimization problem which does not require an
initial guess for the solution. This approach is well suited for problems under linear dynamic
equations, therefore perfectly fitting the case of spacecraft relative motion.

11:00

AAS New Horizons 2014MU69 Flyby Design and Operation
19-334 Yanping Guo, JHUAPL; Wayne Schlei, JHUAPL
After the Pluto flyby in July 2015, the New Horizons spacecraft continued its journey to theoutermost region of solar system to explore the Kuiper Belt. New Horizons will fly by a Kuiper Belt
Object (KBO), designated 2014MU69, on January 1, 2019 for the closest observations of a KBO
ever by a spacecraft. The design plan includes both prime and alternate flyby trajectories at closest
approach distances of 3,500 km and 10,000 km, respectively. Seven trajectory correction maneuvers
are scheduled during the final approach phase for flight path refinement and final targeting of the
MU69 flyby.

11:20

AAS The Low-Thrust Interplanetary Explorer: A Medium-Fidelity Algorithm for Multi19-348 Gravity Assist Low-Thrust Trajectory Optimization
Martin Ozimek, The Johns Hopkins University Applied Physics Laboratory; Jack Riley,Johns Hopkins Applied Physics Laboratory; Juan Arrieta, Nabla Zero LabsThe Johns Hopkins University Applied Physics Laboratory and Nabla Zero Labs have developed amulti-gravity assist, low-thrust trajectory optimization software tool known as LInX: the Low-thrustInterplanetary eXplorer. LInX relies on the well-known Sims-Flanagan transcription and nonlinear
programming. The tool features fully analytical partial derivatives with accurate hardware models
and is well-suited for medium-fidelity applications. There are many novel aspects to LInX,
including a modular implementation based on the latest C++ standard; an efficient parallel
ephemeris implementation of SPICE; and support for deployment in heterogeneous computing
environments for large-scale applicatins. Results against established trajectory optimization
benchmark problems exhibit favorable convergence and performance.

Session 13: Large Space Structures & Tethers
Tuesday, Kapulua
Chair: Islam Hussein, Applied Defense Solutions
13:30
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19-238 Structural Models
Dong-Huei Tseng; Minh Phan, Dartmouth College; Richard Longman, Columbia
University
A method to identify the stiffness and damping matrices of high degree-of-freedom structuralmodels is described. The number of degrees of freedom is considered high if the state-space modelof the correct dimension from force inputs to measured outputs becomes uncontrollable and cannot
be identified from input-output measurements, thus preventing the structure mass, stiffness, anddamping matrices from being recovered. This difficulty is overcome by identifying the physicalparameters associated with each individual degree of freedom, where controllability is notcompromised. These parameters are aggregated to form the stiffness and damping matrices of theentire structure.

13:50

AAS Partial System Identification of Stiffness and Damping Matrices From Output
19-239 Measurements Only
Minh Phan, Dartmouth College; Dong-Huei Tseng; Richard Longman, Columbia
University
This paper deals with the partial system identification of stiffness and damping matrices of astructure from output measurements only. The input forces that excite the structure are unknown andnot necessarily white. This is a common scenario in practice where a structure is richly instrumented
with accelerometers that provide a wealth of output measurements, yet the forces that excite thestructure are unknown or unmeasured. This paper shows that if the mass matrix is known then therows of the stiffness and damping matrices associated with the degrees of freedoms that are notdirectly actuated can still be recovered.

14:10

AAS Optimal Control of Space Debris Deorbit Using Space Tethered Satellite System
19-247 Li Pengjie, Beihang University, Beijing, China; Rui Zhong; Hongwen Wang, Beihang
University
This paper proposes an optimal control scheme for space debris deorbit by a space tethered satellite(STS) system with minimal fuel consumption. The scheme includes two phases, the open-loop
control trajectory optimization and the closed-loop optimal control. The first phase, the open-loop
control trajectory optimization, is derived by solving a STS system optimal deorbit problem using a
direct collocation method based on Gauss pseudospectral method. The second phase concerns theclosed-loop optimal control for tracking the optimal states reference trajectory using the model
predictive control method. Numerical results showed that the proposed scheme can achieve spacedebris deorbiting to graveyard safely, economically and efficiently.

14:30

AAS HIGH-FIDELITY DYNAMIC MODELLING OF PARTIAL SPACE ELEVATOR
19-363 WITH DEPOYMENT OR RETRIEVAL OF TETHER
George Zhu, York University; Gangqiang Li, York University
This paper presents a high-fidelity model for the partial space elevator system. The partial spaceelevator system is modeled by nodal position finite element method in arbitrary Lagrangian-Euler
description, where a material coordinate is introduced as the state variable to represent the climbers
moving along the tether. A dividing/emerging of element process is developed to model theclimbers’ motion by changing the length of variable-length elements. The simulation results showthat the proposed method can be easily extended to multiple-climber case by assigning the moving

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nodes and variable-length elements.

14:50

AAS FLIGHT DYNAMIC AND CONTROL STRATEGY OF FLEXIBLE ELECTRIC
19-365 SOLAR WIND SAIL
George Zhu, York University; Gangqiang Li, York University; Chonggang Du, York
University
A high-fidelity multiphysics model of an electric solar wind sail is developed by the nodal position
finite element method. The coupling effects between the orbital and self-spinning motion are
analyzed when the system subjects to the gravitational force only, and major coupling terms are
identified and examined. The numerical simulations also show that the coupling effect between theorbital and self-spinning motions causes a periodic variation of the self-spin rate of E-sail and thetether tension.

15:10

AAS PARALLEL OPTIMIZAL CONTROL FOR PARTIAL SPACE ELEVATOR
19-369 George Zhu, York University
A new piecewise parallel optimal control scheme to suppress the libration of a partial space elevator
is developed. The libration is controlled by regulating tether length. The original optimal control
scheme is split into two parallel phases on a dual-CPU system to reduce computational burden. CPU
I predicts an optimal reference state trajectory for the next time interval piecewise by an open-loop
optimization with a grossly simplified three-body tethered system model. CPU II tracks thepredicted reference trajectory at the current time interval simultaneously by a closed-loop receding
horizon control using a full dynamic model. The simulation results reveal that

15:30

AAS NANOSATELLITE MISSION FOR SPACE DEBRIS DEORBIT
19-370 DEMONSTRATION BY ELECTRODYNAMIC TETHER
George Zhu, York University
Electrodynamic space tethers (EDT) have unique capabilities to provide cost-effective
demonstrations of innovative concepts and acquire science data which would otherwise not be
achievable on Earth. Over the past four decades, the development of space tether technology has
witnessed 26 suborbital and orbital flights. These missions demonstrated that space tether
technology has the near-term potential to meet a broad range of scientific and engineering demands.
This paper will cover the mission concept study, mission objectives, nanosatellite design, hardware
selection, and operation.

15:50

AAS A Multidisciplinary Performance Analysis for the Cygnus Cargo Resupply Mission to
19-251 the ISS
Virgil Hutchinson, Northrop Grumman
The Cygnus propellant is a critical flight resource and consumption analysis is performed for every
CRS mission to determine the propellant load required to complete the mission with adequate
propellant contingency and margin. An integrated analysis model involving several coupledanalyses is used to generate the propellant budget by calculating the propellant usage for eachmaneuver during the CRS mission. Mission and configuration parameters within the integrated
analysis model were varied probabilistically by performing a Monte Carlo analysis. Statistical
distributions for the propellant usage from the Monte Carlo analysis are used to determine thePage 51

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recommended propellant load for the mission.

Session 14: Dynamical Systems Theory
Tuesday, Napili
Chair: Diane Davis, a.i. solutions, Inc.
13:30

AAS Designing Low-Thrust Enabled Trajectories for A Heliophysics SmallSat Mission to
19-266 Sun-Earth L5
Ian Elliott, University of Colorado Boulder; Christopher Sullivan, University of Colorado
Boulder; Natasha Bosanac, University of Colorado, Boulder; Farah Alibay; Jeffrey Stuart,
Jet Propulsion Laboratory
A small satellite deployed to Sun-Earth L5 could serve as a low-cost platform to observe solar
phenomena such as coronal mass ejections. However, the small satellite platform introduces
significant challenges in the trajectory design process via limited thrusting capabilities, power andoperational constraints, and fixed deployment conditions. To address these challenges, a strategy
employing dynamical systems theory is used to design a low-thrust-enabled trajectory for a small
satellite to reach the Sun-Earth L5 region. This procedure is demonstrated for a small satellite thatlaunches as a secondary payload with a larger spacecraft destined for a Sun-Earth L2 halo orbit.

13:50

AAS Exploring the Low-Thrust Trajectory Design Space for SmallSat Missions to the Sun19-267 Earth Triangular Equilibrium Points
Christopher Sullivan, University of Colorado Boulder; Ian Elliott, University of Colorado
Boulder; Natasha Bosanac, University of Colorado, Boulder; Farah Alibay; Jeffrey Stuart,
Jet Propulsion Laboratory
With the increasing availability of upcoming rideshare opportunities, low-thrust-enabled small
satellites could be leveraged as a platform for targeted heliophysics investigations conducted fromthe Sun-Earth L4 or L5 regions. In the early stages of mission concept development for small
satellites, understanding the trajectory trade space – and the influence of the spacecraft hardware
configuration and scientific objectives – is crucial. Fundamental dynamical structures within the
Sun-Earth system are examined and used to extract insight into the properties of the trajectory
design space for low-thrust-enabled small satellites to visit Sun-Earth L4 or L5 from several fixed
deployment conditions.

14:10

AAS Transit and Capture in the Planar Three-Body Problem Leveraging Low-Thrust
19-280 Dynamical Structures
Andrew Cox, Purdue University; Kathleen C. Howell, Purdue University; David Folta,
NASA Goddard Space Flight Center
Path planning in the circular restricted 3-body problem (CR3BP) is frequently guided by theforbidden regions and manifold arcs. However, when low-thrust is employed to modify the
spacecraft trajectory, these dynamical structures pulsate with the varying Hamiltonian value. In a
combined CR3BP, low-thrust (CR3BP-LT) model, an additional low-thrust Hamiltonian is available
that remains constant along low-thrust arcs. Accordingly, the analogous low-thrust forbidden
regions and manifolds are static and are useful guides for low-thrust trajectory design. Strategies
leveraging these structures and other insights from the CR3BP-LT are explored to construct transit

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and capture itineraries.

14:30

AAS GLOBAL SEARCH OF RESONANT TRANSFERS FOR EUROPA LANDER TO
19-366 CLIPPER DATA RELAY
Damon Landau, Jet Propulsion Laboratory; Stefano Campagnola, Jet Propulsion
Laboratory
Following its prime mission Europa Clipper becomes a potential asset to relay data from Europa
Lander back to Earth. To this end, we propose an efficient method to globally search for trajectories
that repeatedly fly over the same location on Europa. Different families of trajectories emerge withdifferent flyby geometries that satisfy a convoluted set of landing constraints. Here, the landing
location and local solar time must match a limited set derived from expected Clipper observations,while providing multiple opportunities to land in a given season. We include estimates for data
volume and radiation dose associated with these resonant trajectories.

14:50

AAS Attitude Dynamics of a Rigid Body in Circular Orbit
19-342 Francisco Crespo, Universidad del Bio-Bio; Jorge Luis Zapata, Universidad del Bío-Bío;
Sebastian Ferrer, Universidad de Murcia; Molero Francisco Javier, Universidad de
MurciaWe address the attitude dynamics of a triaxial rigid body in a circular orbit. This task is done bymeans of a 1-DOF approximation dubbed as the intermediary system. Our study is carried out inglobal non-canonical variables. The key role played by the moments of inertia and the magnitude of
the angular momentum modulus in the different types of relative equilibria and bifurcations isshown in detail. Precisely, the classic dynamics of the free rigid body is modified for slow rotation
regime: several bifurcations with changes of stability are displayed. Moreover, the precession of theangular momentum plane circulates.

15:10

AAS Sparse Optimal Trajectory Design in Three-Body Problem
19-359 Yuki Kayama; Mai Bando, Kyushu University; Shinji Hokamoto, Kyushu University
A structure of the optimal trajectory for minimizing fuel consumption in an unstable dynamical
environment such as the three-body problem is not revealed. Recently, it has been found that asparse solution structure appears also in an optimization of a dynamical system. This concept
explains the property that sections the minimum fuel trajectory corresponds to the trajectory which
minimizes the total thrusting time. In this paper we propose a numerical method to obtain theminimum-fuel sparse optimal trajectory in the unstable dynamical system. As an example, proposed
method applies to the transfer between halo orbits in the Sun-Earth system.

15:30

AAS Applications to Space Flight of new results on minimum-time Control of Linear
19-372 Systems between Two Arbitrary States
Marcello Romano, Naval Postgraduate School; Fabio Curti, School of Aerospace
Engineering
A new general solution method, recently developed by the authors, is presented here which issolving for the first time to the best knowledge of the author the general problem of minimum-time
control of a linear time-invariant normal system evolving from an arbitrary initial state to anarbitrary desired final state subjected to a cubic-constrained control. The method and its

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demonstration are here summarized. Furthermore, new solutions are presented for this optimal
control problem for widely used dynamic models used in space flight dynamics, including the
double integrator system, the undamped harmonic oscillator system and other cases.

15:50

AAS Finding Symmetric Halo Orbits Framed as a Global Optimization problem Using
19-543 Monotonic Basin Hopping
David Hinckley, University of Vermont; Darren Hitt, University of Vermont
In this work we use the stochastic optimization algorithm Monotonic Basin Hopping to findsymmetric halo orbits of a prescribed amplitude in the Sun-Earth and Earth-Moon systems throughposing the search as an optimization problem. Stochastic methods are well suited for this problem
due to its highly multi-modal nature. Monotonic Basin Hopping is proposed here since it can takeadvantage of the clustering of sub-optima around an orbit of desired precision. The result is a fastmeans of finding halo orbits of a desired amplitude which are symmetric within a prescribed
tolerance.

Session 15: Special Session - Mars Insight
Tuesday, Kula
Chair: Eric Gustafson, NASA / JPL Caltech
13:30

AAS 2018 Mars InSight Trajectory Reconstruction and Performance from Launch through
19-204 Landing
Fernando Abilleira, NASA Jet Propulsion Laboratory/Caltech; Allen Halsell, JPL/Caltech;
Min-Kun Chung, NASA/JPL; Ken Fujii; Eric Gustafson, NASA / JPL Caltech; Yungsun
Hahn, Jet Propulsion Laboratory; Mark Johnson; Thomas Kennedy, Lockheed Martin
Corporation; Julim Lee, NASA JPL; Sarah Elizabeth McCandless, Jet Propulsion
Laboratory; Neil Mottinger, NASA / Caltech JPL; Jill Seubert, NASA / Caltech JPL; Gina
Signori, Lockheed Martin Corporation; Evgeniy Sklyanskiy, NASA / Caltech JPL; MarkWallace, Jet Propulsion Laboratory, California Institute of Technology
The InSight mission successfully launched on an Atlas V 401 launch vehicle from the Western Test
Range (WTR) at Vandenberg Air Force Base (VAFB) at 11:05:00 UTC on May 5th, 2018. At
12:38:41 UTC, 20 sec after the InSight spacecraft separated from the Centaur upper stage, thespacecraft transmitter was turned on and in about 8 sec spacecraft carrier lock was achieved at theGoldstone tracking station. This paper summarizes in detail the actual vs. predicted trajectory
performance in terms of launch vehicle events, injection performance, actual DSN performance,
trajectory correction maneuver performance, and Entry, Descent, and Landing events.

13:50

AAS Mars Reconnaissance Orbiter Navigation Strategy for Support of InSight Lander's
19-209 Entry, Descent and Landing Sequence
Premkumar Menon, NASA/JPL; Sean Wagner, Jet Propulsion Laboratory; David Jefferson,
NASA / Caltech JPL; Eric Graat, NASA/JPL; Kyong Lee, NASA/JPL; William Schulze,
NASA/JPL; Robyn Woollands, Jet Propulsion Laboratory; Kevin Criddle, NASA / Caltech
JPL
The Mars Reconnaissance Orbiter (MRO) provided primary relay support for the InSight mission's
Entry, Descent and Landing (EDL) on November 26, 2018 and after its landing on Mars. To

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position MRO for relay support during InSight EDL, two propulsive maneuvers were performed:
the first on August 22, 2018 and the second on October 24, 2018. This paper documents the phasing
strategy employed by the MRO Navigation Team to support the InSight EDL sequence.

14:10

AAS InSight Orbit Determination
19-213 Eric Gustafson, NASA / JPL Caltech; Allen Halsell, Jet Propulsion Laboratory, California
Institute of Technology; David Jefferson, NASA / Caltech JPL; Eunice Lau, NASA / Caltech
JPL; Julim Lee, NASA JPL; Sarah Elizabeth McCandless, Jet Propulsion Laboratory; Neil
Mottinger, NASA / Caltech JPL; Jill Seubert, NASA / Caltech JPL
The InSight mission depends on accurate deep-space navigation for a successful Mars landing. In
this paper, we discuss the role of the cruise Orbit Determination team, whose responsibility included
determining the spacecraft state, predicting the future trajectory, and quantifying the uncertainty
associated with those estimates. In particular, we will focus on spacecraft dynamic modeling, small
forces due to attitude control, radiometric tracking data, filter strategies, uncertainty quantification,and responses to unexpected flight situations. We will also provide a full analysis of reconstructed
maneuvers, small forces, and delivery accuracy at Mars arrival.

14:30

AAS InSight Attitude Control System Thruster Characterization and Calibration for
19-222 Successful Navigation to Mars
Jill Seubert, NASA / Caltech JPL; Eric Gustafson, NASA / JPL Caltech; Allen Halsell, Jet
Propulsion Laboratory, California Institute of Technology; Sarah Elizabeth McCandless,
Jet Propulsion Laboratory; Julim Lee, NASA JPL
In order for the InSight spacecraft to execute a safe Mars landing, it is crucial that the navigation teamaccurately predict the trajectory and deliver the spacecraft to the targeted atmospheric entry
point. One of the primary challenges faced by the Navigation Team was the accurate

reconstruction and prediction of small but frequent velocity changes imparted by the
spacecraft’s Attitude Control System thrusters. This paper discusses the in-flight thruster
calibration campaign, the reconstruction and prediction of thruster accelerations throughout various
phases of cruise (including compensating for significant outgassing post-launch and -attitudetransition), and the subsequent impact on atmospheric entry point delivery.

14:50

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AAS Navigation Performance of the 2018 InSight Mars Lander Mission
19-228 Allen Halsell, JPL/Caltech; Min-Kun Chung, Jet Propulsion Laboratory; Eric Gustafson,
NASA / JPL Caltech; Yungsun Hahn, Jet Propulsion Laboratory; David Jefferson, NASA /Caltech JPL; Eunice Lau, NASA / Caltech JPL; Julim Lee, NASA JPL; Sarah Elizabeth
McCandless, Jet Propulsion Laboratory; Neil Mottinger, NASA / Caltech JPL; Jill Seubert,
NASA / Caltech JPL; Evgeniy Sklyanskiy, NASA / Caltech JPL; Mark Wallace, Jet
Propulsion Laboratory, California Institute of Technology
The Mars InSight mission was launched on May 5th, 2018. The spacecraft trajectory had to becontrolled to a set of precise atmospheric entry and landing conditions to land safely on the surfaceof Mars. The two corresponding critical components of the atmospheric entry conditions are theentry flight path angle (to allow for successful descent to the surface) and the entry time (to ensurethat real-time data could be seen). This paper will describe how the InSight Navigation team met
this difficult task.

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15:10

AAS Maneuver Design Overview of the 2018 InSight Mars Lander Mission
19-232 Min-Kun Chung, Jet Propulsion Laboratory; Yungsun Hahn, Jet Propulsion Laboratory;
Allen Halsell, Jet Propulsion Laboratory, California Institute of Technology; Sarah
Elizabeth McCandless, Jet Propulsion Laboratory; Evgeniy Sklyanskiy, NASA / Caltech
JPL; Mark Wallace, Jet Propulsion Laboratory, California Institute of Technology
Launched on May 5, 2018, the InSight spacecraft is scheduled for Mars landing on November 26,
2018. To ensure a safe and accurate landing, six nominal trajectory correction maneuvers (TCMs)
are planned along the reference trajectory from Earth launch to Mars arrival with two contingency
TCMs. There are also twenty pre-designed menu TCMs available for execution at the time of thelast contingency TCM, 8 hours before the Mars entry, descent, and landing phase begins. Thisnavigation paper will describe the purpose and design strategy of each TCM as well as how eachone actually performed during the flight.

15:30

AAS Mars Reconnaissance Orbiter Maneuver Plan for Mars 2020 Entry, Descent, and19-233 Landing Support and Beyond
Sean Wagner, Jet Propulsion Laboratory; Premkumar Menon, NASA/JPLThe Mars Reconnaissance Orbiter (MRO) spacecraft continues to perform valuable scienceobservations at Mars, provide telecommunication relay for surface assets, and characterize landingsites for future missions. MRO provided primary relay support for the InSight mission during
Entry, Descent, and Landing (EDL) on November 26, 2018. This paper discusses the current
maneuver plan to support Mars 2020 EDL and maintain MRO's orbit for science operations through
2028.

15:50

AAS Atmospheric Impacts on EDL Maneuver Targeting for the Insight Mission and19-264 Unguided Mars Landers
Eugene Bonfiglio, Jet Propulsion Laboratory; Mark Wallace, Jet Propulsion Laboratory,
California Institute of Technology; Eric Gustafson, NASA / JPL Caltech; Min-Kun Chung,
Jet Propulsion Laboratory; Evgeniy Sklyanskiy, NASA / Caltech JPL; Devin Kipp, Jet
Propulsion Laboratory
During operational testing for the InSight mission to Mars, it was discovered that the final
maneuvers to target the atmosphere were unexpectedly sensitive to planned atmosphere model
updates that would be based on real-time MRO measurements of Mars. The team realized that the
Phoenix mission also discovered this sensitivity during operational testing. An investigation
identified the cause and revealed that any unguided Mars EDL mission would be impacted by thissensitivity if it used ‘real-time’ atmosphere observations to model the atmosphere used for
maneuver targeting. This paper discusses the investigation results, potential mitigations, and theconsequences of ignoring the sensitivity.

16:10

AAS Orbiters, Cubesats, and Radio Telescopes, Oh My; Entry, Descent, and Landing
19-291 Communications for the 2018 InSight Mars Lander Mission
Mark Wallace, Jet Propulsion Laboratory, California Institute of Technology; Daniel
Litton, NASA; Tomas Martin-Mur, NASA/JPL; Sean Wagner, Jet Propulsion Laboratory
The Interior Exploration using Seismic Investigations, Geodesy, and Heat Transport (InSight) Marslander mission was launched on May 5th, 2018 and its November 26, 2018 entry, descent, andlanding sequence was observed by no less than five separate assets. The Mars Reconnaissance

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Orbiter (MRO) in orbit about Mars, the two Mars Cube One (MarCO) spacecraft flying by, and two
radio telescopes back on Earth were all used for this critical event communication coverage. These
many paths of communication were enabled via the InSight launch/arrival strategy design, MRO
orbital phasing selection, and MarCO trajectory design.

Special Session - Mars Sample Return
Tuesday, Hana
Chair: Ryan Woolley, NASA / Caltech JPL
13:30

AAS End to End Optimization of a Mars Hybrid Transportation Architecture
19-225 Min Qu, AMA; Raymond Merrill, NASA Langley Research Center; Patrick Chai, NASA
Langley Research Center
NASA’s Mars Study Capability Team (MSCT) is developing a reusable Mars hybrid transportationarchitecture in which both chemical and solar electric propulsion systems are used in a single
vehicle design to send crew and cargo to Mars. This paper presents a new integrated framework thatcombines Earth departure/arrival, heliocentric trajectory, Mars orbit reorientation, and vehicle sizing
into a single environment and solves the entire mission from beginning to end in an effort to find a
globally optimized solution for the hybrid architecture.

13:50

AAS Mars Sample Return -- ORBITAL RENDEZVOUS DETECTION METHODS
19-230 Robert Haw, JPL; Eric Gustafson, NASA / JPL Caltech
Passive optical detection of a capsule in orbit around Mars by a Mars orbiter is investigated andcompared with active capsule detection (radio beacon). Navigation trades while in pursuit of arendezvous with the capsule are described. Passive methods are, to first order, unconstrained bytime while a radiometric link is time-limited. The rendezvous operation is described in terms of farfield and near-field detection.

14:10

AAS Low-Thrust Trajectory Bacon Plots for Mars Mission Design19-326 Ryan Woolley, NASA / Caltech JPL; Austin Nicholas, Jet Propulsion Laboratory/Caltech;Frank Laipert, Jet Propulsion Laboratory; Zubin Olikara, NASA Jet Propulsion Laboratory
The best way to understand a mission design trade space is by creating a good map of all thepossibilities, and by knowing how to read it. Bacon plots, which are low-thrust analogs to porkchop
plots, give insight into key parameters and sensitivities of possible transfers to Mars (or otherdestinations). They are mission and parameter specific, and can be created to represent single ormultiple legs. This paper outlines the creation process and lessons learned in interpreting theresults. An example is given on how bacon plots have been employed for complex mission-level
optimization.

14:30

AAS Hybrid Chemical-Electric Trajectories for a Mars Sample Return Orbiter
19-345 Frank Laipert, Jet Propulsion Laboratory; Austin Nicholas, Jet Propulsion
Laboratory/Caltech; Zubin Olikara, NASA Jet Propulsion Laboratory; Ryan Woolley,
JPL/Caltech; Robert Lock, Caltech

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The Earth return orbiter component of a Mars sample return campaign is a high-impulse mission
with challenging timeline constraints. These competing demands mean a hybrid chemical-electric
propulsion architecture may be needed for a feasible design, with chemical providing timely impulse
and electric providing high volume impulse. We describe an approach to map out the hybrid
trajectory design space and create a database to use in conjunction with a spacecraft design tool,
enabling co-optimization of trajectory and spacecraft. This method is applied to both the outboundand inbound legs of a Mars sample return mission concept.

14:50

AAS Simultaneous Optimization of Spacecraft and Trajectory Design for Interplanetary
19-456 Missions Utilizing Solar Electric Propulsion
Austin Nicholas, Jet Propulsion Laboratory/Caltech; Ryan Woolley, JPL/Caltech; Alan
Didion, NASA Jet Propulsion Laboratory; Frank Laipert, Jet Propulsion Laboratory; Zubin
Olikara, NASA Jet Propulsion Laboratory; Ryan Webb, NASA / JPL / Caltech; Robert
Lock, Caltech
A major challenge in formulating interplanetary mission concepts utilizing electric propulsion is thelarge number of trajectory variables that must be considered (thrust profile, flyby options, launchvehicle delivery), all of which are affected by spacecraft design variables (power, mass, thruster,
payload, staging). This is significantly more complex than traditional ballistic/chemical mission
design and early concepts are often suboptimal as a result, potentially missing valuable options. This
paper presents a novel tool (MORT) for simultaneously optimizing the spacecraft design alongside
the trajectory given mission constraints and objectives, including example results relevant to the
exploration of Mars.

15:10

AAS Mission Analysis for a Potential Mars Sample Return Campaign in the 2020’s
19-458 Austin Nicholas, Jet Propulsion Laboratory/Caltech; Alan Didion, NASA Jet Propulsion
Laboratory; Frank Laipert, Jet Propulsion Laboratory; Zubin Olikara, NASA Jet
Propulsion Laboratory; Ryan Woolley, JPL/Caltech; Robert Lock, Caltech
The Mars 2020 mission, currently under development by NASA, plans to acquire and cache up to
42 carefully-selected rock and regolith samples from the surface of Mars for potential future return.
NASA and ESA are jointly studying options for returning those samples to Earth with missions
launching in the 2020s. This paper demonstrates a method for modeling the various campaign
elements, synthesizing coordinated campaign timelines, and assuring trajectory feasibility of in thepresence of many constraints, and finally optimizing towards mission success. Options for complete
sample return campaigns in multiple launch and arrival opportunities are explored and compared.

15:30

AAS Chemical and Solar Electric Propulsion Orbit Matching for Mars Sample Rendezvous
19-459 Zubin Olikara, NASA Jet Propulsion Laboratory; Austin Nicholas, Jet Propulsion
Laboratory/Caltech
A concept for returning samples from the surface of Mars involves rendezvous between an orbiter
and a passive sample container in low Mars orbit. This work presents orbit matching maneuver
design approaches for chemical and solar electric propulsion (SEP) options. The chemical scheme
selects a sequence of intermediate orbits to achieve desired node and phase drifts. The SEP scheme
optimizes the averaged relative dynamics accounting for eclipses, drift due to J2, and attitude rate
constraints. The performance of these approaches is analyzed as a function of orbit inclination andsample container state dispersions.

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15:50

AAS Potential Campaign Architectures and Mission Design Challenges for International
19-583 Mars Sample Return Mission Studies
Robert Lock, Caltech; Austin Nicholas, Jet Propulsion Laboratory/Caltech; Ryan Woolley,
JPL/Caltech; Alan Didion, NASA Jet Propulsion Laboratory; Frank Laipert, Jet Propulsion
Laboratory; Zubin Olikara, NASA Jet Propulsion Laboratory
Mars Sample Return is a high priority mission in the planetary science community and a decadeslong goal of international planetary exploration programs. Architectures and mission options are
currently under study by NASA and ESA to find potential partnership opportunities to develop andconduct MSR missions at Mars in the 2020s. The major elements of the MSR campaign havesignificant architectural options and mission launch, arrival and return options. The decision criteria
often depend on mission design and functional allocations across many elements. This paper
outlines the architecture trades and the mission design optimization challenges faced by the current
studies.

16:10

AAS OPTIMAL FEEDBACK CONTROL FOR THE HYPERSONICRE-ENTRY
19-555 PROBLEM
mehrdad mirzaei, Aerospace Engineering; Puneet Singla, Pennsylvania State University;
Maruthi R. Akella, University of Texas at Austin
In this paper, sparse collocation approach is applied to determine optimal feedback laws forHypersonic vehicle (HV) reentry mission. The effective collocation process is used by applying the
new developed Conjugate Unscented Transformation to prepare a minimal set of collocation points.
In conjunction with the minimal cubature points, an $l_1$ norm minimization methodology isapplied to optimally select the best basis functions from a larger complete dictionary of polynomial
basis functions. Reentry problem for a hypersonic vehicle with inequality path constraint is
considered.

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Wednesday, January 16
Session 17: Space Situational Awareness & Conjunction Analysis
Wednesday, Kapulua
Chair: Florian Renk, European Space Agency
8:00

AAS Hayabusa2 Mission Solar Conjunction Phase for Hovering Satellite: Trajectory
19-241 Design, Navigation and Post-Operation Evaluation
Stefania Soldini, ISAS/JAXA; Yuichi Tsuda, Japan Aerospace Exploration Agency;
Tomohiro Yamaguchi, ISAS/JAXA
Hayabusa2 mission is the ongoing JAXA’s sample and return mission to Ryugu asteroid. In late
2018, Ryugu will be in solar conjunction. Therefore, the Hayabusa2 spacecraft will experience
communication blackouts while hovering at 20 km from Ryugu. In this article, the design of a safe
conjunction trajectory is given in the Hill frame and then verified in the full-body. Two Trajectory
Correction Manoeuvres (TCMs) are scheduled before and after the deep conjunction. A linear
covariance analysis is shown together with the results of the Monte Carlo analysis to compute thestochastic delta-V at TCMs. Pre-/Post-flight operation data are also compared.

8:20

AAS Maneuver Design for Asteroid Rendezvous Considering Uncertainty
19-284 Marc Balducci, SpaceNav; Brandon Jones, University of Texas at Austin
When designing maneuvers for rendezvous in space, many current methods assume a deterministic
system, leaving system uncertainty unquantified. This paper presents the case of a rendezvous whileconsidering the propagated uncertainty of an asteroid and approaching spacecraft. Using thesurrogate method of separated representations, uncertainty is efficiently propagated and utilized in
an optimization under uncertainty algorithm which allows for variations in maneuver components.
By estimating differences in position components rather than the position state of each object, theabsolute accuracy of the surrogate is improved. From this, a tractable means of designing arendezvous maneuver under uncertain conditions is formulated.

8:40

AAS Context-Based Non-Compliance for GEO Satellite Reorbiting
19-433 shiva iyer, University of Texas, Austin; Moriba K. Jah, University of Texas at Austin; Islam
Hussein, Applied Defense Solutions; Emmanuel Delande, University of Texas at Austin;
Drew McNeely, University of Texas, Austin
The Inter-Agency Space Debris Coordination Committee (IADC) established guidelines
in 1997 to ensure proper disposal of GEO satellites at the end of their operational lifetimes. This
paper analyzes inactive GEO satellites to determine the extent to which they comply with theseguidelines. Space object data from USSTRATCOM, JSC Vimpel, the European Space Agency, andUnion of Concerned Scientists catalogs are used to obtain the current population of inactive GEO
satellites. A consistent data model is developed to capture the parameters of the problem. Context
information including country of origin and launch year is used to identify patterns of behavior withregard to compliance.

9:00

AAS A Probabilistic Approach for Reachability Set Computation for Efficient Space19-437 Situational AwarenessZachary Hall, Pennsylvania State University; Puneet Singla, Pennsylvania State University

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The focus of this paper is the application of the polynomial approximation method to obtain satellite
reachability sets for Space Situational Awareness (SSA) applications. Least squares coefficients forthe approximation of the final state solution are calculated in a Jacobian free and computationallytractable manner. The Conjugate Unscented Transformation (CUT) method is utilized for thispurpose, and is used to calculate the coefficients with a minimal number of full number of fullmodel propagations. Numerical simulation results are given to validate the approach.

9:20

10:00

AAS A new representation of uncertainty for collision assessment
19-452 Emmanuel Delande, University of Texas at Austin; Moriba K. Jah, University of Texas atAustin; Brandon Jones, University of Texas at Austin
In the context of collision assessment, it is customary to represent the uncertainty on an object's state(kinematic state, attitude, etc.) with a random variable and an associated pdf. However, aprobabilistic representation sometimes produces counter-intuitive results, with potentially dangerous
implications for collision avoidance. We exploit an alternative representation based on outerprobability measures (o.p.m.s) rather than probability distributions, matching more closely the
information available on an uncertain system. We show that an o.p.m.-formulation of the objects’states leads to a more intuitive and satisfying interpretation of a collision assessment event, and we
illustrate this concept on a few scenarios.

Morning Break10:20

AAS Early Collision and Fragmentation Detection of Space Objects without Orbit
19-483 Determination
Lyndy Axon, The Boeing Company; Marcus Holzinger, University of Colorado Boulder
This paper demonstrates that using the hypothesized constraint of the admissible regions, it ispossible to determine if a combination of new uncorrelated debris objects have a common originthat also intersects with a known catalog object orbit, thus indicating a collision or fragmentation
has occurred. Admissible region methods are used to bound the feasible orbit solutions of multiple
observations using constraints on energy and radius of periapsis, propagating them to a common
epoch in the past, and using sequential quadratic programming to find a set of solution states thatminimize the Euclidean distance between the observations at that time.

10:40

AAS A New Impact-Time Guidance Strategy via Dual Virtual-Target Concept
19-355 Yanning Guo, Harbin Institute of Technology; Pengyu Wang, Harbin Institute ofTechnology; Yueyong Lyu, Harbin Institute of Technology; Bong Wie, Iowa State
University
The paper investigates the problem of impact time control for homing missile in the context of
employing the differential geometric guidance approach, subject to nonlinear kinematics and lateral
acceleration limits. A circular predictive impact time guidance law and two progressive virtual
target approaches are developed to achieve the impact time requirement and bedeck the guidance
procedure. The new guidance strategy has great potential for autonomous onboard implementation
since it can avoid the time-to-go estimation and computational iterations. Theoretical analysis andnumerical simulations are exhibited to validate the effectiveness of the proposed guidance strategy.

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11:00

AAS Spacecraft Detection Avoidance Maneuver Optimization Using Reinforcement
19-506 Learning
Jason Reiter, Penn State ARGoPS; David B. Spencer, Pennsylvania State University;
RICHARD LINARES, Massachusetts Institute of Technology
Spacecraft maneuvers are planned with operational objectives in mind, usually ranging from making
up for orbit perturbations to maneuvering to avoid a possible collision. Though these areas havebeen researched in depth, little work has been done exploring maneuvers performed to avoid
detection by sensors. This paper explores the optimization of detection avoidance maneuvers using
reinforcement learning. Numerical transcription is used for comparison purposes, but the open-loop
nature of optimal control is not conducive to solving the entirety of the detection avoidance
problem. Reinforcement learning produces reliable results for maneuver optimization which will
provide a unique alternative for maneuver planning.

11:20

AAS AN INITIAL ANALYSIS OF AUTOMATING CONJUNCTION ASSESSMENT AND
19-517 COLLISION AVOIDANCE PLANNING IN SPACE TRAFFIC MANAGEMENT
Jannuel Cabrera, Purdue University, NASA Ames Research Center, and Bay Area
Environmental Research Institute; Sreeja Nag, NASA Ames Research Center and Bay Area
Environmental Research Institute; David Murakami, NASA Ames Research Center
Conjunction assessment (CA) and collision avoidance (COLA) involve the respective detection andmitigation of threatening encounters in orbit and both are vital components of a space traffic
management (STM) system. Safe operations in space requires near-continuous CA, and COLA
where necessary, leading to a need for autonomous interoperability and distributed decision-making
within a capable STM system. This paper presents a software framework being developed at NASA
Ames Research Center that utilizes readily-available commercial and open-source software tools to
support a fully-automated CA and COLA process in STM.

Session 18: Asteroid & Non-Earth Orbiting Missions II
Wednesday, Napili
Chair: Mar Vaquero, Jet Propulsion Laboratory
8:00

AAS Asteroid Manipulation with Active Boulder Removal
19-427 Daniel Brack, University of Colorado Boulder; Jay McMahon, CCAR (Colorado Center for
Astrodynamics Research)
A control law that links an asteroid's rotation and orbit to activity on its surface is presented. The
control law is simulated using the Combined Asteroid Surface-Boulder model which observes the
dynamical effects of boulder motion and surface topography changes on an asteroid's rotation andorbital states. This control law is used to maneuver an asteroid in its orbit while preventing asignificant change in its rotation state, and to disrupt an asteroid's rotation in such a way that induces
surface activity.

8:20

AAS Large Constellations and Formations for Exploring Interstellar Objects and Long19-436 Period Comets
Soon-Jo Chung, California Institute of Technology; Karen Meech, Institute for Astronomy,

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University of Hawaii; Julie Castillo-Rogez, Jet Propulsion Laboratory, California Instituteof Technology
This paper identifies the best strategies of using formation flying spacecraft for the in-depth
exploration of planetary bodies with very long periods, i.e., bodies that cross our solar system andapproach Earth only once in a lifetime. These bodies include Oort cloud comets and, now,
interstellar objects, as the recently discovered ‘Oumuamua is not the first, and certainly not the lastinterstellar visitor in our solar system. Long-period comets are the most primitive witnesses of theearly solar system. Hence the scientific value of exploring these objects is unbounded.

8:40

AAS Effect of Shifted Origin on the Osculating Orbital Elements of Terminator Orbit
19-450 Shota Takahashi, University of Colorado Boulder; Daniel Scheeres, University of Colorado
at Boulder
The secular dynamics of SRP perturbed two-body problem has been proven to have a closed-form
solution. As there is an offset between the orbit and mass centers, however, actual dynamics
deviates from the solution of secular dynamics. What causes this discrepancy is a short-periodvariation over one orbit period. In this research, we introduce an arbitrary offset along the Sunasteroid line and investigate a short-period oscillation of orbital elements defined about the offset.
The optimal offset will be analytically formulated and numerically verified. Further corrections tobetter define a frozen terminator orbit are also discussed.

9:00

AAS Modeling Imaging Uncertainty For OSIRIS-REx's Asteroid Approach Observations
19-509 Kristofer Drozd, University of Arizona; Roberto Furfaro, The University of Arizona; Diane
Lambert, University of Arizona; John Kidd, University of Arizona; Bill Boynton, OSIRISRExThis paper outlines and solves the problem of imaging the asteroid Bennu to a confidence of 3sigma in the presence of spacecraft state perturbation during OSIRIS-REx's approach trajectory. The
problem consists of the uncertainty ellipse, that a mosaic must cover, changing size as the spacecraft
state is perturbed. A method for determining how much to over image the uncertainty ellipse, inorder to satisfy observation requirements, is developed and utilized for the Approach Late OCAMS
Shape Model observations. Machine learning classification techniques are also implemented to
explore their utility at predicting mosaic coverage for future OSIRIS-REx observations.

9:20

AAS Expected Accuracy of Density Recovery using Satellite Swarm Gravity Measurements
19-529 William Ledbetter, University of Alabama; Rohan Sood, University of Alabama; Jeffrey
Stuart, Jet Propulsion Laboratory
Asteroids represent the remnants of planetary formation, and effective, rapid characterization of
their internal structure can facilitate identification of bodies that merit closer investigation. Previous
work outlined a preliminary framework for such characterization, but lacked comprehensive
stochastic validation. In this paper, the researchers build upon the existing method by performing
the necessary stochastic analysis, as well as expanding the recovery technique by testing various
iterative update algorithms.

10:00

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FINAL PROGRAMAAS On the design of multiple-revolution solar gravity driven orbital transfers around19-234 Mars
Stijn De Smet, University of Colorado; Daniel Scheeres, University of Colorado at Boulder;
Jeff Parker, CCAR, Advanced Space, LLC
Current solar electric propulsion and launch vehicle technology enable sending multiple spacecraftto Mars simultaneously. For capture orbits with very high apoapse, solar gravity perturbations candeploy the spacecraft into vastly different orbits. This paper utilizes artificial neural networks toefficiently identify transfers with multiple solar perturbed revolutions and intermediate maneuvers at
periareion. The methodology is applied to several applications. Transfers are identified that arrive at
Phobos or Deimos, and transfers that target both Phobos and Deimos on a single trajectory. Besides
the efficient determination of initial conditions, the frequency with which transfers exist in the phasespace is computed.

10:40

AAS Swarm Optimization of Lunar Transfers from Earth Orbit with Radiation Dose
19-244 Constraints
Justin Mansell, Purdue University; Samantha Dickmann, Purdue University; David A.
Spencer, Purdue University
Due to the frequent launches of primary satellites into geosynchronous transfer orbits, lunar transferfrom an initial geosynchronous transfer orbit represents an attractive option for secondary payloads
with lunar mission objectives. Lunar trajectory design from such orbits involves trade offs between
coasting time and radiation dose. We train a mixture density neural network on state-of-the-art
radiation environment models to estimate dose distributions rapidly. The network is combined withthe particle swarm method to optimize the coasting and transfer arcs of a lunar mission while
obeying radiation dose constraints with high confidence. Results are refined in a high fidelity orbit
propagator.

11:00

AAS SRP-based orbit control with application to orbit stationkeeping at small bodies
19-415 Kenshiro Oguri, University of Colorado Boulder; Jay McMahon, CCAR (Colorado Center
for Astrodynamics Research)
With appropriate control algorithms, solar radiation pressure (SRP) can be effectively utilized as asource of orbit control force around asteroids. In contrast to the historical treatment of SRP as a
disturbance at the weak gravity environment, the present paper finds active control of spacecraft
attitude promising for orbit control. Based on the authors' previous development of an SRP-based
orbit control law, the present paper investigates its applications to orbit stationkeeping problems at
small bodies. As preliminary results, numerical simulations confirm the effectiveness of the SRPbased control, where an originally unstable terminator orbit is stabilized by the stationkeeping
control.

11:20

AAS Ballistic Moon-Moon Transfers in the Cislunar Restricted Four-Body Problem
19-547 Anthony Genova, NASA; Brian Kaplinger, Florida Institute of Technology; David Dunham,
KinetX, Inc.
This paper investigates the continuity of several families of transfer trajectories using ballistic lunar
capture. Ballistic capture trajectories are of interest for spacecraft with low-thrust propulsion orPage 64

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those otherwise unable to enter lunar orbit from a traditional lunar transfer orbit. A continuation
model is used to map two-body problem candidate solutions into trajectories satisfying the dynamics
of the Sun-Earth-Moon (SEM) restricted four-body problem. The change of each family ofcandidate solutions with SEM angle of the initial lunar flyby is expected to impact the ability toclaim existence of a solution across a wide range of initial TLI epochs.

11:40

AAS Gravitational capture at Saturn with low-thrust assistance
19-371 Elena Fantino, Khalifa University of Science and Technology; Jesus Pelaez, Technical
University of Madrid (UPM); Roberto Flores, International Center for Numerical Methods
in Engineering; Virginia Raposo-Pulido
Orbit insertion at Saturn requires a large manoeuver with chemical thrusters to compensate for theenergy difference between the spacecraft and the planet. The impact that this has on the propellant
budget is huge. This paper discusses an alternative strategy: after a gravity assist with Jupiter, anelectrical motor with an ad hoc thrusting law modifies the orbital elements to minimize thehyperbolic excess speed at Saturn and, thus, facilitate the capture. The control law algorithm, as well
as all the dynamical and technological aspects are discussed and presented.

Session 19: Proximity Missions & Formation Flying I
Wednesday, Kula
Chair: Brett Newman, Old Dominion Univ.
8:00

AAS Exact Keplerian Relative Motion: An Elementary Formulation of the Initial-Value
19-235 Problem
Paul W. Schumacher, Air Force Research Laboratory / RDSM; Wesley Jackson,
Department of Astronautical Engineering; Ryan Olson, Department of AstronauticalEngineering
This paper presents the explicit solution for the initial-value problem of exact nonlinear relative
motion between satellites in Keplerian orbits. The elementary approach taken here is designed tocomplement several more advanced mathematical formulations published by other authors in recent
years. Although this approach can be used to represent the relative motion between any two orbits
having non-zero angular momentum, the present analysis is limited to elliptical chief and deputy
orbits. Formulas are given for computing the deputy's relative position and velocity in any inertiallyoriented frame centered on the chief and in the usual Euler-Hill frame. Several numerical examples
are included.

8:20

AAS Relative Motion Analysis Using Third- and Fourth-Order Solutions of the Relative
19-290 Two-Body Problem
Julio Caesar Benavides, Embry-Riddle Aeronautical University; David B. Spencer,
Pennsylvania State University
In this paper, third-order and fourth-order, time-dependent solutions of the relative two-bodyproblem in conjunction with the general equations of relative motion to analyze the relative motionof a chase vehicle with respect to a target vehicle in low-Earth orbit are used. The results of thisanalysis are then compared to the outcomes that are derived from the Hill-Clohessy-Wiltshire
equations and the numerical integration of the general equations of relative motion. The results

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demonstrate that the third- and forth-order formulations provide a robust method of analyzing
relative motion that is not hindered by the assumptions of linear orbit theory.

8:40

AAS ANALYTICAL SPACECRAFT FORMATION DYNAMICS IN ECCENTRIC
19-338 ORBITS WITH GRAVITATIONAL, DRAG AND THIRD-BODY
PERTURBATIONS
Ahmad yazan Chihabi, Carleton University; Steve Ulrich, Carleton University
There has been a growing interest in spacecraft formation-flying for space science applications.
Such missions will require an accurate and efficient dynamics model, on-board the flight computer,to calculate and control the desired relative motion. Hence, an analytical dynamics model which canbe applied to eccentric orbits and includes perturbations that can provide an increase in accuracy andefficiency. This paper achieves an accurate analytical solution of relative motion between two
spacecraft by propagating each spacecraft’s classical orbital elements forward in time andcalculating the relative position of the chaser spacecraft at each time-step.

9:00

AAS Second Order Analytical Solution for Relative Motion on Arbitrarily Eccentric Orbits
19-364 Matthew Willis, Stanford University; Simone Damico, Stanford University; Alan Lovell
Analytical solutions describing the relative motion of two spacecraft in close proximity are desirable
for onboard implementation of guidance and navigation algorithms. A new, second-order, Cartesianstate solution applicable to orbits of arbitrary eccentricity has been derived by extension of the firstorder Yamanaka-Ankersen solution through perturbation methods. The new solution is shown togive better accuracy than existing first-, second-, and third-order translational state solutions over awide range of orbit eccentricities and inter-spacecraft separations when compared to 2-bodydynamics.

9:20

AAS Simultaneous Localization and Mapping for Satellite Rendezvous and Proximity
19-282 Operations Using Random Finite Sets
Lauren Schlenker; Mark Moretto, University of Colorado Boulder; David Gaylor, NASA
Goddard Space Flight Center; RICHARD LINARES, Massachusetts Institute of Technology
Current approaches to spacecraft relative navigation require computationally expensive dataassociation and precise a priori maps and can have difficulties with clutter measurements. Recently,
new estimation filters based on random finite sets (RFS) have emerged that have shown muchpromise in addressing these issues. RFS based filters have been successfully applied to
Simultaneous Localization and Mapping (SLAM) for terrestrial navigation. This paper proposes
using an RFS-SLAM approach for spacecraft relative navigation and presents simulation results
demonstrating the feasibility of using RFS-SLAM for autonomous, precise relative navigation to
support on-orbit assembly and servicing of spacecraft or asteroid/comet circumnavigation andsample return.

10:00

10:20
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Analysis fo a swarm deployment for very low Earth orbit operations
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19-582 Bogdan Udrea, VisSidus Technologies, Inc.
Preliminary results of orbit analysis for a 12-space vehicle swarm are presented

10:40

AAS Rapid Algorithm for Satellite Close Approaches Determination
19-501 Huijiang Wang, Beihang University; Xiucong Sun; Chao Han, Beihang University
A rapid algorithm to determine the satellite close approaches is presented in this paper. Close
approaches determination is vital for satellite safety and collision avoidance, this paper proposed anadaptive piecewise interpolation technique to rapidly compute the close approaches. The entry-andexit opportunities are determined by the close approach function, the algorithm adopts forth-orderderivative and “half-value consistency check” technique to control the approximation error andinterpolation step. The algorithm is applicable for non-circular and perturbed orbits. Numericalsimulations show that, compared with the exhaustive search, the adaptive algorithm achieves over
90% decrease in computation time with adequate accuracy.

11:00

AAS A Tip-Tilt Hardware-in-the-loop air-bearing test bed with physical emulation of the
19-511 relative orbital dynamics
Ayansola Ogundele, Naval Postgraduate School; Josep Virgili-Llop, Naval Postgraduate
School; Marcello Romano, Naval Postgraduate School
This paper presents the development of a hardware-in-the-loop air bearing test bed that is capable ofphysically emulating the relative orbital dynamics. Typically, air bearing test beds consist of test
vehicles operating on top of a planar and horizontally-leveled surface. These test beds have been
widely adopted but they are limited to reproduce short maneuvers where the vehicles are in very
close proximity of each other. Here, we propose to emulate the relative orbital dynamics bydynamically changing the inclination of the operating surface. Finally, a maneuver example
showcasing the capabilities of the prototype implementation is provided.

Session 20: Trajectory Design & Optimization IV
Wednesday, Hana
Chair: Atri Dutta, Wichita State University
8:00

AAS Time-Optimal Repointing Maneuver of a Rigid Spacecraft with One Degree of
19-361 Freedom for Final Attitude
Yuanzhuo Geng; Chuanjiang Li; Yanning Guo, Harbin Institute of Technology
This paper deals with the problem of time-optimal repointing maneuver of a rigid spacecraft that
performs a staring operation. It only contrains the orientation of the body-fixed optic axis and thus
the final rotation of the spacecraft about optic axis is free. The problem is first formulated andsolved using a numerical method. Motion characteristics and four-switch solutions are presented.
Furthermore, a simple yet efficient eigenaxis determination method under eigenaxis maneuver
scheme is proposed in which eigenaxis direction is determined analytically to minimize manerver
time. Numerical results are evaluated to demonstrate the effectiveness of the proposed method.

8:20

AAS

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Series Solution for Motion in an Arbitrary Potential Field
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19-443 Nathan Strange, NASA / JPL
In this paper, the equations of motion for a test particle in an arbitrary potential field is solved as aformal power series. This solution is in terms of the time derivatives of the motion of the test
particle. These derivative may be used to construct a Taylor series for the motion of the particle inthe vicinity of given initial conditions.

8:40

AAS Science Orbits Design for The Lunar CubeSat EQUULEUS and for The Phobos
19-389 Sample Return Mission MMX
Takuya Chikazawa, University of Tokyo; Nicola Baresi, Institute of Space andAstronautical Science; Naoya Ozaki, ISAS, JAXA; Stefano Campagnola, Jet Propulsion
Laboratory; Yasuhiro Kawakatsu, JAXA / ISAS
We present the candidate science orbits for two JAXA missions, satisfying science and flight systemconstraints, including thermal and power budgets. To minimize the eclipse time, we restricted thedesign space to synodic resonant periodic orbits, with a period that take a certain ratio of the synodic
period, which is a period where geometry of three celestial bodies repeats the same relative
geometry. We introduce two key design parameters, synodic ratio and elongation, that we vary to
maximize the science benefits and enforce a maximum eclipse time constraint.

9:00

AAS MULTI-OBJECTIVE OPTIMIZATION OF LOW THRUST TRAJECTORIES FOR
19-398 PROPELLANT MASS, TIME OF FLIGHT, AND RADIATION DOSE
Christopher Lorenz, The Aerospace Corporation; Lake Singh, The Aerospace Corporation;
Jose Guzman, The Aerospace Corporation
Low thrust trajectories typically trade propellant usage and transfer time. Radiation dosage istraditionally minimized using transfer time as a surrogate, which may not fully capture the radiation
exposure of the satellite. This paper treats radiation dose directly by adopting a multi-objective
optimization approach with the inclusion of a radiation model to explore the trade-space oftrajectory options for the objectives of minimum propellant usage, minimum transfer time, andminimum radiation dose. Results indicate that trajectories are available that offer decreased
radiation dose at the expense of increased transfer time and/or increased propellant usage, providing
increased flexibility for mission planners.

9:20

AAS A Relaxation Approach for Hybrid Multi-Objective Optimal Control: Application to
19-406 Multiple Debris Removal Missions
Lorenzo Angelo Ricciardi, University of Strathclyde; Massimiliano Vasile, University ofStrathclyde
This paper presents a novel approach to the solution of multi-phase multi-objective hybrid optimal
control problems. The proposed solution strategy extends previous work which integrated the Direct
Finite Elements Transcription (DFET) method to transcribe dynamics and objectives, with amemetic strategy called Multi Agent Collaborative Search (MACS). The approach is first tested ona motorised travelling salesmen problem, for which solutions are available in the literature, and thenapplied to the mission design of a multiple debris removal mission.

10:00

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10:20

AAS Low Energy Escape Using Tube Dynamics Associated with Quasi-halo Orbit
19-408 Kazutoshi Takemura, Waseda University; Nicola Baresi, Institute of Space andAstronautical Science; Yasuhiro Kawakatsu, JAXA / ISAS; Hiroaki Yoshimura,
Waseda University
In spacecraft trajectory design based on dynamical theory, research extended to the spatial problem
is insufficient. This work discusses on designing Mars escape trajectory in the three-body system via
invariant manifolds. In contrast with the conventional methods, we propose to use an invariant
manifold from a quasi-halo orbit. We have computed a quasi-halo orbit and its manifold. We
investigate how invariant manifolds of quasi-periodic orbits can provide new escape trajectories
from the Martian system in the circular restricted three-body problem.

10:40

AAS QUASI-SATELLITE ORBIT TRANSFERS VIA MULTI-REVOLUTIONAL
19-422 PERIODIC ORBITS
Kento Ichinomiya, Waseda University; Nicola Baresi, Institute of Space and Astronautical
Science; Yasuhiro Kawakatsu, JAXA / ISAS; Tomohiro Yanao, Waseda University
Several international teams are currently planning to send probes around the Martian moons, Phobos
and Deimos, using single-revolutional periodic quasi-satellite orbits or SP-QSOs. While the orbital
stability of SP-QSOs is well known, it is still unclear whether reasonable transfer orbits can befound from/to or between them. This paper investigates the application of multi-revolutional
periodic quasi-satellite orbits or MP-QSOs to design transfer orbits between SP-QSOs. In thisresearch, we generate MP-QSOs from bifurcation points of the SP-QSO family using standard
predictor/corrector procedures, classify them based on practical rules for orbit design and consider
their application to orbit transfer problems.

11:00

AAS Integrated Optimization of Ascent Trajectory and SRM Design of Multistage Launch
19-424 Vehicles
Lorenzo Federici, Sapienza University of Rome; Alessandro Zavoli; Guido Colasurdo,
Università di Roma Sapienza; Lucandrea Mancini; Agostino Neri, ESA ESRIN - VEGA
Integrated Project Team
This paper presents a methodology for the concurrent first-stage preliminary design and ascent
trajectory optimization, with application to a VEGA-derived Light Launch Vehicle. The reuse as
first stage of an existing upper-stage (Z40) requires a grain redesign, to account for the
mutated operating conditions. An optimization code based on the parallel running ofseveral Differential Evolution algorithm is used to find the optimal internal pressure law during Z40
operation, together with the optimal thrust direction and other relefant flight parameters of
the ascent trajectory. Payload injected into a target orbit is maximized, while respecting
multiple design and path constraints. Numerical results for SSO injection are presented.

11:20

AAS Using the Paramat System in Mission Analysis and Design
19-442 Darrel Conway, Thinking Systems, Inc.
Thinking Systems is building a parallel processing mission analysis tool, Paramat, for large scale
analysis problems. Paramat is an extension of the General Mission Analysis Tool (GMAT), taking
the GMAT system as the core numerical engine for analysis in a parallel processing
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seek and find viable trajectories. In this paper, the combination of Paramat and GMAT is used fortwo problems: a transfer from low Eaerth orbit to a lunar flyby, and an Earth to Venus transfer
starting from a piggybacked ride on another vehicle.

11:40

AAS Missed Thrust Analysis and Design for Low Thrust Cislunar Transfers
19-426 Steven McCarty, NASA Glenn Research Center; Daniel Grebow, NASA / Caltech JPL
In a continuation of previous analysis of low thrust cislunar transfers, analysis is completed tounderstand and address their sensitivities to periods of unplanned thrust outages. Previous studies
have addressed this challenge for interplanetary trajectories where the flight times are long and the
dynamics are relatively benign, whereas this study will address the challenge in a more chaotic
cislunar regime where the appropriate design strategies may be different. This paper includes missed
thrust analysis, one or more approaches to missed thrust design, and general thoughts,
considerations and strategies for addressing missed thrust for a set of reference cislunar transfers.

Session 21: Space Situational Awareness & Flight Dynamics Operations
Wednesday, Kapulua
Chairs: Ryan Park, Jet Propulsion Laboratory & Nathan Strange, Jet Propulsion Laboratory / California
Institute of Technology
13:30

AAS Real-Time Telescope Tasking for Custody and Anomaly Resolution Using Judicial
19-534 Evidential Reasoning
Daniel Aguilar Marsillach, University of Colorado - Boulder; Shahzad Virani, Universityof Colorado - Boulder; Marcus Holzinger, University of Colorado Boulder; Moses Chan;
Prakash Shenoy, The University of Kansas
Sensor tasking for space situational awareness remains an area where tactical improvements can be
made. At its core, tasking boils down to resource allocation and decision-making. A new form of which ishypothesis based using Dempster- Shafer evidential reasoning to mathematically formulate hypotheses
that need to be resolved. One such method, known as judicial evidential reasoning, lead to promising
results for unbiased hypothesis resolution under time constraints. This paper primarily focuses on
resolving new hypotheses, formulating new evidence to hypothesis belief mappings in Dempster-Shafer
theory, and implementing the algorithm in real-time with a narrow field of view telescope.

13:50

AAS Label Assignments in CubeSat Cluster Deployment Tracking
19-540 John Gaebler, University of Colorado at Boulder; Penina Axelrad
A Labeled Multi-Bernoulli filter is used to estimate the states and identities of multiple CubeSats
deployed in a cluster during the first few days in orbit. This work focuses on the label assignments
in a scenario combining labeled measurements provided by owner/operators with typical radarobservations. When objects are clustered, there can be enough uncertainty (in a priori positions andmeasurements) that labeled measurements cannot be unambiguously associated with specificobjects. A method is presented to probabilistically manage label assignments as additional
hypotheses within the LMB framework. A simulation of the 88-CubeSat deployment from PSLV37 demonstrates the approach.

14:10

AAS

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Automated Near Real-time Validation and Data Integrity Assessment Using an
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19-521 Unscented Schmidt Kalman Filter (USKF)
Thomas M. Kelecy, L3 Applied Defense Solutions
Quality of the data affects the quality of the derived orbit products and, in particular, data biases will
result in biased orbits and subsequent predictions. In this paper we demonstrate an automated nearreal-time assessment of data biases with an appropriately implemented Unscented Schmidt Kalman
Filter (USKF). Known biases that are not observable and cannot immediately be estimated areaccounted for as consider parameters. The work presents a multi-state filter which “unifies”
estimates of observable sensor performance parameters, when observable and when appropriately
vetted sensor or reference data are available, and demonstrates immediate performance benefits inthe state estimation process.

14:30

AAS DISTANT RETROGRADE ORBIT CONSTELLATIONS FOR RELATIVE-ONLY
19-551 NAVIGATION IN NEAR RECTILINEAR HALO ORBITS
Michael Volle, a.i. solutions, Inc.
The performance of relative-only navigation between the Gateway spacecraft in an NRHO and aconstellation of navigation relay spacecraft in Distant Retrograde Orbits (DROs) are examined andcompared to DSN tracking using a Square Root Information Filter (SRIF). Crewed orbit
disturbances such as CO2 and waste dumps, attitude deadbanding and momentum unloads aremodeled based on realistic attitude information for Gateway. Multiple constellation configurations
and tracking scenarios are examined using a closed-loop simulation where navigation errors informmaneuver planning and maneuver execution errors affect navigation performance.

14:50

AAS COGITATION OF SPACE CURVE PRINCIPLES FOR LAPLACE ORBIT
19-563 DETERMINATION
Brett Newman, Old Dominion Univ.; Alan Lovell
This paper investigates application of space curve principles to Laplace orbit determination with
benefits including new insights and computations. The curve traced out on a unit sphere, by thesatellite line-of-sight unit vector, is first established. The unit sphere track is then described with aFrenet coordinate system. The angular velocity of the Frenet axes and their relationship to the lineof-sight rates are developed. The angular velocity components provide new physical insights andfacilitate isolation of crossrange and downrange components. Advantages of transforming
measurement equations to the Frenet axes and transforming to angular velocity unknowns are
explored.

15:30

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Afternoon BreakAAS ACCURATE AND ROBUST ESTIMATION METHOD OF AUTONOMOUS ORBIT
19-569 DETERMINATION USING ACTIVE MANEUVERS AND INTER-SATELLITERANGING
Kota Kakihara, The University of Tokyo; Naoya Ozaki, ISAS, JAXA; Ryu Funase, The
University of Tokyo; Shinichi Nakasuka, The University of Tokyo
Autonomous orbit determination is a key technology for future low-cost and frequent deep-space
missions. Previous study shows that inter-satellite ranging is applicable to autonomous orbit
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determination in two-body problems by using active ΔV maneuvers. Orbit determination algorithm,
however, proposed in the previous study does not consider maneuver execution errors and orbit
determination accuracy become worse when there are ΔV execution errors. This paper proposes
more accurate and robust orbit determination algorithm considering ΔV execution errors. Numericalsimulation shows proposed method results improved orbit determination accuracy and more stableestimation than previous study.

16:10

AAS New Horizons 2014MU69 (Ultima Thule) Flyby Design and Execution
19-227 Gabe D. Rogers, The Johns Hopkins University Applied Physics Laboratory; Alice
Bowman, JHUAPL; Chris Hersman, JHUAPL; Ann Harch, Southwest Research Institute;Ann Harch, Southwest Research InstituteSince the encounter with the Pluto system in 2015, the New Horizons team has been preparing for a
flyby of the Kuiper Belt Object 2014MU69 (Ultima Thule). This paper discusses how the teamdesigned and executed the spacecraft encounter within the various constraints imposed after the
Pluto flyby. In addition to a brief overview of key spacecraft subsystems, it will describe how thedesign needed to accommodate for large uncertainties in the target’s position while minimizing
image smear during science observations. It will detail resource management, maneuver planning,and power and data downlink constraint management.

16:30

AAS Orbit Determination Simulation for Korea Pathfinder Lunar Orbiter Using
19-383 Sequential Estimation Approach
Young-Rok Kim, Korea Aerospace Research Institute; Young-Joo Song, Korea Aerospace
Research Institute; Jonghee Bae, Korea Aerospace Research Institute; Seok-Weon Choi,
Korea Aerospace Research Institute
The Korea Pathfinder Lunar Orbiter (KPLO) is Korea’s first lunar exploration program developed
by Korea Aerospace Research Institute and will be launched in late 2020. The KPLO will employ a
3.5 phasing loop and 100 km altitude lunar polar orbit. In this study, we introduce orbit
determination (OD) strategy of KPLO and demonstrate OD simulation results using sequential
estimation technique during trans-lunar and mission orbit phase. For OD accuracy assessment,
orbital element and position uncertainties are utilized for trans-lunar and mission orbit, respectively.
Finally, we confirmed that the simulated OD performance addresses the OD requirements of
KPLO.

16:50

AAS Single-Waypoint Guidance for Rotating Target Formation Flying
19-474 Armando Rolins, Embraer Executive Jets; Brian Kaplinger, Florida Institute of Technology
This paper addresses an autonomous rendezvous procedure between two spacecraft in close
proximity in which the chaser object is attempting to dock at a location on a rotating target. This
research proposes to use a fully closed-loop control to perform this kind of rendezvous andcompares the cost attained by three different control laws given the same problem parameters. The
proposed solution makes use of a single waypoint to avoid a trajectory which causes a collision
while meeting all boundary conditions. Proposed methods for the efficient choice of waypoint basedon a rigorous search are addressed.

Session22: Guidance, Navigation, and Control I
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Wednesday, Napili
Chair: Robyn Woollands, Jet Propulsion Laboratory

13:30

AAS Unscented Guidance for Zero-Feedback Reaction Wheel Slews
19-207 Lara Magallanes, Naval Postgraduate School; Mark Karpenko, Naval Postgraduate School
Spacecraft control system failures are often mission ending even when the payload remains
operational. Few, if any, methodologies currently exist to enable an accurate slew to a target in theabsence of feedback. An approach will be explored using unscented guidance to expand the limitsof control system operation by enabling attitude control authority to be recovered in the event offeedback sensor failures. This paper will explain the mechanism underlying the unscented guidance
solution that enables a slew to a target to be completed in the absence of feedback.

13:50

AAS Modern Aerocapture Guidance to Enable Reduced-lift Vehicles at Neptune
19-221 Casey Heidrich, University of Colorado Boulder; Soumyo Dutta, NASA Langley ResearchCenter; Robert Braun, University of Colorado Boulder
Modern predictor-corrector guidance strategies have shown promise in recent years to provide
robust control schemes in-situ. This research implements modern predictor-corrector guidance formoderate-lift vehicles at Neptune. Previous studies required vehicles with high lift-to-drag ratios toaccount for in-flight uncertainties. Reducing lift-to-drag requirements will enable heritage flightproven vehicles to perform aerocapture, greatly improving options for Neptune exploration.

14:10

AAS A DIRECT CHEBYSHEV PICARD ITERATION APPROACH TO PERTUBED
19-246 BALLISTIC PROPAGATION AND LAMBERT BOUNDARY VALUE PROBLEMSCharles Wright, Cummings Aerospace
A simplified approach to Modified Chebyshev Picard Iteration (MCPI) is introduced which relies on
exact analytical integration of the Chebyshev polynomials. Unlike other MCPI methods, the Direct
Chebyshev Picard Iteration (DCPI) approach does not calculate separate polynomial seriescoefficients for each integral. It simply applies the original series coefficients to the integrated
Chebyshev polynomials to form invariant integral transformation matrices. The boundary
conditions are applied after the integrations to perform either a Lambert Boundary Value Problem(BVP), or a ballistic propagation Initial Value Problem (IVP) in a way that is intuitive to anyone
familiar with basic integral Calculus.

14:30

AAS Using GNSS Receiver at Near Rectlinear Halo Orbit
19-276 Yu Nakajima, JAXA; Toru Yamamoto, Japan Aerospace Exploration Agency; Hitoshi Ikeda,
Japan Aerospace Exploration Agency
In this paper, feasibility to use GNSS receiver on Cis-Lunar Near Rectilinear Halo Orbits (NRHO)
was examined. We describe the purpose, overall picture of using GNSS receiver on NRHO. The
receiver was based on those used at geostationary orbit and optimized for the Cis-lunar orbit. In
addition, we verify the feasibility of the proposed idea by presenting received power analysis,
dilution of precision analysis, and navigation performance simulation. Furthermore, we propose an
example case of using GNSS on NRHO from the analysis results.

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FINAL PROGRAMAAS Adaptive Guidance with Reinforcement Meta Learning
19-293 Brian Gaudet, Deep AnalytX, LLC; RICHARD LINARES, Massachusetts Institute ofTechnology
This paper proposes a novel adaptive guidance system developed using reinforcement meta learningwith a recurrent policy and value function approximator. The use of recurrent network layers allows
the deployed policy to adapt real time to environmental forces acting on the agent. We evaluate theperformance of the agent trained via reinforcement meta-learning on four difficult tasks. These tasks
include a safe Mars landing with random engine failure and a landing on an asteroid with unknown
environmental dynamics. We also demonstrate the ability of a recurrent policy to navigate using
only Doppler radar altimeter returns, thus integrating guidance and navigation.

Afternoon Break

15:50

AAS Drag-Free and Attitude Control System, lessons learned from MICROSCOPE flight
19-303 (2016-2018)
Pascal PRIEUR, Centre National d'Etudes Spatiales; Stéphanie DELAVAULT, Centre
National d'Etudes Spatiales; Thomas LIENART; Manuel RODRIGUES, ONERA; Bernard
FOULON, ONERA; John MOYARD, Centre National d'Etudes Spatiales; Alain ROBERT,
Centre National d'Etudes Spatiales; Pierre-Yves GUIDOTTI, Centre National d'Etudes
Spatiales
Microscope is a CNES-ESA-ONERA-CNRS-OCA-DLR-ZARM mission dedicated to the test of theEquivalence Principle with an improved accuracy of 10-15. The 300kg drag-free microsatellite has
recently completed its 2-year flight. The Drag Free and Attitude Control System (DFACS) aims at
giving a pure gravitational motion to the scientific instrument. The paper presents the main lessons
learnt from this mission, from phase A to the de-orbitation: the key choices of DFACS architecture,
the performance observed in flight, comparison to other missions (Gravity-Probe-B, GOCE LisaPathfinder). What could be a good DFACS design for Microscope II ?

16:10

AAS A New Guidance and Control Architecture for Accurate Orbit Injection
19-305 Mauro Pontani, Sapienza University of Rome ; Fabio Celani, Sapienza University of Rome
- School of Aerospace Engineering
Orbit insertion maneuvers represent a crucial issue in several mission scenarios, both for spacecraft
orbiting the Earth and for payload release from an ascent vehicle. This research considers a new
guidance and control architecture based on the combined use of (i) the variable-time-domainneighboring optimal guidance technique and (ii) the constrained proportional-derivative algorithm
for attitude control, with the aim of achieving precise orbit insertion, in the presence of nonnominal
flight conditions. Extensive Monte Carlo (MC) campaigns demonstrate that the guidance andcontrol architecture at hand is effective for determining precise and fuel-efficient orbit injection
maneuvers.

16:30

AAS Data-driven model-free adaptive sliding mode attitude control of combined spacecraft
19-313 Yueyong Lyu, Harbin Institute of Technology; Han Gao; Guangfu Ma, Harbin Institute ofTechnology; Zhiyong She

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In this paper, a novel data-driven model-free adaptive sliding mode attitude control (MFASMC)
method is proposed for the postcapture combined spacecraft in the presence of unknown
mathematical model and external disturbance. A sliding-mode-based supplementary controller isintroduced to improve the tracking performance of MFAC in terms of robustness. Compared withthe existing works, the designed control scheme only utilizes the attitude angle and attitude angularvelocity of the combined spacecraft and no mechanism model of combined spacecraft is required.

16:50

AAS AN ANALYSIS OF LOW-THRUST GUIDANCE ALGORITHMS AROUND SMALL
19-351 BODIES
Donald Kuettel, Colorado Center for Astrodynamics Research; Jay McMahon, CCAR
(Colorado Center for Astrodynamics Research)
This paper examines the performance of low-thrust guidance algorithms around small bodies.
Current small body missions (e.g. OSIRIS-Rex and Rosetta) use chemical thrusters which are
inefficient for maneuvering in the microgravity environment around small bodies. When comparedto impulsive propulsion systems, low-thrust propulsion provides a smaller force with greater
efficiency while still having a high control authority. By perturbing the initial conditions or
dynamics of a nominal trajectory, the performance of the guidance algorithms can be tested. It ishypothesized that these low-thrust guidance algorithms will provide accurate, mass-efficient, androbust guidance to a perturbed spacecraft trajectory around small bodies.

Session 23: Proximity Missions & Formation Flying II
Wednesday, Kula
Chair: Roby Wilson, Jet Propulsion Laboratory
13:30

AAS Random Finite Set Theory and Optimal Control of Large Spacecraft Swarms
19-482 Bryce Doerr, University of Minnesota; RICHARD LINARES, Massachusetts Institute ofTechnology; Pingping Zhu, Department of Mechanical and Aerospace Engineering,
Cornell University; Silvia Ferrari, Sibley School of Mechanical and Aerospace Engineering
Cornell University
Controlling large swarms of robotic agents has many challenges including, but not limited to,computational complexity due to the number of agents, uncertainty in the functionality of each agent
in the swarm, and uncertainty in the swarm's configuration. This work generalizes the swarm stateusing Random Finite Set (RFS) theory and solves the control problem using model predictive
control (MPC) and iterative linear quadratic regular (ILQR). This work uses information divergenceto define the distance between swarm RFS and a desired distribution. The RFS control solution isapplied to the spacecraft relative-motion problem showing the viability for this real-world scenario.

13:50

AAS Network architecture for UWB-based relative navigation of multiple spacecraft in
19-349 formation flightNobuhiro Funabiki, the University of Tokyo; Satoshi Ikari, The University of Tokyo; Ryu
Funase, The University of Tokyo; Shinichi Nakasuka, The University of Tokyo
To realize a formation flight of multiple spacecraft, relative navigation among the member
spacecraft is essential. In this paper, the use of an Ultra-Wide Band (UWB) positioning system forspacecraft formation flight is proposed. When a formation is composed of tens or hundreds ofPage 75

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spacecraft, it is not realistic to measure relative distances among the all member spacecraft in termsof the time consumption for UWB ranging. This paper discusses the kinds of ranging network basedon UWB devices are effective to increase the accuracy of the relative navigation.

14:10

AAS Pose Estimation For Non-Cooperative Spacecraft Rendezvous Using Neural Networks
19-350 Sumant Sharma, Stanford University; Simone Damico, Stanford University
The paper presents a novel pose estimation technique that uses neural networks to determine thepose of a target spacecraft from a single image. The pose from the networks is used for the
initialization as well as the measurement update of a multiplicative kinematic kalman filter. In
contrast to current techniques, this technique does not require the assumption of small baselinechanges between subsequent images during tracking or favorable relative motion duringinitialization. The technique is trained and validated using the Spacecraft Pose Estimation Dataset(SPEED) benchmark. Sensitivity analysis of the performance with respect to synthetic image
fidelity is presented.

14:30

AAS Spacecraft Pose Estimation and Swarm Localization Performance Under Varying
19-405 Illumination and Viewing Conditions
William Bezouska, University of Southern California
Spacecraft swarm localization using relative pose measurements from passive cameras will be
impacted by viewing conditions including relative solar angle and relative orientation between thetarget and the observer. This work attempts to assess the pose estimation performance under all
viewing geometries by simulating stereo images using both computer graphics rendering and real
images of a spacecraft model under partially collimated lighting. The relative pose estimation error
when using stereo vision and point cloud registration is computed. This error information is thenincoprorated into an Extended Kalman Filter cooperative localization scheme to determine theoverall impact on swarm localization.

14:50

AAS Optimal Inspection of a Nadir-Pointing Satellite with Dynamic Angle Constraints
19-407 Mark Mercier; Kirk W. Johnson, US Air ForceRecent advancements in on-orbit proximity operations facilitate more complex inspection missionsof active satellites with active sensors. These sensors can be simulated by keep-out cones; many
will be nadir-pointing, but others may change direction in the local-horizontal/local-verticalframe. These keep-out cones define dynamic angle constraints for a satellite on a fuel-optimal
inspection trajectory. This study will pose and solve the corresponding optimization problem using
the multi-phase Gauss Pseuspectral Solver, GPOPS-II, with linearized Hill-Clohessy-Wiltshire
dynamics. This solution method will allow for the flexibility to incorporate various dynamic keepout cone constraints as well as desired viewing angle constraints.

15:10

AAS Impact of Internal Heating on Spacecraft Thermal Signature
19-471 Scott Carnahan, Colorado Center for Astrodynamics Research; Hanspeter Schaub,
University of Colorado; Benjamin Lane, Draper Lab
Infrared (IR) vision-based navigation has gained more interest recently for uncooperative
rendezvous because it can produce clear images regardless of eclipse conditions. Image matchingalgorithms have been demonstrated as feasible for spacecraft recognition in IR, but these methods

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often struggle with attitude ambiguity due to spacecraft symmetry. This work aims to address theissue of attitude ambiguity by the incorporation of additional IR-visual information due to internal
thermal systems. Simulated IR images of spacecraft are generated using internal quasi-1D thermal
networks combined with external radiation models.

15:30

Afternoon Break15:50

AAS Optimal Range Observability Maneuvers for Angles-Only Navigation in Elliptic
19-535 Orbits
Francisco José Franquiz Maldonado, Embry-Riddle Aeronautical University; Bogdan
Udrea, VisSidus Technologies, Inc.; Troy Henderson, Embry-Riddle Aeronautical
University
A generalization of existing methods for planning optimal observability trajectories for spacecraft
using angles-only measurements of a non-cooperative target is proposed. Dynamics are modeledusing a state transition matrix applicable to elliptical planetary orbits of arbitrary eccentricity.
Together with a pseudo-time parameterization of relative trajectories, transfers between any two
feasible flight paths can be calculated without the need for numerical integration. Simulation results
are presented which compare representative examples of proximity operations in low Earth orbit atdifferent eccentricities. Results include a preliminary verification procedure which uses unscented
filtering to demonstrate improved navigational performance due to the planned maneuvers.

16:10

AAS Prototype Test Results of IVA Hopping Maneuvers of an Autonomous Robotic Vehicle
19-539 Katrina Alsup, Naval Postgraduate School; Justin Komma, Naval Postgraduate School;
Josep Virgili-Llop, Naval Postgraduate School; Marcello Romano, Naval Postgraduate
SchoolHopping is an alternative mobility approach for intravehicular activities (IVA). In a hopping
maneuver a spacecraft uses its robotic manipulator to execute a hop between two locations. In
previous work we have derived the formulation of IVA hopping maneuvers. Here we use thisderivation to develop a series of controllers for the three phases of the hopping maneuver. We thenuse these controllers on NASA's Astrobee free-flyer to simulate IVA hopping maneuvers inside theInternational Space Station. Here the controllers implementation and the simulation results arepresented in details. The video of a simulated maneuver can be found athttps://youtu.be/QBWxiiJGZmY.

16:30

AAS Output Regulation Control for Satellite Formation Flying Using Differential Drag
19-307 Mohamed Shouman, Department of Aeronautics and Astronautics, Kyushu University.; Mai
Bando, Kyushu University; Shinji Hokamoto, Kyushu University
This paper studies the viability of using differentials in drag with thrusters for satellite formation
flying (SFF) missions. For the atmospheric drag control, it is revealed that the tracking problem is
not solvable, therefore thrust input in another direction is added to achieve asymptotic tracking forexogenous SFF system. The output regulator algorithm is derived based on a linear ScheiwgartSedwick model for SFF using atmospheric drag and thrust force and subject to saturation. All
numerical simulations for relative models and high precision orbit propagator are implemented tovalidate the stability and analyze the performance of the proposed control algorithm.

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16:50

AAS AUTONOMOUS SPACECRAFT RENDEZVOUS BY LINE-OF-SIGHT CONTROL
19-367 George Zhu, York University; Peng Li, York University
The paper investigates the autonomous spacecraft rendezvous by line-of-sight control. Nonlinear
model predictive control method is applied for the problem and it is formulated in terms of line-ofsight range and azimuth angle. The numerical results show that the newly proposed line-of-sight
nonlinear model predictive control scheme is able to effectively generate optimized approachtrajectories with satisfactory control accuracy and the proposed method is insensitive to themeasurement uncertainties.

17:10

AAS 3-Dimensional Reachable Set Applications to Multi-Spacecraft Trajectory
19-475 Coordination
Chandrakanth Venigalla, University of Colorado Boulder; Daniel Scheeres, University ofColorado at Boulder
To work towards advancing mission design capabilities for spacecraft formations and constellations,
we investigate the application of reachable sets to solve coordination problems. We generate threedimensional reachable sets that give the set of reachable orbits for a given spacecraft in semimajoraxis-eccentricity-inclination space. We verify the delta-V optimality of these sets which are
generated using an analytic control law, and then use the sets to explore optimal rendezvous orbits
for systems of 2 and more spacecraft. Rendezvous optimality criteria includes, but is not limited tototal delta-V. We further investigate how these sets allow us to find optimal evasion strategies.

Session 24: Trajectory Design & Optimization V
Wednesday, Hana
Chair: Roberto Armellin, University of Surrey
13:30

AAS Q-Law Aided Direct Trajectory Optimization for the High-Fidelity, Many-Revolution
19-448 Low-Thrust Orbit Transfer Problem
Jackson Shannon, University of Maryland; Martin Ozimek, The Johns Hopkins University
Applied Physics Laboratory; Justin Atchison, JHU Applied Physics Laboratory; Christine
Hartzell
Low-thrust spacecraft trajectory optimization for the many-revolution orbital transfer problem is
especially challenging due to the dimension of the problem and the fact that perturbation effects
play a role in preventing accurate analytical solutions. This analysis seeks to simplify the calculationof the non-averaged, high-fidelity spiral trajectory through the use of the well-known Q-Law
Guidance. Here, Q-Law is used to seed various phases of the direct trajectory optimization problem.
We demonstrate the trade space between calculation speed of Q-Law and the optimality of the full
optimization problem on the common example problem of the GTO to GEO transfer.

13:50

AAS Visual Interactive Trajectory Design
19-449 Ravishankar Mathur, Emergent Space Technologies, Inc.
A method of altering trajectories via visual “grab-and-drag” gestures with immediate graphicalresponse, called Visual Interactive Trajectory Design (VITD), is presented. The various components
of VITD are defined (e.g. draggable objects), and how they affect the trajectory is discussed. An

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implementation of VITD is demonstrated that uses the General Mission Analysis Tool (GMAT) to
propagate trajectories, and visualizes them in realtime using the OpenFrames 3D visualization API.
Examples of using VITD are shown, including finding a lunar free-return trajectory by simply
dragging the trajectory’s initial velocity vector. The benefits of VITD to rapidly generating initialguess trajectories for optimization are explored.

14:10

AAS On-Orbit Servicing Mission Design in a Dynamic Client Environment
19-451 Jennifer Hudson, Western Michigan University; Daniel Kolosa
Mission design for a versatile, robotic servicing spacecraft can be formulated as a combinatorialoptimization problem. If a servicing spacecraft operates in a dynamic environment, where newclient spacecraft with urgent servicing needs emerge at different times, then decisions about
operational sequencing and client-to-client transfer trajectories will play a significant role in overall
mission success and profitability. This problem is investigated using stochastic methods. A model
for future client demand is proposed and Monte Carlo simulations are used to evaluate likely
mission scenarios. High-thrust and low-thrust cases are considered.

14:30

AAS Dynamic Optimization for Large Scale Active Debris Removal Mission Design
19-461 Applications
Tyler Doogan, Texas A&M University; Manoranjan Majji, Texas A&M University, College
StationThis paper uses a multi-step approach to tackle large scale (decades long) ADR mission design.
Firstly, a clustering algorithm is applied to a large list of high risk debris objects, splitting them into
groups of a user defined size (5 in this case). Each cluster represents a separate mission, each ofwhich occurs in a successive, user-defined, timespan. Then a dynamic traveling salesman problem issolved for each of these clusters in order to find the optimal order of visitation for each mission.

14:50

AAS Modeling Attitude-Dependent Maneuver Errors with Polynomial Chaos Expansions
19-464 Brandon Jones, University of Texas at Austin
This paper presents a framework for including random inputs on the unit sphere in Polynomial
Chaos Expansions (PCEs) to decouple attitude dependent execution errors from magnitude
errors. To maintain efficiency in the expansion, the basis functions must be orthogonal with respect
to the density function of the inputs. Due to the unit norm constraint, random directions in threedimensional space are defined on the unit sphere, which requires an extension to existing PCE
methods. This paper presents the mathematical framework and revisits previous test cases in theliterature that leveraged directional quantities.

15:30

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Afternoon BreakAAS Disposal, Deployment, and Debris in Near Rectilinear Halo Orbits
19-466 Diane Davis, a.i. solutions, Inc.; Kenza Boudad, Purdue University; Sean Phillips;
Kathleen C. Howell, Purdue University

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A proposed Gateway facility in a lunar Near Rectilinear Halo Orbit (NRHO) will serve as an outpost
in deep space, with spacecraft periodically arriving and departing. Departing objects will include
Logistics Elements, requiring safe disposal, cubesats, deployed to various destinations, and debris
objects, whose precise paths may be unknown. Escape dynamics from NRHOs are complex;
primarily influenced by the Earth and Moon within the orbit, spacecraft are significantly impacted
by solar gravity upon departure. The current investigation explores the dynamics of departure fromthe NRHO, including the risk of debris recontact, safe heliocentric disposal, and deployment toselect destinations.

16:10

AAS Automating Tour Design with Applications for Europa Lander
19-324 Kaela Martin, Embry-Riddle Aeronautical University (ERAU); Damon Landau, NASA /JPL; Stefano Campagnola, Jet Propulsion Laboratory; Tim McElrath, JPL/Caltech
Creating a tour design can involve a great deal of trial and error to produce a viable end-to-end
trajectory. This paper highlights a new methodology which starts with a broad-search patch-conic
tool and ends with an integrated optimizer. The tool is applied to Europa Lander starting at thesecond Ganymede flyby and ending with the first Europa flyby to produce a trajectory option for a2033 landing date.

16:30

AAS Robust Trajectory Design for Asteroid Orbiters
19-486 Erica Jenson, University of Colorado Boulder; Daniel Scheeres, University of Colorado at
Boulder
In low gravity environments with significant uncertainty, robust trajectories may be preferred overfuel optimal trajectories. This paper will investigate two parametric robust optimization methods
with applications to asteroid missions, where the robust-optimal solution will minimize the varianceof error in a terminal constraint. The first method will address trajectories with open loop control
and the second will allow downstream maneuvers to be redesigned given new state estimates
throughout the trajectory. Robust trajectories will be designed for three cases: orbit corrections
using the Clohessy-Wiltshire equations, orbit transfers in the two-body problem, and an asteroid
approach trajectory approximated with rectilinear motion.

16:50

AAS Mission Designs for Human Lunar Surface Access from an Earth-Moon Near
19-477 Rectilinear Halo Orbit
Raymond Merrill, NASA Langley Research Center; Min Qu, AMA; David Komar, NASA
Langley Research Center; Dan Mazanek, NASA Langley / Space Mission Analysis Branch;
Daniel Tiffin, NASA LaRC / Space Mission Analysis Branch
The mission design trade space for human lunar return has multiple staging locations, varied vehicle
functional responsibilities, and options for partial to full system evolution to reusability. These
options fit within a constraint space governed by NASA’s current investments, current and near
future commercial launch vehicle capabilities, and the recent confirmation of ice at the Moon’s
poles. When assessing Human lunar return architectures it is important to understand both thenominal mission design and contingency options associated with each transportation architecture
option prior to selecting one and beginning to set requirements for individual elements.

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Thursday, January 17
Session 25: Guidance, Navigation, and Control II
Thursday, Kapulua
Chairs: Troy Henderson, Embry-Riddle Aeronautical University & Christopher Scott, The Johns Hopkins
University Applied Physics Laboratory
8:00

AAS New improvements on atmospheric trajectory optimization of a rocket reusable first
19-315 stage with turbo engines
Eric Bourgeois, CNES; Jérémie Hassin; Nicolas Praly
Following paper 16-230, methodological improvements are presented to optimize the trajectory of areusable microlauncher first stage. The stage comes back to the launch site thanks to aerodynamics
and turbo engines. Thrust characteristics of turboengines depend on flight conditions, and allow awide thrust modulation, challenging methods to optimize rocket trajectory. Firstly, two simplified
methods were combined to benefit from their respective assets, this process allowing to ensure
feasible trajectory, with no guaranty on optimality. Now is presented a method relying on optimal
control theory taking into account a turboengine model defining relationships between flight
conditions, thrust and kerosene consumption.

8:20

AAS Coordination of a Decentralized Satellite Swarm with Internal Formation
19-522 John McCormack, UNH Mechanical Engineering; May-Win Thein, University of New
Hampshire
An Artificial Potential Field (APF) using Sliding Mode Control (SMC) is proposed for control andcoordination of spacecraft in constellation/swarm missions. The APF will be analyzed to ensuresatisfaction of necessary assumptions made for a given proof of stability: specifically,
gain boundedness and equilibrium locations. Attractive nodes will be introduced to create adecentralized spacecraft swarm capable of aggregating a formation with additional agents present.
Gain ranges for the APF equation will be determined to ensure that spacecraft maintain “safedistance”. Numerical simulations will be presented to demonstrate feasibility of this swarm
coordination control technique.

8:40

AAS Integrated Targeting, Guidance, Navigation and Control for Unmanned Aerial
19-542 Vehicles
Evan Kawamura; Dilmurat Azimov, University of Hawaii at Manoa
This study aims to develop targeting, guidance, navigation and control (TGNC) functions and theirintegration for applications. Due to its simplicity and accessibility, the INAV software has been
selected a framework for the proposed integration. It is shown that the proposed study changes thecurrent PID control laws and the utility of new nonlinear control schemes allow us to leverage theflight autonomy thereby paving the way for creating an autonomous TGNC technology with realtime target-relative guidance capabilities. An illustrative example is considered to demonstrate theutility of GNC functions in INAV to perform a rolling maneuver.

9:00

AAS MULTI-SENSOR NAVIGATION WITH SPACECRAFT DYNAMICS BASED ON
19-391 FACTOR GRAPH
Yongchao Zhao; Shijie Zhang; Botian Zhou; Xu Tang, Research Center of Satellite

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Technology, Harbin Institute of Technology; Kaicheng Zhang
This paper presents a new method for improving accuracy of factor graph based integrated
navigation. Traditional algorithms, without updating velocities covariance matrix, suffer thelimitation of estimation accuracy. To address this problem, we incorporate the aircraft dynamics into
the factor graph which can predict the aircraft state and its variance. Meanwhile, we build the factor
graph model of Inertial Measurement Unit, Global Positioning System receivers and star sensor,
which can update the position, velocity, orientation and angular velocity of aircraft and its variance.
The simulation is expected to demonstrate the proposed method can improve the navigation
accuracy compared with the traditional methods.

9:20

10:00

AAS Gyroscope-Based Spacecraft Angular Rate and Mass Properties Estimation
19-429 Cameron Helmuth; Jacob Darling, Air Force Research Laboratory; Kyle DeMars,
Missouri University of Science and Technology
Typically, the center of mass and inertia tensor of a spacecraft are estimated pre- launch using a
mass properties table and/or a CAD model of the spacecraft. If these estimates are not sufficiently
accurate to meet mission requirements, they can be refined after launch using sensor data from thespacecraft. In order to refine pre-launch estimates of these properties, a gyroscope-based Kalmanfilter is developed to operate alongside a conventional gyroscope-based attitude filter to estimate theangular rate of the spacecraft as well as its inertia tensor.

Morning Break

10:20

AAS Optimal Steering Law for Single-Gimbal Control Moment Gyroscopes with
19-435 Singularity Avoidance and Vibration Suppression
Zhili Hou, Tsinghua univercity; Simeng Huang, Politecnico di Milano
This paper presents an optimal steering law for the Single-Gimbal Control Moment Gyroscopes(SGCMG) system to cope with the SGCMG singularity problem as well as the residual vibration
problem. The designing process is comprised of three steps. Firstly, a combined performance index
for the SGCMG gimbal rates and the reference angular acceleration amplitude is dsigned. Secondly,
the residual vibrations of the points near the natrual frequency is constrained to be zero to suppress
the vibrations. Thirdly, an analytical solution for the steering law is derived by minimizing the
combined performance index under the constraints in the second step.

10:40

AAS A Real-Time GNC Framework for Rendezvous of Small Satellites Using Constant
19-574 Thrust in a Uniform Gravitational Field
Jonathan De Leon, University of Hawaii at Manoa
With the use of small satellites on the rise as a cheap alternative to conventional satellites, there is arising need for autonomous solutions for their maneuvers. The purpose of this research is to generate
an real time analytical solution for rendezvous of small satellites in a uniform gravitational fieldusing constant thrust and create a Guidance Navigation and Control (GNC) solution for thisrendezvous problem. This analytical solution will make computations less expensive than thecurrent numerical methods that are in use.

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11:00

AAS CENTROIDING PERFORMANCE FOR HORIZON-BASED OPTICAL
19-494 NAVIGATION WITH CASSINI IMAGES OF DIONE AND RHEA
Courtney Hollenberg, Rensselaer Polytechnic Institute; John Christian, Rensselaer
Polytechnic Institute; Shyam Bhaskaran, Jet Propulsion Laboratory; William Owen, Jet
Propulsion Laboratory
In recent work, the authors introduced a new horizon-based optical navigation (OPNAV) techniquethat combines an improved subpixel edge localization method with a noniterative solution forspacecraft position relative to an ellipsoidal body. In this work, the performance of the newtechnique is evaluated on OPNAV images of the Saturnian satellites Dione and Rhea from theCassini spacecraft. Image plane centroid estimates from the new method are compared to the legacy
centerfinding results produced by JPL in support of the Cassini mission, which were computed via
an iterative limb-scan technique. Additionally, kinematic position residuals are presented for the fullmission

11:20

AAS Model-Based Optical Navigation and Guidance for Autonomous Landing on Asteroids
19-570 Yuki Takao, The University of Tokyo; Yuichi Tsuda, Japan Aerospace Exploration Agency;
Takanao Saiki, JAXA / ISAS; Naoko Ogawa, Japan Aerospace Exploration Agency
An optical navigation and guidance scheme for autonomous landing on asteroids using asteroid
shape model is presented. Vertices of the shape model are tracked in the sequential images obtainedby a monocular camera. The proposed method does not need the process of landmark detection or
mapping. The pose of the spacecraft is estimated using extended Kalman filter, including the
dynamics around the asteroid. The stochastic performance of control loop is evaluated via numericalsimulation using computer graphics rendered from the shape model. The effectiveness of the
proposed method is also validated using the flight results in Hayabusa2 Mission.

Session 26: Astrodynamics
Thursday, Napili
Chairs: Juan Arrieta, Nabla Zero Labs & Rohan Sood, University of Alabama
8:00

AAS Parking orbit design for generic near-Earth object flyby missions
19-492 Oscar Fuentes-Munoz, University of Colorado Boulder; Daniel Scheeres, University ofColorado at Boulder
Near Earth Objects (NEOs) are promising targets of opportunity for science. We propose andanalyze an observation system to be placed in orbit until an interesting NEO is found. Afterwards, aprobe would be injected to a flyby mission from that orbit. This paper investigates both a suitableparking orbit design and the desired maneuver capabilities for the system. Each proposed parking
orbit performance is described statistically based on the NEO database.Discovery conditions arise
naturally as design constraints. Results show the polar Laplace plane equilibrium solution as asuitable parking orbit. Lastly, stability concerns of the flyby orbits are covered.

8:20

AAS Vertically Stable and Unstable Manifolds of Planar Periodic Orbits: Applications to
19-421 Spacecraft and Asteroid Trajectories
Kenta Oshima, National Astronomical Observatory of Japan

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This study explores applications of stable and unstable manifolds associated with vertical instabilityof planar periodic orbits in the circular restricted three-body problem. For spacecraft trajectories,
significant savings of delta-v as compared with known solutions are achieved for impulsive transfersfrom near rectilinear halo orbits to planar distant retrograde orbits (DROs) by exploiting verticallystable manifolds emanating from planar Lyapunov orbits in the Earth-Moon system. For asteroid
trajectories, we point out the possibility that Jupiter's DROs may host undetected potentiallyhazardous asteroids based on inclination oscillations of vertically unstable manifolds associated withvertical instability of DROs.

8:40

AAS Connecting Resonant Trajectories to a Europa Capture through Lissajous Staging
19-455 Orbits
Sonia Hernandez, Jet Propulsion Laboratory; Ricardo Restrepo, University of Texas atAustin; Rodney L. Anderson, Jet Propulsion Laboratory/Caltech
Efficient strategies such as a low energy moon tour are needed to land on the surface of Europa.
This strategy provides natural access to the moon via the L2 gateway. Staging around this libration
point allows to decouple the moon tour and the landing trajectory, allowing to design each phaseseparately. Furthermore, a staging step frees the landing time from the capture phase, adding an
additional degree of freedom. In this paper, the possible ballistic connections between theresonances from the moon tour and Lissajous orbits are studied, including the different geometries
that allow for time phasing control.

9:00

AAS The Stability of Orbital Resonances for Europa Quarantine Design: Escape Orbit
19-481 Case
Brian Anderson, University of Southern California; Martin Wen-Yu Lo, Jet Propulsion
Laboratory; Mar Vaquero, Jet Propulsion Laboratory
NASA’s planetary protection policies require that spacecraft seek to avoid biologicallycontaminating Europa. For low-energy missions to Europa, we study the feasibility of placing
spacecraft in quarantine orbits. This study sought to define what would be needed for the spacecraft
to remain in quarantine orbit around Jupiter long enough to become sterilized by Jupiter’s radiation
environment. The mutual resonance of the four Galilean moons leads us to predict certain
resonances as more stable in the ephemeris model. We verify this through a six-body Galilean
System model Poincare Map and propagation in the ephemeris model.

9:20

AAS Surfing in the phase space of Earth’s oblateness and third body perturbations
19-484 Camilla Colombo, Politecnico di Milano; Francesca Scala, Politecnico di Milano; Ioannis
Gkolias, Politecnico di Milano
We consider the exploitation of luni-solar perturbations for the post-mission disposal of satellites inhigh-altitude orbits. A representation of the double averaged dynamical system with respect to theplane of the perturbing body, yields a two degree of freedom Hamiltonian. An analytical method is
proposed for designing the disposal manoeuvre with the goal to achieve natural re-entry by
exploiting the long-term effect of the natural perturbations, enhanced by impulsive manoeuvres. The
optimal initial conditions during the natural evolution of the argument of perigee and the orbit
eccentricity are designed through a gradient based method in the phase space.

9:40

AAS

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JUICE Equinox Jupiter Tour: the Challenge of Long Eclipses
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19-413 Arnaud Boutonnet, European Space Agency / ESOC; Gábor Varga, European Space
AgencyJUICE is the next ESA L-class mission towards Jupiter and its Galilean moons. The Jupiter tour iscomposed of several very different phases requiring a total of 29 flybys before injection in-orbit
around Ganymede. The baseline tour in 2022 corresponds to a solstice mission. The backup tour in
2023 leads to an equinox tour and to unacceptable eclipse duration when reusing the baseline tour
structure. This paper presents the profound modifications of the tour that were necessary to remaincompliant with the spacecraft design constraint.

10:00

Morning Break

10:20

AAS A Data Mining Approach to Using Poincaré Maps in Multi-Body Trajectory Design
19-562 Strategies
Natasha Bosanac, University of Colorado, Boulder
Poincaré maps representing two-dimensional data sets are a powerful tool for rapid trajectory designin multi-body systems. However, projections of higher-dimensional data sets onto a map arechallenging to analyze. To reduce their complexity, data mining is employed to cluster map
crossings by the geometry of their associated trajectories. Then, interactive data analysis can be
performed via a global view of a reduced data set summarizing the clusters and an individual viewof the solutions in a single cluster. This data mining approach to leveraging Poincaré maps in the
trajectory design process is demonstrated in the circular restricted three-body problem.

10:40

AAS A Kriging based framework for rapid satellite-to-site visibility determination
19-215 Xinwei Wang, Beihang University; Chao Han, Beihang University
Rapid satellite-to-site visibility determination is of great significance to coverage analysis of satellite
constellations as well as onboard mission planning of autonomous spacecraft. A Kriging
interpolation technique based framework for rapid visibility determination is proposed in this paper.
Kriging is an advanced geostatistical procedure that generates an estimated surface from a scattered
set of points. The idea is introduced in the paper to determine the rise and set times of visibility,
where the estimation errors are controlled by weighted surrounding measurement values. To further
increase the computational speed, an interval shrinking strategy preprocessing is adopted via
investigating the geometric relationship

11:00

AAS LANDING ON EUROPA: KEY CHALLENGES AND ARCHITECTURE CONCEPT
19-223 Aline K. Zimmer, Jet Propulsion Laboratory; Eli Skulsky, Jet Propulsion Laboratory; A.
Miguel San Martin, NASA Jet Propulsion Laboratory; Gurkipal Singh, Jet Propulsion
Laboratory; Nikolas Trawny, NASA/JPL; Tejas Kulkarni, Jet Propulsion Laboratory;
Martin Greco, NASA / Caltech JPL
NASA has extended the scope of the potential exploration of Europa beyond the planned Europa
Clipper mission and initiated a Pre-Phase A mission concept study of a potential Europa Lander.
Jupiter’s hostile radiation environment and the lack of information about the moon’s terrain at thescale of a lander spacecraft would require significant technology development to overcome theinherent landing challenges. This paper provides an overview of the Europa Lander mission concept

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and describes the significant challenges associated with landing on Europa, the technologies
required to overcome those challenges, and a strategy for Deorbit, Descent, and Landing (DDL).

11:20

AAS OPTIMAL-FEEDBACK ACCELERATED PICARD ITERATION METHODS AND
19-286 A FISH-SCALE GROWING METHOD FOR WIDE-RANGING AND MULTIPLEREVOLUTION PERTURBED LAMBERT’S PROBLEMS
Xuechuan Wang, Texas Tech University; Satya Atluri, texas tech university
Wide-ranging and multiple-revolution perturbed Lambert’s problems are building blocks forpractical missions such as development of cislunar space, interplanetary navigation, orbital
rendezvous, etc. However, it is of a great challenge to solve these problems both accurately andefficiently, considering the long transfer time and the complexity of high-fidelity mod-eling of spaceenvironment. For that, a methodology combining Optimal-Feedback Accelerated Picard Iteration
methods and Fish-Scale Growing Method is demonstrated. The resulting iterative formulae are
explicitly de-rived and applied to an Earth-Moon restricted three-body problem and mul-tirevolution earth rendezvous problem. The examples demonstrate the va-lidity and high efficiency ofthe proposed methods.

11:40

AAS Enabling Repeat Pass Interferometry from Low Venus Orbit
19-292 Mark Wallace, Jet Propulsion Laboratory, California Institute of Technology; Theodore H.
(Ted) Sweetser, Jet Propulsion Laboratory; Robert Haw, NASA / Caltech JPL; Eunice Lau,
NASA / Caltech JPL; Scott Hensley, Jet Propulsion Laboratory, California Institute ofTechnology
Repeat-pass interferometry is a powerful technique for determining changes in topography by flyinga radar over the terrain two or more times. These overflights must be very close to each other inspace. To design and maintain a low Venus orbit which enables this requires the consideration ofdrag, non-spherical gravitational effects, and solar tides. Once the orbit is designed, the spacecraftmust be navigated. To do so requires the use of radar-based terrain-relative navigation in addition to
the traditional radiometric datatypes. The mission design and navigation to enable repeat passinterferometry at Venus are described.

Session 27: Proximity Missions & Formation Flying III
Thursday, Kula
Chair: Mauro Massari, Politecnico di Milano
8:00

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AAS Spacecraft Formations Using Artificial Potential Functions and Relative Orbital
19-258 Elements
Sylvain Renevey, Purdue University; David A. Spencer, Purdue University
Spacecraft formation flight has applications to numerous science and infrastructure mission
applications. The disaggregation of a single monolithic spacecraft into multiple smaller spacecraft
flying in formation offers enhanced resilience and flexibility. However, the design of relative
motion trajectories using Cartesian coordinates is challenging, and the need for collision avoidance
requires computationally efficient control algorithms. In this paper, a control algorithm based on
artificial potential functions and using a set of relative orbital elements is presented. This method
allows the straightforward design and efficient control of a spacecraft formation. The effectiveness29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

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of the control algorithm is illustrated with numerical simulations.

8:20

AAS An Artificial Bifurcation Potential Field Method for Spacecraft Swarm Formation
19-314 Planning
Mu Li, Beihang University; Haibing Chen, Beihang University; Hengxian Jin, Beihang
University; Wei Lin; Kang Li, Beijing Institute of Control Engineering
Spacecraft swarms with huge members have great advantages in many applications. In traditional
formation control framework, path planning needs to be settled before orbital maneuver, and every
spacecraft follows the preconditioned path. When the number of spacecraft reaches to swarm level,
the computation consuming may be not affordable. A new formation planning methodology is
proposed by using nonlinear bifurcation dynamics. The artificial force filed with bifurcation
characteristics is designed. With bifurcation arising, each spacecraft can be drove to new position
under bifurcation dynamics to accomplish formation capture, maintenance and reconfiguration. The
presented method is more applicable and less calculation consuming.

8:40

AAS Evolutionary Neurocontrol for Spacecraft Proximity Operations
19-325 Cole George, Air Force Institute of Technology; Joshuah Hess, Air Force Institute ofTechnology; Richard Cobb, Air Force Institute of Technology
Recent research has demonstrated the potential of evolutionary strategies to the solution of deep
reinforcement learning problems. In this paper, such techniques are applied to the control of relative
spacecraft motion. Open-loop and closed-loop feedback controllers, represented by multi-layer
artificial neural networks, are developed using evolutionary optimization. The implementation andperformance of these so-called evolutionary neurocontrollers are compared to classical optimal andnonlinear control techniques. For this problem space, recommendations are made on appropriate
network hyperparameters and input-output representations. The resulting analysis is expected toprovide an alternative control approach for spacecraft proximity operations.

9:00

AAS Relative Maneuvering for Multiple Spacecraft via Differential Drag using LQR and
19-346 Constrained Least Squares.
Camilo Riano-Rios, University of Florida; Riccardo Bevilacqua, University of Florida;
Warren Dixon, University of Florida
In this paper, a spacecraft fleet with multiple chasers and a single target is considered for relative
maneuvering, with each spacecraft capable of changing its experienced drag force in a continuous
way. This feature is exploited to develop a control framework where the relative states of eachchaser-target pair are driven to zero using an LQR with linearized relative dynamics. A Constrained
Least Squares Problem is then formulated to find the best achievable set of individual inputs tocontrol all chasers simultaneously. Preliminary results are shown along with a description of current
work to reduce the risk of potential collisions.

9:20

AAS Fractional Control of Relative Orbit Trajectories
19-505 David Yaylali, University of Arizona; Eric Butcher, University of Arizona; Andrew J.
Sinclair, Air Force Research Laboratory
Fractional control laws are formulated for linearized relative orbit dynamics. In these controllers,
fractional-order derivative feedback of the relative position is used in addition to standard

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proportional and integer-order derivative feedback terms. The fractional order serves as anadditional tunable parameter which allows one more freedom in shaping the closed-loop relative
orbit trajectory. Methods of optimizing such controllers are investigated, including parameter spacesurveys and fractional variational calculus. Specific cases where fractional relative-orbit controllers
outperform standard integer-order controllers are shown.

9:40

10:00

AAS Controllability Analysis of Propellant-Free Satellite Formation Flight
19-384 Mohamed Shouman, Department of Aeronautics and Astronautics, Kyushu University.; Mai
Bando, Kyushu University; Shinji Hokamoto, Kyushu University
This paper analyzes the controllability of relative motion using different space environmental forces.
It mainly considers the controllability of relative motion by environmental forces as atmosphericdrag, solar radiation pressure and Lorentz forces and propose a minimal configuration for the
missions exploiting such forces. It illustrates the constraints in each space environmental force. It
studies the integration of these forces to achieve full controllability of the satellite formation flightfor near-circular low earth orbits with different orbit configurations. Numerical simulations areinvestigated to validate the full controllability of different configurations for the combined spaceenvironmental forces.

Morning Break

10:20

AAS Proximity Operations with Obstacles Avoidance based on Artificial Potential Field
19-400 and Sliding Mode Control
Nicoletta Bloise, Politecnico di Torino; Elisa Capello , Politecnico di Torino CNR-IEIIT;
Elisabetta Punta
This paper combines Guidance and Control algorithms for spacecraft proximity operations inpresence of obstacles. The guidance algorithm is based on Artificial Potential Field theory, while theadopted control strategies are first-order Sliding Mode considering two different methods: thesimplex-based and the component-wise. Both control strategies result to be effective and suitable tobe implemented by the mono-directional actuation system and for a ground test-bed developed
within the STEPS project (Systems and Technologies for Space Exploration). The algorithms result
to be suitable for real-time control with a minimum on-board computational effort and to avoid
obstacles and local minima.

10:40

AAS Safe Rendezvous Trajectory Design for the Restore-L Mission
19-410 Matthew Vavrina, a.i. solutions; Eugene Skelton; Keith DeWeese; Bo Naasz, NASA ; David
Gaylor, NASA Goddard Space Flight Center
The Restore-L mission will capture and robotically service Landsat 7 in the early 2020s. The
rendezvous will be autonomous with onboard sensors providing relative navigation measurements
and onboard guidance algorithms controlling to a reference trajectory. The trajectory design ispredicated on maintaining passive safety through any fault until relative navigation is sufficiently
accurate to proceed within proximity of Landsat 7. This requirement must be addressed withconsideration for sensor range, measurement accuracy, dispersions, thruster faults, and lighting,among others. The trajectory design incorporates co-elliptic transfers for gradual far-field approachand periodic relative motion strategies for near-field approach and inspection.

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11:00

AAS SATELLITE FORMATION FLYING: ON-GROUND EXPERIMENT ON
19-416 RELATIVE ORBIT ELEMENTS-BASED CONTROL
Lisa DeWitte, University of Florida; Lucas Bassett-Audain, University of Florida; Aastha
Rajbhandary, University of Florida; Brandon Paz, University of Florida; Giuseppe Di
Mauro, University of Florida; Riccardo Bevilacqua, University of Florida
Accurate preflight testing environments for formation flying are crucial in transitioning between
numerical simulation and actual orbital flight. A 3DOF experimental testbed was developed at theAdvanced Autonomous Multiple Spacecraft (ADAMUS) laboratory to validate a relative orbit
elements-based control strategy for satellite formation reconfiguration maneuvering. The
experimental facility consists of two completely autonomous vehicles floating on an epoxy 4×4 m
surface. To mimic the hardware capabilities of a small spacecraft, the control algorithm was
executed by the space-qualified Tyvak Intrepid computer board. The paper presents the design andintegration of the vehi-cles with their preliminary experimental results.

11:20

AAS Low-Thrust Reconfiguration for Formation Flying Using Jordan Normal Form
19-430 Theory
Xue Bai; Ming Xu; Yuying Liang
Reconfiguration is a hot topic due to its scalability and flexibility of the formation in on-orbit
assembly and servicing. Jordan normal form of C-W equation is used to guide reconfiguration
strategy, which decompose all the terms in relative motions. The initial value is regarded as theinvariants of configuration just as the definition of orbital elements for Keplerian orbit. The
reconfiguring path is derived and then proved as a functional from initial to final configuration. The
polynomial series method is used to approximate the functional. The optimal coefficients ofpolynomial series are much easier to be found than previous optimizations.

Session 28: Trajectory Design & Optimization VI
Thursday, Hana
Chairs: Pradipto Ghosh, Analytical Graphics, Inc. & Jennifer Hudson, Western Michigan University
8:00

AAS Efficient Computation of Optimal Low Thrust Gravity Perturbed Orbit Transfers
19-487 Robyn Woollands, Jet Propulsion Laboratory; Ehsan Taheri, Texas A&M University; John
L. Junkins, Texas A&M University
We have developed a new method for solving the optimal low thrust minimum-fuel orbit transfer
problem in the vicinity of a large body, considering a high fidelity spherical harmonic gravity
model. The algorithm is formulated via the indirect variational calculus approach, leading to a twopoint boundary value problem. We make use of a hyperbolic tangent smoothing law for performing
continuation on the thrust magnitude to reduce the sharpness of the control switches in early
iterations and thus promote convergence. The two-point boundary value problem is solved using themethod of particular solutions shooting method and Picard-Chebyshev numerical integration.

8:20

AAS Synthesis of fuel-optimal powered descent trajectories for planetary landing missions
19-568 Minji Jo, University of Hawaii at Manoa; Dilmurat Azimov, University of Hawaii at Manoa

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Synthesis of feasible and extremal planetary entry, descent and landing trajectories is investigatedfor a central Newtonian field. In this synthesis, all trajectories are started with the initial thrust arc
and ended with the final thrust arc, and the ballistic arc connects both thrust arcs. The proposedsynthesis is presented for feasible and extremal and fuel-optimal trajectories. The feasible
trajectories are designed with the 7-state model and the extremal trajectories are considered with the
14-state model. The proposed synthesis can be used in mission design for planetary landing
missions including moon and Mars missions, and sample return missions.

8:40

AAS Hyperbolic-Tangent-Based Smoothing with State Transition Matrix implementation
19-496 for generating Fuel-optimal trajectories
Vishala Arya, Texas A & M University; Ehsan Taheri, Texas A&M University; John L.
Junkins, Texas A&M University
Indirect methods are among the powerful techniques for formulating and solving optimal control
problems since they guarantee local optimality of the resulting solutions. Traditionally, smoothing
techniques such as quadratic, logarithmic and extended logarithmic have been employed withhomotopy to alleviate non-smoothness arising due to bang-bang control structures. In this work, a
recently introduced hyperbolic tangent smoothing (HTS) is used for designing time-fixed,
rendezvous-type, fuel-optimal maneuvers. Implementation of the State Transition Matrix (STM)
within the HTS is demonstrated that enhances convergence performance of solvers that rely on
Newton update iterative schemes. Utility of the method is demonstrated through interplanetary lowthrust trajectories.

9:00

AAS Transfer Trajectory Options for Servicing Sun-Earth-Moon Libration Point Missions
19-500 David Folta, NASA Goddard Space Flight Center; Cassandra Webster, NASA Goddard
Space Flight Center
Future missions to the Sun-Earth Libration L1 and L2 regions will require scheduled servicing tomaintain hardware and replenish consumables. While there have been statements made by various
NASA programs regarding servicing of vehicles at these locations or in Cis-lunar space, a true
feasibility transfer study has not been extensively investigated in an operational fashion. This
investigation uses dynamical systems and operational models to design transfer trajectories between
the Sun-Earth Libration region (Lyapunov, Lissajous, and Quasi-halo) and the Earth-Moon vicinity(Distant Retrograde, Quasi-Halo, Lissajous, and Near Rectilinear Halo Orbits). We address the costof transfers between each pair of locations.

9:20

AAS Vector Formulations for Spherically Bounded Search Spaces
19-504 David Hinckley, University of Vermont; Darren Hitt, University of Vermont
In the optimization of spacecraft trajectories, it is often the case that there is some naturally arisingbound(s) on the magnitudes of the associated velocities. Such constraints lead to a spherical or,
more generally, an elliptical search space. Unfortunately, typical problem transcriptions instead
search within a Cartesian box, applying these bounds to each dimension independently. This leads
to a search space where nearly half of the search space is known to be useless {\it a priori}. The
present work investigates an alternate interpretation of a velocity decision vector and assesses theeffects of precluding this known sub-optimal space.

9:40

AAS

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Multi-Objective Optimization For Spacecraft Detection Avoidance Using Reachability
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19-514 Sets
Jason Reiter, Penn State ARGoPS; Zachary Hall, Pennsylvania State University; David B.
Spencer, Pennsylvania State University; Puneet Singla, Pennsylvania State University
The Conjugate Unscented Transform allows for an easy calculation of reachabil-ity sets with aminimal number of full model propagations. The computation time savings that come with thismethod encourages implementation of reachability sets in more complex problems. Spacecraft
maneuvers planning for detection avoidance is unique in that all objectives may not be met bymoving some mini-mum distance from the nominal orbit. Analyzing the reachable sets in
topographic coordinates instead presents a unique metric for quantifying detection avoidance.
Combining ground-track manipulation and propellant-use in reachability-based multi-objective
optimization gives planners an efficient and accurate method for designing detection avoidance
maneuvers.

10:00

Morning Break

10:20

AAS ANALYSIS OF ANALOG-TO-DIGITAL CONVERSION TECHNIQUES FOR
19-519 SATELLITE ORBITAL MANEUVERING USING COLD GAS THRUSTERS
Spencer Harwood, South Dakota State University
Analog-to-digital conversion strategies for cold gas thrust actuation are examined. In particular, theinterest is directed toward the accurate and efficient actuation of continuous thrust histories via onoff thrusting action. We considered different actuation strategies, including pulse-width modulation,delta-sigma modulation, and a novel compensated pulse-width modulation. The scenario of interest
involves an orbiting small satellite performing proximity maneuvers propelled by a single cold gas
thruster. Different settings for the actuation strategies are studied to determine their effects on
actuation accuracy and efficiency in propellant usage.

10:40

AAS Multi-Objective Optimization of Spacecraft Trajectories for Small-Body Coverage
19-536 Missions with Non-Keplerian Orbit Dynamics
David Hinckley, University of Vermont; Jason Pearl, University of Vermont; Darren Hitt,
University of Vermont
Visual coverage of surface elements of a small-body requires multiple images to be taken that meetmany requirements on their viewing angles, illumination angles, times of day, and combinations
thereof. Finding trajectories that allow for these conditions to be met in a timely manner is a
nontrivial task; made more difficult by the competing criteria for such trajectories. This workphrases the search for suitable trajectories as an optimization problem handled with a multiobjective evolutionary algorithm.

11:00

AAS Innovative Solar Sail Earth-Trailing Trajectories Enabling Sustainable Heliophysics
19-541 Missions
James Pezent, The University of Alabama; Andrew Heaton, NASA Marshall Space Flight
Center; Rohan Sood, University of Alabama
As a successor to NEA Scout, there is a growing interest in leveraging solar sails for heliophysics
science missions. The presented work is a design study demonstrating the feasibility of possible

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trajectory architectures under specific operational constraints and initial conditions. Trade studies
are carried out to ensure that a solar sail can reach and maintain innovative science orbits about
Earth-trailing equilibrium points. Additionally, optimal solutions in terms of time of flight (TOF)
and solar observation time are presented. Preliminary results suggest that the proposed trajectories
are robust to varying initial conditions, sail performance levels, and operational constraints.

11:20

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AAS Objective Function Weight Selection for Sequential Low-Thrust Orbit-Raising19-567 Optimization Problem
Atri Dutta, Wichita State University; Lakshay Arora, Wichita State University
In this paper, we consider the low-thrust orbit-raising problem formulated at a sequence of optimal
control sub-problems. This formulation is helpful in rapid and robust generation of geocentric
electric orbit-raising trajectories, however this advantage comes at the cost of sub-optimality of thesolutions. This paper explores the impact of weights in the objective function on the optimality gapof computed solutions. Numerical simulations are presented to illustrate the effect.

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

Program by time
January 14, 2019
SessionRoom
Session 3:
Kula
AttitudeDynamics &Control I
Session 1:
Kapulua
Orbit
Determination& SpaceSurveillanceTracking
Session 2:
NapiliOrbitalDynamics,
Perturbations,and Stability I
Session 4:
Hana
Trajectory
Design &Optimization I

Doc. #
AAS 19202

PresenterJulie
8:00 - 8:20
Halverson

Title
Lunar Reconnaissance
Orbiter Operations Withouta GyroAAS 19220

Sarah
8:00 - 8:20
Elizabeth
McCandlessAnalyzing Feasibility of
Optical Communication
Observables for Navigation

AAS 19254

DanielGrebow

8:00 - 8:20

Stability and Targeting in
Dawn's Final Orbit

AAS 19201

BradleyWall

8:00 - 8:20

INDIRECT OPTIMIZATION
OF LOW-THRUSTTRAJECTORIES USING
HOMOTOPY

Session 3:
Kula
AttitudeDynamics &Control I
Session 1:
Kapulua
Orbit
Determination& SpaceSurveillanceTracking
Session 2:
NapiliOrbitalDynamics,
Perturbations,and Stability I
Session 4:
Hana
Trajectory

AAS 19240

BotianZhou

8:20 - 8:40

AAS 19231

Shyam
8:20 - 8:40
Bhaskaran

CONFIGURATIONOPTIMAZATION OF 0-1
SUN SENSORS FOR SUN
VECTOR DETERMINATION
Navigation Accuracy at
Jupiter and Saturn using
Optical Observations ofPlanetary Satellites

AAS 19270

RobertoArmellin

8:20 - 8:40

AAS 19203

Fernando
Abilleira

8:20 - 8:40

Page 93

Design and Control of
Repeat Ground Track Orbit
in High Fidelity Dynamical
Model via High Order
Poincaré Mapping
Mars 2020 Mission Design
and Navigation Overview

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

Design &Optimization I
Session 3:
Kula
AttitudeDynamics &Control I
Session 1:
Kapulua
Orbit
Determination& SpaceSurveillanceTracking
Session 2:
NapiliOrbitalDynamics,
Perturbations,and Stability I
Session 4:
Hana
Trajectory
Design &Optimization I

AAS 19296

RenatoZanetti

8:40 - 9:00

Rotations, Transformations,
Left Quaternions, Right
Quaternions?

AAS 19271

Zahi Tarzi

8:40 - 9:00

ORBIT DETERMINATIONSENSITIVITY ANALYSISFOR THE EUROPA CLIPPERMISSION TOURAAS 19277

YuyingLiang

8:40 - 9:00

Capture an asteroid to the
Earth-Moon system via
triangular libration points

AAS 19206

Chris
Ranieri

8:40 - 9:00

AL YAH 3 ORBITTRANSFER RECOVERYDESIGN

Session 3:
AttitudeDynamics &Control I

AAS 19368

KameshSubbarao

9:00 - 9:20

AAS 19445

SimoneServadio

9:00 - 9:20

UNCERTAINTYQUANTIFICATION AND
ANALYSIS OF INVARIANTS
OF RIGID BODY ATTITUDE
DYNAMICSRECURSIVE POLYNOMIALMINIMUM MEAN SQUAREERROR ESTIMATION WITH
APPLICATIONS TO ORBITDETERMINATIONAAS 19310

Virginia
RaposoPulido

9:00 - 9:20

DROMO propagator for
highly perturbed problems

AAS 19226

Patrick
Chai

9:00 - 9:20

Hybrid Transportation
System Integrated
Trajectory Design and
Optimization for Mars
Landing Site Accessibility

Kula

Session 1:
Kapulua
Orbit
Determination& SpaceSurveillanceTracking
Session 2:
NapiliOrbitalDynamics,
Perturbations,and Stability I
Session 4:
Hana
Trajectory
Design &Optimization I

Page 94

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

Session 3:
Kula
AttitudeDynamics &Control I
Session 1:
Kapulua
Orbit
Determination& SpaceSurveillanceTracking
Session 2:
NapiliOrbitalDynamics,
Perturbations,and Stability I
Session 4:
Hana
Trajectory
Design &Optimization I

AAS 19399

HongwenWang

9:20 - 9:40

Fault Points Detection forLarge Solar Panel Based on
Photogrammetry

AAS 19518

Troy
9:20 - 9:40
Henderson

AAS 19322

CarmineGiordano

INDENTIFYINGSPACECRAFTCONFIGURATION USING
DEEP NEURAL NETWORKS
FOR PRECISE ORBITESTIMATION
Dedicated Mission to the
Sun-Earth Saddle Point: A
Feasibility Assessment

AAS 19236

Zhemin Chi 9:20 - 9:40

9:20 - 9:40

Optimization of VariableSpecific-Impulse GravityAssist Trajectories

Morning Break 10:00 - 10:20
Session 3:
Kula
AttitudeDynamics &Control I
Session 1:
Kapulua
Orbit
Determination& SpaceSurveillanceTracking
Session 2:
NapiliOrbitalDynamics,
Perturbations,and Stability I
Session 4:
Hana
Trajectory
Design &Optimization I

AAS 19460

Thibaud
Teil

AAS 19507

Yoola
Hwang

AAS 19328

Hodei
Urrutxua

10:20 - 10:40 Sensitivity Analysis ofRegularised Orbit
Formulations with Interval
Arithmetic

AAS 19242

Tim
McElrath

10:20 - 10:40 On Alighting Daintily at
Jupiter: Innovative Methods
for Efficiently Achieving
Jovian Orbit

Session 3:
AttitudeDynamics &AAS 19473

Christine
Schmid

10:40 - 11:00 Angular Correlation using
Rogers-Szego-Chaos

Page 95

Kula

10:20 - 10:40 Removing Rate Unobservability in Sun
Heading Filters Without
Rate Gyros
10:20 - 10:40 GEOSTATIONARYSATELLITE ORBITACCURACY ANALYSIS FORMANEVEUR EFFICIENCYCALIBRATION

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

Control I
Session 1:
Kapulua
Orbit
Determination& SpaceSurveillanceTracking
Session 2:
NapiliOrbitalDynamics,
Perturbations,and Stability I
Session 4:
Hana
Trajectory
Design &Optimization I

AAS 19513

David
Ciliberto

10:40 - 11:00 Extended Kalman Filteringin Regularized Coordinates
for Orbit Determination

AAS 19375

Mark
Moretto10:40 - 11:00 Attitude Dependent
Evolution of Orbits about
Active Comets

AAS 19245

Juan
Arrieta

10:40 - 11:00 High Performance
Interpolation of Chebyshev
Ephemerides

Session 3:
Kula
AttitudeDynamics &Control I
Session 1:
Kapulua
Orbit
Determination& SpaceSurveillanceTracking
Session 2:
NapiliOrbitalDynamics,
Perturbations,and Stability I
Session 4:
Hana
Trajectory
Design &Optimization I

AAS 19503

Sital
11:00 - 11:20 Control of an Earth-Based
Khatiwada
Satellite Test Platform
through Vision Based
Position Measurement
Troy
11:00 - 11:20 INITIAL RELATIVE ORBIT
Henderson
DETERMINATIONSOLUTIONS USINGPOLYNOMIAL SYSTEMS

Session 3:
AttitudeDynamics &Control I

Page 96Kula

AAS 19515

AAS 19379

AndresDono

11:00 - 11:20 Stability and spin-orbit
resonance analysis of low
altitude Martian orbits

AAS 19248

Elisabet
Canalias

11:00 - 11:20 Transfer between planar
and three-dimensional
Quasi Satellit Orbits in thevicinity of Phobos

AAS 19531

Patrick
Kenneally

11:20 - 11:40 SPACECRAFT RADIATIONPRESSURE USINGCOMPLEX BIDIRECTIONAL
REFLECTANCE
DISTRIBUTION FUNCTIONSON GRAPHICS PROCESSING
UNIT

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

Session 4:
Hana
Trajectory
Design &Optimization I

AAS 19249

WilliamStein

11:20 - 11:40 The Implementation of
Maximum Likelihood
Estimation in Space Launch
System Vehicle Design

Session 3:
Kula
AttitudeDynamics &Control I
Session 4:
Hana
Trajectory
Design &Optimization I

AAS 19545

Clark
NewmanAAS 19255

Naoya
Ozaki

11:40 - 12:00 Attitude Control and Orbit
Determination of a Crewed
Spacecraft With a Lander in
Near Rectilinear Halo Orbit
11:40 - 12:00 Tube Stochastic OptimalControl For Nonlinear
Constrained Trajectory
Optimization Problems

SessionRoom
Session 5:
Kapulua
Artificial
Intelligence inAstrodynamics
Session 6:
NapiliAsteroid &Non-EarthOrbiting
Missions I
Session 7:
Kula
AttitudeDynamics &Control II
Session 8:
Hana
Trajectory
Design &Optimization
II

Doc. #
AAS 19304

Presenter
Title
Lin Cheng 13:30 - 13:50 Real-time Optimal Control
for Irregular Asteroid
Landings Using Deep
Neural Networks
Stefaan Van 13:30 - 13:50 Deployment analysis andWal
trajectory reconstruction of
MINERVA-II rovers on
asteroid Ryugu

Session 5:
Kapulua
Artificial
Intelligence inAstrodynamics
Session 6:
NapiliAsteroid &Non-EarthOrbiting
Missions I
Session 7:
Kula
Page 97

AAS 19243

AAS 19210

Fabio
CelaniAAS 19259

Kanta
Yanagida

AAS 19441

Andrea13:50 - 14:10 Actor-Critic Reinforcement
Scorsoglio
Learning Approach toRelative Motion Guidancein Near-Rectilinear Orbit
Benjamin 13:50 - 14:10 Initial Orbit Determination
Bercovici
about Small Bodies Using
Flash LIDAR and Rigid
Transform Invariants

AAS 19253

AAS 19-Yasuhiro

13:30 - 13:50 Spacecraft Attitude Motion
Planning on SO(3) using
Gradient-based
Optimization
13:30 - 13:50 Designing Low-Energy
Transfers from Low-Earth
Orbit to a TemporarilyCaptured Orbiter

13:50 - 14:10 Innovative Guidance and29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

AttitudeDynamics &Control II

257

MoritaAAS 19265

Mar
VaqueroSession 5:
Kapulua
Artificial
Intelligence inAstrodynamics
Session 6:
NapiliAsteroid &Non-EarthOrbiting
Missions I
Session 7:
Kula
AttitudeDynamics &Control II

AAS 19447

AndrewHarrisAAS 19260

Javier Roa

Session 8:
Trajectory
Design &OptimizationII

AAS 19285

Session 8:
Trajectory
Design &Optimization
II

Hana

Hana

AAS 19275

14:10 - 14:30 Spacecraft Decision-Making
Autonomy using Deep
Reinforcement Learning

14:10 - 14:30 Multilayer ClusteredSampling Technique(MLCS) for Near-EarthAsteroid Impact Hazard
Assessment
Ting Jin
14:10 - 14:30 HIGH PRECISIONATTITUDE CONTROL OF
SPACECRAFT BASED ON
ELECTRIC THRUSTER AND
FLYWHEEL
Marilena Di 14:10 - 14:30 Robust Optimisation of
Carlo
Low-Thrust Interplanetary
Transfers using Evidence
TheorySession 5:
Kapulua
Artificial
Intelligence inAstrodynamics

AAS 19462

Jacob
BroidaSession 6:
Asteroid &Non-EarthOrbiting
Missions I
Session 7:
AttitudeDynamics &NapiliAAS 19269

Kenshiro
Oguri

Kula

AAS 19283

Mark
Karpenko

Page 98

Control Design of the
Versatile Orbit Transfer
Space Vehicle of the Epsilon
Rocket13:50 - 14:10 A TITAN GRAVITY-ASSISTTECHNIQUE FORBALLISTIC TOURSSKIMMING OVER THE
RINGS OF SATURN

14:30 - 14:50 SPACECRAFT
RENDEZVOUS GUIDANCEIN CLUTTEREDENVIRONMENTS VIA
REINFORCEMENTLEARNING
14:30 - 14:50 Science Orbit Design with
Frozen Beta angle: Theory
and Application to Psyche
mission14:30 - 14:50 WAYPOINT FOLLOWINGDYNAMICS OF A
QUATERNION ERROR

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

Control II
Session 8:
Trajectory
Design &Optimization
II

Hana

AAS 19294

FEEDBACK ATTITUDE
CONTROL SYSTEM
Powtawche 14:30 - 14:50 Charting a Course to theValerino
Sun: Flight Path Control for
Parker Solar Probe

Session 5:
Kapulua
Artificial
Intelligence inAstrodynamics

AAS 19479

Session 6:
Asteroid &Non-EarthOrbiting
Missions I
Session 7:
AttitudeDynamics &Control II
Session 8:
Trajectory
Design &Optimization
II

NapiliAAS 19339

Kula

AAS 19287

MichaelMarshall

14:50 - 15:10 Attitude Maneuver Designfor Planar Space Solar
Power Satellites

Hana

AAS 19295

AmandaHaapala

14:50 - 15:10 MARS GRAVITY ASSISTOPTIONS TO REDUCEMISSION ΔV FOR EUROPALANDER

Session 5:
Kapulua
Artificial
Intelligence inAstrodynamics

AAS 19537

Session 8:
Trajectory
Design &OptimizationII

AAS 19297

Mohammad 15:10 - 15:30 ADAPTIVE CONTROL BY
Ramadan
REINFORCEMENTLEARNING FORSPACECRAFT ATTITUDE
CONTROL
Pradipto
15:10 - 15:30 A Survey of the Methods
Ghosh
Available for the Design ofMany-Revolution LowThrust Planetocentric
Trajectories

Hana

Damien
GUEHO

14:50 - 15:10 INVESTIGATION OF
DIFFERENT NEURALNETWORKARCHITECTURES FOR
DYNAMIC SYSTEMIDENTIFICATION:APPLICATIONS TO
ORBITAL MECHANICS
Jason Pearl 14:50 - 15:10 Curvilinear Surface-Based
Gravity Model for
Evolutionary Trajectory
Optimization around Bennu

Afternoon Break 15:30 - 15:50
Session 5:
Page 99

Kapulua

AAS 19-Daniel

15:50 - 16:10 Low-Thrust Optimal

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

Artificial
Intelligence inAstrodynamics
Session 6:
NapiliAsteroid &Non-EarthOrbiting
Missions I

560

MillerAAS 19385

Florian
Renk

Session 7:
AttitudeDynamics &Control II
Session 8:
Trajectory
Design &Optimization
II

Kula

AAS 19319

Hana

AAS 19298

15:50 - 16:10 Lagrange – Mission
Analysis for the European
Space Agency’s Space
Weather Mission to the
Sun-Earth Libration Point
L5
Yash
15:50 - 16:10 Predicting Time-Optimal
Khatavkar
Slews Across Multiple
Spacecraft with Inertia
RatiosJulia
15:50 - 16:10 Julia Language 1.0
Mihaylov
Ephemeris and Physical
Constants Reader for Solar
System Bodies

Session 5:
Kapulua
Artificial
Intelligence inAstrodynamics
Session 6:
NapiliAsteroid &Non-EarthOrbiting
Missions I
Session 7:
Kula
AttitudeDynamics &Control II

AAS 19566

Patrick
Doran

AAS 19387

Francesco
TopputoAAS 19374

AlannaSharp

Session 8:
Trajectory
Design &OptimizationII

AAS 19299

KentaroNishi

AAS 19573

Zachary
ReinkeHana

Session 5:
Kapulua
Artificial
Intelligence inAstrodynamics
Page 100Control via Reinforcement
Learning

16:10 - 16:30 COLLISION PREDICTIONWITHIN A CUBESATSWARM USING MACHINELEARNING
16:10 - 16:30 Trajectory design for
LUMIO CubeSat in thecislunar space

16:10 - 16:30 NUMERICAL RESULTS ON
THE GENERAL TIMEOPTIMAL REST-TO-REST
THREE-AXISREORIENTATION OF A
RIGID SPACECRAFT
16:10 - 16:30 Multi-step Optimization of
Orbit Raising Trajectories
for All-electric Propulsion
Geostationary Satellites
16:30 - 16:50 TRAINING SET DATAOPTIMIZATION FOR
ARTIFICIAL NEURALNETWORKS FOR ORBITAL

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

Session 6:
Asteroid &Non-EarthOrbiting
Missions I
Session 7:
AttitudeDynamics &Control II
Session 8:
Trajectory
Design &Optimization
II

FINAL PROGRAM

STATE SPACE TRAJECTORY
PREDICTIONS
16:30 - 16:50 Mascot: flight dynamics
activities in support of anasteroid landing mission

NapiliAAS 19411

Elisabet
CanaliasKula

AAS 19490

Bing SongHana

AAS 19306

Zhaowei
Wang

Session 5:
Kapulua
Artificial
Intelligence inAstrodynamics
Session 6:
NapiliAsteroid &Non-EarthOrbiting
Missions I
Session 7:
Kula
AttitudeDynamics &Control II

AAS 19336

Haiyang Li 16:50 - 17:10 Deep neural networks of
Optimal Low-Thrust Orbit
Raising

AAS 19412

Fabio
Ferrari

16:50 - 17:10 A new environment tosimulate the dynamics inthe close proximity of
rubble-pile asteroids

AAS 19572

Bowen
Wang

Session 8:
Trajectory
Design &OptimizationII

AAS 19308

Mauro
Pontani

16:50 - 17:10 ON THE USE OF SINGULAR
VALUE DECOMPOSITIONBASIS FUNCTIONS TOPREVENT ERROR SIGNAL
ACCUMULATION IN
ITERATIVE LEARNINGCONTROL
16:50 - 17:10 Optimal Hyperbolic
Rendezvous Trajectories
for Cycler Missions

AAS 19397

Lin Cheng

Hana

Session 5:
Kapulua
Artificial
Intelligence inAstrodynamics

Page 101

16:30 - 16:50 Discrete-Time Iterative
Learning Control for
Nonlinear Systems byFeedback Linearization
16:30 - 16:50 REACHABLE DOMAIN OF
CONTINUOUS LOWTHRUST TRAJECTORIESWITH LINEARIZEDDYNAMIC MODEL

17:10 - 17:30 Fast Estimation ofGravitational Field of
Irregular Asteroids Basedon Deep Learning and Its
Applications

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

Session 8:
Trajectory
Design &Optimization
II

FINAL PROGRAM

Hana

AAS 19311

Di Wu

17:10 - 17:30 Adjoint Estimation Methodfor Low-thrust Manyrevolution Trajectory
Optimization

Doc. #

Presenter

Title

Session 11:
Kula
AtmosphericRe-entry &Satellite
Constellations
Session 9:
Kapulua
Orbital Debris& Space
Environment
Session 10:
NapiliOrbitalDynamics,
Perturbations,and Stability
II
Session 12:
Hana
Trajectory
Design &Optimization
III

AAS 19212

Rohan
8:00 - 8:20
Deshmukh

Investigation of Direct ForceControl for Planetary
Aerocapture at Neptune

AAS 19229

Mark
Vincent

8:00 - 8:20

Conjunction Assessment andRisk Mitigation Automation(CARMA)AAS 19390

Xiaoyu Liu 8:00 - 8:20

AAS 19316

Luke Bury

8:00 - 8:20

SECULAR ORBITALELEMENT VARIATIONS DUETO CONTINUOUS LOWTHRUST CONTROL AND
THIRD-BODY
PERTURBATIONS
Low-Energy Trajectories as
Staging Points for Landingon the Secondary Body in
the CR3BP

Session 11:
Kula
AtmosphericRe-entry &Satellite
Constellations

AAS 19301

PengleiZhao

8:20 - 8:40

Session 9:
Kapulua
Orbital Debris& Space
Environment
Session 10:
NapiliOrbitalDynamics,

AAS 19557

Aaron J.
8:20 - 8:40
Rosengren

AAS 19396

Yuki
OshimaJanuary 15, 2019
Session

Page 102

Room

8:20 - 8:40

Autopilot for Near-Space
Hypersonic Vehicle
Controlled by Aerodynamic
Lift and Divert Thrusters
with Off-Centered Seeker
Window
Resident Space Object
Proper Orbital Elements

Trajectory Design in the
Circular Restricted Threebody Problem Using

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

Perturbations,and Stability
II
Session 12:
Hana
Trajectory
Design &Optimization
III

Artificial Invariant Manifolds

AAS 19323

CarmineGiordano

8:20 - 8:40

Modeling and Optimizationof Aero-Ballistic Capture

Session 11:
Kula
AtmosphericRe-entry &Satellite
Constellations
Session 9:
Kapulua
Orbital Debris& Space
Environment

AAS 19463

Evan Zinner 8:40 - 9:00

PARKING ORBIT SELECTION
FOR MARS AEROCAPTUREENTRY SYSTEMSAAS 19268

Matthew
8:40 - 9:00
Richardson

Session 10:
NapiliOrbitalDynamics,
Perturbations,and Stability
II
Session 12:
Hana
Trajectory
Design &Optimization
III

AAS 19401

Zachary
FolcikMass Estimation ThroughFusion of Astrometric and
Photometric Data Collection
with Applications to Orbital
Debris Characterization
VERY LONG ARC TIMING
COEFFICIENT AND SOLAR
LUNAR PLANETARYEPHEMERIS FILES ANDAPPLICATIONSAAS 19356

Collin York 8:40 - 9:00

A Two-Level Differential
Corrections Algorithm for
Low-Thrust Spacecraft
Trajectory Targeting

Session 11:
Kula
AtmosphericRe-entry &Satellite
Constellations
Session 9:
Kapulua
Orbital Debris& Space
Environment

AAS 19468

PuneetSingla9:00 - 9:20

STOCHASTIC
REACHABILITY ANALYSISFOR THE HYPERSONIC REENTRY PROBLEM

AAS 19320

Stefan Frey 9:00 - 9:20

Session 10:
OrbitalDynamics,

AAS 19512

Tahsinul
9:00 - 9:20
Haque Tasif

Interpolation andIntegration of Phase Space
Density for Estimation of
Fragmentation Cloud
Distribution
A HIGH ORDER ANALYTIC
CONTINUATIONTECHNIQUE FOR THE

Page 103

Napili

8:40 - 9:00

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

Perturbations,and Stability
II
Session 12:
Hana
Trajectory
Design &Optimization
III

FINAL PROGRAMPERTURBED TWO-BODY
PROBLEM STATE
TRANSITION MATRIXEuropa Lander trajectory
design: case studies for the
Direct-To-Earth architecture

AAS 19327

Stefano9:00 - 9:20
Campagnola

Session 11:
Kula
AtmosphericRe-entry &Satellite
Constellations
Session 9:
Kapulua
Orbital Debris& Space
Environment
Session 10:
NapiliOrbitalDynamics,
Perturbations,and Stability
II
Session 12:
Hana
Trajectory
Design &Optimization
III

AAS 19499

Breanna
Johnson

9:20 - 9:40

Mid-Lift-to-Drag ratio Rigid
Vehicle 6-DoF EDL
Performance Using Tunable
Apollo Powered Guidance

AAS 19438

PiyushMehta

9:20 - 9:40

Data-driven investigation ofthermospheric variations

AAS 19470

Jules Simo

9:20 - 9:40

Identification of Families of
Periodic Orbits
Above/Below the Solar Sail
Earth-Moon Libration Points

AAS 19329

Brian
McCarthy

9:20 - 9:40

Trajectory Design Using
Quasi-Periodic Orbits in theMulti-Body Problem

Session 9:
Kapulua
Orbital Debris& Space
Environment
Session 10:
NapiliOrbitalDynamics,
Perturbations,and Stability
II
Session 12:
Hana
Trajectory
Design &Optimization

AAS 19439

PiyushMehta

9:40 - 10:00

On deriving Self-Consistent,High-accuracy Mass Density
Measurements

AAS 19510

Robyn
9:40 - 10:00
Woollands

Feasibility study of nearfrozen, near-circular, nearpolar and extremely low
altitude lunar orbits

AAS 19330

Anthony
Craig

Mission Design for the Lunar
Pallet Lander

Page 104

9:40 - 10:00

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

III
Morning Break 10:00 - 10:20
Session 11:
Kula
AtmosphericRe-entry &Satellite
Constellations
Session 9:
Kapulua
Orbital Debris& Space
Environment
Session 10:
NapiliOrbitalDynamics,
Perturbations,and Stability
II
Session 12:
Hana
Trajectory
Design &Optimization
III

AAS 19491

Hao Wang

10:20 - 10:40

Neural Network Trained
Controller for Atmospheric
Entry in Mars Missions

AAS 19465

Marielle
Pellegrino

10:20 - 10:40

Robustness of Targeting
Regions of Chaos In the
GNSS Regime

AAS 19526

Satoshi
Ikari

10:20 - 10:40

ANALYSIS OFDISTURBANCE ANOMALYOF INTERPLANETARYMICRO-SPACECRAFTPROCYONAAS 19331

Anthony
Craig

10:20 - 10:40

NASA Exploration Mission 2
Mission Design

Session 11:
Kula
AtmosphericRe-entry &Satellite
Constellations
Session 9:
Kapulua
Orbital Debris& Space
Environment
Session 10:
NapiliOrbitalDynamics,
Perturbations,and Stability
II
Session 12:
Hana
Trajectory
Design &Optimization
III

AAS 19508

Larissa
Balestrero
Machado10:40 - 11:00

Guidance and Control
System Design for Mars
Aerocapture

AAS 19502

RICHARD
LINARES

10:40 - 11:00

Koopman Operator Theory
for Thermospheric Density
Modeling

AAS 19544

Ahmed
Atallah

10:40 - 11:00

Analytical Radial Adaptive
Method for Spherical
Harmonics Gravity Models

AAS 19333

Mauro
Massari

10:40 - 11:00

Fuel-Optimal Convex
Trajectory Optimization ofRendezvous on Elliptical
OrbitsPage 105

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

Session 11:
Kula
AtmosphericRe-entry &Satellite
Constellations
Session 9:
Kapulua
Orbital Debris& Space
Environment
Session 10:
NapiliOrbitalDynamics,
Perturbations,and Stability
II
Session 12:
Hana
Trajectory
Design &Optimization
III

AAS 19402

KatherineMott

11:00 - 11:20

AAS 19409

Mirko
Trisolini

11:00 - 11:20

AAS 19554

Yusuke Oki 11:00 - 11:20

Retrograde Teardrop Orbits
about Asteroids: Application
to the Hayabusa2 Mission

AAS 19334

YanpingGuo

11:00 - 11:20

New Horizons 2014MU69
Flyby Design and Operation

Session 11:
Kula
AtmosphericRe-entry &Satellite
Constellations
Session 9:
Kapulua
Orbital Debris& Space
Environment
Session 10:
NapiliOrbitalDynamics,
Perturbations,and Stability
II
Session 12:
Hana
Trajectory
Design &Optimization
III

AAS 19431

AndrewHarris

11:20 - 11:40

Differential Lift and Drag
Based Constellation Control
Using Trimmed Attitude

AAS 19480

SimengHuang

11:20 - 11:40

Large Constellation DeOrbiting with Low-Thrust
Propulsion

AAS 19564

YupengGong

11:20 - 11:40

ANALYTIC PROBABILITYDENSITY MODEL OFSATELLITE SWARMS

AAS 19348

MartinOzimek

11:20 - 11:40

The Low-ThrustInterplanetary Explorer: A
Medium-Fidelity Algorithm
for Multi-Gravity Assist LowThrust Trajectory
Optimization

SessionDoc. #

Presenter

Page 106Room

DESIGN OF A RESILIENTRIDESHARE-BASED SMALLSATELLITECONSTELLATION USING AGENETIC ALGORITHM
A density-based approach tothe propagation of re-entry
uncertainties

Title

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

Session 14:
NapiliDynamical
Systems
TheorySession 13:
Kapulua
Large Space
Structures &Tethers
Session 15:
KulaSpecialSession - Mars
Insight
Session 16:
HanaSpecialSession - Mars
SampleReturnAAS 19266

Ian Elliott

AAS 19238

Dong-Huei 13:30 - 13:50
Tseng

AAS 19204

Fernando
Abilleira

13:30 - 13:50

AAS 19225

Min Qu13:30 - 13:50

Session 14:
Dynamical
Systems
TheoryAAS 19267

Christopher 13:50 - 14:10
SullivanSession 13:
Kapulua
Large Space
Structures &Tethers
Session 15:
KulaSpecialSession - Mars
Insight

AAS 19239

Minh Phan 13:50 - 14:10

AAS 19209

Premkumar 13:50 - 14:10
Menon

Session 16:
HanaSpecialSession - Mars
SampleReturnAAS 19230

Robert Haw 13:50 - 14:10

Session 14:
Dynamical
Systems
TheorySession 13:
Large Space

NapiliAAS 19280

Andrew Cox 14:10 - 14:30

Kapulua

AAS 19247

Hongwen
Wang

Page 107

Napili

13:30 - 13:50

14:10 - 14:30

Designing Low-Thrust
Enabled Trajectories for A
Heliophysics SmallSat
Mission to Sun-Earth L5
Identification of Stiffnessand Damping Matrices ofHigh Degree-of-Freedom
Structural Models
2018 Mars InSight
Trajectory Reconstruction
and Performance from
Launch through Landing
End to End Optimization of aMars Hybrid Transportation
Architecture

Exploring the Low-Thrust
Trajectory Design Space for
SmallSat Missions to the
Sun-Earth Triangular
Equilibrium Points
Partial System Identificationof Stiffness and Damping
Matrices From Output
Measurements Only
Mars Reconnaissance
Orbiter Navigation Strategy
for Support of InSight
Lander's Entry, Descent andLanding Sequence
Mars Sample Return -ORBITAL RENDEZVOUS
DETECTION METHODSTransit and Capture in the
Planar Three-Body Problem
Leveraging Low-Thrust
Dynamical Structures
Optimal Control of Space
Debris Deorbit Using Space

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

Structures &Tethers
Session 15:
KulaSpecialSession - Mars
Insight
Session 16:
HanaSpecialSession - Mars
SampleReturnTethered System
AAS 19213

Eric
Gustafson

14:10 - 14:30

InSight Orbit Determination

AAS 19326

Ryan
Woolley

14:10 - 14:30

Low-Thrust Trajectory
Bacon Plots for Mars
Mission Design

NapiliAAS 19366

Damon
Landau14:30 - 14:50

Kapulua

AAS 19363

George Zhu 14:30 - 14:50

Session 15:
KulaSpecialSession - Mars
Insight

AAS 19222

Jill Seubert 14:30 - 14:50

Session 16:
HanaSpecialSession - Mars
SampleReturnAAS 19345

Frank
Laipert14:30 - 14:50

GLOBAL SEARCH OF
RESONANT TRANSFERS
FOR EUROPA LANDER TO
CLIPPER DATA RELAY
HIGH-FIDELITY DYNAMIC
MODELLING OF PARTIALSPACE ELEVATOR WITH
DEPOYMENT OR
RETRIEVAL OF TETHERInSight Attitude Control
System Thruster
Characterization andCalibration for Successful
Navigation to Mars
Hybrid Chemical-Electric
Trajectories for a Mars
Sample Return Orbiter

Session 14:
NapiliDynamical
Systems
TheorySession 13:
Kapulua
Large Space
Structures &Tethers
Session 15:
KulaSpecialSession - Mars
Insight

AAS 19342

FranciscoCrespo14:50 - 15:10

Attitude Dynamics of a Rigid
Body in Circular Orbit

AAS 19365

George Zhu 14:50 - 15:10

AAS 19228

Allen
Halsell

FLIGHT DYNAMICS AND
CONTROL STRATEGY OF
FLEXIBLE ELECTRIC SOLAR
WIND SAIL
Navigation Performance ofthe 2018 InSight Mars
Lander Mission

Session 14:
Dynamical
Systems
TheorySession 13:
Large Space
Structures &Tethers

Page 108

14:50 - 15:10

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

Session 16:
HanaSpecialSession - Mars
SampleReturnAAS 19456

AustinNicholas

14:50 - 15:10

Simultaneous Optimizationof Spacecraft and Trajectory
Design for Interplanetary
Missions Utilizing Solar
Electric Propulsion

Session 14:
NapiliDynamical
Systems
TheorySession 13:
Kapulua
Large Space
Structures &Tethers
Session 15:
KulaSpecialSession - Mars
Insight
Session 16:
HanaSpecialSession - Mars
SampleReturnAAS 19359

Yuki
Kayama15:10 - 15:30

Sparse Optimal Trajectory
Design in Three-Body
Problem

AAS 19369

George Zhu 15:10 - 15:30

PARALLEL OPTIMALCONTROL FOR PARTIALSPACE ELEVATOR

AAS 19232

Min-KunChung

15:10 - 15:30

Maneuver Design Overview
of the 2018 InSight Mars
Lander Mission

AAS 19458

AustinNicholas

15:10 - 15:30

Mission Analysis for a
Potential Mars Sample
Return Campaign in the2020’sSession 14:
Dynamical
Systems
TheoryNapiliAAS 19372

Marcello
Romano15:30 - 15:50

Session 13:
Large Space
Structures &Tethers

Kapulua

AAS 19370

George Zhu 15:30 - 15:50

Session 15:
KulaSpecialSession - Mars
Insight

AAS 19233

Sean
Wagner

15:30 - 15:50

Session 16:
HanaSpecialSession - Mars
SampleReturnAAS 19459

Zubin
Olikara15:30 - 15:50

New Results on Minimumtime Control of Linear
Systems between Arbitrary
States with Applicability toSpace Flight
NANOSATELLITE MISSIONFOR SPACE DEBRISDEORBIT DEMONSTRATIONBY ELECTRODYNAMICTETHER
Mars Reconnaissance
Orbiter Maneuver Plan forMars 2020 Entry, Descent,and Landing Support and
BeyondChemical and Solar Electric
Propulsion Orbit Matchingfor Mars Sample
Rendezvous

Page 109

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

Session 14:
NapiliDynamical
Systems
TheorySession 13:
Kapulua
Large Space
Structures &Tethers
Session 15:
KulaSpecialSession - Mars
Insight
Session 16:
HanaSpecialSession - Mars
SampleReturnAAS 19543

David
Hinckley

15:50 - 16:10

AAS 19251

Virgil
15:50 - 16:10
Hutchinson

AAS 19264

EugeneBonfiglio

AAS 19583

Robert Lock 15:50 - 16:10

Session 15:
KulaSpecialSession - Mars
Insight

AAS 19291

Mark
Wallace

16:10 - 16:30

Session 16:
HanaSpecialSession - Mars
SampleReturnAAS 19555

PuneetSingla16:10 - 16:30

15:50 - 16:10

Finding Symmetric Halo
Orbits Framed as a Global
Optimization problem Using
Monotonic Basin Hopping
A Multidisciplinary
Performance Analysis for
the Cygnus Cargo Resupply
Mission to the ISS
Atmospheric Impacts on
EDL Maneuver Targeting for
the Insight Mission andUnguided Mars Landers
Potential Campaign
Architectures and Mission
Design Challenges forInternational Mars Sample
Return Mission Studies
Orbiters, Cubesats, andRadio Telescopes, Oh My;
Entry, Descent, and Landing
Communications for the2018 InSight Mars Lander
MissionOPTIMAL FEEDBACK
CONTROL FOR THE
HYPERSONICRE-ENTRY
PROBLEM

January 16, 2019
SessionRoom

Doc. #

Presenter

Title

Session 18:
Asteroid &Non-EarthOrbiting
Missions II
Session 19:
Proximity
Missions &Formation
Flying I

NapiliAAS 19427

Daniel Brack 8:00 - 8:20

Asteroid Manipulation with
Active Boulder Removal

Kula

AAS 19235

Paul
Schumacher

Exact Keplerian Relative
Motion: An Elementary
Formulation of the InitialValue Problem

Page 110

8:00 - 8:20

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

Session 17: Kapulua
Space
Situational
Awareness&
Conjunction
Analysis
Session 20: Hana
Trajectory
Design &OptimizationIV

AAS 19241

Stefania
Soldini

8:00 - 8:20

Hayabusa2 Mission Solar
Conjunction Phase for
Hovering Satellite: Trajectory
Design, Navigation and PostOperation Evaluation

AAS 19361

YuanzhuoGeng

8:00 - 8:20

Time-Optimal Repointing
Maneuver of a Rigid
Spacecraft with One Degreeof Freedom for Final Attitude

Session 18: Napili
Asteroid &Non-EarthOrbiting
Missions II
Session 19: Kula
Proximity
Missions &Formation
Flying I
Session 17: Kapulua
Space
Situational
Awareness&
Conjunction
Analysis
Session 20: Hana
Trajectory
Design &OptimizationIV

AAS 19436

Soon-Jo
Chung

8:20 - 8:40

Large Constellations andFormations for Exploring
Interstellar Objects and LongPeriod Comets

AAS 19290

Julio Cesar
Benavides

8:20 - 8:40

Relative Motion Analysis
Using Third- and FourthOrder Solutions of theRelative Two-Body Problem

AAS 19284

Marc Balducci 8:20 - 8:40

Maneuver Design for Asteroid
Rendezvous Considering
Uncertainty

AAS 19443

NathanStrange

8:20 - 8:40

Series Solution for Motion in
an Arbitrary Potential Field

Session 18:
Asteroid &Non-EarthOrbiting
Missions II
Session 19:
Proximity
Missions &Formation

NapiliAAS 19450

Shota
Takahashi

8:40 - 9:00

Effect of Shifted Origin on the
Osculating Orbital Elementsof Terminator Orbit

Kula

AAS 19338

Ahmad yazan 8:40 - 9:00
Chihabi

ANALYTICAL SPACECRAFT
FORMATION DYNAMICS IN
ECCENTRIC ORBITS WITHGRAVITATIONAL, DRAG AND

Page 111

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

Flying I

THIRD-BODY
PERTURBATIONS
Context-Based NonCompliance for GEO Satellite
Reorbiting

Session 17: Kapulua
Space
Situational
Awareness&
Conjunction
Analysis
Session 20: Hana
Trajectory
Design &OptimizationIV

AAS 19433

shiva iyer

8:40 - 9:00

AAS 19389

TakuyaChikazawa

8:40 - 9:00

Science Orbits Design for The
Lunar CubeSat EQUULEUS
and for The Phobos Sample
Return Mission MMX

Session 18: Napili
Asteroid &Non-EarthOrbiting
Missions II
Session 19: Kula
Proximity
Missions &Formation
Flying I
Session 17: Kapulua
Space
Situational
Awareness&
Conjunction
Analysis
Session 20: Hana
Trajectory
Design &OptimizationIV

AAS 19509

Kristofer
Drozd

9:00 - 9:20

Modeling Imaging
Uncertainty For OSIRIS-REx's
Asteroid Approach
Observations

AAS 19364

Matthew
Willis

9:00 - 9:20

Second-Order Analytical
Solution for Relative Motion
on Arbitrarily Eccentric
OrbitsAAS 19437

Zachary Hall 9:00 - 9:20

A Probabilistic Approach for
Reachability Set Computation
for Efficient Space Situational
Awareness

AAS 19398

Christopher
Lorenz

9:00 - 9:20

MULTI-OBJECTIVE
OPTIMIZATION OF LOW
THRUST TRAJECTORIES FOR
PROPELLANT MASS, TIME OF
FLIGHT, AND RADIATION
DOSE

Session 18:
Asteroid &Non-EarthOrbiting
Missions II

AAS 19529

WilliamLedbetter

9:20 - 9:40

Expected Accuracy of Density
Recovery using Satellite
Swarm Gravity
Measurements

Page 112

Napili29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

Session 19: Kula
Proximity
Missions &Formation
Flying I
Session 17: Kapulua
Space
Situational
Awareness&
Conjunction
Analysis
Session 20: Hana
Trajectory
Design &OptimizationIV

AAS 19282

LaurenSchlenker

9:20 - 9:40

AAS 19452

Emmanuel
Delande9:20 - 9:40

AAS 19406

Lorenzo
AngeloRicciardi

9:20 - 9:40

Simultaneous Localizationand Mapping for Satellite
Rendezvous and Proximity
Operations Using Random
Finite Sets
A new representation of
uncertainty for collisionassessment

A Relaxation Approach forHybrid Multi-Objective
Optimal Control: Application
to Multiple Debris Removal
Missions

Morning Break 10:00 - 10:20
Session 18: Napili
Asteroid &Non-EarthOrbiting
Missions II
Session 19: Kula
Proximity
Missions &Formation
Flying I
Session 17: Kapulua
Space
Situational
Awareness&
Conjunction
Analysis
Session 20: Hana
Trajectory
Design &OptimizationIV

AAS 19234

Stijn De Smet 10:20 - 10:40 On the design of multiplerevolution solar gravity
driven orbital transfersaround Mars

AAS 19582

Bogdan Udrea 10:20 - 10:40 Analysis fo a swarm
deployment for very low
Earth orbit operations

AAS 19483

Lyndy Axon

10:20 - 10:40 Early Collision andFragmentation Detection ofSpace Objects without Orbit
Determination

AAS 19408

Kazutoshi
Takemura

10:20 - 10:40 Low Energy Escape Using
Tube Dynamics Associatedwith Quasi-halo Orbit

Session 18:
Asteroid &AAS 19244

Justin Mansell 10:40 - 11:00 Swarm Optimization of Lunar
Transfers from Earth Orbit

Page 113

Napili29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

Non-EarthOrbiting
Missions II
Session 19: Kula
Proximity
Missions &Formation
Flying I
Session 17: Kapulua
Space
Situational
Awareness&
Conjunction
Analysis
Session 20: Hana
Trajectory
Design &Optimization
IV
Session 18: Napili
Asteroid &Non-EarthOrbiting
Missions II
Session 19: Kula
Proximity
Missions &Formation
Flying I
Session 17: Kapulua
Space
Situational
Awareness&
Conjunction
Analysis
Session 20: Hana
Trajectory
Design &Optimization
IV

Page 114

FINAL PROGRAM

with Radiation Dose
Constraints
AAS 19501

HongwenWang

10:40 - 11:00 Rapid Algorithm to
Determine the Close
Approaches and Durations
Between Satellites

AAS 19355

Yueyong Lyu 10:40 - 11:00 Two-Phase Impact Time
Guidance Strategy via DualVirtual-Target Concept

AAS 19422

Kento
Ichinomiya

10:40 - 11:00 QUASI-SATELLITE ORBITTRANSFERS VIA MULTIREVOLUTIONAL PERIODIC
ORBITSAAS 19415

KenshiroOguri

11:00 - 11:20 SRP-based orbit control withapplication to orbit
stationkeeping at small
bodiesAAS 19511

Ayansola
Ogundele

11:00 - 11:20 A Tip-Tilt Hardware-in-theloop air-bearing test bed withphysical emulation of therelative orbital dynamics

AAS 19506

Jason Reiter

11:00 - 11:20 Spacecraft Detection
Avoidance Maneuver
Optimization Using
Reinforcement Learning

AAS 19424

Lorenzo
Federici

11:00 - 11:20 Integrated Optimization of
Ascent Trajectory and SRM
Design of Multistage Launch
Vehicles29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

Session 18: Napili
Asteroid &Non-EarthOrbiting
Missions II
Session 17: Kapulua
Space
Situational
Awareness&
Conjunction
Analysis
Session 20: Hana
Trajectory
Design &OptimizationIV

AAS 19547

Anthony
Genova11:20 - 11:40 Ballistic Moon-Moon
Transfers in the Cislunar
Restricted Four-Body
Problem

AAS 19517

JannuelCabrera11:20 - 11:40 AN INITIAL ANALYSIS OF
AUTOMATING CONJUNCTIONASSESSMENT AND
COLLISION AVOIDANCEPLANNING IN SPACE
TRAFFIC MANAGEMENTAAS 19442

DarrelConway11:20 - 11:40 Using the Paramat System in
Mission Analysis and Design

Session 18: Napili
Asteroid &Non-EarthOrbiting
Missions II
Session 20: Hana
Trajectory
Design &OptimizationIV

AAS 19371

Virginia
RaposoPulido

11:40 - 12:00 Gravitational capture at
Saturn with low-thrust
assistanceAAS 19426

StevenMcCarty

11:40 - 12:00 Missed Thrust Analysis andDesign for Low Thrust
Cislunar Transfers

SessionRoom
Session 22: Napili
Guidance,
Navigation,
and Control I
Session 23: Kula
Proximity
Missions &Formation
Flying II
Session 21: Kapulua
Space
Situational
Awareness& Flight

Doc. #
Presenter
Title
AAS 19Lara
13:30 - 13:50 Unscented Guidance for Zero207
Magallanes
Feedback Reaction Wheel
Slews

Page 115

AAS 19482

Bryce Doerr

13:30 - 13:50 Random Finite Set Theory
and Optimal Control of Large
Spacecraft Swarms

AAS 19534

DanielAguilarMarsillach

13:30 - 13:50 Real-Time Telescope Tasking
for Custody and Anomaly
Resolution Using Judicial
Evidential Reasoning

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

Dynamics
Operations
Session 24: Hana
Trajectory
Design &OptimizationV

AAS 19448

JacksonShannon13:30 - 13:50 Q-Law Aided Direct
Trajectory Optimization for
the High-Fidelity, ManyRevolution Low-Thrust Orbit
Transfer Problem

Session 22: Napili
Guidance,
Navigation,
and Control I
Session 23: Kula
Proximity
Missions &Formation
Flying II
Session 21: Kapulua
Space
Situational
Awareness& Flight
Dynamics
Operations
Session 24: Hana
Trajectory
Design &OptimizationV

AAS 19221

Casey
Heidrich

13:50 - 14:10 Modern Aerocapture
Guidance to Enable Reducedlift Vehicles at Neptune

AAS 19349

Nobuhiro
Funabiki

13:50 - 14:10 Network architecture for
UWB-based relative
navigation of multiple
spacecraft in formation flightAAS 19540

John Gaebler 13:50 - 14:10 Label Assignments in CubeSat
Cluster Deployment Tracking

AAS 19449

Ravishankar 13:50 - 14:10 Visual Interactive Trajectory
MathurDesignSession 22: Napili
Guidance,
Navigation,
and Control I

AAS 19246

Charles
WrightSession 23:
Proximity
Missions &Formation
Flying II
Session 21:
Space
Situational

AAS 19350

SumantSharmaKapulua AAS 19521

ThomasKelecyPage 116

Kula

14:10 - 14:30 A DIRECT CHEBYSHEVPICARD ITERATIONAPPROACH TO PERTUBEDBALLISTIC PROPAGATION
AND LAMBERT BOUNDARYVALUE PROBLEMS
14:10 - 14:30 Pose Estimation For NonCooperative Spacecraft
Rendezvous Using Neural
Networks
14:10 - 14:30 Automated Near Real-time
Validation and Data Integrity
Assessment Using an

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

Awareness& Flight
Dynamics
Operations
Session 24: Hana
Trajectory
Design &Optimization
V

FINAL PROGRAM

Unscented Schmidt Kalman
Filter (USKF)AAS 19451

Jennifer
HudsonSession 22: Napili
Guidance,
Navigation,
and Control I
Session 23: Kula
Proximity
Missions &Formation
Flying II
Session 21: Kapulua
Space
Situational
Awareness& Flight
Dynamics
Operations
Session 24: Hana
Trajectory
Design &OptimizationV

AAS 19276

Yu Nakajima 14:30 - 14:50 Using GNSS Receiver at Near
Rectlinear Halo Orbit

AAS 19405

WilliamBezouska

AAS 19461

Tyler Doogan 14:30 - 14:50 Dynamic Optimization forLarge Scale Active Debris
Removal Mission Design
Applications

Session 22: Napili
Guidance,
Navigation,
and Control I
Session 23: Kula
Proximity
Missions &Formation
Flying II
Session 21: Kapulua
Space
Situational

AAS 19293

RICHARD
LINARESAAS 19407

Mark Mercier 14:50 - 15:10 Optimal Inspection of a
Nadir-Pointing Satellite with
Dynamic Angle Constraints

AAS 19563

Brett
NewmanPage 117

AAS 19551

14:10 - 14:30 On-Orbit Servicing Mission
Design in a Dynamic Client
Environment

14:30 - 14:50 Spacecraft Pose Estimationand Swarm Localization
Performance Under Varying
Illumination and Viewing
Conditions
Michael Volle 14:30 - 14:50 DISTANT RETROGRADE
ORBIT CONSTELLATIONSFOR RELATIVE-ONLY
NAVIGATION IN NEARRECTILINEAR HALO ORBITS

14:50 - 15:10 Adaptive Guidance withReinforcement Meta Learning

14:50 - 15:10 COGITATION OF SPACECURVE PRINCIPLES FORLAPLACE ORBIT

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

Awareness& Flight
Dynamics
Operations
Session 24: Hana
Trajectory
Design &Optimization
V
Session 23:
Proximity
Missions &Formation
Flying II

Kula

DETERMINATIONAAS 19464

BrandonJones

14:50 - 15:10 Modeling Attitude-Dependent
Maneuver Errors with
Polynomial Chaos Expansions

AAS 19471

Scott
Carnahan

15:10 - 15:30 Impact of Internal Heating onSpacecraft Thermal Signature

Afternoon Break 15:30 - 15:50
Session 22: Napili
Guidance,
Navigation,
and Control I
Session 23: Kula
Proximity
Missions &Formation
Flying II
Session 21: Kapulua
Space
Situational
Awareness& Flight
Dynamics
Operations
Session 24: Hana
Trajectory
Design &OptimizationV

AAS 19303

Session 22: Napili
Guidance,
Navigation,
and Control I
Session 23: Kula
Page 118

AAS 19535

PascalPRIEUR

15:50 - 16:10 Drag-Free and Attitude
Control System, lessons
learned from MICROSCOPE
flight (2016-2018)
Francisco
15:50 - 16:10 Optimal Range Observability
José Franquiz
Maneuvers for Angles-Only
Maldonado
Navigation in Elliptic Orbits

AAS 19569

Kota Kakihara 15:50 - 16:10 ACCURATE AND ROBUSTESTIMATION METHOD OFAUTONOMOUS ORBITDETERMINATION USINGACTIVE MANEUVERS AND
INTER-SATELLITE RANGING

AAS 19466

Diane Davis

15:50 - 16:10 Disposal, Deployment, andDebris in Near Rectilinear
Halo Orbits

AAS 19305

Mauro
Pontani

16:10 - 16:30 A New Guidance and Control
Architecture for Accurate
Orbit Injection

AAS 19-Marcello

16:10 - 16:30 Prototype Test Results of IVA

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

Proximity
Missions &Formation
Flying II
Session 21: Kapulua
Space
Situational
Awareness& Flight
Dynamics
Operations
Session 24: Hana
Trajectory
Design &Optimization
V

539

RomanoHopping Maneuvers of an
Autonomous Robotic Vehicle

AAS 19227

Gabe D.
Rogers

16:10 - 16:30 New Horizons 2014MU69(Ultima Thule) Flyby Design
and Execution

AAS 19324

Kaela Martin 16:10 - 16:30 Automating Tour Design with
Applications for Europa
LanderSession 22: Napili
Guidance,
Navigation,
and Control I
Session 23: Kula
Proximity
Missions &Formation
Flying II
Session 21: Kapulua
Space
Situational
Awareness& Flight
Dynamics
Operations
Session 24: Hana
Trajectory
Design &OptimizationV

AAS 19313

Yueyong Lyu 16:30 - 16:50 Data-driven model-free
adaptive sliding mode
attitude control of combined
spacecraft
Mohamed
16:30 - 16:50 Output Regulation Control forShoumanSatellite Formation Flying
Using Differential Drag

Session 22: Napili
Guidance,
Navigation,
and Control I
Session 23: Kula
Page 119AAS 19307

AAS 19383

Young-Rok
Kim

16:30 - 16:50 Orbit Determination
Simulation for Korea
Pathfinder Lunar Orbiter
Using Sequential Estimation
Approach

AAS 19486

Erica Jenson

16:30 - 16:50 Robust Trajectory Design for
Asteroid Orbiters

AAS 19351

DonaldKuettelAAS 19-George Zhu

16:50 - 17:10 AN ANALYSIS OF LOWTHRUST GUIDANCEALGORITHMS AROUND
SMALL BODIES
16:50 - 17:10 AUTONOMOUS SPACECRAFT

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

Proximity
Missions &Formation
Flying II
Session 21: Kapulua
Space
Situational
Awareness& Flight
Dynamics
Operations
Session 24: Hana
Trajectory
Design &OptimizationV

367

Session 23:
Proximity
Missions &Formation
Flying II

Kula

RENDEZVOUS BY LINE-OFSIGHT CONTROLAAS 19474

Brian
Kaplinger

16:50 - 17:10 Single-Waypoint Guidance for
Rotating Target Formation
FlyingAAS 19477

RaymondMerrill

16:50 - 17:10 Mission Designs for Human
Lunar Surface Access from an
Earth-Moon Near Rectilinear
Halo Orbit

AAS 19475

Chandrakanth 17:10 - 17:30 3-Dimensional Reachable Set
Venigalla
Applications to MultiSpacecraft Trajectory
Coordination

January 17, 2019
SessionRoom

Doc. #

Presenter

Session 26:
NapiliAstrodynamics

AAS 19492

8:00 - 8:20

Session 25:
Kapulua
Guidance,
Navigation,
and Control II

AAS 19315

Oscar
FuentesMunoz
Eric
Bourgeois

Session 27:
Proximity
Missions &Formation
Flying III
Session 28:
Trajectory
Design &Optimization

Kula

AAS 19258

SylvainRenevey

8:00 - 8:20

Hana

AAS 19487

Robyn
Woollands

8:00 - 8:20

Page 120

Title

8:00 - 8:20

Parking orbit design forgeneric near-Earth object
flyby missions
New improvements on
atmospheric trajectory
optimization of a rocket
reusable first stage withturbo engines
Spacecraft Formations
Using Artificial Potential
Functions and Relative
Orbital Elements
Efficient Computation of
Optimal Low Thrust
Gravity Perturbed Orbit
Transfers

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

VI
Session 26:
NapiliAstrodynamics

AAS 19421

Kenta
OshimaSession 25:
Kapulua
Guidance,
Navigation,
and Control II
Session 27:
Kula
Proximity
Missions &Formation
Flying III
Session 28:
Hana
Trajectory
Design &OptimizationVI

AAS 19522

John
8:20 - 8:40
McCormack

AAS 19314

Wei Lin8:20 - 8:40

AAS 19568

Minji Jo

8:20 - 8:40

Synthesis of fuel-optimal
powered descent
trajectories for planetarylanding missions

Session 26:
NapiliAstrodynamics

AAS 19455

Sonia
Hernandez

8:40 - 9:00

Session 25:
Kapulua
Guidance,
Navigation,
and Control II
Session 27:
Kula
Proximity
Missions &Formation
Flying III
Session 28:
Hana
Trajectory
Design &OptimizationVI

AAS 19542

Evan
Kawamura

8:40 - 9:00

AAS 19325

Cole George 8:40 - 9:00

Connecting Resonant
Trajectories to a Europa
Capture through Lissajous
Staging Orbits
Integrated Targeting,
Guidance, Navigation andControl for Unmanned
Aerial Vehicles
Evolutionary Neurocontrol
for Spacecraft Proximity
Operations

AAS 19496

Vishala Arya 8:40 - 9:00

Hyperbolic-Tangent-Based
Smoothing with State
Transition Matrix
implementation forgenerating Fuel-optimal
trajectories

Session 26:
NapiliAstrodynamics

AAS 19481

Brian
Anderson

The Stability of Orbital
Resonances for Europa
Quarantine Design: Escape

Page 121

8:20 - 8:40

9:00 - 9:20

Vertically Stable andUnstable Manifolds of
Planar Periodic Orbits:
Applications to Spacecraft
and Asteroid Trajectories
Coordination of a
Decentralized Satellite
Swarm with Internal
Formation
An Artificial Bifurcation
Potential Field Method forSpacecraft Swarm
Formation Planning

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

Orbit Case
MULTI-SENSOR
NAVIGATION WITHSPACECRAFT DYNAMICS
BASED ON FACTOR GRAPH
Relative Maneuvering forMultiple Spacecraft via
Differential Drag using LQR
and Constrained Least
Squares.
Transfer Trajectory
Options for Servicing SunEarth-Moon Libration
Point Missions

Session 25:
Kapulua
Guidance,
Navigation,
and Control II
Session 27:
Kula
Proximity
Missions &Formation
Flying III
Session 28:
Hana
Trajectory
Design &OptimizationVI

AAS 19391

Yongchao
Zhao

9:00 - 9:20

AAS 19346

CamiloRiano-Rios

9:00 - 9:20

AAS 19500

David Folta 9:00 - 9:20

Session 26:
NapiliAstrodynamics

AAS 19484

CamillaColombo

9:20 - 9:40

Session 25:
Kapulua
Guidance,
Navigation,
and Control II
Session 27:
Kula
Proximity
Missions &Formation
Flying III
Session 28:
Hana
Trajectory
Design &OptimizationVI

AAS 19429

CameronHelmuth

9:20 - 9:40

AAS 19505

David
Yaylali

9:20 - 9:40

AAS 19504

David
Hinckley

9:20 - 9:40

Vector Formulations forSpherically Bounded
Search Spaces

Session 26:
NapiliAstrodynamics

AAS 19413

ArnaudBoutonnet

9:40 - 10:00

Session 27:
Proximity
Missions &Formation
Flying III
Session 28:
Trajectory

Kula

AAS 19384

MohamedShouman

9:40 - 10:00

JUICE Equinox Jupiter
Tour: the Challenge of Long
Eclipses
Controllability Analysis of
Propellant-Free Satellite
Formation FlightHana

AAS 19514

Jason Reiter 9:40 - 10:00

Page 122

Surfing in the phase spaceof Earth’s oblateness andthird body perturbations
Gyroscope-BasedSpacecraft Angular Rateand Mass Properties
Estimation
Fractional Control ofRelative Orbit Trajectories

Multi-Objective
Optimization For

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

Design &Optimization
VI

Spacecraft Detection
Avoidance Using
Reachability Sets
Morning Break 10:00 - 10:20

Session 26:
NapiliAstrodynamics

AAS 19562

NatashaBosanac

10:20 - 10:40

Session 25:
Kapulua
Guidance,
Navigation,
and Control II

AAS 19435

SimengHuang

10:20 - 10:40

Session 27:
Proximity
Missions &Formation
Flying III
Session 28:
Trajectory
Design &Optimization
VI

Kula

AAS 19400

Elisa
Capello

10:20 - 10:40

Hana

AAS 19519

Spencer
Harwood

10:20 - 10:40

ANALYSIS OF ANALOG-TODIGITAL CONVERSIONTECHNIQUES FORSATELLITE ORBITALMANEUVERING USINGCOLD GAS THRUSTERS

Session 26:
NapiliAstrodynamics

AAS 19215

XinweiWang

10:40 - 11:00

Session 25:
Kapulua
Guidance,
Navigation,
and Control II

AAS 19574

Jonathan De 10:40 - 11:00
Leon

Session 27:
Proximity
Missions &Formation
Flying III
Session 28:
Trajectory
Design &Optimization

Kula

AAS 19410

Matthew
Vavrina

10:40 - 11:00

A Kriging based framework
for rapid satellite-to-site
visibility determination
A Real-Time GNC
Framework for
Rendezvous of Small
Satellites Using ConstantThrust in a Uniform
Gravitational Field
Safe Rendezvous
Trajectory Design for the
Restore-L Mission

Hana

AAS 19536

David
Hinckley

10:40 - 11:00

Page 123

A Data Mining Approach to
Using Poincaré Maps inMulti-Body Trajectory
Design Strategies
Optimal Steering Law forSingle-Gimbal Control
Moment Gyroscopes with
Singularity Avoidance andVibration Suppression
Proximity Operations with
Obstacles Avoidance basedon Artiﬁcial Potential Field
and Sliding Mode Control

Multi-Objective
Optimization of Spacecraft
Trajectories for Small-Body
Coverage Missions with

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

VI

Non-Keplerian Orbit
Dynamics

Session 26:
NapiliAstrodynamics

AAS 19223

Aline K.
ZimmerSession 25:
Kapulua
Guidance,
Navigation,
and Control II

AAS 19494

Courtney
11:00 - 11:20
Hollenberg

Session 27:
Proximity
Missions &Formation
Flying III

Kula

AAS 19416

Aastha11:00 - 11:20
Rajbhandary

Session 28:
Trajectory
Design &Optimization
VI

Hana

AAS 19541

James
Pezent11:00 - 11:20

Session 26:
NapiliAstrodynamics

AAS 19286

XuechuanWang

11:20 - 11:40

Session 25:
Kapulua
Guidance,
Navigation,
and Control II
Session 27:
Kula
Proximity
Missions &Formation
Flying III
Session 28:
Hana
Trajectory

AAS 19570

Yuki Takao 11:20 - 11:40

AAS 19430

YuyingLiang

11:20 - 11:40

AAS 19567

Atri Dutta

11:20 - 11:40

Page 124

11:00 - 11:20

LANDING ON EUROPA:
KEY CHALLENGES AND
ARCHITECTURE CONCEPTCENTROIDINGPERFORMANCE FORHORIZON-BASED OPTICALNAVIGATION WITHCASSINI IMAGES OF DIONEAND RHEASATELLITE FORMATIONFLYING: ON-GROUNDEXPERIMENT ON
RELATIVE ORBITELEMENTS-BASEDCONTROL
Innovative Solar Sail EarthTrailing Trajectories
Enabling Sustainable
Heliophysics Missions
OPTIMAL-FEEDBACKACCELERATED PICARDITERATION METHODS
AND A FISH-SCALEGROWING METHOD FOR
WIDE-RANGING AND
MULTIPLE-REVOLUTIONPERTURBED LAMBERT’S
PROBLEMS
Model-Based Optical
Navigation forAutonomous Landing on
Asteroids
Low-Thrust
Reconfiguration for
Formation Flying Using
Jordan Normal Form
TheoryObjective Function Weight
Selection for Sequential

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

Design &Optimization
VI
Session 26:
NapiliAstrodynamics

Page 125

Low-Thrust Orbit-Raising
Optimization Problem
AAS 19292

Mark
Wallace

11:40 - 12:00

Enabling Repeat Pass
Interferometry from Low
Venus Orbit

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

1/6/2019

FINAL PROGRAM

Author index
Aaron, Seth - Trajectory Design & Optimization I
Abilleira, Fernando - Special Session - Mars Insight , Trajectory Design & Optimization I
Aguilar Marsillach, Daniel - Space Situational Awareness & Flight Dynamics Operations
Akella, Maruthi R. - Atmospheric Re-entry & Satellite Constellations , Special Session - Mars
Sample Return
Alessi, Elisa Maria - Orbital Debris & Space Environment
Alibay, Farah - Dynamical Systems Theory
Alsup, Katrina - Proximity Missions & Formation Flying II
Amato, Davide - Orbital Debris & Space Environment
Anderson, Brian - Astrodynamics
Anderson, Rodney L. - Astrodynamics
Armellin, Roberto - Orbital Dynamics, Perturbations, and Stability I
Arora, Lakshay - Trajectory Design & Optimization VI
Arrieta, Juan - Trajectory Design & Optimization I , Trajectory Design & Optimization III
Arya, Vishala - Trajectory Design & Optimization VI
Atallah, Ahmed - Orbital Dynamics, Perturbations, and Stability II
Atchison, Justin - Trajectory Design & Optimization V
Atluri, Satya - Astrodynamics
Axelrad, Penina - Space Situational Awareness & Flight Dynamics Operations
Axon, Lyndy - Space Situational Awareness & Conjunction Analysis
Azimov, Dilmurat - Guidance, Navigation, and Control II , Trajectory Design & Optimization VI
Bae, Jonghee - Space Situational Awareness & Flight Dynamics Operations
Bai, Xue - Proximity Missions & Formation Flying III
Baker, Chuck - Trajectory Design & Optimization I
Balducci, Marc - Space Situational Awareness & Conjunction Analysis
Balestrero Machado, Larissa - Atmospheric Re-entry & Satellite Constellations
Bando, Mai - Dynamical Systems Theory , Orbital Dynamics, Perturbations, and Stability II ,Proximity Missions & Formation Flying II , Proximity Missions & Formation Flying III
Bani Younes, Ahmad - Artificial Intelligence in Astrodynamics , Orbital Dynamics,
Perturbations, and Stability II
Baoyin, Hexi - Artificial Intelligence in Astrodynamics , Trajectory Design & Optimization II
Baresi, Nicola - Trajectory Design & Optimization IV
Bassett-Audain, Lucas - Proximity Missions & Formation Flying III
Benavides, Julio Cesar - Proximity Missions & Formation Flying I
Bercovici, Benjamin - Asteroid & Non-Earth Orbiting Missions I
Berry, Christopher - Trajectory Design & Optimization III
Besser, Rebecca - Attitude Dynamics & Control II
Bevilacqua, Riccardo - Proximity Missions & Formation Flying III
Bezouska, William - Proximity Missions & Formation Flying II
Bhaskaran, Shyam - Guidance, Navigation, and Control II , Orbit Determination & SpaceSurveillance Tracking
Biele, Jens - Asteroid & Non-Earth Orbiting Missions I
Page 126

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

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FINAL PROGRAM

Bjorkman, Michael D. - Trajectory Design & Optimization III
Black, Jonathan - Atmospheric Re-entry & Satellite Constellations
Bloise, Nicoletta - Proximity Missions & Formation Flying III
Bombardelli, Claudio - Orbital Debris & Space Environment
Bonfiglio, Eugene - Special Session - Mars Insight
Boone, Dylan - Orbit Determination & Space-Surveillance Tracking
Bosanac, Natasha - Astrodynamics , Dynamical Systems Theory
Boudad, Kenza - Trajectory Design & Optimization V
Bourgeois, Eric - Guidance, Navigation, and Control II
Boutonnet, Arnaud - Astrodynamics
Bowman, Alice - Space Situational Awareness & Flight Dynamics Operations
Boynton, Bill - Asteroid & Non-Earth Orbiting Missions II
Brack, Daniel - Asteroid & Non-Earth Orbiting Missions II
Bradley, Nicholas - Orbit Determination & Space-Surveillance Tracking , Orbital Dynamics,
Perturbations, and Stability I
Braun, Robert - Guidance, Navigation, and Control I
Broida, Jacob - Artificial Intelligence in Astrodynamics
Broschart, Stephen - Orbit Determination & Space-Surveillance Tracking
Burkhart, P. Daniel - Trajectory Design & Optimization I
Bury, Luke - Trajectory Design & Optimization III
Butcher, Eric - Proximity Missions & Formation Flying III
Cabrera, Jannuel - Space Situational Awareness & Conjunction Analysis
Cai, Jian - Attitude Dynamics & Control II
Calhoun, Philip - Attitude Dynamics & Control I
Campagnola, Stefano - Dynamical Systems Theory , Trajectory Design & Optimization I ,Trajectory Design & Optimization III , Trajectory Design & Optimization IV , Trajectory Design& Optimization V
Canalias, Elisabet - Asteroid & Non-Earth Orbiting Missions I , Trajectory Design &Optimization I
Cantara, Aaron - Attitude Dynamics & Control I
Capello , Elisa - Proximity Missions & Formation Flying III
Carnahan, Scott - Proximity Missions & Formation Flying II
Castillo-Rogez, Julie - Asteroid & Non-Earth Orbiting Missions II
Cefola, Paul J. - Orbital Dynamics, Perturbations, and Stability II
Celani, Fabio - Attitude Dynamics & Control II , Guidance, Navigation, and Control I
Cerimele, Christopher - - Atmospheric Re-entry & Satellite Constellations
Ceriotti, Matteo - Orbital Dynamics, Perturbations, and Stability II
Chai, Patrick - Special Session - Mars Sample Return , Trajectory Design & Optimization I
Chan, Moses - Space Situational Awareness & Flight Dynamics Operations
Chen, Haibing - Proximity Missions & Formation Flying III
Chen, Wanchun - Atmospheric Re-entry & Satellite Constellations
Cheng, Lin - Artificial Intelligence in Astrodynamics
Chi, Zhemin - Trajectory Design & Optimization I
Chihabi, Ahmad yazan - Proximity Missions & Formation Flying I
Chikazawa, Takuya - Trajectory Design & Optimization IV
Choi, Seok-Weon - Space Situational Awareness & Flight Dynamics Operations
Page 127

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

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FINAL PROGRAM

Chow, Channing - Orbital Debris & Space Environment
Christian, John - Guidance, Navigation, and Control II
Christiansen, Eric - Trajectory Design & Optimization III
Chung, Min-Kun - Special Session - Mars Insight
Chung, Soon-Jo - Asteroid & Non-Earth Orbiting Missions II
Ciarcia, Marco - Trajectory Design & Optimization VI
Ciliberto, David - Orbit Determination & Space-Surveillance Tracking
Cobb, Richard - Proximity Missions & Formation Flying III
Colasurdo, Guido - Trajectory Design & Optimization IV
Colombo, Camilla - Astrodynamics , Orbital Debris & Space Environment
Condon, Gerald - Trajectory Design & Optimization III
Conway, Darrel - Trajectory Design & Optimization IV
Cox, Andrew - Dynamical Systems Theory
Craig, Anthony - Trajectory Design & Optimization I , Trajectory Design & Optimization III
Crespo, Francisco - Dynamical Systems Theory
Criddle, Kevin - Special Session - Mars Insight
Curti, Fabio - Dynamical Systems Theory
D'Amico, Simone - Proximity Missions & Formation Flying I , Proximity Missions & Formation
Flying II
Darling, Jacob - Guidance, Navigation, and Control II
Davis, Diane - Attitude Dynamics & Control I , Trajectory Design & Optimization V
De Leon, Jonathan - Guidance, Navigation, and Control II
De Smet, Stijn - Asteroid & Non-Earth Orbiting Missions II
Dei Tos, Diogene Alessandro - Asteroid & Non-Earth Orbiting Missions I
Delande, Emmanuel - Space Situational Awareness & Conjunction Analysis
DELAVAULT, Stéphanie - Guidance, Navigation, and Control I
DeMars, Kyle - Attitude Dynamics & Control I , Guidance, Navigation, and Control II
Deshmukh, Rohan - Atmospheric Re-entry & Satellite Constellations
DeWeese, Keith - Proximity Missions & Formation Flying III
DeWitte, Lisa - Proximity Missions & Formation Flying III
Di Carlo, Marilena - Trajectory Design & Optimization II
Di Mauro, Giuseppe - Proximity Missions & Formation Flying III
Dickmann, Samantha - Asteroid & Non-Earth Orbiting Missions II
Didion, Alan - Special Session - Mars Sample Return
DiPrinzio, Marc - Trajectory Design & Optimization I
Dixon, Warren - Proximity Missions & Formation Flying III
Doerr, Bryce - Proximity Missions & Formation Flying II
Dono, Andres - Orbital Dynamics, Perturbations, and Stability I
Doogan, Tyler - Trajectory Design & Optimization V
Doran, Patrick - Artificial Intelligence in Astrodynamics
Drozd, Kristofer - Asteroid & Non-Earth Orbiting Missions II
Du, Chonggang - Large Space Structures & Tethers
Dunham, David - Asteroid & Non-Earth Orbiting Missions II
Dutta, Atri - Trajectory Design & Optimization VI
Dutta, Soumyo - Atmospheric Re-entry & Satellite Constellations , Guidance, Navigation, andControl I
Page 128

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

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FINAL PROGRAM

Edelman, Peter - Trajectory Design & Optimization I
Elgohary, Tarek - Atmospheric Re-entry & Satellite Constellations , Orbital Dynamics,
Perturbations, and Stability II
Elliott, Ian - Dynamical Systems Theory
Epenoy, Richard - Trajectory Design & Optimization II
Fantino, Elena - Asteroid & Non-Earth Orbiting Missions II
Farnocchia, Davide - Asteroid & Non-Earth Orbiting Missions I
Federici, Lorenzo - Trajectory Design & Optimization IV
Ferrari, Fabio - Asteroid & Non-Earth Orbiting Missions I
Ferrari, Silvia - Proximity Missions & Formation Flying II
Ferrer, Sebastian - Dynamical Systems Theory
Flores, Roberto - Asteroid & Non-Earth Orbiting Missions II
Folcik, Zachary - Orbital Dynamics, Perturbations, and Stability II
Folta, David - Dynamical Systems Theory , Trajectory Design & Optimization VI
Foster, Christopher - Trajectory Design & Optimization III
FOULON, Bernard - Guidance, Navigation, and Control I
Francisco Javier, Molero - Dynamical Systems Theory
Franquiz Maldonado, Francisco José - Proximity Missions & Formation Flying II
Frey, Stefan - Orbital Debris & Space Environment
Fruth, Gregory - Trajectory Design & Optimization I
Fuentes-Munoz, Oscar - Astrodynamics
Fujii, Ken - Special Session - Mars Insight
Funabiki, Nobuhiro - Proximity Missions & Formation Flying II
Funase, Ryu - Orbital Dynamics, Perturbations, and Stability II , Proximity Missions &Formation Flying II , Space Situational Awareness & Flight Dynamics Operations , Trajectory
Design & Optimization I , Trajectory Design & Optimization II
Furfaro, Roberto - Artificial Intelligence in Astrodynamics , Asteroid & Non-Earth Orbiting
Missions II
Gaebler, John - Space Situational Awareness & Flight Dynamics Operations
Gao, Han - Guidance, Navigation, and Control I
Garmier, Romain - Asteroid & Non-Earth Orbiting Missions I
Gaudet, Brian - Guidance, Navigation, and Control I
Gaylor, David - Proximity Missions & Formation Flying I , Proximity Missions & Formation
Flying III
Gearhart, James - Trajectory Design & Optimization I
Geng, Yuanzhuo - Trajectory Design & Optimization IV
Genova, Anthony - Asteroid & Non-Earth Orbiting Missions II
George, Cole - Proximity Missions & Formation Flying III
Ghosh, Pradipto - Trajectory Design & Optimization II
Giordano, Carmine - Orbital Dynamics, Perturbations, and Stability I , Trajectory Design &Optimization III
Gkolias, Ioannis - Astrodynamics
Godinez, Humberto C -. Orbital Debris & Space Environment
Goel, Ashish - Attitude Dynamics & Control II
Gondelach, David - Orbital Debris & Space Environment
Gong, Shengping - Artificial Intelligence in Astrodynamics
Page 129

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FINAL PROGRAM

Gong, Yupeng - Orbital Dynamics, Perturbations, and Stability II
Goodson, Troy - Trajectory Design & Optimization II
Goulet, Michael - Attitude Dynamics & Control I
Graat, Eric - Special Session - Mars Insight
Grebow, Daniel - Orbital Dynamics, Perturbations, and Stability I , Trajectory Design &Optimization IV
Greco, Cristian - Trajectory Design & Optimization II
Greco, Martin - Astrodynamics
GUEHO, Damien - Artificial Intelligence in Astrodynamics , Atmospheric Re-entry & Satellite
Constellations
GUIDOTTI, Pierre-Yves - Guidance, Navigation, and Control I
Guo, Yanning - Space Situational Awareness & Conjunction Analysis , Trajectory Design &Optimization IV
Guo, Yanping - Trajectory Design & Optimization III
Gustafson, Eric - Special Session - Mars Insight , Special Session - Mars Sample Return
Guzman, Jose - Trajectory Design & Optimization I , Trajectory Design & Optimization IV
Haapala , Amanda Trajectory Design & Optimization I , Trajectory Design & Optimization II
Hahn, Yungsun - Special Session - Mars InsightHall, Zachary - Space Situational Awareness & Conjunction Analysis , Trajectory Design &Optimization VI
Halsell, Allen - Special Session - Mars Insight
Halverson, Julie - Attitude Dynamics & Control I , Attitude Dynamics & Control II
Han, Chao - Astrodynamics , Proximity Missions & Formation Flying I
Hannan, Mike - Trajectory Design & Optimization III
Harch, Ann - Space Situational Awareness & Flight Dynamics Operations
Harden, Adam - Trajectory Design & Optimization III
Harris, Andrew - Artificial Intelligence in Astrodynamics , Atmospheric Re-entry & Satellite
Constellations
Hart, William - Asteroid & Non-Earth Orbiting Missions I
Hartmann, John - Trajectory Design & Optimization I
Hartzell, Christine - Trajectory Design & Optimization V
Harwood, Spencer - Trajectory Design & Optimization VI
Hassin, Jérémie - Guidance, Navigation, and Control II
Haw, Robert - Astrodynamics, Special Session - Mars Sample Return, Trajectory Design &Optimization II
He, Yanchao - Orbital Dynamics, Perturbations, and Stability I
Heaton, Andrew - Trajectory Design & Optimization VI
Heidrich, Casey - Guidance, Navigation, and Control I
Hekma, Enne - Trajectory Design & Optimization I
Helmuth, Cameron - Guidance, Navigation, and Control II
Henderson, Troy - Orbit Determination & Space-Surveillance Tracking , Proximity Missions &Formation Flying II
Hensley, Scott - Astrodynamics
Hernandez, Sonia - Astrodynamics
Hersman, Chris - Space Situational Awareness & Flight Dynamics Operations
Hess, Joshuah - Proximity Missions & Formation Flying III
Page 130

29th AAS/AIAA Space Flight Mechanics Meeting, Ka’anapali, Hawaii

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FINAL PROGRAM

Hinckley, David - Asteroid & Non-Earth Orbiting Missions I , Dynamical Systems Theory ,Trajectory Design & Optimization VI
Hitt, Darren - Asteroid & Non-Earth Orbiting Missions I , Dynamical Systems Theory ,Trajectory Design & Optimization VI
Hokamoto, Shinji - Dynamical Systems Theory , Orbital Dynamics, Perturbations, and Stability
II , Proximity Missions & Formation Flying II , Proximity Missions & Formation Flying III
Hollenberg, Courtney - Guidance, Navigation, and Control II
Holt, James - Trajectory Design & Optimization III
Holzinger, Marcus - Space Situational Awareness & Conjunction Analysis , Space Situational
Awareness & Flight Dynamics Operations
Horneman, Kenneth - Orbit Determination & Space-Surveillance Tracking
Hou, Zhili - Guidance, Navigation, and Control II , Orbital Debris & Space Environment
Howell, Kathleen C. - Dynamical Systems Theory , Trajectory Design & Optimization III ,Trajectory Design & Optimization V
Hsu, Oscar - Attitude Dynamics & Control I
Huang, Rosemary - Trajectory Design & Optimization I
Huang, Simeng - Guidance, Navigation, and Control II , Orbital Debris & Space Environment
Hudson, Jennifer - Artificial Intelligence in Astrodynamics , Trajectory Design & Optimization
V
Hussein, Islam - Space Situational Awareness & Conjunction Analysis
Hutchinson, Virgil - Large Space Structures & Tethers
Hwang, Yoola - Orbit Determination & Space-Surveillance Tracking
Ichinomiya, Kento - Trajectory Design & Optimization IV
Ikari, Satoshi - Orbital Dynamics, Perturbations, and Stability II , Proximity Missions &Formation Flying II
Ikeda, Hitoshi - Guidance, Navigation, and Control I , Orbital Dynamics, Perturbations, andStability II
Inamori, Takaya - Orbital Dynamics, Perturbations, and Stability II
Ito, Takahiro - Orbital Dynamics, Perturbations, and Stability IIiyer, shiva - Space Situational Awareness & Conjunction Analysis
Jackson, Wesley - Proximity Missions & Formation Flying I
Jah, Moriba K. - Orbital Debris & Space Environment , Space Situational Awareness &Conjunction Analysis
Jain, Amit - Atmospheric Re-entry & Satellite Constellations
Jefferson, David - Special Session - Mars InsightJenson, Erica - Trajectory Design & Optimization V
Jesick, Mark - Trajectory Design & Optimization I
Jiang, Fanghua - Artificial Intelligence in Astrodynamics, Trajectory Design & Optimization I ,Trajectory Design & Optimization II
Jin, Hengxian - Proximity Missions & Formation Flying III
Jin, Ting - Attitude Dynamics & Control II
Jo, Minji - Trajectory Design & Optimization VI
Johnson, Breanna - Atmospheric Re-entry & Satellite Constellations
Johnson, Kirk W. - Proximity Missions & Formation Flying II
Johnson, Mark - Special Session - Mars InsightJones, Brandon - Space Situational Awareness & Conjunction Analysis , Trajectory Design &Page 131

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Optimization V
Jones, Drew - Trajectory Design & Optimization II
Joshi, Anant - Attitude Dynamics & Control I
Junkins, John L. - Orbital Dynamics, Perturbations, and Stability II , Trajectory Design &Optimization VI
Kakihara, Kota - Space Situational Awareness & Flight Dynamics Operations
Kangas, Julie - Trajectory Design & Optimization I
Kaplinger, Brian - Asteroid & Non-Earth Orbiting Missions II , Atmospheric Re-entry & Satellite
Constellations , Space Situational Awareness & Flight Dynamics Operations
Karimi, Reza - Orbit Determination & Space-Surveillance Tracking , Trajectory Design &Optimization V
Karpenko, Mark - Attitude Dynamics & Control II , Guidance, Navigation, and Control I
Kawakatsu, Yasuhiro - Trajectory Design & Optimization IV
Kawamura, Evan - Guidance, Navigation, and Control II
Kayama, Yuki - Dynamical Systems Theory
Kelecy, Thomas - Orbital Debris & Space Environment , Space Situational Awareness & Flight
Dynamics Operations
Kenneally, Patrick - Attitude Dynamics & Control I
Kennedy, Brian - Orbital Dynamics, Perturbations, and Stability I
Kennedy, Thomas - Special Session - Mars Insight
Khan, Michael - Asteroid & Non-Earth Orbiting Missions I
Khatavkar, Yash - Attitude Dynamics & Control II
Khatiwada, Sital - Attitude Dynamics & Control I
Kidd, John - Asteroid & Non-Earth Orbiting Missions II
Kikuchi, Shota - Orbital Dynamics, Perturbations, and Stability II
Kim, Young-Rok - Space Situational Awareness & Flight Dynamics Operations
King, Jeffery - Attitude Dynamics & Control II
Kipp, Devin - Special Session - Mars Insight
Kolosa, Daniel - Trajectory Design & Optimization V
Komar, David - Trajectory Design & Optimization V
Komma, Justin - Proximity Missions & Formation Flying II
Kruizinga, Gerhard - Trajectory Design & Optimization I
Kuettel, Donald - Guidance, Navigation, and Control I
Kulkarni, Tejas - Astrodynamics
Laipert, Frank - Special Session - Mars Sample Return
Lambert, Diane - Asteroid & Non-Earth Orbiting Missions II
Landau, Damon - Dynamical Systems Theory, Trajectory Design & Optimization II , Trajectory
Design & Optimization III , Trajectory Design & Optimization V
Lane, Benjamin - Proximity Missions & Formation Flying II
Lange, Robert - Trajectory Design & Optimization I
Lantoine, Gregory - Asteroid & Non-Earth Orbiting Missions I
Lantukh, Demyan - Trajectory Design & Optimization I
Lau, Eunice - Astrodynamics , Special Session - Mars Insight , Trajectory Design & OptimizationII
Lauretta, Dante - Asteroid & Non-Earth Orbiting Missions II
Ledbetter, William - Asteroid & Non-Earth Orbiting Missions II
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Lee, Byoung-Sun - Orbit Determination & Space-Surveillance Tracking
Lee, Julim - Special Session - Mars InsightLee, Kyong - Special Session - Mars Insight
Lemmens, Stijn - Orbital Debris & Space Environment
Li, Chuanjiang - Trajectory Design & Optimization IVli, gangqiang - Large Space Structures & Tethers
Li, Haiyang - Artificial Intelligence in Astrodynamics
Li, Junfeng - Trajectory Design & Optimization I , Trajectory Design & Optimization II
Li, Kang - Proximity Missions & Formation Flying III
Li, Mu - Proximity Missions & Formation Flying III
Li, Peng - Proximity Missions & Formation Flying II
Liang, Bin - Guidance, Navigation, and Control II
Liang, Yuying - Orbital Dynamics, Perturbations, and Stability I , Proximity Missions &Formation Flying III
LIENART, Thomas - Guidance, Navigation, and Control I
Lin, Wei - Proximity Missions & Formation Flying III
LINARES, RICHARD - Artificial Intelligence in Astrodynamics , Guidance, Navigation, andControl I , Orbital Debris & Space Environment , Proximity Missions & Formation Flying I ,Proximity Missions & Formation Flying II , Space Situational Awareness & Conjunction
Analysis
Little, Jeffery - Trajectory Design & Optimization III
Litton, Daniel - Special Session - Mars Insight
Liu, Xiaoyu - Orbital Dynamics, Perturbations, and Stability II
Liu, Yuhan - Guidance, Navigation, and Control I
Lo, Martin Wen-Yu - Astrodynamics
Lock, Robert - Special Session - Mars Sample Return
Longman, Richard - Attitude Dynamics & Control II , Large Space Structures & Tethers
Lorda, Laurence - Asteroid & Non-Earth Orbiting Missions I , Trajectory Design & Optimization
I
Lorenz, Christopher - Trajectory Design & Optimization IV
Louisos, William - Asteroid & Non-Earth Orbiting Missions I
Lovell, Alan - Orbit Determination & Space-Surveillance Tracking, Proximity Missions &Formation Flying I
Lu, Ping - Atmospheric Re-entry & Satellite Constellations
Lucarelli, Dennis - Attitude Dynamics & Control II
Lyu, Yueyong - Guidance, Navigation, and Control I , Space Situational Awareness &Conjunction Analysis
Magallanes, Lara - Guidance, Navigation, and Control I
Majji, Manoranjan - Orbit Determination & Space-Surveillance Tracking , Trajectory Design &Optimization V
Mancini, Lucandrea - Trajectory Design & Optimization IV
Mansell, Justin - Asteroid & Non-Earth Orbiting Missions II
Markin, Robert - Trajectory Design & Optimization I
Marshall, Michael - Attitude Dynamics & Control II
Martin, Dillon - Atmospheric Re-entry & Satellite Constellations
Martin, Kaela - Trajectory Design & Optimization II , Trajectory Design & Optimization V
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Martin, Thierry - Asteroid & Non-Earth Orbiting Missions I
Martin-Mur, Tomas - Orbit Determination & Space-Surveillance Tracking , Special Session Mars Insight
Massari, Mauro - Artificial Intelligence in Astrodynamics , Trajectory Design & Optimization III
Massioni, Paolo - Trajectory Design & Optimization III
Masters, Andrew - Attitude Dynamics & Control I
Mathur, Ravishankar - Trajectory Design & Optimization V
Matunaga, Saburo - Trajectory Design & Optimization II
Mazanek, Dan - Trajectory Design & Optimization V
McCandless, Sarah Elizabeth - Orbit Determination & Space-Surveillance Tracking , Special
Session - Mars Insight , Trajectory Design & Optimization I
McCarthy, Brian - Trajectory Design & Optimization III
McCarty, Steven - Trajectory Design & Optimization IV
McCormack, John - Guidance, Navigation, and Control II
McElrath, Tim - Trajectory Design & Optimization I , Trajectory Design & Optimization II ,Trajectory Design & Optimization III , Trajectory Design & Optimization V
McInnes, Colin - Orbital Dynamics, Perturbations, and Stability II
McMahon, Jay - Asteroid & Non-Earth Orbiting Missions I , Asteroid & Non-Earth Orbiting
Missions II , Guidance, Navigation, and Control I , Orbital Dynamics, Perturbations, and Stability
I , Trajectory Design & Optimization III
McNeely, Drew - Space Situational Awareness & Conjunction Analysis
Meech, Karen - Asteroid & Non-Earth Orbiting Missions II
Mehta, Piyush - Orbital Debris & Space Environment
Melton, Robert G. - Artificial Intelligence in Astrodynamics
Menon, Premkumar - Special Session - Mars Insight
Mercier, Mark - Proximity Missions & Formation Flying II
Merrill, Raymond - Special Session - Mars Sample Return , Trajectory Design & Optimization I ,Trajectory Design & Optimization V
Mihaylov, Julia - Trajectory Design & Optimization II
Miller, Daniel - Artificial Intelligence in Astrodynamics
mirzaei, mehrdad - Special Session - Mars Sample Return
Moretto, Mark - Orbital Dynamics, Perturbations, and Stability I , Proximity Missions &Formation Flying I
Morita, Yasuhiro - Attitude Dynamics & Control II
Moses, Robert - Atmospheric Re-entry & Satellite Constellations
Mott, Katherine - Atmospheric Re-entry & Satellite Constellations
Mottinger, Neil - Special Session - Mars Insight , Trajectory Design & Optimization II
Moussi, Aurélie - Asteroid & Non-Earth Orbiting Missions I
MOYARD, John - Guidance, Navigation, and Control I
Murakami, David - Space Situational Awareness & Conjunction Analysis
Naasz, Bo - Proximity Missions & Formation Flying III
Nag, Sreeja - Space Situational Awareness & Conjunction Analysis
Nakajima, Yu - Guidance, Navigation, and Control I
Nakasuka, Shinichi - Proximity Missions & Formation Flying II , Space Situational Awareness &Flight Dynamics Operations
Nakhjiri, Navid - Artificial Intelligence in Astrodynamics
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Nandi, Sumita - Orbit Determination & Space-Surveillance Tracking
Neri, Agostino - Trajectory Design & Optimization IV
Newman, Brett - Space Situational Awareness & Flight Dynamics Operations
Newman, Clark - Attitude Dynamics & Control I
Nicholas, Austin - Special Session - Mars Sample Return
Nishi, Kentaro - Trajectory Design & Optimization II
Ogawa, Naoko - Guidance, Navigation, and Control II
Ogundele, Ayansola - Proximity Missions & Formation Flying I
Oguri, Kenshiro - Asteroid & Non-Earth Orbiting Missions I , Asteroid & Non-Earth Orbiting
Missions II
Oki, Yusuke - Orbital Dynamics, Perturbations, and Stability II
Olikara, Zubin - Orbit Determination & Space-Surveillance Tracking , Special Session - Mars
Sample Return
Olson, Ryan - Proximity Missions & Formation Flying I
Ono, Go - Orbital Dynamics, Perturbations, and Stability II
Orphee, Juan - Trajectory Design & Optimization III
Oshima, Kenta - Astrodynamics
Oshima, Yuki - Orbital Dynamics, Perturbations, and Stability II
Owen, William - Guidance, Navigation, and Control II
Ozaki, Naoya - Space Situational Awareness & Flight Dynamics Operations , Trajectory Design& Optimization I , Trajectory Design & Optimization II , Trajectory Design & Optimization IV
Ozawa, Satoru - Trajectory Design & Optimization II
Ozimek, Martin - Trajectory Design & Optimization III , Trajectory Design & Optimization V
Parker, Jeff - Asteroid & Non-Earth Orbiting Missions II
Paz, Brandon - Proximity Missions & Formation Flying III
Pearl, Jason - Asteroid & Non-Earth Orbiting Missions I , Trajectory Design & Optimization VI
Pelaez, Jesus - Asteroid & Non-Earth Orbiting Missions II , Orbital Dynamics, Perturbations, andStability I
Pellegrini, Etienne - Trajectory Design & Optimization V
Pellegrino, Marielle - Orbital Debris & Space Environment
Pellegrino, Sergio - Attitude Dynamics & Control II
Pengjie, Li - Attitude Dynamics & Control I , Large Space Structures & Tethers
Perryman, Trey - Trajectory Design & Optimization III
Petropoulos, Anastassios - Trajectory Design & Optimization I
Pezent, James - Trajectory Design & Optimization VI
Pfrang, Kaila - Trajectory Design & Optimization I
Phan, Minh - Attitude Dynamics & Control II , Large Space Structures & Tethers
Phillips, Sean - Trajectory Design & Optimization V
Piggott, Scott - Attitude Dynamics & Control I
Plice, Laura - Orbital Dynamics, Perturbations, and Stability I
Pontani, Mauro - Guidance, Navigation, and Control I , Trajectory Design & Optimization II
Praly, Nicolas - Guidance, Navigation, and Control II
PRIEUR, Pascal - Guidance, Navigation, and Control I
Punta, Elisabetta - Proximity Missions & Formation Flying III
Putnam, Zachary - Atmospheric Re-entry & Satellite Constellations
Qu, Min - Special Session - Mars Sample Return , Trajectory Design & Optimization I ,Page 135

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Trajectory Design & Optimization V
Rajbhandary, Aastha - Proximity Missions & Formation Flying III
Ramadan, Mohammad - Artificial Intelligence in Astrodynamics
Ranieri, Chris - Trajectory Design & Optimization I
Raposo-Pulido, Virginia - Asteroid & Non-Earth Orbiting Missions II , Orbital Dynamics,
Perturbations, and Stability I
Reinke, Zachary - Artificial Intelligence in Astrodynamics
Reiter, Jason - Space Situational Awareness & Conjunction Analysis , Trajectory Design &Optimization VI
Renevey, Sylvain - Proximity Missions & Formation Flying III
Renk, Florian - Asteroid & Non-Earth Orbiting Missions I
Restrepo, Ricardo - Astrodynamics
Riano-Rios, Camilo - Proximity Missions & Formation Flying III
Ricciardi, Lorenzo Angelo - Trajectory Design & Optimization IV
Richardson, Matthew - Orbital Debris & Space Environment
Riley, Jack - Trajectory Design & Optimization III
Roa, Javier - Asteroid & Non-Earth Orbiting Missions I
ROBERT, Alain - Guidance, Navigation, and Control I
RODRIGUES, Manuel - Guidance, Navigation, and Control I
Rogers, Gabe D. - Space Situational Awareness & Flight Dynamics Operations
Rolins, Armando - Space Situational Awareness & Flight Dynamics Operations
Romano, Marcello - Attitude Dynamics & Control II , Dynamical Systems Theory , Proximity
Missions & Formation Flying I , Proximity Missions & Formation Flying II
Rosengren, Aaron J. - Orbital Debris & Space Environment
Ryne, Mark - Trajectory Design & Optimization I , Trajectory Design & Optimization II
Saiki, Takanao - Guidance, Navigation, and Control II , Orbital Dynamics, Perturbations, andStability II
San Martin, A. Miguel - Astrodynamics
Scala, Francesca - Astrodynamics
Schaub, Hanspeter - Artificial Intelligence in Astrodynamics , Atmospheric Re-entry & Satellite
Constellations , Attitude Dynamics & Control I , Proximity Missions & Formation Flying II
Scheeres, Daniel Asteroid & Non-Earth Orbiting Missions II , Astrodynamics , Orbital Debris &Space Environment , Proximity Missions & Formation Flying II , Trajectory Design &Optimization V
Schlei, Wayne - Trajectory Design & Optimization III
Schlenker, Lauren - Proximity Missions & Formation Flying I
Schmid, Christine - Attitude Dynamics & Control I
Schulze, William - Special Session - Mars InsightSchumacher, Paul - Proximity Missions & Formation Flying I
Scorsoglio, Andrea - Artificial Intelligence in Astrodynamics
Scoubeau, Mehdi - Asteroid & Non-Earth Orbiting Missions I
Senent, Juan - Trajectory Design & Optimization II
Servadio, Simone - Orbit Determination & Space-Surveillance Tracking
Seubert, Jill - Special Session - Mars Insight , Trajectory Design & Optimization I
Shan, Jinjun - Orbital Dynamics, Perturbations, and Stability I
Shannon, Jackson - Trajectory Design & Optimization V
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FINAL PROGRAM

Sharma, Sumant - Proximity Missions & Formation Flying II
Sharp, Alanna - Attitude Dynamics & Control II
Shenoy, Prakash - Space Situational Awareness & Flight Dynamics Operations
Shouman, Mohamed - Proximity Missions & Formation Flying II , Proximity Missions &Formation Flying III
Siddique, Fazle - Trajectory Design & Optimization I , Trajectory Design & Optimization II
Sieling, Ryan - Attitude Dynamics & Control I
Signori, Gina - Special Session - Mars Insight
Simo, Jules - Orbital Dynamics, Perturbations, and Stability II
Sinclair, Andrew J. - Proximity Missions & Formation Flying III
Singh, Gurkipal - Astrodynamics
Singh, Lake - Trajectory Design & Optimization IV
Singh, Sandeep - Orbital Dynamics, Perturbations, and Stability II
Singla, Puneet - Artificial Intelligence in Astrodynamics , Atmospheric Re-entry & Satellite
Constellations , Orbit Determination & Space-Surveillance Tracking , Space Situational
Awareness & Conjunction Analysis , Special Session - Mars Sample Return , Trajectory Design& Optimization VI
Sizemore, Alex - Orbit Determination & Space-Surveillance Tracking
Skelton, Eugene - Proximity Missions & Formation Flying III
Sklyanskiy, Evgeniy - Special Session - Mars Insight
Skulsky, Eli - Astrodynamics
Soldini, Stefania - Space Situational Awareness & Conjunction Analysis
Song, Bing - Attitude Dynamics & Control II
Song, Young-Joo - Space Situational Awareness & Flight Dynamics Operations
Song, Yu Artificial - Intelligence in Astrodynamics
Sood, Rohan - Asteroid & Non-Earth Orbiting Missions II , Trajectory Design & Optimization VI
Souied, Youssef - Orbital Dynamics, Perturbations, and Stability I
Spear, Renee - Trajectory Design & Optimization II
Spencer, David A. - Asteroid & Non-Earth Orbiting Missions II , Atmospheric Re-entry &Satellite Constellations , Proximity Missions & Formation Flying III
Spencer, David B. - Proximity Missions & Formation Flying I , Space Situational Awareness &Conjunction Analysis , Trajectory Design & Optimization VI
Statham, Tamara - Trajectory Design & Optimization I
Stauch, Jason - Orbital Debris & Space Environment
Stein, William - Trajectory Design & Optimization I
Strange, Nathan - Trajectory Design & Optimization IV
Stuart, Jeffrey - Asteroid & Non-Earth Orbiting Missions II , Dynamical Systems Theory
Subbarao, Kamesh - Attitude Dynamics & Control I
Sullivan, Christopher - Dynamical Systems Theory
Sun, Xiucong - Proximity Missions & Formation Flying I
Sweetser, Theodore H. (Ted) - Astrodynamics
Taheri, Ehsan - Orbital Dynamics, Perturbations, and Stability II, Trajectory Design &Optimization VI
Takahashi, Shota - Asteroid & Non-Earth Orbiting Missions II
Takao, Yuki - Guidance, Navigation, and Control II
Takei, Yuto - Orbital Dynamics, Perturbations, and Stability II
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Takemura, Kazutoshi - Trajectory Design & Optimization IV
Takeuchi, Hiroshi - Orbital Dynamics, Perturbations, and Stability II
Tang, Xu - Guidance, Navigation, and Control II
Tarzi, Zahi - Orbit Determination & Space-Surveillance Tracking
Tasif, Tahsinul Haque - Orbital Dynamics, Perturbations, and Stability II
Teil, Thibaud - Artificial Intelligence in Astrodynamics , Attitude Dynamics & Control I
Thein, May-Win - Attitude Dynamics & Control I , Guidance, Navigation, and Control II
Thompson, Paul Frank - Trajectory Design & Optimization II
Thompson, Seth - Trajectory Design & Optimization I , Trajectory Design & Optimization III
Tiffin, Daniel - Trajectory Design & Optimization V
Tiscareno, Matthew - Trajectory Design & Optimization II
Tiwari, Madhur - Orbit Determination & Space-Surveillance Tracking
Topputo, Francesco - Artificial Intelligence in Astrodynamics , Asteroid & Non-Earth Orbiting
Missions I , Orbital Dynamics, Perturbations, and Stability I , Trajectory Design & Optimization
III
Trawny, Nikolas - Astrodynamics
Trenkel, Christian - Orbital Dynamics, Perturbations, and Stability I
Trisolini, Mirko - Orbital Debris & Space Environment
Tseng, Dong-Huei - Large Space Structures & Tethers
Tsuda, Yuichi - Asteroid & Non-Earth Orbiting Missions I , Guidance, Navigation, and Control II ,Orbital Dynamics, Perturbations, and Stability II , Space Situational Awareness & Conjunction
Analysis
Udrea, Bogdan - Proximity Missions & Formation Flying I , Proximity Missions & Formation
Flying II
Ulrich, Steve - Proximity Missions & Formation Flying I
Urrutxua, Hodei - Orbital Dynamics, Perturbations, and Stability I
Valerino, Powtawche - Trajectory Design & Optimization II
Van Wal, Stefaan - Asteroid & Non-Earth Orbiting Missions I
Vaquero, Mar -Astrodynamics , Trajectory Design & Optimization II
Varga, Gábor - Astrodynamics
Vasile, Massimiliano - Trajectory Design & Optimization II , Trajectory Design & Optimization
IV
Vavrina, Matthew - Proximity Missions & Formation Flying III
Venigalla, Chandrakanth - Proximity Missions & Formation Flying II
Vincent, Mark - Orbital Debris & Space Environment
Virani, Shahzad - Space Situational Awareness & Conjunction Analysis , Space Situational
Awareness & Flight Dynamics Operations
Virgili-Llop, Josep - Proximity Missions & Formation Flying I , Proximity Missions & Formation
Flying II
Volle, Michael - Space Situational Awareness & Flight Dynamics Operations
Wagner, Sean - Special Session - Mars Insight , Trajectory Design & Optimization I
Wall, Bradley - Trajectory Design & Optimization I
Wallace, Mark - Astrodynamics , Special Session - Mars Insight
Wang, Bowen - Attitude Dynamics & Control II
Wang, Hao - Atmospheric Re-entry & Satellite Constellations
Wang, Hongwen - Attitude Dynamics & Control I , Large Space Structures & Tethers , Proximity
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Missions & Formation Flying I
Wang, Huijiang - Proximity Missions & Formation Flying I
Wang, Pengyu - Space Situational Awareness & Conjunction Analysis
Wang, Shiqiang - Attitude Dynamics & Control I
Wang, Xinwei - Astrodynamics
Wang, Xuechuan - Astrodynamics
Wang, Xueqian - Guidance, Navigation, and Control II
Wang, Zhaowei - Trajectory Design & Optimization II
Wang, Zhenbo - Artificial Intelligence in Astrodynamics
Webb, Ryan - Special Session - Mars Sample Return
Webster, Cassandra - Trajectory Design & Optimization VI
Wetterer, Jack - Orbital Debris & Space Environment
Whitley, Ryan - Attitude Dynamics & Control I
Wie, Bong - Space Situational Awareness & Conjunction Analysis
Wilde, Markus - Atmospheric Re-entry & Satellite Constellations
Willis, Matthew - Proximity Missions & Formation Flying I
Wong, Mau C. - Trajectory Design & Optimization I
Woollands, Robyn - Orbital Dynamics, Perturbations, and Stability II , Special Session - Mars
Insight , Trajectory Design & Optimization VI
Woolley, Ryan - Special Session - Mars Sample Return
Wright, Charles - Guidance, Navigation, and Control I
Wu, Di - Trajectory Design & Optimization I , Trajectory Design & Optimization II
Xu, Ming - Orbital Dynamics, Perturbations, and Stability I , Proximity Missions & Formation
Flying III
Xu, Shijie - Orbital Dynamics, Perturbations, and Stability I
Yamaguchi, Tomohiro - Space Situational Awareness & Conjunction Analysis
Yamamoto, Toru - Guidance, Navigation, and Control I
Yanagida, Kanta - Trajectory Design & Optimization II
Yanao, Tomohiro - Trajectory Design & Optimization IV
Yaylali, David - Proximity Missions & Formation Flying III
York, Collin - Trajectory Design & Optimization III
Yoshikawa, Kent - Asteroid & Non-Earth Orbiting Missions I
Yoshimura, Hiroaki - Trajectory Design & Optimization IV
Young, Brian - Orbit Determination & Space-Surveillance Tracking
Yu, Wenbin - Atmospheric Re-entry & Satellite Constellations
Zanetti, Renato - Attitude Dynamics & Control I , Orbit Determination & Space-SurveillanceTracking
Zapata, Jorge Luis - Dynamical Systems Theory
Zavoli, Alessandro - Trajectory Design & Optimization IV
Zhang, Kaicheng - Guidance, Navigation, and Control II
Zhang, Shijie - Attitude Dynamics & Control I , Guidance, Navigation, and Control II
Zhao, Penglei - Atmospheric Re-entry & Satellite Constellations
Zhao, Yongchao - Guidance, Navigation, and Control II
Zhaowei, Sun - Guidance, Navigation, and Control I
Zhong, Rui - Attitude Dynamics & Control I , Large Space Structures & Tethers
Zhou, Botian - Attitude Dynamics & Control I , Guidance, Navigation, and Control II
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Zhu, George - Large Space Structures & Tethers , Proximity Missions & Formation Flying II
Zhu, Pingping - Proximity Missions & Formation Flying II
Zimmer, Aline K. - Astrodynamics , Trajectory Design & Optimization III
Zinner, Evan - Atmospheric Re-entry & Satellite Constellations
Zuehlke, David - Orbit Determination & Space-Surveillance Tracking

Session Chairs
Armellin, Roberto - Trajectory Design & Optimization V
Arrieta, Juan - Astrodynamics
Ciarcia, Marco - Attitude Dynamics & Control II
D'Amico, Simone - Orbital Debris & Space Environment
Davis, Diane - Dynamical Systems Theory
Dutta, Atri - Trajectory Design & Optimization IV
Furfaro, Roberto - Artificial Intelligence in Astrodynamics
Ghosh, Pradipto - Trajectory Design & Optimization VI
Gustafson, Eric - Special Session - Mars InsightHenderson, Troy - Guidance, Navigation, and Control II
Hernandez, Sonia - Trajectory Design & Optimization II
Hudson, Jennifer - Trajectory Design & Optimization VI
Hussein, Islam - Large Space Structures & Tethers
Jones, Brandon - Orbit Determination & Space-Surveillance Tracking
Kelecy, Thomas - Orbital Dynamics, Perturbations, and Stability II
Kim, Donghoon - Asteroid & Non-Earth Orbiting Missions I
Linares, Richard - Orbital Dynamics, Perturbations, and Stability I
Massari, Mauro - Proximity Missions & Formation Flying III
Newman, Brett - Proximity Missions & Formation Flying I
Ozimek, Martin - Trajectory Design & Optimization I
Park, Ryan - Space Situational Awareness & Flight Dynamics Operations
Renk, Florian - Space Situational Awareness & Conjunction Analysis
Romano, Marcello - Attitude Dynamics & Control I
Russell, Ryan - Trajectory Design & Optimization III
Scott, Christopher - Guidance, Navigation, and Control II
Sood, Rohan - Astrodynamics
Strange, Nathan - Space Situational Awareness & Flight Dynamics Operations
Subbarao, Kamesh - Atmospheric Re-entry & Satellite Constellations
Vaquero, Mar - Asteroid & Non-Earth Orbiting Missions II
Wilson, Roby - Proximity Missions & Formation Flying II
Woollands, Robyn - Guidance, Navigation, and Control I
Woolley, Ryan - Special Session - Mars Sample Return

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