Post on 26-Mar-2018
Jupiter Europa OrbiterThe NASA Element of the Europa Jupiter System Mission
Presented by:Karla B. Clark
EJSM–JEO Study ManagerJet Propulsion Laboratory
California Institute of Technology
Current Status of the EJSM Jupiter Europa Orbiter Flagship Mission Design
Presentation to the International workshop:“Europa lander: science goals and experiments”
2/09
• NASA & ESA share mission leadership• Two independently launched and operated
flight systems with complementary payloads
EJSM Baseline Mission Overview
2/8/08 2Predecisional, For Planning Purposes Only
• ~10–11 Instruments on each flight system, including Radio Science
– Jupiter Europa Orbiter (JEO):NASA-led mission element
– Jupiter Ganymede Orbiter (JGO):ESA-led mission element
• Mission Timeline– Nominal Launch: 2020– Jovian system tour
phase: 2–3 years– Moon orbital phase: 6–12
months– End of Prime Missions:
2029
JGO Baseline Mission Overview
• ESA-led portion of EJSM• Objectives: Jupiter System, Callisto, Ganymede • Launch vehicle: Arianne 5• Power source: Solar Arrays• Mission timeline:
– Launch: 2020• Uses 6-year Venus-Earth-Earth gravity assist
trajectory– Jovian system tour phase: ~28 months
• Multiple satellite flybys– 9 Ganymede– 21 Callisto (19 close flybys)
– Ganymede orbital phase: 260 days– End of prime mission: 2029– Spacecraft final disposition: Ganymede surface
impact• Radiation: ~85 krad behind 320 mils of Al
(requirement to keep it below 100 krad)
2/8/08 3Predecisional, For Planning Purposes Only
Wide Angle and Medium Resolution Camera
V/NIR Imaging Spectrometer
EUV/FUV Imaging Spectrometer
Ka-band transponder
Ultra Stable Oscillator
Magnetometer
Radar Sounder
Micro Laser Altimeter
Thermal IR Mapper
Sub-millimeter wave sounder
Plasma Package
JGO Science• Key Science Objectives
– In depth post-Galileo exploration of the Jupiter system, synergistically with JEO
• En route to Callisto and Ganymede
– In-depth study and full mapping of Callisto• Multiple flybys using a resonant orbit
– Detailed orbital study of Ganymede• Two successive dedicated moon orbits
(elliptical first, then circular)
• A major step forward in our understanding of the two “icy” Galilean satellites, Ganymede and Callisto:
– Ocean detection/characterisation– State of internal differentiation– Global surface mapping: morphology and chemistry– Comprehensive study of Ganymede’s magnetism– Relations between thermal history, geology, oceans
and the Laplace resonance
2/8/08 4Predecisional, For Planning Purposes Only
JEO Baseline Mission Overview• NASA-led portion of EJSM extensively studied in 2007–2008• Objectives: Jupiter System, Europa • Launch vehicle: Atlas V 551• Power source: 5 MMRTG or 5 ASRG• Mission timeline:
– Launch: 2018 to 2022, nominally 2020• Uses 6-year Venus-Earth-Earth gravity assist trajectory
– Jovian system tour phase: 30 months• Multiple satellite flybys: 4 Io, 6 Ganymede,
6 Europa, and 9 Callisto – Europa orbital phase: 9 months– End of prime mission: 2029– Spacecraft final disposition: Europa surface impact
• 11 Instruments, including radio science• Radiation dose: 2.9 Mrad (behind 100 mils of Al)
– Handled using a combination of rad-hard parts and tailored component shielding– Key rad-hard parts are available, with the required heritage– Team is developing and providing design information and approved parts list for
prospective suppliers of components, including instruments
2/8/08 5Predecisional, For Planning Purposes Only
JEO Goal: Explore Europa to Investigate Its Habitability
Objectives:• Ocean and Interior• Ice Shell• Chemistry and Composition• Geology• Jupiter System
– Satellite surfaces and interiors– Satellite atmospheres– Plasma and magnetospheres– Jupiter atmosphere– Rings
Europa is the archetype of icy world habitability 2/8/08 6Predecisional, For Planning Purposes Only
JEO Model PayloadJEO Instrument Similar InstrumentsRadio Science New Horizons USO, Cassini KaTLaser Altimeter MESSENGER MLA, NEAR NLRIce Penetrating Radar MRO SHARAD, Mars Express MARSISVIS-IR Spectrometer MRO CRISM, Chandrayaan MMMUV Spectrometer Cassini UVIS, New Horizons AliceIon & Neutral Mass Spectrometer Rosetta ROSINA RTOFThermal Instrument MRO MCS, LRO Diviner Narrow-Angle Camera New Horizons LORRI, LRO LROCCamera Package MRO MARCI, MESSENGER MDISMagnetometer MESSENGER MAG, Galileo MAGParticle and Plasma Instrument New Horizons PEPSSI, Deep Space 1 PEPE
2/8/08 7Predecisional, For Planning Purposes Only
JEO Baseline Flight System• Three-axis stabilized with instrument
deck for nadir pointing• Articulated HGA for simultaneous
downlink during science observations• Data rate of 150 kbps to DSN 34m
antenna on Ka-band• Performs 2260 m/s ∆V with 2646 kg of
propellant• Five MMRTGs would provide 540 W
(EOM) with batteries for peak modes• Rad-hardened electronics with
shielding to survive 2.9 Mrad (behind 100 mil Al) environment
• 9-year lifetime• Healthy mass and power margins
(43%, >33% respectively)
JEO incorporates minor modifications to a strong EE2007 design
Artist Rendering
2/8/08 8Predecisional, For Planning Purposes Only
Power Assembly
Balanced Bus Grounding Hardware
RPS Protection Diodes
Battery Control FET Board
Pyro and Prop Enable Relays
Shunt Limiter FETs
Wheel Drive Electronics (4)
Star Trackers (2)
25 Nms RWA (4) w/ electronics
2-Channel Gimbal Drive Electronics (3)4-Channel Gimbal
Drive Electronics (2)
SIRU (1)
12 A-Hr Li-Ion
Batteries (2)
Lightning Suppression
Assembly
Power Distribution Unit
Power Bus Controller
Power Switch Cards (8)
Power Switch Cards (8)
Power Switch Cards (8)
Power Switch Cards (8)
Power Switch Cards (8)
Power Switch Cards (8)
Power Switch Cards (8)
Power Switch Cards (8)
Prop Drive Electronics (4)
Prop Drive Electronics (4)
Prop Drive Electronics (4)
Prop Drive Electronics (4)
Pyro Driver Cards (6)
Pyro Driver Cards (6)
Pyro Driver Cards (6)
Pyro Driver Cards (6)
Pyro Driver Cards (6)
Pyro Driver Cards (6)
Remote Engineering
Unit (2)
Remote Engineering
Unit (2)
Power Conditioning
Unit (2)
Power Conditioning
Unit (2)
Temp Sensors & Heaters
MLI
Model Payload
C&DH*
Power
Telecom
GHe GHe
Fuel Tank
Gimbaled 890 N HiPATMain Engine
L
16 (8 coupled clusters) 4.5 N ACS Thrusters
Ox Tank
Propulsion
To S/C Loads
U/L, D/L
10m Magnetometer Boom
HGA Gimbal
Variable RHUs (24)
Linear Separation AssemblyLouvers
Main Engine Gimbal
X 4 TWTA
Ka-band
TWTAX-band
25W RF Ka-Band TWTA
(2)
25W RFX-band
TWTA (2)
HYB
X 4
Filter
WTS (2)
WTS
X-Band LGA (2)
3m Ka/X HGA
WTS
HYB
X-Band MGA
WTS
CTS
USO
T
TELECOM ENCLOSURES BEHIND HGA
High-Rate Instruments
IR Spectrometer (VIRIS)
Ice Penetrating Radar (IPR)
Wide Angle & Medium Angle Cameras (WAC + MAC)
Narrow Angle Camera (NAC)
Low-Rate Instruments
Ultraviolet Spectrometer (UVS)
Laser Altimeter (LA)
Ion and Neutral Mass Spectrometer (INMS)
Dual Magnetometer (MAG)
Thermal Instrument (TI)
Particle and Plasma Instrument (PPI)
Shunt Radiator
Computer Chassis (2)
cPC
I Bac
kpla
ne
CEPCU
MTIF
BAE RAD750 (2 slot width)
Custom JEO Card
MREU
Computer Chassis (2)
cPC
I Bac
kpla
ne
MTIF
BAE RAD750 (2 slot width)
Custom JEO Card
MREU
CEPCU
Wheel Drive Electronics (4)Wheel Drive
Electronics (4)Sun Acquisition
Detectors (3)
SDST (2)
X/Ka-bandExciter
X-bandExciter
X-bandReceiver
SDST (2)
X/Ka-bandExciter
X-bandExciter
X-bandReceiver
MMRTG (5)
MMRTG (5)
MMRTG (5)
MMRTG (5)
MMRTG (5)
Waste Heat
Mechanical & Thermal
KaT
Rad Monitoring
Rad Monitoring 6U Electronics Card (Physically
in C&DH Chassis)
3m HGA Boom
Pressure Transducers (10)
DiplexerKa Diplexer (2)
HYB
DiplexerX Diplexer (2)
Sensor 1
Sensor 3
Sensor 2
Hybrid SSR:1Gb CRAM
16 Gb SDRAM Science Memory
JEO Flight System Block Diagram
RHUs (20)
*Note: All C&DH interfaces are cross-strapped.
To MTIF Card in C&DH
Atlas V 551
LV Adapter (LV provides)
T-0 Umbilical
AACS
2/8/08 9Predecisional, For Planning Purposes Only
JEO Mass Summary
JEO’s design is robust to future changes due to large mass margins
CBE Cont. CBE+Cont.
Payload 163 30% 211Model Payload 106 30% 137Payload Radiation Shielding 57 30% 74
Spacecraft 1208 24% 1498Power (w/o RPSs) 55 30% 72C&DH 34 17% 40Telecom 56 27% 70Structures & Mechanisms 320 31% 420Thermal 68 30% 88Propulsion 157 28% 201AACS 69 33% 91Cabling 83 30% 108Radiation Monitoring System 8 30% 10RPS System 226 0% 226Spacecraft Radiation Shielding 132 30% 172
Flight System Total Dry 1371 25% 1709Additional System Margin to achieve study req. 226
Flight System Total Dry with Required Margin 1371 41% 1935Propellant 2646
Flight System Total Wet 1371 4581LV Adapter with required margin 123
Flight System Launch Mass Wet 1453 4704
Atlas V 551 Capability for 2020 VEEGA 5040
Additional Margin 336
System Margin (33% required per study guidelines) 43%
JEO Baseline Mass Equipment ListFlight System Mass, kg
Payload and Shielding
Very Healthy Margins
5 MMRTGs
S/C Radiation
Shielding for 2.9 Mrad
Delta V of 2260 m/s
Calculating Dry Mass Margin per Study
Guidelines:
Dry Mass Allocation (MPRV) = LV Capability – Prop–RTG Mass* = 5040 – 2646 – 226 = 2168 kg
Dry Mass CBE (PRV) = S/C CBE + LV Adapt–RTG Mass* = 1371 + 82 – 266 = 1227Dry Mass Margin
= (MPRV – PRV)/MPRV = (2168 – 1227)/2168 = 43%
*Note: The MMRTG mass is considered a Not-To-Exceed Mass, and is therefore excluded from the margin calculations, per HQ direction.
2/8/08 10Predecisional, For Planning Purposes Only
2/8/08 11
Jupiter System Science• Jupiter and Io monitoring, atmospheres, magnetospheres,
rings and small bodies• Satellite science
– Io: 3 flybys• Opportunities for imaging, IR spectroscopy, and altimetry• In situ analysis of extended atmosphere with INMS at 75 km
– Europa: 6 flybys• Radar and altimetry characterization and calibration • Imaging at up to 10−50 m resolution, NIR 250−1250 m
– Ganymede: 6 flybys• Radar sounding of grooved and dark terrains • Range of lats, lons for magnetosphere sampling
– Callisto: 9 flybys• High-latitude flyby for gravity field determination• Ocean characterization with magnetometer• Radar for subsurface structure of ancient cratered terrain
Predecisional, For Planning Purposes Only
2/8/08 Predecisional, For Planning Purposes Only 12
Io Flyby Example
IoFlyb05LF.wmvIoFlyb05LF.wmv
JOI to EOI Jul 2028 Aug 2028 Sep 2028 Oct 2028
Observing Strategies for Europa Campaigns 1−3• Always on: LA, MAG, PPI, TI, INMS (50%)• 2-orbit ops scenario permits power/data rate equalization:
- Even orbits emphasize optical remote sensing:- Odd orbits emphasize radar sounding to locate water
• Targets collected with residual data volume
4
10° x 10°
Eng Assessment (6 d)Initial Europa OrbitAltitude: 200 kmInclination: 95−100 deg
(~85° N lat) Lighting: 2:30 PM LSTRepeat: 4 Eurosols
After Campaign 1Altitude: 100 kmRepeat: 6 Eurosols
3
Targeted Processes100 km altitude
8 eurosols ≈ 28 days
MAC80x20 km
IRS10x10 km
IPR + LA
WAC context
Europa Campaigns 1−3 total 99 days
Europa Science Campaigns
Regional Processes100 km altitude
(100 m/pixel WAC)12 eurosols ≈ 43 days
2A 2B
Global Framework200 km altitude
(200 m/pixel WAC)8 eurosols ≈ 28 days
1A 1B Europa Science Campaigns
2/8/08 13Predecisional, For Planning Purposes Only
Paving the Way for a Future Lander• Best for Science - Recent material
exchange with subsurface (i.e. young in age) and rich in chemistry– High resolution imaging, radar, IR
spectroscopy, thermal imaging
2/8/08 Predecisional, For Planning Purposes Only 14
• Safe for landing - Meter scale topography, heterogeneity, depth and porosity of regolith– High resolution imaging, laser altimetry, radar,
thermal inertia– Fine scale processes: mass wasting, sputter
erosion, sublimation, impact gardening, frost deposition
Europa Jupiter System MissionNASA Jupiter Europa Orbiter + ESA Jupiter Ganymede Orbiter
EJSM is well defined and ready to go!
• EJSM Study• International team,
shared leadership• Built on previous studies• Community involvement
• Scientifically rich• Well-defined, mature science• Exploration opportunities• Technology/mission design
mature
2/8/08 15Predecisional, For Planning Purposes Only