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.
Slide 3
For planning and discussion purposes only
Slide 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."
Slide 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
Slide 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
Slide 7
For planning and discussion purposes only Our Mission: SHOTPUT
Reconnaissance and impactor study of Trojan asteroids and Centaurs
Centaurs Trojans
Slide 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
Slide 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
Slide 10
For planning and discussion purposes only Science Traceability
Matrix
Slide 11
For planning and discussion purposes only
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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
Slide 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
Slide 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
Slide 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
Slide 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)
Slide 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.
Slide 23
For planning and discussion purposes only Impactor Science
Motivation: Observe subsurface materials Lisse et al. (2006)
Slide 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
Slide 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
Slide 26
For planning and discussion purposes only Significant advance
in understanding Some advance in understanding Science Traceability
Matrix Breakthrough level of understanding
Slide 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
Slide 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
Slide 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 m) Spatial resolution variable,
but
Slide 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 , = 4.8 ) 4. XUV
Spectrometer (563 - 1182 , = 4.8 ) 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
Slide 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
Slide 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
Slide 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)
Slide 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
Slide 35
For planning and discussion purposes only Baseline
Trajectory
Slide 36
For planning and discussion purposes only Baseline
Trajectory
Slide 37
For planning and discussion purposes only Edge On Trajectory
View
Slide 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
Slide 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
Slide 40
For planning and discussion purposes only Hektor encounter
flyby simulation
Slide 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
Slide 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
Slide 43
For planning and discussion purposes only 1850 kg total mass
(Atlas 531 < 1890 kg) 700W peak power System Mass and Power
Slide 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
Slide 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
Slide 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
Slide 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
(0.5C)
Slide 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
Slide 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
Slide 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
Slide 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
Slide 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
Slide 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
Slide 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 FY08
Slide 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
Slide 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
Slide 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
Slide 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
Slide 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
Slide 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
Slide 61
For planning and discussion purposes only Acknowledgments
Charles Budney Anita Sohus Amber Norton Team X JPL NASA Science
Mission Directorate
Slide 62
For planning and discussion purposes only Thank you very
much!
Slide 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)
Slide 64
For planning and discussion purposes only Science Returns for
Threshold Mission
Slide 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)