For planning and discussion purposes only Team X

For planning and discussion purposes only

Team X “Team X is a cross-functional multidisciplinary team of engineers that utilizes concurrent engineering methodologies to complete rapid design, analysis and evaluation of mission concept designs. ” For planning and discussion purposes only

For planning and discussion purposes only

SHOTPUT Survey of Hektor and Oterma Through Pulverization of Unique Targets First Mission to Explore Trojans and Centaur Through Flybys and Impacts "This presentation was created by students at an educational activity at the Jet Propulsion Laboratory, California Institute of Technology, and does not represent an actual mission. " PICS Fall 2008 - Alessondra Springmann November 4, 2008 For planning and discussion purposes only

A Unique Mission to Unexplored Worlds William K. Hartmann • 1 st mission to Trojan & Centaur (likely primordial material) + a Main Belt Asteroid! • 1 st visit to a contact binary/satellite system! • 1 st in situ investigation of small body compositional gradient from mid- to outer solar system! • 1 st release of two separate impactors in one mission to reveal subsurface composition! • Low risk, high science return For planning and discussion purposes only

Scientific Rationale • Primitive small bodies hold clues to the origin and evolution of the solar system • Trojans and Centaurs are two major populations of small bodies that have never been explored by spacecraft – These dim and distant objects have only been observed by ground-based telescopes • Centaurs are an accessible source of Kuiper Belt and cometary material – 5 -6 A. U. vs. >40 A. U. William K. Hartmann For planning and discussion purposes only

Our Mission: SHOTPUT • Reconnaissance and impactor study of Trojan asteroids and Centaurs Trojans Centaurs For planning and discussion purposes only

Background on Bodies • Trojans – Discovered in early 20 th century – Spectral D-type asteroids, dark, reddish – Possibly captured during giant planet formation – Possibly formed in place and represent Jupiter accretionary material • Centaurs – Further from Sun than Trojans – Too distant from the Sun to study in detail from Earth – Thought to have originated as Kuiper Belt Objects For planning and discussion purposes only

Targets Binary System 2001 HM 10 (624) Hektor S/2006 (624) 1 39 P Oterma Type Main Belt Asteroid Trojan (Contact Binary) Trojan Companion Centaur Spectral Type D D ? ? Albedo ? 0. 025 ? ? Diameter (km) ? 225 15 30 -60 Density (g/cm 3) ? 2. 0 -2. 4 ? Inclination (deg) 3. 17 18. 19 1. 94 binary semimajor axis (km) ~1000? binary orbital period(h) ~50? ? For planning and discussion purposes only

Science Traceability Matrix For planning and discussion purposes only

For planning and discussion purposes only

For planning and discussion purposes only

For planning and discussion purposes only

For planning and discussion purposes only

For planning and discussion purposes only

For planning and discussion purposes only

Investigation of Fundamental Properties • High scientific yield • Mass of bodies and binaries • Topography of unknown bodies • Surface and sub-surface thermophysics • Color, albedo, size, presence of binaries and satellites For planning and discussion purposes only

Where in the Solar System Did These Bodies Originate? • Follow the chemical trail – Measure isotope ratios – Study surface mineralogy – Bulk chemistry – Ice Previous work showing spectra for minerals found on asteroid surfaces For planning and discussion purposes only

Organic Matter in the Outer Solar System • Nature of comets - organic content of target objects reveals possible genetic links with Kuiper Belt objects farther from the Sun – Implications for solar system formation • Formation of organic-rich comets close to Sun has implications for — Delivery of water to the terrestrial planets — Origin of life • Theories of panspermia, delivery of life or its ingredients to Earth • Prebiotic chemistry at low temperatures For planning and discussion purposes only

Has Dynamical Evolution Occurred? • Trojan asteroids – Formed near Jupiter and were captured into Lagrange points – Dynamical capture - Nice model • Centaurs are on chaotic orbits – Lifetimes of under 10 million years – Oterma has moved outward in its orbit since the 1940 s • Comparison of known dynamic object with one that is possibly dynamic Morbidelli et al. 2005 For planning and discussion purposes only

Evolutionary Processes on Small Bodies • Space weathering – Indicates interaction with space environment. May correlate with migration history. • Morphology – Have these bodies experienced outgassing, cratering, and/or weathering? • Bulk chemistry and minerological composition Hektor (Artist's Conception) – Initial composition and thermal history? – What is the degree of differentiation? • Density – Are the objects more like asteroids (~2 g / cc) or comets (~1 g / cc) ? For planning and discussion purposes only

Impactors! • Expose subsurface and make material available for measurement For planning and discussion Christiansen, E. H. , Exploring the Planets, 2/E, purposes © 1995. only

Impactor Science • Motivation: Observe subsurface materials Lisse et al. (2006) For planning and discussion purposes only

• Two identical spherical tungsten dead impactors • Mass: 75 kg • Diameter: 20 cm Plume height Impactor Design Time after impact For planning and discussion purposes only

Instruments • Multi-Spectral Imager (Narrow Angle Camera and IR Spec) (MSI) • Dust Secondary Ion Mass Spectrometer (DSIMS) • Thermal Infrared Spectrometer (TIR) • Ultra-Violet Imaging Spectrograph (UVIS) • Wide Angle Camera (WAC) • Radio Science Experiment (RSE) • • Instrument Package: Total mass: 94 kg Total operational power: 98 W Total data rate: 5000 kbit/s For planning and discussion purposes only

Science Traceability Matrix Breakthrough level of understanding Significant advance in understanding Some advance in understanding For planning and discussion purposes only

Multi-Spectral Imager (MSI) • Primary purposes: – Determine topography, mineralogy (silicates and organics), presence and abundance of water ice, and potentially the degree of space weathering Mass 52 kg Power 58 W For planning and discussion purposes only

Dust Secondary Ion Mass Spectrometer (DSIMS) • Instrument Goals: To characterize the chemical composition of dust grains in each region. • Characterization includes elements, isotopes and functional groups. Data Rate Mass Atomic Mass Range Power 500 bits/ sec 19. 8 1 to 3, 500 AMU 20. 4 W For planning and discussion purposes only

Thermal Infrared Spectrometer (TIS) • Purpose: – surface and subsurface mineralogy – volatiles – thermophysical properties Spectral range ~ 400 -1200 cm-1 (8 -25 μm) Spatial resolution variable, but <16 km/pixel closest Data rate ~ 800 bps Dimensions 24 x 35 x 40 cm Mass 14. 1 kg Power Req. 13. 2 W TIS instrument to be used on board Trojan/Centaur Mission (after TES instrument, ASU) For planning and discussion purposes only

Ultraviolet Imaging Spectrograph (UVIS) • Primary purposes: – Determine D/H ratio – Hydrocarbons – ion emission (e. g. N+, N 2+, O 2+) – volatiles (e. g. H, H 2, N, N 2, Ar, CO, C 2 N 2) – UV spatial variation due to surface/exposure ages Mass Power 15. 6 kg 8 W avg, 12 W peak 1. High speed photometer 2. Hydrogen-Deuterium Absorption Cell 3. FUV Spectrometer (1115 -1912 Å, = 4. 8 Å) 4. XUV Spectrometer (563 - 1182 Å, = 4. 8 Å) For planning and discussion purposes only

Wide Angle Camera (WAC) • Required for optical navigation: – 2 cameras for stereo images – 5 color filter wheel – (SDSS – ugriz) • Primary purposes: – Mapping and topography Mass 4 kg Power 3 W Data rate 500 kbps For planning and discussion purposes only

Radio Science Experiment (RSE) • Primary purposes: – Measure the mass of the target bodies. • Uses the Doppler Effect between the spacecraft and the DSN antenna utilizing the Telecom subsystem Xband. Target Body – During the flyby the spacecraft will be gravitationally attracted to the target body and create a velocity perturbation. For planning and discussion purposes only

Phase A-D Schedule based on historical data from similar missions AO driven New Frontiers Mission with some precedent from Cassini, Deep Impact, Rosetta and MGS, no new technology Phase E = 93 months 7 years of passive cruise 12 months of science operations 3 flybys (2001 HM 10, Hektor, Oterma) For planning and discussion purposes only

Baseline Mission Design Mar 27, 2015 - Launch Jan 13, 2016 – 2001 HM 10 Jun 14, 2016 – Deep Space Maneuver May 17, 2018 – Earth Flyby – Launch – Kennedy Space Center, Fl – Launch vehicle: Atlas V 531 – C 3: 51. 4 km 2/s 2 Mar 25, 2020 – Hektor / S/2006 and Deep Space Maneuver Oct 30, 2022 – Oterma For planning and discussion purposes only

Baseline Trajectory For planning and discussion purposes only

Baseline Trajectory For planning and discussion purposes only

Edge On Trajectory View For planning and discussion purposes only

Approach speed = 8. 24 km/sec Encounter Strategy Main belt asteroid Closest approach ~ 900 km Close Encounter mode 15 K km, 30 minutes away Far Encounter mode Approach mode TIS and UVIS On 2 M km, 3 days 3 M km, 4 days IR on imager on Dust analyzer on, continuously Radio science begins Imager: 4 hours per day, without IR instrument Instrument check-out begins 2 weeks out BEFORE approach Scheme is symmetrical around closest approach through far encounter mode For planning and discussion purposes only

Encounter Strategy Approach speed = 8. 2 km/sec Hektor Closest approach 700 km Close Encounter mode 15 K km, 30 minutes away Far Encounter mode 7. 5 M km, 7 days Approach mode 110 M km, 150 days Imager: 4 hours per day, without IR instrument TIR, UV on One hour delay for impact Impactor Release ~6 days out IR on imager on Dust analyzer on, continuously Radio Science begins Scheme is symmetrical around closest approach through far encounter mode Instrument check-out begins For planning and discussion purposes only

Hektor encounter flyby simulation For planning and discussion purposes only

Approach speed = 9. 11 km/sec Encounter Strategy Oterma Closest approach ~ 800 km Close Encounter mode 15 K km, 30 minutes away Far Encounter mode Approach mode 7. 5 M km, 9. 5 days 34 M km, 44 days Imager: 4 hours per day, without IR instrument TIR, UV on One hour delay for impact IR on imager on Dust analyzer on, continuously Radio Science begins Impactor Release ~6 days out Scheme is symmetrical around closest approach through far encounter mode Instrument checkout For planning and discussion purposes only

Design Rationale • Designed within constraints of AO – Limited mass – Limited cost • Constraint: Limited mass – Atlas V 531 max LV – Solution: reduce impactor mass • Constraint: Limited cost ($650 M) – Solution: Created a small but robust instrument package – Solution: Using proven technology to shorten the development and science phases For planning and discussion purposes only

System Mass and Power 700 W peak power 1850 kg total mass (Atlas 531 < 1890 kg) For planning and discussion purposes only

Launch/Carrier Spacecraft High Gain Antenna Solar Arrays Propulsion Thruster Stowed Probe with Antenna and Solar Arrays Deployed For planning and discussion purposes only

Major Architectural Components RCS Thrusters (12) Fuel Tanks (2) & Oxidizer Tank Radiator Panels (4) Reaction Wheels (4) Impactors (2) Pressurant Tanks (3) Battery C&DH Instruments (4) For planning and discussion purposes only

Power Subsystem • • • Main Power: ultraflex solar arrays • Sized for “approach mode” – when science ops begin at 5. 5 AU (560 W) Back up Power: 2 Li-Ion batteries: • 864 W-hr each • Two backups Compliant with launch and eclipse For planning and discussion purposes only

Thermal Control • Features – No moving parts – 32 kilograms of total thermal weight – 40 Watts maximum power consumption • Operating temperature : – Above 10 C during cruise – Below 40 C during close encounters – Precision temperature control for instruments and communication system only (0. 5ºC) For planning and discussion purposes only

Propulsion • Dual mode system – N 2 O 4 (oxidizer) and N 2 H 4 (fuel) • Main engine: bipropellant • RCS and TVC monopropellant • RCS thrusters in four branches of 3 thrusters • RCS selective redundancy • Main engine and TVC thrusters are single string • Identical tanks for oxidizer (1) and fuel (2) • COTS components For planning and discussion purposes only

Attitude Control System • Four reaction wheels in pyramid set-up • Pointing Requirements – Control • Driven by NAC on MSI during Far Encounter (40 arcsec) – Knowledge • Driven by WAC on Nav. Cam during Far Encounter (5 arcsec) – Stability • Driven by NAC on MSI during Close Encounter (0. 41 arcsec) • Slew Maneuvers – 164 degree maneuvers in 18 -24 min during encounter. – Will have to do a zero order crossing to get twice the acceleration – Can do with 3 of 4 wheels For planning and discussion purposes only

Computer Data Systems Data Storage: 11. 5 Gbits Science, Engineering, Software, Margin MSAP system with 3 x 4 Gbits Non-Volatile Memory Cards Assumed MSAP heritage from MSL CDS Block Diagram For planning and discussion purposes only

Software • Integrates all flight hardware functionality into cohesive system • Design rationale takes into account – Guidance, Navigation, and Control – Command Data Handling – Engineering Subsystems – Payload Accommodation • Heritage: MSL For planning and discussion purposes only

Telecommunications Subsystem • Redundant 2 -way X-Band • Main: – HGA, 3 meter dish pointed within 0. 2 0 to 34 m DSN • Safe mode: – MGA , 200 beamwidth, 70 m DSN. – 2 LGA, combined 900 beamwidth, 70 m DSN • Operational Modes – Receiver is always on. – Receiver and transmitter on during maneuvers, impactor Antenna deployment, close and far encounters, and during some part of approach. HGA Range (AU) Data Rate (kbps) Link Margin (db) 6. 4 25 3. 3 MGA 6. 4 10 3 LGA 1. 2 10 3. 3 For planning and discussion purposes only

Ground Systems • 2 Primary Systems: – Mission Operations System (MOS) – Ground Data System (GDS) • Science Return: – Data volumes: 25 Gb during flybys – Data rates range from 25 -75 kbps – Data downlinked within 2 wks after encounters Cruise phases: • 1 regular cruise • 4 quiescent cruises • No cruise science The 70 m DSN antenna at Goldstone, CA (NASA, DSN Antennae at Goldstone, CA Tracking Station (NASA/DSN) For planning and discussion purposes only

Cost Summary: Within $650 M Cost Cap! COST FY’ 08 Launch Vehicle Development Cost (30%) Phase A Phase B Phase C/D Operations Cost (15%) Project Cost $0. 0 M $520. 0 M $2. 0 M $46. 8 M $471. 2 M $102. 7 M $622. 8 M For planning and discussion purposes only

Development Cost (Phase A-D) Project Management $17. 2 M Project Systems Engineering $16. 9 M Mission Assurance $15. 0 M Science $11. 3 M Payload System $65. 9 M Flight System $211. 3 M Mission Operations Preparation $16. 8 M Ground Data Systems $14. 9 M ATLO $19. 4 M Education and Public Outreach $1. 2 M Mission and Navigation Design $10. 0 M Development Reserves (30%) $119. 9 M Total $520. 0 M For planning and discussion purposes only

Payload Systems Cost High Resolution Multispectral Imager Thermal IR Spectrometer Dust Secondary Ion Mass Spectrometer UV Imaging Spectrograph Impactor capsules (2) Total $20. 4 M $12. 0 M $26. 8 M $6. 0 M $0. 7 M $69. 5 M Additional science instruments include Radio Science and Wide Angle Camera - not included in instrument cost calculation For planning and discussion purposes only

Flight Systems Cost Power C&DH Telecom Structures (includes Mech. I&T) Thermal Propulsion ACS Harness S/C Software Total $40. 0 M $13. 8 M $19. 0 M $24. 3 M $9. 9 M $20. 1 M $32. 5 M $2. 1 M $21. 5 M $183. 2 M For planning and discussion purposes only

Operations Cost (Phase E-F) Project Management Project Systems Engineering Mission Assurance Science Mission Operations Ground Data Systems Education and Public Outreach Total (15%) $9. 1 M $0. 0 M $0. 5 M $19. 8 M $51. 1 M $7. 6 M $3. 7 M $91. 8 M For planning and discussion purposes only

Threshold Science Mission Baseline Payload Threshold Payload Baseline Max Data Threshold Max Data Mass Power Rate Mission element (kg) (W) (kbps) Baseline Comment (kg) (W) (kbps) Threshold Comment Multispectral Imager imager combined with 52 58 4000 45 51 4000 imager only (MSI) IR spectrometer descope filter wheel, Navigation camera allows imaging in 9 7. 4 4000 9 7 4000 minimal science return with filter wheel visible range Secondary Ion Mass power on at far power on at close 19. 8 20. 4 0. 5 19. 8 7. 0 0. 5 Spectrometer (SIMS) encounter mode encounter reduced data rate, Ultraviolet Imaging 8 7 0. 8 4. 4 0. 4 reduced spectral range Spectrometer (UVIS) Thermal and Infrared Spectrometer (TIR) 14. 1 13 0. 8 Main Belt Asteroid reconnaissance n/a n/a Trojan Impactor 75 n/a Centaur Impactor 75 n/a 253 106 8002 TOTAL fully descoped adds value to mission, instrument and ops test fully descoped 75 n/a fully descoped 153 70 very low mineralogy data return potential operations cost savings same as baseline mission reduced mass and operations cost 8001 For planning and discussion purposes only

Conclusions • Significant advances in our understanding of the outer solar system • First observations of a MBA, Trojan asteroid, and a Centaur • Two impactors provide both innovative science and add public interest to mission • Robust suite of instruments with proven and reliable science capability • Well-designed spacecraft and trajectory • Budgeted below cap with a descoping plan that preserves science outcomes For planning and discussion purposes only

Acknowledgments • • • Charles Budney Anita Sohus Amber Norton Team X JPL NASA Science Mission Directorate For planning and discussion purposes only

Thank you very much! For planning and discussion purposes only

Science Returns for Threshold Mission For planning and discussion purposes only

Evolutionary processes on small bodies • Space Weathering – Indicates interaction with space environment. May correlate with migration history. • Morphology – Have these bodies experienced outgassing, cratering, and/or weathering? • Bulk Chemistry and Minerological Composition – Initial composition and thermal history? Also what is the degree of differentiation? • Density – Are the objects more like asteroids (~2 g / cc) or comets (~1 g / cc) ? Hektor (Artist's Conception) Itokawa. Hayabusa For planning and discussion purposes only