1. For planning and discussion purposes only

2. 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.”

3. For planning and discussion purposes only

4. SHOTPUT Survey of Hektor and Oterma Through Pulverization of Unique Targets First Mission to Explore Trojans and Centaur Through Flybys and Impacts PICS Fall 2008 - Alessondra Springmann November 4, 2008 "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."

5. For planning and discussion purposes only A Unique Mission to Unexplored Worlds 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 William K. Hartmann

6. 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

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

8. For planning and discussion purposes only Background on Bodies Trojans –Discovered in early 20th 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

9. For planning and discussion purposes only ? Targets 2001 HM10(624) HektorS/2006 (624) 139P Oterma TypeMain Belt Asteroid Trojan (Contact Binary) Trojan CompanionCentaur Spectral TypeDD?? Albedo?0.025?? Diameter (km)?2251530-60 Density (g/cm3)?2.0-2.4? Inclination (deg)3.1718.191.94 binary semimajor axis (km)~1000? binary orbital period(h)~50? Binary System Targets

10. For planning and discussion purposes only Science Traceability Matrix

11. For planning and discussion purposes only

17. 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

18. 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

19. For planning and discussion purposes only 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 Organic Matter in the Outer Solar System

20. 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 1940s Comparison of known dynamic object with one that is possibly dynamic Morbidelli et al. 2005

21. 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? –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)‏

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

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

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

25. 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

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

27. 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 Mass52 kg Power58 W

28. 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 500 bits/ sec Mass 19.8 Atomic Mass Range 1 to 3,500 AMU Power 20.4 W

29. For planning and discussion purposes only Thermal Infrared Spectrometer (TIS) Purpose: –surface and subsurface mineralogy –volatiles –thermophysical properties TIS instrument to be used on board Trojan/Centaur Mission (after TES instrument, ASU) Spectral range~ 400-1200 cm -1 (8-25 μm) Spatial resolution variable, but <16 km/pixel closest Data rate~ 800 bps Dimensions24 x 35 x 40 cm Mass14.1 kg Power Req.13.2 W

30. For planning and discussion purposes only Ultraviolet Imaging Spectrograph (UVIS) 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 ) Primary purposes: –Determine D/H ratio –Hydrocarbons –ion emission (e.g. N +, N 2+,O +, 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 Mass15.6 kg Power8W avg, 12W peak

31. For planning and discussion purposes only Wide Angle Camera (WAC) Primary purposes: –Mapping and topography Required for optical navigation: –2 cameras for stereo images –5 color filter wheel –(SDSS – ugriz) Mass4 kg Power3 W Data rate500 kbps

32. 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 X- band. –During the flyby the spacecraft will be gravitationally attracted to the target body and create a velocity perturbation. Target Body

33. For planning and discussion purposes only Phase A-D Schedule 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 HM10, Hektor, Oterma)

34. For planning and discussion purposes only Baseline Mission Design Mar 27, 2015 - Launch Jan 13, 2016 – 2001 HM10 Jun 14, 2016 – Deep Space Maneuver May 17, 2018 – Earth Flyby Mar 25, 2020 – Hektor / S/2006 and Deep Space Maneuver Oct 30, 2022 – Oterma –Launch –Kennedy Space Center, Fl –Launch vehicle: Atlas V 531 –C3: 51.4 km 2 /s 2

35. For planning and discussion purposes only Baseline Trajectory

36. For planning and discussion purposes only Baseline Trajectory

37. For planning and discussion purposes only Edge On Trajectory View

38. For planning and discussion purposes only Main belt asteroid Closest approach ~ 900 km 15K km, 30 minutes away 2M km, 3 days 3M km, 4 days Imager: 4 hours per day, without IR instrument Instrument check-out begins 2 weeks out - BEFORE approach Radio science begins IR on imager on Dust analyzer on, continuously Approach mode Far Encounter mode Close Encounter mode Scheme is symmetrical around closest approach through far encounter mode Approach speed = 8.24 km/sec TIS and UVIS On Encounter Strategy

39. For planning and discussion purposes only Hektor Closest approach - 700 km 15K km, 30 minutes away 7.5M km, 7 days 110M km, 150 days Imager: 4 hours per day, without IR instrument Instrument check-out begins TIR, UV on One hour delay for impact IR on imager on Dust analyzer on, continuously Radio Science begins Approach mode Far Encounter mode Close Encounter mode Scheme is symmetrical around closest approach through far encounter mode Approach speed = 8.2 km/sec Impactor Release ~6 days out Encounter Strategy

40. For planning and discussion purposes only Hektor encounter flyby simulation

41. For planning and discussion purposes only Oterma Closest approach ~ 800 km 15K km, 30 minutes away 7.5M km, 9.5 days 34M km, 44 days Imager: 4 hours per day, without IR instrument Instrument checkout TIR, UV on One hour delay for impact IR on imager on Dust analyzer on, continuously Radio Science begins Approach mode Far Encounter mode Close Encounter mode Scheme is symmetrical around closest approach through far encounter mode Impactor Release ~6 days out Approach speed = 9.11 km/sec Encounter Strategy

42. 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

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

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

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

46. 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 (560W) Back up Power: 2 Li-Ion batteries: 864 W-hr each Two backups Compliant with launch and eclipse

47. 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)

48. 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

49. 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 NavCam 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

50. 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

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

52. For planning and discussion purposes only Telecommunications Subsystem Redundant 2-way X-Band Main: –HGA, 3 meter dish pointed within 0.2 0 to 34m DSN Safe mode: –MGA, 20 0 beamwidth, 70m DSN. –2 LGA, combined 90 0 beamwidth, 70m DSN Operational Modes –Receiver is always on. –Receiver and transmitter on during maneuvers, impactor deployment, close and far encounters, and during some part of approach. AntennaRange (AU) Data Rate (kbps) Link Margin (db) HGA6.4253.3 MGA6.4103 LGA1.2103.3

53. For planning and discussion purposes only Ground Systems DSN Antennae at Goldstone, CA Tracking Station (NASA/DSN) 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

54. For planning and discussion purposes only Cost Summary: Within $650 M Cost Cap! Launch Vehicle$0.0 M Development Cost (30%)$520.0 M Phase A$2.0 M Phase B$46.8 M Phase C/D$471.2 M Operations Cost (15%)$102.7 M Project Cost$622.8 M COST FY’08

55. 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

56. For planning and discussion purposes only Payload Systems Cost High Resolution Multispectral Imager$20.4 M Thermal IR Spectrometer$12.0 M Dust Secondary Ion Mass Spectrometer$26.8 M UV Imaging Spectrograph$6.0 M Impactor capsules (2)$0.7 M Total$69.5 M Additional science instruments include Radio Science and Wide Angle Camera - not included in instrument cost calculation

57. For planning and discussion purposes only Flight Systems Cost Power$40.0 M C&DH$13.8 M Telecom$19.0 M Structures (includes Mech. I&T)$24.3 M Thermal$9.9 M Propulsion$20.1 M ACS$32.5 M Harness$2.1 M S/C Software$21.5 M Total$183.2 M

58. For planning and discussion purposes only Operations Cost (Phase E-F) Project Management$9.1 M Project Systems Engineering$0.0 M Mission Assurance$0.5 M Science$19.8 M Mission Operations$51.1 M Ground Data Systems$7.6 M Education and Public Outreach$3.7 M Total (15%)$91.8 M

59. For planning and discussion purposes only Baseline Mass (kg) Baseline Power (W) Max Data Rate (kbps)Baseline Comment Threshold Mass (kg) Threshold Power (W) Max Data Rate (kbps)Threshold Comment 52584000 imager combined with IR spectrometer 45514000imager only 97.44000 allows imaging in visible range 974000 descope filter wheel, minimal science return 19.820.40.5 power on at far encounter mode 19.87.00.5 power on at close encounter 870.84.4 0.4 reduced data rate, reduced spectral range 14.1130.8 very low mineralogy data return n/a adds value to mission, instrument and ops test potential operations cost savings 75n/a 75n/a same as baseline mission 75n/a reduced mass and operations cost Mission element Multispectral Imager (MSI) Navigation camera with filter wheel Secondary Ion Mass Spectrometer (SIMS) Ultraviolet Imaging Spectrometer (UVIS) Thermal and Infrared Spectrometer (TIR) Main Belt Asteroid reconnaissance Trojan Impactor Centaur Impactor TOTAL 253 1068002 153708001 Baseline PayloadThreshold Payload fully descoped Threshold Science Mission

60. 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

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

62. For planning and discussion purposes only Thank you very much!

63. For planning and discussion purposes only Trojans and Centaurs Never previously observed in situ First visit to a D-type asteroid Bimodal Color Distribution in Centaurs –Blue objects originated further in? Trojans are red (and formed near Jupiter)

64. For planning and discussion purposes only Science Returns for Threshold Mission

65. 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) ? Itokawa- Hayabusa Hektor (Artist's Conception)‏