Presentation to SBAG – January 2016 · Presentation to SBAG – January 2016. Payload NASA...
Transcript of Presentation to SBAG – January 2016 · Presentation to SBAG – January 2016. Payload NASA...
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Julie Castillo-Rogez (JPL/Caltech/NASA)Les Johnson (Marshall Space Flight Center/NASA)
And the NEAScout Team
Edit as appropriate
Presentation to SBAG – January 2016
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PayloadNASA Centers
Strategic Knowledge Gaps Addressed
Mission Concept
BioSentinelARC/JSC
Human health/performance in high-radiation space environments• Fundamental effects on biological systems
of ionizing radiation in space environments
Study radiation-induced DNA damage of live organisms in cis-lunar space; correlate with measurements on ISS and Earth
Lunar FlashlightJPL/MSFC
Lunar resource potential• Quantity and distribution of water and other
volatiles in lunar cold traps
Locate ice deposits in the Moon’s permanently shadowed craters
Near Earth Asteroid (NEA) ScoutMSFC/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
AES EM-1 Secondary Payload Overview
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• 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 2014
- 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
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INSPIRE, MarCO, and EM-1 CubeSatsas Stepping Stones to Deep Space
LEON 3 ‘Sphinx’
X-Band
Transponder ‘Iris’
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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)
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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
Key Technical Constraints: • 6U Cubesat and ~86 m2 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
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: 400-900 nm (incl. 4 color channels)• ≥30% surface coverage imaging at ≤10 cm/px
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Near Earth Asteroid Scout Mission Overview
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JPL IntelliCam(Updated OCO-3 Context Camera)
Target Detection and Approach: 50K km, Light source observation
SKGs: Ephemeris determination and composition assessment (color)
Close Proximity ScienceHigh-resolution imaging,
10 /px GSD over >30% surfaceSKGs: Local morphology
Regolith properties
NEA Reconnaissance <100 km distance at encounter
50 cm/px resolution over 80% surfaceSKGs: volume, global shape, spin
properties, local environment
Reference stars
Target
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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
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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 timeFlight time increases non-linearly with delayed escapes 8
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Baseline Target: 1991 VG
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Backup Target
Absolute magnitude
30% albedo Diameter (m)
5% albedo Diameter (m)
Orbit Condition
Code
ObservationOpportunity prior to launch
2013 BS45 25.9 11 51 0 2015-01 (Optical)
• 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
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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
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Ref
lect
ance
• 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
Instrument Summary
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Proximity Science
Low phase angles for geology imaging
Flyby velocity ~ 20m/s
Target rotation period is key uncertainty on the science capture timeline
Size
Rotation
Morphology, Environment
Local morphology
12Distance (km)
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Proximity Science - Movie
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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
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