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Jupiter System ObserverJupiter System Observer
Mission ImplementationMission Implementation
Polar Gateways ConferencePolar Gateways Conference
January 28, 2008January 28, 2008
18 October 2007 2JSO TMC & Science Panel Site Visit
Engineering Definition TeamEngineering Definition TeamTechnical LeadTechnical Lead Johnny KwokJohnny Kwok Science OpsScience Ops Bill SmytheBill Smythe
Systems EngineerSystems Engineer Grace Tan-Wang,Grace Tan-Wang,
Sarah HornbeckSarah Hornbeck
TelecomTelecom Dave HansenDave Hansen
Mission ArchitectMission Architect Tom SpilkerTom Spilker Ground SystemsGround Systems Sue Barry, Greg WelzSue Barry, Greg Welz
Payload EngineerPayload Engineer Ken Klaasen,Ken Klaasen,
Mark ReddingMark Redding
ThermalThermal Bob Miyake, Don Bob Miyake, Don Strayer, Glen TsuyukiStrayer, Glen Tsuyuki
Mission DesignMission Design Nathan StrangeNathan Strange
Ryan RussellRyan Russell
SoftwareSoftware Suzanne Klein, Jay Suzanne Klein, Jay BrownBrown
Concurrent EngineerConcurrent Engineer Keith Warfield, Erick Keith Warfield, Erick Sturm, Tracy Van HoutenSturm, Tracy Van Houten
CostCost Chuck Baker, Ed Chuck Baker, Ed JorgensenJorgensen
ACSACS Bob KinseyBob Kinsey RiskRisk Jim Kinnison (APL),Jim Kinnison (APL),
Julie WertzJulie Wertz
CDSCDS Brian Cox, Yutao HeBrian Cox, Yutao He RadiationRadiation Shawn Kang, Insoo Shawn Kang, Insoo JunJun
MechanicalMechanical Steve Kondos, Ted Steve Kondos, Ted IskenderianIskenderian
Planetary Planetary ProtectionProtection
Laura NewlinLaura Newlin
PowerPower Paul Timmerman, Hrair Paul Timmerman, Hrair AntablianAntablian
Report ManagerReport Manager Jan LudwinskiJan Ludwinski
PropulsionPropulsion Chris England, Paul Chris England, Paul WoodmanseeWoodmansee
18 October 2007 3JSO TMC & Science Panel Site Visit
Architectural ElementsArchitectural Elements
Delta IVH
Atlas V Direct
V-EGA
VEEGA
VkEmMnGA
Chemical
SEP
RTG
Solar
Single
+Probe
+Sub-Sat
~ 0.5 m
~ 1.5m
~ 1 m
J. Sat. Tour
G. Circular
G. EllipticalInc. > 40°
LaunchVehicle
InterplanetaryTrajectory
PropulsionPowerSource
# of S/C ApertureFinal
Destination
+Lander
G. EllipticalInc. < 40°
18 October 2007 4JSO TMC & Science Panel Site Visit
Architectures SelectionArchitectures Selection
Single S/C
+Sub-Satellite
+Probe
Single S/C ~ 0.5 m
Jovian Tour
G. Elliptical < 40°Atlas 551
~ 0.5 m
> 1.0 m
~ 0.5 m
~ 0.5 m
Delta IVH
G. Circular
G. Elliptical
Jovian Tour
Jovian Tour
Jovian Tour
G. Elliptical > 40°
G. Elliptical < 40°
G. Elliptical > 40°
G. Elliptical > 40°
Descoped
Baseline
18 October 2007 5JSO TMC & Science Panel Site Visit
Descoped Options & Trade StudiesDescoped Options & Trade Studies
Alternative Descoped MissionsAlternative Descoped Missions Atlas V with circular Ganymede orbit – Completed after report dateAtlas V with circular Ganymede orbit – Completed after report date
Reduced Io flyby to 2Reduced Io flyby to 2 Reduced MMRTG to 6Reduced MMRTG to 6 Direct insertion to circular orbitDirect insertion to circular orbit
Atlas V with slightly elliptical final Ganymede orbitAtlas V with slightly elliptical final Ganymede orbit Determined by available propellantDetermined by available propellant
Explore Orbit Options Explore Orbit Options Explore transfer orbit options to reduce GOI Explore transfer orbit options to reduce GOI V V
Lagrangian point dynamics, distant retrograde orbitLagrangian point dynamics, distant retrograde orbit Study different elliptical orbit at different inclinations and eccentricityStudy different elliptical orbit at different inclinations and eccentricity
Additional TradesAdditional Trades Mission lifetimeMission lifetime Science payloadScience payload
We are presenting two possible missions within the study guidelines
Jupiter System Observer Jupiter System Observer
January 28, 2008January 28, 2008
Payload for Planning Purposes
18 October 2007 7JSO TMC & Science Panel Site Visit
Planning PayloadPlanning Payload
Notional set of instruments that will meet science measurement Notional set of instruments that will meet science measurement requirementsrequirements
Used to understand the engineering aspects of the mission design, Used to understand the engineering aspects of the mission design, spacecraft design, and operational scenariosspacecraft design, and operational scenarios
Proof of concept, not final selectionsProof of concept, not final selections Actual instrument selections to be done via NASA AO processActual instrument selections to be done via NASA AO process
18 October 2007 8JSO TMC & Science Panel Site Visit
Payload Accommodation - 1Payload Accommodation - 1
Remote sensing instruments mounted on nadir-viewing deckRemote sensing instruments mounted on nadir-viewing deck Detector cooling provided via passive radiators viewing away from Detector cooling provided via passive radiators viewing away from
the Sun and away from Ganymede when in orbitthe Sun and away from Ganymede when in orbit Pointing requirementsPointing requirements
Control to ≤ 0.4 mradControl to ≤ 0.4 mrad Stability to ≤ 2 Stability to ≤ 2 rad over 0.5srad over 0.5s S/C scanning at rates that are slow (40 S/C scanning at rates that are slow (40 rad/s to 9 mrad/s) and smooth rad/s to 9 mrad/s) and smooth
(rate stability to <10% of commanded rate) for distant spectrometer slit (rate stability to <10% of commanded rate) for distant spectrometer slit scanningscanning
Reconstruction to ≤ 0.08 mradReconstruction to ≤ 0.08 mrad Trade studies ruled out both a scan platform and a turntable as too Trade studies ruled out both a scan platform and a turntable as too
massive to accommodatemassive to accommodate
18 October 2007 9JSO TMC & Science Panel Site Visit
Hi-Res Camera/Vis IR Spectrometer
UV Spectrometer
Magnetometer & Boom
Thermal SpectrometerPlasma Spectrometer/Energetic Particle Detector
Laser Altimeter
Med ResStereo Camera
Star Tracker (2)
LGA, X-band (2)
LGA, Ka-band (2)
Dual axis HGA Gimbal
ReactionWheelAssembly (4)
Instrument ViewInstrument View
18 October 2007 10JSO TMC & Science Panel Site Visit
Payload Accommodation - 2Payload Accommodation - 2
Space for electronics cards in radiation-shielded chassis (reduces Space for electronics cards in radiation-shielded chassis (reduces environment to 150 krad)environment to 150 krad)
Downlink data rate Downlink data rate 600 kbps to support Jovian system science600 kbps to support Jovian system science Periodic Jupiter global coverage and Io monitoringPeriodic Jupiter global coverage and Io monitoring Near-global multi-spectral satellite imaging (UV through thermal IR)Near-global multi-spectral satellite imaging (UV through thermal IR) Altimetry of satellites (global of Ganymede)Altimetry of satellites (global of Ganymede) Radar mapping of satellites (global of Ganymede)Radar mapping of satellites (global of Ganymede) Continuous fields and particles dataContinuous fields and particles data Remote sensing coverage of ~1000 selected target regions on each Galilean Remote sensing coverage of ~1000 selected target regions on each Galilean
satellite and satellite and 50,000 targets on Ganymede50,000 targets on Ganymede Control of Ganymede low circular orbital period to provide specific ground Control of Ganymede low circular orbital period to provide specific ground
track spacing and interleaving for global mappingtrack spacing and interleaving for global mapping Ganymede orbit reconstruction to 1 m radial accuracy during at least 30 Ganymede orbit reconstruction to 1 m radial accuracy during at least 30
days in low circular orbitdays in low circular orbit Implies near-continuous Doppler tracking (dual frequency preferred)Implies near-continuous Doppler tracking (dual frequency preferred) No more than one thruster firing per day No more than one thruster firing per day
18 October 2007 11JSO TMC & Science Panel Site Visit
Unique Technical ChallengesUnique Technical Challenges
Radiation toleranceRadiation tolerance Sensors and supporting electronics located outside shielded chassis Sensors and supporting electronics located outside shielded chassis
may need their own shielding (included in current mass allocations)may need their own shielding (included in current mass allocations) Cost estimates include a factor (25%) for addressing radiation design Cost estimates include a factor (25%) for addressing radiation design
issues issues Data rate reductionData rate reduction
High-rate instruments will be required to include large internal data High-rate instruments will be required to include large internal data reduction factors via compression, editing, summing, etc.reduction factors via compression, editing, summing, etc.
Frequent power cyclingFrequent power cycling Power limitations will require frequent instrument duty cycling into low-Power limitations will require frequent instrument duty cycling into low-
power modes (1000s of times for all but F&P instruments)power modes (1000s of times for all but F&P instruments)
Jupiter System Observer Jupiter System Observer
January 28, 2008January 28, 2008
Mission Design
18 October 2007 13JSO TMC & Science Panel Site Visit
Mission Design Alignment with PayloadMission Design Alignment with Payload
En
cou
nte
rs
Jovi
an
To
ur
Ga
nym
ed
e E
llip
tica
l Orb
it
Ga
nym
ed
e C
ircu
lar
Orb
it
High-Res Camera X X X X
VIS-NIR Hyperspectral Imager X X X X
Medium-res Camera X X X X
UV Spectrometer X X X X
Thermal Spectrometer X X X X
Ground-Penetrating Radar X X X
Laser Altimeter X X X
Magnetometer X X X X
Plasma Spectrometer/Energetic Particle Detector X X X X
Radio Science - Gravity X X X
Radio Science - Atmospheres X X X X
JSO science mission is uniquely designed to meet the science goalsand fully utilize the instrumentation
18 October 2007 14JSO TMC & Science Panel Site Visit
Mission TimelineMission Timeline
CruiseIo
TourIcy Moon Tour
Ganymede OrbitBaseline (Ellip + Cir)Descope (Ellip only)
VEEGA, 5 ½ to 7 years
9 - 12 mo 6 mo18 – 21 mo 2 years
JOI GOI
Capture
5 to 5 ½ years
24 hr period60° inclination
Polar 200 km altitude
Flybys4 Io6 Europa7 Ganymede11 Callisto
OpportunitiesLaunch Arrival Atlas (kg) DIVJan 2015 Jul 2021 4964 7287Jun 2015 Jul 2021 4627 6781Sep 2016 Oct 2023 5050 7423Jan 2017 Aug 2022 4888 7196 selectedSep 2018 Oct 2025 4999 7332Mar 2020 Feb 2026 5270 7760May 2021 Mar 2028 5053 7416
18 October 2007 15JSO TMC & Science Panel Site Visit
Interplanetary TrajectoryInterplanetary Trajectory
Date Alt Vinf ET/SCET km km/s
Launch 03-Jan-2017 3.0 Venus 27-Apr-2017 1693 4.8 Earth 14-Jan-2018 3136 7.9 Earth 09-Apr-2020 300 9.6
Jupiter 11-Sep-2022 4.6
• Launch C3 10 km2/s2 over 21 day launch period• Launch on Delta IV-H (Atlas V for descoped option)• 265 m/s DSM (Feb-2019)• Backups in 2018-2021
LaunchEarth-1
Earth-2 Venus
Jupiter
Mercury
Mars
Venus
Earth
Jupiter
18 October 2007 16JSO TMC & Science Panel Site Visit
Example Jovian TourExample Jovian Tour
3 Year Tour:3 Year Tour: 9-12 month Io phase9-12 month Io phase 18-21 mo. outer moon tour18-21 mo. outer moon tour ~ 6 month endgame~ 6 month endgame 24-28 close flybys24-28 close flybys
Tour reduces energy and circularizes orbit prior to GOI
Opportunities Ranges (km) Jupiter 9
23 290,000 – 500,000 500,000-1,000,000
Encounters Callisto Europa Ganymede Io
11 6 7 4
100 – 1940 100 – 600
100 – 2850 100 – 500
Non-Targeted Encounters Callisto Europa Ganymede Io
2 8 7 8
230,000 – 400,000 78,000 – 490,000 24,000 – 410,000
110,000 – 480,000
1
23
4
15
10
20
5
8
7
6
9
30
18 October 2007 17JSO TMC & Science Panel Site Visit
Ganymede Science OrbitsGanymede Science Orbits
•24 hour “Elliptical” Orbit:•Novel 3-body orbit using Jupiter and Ganymede gravity•Long-term stable (10+ years)
•inclination varies from 50º to 60º•near the highest inclination possible for stable orbits
•44 d oscillation between near-circular and highly eccentric•Close approaches are distributed around the body•24 hr period avoids changing shift issues for ops•Representative of larger set of possible orbits
•200 km Circular Orbit:•Low altitude and high inclination•Can be sun-synchronous (with Jupiter perturbation)•Could instead have varying solar phase over mission•Only mildly unstable ( ~0.1 m/s per day of DV to maintain)
18 October 2007 18JSO TMC & Science Panel Site Visit
DV BudgetDV Budget
Baseline [m/s]Baseline [m/s]
(Low Circular Orbit)(Low Circular Orbit)
Descoped [m/s]Descoped [m/s]
(Elliptical Orbit)(Elliptical Orbit)Launch Injection CorrectionLaunch Injection Correction 30 (est.)30 (est.)
Earth BiasingEarth Biasing 50 (est.)50 (est.)
DSMDSM 265 (max)265 (max)
Interplanetary TCMsInterplanetary TCMs 20 (est.)20 (est.)
JOIJOI 660660
PJRPJR 165165
Tour (24+ flybys)Tour (24+ flybys) 200 (with 15% margin)200 (with 15% margin)
Ganymede EndgameGanymede Endgame 200 (with 10% margin)200 (with 10% margin)
Ganymede Orbit InsertionGanymede Orbit Insertion 200 (with 10% margin)200 (with 10% margin)
Orbit Maintenance (elliptical)Orbit Maintenance (elliptical) 25 (est.)25 (est.) 50 (est.)50 (est.)
Plane ChangePlane Change 230230
------CircularizationCircularization 620620
Orbit Maintenance (circular)Orbit Maintenance (circular) 40 (est.)40 (est.)
De-OrbitDe-Orbit ------ 15 (est.)15 (est.)
TotalTotal 27052705 18551855
Jupiter System Observer Jupiter System Observer
January 28, 2008January 28, 2008
Spacecraft & Operations
18 October 2007 20JSO TMC & Science Panel Site Visit
Design Drivers on Flight System Design Drivers on Flight System
Payload SuiteLarge OpticsComprehensive Payload
Mission DesignJovian SystemGanymede Orbit
Higher Data Generation
Fine Pointing
Large ∆V
Configuration
Structures
Downlink
Data Storage
On-board Data Handling
Attitude Control
Radiation Environment
Shielding, Parts upgrade
High Propellant Load
18 October 2007 21JSO TMC & Science Panel Site Visit
Baseline SpacecraftBaseline Spacecraft
• 7262 kg (4612 kg, descoped) wet mass• 228 kg (208 kg, descoped) planning
payload• Eight (seven, descoped) MMRTGs and
two 38 A-hr batteries• Two-axis gimbaled, 2.75 m HGA• Two-way Doppler at both X-/Ka-band
for radio science - gravity investigation• USO for radio science - atmosphere
investigation• 600 kb/s to 70m from 6.5 AU at Ka-
band• 9.6 Gb solid state recorder• Dual-mode propulsion system; 2705
m/s (1855 m/s, descoped)• Reaction wheels for long arcs without
non-gravity disturbances• Single-fault tolerant; redundant
assemblies• Radiation-hardened electronics• 1.8 Mrad radiation design point• 12 year mission life
JSO Spacecraft is a capable robust design that accommodatesthe instrumentation and the mission while taking advantage of the environment
MMRTG (8)
Main Engine
Pressurant Tank
Fuel & Oxidizer Tanks (inside)
ThrusterClusters (8)
LouveredRadiator (2)
Magnetometer
Ground Penetrating Radar
TelecomElectronics
Chassis
HGAMGA (hidden)
18 October 2007 22JSO TMC & Science Panel Site Visit
Baseline vs. Descope DifferencesBaseline vs. Descope Differences
BaselineBaseline DescopeDescope
PayloadPayload 228 kg228 kg
9 instruments9 instruments
208 kg208 kg
Same payload except: Same payload except:
MRC is non-stereo, PS/EPD is MRC is non-stereo, PS/EPD is less TOF spectrometerless TOF spectrometer
∆∆VV 2705 m/s2705 m/s
4775 kg propellant4775 kg propellant
1855 m/s1855 m/s
2627 kg propellant2627 kg propellant
Power SourcePower Source 8 MMRTGs (778 W EOM)8 MMRTGs (778 W EOM) 7 MMRTGs (681 W EOM)7 MMRTGs (681 W EOM)
Mass MarginMass Margin S/C dry mass (CBE): 1959 kgS/C dry mass (CBE): 1959 kg
27% contingency27% contingency
21% system margin*21% system margin*
S/C dry mass (CBE): 1568 kgS/C dry mass (CBE): 1568 kg
27% contingency27% contingency
33% system margin*33% system margin*
Power MarginPower Margin 30% contingency30% contingency
>100 W margin on RTG modes>100 W margin on RTG modes
<20% DoD on Battery modes, plus <20% DoD on Battery modes, plus redundant batteryredundant battery
30% contingency30% contingency
>80 W margin on RTG modes>80 W margin on RTG modes
<40% DoD on Battery modes, plus <40% DoD on Battery modes, plus redundant batteryredundant battery
* Margin = Remaining LV Mass/Spacecraft Dry Mass (CBE+cont)
18 October 2007 23JSO TMC & Science Panel Site Visit
Mass SummaryMass Summary
CBE (kg)Cont. (%)
CBE+Cont. (kg) CBE (kg)
Cont. (%)
CBE+Cont. (kg)
PayloadInstruments 228 36% 310 208 37% 284
Bus
Attitude Control 51 31% 67 51 31% 67Command & Data 49 37% 67 49 37% 67Power (non-MMRTG) 54 30% 70 54 26% 68 MMRTGs 376 5% 395 329 5% 345Propulsion 356 28% 454 204 24% 254Structures & Mechanisms 448 30% 582 315 30% 410Cabling 125 30% 163 99 30% 129Telecom 58 20% 69 58 20% 69Thermal 53 28% 67 48 28% 61
Bus Total 1569 23% 1934 1207 22% 1470Radiation Shielding 162 50% 243 153 50% 230
SpacecraftSpacecraft Dry Mass 1959 27% 2487 1568 27% 1984Propellant & Pressurant 4775 2627Wet Mass 7262 4612
Mass (kg) Mass (kg)
System Margin * 21% 523 33% 663
Spacecraft Dry Mass Allocation 3010 2648
Launch Vehicle Adapter (LV side) 25 25Launch Vehicle Capability Delta IV 4050H-19 7810 Atlas V 551 5300
* Margin = Remaining LV Mass/Spacecraft Dry Mass (CBE+Cont)
Jupiter System Observer2007-07-10
Systems Comparison
Baseline Architecture (kg) Descope Architecture (kg)
18 October 2007 24JSO TMC & Science Panel Site Visit
Dose-Depth Curves (Free Space)Dose-Depth Curves (Free Space)
TID (per Day) vs Jovian Altitude (Rj)
1.E-01
1.E+00
1.E+01
1.E+02
1.E+03
1.E+04
1.E+05
1.E+06
10 100 1000 10000
aluminum spherical shell thickness, mils
rad
(Si)
/da
y
Europa
10 Rj
11Rj
12 Rj
13 Rj
14 Rj
GanymedeEuropa: ~30 krad/day
Ganymede: ~1 krad/day
18 October 2007 25JSO TMC & Science Panel Site Visit
Ganym
ede
Elliptic
al Orb
itGan
ymed
e Circ
ular O
rbit
0.0E+00
2.0E+05
4.0E+05
6.0E+05
8.0E+05
1.0E+06
1.2E+06
1.4E+06
1.6E+06
1.8E+06
2.0E+06
0.00 1.00 2.00 3.00 4.00 5.00 6.00
Years at Jupiter
TID
(10
0 m
il A
l, R
ad S
i)
Flyby (#)
I - Io (4)E - Europa (6)G - Ganymeded (7)C - Callisto (11)
II
I
I
CC
G
CC
EC
E E EGC
EE
CGC C GG CC GG
Radiation TIDRadiation TID
Ganym
ede O
rbit
18 October 2007 26JSO TMC & Science Panel Site Visit
JSO Information FlowJSO Information Flow
Low-rate Instruments(e.g,magnetometer, plasma
spectrometer, etc.)
High-rate Instruments with compression
(e.g, hi-res camera, hyperspectral imager, etc.)
MSAP-based Flight Computer
([2:1] low-rate compression)
9.6 Gb SSR
Telecom/SDST(50 W TWTA, 2.75 m HGA)
Tour Encounters Flybys of Io, Europa, Ganymede, Callisto
Orbits(at Ganymede)
High-data-rate Scienceinstruments(12 to 3500 Mbps)
Low-data-rate Scienceinstruments(< 1 Mbps)
1553B(< 1 Mbps)
LVDS(< 40 Mbps)
LVDS(10 Mbps)
1553B(< 1 Mbps)
DSN Coverage(70 m, 8-16
hrs/day)Ka-band Downlink
(>600 kbps)
15% packetization added to downlink
Flight System
10% retransmission rate assumed
80% DSN Window Availability
500 bps engineering data generated by FS
Driving Scenarios
18 October 2007 27JSO TMC & Science Panel Site Visit
DSN CoverageDSN Coverage
Phase Sub-phase Duration DSN Coverage-hours/day Sub-net Activity SummaryLaunch and Early Operations
1 month Continuous
8 twice a week, except: 1) Continuous +/- one
week @ Venus and Earth gravity assists
2) Continuous for two days @ tracking data cutoff for TCMs
Jupiter Approach 2 months Continuous 34m Optical navigation, Jupiter imaging
8 during cruise Continuous fields and particles,
24 during encounter day Mapping activities for targetand within +/-2 days satellites,
GPR and altimetry whenIo Sub-tour altitude <2000 kmEGC Sub-tour Io monitoring,
Continuous in last month Jupiter atmospheric monitoring Close satellite flybys for gravity
assistsContinuous for 1st month 70 m equivalent Fields and particles science - 16 over next 2 months 24/7
High-resolution global mappingof Ganymede, selected targets
Continuous for 1st month Fields and particles science -
16 over next 2 months 24/78 over last 9 months GPR, Altimetry, Gravity map,
Mag mapSelected high-res targets
Ganymede Science
Jovian Tour
prior to GOI
around perijove
6 monthsGanymede Approach
34 m for X & Ka uplink/downlink for radio science
8 over last 9 months
1 yearElliptical Orbit
8/day Ka for 1st month
1 yearCircular Orbit
Interplanetary
23 months
Up to 83 months
Cruise
Flight system characterization, calibrations, maintenance, housekeeping, and cruise science
JOI and Capture Orbit 7 months 70m equivalent @ encounters
34m
34m
18 October 2007 28JSO TMC & Science Panel Site Visit
Capabilities and AssumptionsCapabilities and Assumptions
Resource constraint: Data returnResource constraint: Data return Downlink Rate: 600 kbps (worst case)Downlink Rate: 600 kbps (worst case)
Function of: HGA, TWTA Power, 70 m DSN antenna or equivalentFunction of: HGA, TWTA Power, 70 m DSN antenna or equivalent Data Storage: 9.6 GbitsData Storage: 9.6 Gbits Encounter Data Returned: 17.6 Gb per encounterEncounter Data Returned: 17.6 Gb per encounter
Function of: Function of: data storagedata storage, duration, downlink, overhead, duration, downlink, overhead Ganymede Data Returned: 700 to 2100 Mb/orbitGanymede Data Returned: 700 to 2100 Mb/orbit
Function of: orbit period, Function of: orbit period, downlinkdownlink, overhead, DSN coverage (1-3 passes/day), overhead, DSN coverage (1-3 passes/day) Scenario AssumptionsScenario Assumptions
Encounter modes: 6 hrs centered at closest approachEncounter modes: 6 hrs centered at closest approach Ganymede orbits: 24 hr “elliptical” orbits, 2.6 hr circular orbitsGanymede orbits: 24 hr “elliptical” orbits, 2.6 hr circular orbits DSN: DSN:
Approach and Tour: 1 pass/dayApproach and Tour: 1 pass/day Encounter: 3 passes/day during encounter dayEncounter: 3 passes/day during encounter day Ganymede orbit: 3 passes/day for initial 30 days, 2 passes/day for 2 months, and 1 Ganymede orbit: 3 passes/day for initial 30 days, 2 passes/day for 2 months, and 1
pass/day thereafterpass/day thereafter
18 October 2007 29JSO TMC & Science Panel Site Visit
Instrument CapabilitiesInstrument Capabilities
Baseline ArchitectureNative Rate (Mbps)
Data Reduction factor at Instrument
Rate to C&DH (Mbps)
Data Volume per set (Mbits) **
High-res camera
126 3 40 12.6
VIS-NIR hyperspectral imager
3500 89 39 38
UV spectrometer12 100 0.12 17
Thermal spectrometer
32 3 11 24.6
Medium-res stereo camera
25 3 8 25.2/12.6
Laser altimeter0.012 1 0.012 10
Ground-penetrating radar
30 100 0.30 240
Magnetometer 0.004 1 0.004 -
Plasma spectrometer/Energetic particle detector
0.002 1 0.002 -
Radio science -
Descoped Difference
18 October 2007 30JSO TMC & Science Panel Site Visit
Notional Encounter ScenarioNotional Encounter Scenario
Altimeter, Radar (± 5 min)
<100 m res HiRes<500 m res VNIR
6 hr encounter mode based on battery sizing 6 hr encounter mode based on battery sizing Strategy:Strategy:
Start with empty SSR and fully charged batteryStart with empty SSR and fully charged batteryTurn on fields and particle instruments (on 100% of the time)Turn on fields and particle instruments (on 100% of the time)Altimeter and Radar can only measure near closest approach (800 sec)Altimeter and Radar can only measure near closest approach (800 sec)Turn on remaining remote sensing instruments to fill data capabilityTurn on remaining remote sensing instruments to fill data capability
Balance of regional-scale and hi-res observationsBalance of regional-scale and hi-res observationsGlobal color and spectral coverage probably obtained 2 to 5 days out on Global color and spectral coverage probably obtained 2 to 5 days out on either side of encountereither side of encounterBest resolution areas for global coverage will be restricted by encounter Best resolution areas for global coverage will be restricted by encounter geometrygeometry
<50 m res HiRes<250 m res VNIR
<10 m res HiRes
-120 min -60 min -10 min Closest Approach
18 October 2007 31JSO TMC & Science Panel Site Visit
Notional “Elliptical” Orbit ScenarioNotional “Elliptical” Orbit Scenario
6 hrAltimeter, radar and gravity mapping40 cm res @200km
4 hrGlobal mapping40 m resolution
2 hrJupiter system monitoring
2 hrJupiter system monitoring 5 hr
SSR Playback
5 hrSSR Playback
Most demanding scenario24 hr DSN coverage
Realtime downlinkRea
ltim
e d o
wnl
i nk
18 October 2007 32JSO TMC & Science Panel Site Visit
Systems SummarySystems Summary Highlights of JSO scenarios:Highlights of JSO scenarios:
Continuous measurements of magnetometer, PS/EPD, radio scienceContinuous measurements of magnetometer, PS/EPD, radio science Encounter: ~8 TbitsEncounter: ~8 Tbits
For remote sensing instrumentsFor remote sensing instruments >600 data sets of Io>600 data sets of Io ~1000 data sets of Europa~1000 data sets of Europa >1100 data sets of Ganymede>1100 data sets of Ganymede >1800 data sets of Callisto>1800 data sets of Callisto
Limited measurements at each closest approach for LA, GPRLimited measurements at each closest approach for LA, GPR ““Elliptical” orbit: ~5.1 Tbits Elliptical” orbit: ~5.1 Tbits
Monochrome 40 m resolution map ~ in first monthMonochrome 40 m resolution map ~ in first month Cooperative global map ~ 80 orbitsCooperative global map ~ 80 orbits
Includes stereo camera return, full spectral resolution for UV and IR, but Includes stereo camera return, full spectral resolution for UV and IR, but significant wavelength reduction for VNIR significant wavelength reduction for VNIR
Circular orbit: ~3.1 TbitsCircular orbit: ~3.1 Tbits >14,000 data sets on each of the remote sensing instruments>14,000 data sets on each of the remote sensing instruments >37,000 data sets on LA>37,000 data sets on LA >3400 data sets on GPR>3400 data sets on GPR
Flight System design shows a proof of conceptFlight System design shows a proof of concept Future trade studies to provide optimization of design Future trade studies to provide optimization of design
Jupiter System Observer Jupiter System Observer
January 28, 2008January 28, 2008
Questions?