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CLOSE ( Characterize and Land on Orpheus with Sample-return to Earth)

jpl team x. psss 2003. close. CLOSE ( Characterize and Land on Orpheus with Sample-return to Earth). PI: Sarah Noble PM: Dominic Papineau. Planetary Science Summer School 2003. August 14 th 2003. JPL Proprietary/Competition Sensitive DO NOT DISTRIBUTE.

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CLOSE ( Characterize and Land on Orpheus with Sample-return to Earth)

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  1. jpl team x psss 2003 close CLOSE(Characterize and Land on Orpheus with Sample-return to Earth) PI: Sarah Noble PM: Dominic Papineau Planetary Science Summer School 2003 August 14th 2003 New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive JPL Proprietary/Competition Sensitive DO NOT DISTRIBUTE

  2. Participants and Roles • Kathryn Fishbaugh, (Brown Univ.) Science and Instruments • Gerald Patterson, (Brown Univ.) Mission Design • Adam Mantz, (Cornell Univ.) Ground System • Erika Wagner, (M.I.T.) Systems • Alison Cohen, (M.I.T.) Cost estimation • Swati Mohan, (Cornell Univ.) Propulsion • Matt Colgan, (Univ. Colo.) Attitude Control System • Nathaniel Putzig, (Univ. Colo.) Command & Data Systems and Software • Harald Heisenger, (Brown Univ.) Power and Thermal Systems • Douglas Jerolmack, (M.I.T.) Structure, Configuration, and Mechanisms • Erwan Mazarico, (M.I.T.) Telecommunications • Ian Garrick-Bethell, (M.I.T.) Entry, Descent, Landing, and Return Vehicle New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  3. Solar System Exploration Roadmap • Objective 1: Learn how the Sun’s family of planets and minor bodies originated • Objective 2: Determine how the Solar System evolved to its current diverse state (asteroid evolution, planetary impact history) • Objective 3: Determine the characteristics of the Solar System that led to the origin of life (e.g. the first billion years of evolution) • Objective 5: Explore the space environment to discover hazards to Earth (terrestrial mass extinctions, physical and chemical characteristics of asteroids) New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  4. 50nm Science Objectives - The big picture Why an asteroid? Didn’t NEAR already do this? • We can compare Orpheus to Eros and other asteroids that we have studied • We are returning samples Why Orpheus? • Vestoid • Make links to Vesta • Make links to meteorites • Explore a primitive differentiated body - this may be a chip of the earliest volcanically active body in the solar system! Why sample return? • Ground truth (great complement to Dawn) • Space weathering - TEM resolution • Detailed chemistry and dating Asteroid 4 Vesta “Space Weathering” New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  5. Science Objectives - What we expect to find? NEAR at Eros BSE image of Kapoeta (Howardite) New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  6. Science Objectives • Characterize the surface of near-earth asteroid Orpheus • Topography, mineralogy, chemistry, space weathering, surface age, morphology • Characterize the shallow sub-surface of the asteroid • Mineralogy, chemistry, age, space weathering, solar wind, physical properties • Characterize the asteroid interior • Density, mass distribution, porosity • Comparisons • Vesta • Eros and other asteroids • HED meteorites New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  7. Science Objective Surface Measurement Requirement Instrument Type & Performance Data Products Topography Elevation Laser Altimeter V=10cm H=0.5m Global DEM Mineralogy Vis/NIR spectra Multi-spec camera/NIR spec Bands: 8 Vis/200 NIR Res:10cm (1m floor) Multi-spectral images, global spectra Chemistry Sample Return N/A N/A Space Weathering Vis/NIR spectra Sample Return Vis/NIR camera Res: 10cm (1m floor) Multi-spectral images/NIR spectra Surface Age High res images Vis/NIR camera Res: 10cm Global image mosaic Morphology High res images Vis/NIR camera Res: 10cm Global DEM, Global image mosaic Remnant Magnetization Gauss Magnetometer Res: 40µgauss Global magnetic map Science Traceability - Surface New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  8. Science Objective Shallow Sub-Surface Measurement Requirement Instrument Type & Performance Data Products Mineralogy Sample Return N/A N/A Chemistry Sample Return N/A N/A Space Weathering Sample Return N/A N/A Physical Properties High res images, Sample Return Microscope and Pan-Cam Panoramics of landing area and microscope images Age Sample Return N/A N/A Solar Gas Composition/Content Sample Return N/A N/A Science Traceability - Shallow Sub-surface New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  9. Science Objective Interior Measurement Requirement Instrument Type & Performance Data Products Density Mass, Volume Radio Science, Seismometers N/A Porosity Mass, Volume, Composition Radio Science, Sample Return N/A Structure Internal Structure, Depth of regolith, Mass distribution Radio Science, Radar, Seismometers, Altimeter Gravity map Science Traceability - Interior New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  10. Performance Floor • The Performance Floor for this mission: • Global characterization of surface via laser altimeter and multi-spectral imager • Return of >10g asteroid material from Orpheus • Model interior structure via laser altimeter and radio science New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  11. Payload Summary Table New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  12. Performance Floor • De-scopes that take mission from baseline to performance floor (in order): • Radar • Seismometers • Magnetometer • Microscope Camera New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  13. Payload Summary LASER ALTIMETER • Key technical performance characteristics • Mass : 7 kg • Power : 5 W • Total Data Volume: 8.6x1011 bits • Heritage : 100% (MESSENGER) • Technology Readiness Level: 7 New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  14. Payload Summary MULTISPECTRAL IMAGER/SPECTROMETER • Key technical performance characteristics • Mass : 16 kg • Power : 10 W • Total Data Volume: 6.2x1010 bits • Special requirements: pointing=0.59°; FOV=0.9° • Heritage : 80% (VIS imager from NEAR; mid-IR modified from MESSENGER) • Technology Readiness Level: 7 New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  15. Payload Summary GROUND PENETRATING ORBITAL RADAR • Key technical performance characteristics • Mass : 17 kg • Power : 70 W • Total Data Volume: 4.8x108 bits • Heritage : 100% (Mars Express) • Technology Readiness Level: 7 New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  16. Payload Summary RADIO SCIENCE • Key technical performance characteristics • Mass : 30.9 kg • Power : 30W • Data Rates: 3x104 bits downlink; 2x103 uplink • Frequency: 8.42 GHz downlink; 7.1 GHz uplink • Special requirements: radio not used for science while performing attitude control • Heritage : 100% (High gain from Cassini) • Technology Readiness Level: 9 New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  17. Payload Summary MAGNETOMETER • Key technical performance characteristics • Mass : 0.1 kg • Power : 1.0 W • Data Rates: 6.9x109 bits/missions; 2.7x108 storage bits • Heritage : commercial • Technology Readiness Level: 9 New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  18. Payload Summary PANORAMIC CAMERA/DESCENT IMAGER • Key technical performance characteristics • Mass : 0.27 kg • Power : 2W • Total Data Volume: 4x109 bits; 25 images/panorama, 10 panoramas • Special requirements: FOV=17x17° • Heritage : 100% (MER) • Technology Readiness Level: 7 New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  19. Payload Summary 3 SEISMOMETERS • Key technical performance characteristics • Mass : 6 kg • Power : 1.5 W • Total Data Volume: 2.9x107 bits • Special requirements: must be coupled to surface; require explosive charges as seismic sources; require drop-off before landing • Heritage : 60% (sensors created and tested at JPL) • Technology Readiness Level: 5 New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  20. Payload Summary MICROSCOPE • Key technical performance characteristics • Mass : 0.5 kg • Power : 2 W • Total Data Volume: 4.5x107 bits • Special requirements: mounted on scoop arm • Heritage : 100% (Mars ‘01 Lander) • Technology Readiness Level: 7 New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  21. Sample Acquisition STICKY PAD Key technical performance characteristics • Mass : 4 kg • Power : <3 W • Heritage : concept originally developed for HERA asteroid sample return • Technology Readiness Level: 3-4 New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  22. Sample Acquisition MOMENTUM-COMPENSATED SAMPLING SPIKE Key technical performance characteristics • Mass : 10 kg • Power : negligible • Heritage : Concept originally developed for the Champollion (ST-4) comet mission • Technology Readiness Level: 2-3 • 3cm diameter / 0.5m length New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  23. Mission Summary • Launch Vehicle: Atlas V (531) • Launch Date: Dec. 2013 (Mar. 8 2006) • Arrival Date: April 2016 (July 3 2008) • Number of days in Launch Period: 21 days (C3 = 18.0) • Trajectory Type: Direct transfer Trajectory • Mission Duration: 3.7 years New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  24. Launch Vehicle • Atlas V (531) • 1st Stage: Common Core Booster RD-180 lO2/kerosene engine • 2nd Stage: Single Centaur lO2/lH2 engine • 3 SRBs • 5 m fairing • 3744.8 kg capacity • No flight heritage in 2003 New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  25. Launch Vehicle Comparison *C3 for 21 day launch window is 18.0 New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  26. Flight Trajectory New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  27. Spacecraft range Ranges (AU) Time at Orpheus New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  28. Ecliptic View at Orpheus Arrival (2008/7/3) New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  29. Mission Plan • Phase 1: Launch and Cruise Day 0 • TCM at apoapse • Phase 2: Orpheus Rendezvous Day 850 • Phase 3: Orbital mapping • Phase 4: Deploy seismometers / charges Day 950 • Locate charges / seismometers • Activate charges • Collect data from seismometers • Phase 5: Descent and Landing Day 952 • Selection of landing site (1km) • Landing / sampling / imaging • Minimum sampling case (2h) • Phase 6: Ascent Day 959 • Collect data from seismometers • Phase 7: Departure and Earth Flyby Day 1140 • Phase 8: EEV deployment Day 1351 New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  30. Descent and Landing • The landing location is chosen. • A straight line trajectory is chosen to the landing site. • Gravity effects are largely negligible. • At 1000m, a burn is made to correct velocity to 1.0m/s. • At 100m, a final burn is made to reduce closure velocity to 10cm/s. • At 100m contamination of the site with exhaust is negligible. • The S/C sets down at 10cm/s. • No hazard avoidance. • No human in loop. • Software must maintain acceptable attitude and descent velocity. New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  31. Trajectory New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  32. Maneuver V (m/s) TCM-1 30.0 Apoapse 1294.0 Apoapse Cleanup 50.0 Orbit Insertion 291.0 Orbit Insertion Cleanup 20.0 Landing Operations 25.0 Departure 823.0 Departure Cleanup 30.0 Earth Arrival 0.0 Earth Deflection 15.0 Total: 2578.0 V Description New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  33. Mission Phase Wet Mass (with margins) Atlas V (531) launch 3425.1 kg Orpheus landing ~1200 kg Earth entry 65 kg Flight System Overview • Architecture: 3-axis stabilized satellite with staged Earth Entry Vehicle (EEV) • Payload: 5 instruments with 500 kbps peak output, 3 sample acquisition tools • Power: GaAs solar panels with secondary Li-Ion battery • Propulsion: Hydrazine monoprop for DV = 2.6 km/s • ACS: Star tracker, reaction control wheels & IMU for 1 arcsec pointing control • Telecom: X band to DSN (30 kbps downlink, 2 kbps uplink), S band to seismometers (2 kbps) • C&DH: Power PC 750 w/80GB solid state storage New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  34. Mass Budget Distribution New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  35. ACS Propulsion Mission Design Structures Power Science Instruments CDS Thermal Telecom Ground Systems System Level Block Diagram New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  36. Structure Summary Main thruster High gain antenna Momentum wheels Earth entry vehicle /sticky pad arm Pan/descent camera Instrument face (next slide) Microscope/scoop 1.5 m New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  37. Structure Summary (cont.) • Solar arrays sweep • back at landing • Lands instrument • side down • Legs developed • w/ separately fun- • ded tech. program • Mass = 287 kg EEV Seismic stations (3) Monoprop. Tanks (3) Data storage/handling Pressurant tank Multispectral imager Ground penetrating radar Laser altimeter 1.5 m New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  38. ACS Requirements • Pointing Control: 1800 arcsec • 2124 arcsec for imager • 1800 arcsec for HGA • Pointing Knowledge: 900 arcsec • Pointing Stability: 20 arcsec/s • 20 arcsec/pixel • 100 ms exposure time • 1/10 pixel (rule of thumb for acceptable smear) New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  39. ACS Design Summary • 3 axis stabilized • Attitude Determination • Star Tracker: primary inertial reference • Coarse Sun Sensor: safe mode & initial deployment • Gyros: backup altitude and horizontal velocity • Attitude Control • Thrusters: reaction wheel de-saturation • Reaction Wheels: fine pointing for radio science • 33 kg, 69 W avg, 99W peak New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  40. Propulsion • Driving Requirements: • ∆V budget • Type of Launch Vehicle • Cost • Hydrazine Mono-propellant System • One 445N main engine • Four 22N thrusters • Twelve 0.7N thrusters • 1 Composite Pressurant Tank and 3 Fuel Tanks • Dry mass: 150 kg • Propellant mass: 2382 kg • Total average power usage: 123 W • Tank Dimensions: Radius=0.5m, Length=1.4m New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  41. Power • Solar arrays are sized to surface operations • Mass: 10.22 kg • Area: 3.16 m2 • Diameter: 1.42 m • 2 GaAs Triple-Junction Rigid Panels • Li-ion technology life issues will be improved by 2010 tech cut-off New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  42. Telecom • HGA • X-band: u/l @8.42Ghz, d/l @7.1GHz • Redundancy: full for components , only 1 antenna • Data rates: u/l @30kb/s, d/l @2kb/s • Power: 30W • LGA • X-band • Redundancy: 2 antennae • Data rates: u/l @40b/s, d/l @15b/s • Power: 30W • Transceivers (orbiter  seismometers) • S-band: 2.25Ghz • Redundancy • Orbiter: 2 transceivers and 1 antenna • Seismometer: 1 transceiver and 2 antennae • Data rates: u/l @3.7kb/s • Power: 50mW New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  43. Ground Systems DSN 34m Beam Wave Guide Subnet used for all operations (70m available for emergencies) • Launch & early ops: 2 weeks, continuous coverage • Cruise: 26.5 months, beacon mode (2 passes/week, health check every 2 weeks) • Orbit, landing and surface ops: 3.5 months, continuous coverage • Data rate of 30 kbps during this phase allows data to be returned in near real-time. • Complex, ground directed navigation during low orbits, probe deployment and landing: work on 3 sequences at once (development, testing and operation) • Earth return: 9.5 months, similar to cruise. • Earth encounter: increased coverage starting 2 months prior to encounter. New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  44. Command & Data Handling Subsystem • Based on the Mars ‘05 CDH subsystem, 20% contingency • 30.5kg Total C&DH system mass 30.5 kg • 36.4W peak power consumption • Redundant processing system, non-volatile memory, and controllers • Single 80GB internally redundant solid state recorder Flight Software Subsystem • 25% inheritance from NEAR and Stardust missions • Estimates employ COCOMO II modeling tool (calibrated to previous JPL missions) • Estimated 241,000 logical lines of code • Estimated 1043 work-months New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  45. Earth Entry Vehicle (EEV) • Stardust model, built by Lockheed Martin. • Contains sticky pad sampling arm, core sample, and scoop sample. • Passively stabilized. • Spin-up required. • Parachute landing in the Utah Test and Training range. • Landing footprint: 30 x 84km. • Ground recovery based on radar tracks and beacon. • Mass: 50kg (including sticky pad sample collection arm). • Dimensions: approx 1.0m diameter. • Technology readiness level: 6 New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  46. Earth Reentry Sequence Images taken from Stardust mission (also HERA reentry study). UTAH Test and Training Range. New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  47. Major System Trades • Mono-propellant vs bi-propellant • Launch vehicle cost vs capability • Solar panel technology & mass vs cost • Science instruments vs mass, power & cost • Mission length vs power and telecom requirements New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  48. Ranges at Orpheus Arrival (2008/7/3) Ranges (AU) New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  49. Systems Risk Management • Significant internal redundancy in ACS and CDS • Functional redundancy in propulsion and telecom • Science redundancy provided by 3 sample collection tools, multiple instruments for internal structural characterization • Heritage elements across all systems • Operations scaled to meet science floor even with single-string failures in surface sample collection New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

  50. Critical events Mission Critical Events Key Elements Launch Launch vehicle capability Orbit insertion and maneuvers Navigation accuracy Attitude control accuracy Descent and landing on asteroid Spike design / unknown surface Anchoring onto asteroid surface Thermal shield, parachute Sample entry into Earth’s atmosphere New Frontiers PAR - <CLOSE> JPL Proprietary/Competition Sensitive

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