Presentation to SBAG January 2016

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1 Presentation to SBAG January 2016 Julie Castillo-Rogez (JPL/Caltech/NASA) Les Johnson (Marshall Space Flight Center/NASA) And the NEAScout Team Edit as appropriate

AES EM-1 Secondary Payload Overview HEOMD s Advanced Exploration Systems (AES) selected 3 concepts for further refinement toward a combined Mission Concept Review (MCR) and

(SKGs) - Life cycle cost - Synergistic use of previously demonstrated technologies - Optimal use of available civil servant workforce Completed a Non-Advocate Review of the

environments Fundamental effects on biological systems of ionizing radiation in space environments Lunar resource potential Quantity and distribution of water and other

deposits in the Moon s permanently shadowed craters Near Earth Asteroid (NEA) Scout MSFC/JPL Human NEA mission target identification NEA size, rotation state (rate/pole

2 AES EM-1 Secondary Payload Overview HEOMD s Advanced Exploration Systems (AES) selected 3 concepts for further refinement toward a combined Mission Concept Review (MCR) and System Requirements Review (SRR) completed in August All projects are in Phase B Primary selection criteria: - Relevance to Space Exploration Strategic Knowledge Gaps (SKGs) - Life cycle cost - Synergistic use of previously demonstrated technologies - Optimal use of available civil servant workforce Completed a Non-Advocate Review of the Science Plan Payload NASA Centers BioSentinel ARC/JSC Lunar Flashlight JPL/MSFC Strategic Knowledge Gaps Addressed Human health/performance in highradiation space environments Fundamental effects on biological systems of ionizing radiation in space environments Lunar resource potential Quantity and distribution of water and other volatiles in lunar cold traps Mission Concept Study radiation-induced DNA damage of live organisms in cislunar space; correlate with measurements on ISS and Earth Locate ice deposits in the Moon s permanently shadowed craters Near Earth Asteroid (NEA) Scout MSFC/JPL Human NEA mission target identification NEA size, rotation state (rate/pole position) How to work on and interact with NEA surface NEA surface mechanical properties Flyby/rendezvous and characterize one NEA that is representative of a potential human mission target 2

3 INSPIRE, MarCO, and EM-1 CubeSats as Stepping Stones to Deep Space LEON 3 Sphinx X-Band Transponder Iris 3

4 Near Earth Asteroid (NEA) Scout WHY NEA Scout? Characterize a NEA with an imager to address key Strategic Knowledge Gaps (SKGs) Demonstrates low cost reconnaissance capability for HEOMD (6U CubeSat) LEVERAGES: Solar sail development expertise (NanoSail-D, Solar Sail Demonstration Project, LightSail-A/B) CubeSat developments and standards (MarCO, University & Industry experience) Commonalities with other AES secondary payloads MEASUREMENTS: NEA volume, spectral type, spin mode and orbital properties, address key physical and regolith mechanical SKG 80% surface coverage imaging at 50 cm/px Spectral range: nm (incl. 4 color channels) 30% surface coverage imaging at 10 cm/px Key Technical Constraints: 6U Cubesat and ~86 m 2 sail, expected dispenser compatibility and optimize cost Target must be within ~1.0 AU distance from Earth due to telecom limitations Slow flyby with target-relative navigation on close approach 4

Near Earth Asteroid Scout Mission Overview Close Proximity Science High-resolution

Reconnaissance <100 km distance at encounter 50 cm/px resolution over 80% surface

(Updated OCO-3 Context Camera) Target Reference stars Target Detection and Approach:

5 Near Earth Asteroid Scout Mission Overview Close Proximity Science High-resolution imaging, 10 /px GSD over >30% surface SKGs: Local morphology Regolith properties NEA Reconnaissance <100 km distance at encounter 50 cm/px resolution over 80% surface SKGs: volume, global shape, spin properties, local environment JPL IntelliCam (Updated OCO-3 Context Camera) Target Reference stars Target Detection and Approach: 50K km, Light source observation SKGs: Ephemeris determination and composition assessment (color) 6

6 NEAScout Targets an NHAT NHATS database contains targets from 1 m to >1 km Do not all carry same value: low orbit condition code, >10 m, synodic period < 10 yr are of high priority Targets accessible to NEAScout are < 50m Expectations is that ~5 new NHATS targets be found each year, with enhanced assets 7

7 Rendezvous Target Search Telecom Distance (AU) blue <.25 green <.5 orange <.75 red < 1 OCC under 2 under 4 under 7 Appx diameter small < ~15 m med. < ~30 m large < ~50 m Local minima for flight time. Flight time increases linearly with pre-escape loiter time Flight time increases non-linearly with delayed escapes 8

8 Baseline Target: 1991 VG H=28.4±0.7 Diameter ~ 5-12 meters Albedo is unknown Position is known within ~2700 km (1- ) but optical observation opportunity in July 17 will decrease uncertainty to a few 100s km Rotation period between a few minutes and less than 1 hr Unlikely to have a companion Unlikely to retain an exosphere or dust cloud Solar radiation pressure sweeps dust on timescales of hours or day Backup Target Absolute magnitude 30% albedo Diameter (m) 5% albedo Diameter (m) Orbit Condition Code Observation Opportunity prior to launch 2013 BS (Optical) 9

9 Ground-Based Target Reconnaissance Paul Abell and Vishnu Reddy to coordinate observations 1991 VG will be in sight from ~July 2017 to March 2018, H~23.5 Arecibo may be able to observe VG but with low SNR between January 16-28, 2018 Doppler uncertainties are 70 Hz on January 16, 2018, would be reduced to ~1 Hz after detection Optical observations best from Southern hemisphere (SOAR, NOAO) 4-telescopes ok for astrometry and lightcurves Larger telescope needed for colors Community is welcome to participate in observation campaign see future announcement Will request Director s Discretionary Time since mission-specific target 10

(20 MP) yields small ifov (0.125 mrad) and wide FOV (15 deg.

10 Instrument Summary Inherited from EECAM on Mars 2020 rover and OCO-3 programs (harsh environmental testing, leverages development dollars) Large detector array (20 MP) yields small ifov (0.125 mrad) and wide FOV (15 deg.) Enables meeting 10 cm/pix at ~800 m closest approach distance Enable target detection from ~50K km Reflectance 11

11 Proximity Science Flyby velocity ~ 20m/s Local morphology Morphology, Environment Target rotation period is key uncertainty on the science capture timeline Rotation Size Low phase angles for geology imaging Distance (km) 12

12 Proximity Science - Movie

13 NEAScout Project Status Project is on track for August Design Review Solar sail deployment pathfinder developed and tested. EDU in development Long lead items identified and in process of being procured (esp. camera, telecom) Science software development is on track Data management plan is in development but data pipeline development effort is pushed to Phase E (cruise) for budgetary reasons Data archival will depend on budget available for Phase E No plan to expand the science team until ~mid-cruise No plan to add science goals at this stage Official announcement of manifest on SLS EM-1 forthcoming 15

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Lunar Flashlight & NEA Scout A NanoSat Architecture for Deep Space Exploration

National Aeronautics and Space Administration Lunar Flashlight & NEA Scout A NanoSat Architecture for Deep Space Exploration Payam Banazadeh (JPL/Caltech) Andreas Frick (JPL/Caltech) EM-1 Secondary Payload