Europa Scout Lander 2020

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Europa Scout Lander 2020

• Concept Design Review
• Wednesday, February 18, 2015

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Proposal Overview

• I. Introduction
• II. Team Roles and Responsibilities
• III. Science Theme and Objectives
• IV. Science Baseline and Floor
• V. Instrumentation
• VI. Traceability Matrix
• VII. Mission Architecture
• A. Timeline and Key Events
• B. Launch Vehicle
• C. Cruise Stage
• D. Landers
• VIII. Trade Studies
• IX. Work to be Completed

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Introduction

• The following Pre-Phase A Mission System
  Concept for this mission is presented in response
  to the National Space Administration Europa Scout
  2020 Announcement of Opportunity released on 5
  Jan 2015
• The proposed mission launch date is January 2021
  with the proposed surface science completed by
  November 2028
• Level 1 Objectives
• Extend the science missions of Galileo and
  Jupiter
• Utilize a platform that allows in-situ analysis
  of the Europa crustal ice
• Employ a mission architecture that is redundant,
  and assumes a low level of overall risk
• Maximize potential scientific return

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Team Roles and Responsibilities
PI Wes Patterson Brown University
Project Manager Bob Thompson
Project Systems Engineer Scott Francis
Flight Systems Randy Olsen
Payload Systems Michael Parsons
Mission Systems Robbie Coffman
Disciplinary Specialists
CAD Michael Parsons Scott Francis
Trajectories Performance Scott Francis Bob
Thompson
Propulsion Power Robbie Coffman Randy Olsen
Masses Structures Randy Olsen Robbie Coffman
Cost Estimation Bob Thompson Michael Parsons
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Science Theme and Objectives

• Theme Geochemistry
• Survey the dynamics of the icy crust of Europa
• Identify potential energy and nutrient resources
• Assess the suitability of the crustal ice to
  supporting life
• Characterize recent sub-surface environmental
  conditions

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Science Baseline and Floor

• Science Baseline
• Survey of three sites
• Site context imagery
• Microscopic imagery at each site
• Spectroscopic and chemical analysis of three
  samples at each site
• Science Floor
• One site survey
• Site context imagery
• Spectroscopic and chemical analysis of two
  samples
• Currently working with PI to establish baseline
  and floor resolution requirements

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Instrumentation

• Panoramic Camera
• - A high resolution stereo color panoramic
  imager for imaging of local environment
• - Location Stereo pair mounted on mast
• Gas Chromatograph / Mass Spectrometer
• - Determines presence and characterization of
  pre-biotic and biotic compounds
• - Location Warmed electronics bay
• Geophone
• - Passive seismic sensor for subsurface
  structure determination
• - Location Placed in drilled hole near
  spacecraft. Data transmitted via attached cable
• Microscopic Imager
• - Fine-scale imager combining optical
  microscope, X-ray fluorescence and X-ray
  diffraction
• - Location Deployed Instrument Array

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Instrumentation (Cont.)

• Aqueous Chemistry Laboratory
• - Suite of chemical sensors for detecting
  chemical properties such as pH, conductivity
• - Location Warmed electronics bay
• Visible/Near-IR Point Spectrometer
• - Remote molecular / elemental analysis of
  surface
• - Location Mirrors on camera mast send light to
  instrument in warmed electronics bay
• Environmental Sensors
• - Suite of sensors for measurement of ambient
  temperature, the rate of delivery of direct solar
  radiation per unit of horizontal surface ambient
  surface radiation
• - Location Sensors on outside of spacecraft bus
  

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Instrumentation (Cont.)

• Raman Spectrometer
• - In-situ molecular analysis of surface
• - Location Deployed Instrument Array
• ? Ultrasonic Corer
• - Piezoelectric corer capable of drilling and
  collecting surface samples to depth of 20 cm
• - Location Deployed Instrument Array

Credit NASA JPL
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Science Traceability Matrix
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Mission Summary

• Launch Vehicle
• Delta IV Heavy
• Atlas V Heavy
• Trajectory
• Chemical propulsion with Triple Venus flyby, with
  an earth escape energy, C3, of 16.5 km2/s2
• Cruise Stage
• Provides navigation and communication during
  interplanetary cruise
• Landers
• Three Landers
• Apollo-style landing scenario
• Full suite of geochemical analysis instruments
• Ultrasonic corer for sample extraction
• RTG for power
• Landing sites at locations of newly surfaced
  material (TBD)
• Two lower risk landing sites (i.e. Linea
  terrain)
• One higher risk landing site (i.e. Chaos
  terrain)

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Landing Sites
Linea Terrain
Chaos Terrain
Credit NASA JPL
Credit NASA JPL

• Landing Sites will be based on a combination of
  scientific interest and landing safety, and will
  be selected by a workshop of the scientific
  community and engineers familiar with the landing
  system.

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Timeline Key Events

• Europa Scout 2020 AO Released 5 Jan 2015
• Pre-Phase A Mission System Concept Design
  Review 18 February 2015
• Pre-Phase A Mission System Concept Completed
  21 April 2015
• Proposal Selection Announced September 2015
• Phase A concept Study Report Completed March
  2016
• Confirmation of Investigation for Flight June
  2016
• Project Preliminary Design Review June 2017
• Launch January 2021
• First Venus Fly-by June 2021
• Second Venus Fly-by September 2022
• Third Venus Fly-By March 2025
• Enter Jupiter Orbit September 2027
• Enter Europa Orbit September 2028
• Landers Descend to Surface October 2028
• Surface Science Completed November 2028

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Launch Vehicle Selection

• The capabilities of a wide range of the
  expendable launch vehicles (ELVs) provided by NSA
  were investigated
• The heavy launch vehicle class was chosen because
  of its capability of launching the desired
  boosted mass of approximately 6770 kg with a C3
  of 16.5 km2/s2
• Within this category, the Boeing Delta IV H
  launch vehicle best matches the required
  performance
• The Lockheed Martin Atlas V H launch vehicle has
  similar capabilities and is also available, thus
  providing dual compatibility

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Cruise Stage

• Communications Ka-band (32 GHz)
• Use of one or more lander antennas
• Receivers Deep Space Network 34 m dishes
• Attitude determination Star trackers, Sun
  sensors, Miniature IMU(s)
• Attitude control Four reaction wheels, redundant
  thrusters

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Lander Mass and Power

• Estimated total mass for one lander 490 kg
• Instruments 20 kg
• Total instrument power required 33 W
• Each lander will have one advanced RTG to power
  its instruments and subsystems
• RTG mass 40 kg
• Average power supplied over duration of mission
  110 W

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Lander Visualization
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Lander Communications

• Parabolic high-gain antenna
• Frequency 32 GHz (Ka-band, DSN supported)
• Diameter 30 cm
• Mass lt 0.5 kg
• Power 6 W
• Data transmission rate 1 kbps
• Receivers DSN 70 m dishes
• Redundant electronics and smaller low-gain
  Ka-band antenna for backup

Credit NASA JPL
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Other Lander Considerations

• Lander life expectancy Approximately one month
  due to radiation
• Shielding and radiation-hardened electronics
• Planetary protection concerns
• Category IVb
• Lander will be maintained with no greater than
  3x105 spores pre-sterilization levels
• Dry heat microbial reduction used on certain
  parts of the spacecraft
• Heat sensitive instruments will be sealed with
  HEPA filters

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Lander Mass Breakdown
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Cruise Stage Mass Breakdown
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Interplanetary Trajectory

• Launch
• Triple Venus gravity assist maneuver
• Deep space maneuvers

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Jupiter System Trajectory

• Jupiter orbit insertion
• Ganymede gravity assist (GGA)
• Chemical Perijove Raise (PJR) maneuvers
• Europa gravity assists (EGAs)
• Europa orbit insertion (EOI)
• 100 km altitude
• Landing

Jupiter
PJR Maneuvers
Ganymede
Europa
Inbound Trajectory
Initial Joviocentric Orbit
EGAs
Perijove Raise Orbits
GGA
EOI
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Propulsion ?V Summary
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Risk Assessment
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Key Trades Completed to Date
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Solar-Electric Propulsion Option

• Provides insufficient gains over chemical
  trajectory with flybys
• Seven xenon electrostatic thrusters
• Isp 3000 sec.
• Required power 423 to 2,288 Watts each
• Large solar array needed
• Thrust range 19.0 to 92.7 mN
• Trajectory modeled as patched conic
• Launch to Earths sphere of influence
• Heliocentric spiral out to Jupiter
• Approximately 5 years
• Joviocentric spiral in to Europa
• Possible use of tether for kinetic energy
  dissipation/power generation

45 meters tip to tip
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Solar Electric Propulsion Trajectory
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Descope Options
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Work to be Done

• Refine Baseline
• Determine landing scenario
• Investigate instrument data collection rate and
  total data volume
• Perform cost versus launch mass trade study
  (descope to 2 landers)
• Determine cruise stage configuration
• Design instruments and Lander layout determine
  necessary instrument tolerances/resolutions
• Create Management Plan
• Perform Cost estimation
• Draft Proposal

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