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Europa Mission Concept Study UpdateD. Senske

Jet Propulsion Laboratory/CaltechPresentation to Planetary Science Subcommittee

10/02/12

110/02/2012Copyright 2012 California Institute of Technology. Government sponsorship acknowledged.

Pre-Decisional — For Planning and Discussion Purposes Only



Init ial concepts, presentedto OPAG in May of 2012





Background

3

• The Jupiter Europa Orbiter (JEO) mission concept wasdeemed to be of extremely high science value, butunaffordable, by the NRC Decadal Survey, which requested adescoped option

• A one year study developed mission options (Orbiter, Clipper

(multiple flyby), and Lander) that retain high science value atsignificantly reduced cost

Europa LanderEuropa Orbiter

The Europa Clipper(Multiple-Flyby in Jupiter Orbit)





An 18 Member Europa ScienceDefinition Team

• Will Brinckerhoff GSFC Astrobiology• Kevin Hand JPL Astrobiology• Tori Hoehler Ames Astrobiology• Mike Mellon SWRI Ice Physics / Geology• Everett Shock ASU Geochemistry

Continued members from JEO SDT:• Bruce Bills JPL Geophysics• Diana Blaney JPL Composition• Don Blankenship Univ. Texas Ice shell• Melissa McGrath MSFC Atmosphere• Jeff Moore Ames Geology• Robert Pappalardo JPL Chair / Study Scientist• Louise Prockter APL Deputy / Geology• Dave Senske JPL Deputy / Geology

New members added to Europa SDT:• Fran Bagenal Univ. Colorado Space Physics• Amy Barr Brown Univ. Geophysics• Jack Connerney GSFC Magnetometry• Bill Kurth Univ. Iowa Plasma• David Smith MIT Geophysics

Additional members added during lander study phase:

10/02/2012 4This document has been reviewed and determined not to contain export controlled technical data.




Science Goal, Habitability Themes,and Objectives

• Goal: Explore Europa to investigate its habitability

• Habitability Themes:

– Water: Solvent to facilitate chemical reactions

– Chemistry: Constituents to build organic molecules

– Energy: Chemical disequilibrium for metabolism

• Objectives:

– Ocean: Existence, extent, and salinity

– Ice Shell: Existence and nature of water within orbeneath, and nature of surface-ice-ocean exchange

– Composition: Distribution and chemistry of keycompounds and the links to ocean composition

– Geology: Characteristics and formation of surfacefeatures, including sites of recent or current activity

water

chemistry energy

habitability





Science:

Payload:

Operations Concept:

- 30 days in 100 km near polar orbit aboutEuropa

- Detailed globally mapping, gravity andmagnetic field measurements

- Simple repetitive science operations

Technical Margins42% 39% 71%Mass Power Data

Cost: $1.7B$FY15, Phases A-E Excl LV

Original Orbiter in a NutshellMay 2012

Langmuir Probe(LP) (x2)

Laser Altimeter(LA)

MappingCamera (MC)

Magnetometer(Mag)


Pre-Decisional — For Planning and Discussion Purposes Only6

OrbiterMay 2012

Ocean

Ice Shell X

Composition X

Geology

Objective

Orbiter

Baseline

LA

MC

Mag

LP

Baseline -

Floor

Instrument



Original Clipper in a NutshellMay 2012

Science:

Payload:

Operations Concept:

- 32 low altitude flybys of Europa from Jupiterorbit over 2.3 years

- Detailed investigation of globally distributedregions of Europa



Clipper

Baseline

IPRSWIRS

TI

Baseline INMS

Floor

Instrument


Ice PenetratingRadar

TopographicalImagerIon & Neutral Mass

Spectrometer

Shortwave InfraredSpectrometer



ClipperMay 2012

Ocean X

Ice Shell

Composition

Geology

Objective



Science:

Payload:

Operations Concept:

- 30 days science investigation on the surface ofEuropa

- Surface and subsurface composition andmorphology measurements

- Autonomous precision landing technologyrequired to mitigate unknown surface conditions

Technical Margins

28% 38% 41%Mass Power Data

Cost: $2.8B+$FY15, Phases A-E Excl LV

The Lander in a NutshellMay 2012

Magnetometer(Mag)

Site Imager(SIS)

Microscopic Imager(MI)

Raman Spectrometer(RS)

Mass Spectrometer(MS)

Multi-BandSeismometer(MBS) (x6)

Arm w/Core Drill

MS

MagMBS

SIS

RS

MI

Instrument

Floor

Baseline

Lander



Ocean

Ice Shell (Locally)

Composition (Locally)

Geology (Locally)

Recon

Objective Lander



How the Cost Was Reduced

Concept modificationsused to reduce cost:• Mission design reduces

radiation levels

• Nested shielding design

eliminated need for mega-rad parts

• Reduced number ofinstruments from 12 to 4

• Repetitive and simplescience operations

• Modularity increasesschedule and test flexibilityand enables smoothing offunding profile

e-





Mission Option ComparisonMay 2012

10/02/2012 10

Option Cost(FY15, Phases

A-E Excl LV)

Risk Science

Europa Orbiter $1.7B Low Very GoodEuropa Clipper $1.98B Low Excellent

Europa Lander $2.8B High Excellent

This document has been reviewed and determined not to contain export controlled technical data.Pre-Decisional — For Planning and Discussion Purposes Only



In the Words of the Reviewers

• Independent technical reviews chaired by Scott Hubbard

Clipper Mission “could be conducted within the cost constraints provided

and have substantial margins”

• Independent cost reviews by the Aerospace Corporation

“Complexity analysis suggests Aerospace & Project cost estimates and

schedule are reasonable based on historical data base.”

• OPAG finding

“All 3 Europa mission options are highly scientifically meritorious and

responsive to the Planetary Science Decadal Survey. ... The strong

majority view of the OPAG community is that the Multiple-Flyby [Clipper]

option … offers the greatest science return per dollar, greatest publicengagement, and greatest flow through to future Europa exploration.”





Since May:Summer Study





Charge from NASAfor Summer Study

13

Enhanced Clipper ScienceExamine the ability to address theOcean science objectives with theClipper mission option andunderstand implications for themission design and number of flybys

while remaining cost neutral ($2B,FY15$, Phase A-E excl LV)

Enhanced Orbiter ScienceExamine the ability to address the IceShell, Composition and/or additionalGeology science objectives with theOrbiter mission option and understandimplications for the mission design and

spacecraft architecture. Remaining withinthe Clipper cost ($2B, $FY15, Phase A-Eexcl LV)

Landing Site ReconnaissanceExamination of the Landed Missionoption in May identified surface

condition uncertainty as a risk.Examine capabilities that can beadded to the current mission tomitigate concern for a future landedmission.

Engineering Trades

• Investigation of solar power options

• Assess the enabling benefits of theSpace Launch System

• Examine the accommodation ofpotential nanosats and the sciencethey could achieve





Programmatic need for feedforward Reconnaissance Data sets

• Reconnaissance data is necessary from

both science and engineering perspectives: – Science reconnaissance for landing site

selection(enabled by the current Clipper model

payload)

• Is the landing site scientifically compelling inaddressing the goal of exploring Europa to

investigate its habitability

– Engineering reconnaissance for landing safety

• Is a safe landing site (within the lander’s designmargins) accessible to a spacecraft?

• Assess 15 sites to determine conditions and findone that is safe

• Reconnaissance capability would includekey elements to complete the data setneeds− High resolution imaging at ~0.5 m/pixel− Thermal imaging to provide knowledge of the

properties of the surface 14

Galileo Europa 6 m/pixel

Highest Resolution Europaimage currently available





Enhanced Europa Orbiter Science A 109-day Mission in Europa Orbit





Orbiter Science

• Ocean: Characterize the extent of

the ocean and its relation to thedeeper interior

• Geology: Understand theformation of surface features,including sites of recent or current

activity to understand regional andglobal evolution

Science Enhancement:

• Ice Shell : Characterize the iceshell and any subsurface water,

including their heterogeneity, andthe nature of surface-ice-oceanexchange.

Focus on providing a comprehensive understanding of the ocean and its

tidal interaction with the icy crust



O bit S i T bilit





Orbiter Science TraceabilityEnhanced with Ice Shell Science

Goal Objective Investigation Model Planning PayloadTheme

W C E

E x p l o r e E

u r o p a t o i n v e s t i g a t e i t s h a b i t a b i l i t y

O c e a n

Characterize the extent of the

ocean and its relation to the

deeper interior.

Determine the amplitude and phase of

gravitational tides.

Radio subsystem,

Laser altimeter

Determine Europa's magnetic induction

response.

Magnetometer,

Langmuir probe


topographic tides.

Laser altimeter,

Radio subsystem

Determine Europa's rotation state. Laser altimeter,

Mapping camera

Investigate the deeper interior. Radio subsystem,

Laser altimeter, Magnetometer,

Langmuir probe

I c e S h e l l

Characterize the ice shell

and any subsurface water,

including their

heterogeneity, and the nature

of surface-ice-ocean

exchange.

Characterize the distribution of any

shallow subsurface water and the

structure of the icy shell

Ice Penetrating Radar

Mapping camera,

Laser altimeter

Search for an ice-ocean interface. Ice Penetrating Radar

Mapping camera,

Laser altimeter

Correlate surface features and

subsurface structure to investigate

processes governing material exchangeamong the surface, ice shell, and ocean.


Mapping camera,

Laser altimeter

Characterize regional and global heat

flow variations.


G e o l o g y

Understand the formation of

surface features, including

sites of recent or current

activity to understand regional

and global evolution.

Determine the distribution, formation, and

three-dimensional characteristics of

magmatic, tectonic, and impact landforms.

Mapping camera,

Laser altimeter

Themes: W= Water, C = Chemistry, E = Energy

17Enhancement





Orbiter key science investigations andaugmented model planning payload

ScienceObjective

Key Science Investigations ModelInstrument

SimilarInstrument

Ocean Time-varying gravity field through Doppler tracking, todetect ocean and determine interior structure.

Radio Sub-system(RS)

Time-varying tidal amplitude, to detect ocean anddetermine interior structure.

Laser Altimeter(LA)

NEAR NLR

Magnetic induction response, to derive ocean thicknessand salinity.

Magnetometer(MAG)

Galileo MAG

Local plasma and electric field, to support magneticinduction experiment.

Langmuir Probe(LP)

Rosetta LAP

Ice Shell Sounding o f dielectric horizons at two frequencies, tosearch for shallow water and the ocean.

Ice-PenetratingRadar (IPR)

MRO SHARAD

Geology Uniform global mapping, for landform global distribution andstratigraphy.

Mapping Camera(MC)

MPL/MSL MARDI

18

Note: Model instrument baselineand floor are equivalent

Enhancement



Enhanced Orbiter w/ Recon

19

Science:

Payload:


Ice PenetratingRadar (IPR)

Magnetometer(Mag)


Recon Camera(Recon)Thermal Imager(Thermal)

Laser Altimeter(LA)


Orbiter

Enh w Recon

LAMC

Mag

LP

Baseline IPR

Recon

Thermal

Instrument

Floor

Operations Concept:

- 109 days in 100 km near polar orbit about Europa

- Detailed global mapping, gravity and magnetic fieldmeasurements


- Addition of IPR used for Ice Shell science

Mapping Camera(MC)



Orbiter

Enhanced w Recon

Ocean

Ice Shell

Composition X

Geology

Recon

Objective



Enhanced Europa Clipper Mission A Multiple-Flyby Europa Mission in Jupiter Orbit

2010/02/2012

Copyright 2012 California Institute of Technology. Government sponsorship acknowledged.Pre-Decisional — For Planning and Discussion Purposes Only



Clipper Science from May Report

21

• Ice Shell: Characterize the ice shelland any subsurface water, includingtheir heterogeneity, and the nature ofsurface-ice-ocean exchange

• Composition: Understand thehabitability of Europa's oceanthrough composition andchemistry

• Geology: Understand the formationof surface features, including sites ofrecent or current activity, andcharacterize high science interestlocalities mosaic by “Orion”





22

Enhanced Clipper Science

- Determine Europa's magneticinduction response to estimate iceshell thickness, and ocean salinityand thickness

- Determine the amplitudeand phase of gravitationaltides

Providing an understanding of

the properties of the ocean

• Ocean: Characterize the properties of the ocean

• Geology: Expand observation strategy to achieve global& regional along with the local coverage

From: Moore andSchubert [2000]

From Khurana 2002

Gravitational TidesMagnetic Induction

Seawater



Cli S i T bilit



Copyright 2012 California Institute of Technology. Government sponsorship acknowledged.Pre-Decisional — For Planning and Discussion Purposes Only

Clipper Science TraceabilityEnhanced with Ocean & Geology Science

Goal Objective InvestigationModel Planning

Payload

Theme

W C E

E x p l o r e E u r o p a t o i n v e s t i g a t e

i t s h a b i t a b i l i t y

O c e a n & I c

e S h e l l

Characterize the ice

shell and any subsurface

water, including their

heterogeneity, and the

nature of surface-ice-ocean

exchange and the

properties of the ocean

Characterize the distribution of any shallow sub-surface water and the structure of the icy shell.

Ice-Penetrating Radar,Topo. Imager

Determine Europa's magnetic induction response

to estimate ocean salinity and thickness

Mag. & Langmuir

Probe

Search for an ice-ocean interface. Ice-Penetrating Radar,

Topo. Imager

Correlate surface features and subsurface struc-ture

to investigate processes governing material exchange

among the surface, ice shell, and ocean.

Ice-Penetrating Radar,

IR spectrometer,

Topo. imager


gravitational tides.

Radio Subsystem

Characterize regional and global heat flow variations. Ice-Penetrating Radar

C o

m p o s i t i o n

Understand the habitability

of Europa's ocean through

composition and chemistry.

Characterize the composition and chemistry of the

Europa ocean as expressed on the surface and in the

atmosphere.

IR spectrometer,

NMS

Determine the role of Jupiter's radiation environment

in processing materials on Europa.

IR spectrometer,

NMS

Characterize the chemical and compositional pathways in Europa's ocean.

IR spectrometer, NMS

G e o l o g y

Understand the formation

of surface features,

including sites of recent or

current activity, and

characterize high science

interest localities.

Determine sites of most recent geological activity,

and characterize high science interest localities.

Topo. Imager

Determine the formation and three-dimensional

characteristics of magmatic, tectonic, and impact

landforms.

Topo. Imager

Themes: W= Water, C = Chemistry, E = Energy 23Enhancement10/02/2012





Clipper key science investigations andaugmented model planning payload

ScienceObjective

Key Science Investigations ModelInstrument

SimilarInstrument

Ocean & IceShell

Time-varying gravity field through Doppler tracking, todetect ocean and determine interior structure.

Radio Sub-system(RS); IndependentGimbaled Antenna

Magnetic induc tion response, to derive ocean thicknessand salinity.

Magnetometer(MAG)

Galileo MAG

Local plasma and electric field, to support magnetic

induction experiment.

Langmuir Probe

(LP)Rosetta LAP

Sounding of dielectric horizons at two frequencies, to searchfor shallow water and the ocean.

Ice-PenetratingRadar (IPR)

MRO SHARAD

Composition Visible and near-infrared spectroscopy, for global mappingand high-resolution scans, to derive surface composition.

ShortWave IRSpectrometer(SWIRS)

LRO M3

Elemental, isotopic, and molecular composition of theatmosphere and ionosphere, during close flybys.

Neutral MassSpectrometer(NMS) Nazomi NMS

Geology Medium to High resolution stereo imagery, to characterizegeological landforms, and to remove clutter noise from IPRdata.

TopographicalImager (TI)

New Horizons

Ralph/MVIC

Floor modelinstrument

Baseline modelinstrument Enhancement

C S O C



Clipper Science Ops ConceptSimple and Repetit ive



1. Magnetometer and Langmuir Probes

− Continuous measurements

2. ShortWave InfraRed Spectrometer(SWIRS)− Global low resolution scan below 66,000 km

altitude

− Targeted high resolution scan below 2,000 kmaltitude

− Passive below 1,000 km altitude

3. Gravity Science

−Measurements below 28,000 km altitude

4. Topographical Imager (TI)

− Pushbroom stereo imaging below 1,000 kmaltitude

− Lower res. pushbroom imaging between 4,000and 1,000 km altitude

5. Ice Penetrating Radar (IPR)

−

Surface scans below 1,000 km altitude6. Mass Spectrometer (NMS)

− In situ scan below 1,000 km altitude

Recon Camera

− High resolution imaging below 105 km altitude

Thermal Imager− Pushbroom thermal imaging below 60,000 km



Enhanced Clipper w/ Recon

Science:

Payload:




(SWIRS)

Ice PenetratingRadar(IPR) Topographical

Imager (TI)


Magnetometer(Mag)

Clipper

Enh w Recon

IPR

SWIRS

TI

NMS

MAG

LP

GS

Recon

Thermal

Baseline

Instrument

Floor

Operations Concept:




- Addition of high resolution reconnaissancecamera and thermal imager

Gravity Science Antenna (GS)

Neutral MassSpectrometer (NMS)

Langmuir Probe (LP)(x2)



Clipper

Enhanced w Recon

Ocean

Ice Shell

Composition

Geology

Recon

Objective



Power Systems

• In addition to ASRG, study team continues to

investigate alternate power sources – Currently examining solar power technology

options for Clipper and Orbiter

• Clipper preliminary results are encouraging

– Array size similar to Juno (~60 m2) even

accounting for radiation & Low Intensity LowTemperature (LILT) derating

– Requires large battery capacity for eclipse/flybys

• Engineering issues to be investigated and addressed

– Cold survival temperature of array• Juno qualification difference

– Radiation 2X Juno test data• Radiation testing needs

– Flexible body effects• Pointing implications





Enhanced Solar Clipper w/ Recon

Science:

Payload:




(SWIRS)

Ice PenetratingRadar(IPR)

TopographicalImager (TI)


Magnetometer(Mag)

Clipper

Enh w Recon

IPR

SWIRS

TI

NMS

MAG

LP

GS

Recon

Thermal

Baseline

Instrument

Floor

Neutral MassSpectrometer (NMS)


Operations Concept:




- Addition of high resolution reconnaissancecamera and thermal imager

Gravity Science

Antenna (GS)



Clipper

Enhanced w Recon

Ocean

Ice Shell

Composition

Geology

Recon

Objective



SDT Conclusion

• The SDT reaffirms that the mission concepts described in the May 2012Report continue to provide robust means to accomplish Europa sciencewith the Clipper ranking above the Orbiter in its ability to achieve highpriority Europa science

The enhanced Clipper concept is excellent in meeting the goal ofexploring Europa to investigate its habitabili ty

– This concept will provide significant advancement in key iceshell, composition, geology, and ocean science

– The Clipper is deemed of higher ranking relative to the refined

Orbiter concept





Conclusion

• OPAG finding (May 2012)

“All 3 Europa mission options are highly scientifically meritorious andresponsive to the Planetary Science Decadal Survey. ... The strong

majority view of the OPAG community is that the Multiple-Flyby [Clipper]

option … offers the greatest science return per dollar, greatest public

engagement, and greatest flow through to future Europa exploration

• Europa SDT Meeting (Aug 2012)“The SDT is of the opinion that the rebalanced Clipper concept is excellent

in meeting the goal of exploring Europa to investigate its habitability”

• Study team has addressed NASA’s request to investigaterebalancing the May 2012 mission options

– Will deliver reports by end of December

• Europa technical concept is mature and implementablewithin the identified cost target





Backup Material



VEEGA I t l t T j t



VEEGA Interplanetary TrajectoryRobust with Annual Launch Opportunities

VGA(6/28/20)

EGA-2(7/26/23)

EGA-1(4/24/21)

Jupiter ’sOrbit

JOI(12/21/25)

Launch(02/29/20)

Interplanetary Phase: VEEGA Trajectory (5.8 years)

Annual Launch Oppor tuni ties

Launch Date Flyby

Path

TOF to JOI

(yrs.)

C3

(km2/s2)

At las V 551

Capability (kg)

21 Jul 2018 VVEE 6.32 15.0 4585

23 Mar 2019 EVEE 6.91 10.5 5011

29 Feb 2020 VEE 5.8 12.8 4794

27 May 2021 VEE 6.87 14.5 454121 Nov 2021 VEE 6.37 15.0 4494

15 May 2022 EVEE 7.22 10.2 4935

23 May 2023 VEE 6.18 16.4 4339

03 Sep 2024 VEE 6.71 13.8 4562

Nominal IP Trajectory

Event Date Flyby Alt . (km)

Launch 29 Feb 2020 -

Venus 28 Jun 2020 20,266

Earth -1 24 Apr 2021 3274

Earth -2 26 Jul 2023 1028

Ganymede-0 20 Dec 2025 500

JOI 21 Dec 2025 12.8 RJ

Nominal

High performanceinterplanetarytrajectory withannual launchopportunities

10/02/2012 32Copyright 2012 California Institute of Technology. Government sponsorship acknowledged.


Programmatic need for feed forward



Programmatic need for feed forwardreconnaissance data sets

• The SDT endorses the inclusion of a programmaticreconnaissance capability on the next Europa-focused orbiter orflyby mission, in preparation for a future Europa surface mission

• The notional Clipper payload as conceived would provided animportant basis for selecting a scientifically compelling landing

site• The SDT recognizes that any reconnaissance capability

involves a cooperative effort between science and engineeringwith significant input from the science community to besuccessful



Programmatic need for feed



Programmatic need for feedforward Reconnaissance Data sets

34

• The Clipper notional remote sensing payload (SWIRS, TI, IPR)already provides a primary basis for selecting a scientificallycompelling landing site

• Enhanced Clipper reconnaissance capability would includekey elements to complete the reconnaissance data set needs

−High resolution imaging at ~0.5 m/pixel

− Thermal imaging to provide knowledge of the properties of thesurface

• Reconnaissance capabilities would also serve to reinforce the

landing site scientific rationale





35

Engineering Investigations



1) Solar Power System2) Space Launch System3) Smallsats



Space Launch System (SLS)

• Examining the benefits of using SLS – Greatly increases mass margins

• >6,000 kg lift mass at a C3 of 73

– Reduce trip time via more efficient

interplanetary trajectory• 6 years to 2.8 years

– Standard Delta IV fairing and payloadinterface planned in Block 1 design

– Actively working with MSFC on a costneutral model

36

B l o

c k

1





Nanosats

Potential Nanosat Science

- Ocean conductance measurement- Radio Science

- High resolution descent imagery

- Magnetometry

- Radiation measurements

Nanosat Development

- University competition, selected on thebasis of science, risk, and cost

- 6-12 “Cubesats” at max. 15kg each

- Deployed during flyby

- Project could provide rad-hard parts asrequired

- Only possible under SLS LV option andoutside of current project costs

Forward Plan

- Investigate feasibility andimplementation options

Copyright 2012 California Institute of Technology Government sponsorship acknowledged

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