Jupiter System Observer Mission Implementation Polar Gateways Conference January 28, 2008.

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


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°


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°



Descoped

Baseline


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


Payload for Planning Purposes


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


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


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


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


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)



Mission Design


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


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


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


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


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)


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



Spacecraft & Operations


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


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)


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


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


>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)


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)


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


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


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


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


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


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


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


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


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



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Jupiter System Observer Mission Implementation Polar Gateways Conference January 28, 2008.

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