Operation status of the asteroid
explorer, Hayabusa2
November 8, 2018
JAXA Hayabusa2 ProjectAgenda
Regarding Hayabusa2I
LReport on TD1-R3 operation
LReport on BOX-C operation
LDescription of conjunction operations
LOther topics (incl. DPS, Ryugu model)
Explanation of the Rover2 (MINERVA-II2) fromTohoku University, the representative of theuniversity consortium.
Contents
0. Hayabusa2 overview & mission flow outline
1. Project status & overall schedule
2. TD1-R3 operation report
3. BOX-C operation report
4. Solar conjunction operations
5. DPS Press Conference
6. Ryugu shape model
7. Other
8. Future plans
TD1-R3HSTouchdown 1 Rehearsal 3 (equivalent to the third rehearsal)
BOX-C operationS operation to descend by hovering from the home
position (about 20km altitude)
DPSSDivision for Planetary Sciences of the American Astronomical
SocietyMone of the world’s largest meetings on planetary scienceNOverview of Hayabusa2
ObjectiveWe will explore and sample the C-type asteroid Ryugu, which is a more primitive
type than the S-type asteroid Itokawa that Hayabusa explored, and elucidate
interactions between minerals, water, and organic matter in the primitive solar
system. By doing so, we will learn about the origin and evolution of Earth, theoceans, and life, and maintain and develop the technologies for deep-space return
exploration (as demonstrated with Hayabusa), a field in which Japan leads theworld.

Expected results and effects
LBy exploring a C-type asteroid, which is rich in water and organic materials, wewill clarify interactions between the building blocks of Earth and the evolution of
its oceans and life, thereby developing solar system science.
L Japan will further its worldwide lead in this field by taking on the new challenge ofobtaining samples from a crater produced by an impacting device.
LWe will establish stable technologies for return exploration of solar-system bodies.

Features:
LWorld’s first sample return mission to a C-type asteroid.
LWorld’s first attempt at a rendezvous with an asteroid and performance ofobservation before and after projectile impact from an impactor.
LComparison with results from Hayabusa will allow deeper understanding of the
distribution, origins, and evolution of materials in the solar system.

International positioningS
LJapan is a leader in the field of primitive body exploration, and visiting a type-C
asteroid marks a new accomplishment.
LThis mission builds on the originality and successes of the Hayabusa mission. In
addition to developing planetary science and solar system exploration
technologies in Japan, this mission develops new frontiers in exploration ofprimitive heavenly bodies.
LNASA too is conducting an asteroid sample return mission, OSIRIS-REx (launch:
2016; asteroid arrival: 2018; Earth return: 2023). We will exchange samples andotherwise promote scientific exchange, and expect further scientific findings
through comparison and investigation of the results from both missions.

(Illustration: Akihiro Ikeshita)
Hayabusa 2 primary specifications
Mass
Approx. 609 kg
Launch3 Dec 2014
MissionAsteroid return
Arrival27 June 2018
Earth return2020
Stay at asteroid
Approx. 18 months
Target body
Near-Earth asteroid Ryugu
Primary instruments
Sampling mechanism, re-entry capsule, optical cameras, laser range-finder,
scientific observation equipment (near-infrared, thermal infrared), impactor,
miniature rovers.

Mission Flow
Launch3 Dec 2014

Arrival at asteroid
June 27, 2018H▲
Earth swing-by
3 Dec 2015

Examine the asteroid by remote sensing
observations. Next, release a small lander androver and also obtain samples from the surface.

Earth returnlate 2020

Depart asteroid
Nov–Dec 2019

Create artificial
craterSample analysis(Illustrations: Akihiro Ikeshita)

After confirming safety, touchdown
within the crater and obtain
subsurface samples

Release impactor

Use an impactor to create
an artificial crater on theasteroid’s surface1. Current project status& schedule overview

Current statusS– Third rehearsal for touchdown, TD1-R3, was performed between October 23 –25. On October 25, a target marker was deployed at an altitude of about 13m,
Hayabusa2 descended to about 12m and the tracking of the target marker was
confirmed.
– BOX-C operation was carried out between October 27 – November 5, with thespacecraft descending to an altitude of about 2.2km on November 1. Imaging
the target marker was attempted successfully.

Schedule overview:
2015
3

12

Event	

3/9/'1
45+7'9/43

2016
10 12

%

launch	+) 

2017

4

8</3-(>'7 :3

4:73+>94'89+74/*

2020
12

Arrival at Ryugu	:3+ "++3912
7>
'79.7+9:73

89+74/*574=/2/9>45+7'9/438

Earth swing-by	+) '7 '>2019

6 7

'5574').

#M &N
9+8945+7'9/438 Southern hemisphere station
operations (CAN/MLG)	
'>  
!)9
'>

Ion engine operations ※	

2018

Departure from Ryugu	 4;U+)

Capsule re-entry	'9+


Optical navigation	
 Solar conjunction	'> :1 4;+)
4;

57

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$

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2. TD1-R3 operation reportPurpose

Operations to confirm the accuracy of the navigation
guidance control at low altitude:l Feedback the measured value from the LRF (Laser Range
Finder) to control the spacecraft.
l If the conditions are satisfied, deploy a target marker.
l Track detached target marker.
Resultl Altitude reduced to 12m: accuracy of navigation guidance: 15.4
m.MThe distances from the center of L08-B to the target markerNl Successful control of six degrees of freedom by the LRFMLaser
Range Finder).
l Successful target marker separation and tracking. 2. TD1-R3 operation report
TD1-R3 schedule

AltitudeReturn to home position
Home position

HHH20km

Target marker
separation
Deceleration ΔV

GCP-NAV (Ground Control Point Navigation)
HH→Method of determining the position andspeed of the spacecraft by observing
characteristic points on the asteroid
surface.

HPNAV (Home Position Navigation)
HH→Method of determining the position andspeed of the spacecraft from direction ofLowest altitude 12m the center of the asteroid image andattitude of the probe.
Increase ΔV

5km
~40m

Time
(JST)©JAXA

10/24
12:40

10/124
23:00

Target marker deployed
10/25 11:37Ialt. 13m

10/26



2. TD1-R3 operation report$ " 14<'19/9:*+8+6:+3)+
Descent at
10cm/s while
using LIDAR.

After tracking TM,
ascend and returnto 20km altitude.

LIDAR altitude measurement

Begin LRF altitudecontrol from ~25m
altitude.

Lateral thruster
injection tosynchronize withasteroid rotation
speed.

Descend a few meters
while pushing TM
towards surface toseparate.TMseparation

Maintain ~20m
altitude while
tracking TM withcamera

25m

20m
FLASH
use

TM track0m


2. TD1-R3 operation report
The target marker resting on the surface of Ryugu
Image of the surface of Ryugu
photographed by the Optical
Navigation Camera – Wide angle(ONC-W1) during TD1-R3.
This image was captured after thetarget marker landed on the surfaceof Ryugu. The white point at thearrow tip is the target marker andthe red circle indicates thetouchdown candidate region L08-B(diameter about 20m).
Image date: October 25 at 11:47
JST.
Image altitude: approx. 2
MImage creditSJAXAN2. TD1-R3 operation report

Image of the target marker descending (captured with the ONC-W1)

Image date: October 25 at 11:38 JST.
Image altitudeSapprox. 122
MThe black dot at the arrow tip is the shadow of thetarget marker)

New

Image data: October 25 at 11:39 JST
Image altitudeS approx122
MImage creditSJAXAN2. TD1-R3 operation report
Imaging	  the	  area	  around	  the	
  target	
  marker	
  with	  the	
  ONC-­‐T
New

Region around the target marker captured by the Optical Navigation Camera – Telescopic(ONC-T). Image taken at an altitude around 100m on October 25, 2018 at about 11:50 JST. (Image credit: JAXA, University of Tokyo, Kochi University, Rikkyo University, Nagoya University, Chiba Institute of Technology, Meiji
University, University of Aizu, AIST)



2. TD1-R3 operation report
Imaging the area around the target marker with the ONC-W1
NewArea around the target marker captured with the Optical Navigation Camera – Wide angle (ONC-W1) froman altitude of around 100m on October 25, 2018 at about 11:50 JST. The yellow square indicates the region
captured by the Optical Navigation Camera – Telescopic (ONC-T) on the previous slide, and the red circle isthe area of L08-B. The distance from the center of L08-B to the target marker (length of arrow) is 15.4m. (Image credit: JAXA, University of Tokyo, Kochi University, Rikkyo University, Nagoya University, Chiba Institute of Technology, Meiji
University, University of Aizu, AIST)



2. TD1-R3 operation report
ReferenceSSimilar to the L08-B areaMtaken during TD1-R1-AN

MmovieN↑ image with the Optical Navigation CameraWide angle (ONC-W1) at an altitude of about
47m. Time: October 15, 2018 at 22:45 JSTA#+6:+39/'1/2'-+84,">:-:/2'-+*(>9.+!59/)'1 ';/-'9/43'2+7'&/*+'3-1+! & 2'-+9/2+!)94(+7    ?  
#$$.+'19/9:*+/39.+,/789/2'-+/8'(4:9 214<+89'19/9:*+/8'(4:92'9 '3*
,/3'1'19/9:*+/8'(4:9  (Image credit: JAXA, University of Tokyo, Kochi
University, Rikkyo University, Nagoya University, Chiba
Institute of Technology, Meiji University, University of
Aizu, AIST)



2. TD1-R3 operation report
Let’s meet with the Le Petit Prince! Million Campaign 2
About the campaign:
PeriodSApril 10, 2013 – August 9, 2013
ContentsS
QPA sheet of names was placed within thetarget marker.
RPNames, messages, illustrations and photos
were put on a memory chip within the reentry capsule.
Registration
number7+'0*4<3(>7+-/43
'5'3

!9.+7
)4:397/+8

$'7-+92'70+7    

"++397>)'58:1+

   

 

$49'1    

About 180,000 names were delivered to Ryugu(Image credit JAXA)



2. TD1-R3 operation report
Process of mounting the name sheet within a target marker
CB

The entered names are printed on film.
The names are divided between two
films of the same shape.
EThe outer part of the target marker
is a sheet of material that canreflect a flash.

The films are wrappedaround the ball-shaped
core of the target marker.

FThe target marker is placed within
the reflective sheet and sewn withyarn so there are no gaps.

MImage creditSJAXAIAssistance with photographySNECN

D

After wrapping the core in the two pieces of film,
they are sealed with tape like the seams of abaseball.

G

The finished product!
Hayabusa2 carries five target markers. All the names
are printed inside each target marker in the same way.



2. TD1-R3 operation reportName sheet within the target marker

MImage creditSJAXAN2. TD1-R3 operation report
You can find the position of your name atS
https://www.haya2-campaign.jp/

OOOOOOO

Campaign entry page
MImage creditSJAXAN

By entering your registration ID number or name,you can search for the block where your name isinscribed. 
NoteSCurrently, this is available only for names in Japan(location where their registration ID number was assigned)  

3. TD1-R3 operation report
Images captured by the small monitor camera(animation N

During TD1-R3, these images were taken with the small monitor camera (CAM-H). Images
were shot every 5 seconds beginning immediately after rising to 11:47 JST on October 25,
2018 (altitude of about 21m). The ascending speed is about 52 cm/2. (Image credit: JAXA) 

3. BOX-C operation
J Between October 27 – November 5, the hovering altitudeof the spacecraft was reduced from the home position(about 20km altitude). This is the second BOX-C
operation.
J On October 30, operation “BOX-C1” reduced the altitudeof the the spacecraft to 5.1km and observations conductedwith the laser altimeter and optical navigation cameras.
J On November 1, operation “BOX-C2” further reduced thealtitude to about 2.2. km, where a successful attempt wasmade to image the target marker.

3. BOX-C operation
TD1-R1-A operation; before
dropping the target marker
L08-B

BOX-C operation: after the target
marker is dropped

No target marker yetHigh contrast image[Left] Image with the Optical Navigation Camera– Wide angle (ONC-W1) on 2018/10/15, 22:45(JST)
Altitude: 47 m
[Right] Image with the Optical Navigation Camera– Telescopic (ONC-T) on 2018/11/01 11:17 (JST)
Altitude: 2.4 km(Image credit: JAXA, University of Tokyo, Kochi University, Rikkyo University,
Nagoya University, Chiba Institute of Technology, Meiji University, University of
Aizu, AIST)

L08-B

Target Marker4. Conjunction operation
J “Conjunction” for spacecraft

2018.12.31

operation refers to the case where
the spacecraft is in the directionthat almost directly overlaps with
the Sun when viewed from Earth.

2018.11.20

Earth

J The alignment means that

communication with thespacecraft is not secure due toradiowaves radiated by the Sun.

SunJ In this period, critical operation is
not carried out.

J For Hayabusa2, the duration ofthis period is from late November
2018 – end of December.

Ryugu
Positions of Ryugu and the Earth©JAXA



4. Conjunction operation
Orbit and trajectory control during the operation
Orbit control
Name

Date

COI

2018/11/23

TCM1

2018/11/30

TCM2

2018/12/25

HPR

2018/12/29

Due to the influence from solar tidal forces,
asteroid gravity and solar light pressure, thetrajectory forms a complex shape.

COI : Conjunction Orbit Insertion
HHHHH
TCM : Trajectory Correction Maneuver
HHHHH
HPR : Home Position Recovery
HHHHH©JAXA

Transition orbit during solar conjunction in the home
position coordinate system4. Conjunction operation
Operation details(1) Preparation period M2018/11/18-2018/11/29N
On November 23, 2018, the spacecraft will be placed into the conjunction transition orbit at
the COI point. As the SEP angle (angle formed by the Sun – Earth – spacecraft) decreases
from six degrees to 3 degrees, communication will still be possible. Observations will be
performed with the Optical Navigation Camera – Wide angle (ONC-W1) for two days before
the orbit control maneuver (TCM1) on November 30, 2018. After conjunction, the positional
relationship between the Sun, Earth and asteroid will be mirrored so a 180 degree attitude
rotation will be performed before entering the conjunction period.
(2) Duration M2018/11/30-2018/12/21N
During this period, the SEP angle decreases below 3 degrees, making it difficult tocommunicate with spacecraft. No trajectory control is performed, but communication withthe spacecraft is still attempted. This is a valuable opportunity to investigate the Sun’senvironment. (3) Reversion period M2018/12/22-2019/01/01N
In this period of return after conjunction there will be two days of observations after which
the orbital control maneuver (TMC2) will be performed on December 25, 2018. Home
Position Return control (HPR) maneuver will be performed on December 29, 2018 to returnthe spacecraft to the home position. 5. DPS press conferenceDPS = Division for Planetary Sciences of the American Astronomical
SocietyMone of the world’s largest academic societies in planetaryscience, date/placeS October 21 – 26, Knoxville, USA.
J Hayabusa2 press conference: October 25, 12:15 ~ 13:15 (October 26,
01:15 ~ 02:15 JSTNJ InformationShttps://aas.org/meetings/dps50/2nd-media-advisory
J TitleSHayabusa2 Explores Asteroid Ryugu
J PresentersMtitles omittedNSMasaki FujimotoMJAXANIHikaru
YabutaMHiroshima U.N, Eri TatsumiMU. TokyoNIDeborah Domingue(Planetary Science Institute)ILucille Le Corre (Planetary Science
Institute)IRalf Jaumann (German Aerospace Center)@ Hayabusa2 Special Session at DPS on October 25 (poster presentation #13), October
26 (oral announcement #9).


5. DPS press conference
Session outline (in order of presentation)■Masaki FujimotoSHayabusa2 Project
LOutline of project progress and observations of Ryugu■Ralf JaumannSMASCOT: Decent, Landing and on-Asteroid Activity
LIntroduction to ; landing and surface operations■Tatsumi EriSRyugu's surface seen from Hayabusa2's remote-sensing observations
LCharacteristics of Ryugu’s surface images by the optical navigation cameras.
■Deborah DomingueSRyugu's surface seen from Hayabusa2's remote-sensing observations
LThe rocky surface of Ryugu, with no regolith like the Moon.
■Lucille Le CorreSAsteroid Ryugu imaged at high resolution
LDetailed topographical model of the surface of Ryugu■Hikaru YabutaSLanding site selection to provide key scientific and engineering findings
from proximal operations and material sampling
LLanding site selection process and results.

5. DPS press conference
Photograph from the press conference

October 25, 2018TKnoxville© Shantanu P. Naidu

6. Ryugu shape model
J JAXA Space Exploration Innovation Hubunveils a simple version of the shapemodel.
J The Hayabusa2 Science Team isdeveloping a precise shape model for
Ryugu.
J Schedule for release with the publicationof the associated paper.
6. Ryugu shape model
Data release of the Ryugu simple shape model by JAXA Space
Exploration Innovation HubJ

Through collaborative research at the Space Exploration
Innovation Hub (Task name: autonomous location
estimation and environmental map creation from exploration
robot images, 2 pairs of 2 companies: Qoncept, Morpho,
Ivis, ViewPLUSN, the three-dimensional shape of Ryugu
was constructed using only image information.

J

The three-dimensional model of Ryugu obtained by thismethod is described as a “simplified shape model” andavailable as a data file. MBecause it is a simple model, thiscannot be used for science or engineering purposes)

HJPublic URL MWebsite of the Space Exploration Innovation
Hub)K
http://www.ihub-tansa.jaxa.jp/ryugu_mokei.html
J

The simplified shape model uses the animation from thearticle on the Hayabusa2 home page entitled “This is Ryugu– a global image in 3D” taken with the Optical Navigation
Camera – Telescopic (ONC-T) on 6/23 at an altitude ofabout 40km. 

Ryugu simple shape model
HHNumber of verticesS157,500
HHNumber of triangular patchesS52,600
HHFile sizeS4MBIFBX format

CooperationSHayabusa2 Project
CreditSJAXA Space Exploration
Innovation Hub / Qoncept,
Morpho, Ivis, ViewPLUS@ Data files can be views with a
3D display tool or the model
output to a 3D printer.

7. Other
■Place names on Ryugu
J A proposal for naming regions of Ryugu was submitted to
the IAU (International Astronomical Union) Working
Group for Planetary System Nomenclature. We are
currently awaiting the results of their consideration.
■OSIRIS-Rex captures image of asteroid Bennu
J OSIRIS-Rex successfully photographed asteroid Bennu,
whose shape was shown to be similar to Ryugu. 7. OtherManimationN

ReferenceSAsteroid Bennu
Bennu Full Rotation at
200 Pixels
J Rotation period: 4hours 11 minutes.
J November 2, 2018
J PolyCam camera
J Shot every 10 degrees
J Distance: 122 miles(197 km)
J Credit: NASA/
Goddard/ University of
Arizona8. Future plans■Scheduled operations
J Late November UDecemberSsolar conjunction■Media and press briefings
J December 6 MThursdayNH13:30U16:00MguidelineNH
Reporters’ conference TSagimihara
J December 13 MThursdayNH11:00HReporters’ briefing T
Ochanomizu

Reference materialSmall Monitor Camera MCAM−HNNJ Camera built & mounted from donation funds.
J View down sampler horn.

The location of CAM-H

Sampler horn

M©JAXANHome Position Coordinate System
Earth

Sun

ZHP

YHP
Ryugu

XHP

BOX definition
Earth Sun

Home position
coordinate system
MXHP, YHP, ZHPN
BOX-A

MReference materialN
BOX-B

BOX YHP-direction size
BOX-C

C1
C2
asteroid averageradiusasteroid center of mass

BOX-A operationSoperations while hovering at
20km altitude. Regular operation standard.
BOX-B operationSTour observation. Hovering
area extended horizontally to enable
observations to either side of the asteroid.
BOX-C operationSHovering area extended
vertically to enable observations at low
altitude. Target Marker
J Size of body (ball): about 10cm
J Retroreflective film
J 4 barsSrolling prevention
J Inside contains many polyimide globules
J First to separateSB
J Order of separation : B→A→E→C→D
J On the inside of the target marker is asheet on which is written the names ofmembers from the general public. 

A

B

C

D

E

