Planetary Science Deep Space SmallSat Studies

1

Planetary Science Deep Space SmallSat Studies

Carolyn Mercer

Program Officer, PSDS3

NASA Glenn Research Center

Lunar Planetary Science Conference Special Session

March 18, 2018

The Woodlands, Texas
Planetary Science Deep Space SmallSat Studies

SMD CubeSat/SmallSat Approach

2

National Academies Report (2016) concluded that 

CubeSats have proven their ability to produce highvalue science: 

• Useful as targeted investigations to augment the 

capabilities of larger missions

• Useful to make highly-specific measurements 

• Constellations of 10-100 CubeSat/SmallSat

spacecraft have the potential to enable 

transformational science 

SMD is developing a directorate-wide approach to:

• Identify high-priority science objectives in each 

discipline that can be addressed with 

CubeSats/SmallSats

• Manage program with appropriate cost and risk

• Establish a multi-discipline approach and 

collaboration that helps science teams learn from 

experiences and grow capability, while avoiding 

unnecessary duplication

• Leverage and partner with a growing commercial 

sector to collaboratively drive instrument and 

sensor innovation
PLANETARY SCIENCE DEEP SPACE SMALLSAT STUDIES

(PSDS3)

• NASA Research Announcement released August 19, 2016

• Solicited concept studies for potential CubeSats and SmallSats

– Concepts sought for 1U to ESPA-class missions

– Up to $100M mission concept studies considered

– Not constrained to fly with an existing mission

• Objectives:

– What Planetary Science investigations can be done with SmallSats?

– What technology development is needed to enable them?

– What’s the anticipated cost range?

• Received 102 proposals

• Funded 19 Studies
Mars

Robert Lillis, Mars Ion and Sputtering Escape Network (MISEN)

Anthony Colaprete, Aeolus - to study the thermal and wind environment of Mars

Luca Montabone, Mars Aerosol Tracker (MAT)

Michael Collier, PRISM: Phobos Regolith Ion Sample Mission 

David Minton, Chariot to the Moons of Mars

Venus

Valeria Cottini, CUVE - Cubesat UV Experiment

Christophe Sotin, Cupid's Arrow

Attila Komjathy, Venus Airglow Monitoring Orbiter for Seismicity (VAMOS)

Tibor Kremic, Seismic and Atmospheric Exploration of Venus (SAEVe) 

Icy Bodies and Outer Planets

Robert Ebert, JUpiter MagnetosPheric boundary ExploreR (JUMPER)

Kunio Sayanagi, SNAP: Small Next-generation Atmospheric Probe

Small Bodies

Beau Bierhaus, Ross (formerly CAESAR)

Jeffrey Plescia, APEX: Asteroid Probe Experiment

Tilak Hewagama, Primitive Object Volatile Explorer (PrOVE)

Moon

Suzanne Romaine, CubeSat X-ray Telescope (CubeX)

Charles Hibbitts, Lunar Water Assessment, Transportation, and Resource Mission (WATER)

Noah Petro, Mini Lunar Volatiles (MiLUV) Mission

Timothy Stubbs, Bi-sat Observations of the Lunar Atmosphere above Swirls (BOLAS)

David Draper, Irregular Mare Patch Exploration Lander (IMPEL)

Planetary Science 

Deep Space SmallSat Studies: Awards

4
Small Innovative Missions For 

Planetary Exploration (SIMPLEx)

• Solicit formulation and development of planetary science 

investigations that require a spaceflight mission that can be 

accomplished using small spacecraft

– ESPA-Class or smaller (< 180Kg)

– Solicitation for secondary payload on specific primary missions, 

which will determine:

• Launch readiness date

• Initial release trajectory

– Cost-capped missions: $15M to $55M

– Continuously Open call with mission-specific deadlines

https://soma.larc.nasa.gov/simplex
SIMPLEx Process (Section 3)

Soon: Release Open Call for proposals 

(public comment period on draft closed March 14)

On-going: Regular Panel Reviews of submitted proposals

Mission Specific Milestones:

• L-4 years: Cut-off consideration for a specific mission

– Select and award ~1 year Phase A/B studies; expected product is PDR-level design

– Launch Vehicle is unknown

• L-3 years: Down-select secondary mission(s) for specific primary mission

– May be possible to select multiple secondaries for a given primary mission

– Selectability coordination with LV selection

– Provided for Phase C design/build:

• More detailed Launch Vehicle trajectory, environments and interfaces

• L-2 years: Build/test secondary payload

• L-1 years: Build/test/integrate secondary payload
SIMPLEx Launch Opportunities

Primary 

Mission

SIMPLEx

Proposal 

Cut-off 

Date

Payload 

Integration 

/Launch 

Readiness 

Dates

Launch Site

Primary 

Payload 

Destination

Launch 

Orbit

Allowed Elements

Potential

Launch 

Vehicle

CubeSat DeployerESPA RingESPA GrandePropulsive ESPA ringRadioactive elements

LEO or GTO On-going On-going Various N/A LEO or 

GTO Y Y Y Y N

Lucy 1 July 2018 August 2021 / 

16 October 2021

Cape Canaveral 

Air Force 

Station

Jupiter L4 

and L5 

Trojan 

Swarms

Heliocentric 

Escape Y Y N N N

Atlas V, 

Falcon 

9, 

Antares, 

...

Psyche 1 July 2018 June 2022 / 

August 2022

Cape Canaveral 

Air Force 

Station

(16) Psyche, 

with Mars 

gravity assist

Elliptic 

Heliocentric Y Y N N N

Atlas V, 

Falcon 

9, 

Antares, 

...

IMAP* TBA TBD TBD TBD TBD N Y N N N TBD

EM-x TBA TBD Kennedy Space 

Center

Lunar Orbit TBD Y N N N N SLS

Table A-1 https://soma.larc.nasa.gov/simplex
SIMPLEx Technology

It is expected that new technologies may be required to accomplish planetary science 

missions proposed under this PEA. Proposals must justify how the proposed technology will 

contribute to mission success. 

For technologies and subsystems that do not have flight heritage, the proposal must include a 

reference to the details and the results of testing and/or analysis that demonstrate performance in 

a relevant environment under conditions that simulate all known significant failure modes 

of the technology to demonstrate technical maturity of TRL 6. If a combination of this testing and 

analysis is proposed to be accomplished in Phase A/B, then a reference must be included 

describing what testing/analysis is planned or has been completed at the time of proposal 

submission to demonstrate a plan for maturing these systems to TRL 6 by PDR. A summary of 

the test/analysis should be included in the body of the proposal. Proposals must include a limited 

life item list and for those items show plans for how they can meet 1.5 times the worst-case 

expected operating life of the proposed mission.

For technologies and subsystems that do have flight heritage, claims of heritage must be 

supported by a description of the similarities in design and flight environments between the 

heritage and the proposed mission.

Section 4.6.1 https://soma.larc.nasa.gov/simplex
Planetary Science Deep Space SmallSat Studies

Science Objectives: Mission Overview:

Team Members/Institutions:

MISEN

ion escape flux @ 3000 km

3-5 spacecraft. Orbits 

chosen to 

maximize coverage

Ion dynamics drives escape 

and hence climate evolution

SC Bus enables 

plasma and 

magnetic field

measurements

Use multi-point simultaneous measurements to 

characterize the magnitude, global patterns, variability, 

and real-time response to space weather, of:

i) ion escape at Mars

ii) ion precipitation-driven sputtering escape at Mars

Measurements:

• Ion and electron energy, direction, flux

• Magnetic field

As multi-point measurements have revolutionized our understanding of

the Earth's magnetosphere, MISEN will build on MAVEN’s legacy for a

fraction of the cost and, for the first time, reveal the dynamic global

picture of ion escape and precipitationat Mars.

UC Berkeley SSL

Principal Investigator: Rob Lillis

Systems Engineer: Dave Curtis

Ion Analyzer Lead: D. Larson

Ion Dynamics: S. Curry, J. Luhmann, 

D. Brain (collaborator, U. Colorado)

Advanced Space LLC

Lead mission designer: 

Jeffrey Parker

UCLA ESS

Magnetometer lead: 

Christopher Russell

Tyvak LLC

Lead spacecraft engineer: 

Jordi Suig-Puari

Ride-along SEP 

cruise to Mars with 

Psyche (15 months) 

11-month 

spiral down 

to final orbits

• 2-year primary science mission.

• Navigation: final orbits should 

precess, no station-keeping.

• Simple ops: spinning spacecraft, 

constant data collection.

• Telemetry: relay and direct-to-earth 

options available

Credit: NASA/CU

Mars Ion and Sputtering Escape Network 
Planetary Science Deep Space SmallSat Studies

Aeolus

Aeolus will make the first direct 

observations of day and nighttime 

winds at all local times

Aeolus Science Objectives:

1. Produce a vertically resolved global wind speed 

map

2. Determine the global energy balance of Mars

3. Correlate wind speeds and surface temperatures 

with CO2 and H2O clouds and dust column 

densities

Mission Overview:

• Aeolus’s inclined orbit allows 

observations between ±75° and at all 

local times

• Spatial Heterodyne Spectrometers 

(SHS) and Mini-TES scan the 

atmosphere limb providing wind 

vectors, temperatures and 

aerosol/cloud densities

• SurSeP (Surface Radiometric Sensing Package) looks nadir measuring the 

total upwelling solar and thermal 

radiance as well as the surface 

temperature and column aerosol/cloud 

density

Team Members/Institutions:

Mini-TES

SHS

SHS SuRSeP

28kkg / 24U / 117W-OAP Spacecraft

6U Payload

The Aeolus Spacecraft

A Mission to Study the Winds of Mars
Planetary Science Deep Space SmallSat Studies

MAT 

Science Objectives: Mission Overview:

Team Members/Institutions:

Mars Aerosol Tracker: An areostationary SmallSat

to monitor Martian dust and water ice dynamics.

Principal Investigator:

Luca Montabone (Space Science Institute, CO)

Co-Investigators:

Michael VanWoerkom (ExoTerra Resource LLC, CO)

Bruce A. Cantor (Malin Space Science Systems, CA)

Michael J. Wolff (Space Science Institute, CO)

Collaborators:

Michael D. Smith (NASA GSFC, MD)

François Forget (CNRS/LMD, France)

Michel Capderou(CNRS/LMD, France)

 Monitor a large, fixed region of the planet where 

dust storms and water ice clouds are likely to occur, 

using visible and infrared wavelengthswith a 

high sampling rate;

 Observe the temporal evolution of dust storms 

and water ice clouds in the monitored area 

throughout the diurnal cycle;

 Detect changes in surface physical properties 

(e.g. thermal inertia and albedo) throughout the 

diurnal cycle, and particularly after the occurrence 

and decay of large dust storms.

 Spacecraft: ESPA-class orbiter; 45 kg; electric 

propulsion (micro Hall thrusters, Xe gas propellant).

 Payload: 1 visible and 2 thermal infrared cameras; 

filters for 6 IR spectral ranges, from 7.9 to 16 μm.

 Journey to Mars: Rideshare on a primary mission 

to Mars; deployment before Mars capture (baseline).

 Orbit: Areostationary (i.e. equatorial, circular, 

planet-synchronous orbit) at 17,031.5 km above the 

equator at one of the 2 stable longitudes (baseline). 

 Duration: 1 Martian year (primary mission).

Figure: The MAT 

SmallSat overviews a

regional dust storm on 

Mars from 

areostationary orbit, 

obtaining visible 

images in daytime and 

column dust optical 

depth measurements 

in daytime as well as 

nighttime.
Planetary Science Deep Space SmallSat Studies

PRISM Phobos Regolith Ion Sample Mission

Science Objectives:

The PRISM CubeSat mission will determine the

origin of Phobos: Did it form in the outer solar

system or in situ near Mars, perhaps through a

collision or by coalescence of a debris disk left

over from the formation of Mars? PRISM will

measure Phobos’ surface composition using

secondary ion mass spectrometry or SIMS and

answer this critical question.

Mission Overview:

PRISM, a 12U CubeSat, will be ejected from the upper

stage of the launch vehicle a few days after launch and,

using a low thrust Solar Electric Propulsion system, will

arrive at Mars in about two years and begin taking data

during an approximately six-month spiral-in period. At the

end of this spiral-in phase, PRISM will be in a Phobos coorbit, making a pass and measurements near Deimos in the

process. PRISM will probe the surface in a Phobos

retrograde orbit at a distance as low as 27 km including the

Mars facing and far sides of Phobos, both red and blue

units, and craters on the leading edge.

Team Members/Institutions:

• NASA/GSFC: Michael R. Collier, William M. Farrell,

David Folta, John Keller, Richard Vondrak, Timothy

Stubbs, Rosemary Killen, Menelaos Sarantos

• Morehead St. University, KY: Ben Malphrus

• JHU/APL: Andy Rivkin, Scott Murchie, Dana Hurley

• University of Iowa: Jasper Halekas

• Georgia Institute of Technology: Micah Schaible

• JPL: Pamela Clark
Planetary Science Deep Space SmallSat Studies

Chariot to the Moons of Mars

Science Objectives:

1. Determine the origin of moons of Mars, Phobos 

and Deimos

2. Evaluate the potential for resource extraction to 

support human exploration on the moons

3. Observe the effects of geologic 

processes contributing to the ongoing evolution 

of the Phobos-Deimos system

Mission Overview:

• Will piggyback on another Mars mission for launch, but 

will be a free flier after separation from the upper stage

• Cruise/aerocapture vehicle with drag modulation 

trajectory control

• 12U CubeSat, 3-axis stabilized, electric propulsion

• One Mars year mapping mission of Phobos & Deimos

• Remote sensing instrument suite

– Spectroscopy and visible imaging

• Mission Operations Center at Purdue University

• Science Operations Center at Arizona State University

Team Members/Institutions:

PI: David Minton (Purdue)

Co-Is:

Briony Horgan (Purdue) 

David Spencer (Purdue)

Philip Christensen (Arizona State University)

Zachary Putnam (Univ. of Illinois at Urbana-Champaign)

Austin Williams (Tyvak Inc.)

Graduate Students

Jacob Elliot (Purdue), Rohan Deshmukh (Purdue)

Collaborators

Andrew Rivkin (JHU/APL), Matija Cuk (SETI), 

Francesca DeMeo (MIT), Erik Asphaug (ASU)
Planetary Science Deep Space SmallSat Studies

CUVE

Science Objectives:

• Nature of the "Unknown” UV-absorber (range 320 –

490 nm) which drives Venus’ thermal radiative 

balance

• Abundances and distributions of SO2 and SO at 

and above Venus’s cloud tops and their correlation 

with the UV absorber (range 190 – 320 nm)

• Atmospheric dynamics at the cloud tops using wind 

tracking (190 – 490 nm) and structure of upper 

clouds

• Nightglow emissions: NO (190-300 nm), CO (205-

240 nm), O2 (400-500 nm)

Mission Overview:

Baseline Spacecraft Configuration 

6U to 12U Cubesat (e.g. Morehead or Dellingr)

• Cruise < 1.5 year, Science phase > 0.5 year

• Propulsion: Chemical, EP, cold gas

• Power Generation: solar arrays

• Polar orbit around Venus 

• Nadir dayside and nightside observations

Payload includes (2U, 2kg)

• UV spectrometer 190 – 570 nm, 0.3 nm spectral 

resolution

• UV imager broadband centered at 365 nm

Team Members/Institutions:

Principal Investigator: 

Valeria Cottini (University of Maryland College Park)

Co-Investigators: 

Shahid Aslam (NASA, GSFC)

Nicolas Gorius (Catholic University of America)

Tilak Hewagama (University of Maryland College Park)

Giuseppe Piccioni (INAF-IAPS, Italy)

Collaborators: 

Lori Glaze (NASA, GSFC)

Nikolay Ignatiev (IKI RAN, Russia)

Emiliano D’Aversa (INAF-IAPS, Italy)

Cubesat UV Experiment: Unveil Venus’ UV Absorber with 

Cubesat UV Mapping Spectrometer
Planetary Science Deep Space SmallSat Studies

Cupid’s Arrow

Science Objectives:

1. Determine how did the atmosphere of Venus 

form and evolve?

2. Compare the primordial volatile compounds 

of the Earth, Mars, and Venus?

3. Determine the volcanic history of Venus

These objectives are achieved by measuring the 

abundances of noble gases (Ne, Ar, Kr, Xe) and 

their isotopic ratios in Venus’ atmosphere below 

the homopause (well mixed atmosphere)

Mission Overview:

Team Members/Institutions:

• Several Venus-bound trajectory options to be studied:

a) Free-flyer launched directly from Earth

b) Drop-off on a gravity assist flyby

c) Drop-off from orbit 

• Probe (mass <30 kg; diam. 60 cm) skims through the 

atmosphere 

• At closest approach (below the homopause), spinstabilized probe grabs a sample of the atmosphere

• Sample is analyzed in a compact mass spectrometer (4 

kg, 31 W, 4U CubeSat form factor)

• Sample analysis data are relayed back to Earth

Christophe Sotin JPL

Guillaume Avice Caltech

John Baker JPL

Murray Darrach JPL

Anthony Freeman JPL

Glenn Lightsey Georgia Tech

Bernard Marty Univ. Nancy

Stojan Madzunkov JPL

Daniel Wenkert JPL

Sterling Peet Georgia Tech

Terry Stevenson – graduate std. Georgia Tech

Atelier team JPL 

A small satellite to measure noble 

gases in Venus' atmosphere
Planetary Science Deep Space SmallSat Studies

VAMOS

Mission Overview:

• Launch SmallSat (<180 kg) into high earth 

orbit as rideshare with larger spacecraft

• Inject into trajectory to Venus using SEP 

(one Earth flyby and one Venus flyby) 

• Insert into 24 hour Venus circular orbit in 

the Sun-Venus plane

• Infrared imaging in two channels: 1.17 μm 

and 4.3 μm building of atmospheric and 

ionospheric waves emanating from Venus 

quakes

Team Members/Institutions:

• Principal Investigator: A. Komjathy of JPL 

• Team JPL: engineering, science

• U. of Illinois, U. of Michigan: modeling, 

signal processing 

• IPGP, CNES, and Geoazur, France: 

modeling, science

• DLR, Germany: instrument design 

Science Objectives:

• Determine the global seismic activity of 

Venus (± 1 Moment magnitude)

• Determine the thickness of the crust 

• Determine oxygen atom abundance and 

variability at 90-110 km altitude from O2

emission 

• Determine horizontal wind velocity 

amplitude (±30 m/s) and direction (±30°) 

from gravity waves detected in O2 emission

Venus Airglow Monitoring Orbiter for Seismicity 
Planetary Science Deep Space SmallSat Studies

SAEVe

Science Objectives:

1) Determine if Venus is seismically active and characterize the 

rate and style of activity

2) Determine the thickness and composition of the crust 

3) Acquire temporal near surface meteorological data to guide 

global circulation models

4) Estimate moment exchange between the planet and its 

atmosphere

5) Measure atmospheric chemistry variability

6) Determine current rate of heat loss from the Venus interior

7) Examine rock and soil distribution and morphology

Mission Overview:

Team Members/Institutions:

Seismic and 

Atmospheric Exploration 

of Venus

Tibor Kremic NASA Glenn

Richard Ghail Imperial College London

Martha Gilmore Wesleyan University

Gary Hunter NASA Glenn

Walter Kiefer Lunar and Planetary Institute

Sanjay Limaye University of Wisconsin

Michale Pauken Jet Propulsion Lab

Colin Wilson University of Oxford

• Leverages recent advances in high-temp electronics & systems 

• Focuses on temporal science and incorporates innovative 

operations approach to make first ever long-duration 

measurements from the surface of Venus

SAEVe revolutionizes our 

paradigm for exploring the 

deep atmosphere, surface, 

and geophysical activity 

of Venus via enabling new 

technologies

Two probes delivered to Venus via ride along

- Probes enter Venus atmosphere via Stardust-like entry capsule

- Descend to surface through the thickening atmosphere

- Turn on and autonomously implement operations

Probes will

Measure seismic data, heat flux, wind speed and direction, abundance of 

atmospheric elements, radiance, temperature and pressure.

Landers will also return images supporting context, morphology and 

instrument coupling information

Transmit data to orbiting spacecraft / comm relay at pre-set intervals for an 

unprecedented 120 days, over 3 orders of magnitude > current record!

Validate capabilities and technologies paving the way for larger, more 

complex Venus lander missions in the future
Planetary Science Deep Space SmallSat Studies

1. Characterize the solar wind upstream of Jupiter’s 

magnetosphere and provide additional context for 

studying magnetospheric dynamics by the primary 

spacecraft.

2. Investigate the modes of solar wind coupling (e.g. 

magnetic reconnection, Kelvin-Helmholtz waves) 

along Jupiter’s dayside magnetopause.

3. Determine the flux, energy spectra, and spatial 

distribution of energetic neutral atoms (ENAs) 

escaping from Jupiter’s magnetosphere.

Spacecraft Overview:

Team Members/Institutions:

The spacecraft consists of an ESPA frame supporting four 

double-deployed solar array panels, and four science 

instruments. A CubeSat sized electronics vault will house 

a majority of the electronics, shielding them from radiation.

Science Objectives:

JUMPER is a Jupiter orbiting 

SmallSat mission concept to 

(i) understand the solar 

wind’s interaction with 

Jupiter’s magnetosphere 

and (ii) quantify the contribution from energetic neutral 

atoms (ENAs) to mass loss 

from Jupiter’s space 

environment.

JUMPER will ride to Jupiter 

onboard another spacecraft 

such as NASA’s Europa 

Clipper.

JUMPER A SmallSat to Explore Jupiter’s Magnetospheric Boundaries 

and Image its Energetic Neutral Atom Emissions
Planetary Science Deep Space SmallSat Studies

SNAP Small Next-Generation Atmospheric Probe

Science Objectives:

SNAP will examine the physical and chemical processes in the 

atmosphere of Uranus to understand the origin and evolution of 

the giant planets and the Solar System. 

Tier-1 Objectives

Determine spatial differences of the following atmospheric 

properties from the Main Probe entry site: 

1. Vertical distribution of cloud-forming molecules

2. Thermal stratification

3. Wind speed as a function of depth

Tier-2 Objectives

Augment Main Probe Science Objectives: 

4. Measure abundances of the noble gases (He, Ne, Ar)

5. Measure isotopic ratios of H, C, N, and S

Mission Overview:

Baseline SNAP Mission Configuration 

Add SNAP to Uranus Orbiter and Probe Mission

Orbiter delivers Main Probe and SNAP to Uranus

Baseline Probe Configuration

Mass: 30 kg

Aeroshell Diameter: 50 cm

Probe Power: Primary Batteries

Heatshield Material: HEEET

Target Atmospheric Pressure: 5 bar

Notional Payload

Atmospheric Structure Instrument: Measures thermal profile

NanoChem: Detects cloud-forming molecules 

Ultrastable Oscillator: Measures wind speeds

Team Members/Institutions:

Kunio M. Sayanagi / Hampton University

Robert A. Dillman / NASA Langley Research Center

David H. Atkinson / Jet Propulsion Laboratory

Amy A. Simon / NASA Goddard Space Flight Center

Michael H. Wong / University of California, Berkeley

Thomas R. Spilker / Independent Consultant

James M. Longuski / Purdue University

Sarag J. Saikia / Purdue University

Jing Li / NASA Ames Research Center

Drew Hope / NASA Langley Research Center

Supported by

NASA Langley Research Center Engineering Design Studio
Planetary Science Deep Space SmallSat Studies

Ross (Formerly CAESAR)

Science Objectives:

1. Evaluate bulk physical characteristics (size, shape, 

spin period, surface morphology) of several small 

Near Earth Asteroids to provide constraints on their 

formation and evolution

2. Determine the thermal properties of these asteroids 

to evaluate Yarkovsky and YORP effects on 

trajectory dispersions.

3. Characterize objects that may pose a threat to 

Earth or offer resources for exploration

Mission Overview: 

12U cubesats each with 1 Visible and 1 IR Camera

24 kg launch mass, with margin

X-band IRIS radio

Build and launch several identical 12U CubeSats with Lucy or 

Psyche to encounter small Near Earth Asteroids. 

Team Members/Institutions:

Beau Bierhaus, P.I., Lockheed Martin

Robert Jedicke, Co-I, University of Hawaii

Michael Ravine, Co-I, Malin Space Science Systems Inc.

Driss Takir, Co-I, SETI Institute

Benton Clark, Co-I Lockheed Martin

Obtain fundamental data on 

size, shape, structure, and 

regolith properties during flyby

Example mission to asteroid 

2000 BM19 shown

Dozens of feasible targets

with low ΔV & encounter 

velocity 

Low Gain Antenna

IR Camera

Vis Camera

Star Tracker / GNC

High Gain Antenna

Green Propellant Propulsion 

Sun

2000 BM19

Earth Ross 

Launch
Planetary Science Deep Space SmallSat Studies

APEX

Science Objectives:

1. Determine the structure of Apophis and observe the 

tidal deformation during encounter with Earth 2029

1. Determine rotational dynamics

2. Establish physical dimensions

3. Determine topography

4. Determine interior structure

5. Define surface morphology

2. Map Apophis before encounter to define the body

3. Remap Apophis after encounter to detect changes 

resulting from tidal forces during encounter

Mission Overview:

Baseline Spacecraft Configuration

3 axis stabilized, solar power

Solar electric propulsion (or possible chemical)

Arm to deploy seismometer on surface

Baseline Instrument Payload

Panchromatic imager

Seismometer

Conops

Rendezvous with Apophis before encounter

Map and characterize Apophis

Deploy the seismometer

Observe deformation during encounter

Remap and recharacterize Apophis

Team Members/Institutions:

Eric Asphaug – Arizona State Univ.

Olivier Barnouin – JHU/APL

Mark Boslough – Sandia National Lab.

Brett Denevi – JHU/APL

Carolyn Ernst – JHU/APL

Jeff Plescia – JHU/APL

Derrick Richardson – Univ. Maryland

Andy Rivkin – JHU/APL

Nicholas Schmerr – Univ. Maryland

Possible spacecraft Hongyu Yu – Arizona State Univ.

configuration with deployment

arm extended.

Apophis shape model (Pravec, 2014)

Seismometer draft configuration –

includes sensor, solar cells, 

electronics and comm.

Asteroid Probe Experiment
Planetary Science Deep Space SmallSat Studies

Science Objectives:

PrOVE will perform a close flyby of a Jupiter-family

or new comet near perihelion when volatile activity

is maximum, to probe the origin of the nucleus and

the formation and evolution of our Solar System.

• Investigate chemical heterogeneity of nucleus by

quantifying volatile species abundances and how these

depend on solar insolation;

• Map spatial distribution of volatiles, especially CO2 (which

cannot be measured from ground based telescopes), and

determine any variations;

• Determine the frequency and distribution of outbursts.

Mission Overview:

• PrOVE will be deployed from any launch platform and

released above Earth’s gravity well.

• Using onboard propulsion, PrOVE will navigate to a

waypoint in space.

• PrOVE will remain at the waypoint until commanded to

a transfer trajectory to intercept a known comet as it

approaches encounter or hibernate indefinitely until an

opportunistic new comet is identified and transfer orbit

is uploaded.

• The PrOVE trajectory will be designed to encounter

the comet at the ascending/descending node to

mitigate large off-plane distances.

Team Members/Institutions:

University of Maryland PI: T. Hewagama CoI: L. Feaga, 

J. Sunshine; Collab: T. Livengood

GSFC CoI: S. Aslam, D. Folta, C. Nixon, G. Villanueva; 

Collab: T. Hurford, M. Mumma, 

Catholic University of America CoI: N. Gorius

Morehead State University CoI: B. Malphrus

JPL: CoI: P. Clark

York University: Collab: M. Daly

Deep Space Spacecraft 

and multispectral camera

PrOVE payload will measure 

volatiles and temperatures

Lunar Orbit

L2 Halo Orbit

Example waypoint

Sample 

Waypoint 

Libration

Orbit

Lunar 

Orbit Sun 

Earth 

Earth L2

PrOVE Primitive Object Volatile Explorer
Planetary Science Deep Space SmallSat Studies

Science Objectives:

1. Measure the vertical and regional composition variation 

of the lunar crust by determining the chemical 

compositions of crater central peaks, basin peak-rings, and 

ejecta blankets from a wide range of crater sizes (~10–200 

km). 

2. Identify outcrops of lunar mantle on the surface (e.g., 

through anomalously high Mg/Si ratios), which then 

become possible targets for future sample return missions. 

3. Conduct X-ray pulsar based deep space navigation

(XNAV) and measure its performance.

Mission Overview:

Image of 

Spacecraft 

and/or 

Mission

Team Members/Institutions:

• Type, Mass: Secondary Mission, 43 kg in 35 x 23 x 68 cm

• Mission Lifetime: 1.5 year; 1 year science operation from a 

2023 – 2027 launch for solar max 

• Science Orbit: Quasi Frozen Circular Polar Lunar Orbit with 

~17 hr period at 6000 km after insertion to 500 x 5000 km orbit 

via primary

• Payload: [1] X-ray Imaging Spectrometer (XIS): Miniature Xray Optics (MiXO, >25 cm2 at 1 keV) + 2 CMOS X-ray sensors 

(<200 eV at 6 keV) + 1 high timing resolution SDD (1 μs) 

[2] Solar X-ray Monitor (SXM): SDD

• Spacecraft (CBE, margin): wet mass (43 kg, 41%), ADN (7 kg, 

22%), R134a (2.2 kg, 31%), energy (136Wh, 46%), power draw 

(72 W, 35%), pointing knowledge (6′′, 60%) & control (30′′, 

50%) and link margin (7 dB for LGA)

Management, SOC and MOC

Suzanne Romaine (SAO) PI; MiXO

Jaesub Hong (Harvard) Deputy-PI; Instrument Design

Janet Evans (SAO) SOC

NASA ARC Mission & S/C Design; MOC

Lunar and XRF Science

Ian Crawford (Birkbeck) David Kring (LPI) 

Noah Petro (GSFC) Larry Nittler (Carnegie)

XNAV and GEONS

Keith Gendreau (GSFC)

Jason Mitchell (GSFC)

Luke Winternitz (GSFC)

Instruments

Ralph Kraft (SAO) XIS

Almus Kenter (SAO) CMOS

Gregory Prigozhin (MIT) SDD 

Rebecca Masterson (MIT) Instr Mgmt, SXM

CubeSat X-ray Telescope for Elemental Abundance CubeX Mapping of Airless Bodies and X-ray Pulsar Navigation SAO
Planetary Science Deep Space SmallSat Studies

Lunar Water Assessment, Transport, 

Evolution, and Resource 

Evaluate mission, 

payload and CONOPS 

feasible with a small 

Lunar orbiter to 

characterize the water 

on the Moon.

Science 

Objectives:

• What are the 

chemical form(s) of 

water on the Moon, 

including the 

PSRs, and how are 

they distributed 

spatially?

• How does surficial 

lunar water evolve 

over space and 

time?

• Is solar wind 

implantation 

responsible for the 

OH on the 

illuminated Moon?

Team Members/Institutions:

PI: C.A. Hibbitts, JHU-APL

D. Blewett, P. Brandt, B. Clyde, D. Hurley, R. 

Klima, D. Lawrence, A. Mirantes, D. Moessner, 

W. Patterson, J. Plescia, J. Sunshine, J. 

Westlake; all JHU-APL

L. Burke, NASA GRC 

B. Cohen, NASA GSFC

J. Dankanich, NASA MSFC 

Mission Overview:

Solar electric propulsion spacecraft, 

3-axis stabilized with instruments on nadir facing deck

Transit GTO to weakly captured lunar orbit, then spiral in

Instrument suite: 

• Mid-Infrared Multi-Spectral Imager (MIMSI)

• Active Multiband IR Reflectometer (WattIR)

• Neutron Spectrometer (NS)

Map surficial water and hydroxyl, 

and near-surface polar hydrogen.

WATER
Planetary Science Deep Space SmallSat Studies

MiLuV

Science Objectives:

Mapping lunar volatiles at the 3.0 and 1.5 μμm 

spectral absorption bands from pole to pole in 

nadir direction in day and night and in 

permanent darkness

– Detecting water ice on surface above 100 parts per 

million concentration 

– Measuring distribution of surface volatiles in areas 

of permanent shadow

– Mapping the global distribution of H2O/OH from 

pole to pole

– Monitoring diurnal cycle of surface H2O/OH frost

Team Members/Institutions:

• N. E. Petro, NASA GSFC

• E. Mazarico, X. Sun, J. Abshire, 

G. Neumann, P. Lucey

• Mission Study Team: GSFC 

and WFF Mission Design Labs

Mission Overview:

ESPA-class spacecraft

GTO deployment to ~100 km circular lunar polar orbit

Orbit allows for dense coverage of the poles

Instrument suite: 

• Lunar Ice LIDaR Spectrometer (LILIS)

• Two bands to maximize water detection and 

discriminate multiple phases of water

Map the moon for 1 year (12 lunations)

Can act as a communications relay

Miniature Lunar Volatiles
Planetary Science Deep Space SmallSat Studies

Bi-sat Observations of the Lunar Atmosphere above Swirls

Science Objectives:

Investigate the hydrogen cycle (including surface 

hydroxylation/hydration) at the Moon by determining: 

1. the mechanisms and dynamics of lunar hydrogen 

implantation, and their dependence on composition, 

regolith properties, local topography, plasma 

conditions, time-of-day, and crustal magnetic fields.

2. how this relates to the formation of the lunar “swirls” 

collocated with magnetic anomalies (crustal fields) 

and space weathering.

Requires repeated in situ measurements at very low 

altitudes (<10 km) – orbit-maintenance propulsion 

requirements are prohibitive for conventional SmallSats.

Mission Overview:

Flight Configuration: BOLAS will deploy a thin, tens of kmlong tether between two CubeSats enabling them to fly in a 

gravity gradient formation.

The BOLAS center-of-mass (C.O.M.) will be in a quasistable, low maintenance orbit, such that the lower CubeSat 

can remain at low altitudes for long durations.

Mission Architecture: Two similar 12U CubeSats (24U total), 

leveraging existing bus and miniaturized subsystems.

Instrument Payload: Ion Spectrometer, Energetic Neutral 

Atom Imager, Plasma Wave System, and Magnetometer.

Orbit: Low inclination to observe magnetic anomalies/swirls 

that are clustered around the equator on short timescales.

Mission Lifetime: 1 year (desirable), 1 lunation (minimum).

Team Members/Institutions:

• PI: Timothy J. Stubbs (NASA/GSFC, 695)

• GSFC Co-Is: Michael R. Collier, William M. Farrell, 

John W. Keller, Jared Espley, Michael A. Mesarch, 

Dean J. Chai, Michael K. Choi

• Morehead State Univ. Co-I: Benjamin K. Malphrus

• Tethers Unlimited Co-I: Robert P. Hoyt

• Busek Co., Inc. Co-I: Michael Tsay

• GSFC Collaborator: Richard R. Vondrak

Lunar 

Swirl

BOLAS
Planetary Science Deep Space SmallSat Studies

IMPEL

Science Objectives:

• Sub-meter-scale imaging (<40 

cm/pixel) to definitively discern small 

fractures or pits in Ina-D

– This will enable determination of 

whether IMPs are made of young 

volcanic lavas

• Determine grain sizes and regolith 

components to understand the age 

and formation mechanism of Ina-D

Mission Overview:

• IMPEL will explore a site of potentially 

recent volcanism (an “Irregular Mare 

Patch”) on the Moon, answering the 

question of when and how the materials 

found at Ina-D formed

• IMPEL consists of two 180 kg, tethered 

spacecraft (science module and descent 

module) attached to an ESPA ring

• The Descent Module deorbits the Science 

Module for a soft landing on the Moon, 

enabling a short, focused science mission

Team Members/Institutions:

PI: Dr. David Draper (NASA-JSC)

Dr. Samuel Lawrence (NASA-JSC)

Dr. Brett Denevi (JHUAPL)

Dr. Julie Stopar (LPI/USRA)

Dr. Kristen John (NASA-JSC)

Lee Graham (NASA-JSC)

Zachary Fletcher (JHUAPL)

Joseph Hamilton (NASA-JSC)

John Gruener (NASA-JSC)

Susan Bertsch (NASA-JSC)

Irregular Mare Patch Exploration Lander