TEMPEST

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TEMPEST
Final Presentation
2011 Mars Scout Mission

• John Christian, Project Manager
• Stacie Dawson, Science Payload Engineer
• Jason Liles, Project Systems Engineer
• Jonathan Lowe, Mission Systems Engineer
• Vickie Maul, Science Requirements Data Engineer

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Agenda

• Science Objectives
• Baseline Architecture
• Risk
• Schedule
• Cost

Credit Visination.com
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Tempest Organization
Mars Program Office NASA SMD
Principal Investigator Joseph Levy, Brown Univ.
Project Management John Christian
Co-Investigators
Project Systems Engineer Jason Liles
Mission Systems Engineer Jonathan Lowe
Science Req and Data Engineer Vickie Maul
Science Payload Engineer Stacie Dawson
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Science Theme and Rationale

• Theme
• Understand processes that control the annual
  variations/transport of volatiles and dust in the
  lower atmosphere and planetary boundary layer.
• Rationale
• Understand how these processes control climate
  change, both past and present, and how they may
  relate to human explorers.

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Potential Benefits

• Update trajectory and general circulation models
• Better prepare future missions for the Martian
  dust environment
• Compliment data collected by orbiting assets with
  in-situ measurements
• Understand radiation shielding properties of
  atmosphere
• Prepare future missions for potential
  electrostatic discharges

Credit John Frassanito Associates
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Science Baseline Performance Floor
Mars Roadmap Committee Meeting Released
February 14, 2005
Performance Floor
Descope
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Platform Selection
Performance Floor
Descope
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Landing Site SelectionHellas Basin

• 7 km below MOLA datum

• 1200 km diameter
• Higher levels of wind and
• dust activity
• Conditions increase
• science return and can
• be extrapolated to other
• landing sites on Mars

Hellas Basin dust devil data from Mars Orbiter
Camera (MOC)
Credit Dept. of Geological Sciences, Arizona
State Univ.
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Baseline ArchitectureOverview
Credit NASA-JPL
Credit NASA-JPL
Credit NASA-JPL
Launch 12/14/2011
Interplanetary Cruise 384 days
Arrival 1/1/2013
Aerial deployment without landing (EDI)
Conduct 90 day science mission
Credit Scientific America
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Baseline ArchitectureEntry and Deployment
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Baseline ArchitectureAerial Operations

• IMU provided with frequent updates via
• Electra Mars Proximity Link Payload
• Laser altimeter
• Velocity updates from microlidar
• Kalman filter to optimize navigation aid feedback
  
• Context imaging will provide additional
  information about Tempests position

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Baseline Architecture Tempest Mass Power
Summary
Cruise Stage
Backshell
Heat Shield
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Baseline ArchitecturePlanetary Protection

• Category IVa
• Assembled and maintained in Class 100,000 clean
  rooms
• No greater than 3x105 spores and a max density
  of 300 spores/m2 (Viking pre- sterilization
  level

Credit NASA PPO
Preparing a Viking Lander for dry heat
sterilization.

• HEPA filters maintain acceptable level of spores
• Dry heat of 110 C for 40 hours or 125 C for 6
  hours for surfaces
• Gamma-ray sterilization for Mylar balloon

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Mission Risk Mitigation
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History of Planetary BalloonMissions and Studies

• Vega
• French and Russian cooperative mission
• Successful aerial deployment of superpressure
  Helium balloon on Venus

• Mars Balloon Studies
• Mars Balloon Validation Program (MABVAP)
• Mars Aerial Platform (MAP)
• Mars Aerobot/Balloon Study (MABS)
• Mars Aerobot Technology Experiment (MABTEX)
• Directed Aerial Robot Explorers (DARE)

DARE Proposal
The Fourth Millennium
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Current ProgramsNASA ULDB Wallops Flight
Facility

• Successful demonstration of autonomous inflation
  of superpressure Helium balloon at a Mars analog
  altitude
• Deployed at an altitude of 100,000 ft
• Dynamic deployment descent of 40 m/s
• Successful demonstration of a ground-launched
  long duration Helium superpressure balloon
  (January 2005)
• 137 meter diameter at 125,000 ft altitude
• Two ton payload lifted for 41 day flight

Credit NASA, Balloon Program Office
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Balloon Development Program

• Extensive drop tests
• NASA Balloon Program Office received 1.5 M for a
  three year campaign (2 drop tests a year).
• Tempest has allocated 9 M for three drop tests,
  two will be a full sized balloon demonstration.
• All drop tests will be in Mars analog conditions.
• Partner with NASA Balloon Program Office, Tethers
  Unlimited, and GSSL

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Project Schedule
Phase A
Phase B
Phase C
Phase D
Phase E
Step 1 TMC
Launch
Step 2 TMC
ARR
PDR
Key Project Milestones
Arrival
Step-1 Selection Announced
PMSR
CDR
MRR ORR
ICR
Confirmation Review
CERR
Flight Tests
FT-1
FT-3
FT-2
Mission Definition
Preliminary Design
Instruments
Instrument Integration
Balloon System
Phase C/D Schedule Margin 7 months
Balloon Integration
Cruise Stage
Cruise Integration
Cruise-Balloon ATLO
Interplanetary Transit
Mission Operations Data Analysis
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Project Cost Estimate
Margin 104 M (30)
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Questions
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TEMPEST
Final Presentation
BACKUP SLIDES

• John Christian, Project Manager
• Stacie Dawson, Science Payload Engineer
• Jason Liles, Project Systems Engineer
• Jonathan Lowe, Mission Systems Engineer
• Vickie Maul, Science Requirements Data Engineer

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Introduction

• Mars Scout 2011
• Augment or complement NASAs MEP
• Must launch by December 31, 2011
• Cost cap at 450 M (FY07)

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VEGA Program
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Baseline ArchitectureMajor Completed Trade
Studies
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Baseline ArchitectureTrajectory
December 14, 2011 Departure C3 10.58 km2/s2
January 1, 2013 Arrival C3 29.14 km2/s2
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Baseline Architecture Launch Vehicle Selection
Delta II 7925 990 kg at C3 10.58 km2/s2
Credit NASA-KSC
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Baseline Architecture Cruise

• Type II, 384 day cruise
• TCM-1 through TCM-6 planned in DV budget

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Baseline ArchitectureMars Entry

• Cruise stage separates prior to entry
• Ablative heat shield for direct entry

Credit NASA-JPL
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Baseline ArchitectureSuperpressure Balloon

• Maintains a constant density altitude
• Reduced risk of large altitude variations
• Ribbed pumpkin envelope reduces stresses in
  envelope assembly
• Withstands high internal pressures better than
  traditional spherical envelopes
• Thoroughly tested and proven Mylar composite
  envelope
• Buoyancy Gas (Helium)
• Lightweight
• Easy to store and transport
• Inert and nonflammable

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Baseline ArchitectureTether and Suspension System

• Tether
• 50 m Hoytether
• Spectra 2000
• High resistance to flex fatigue, UV, chemicals,
  and abrasions
• Excellent vibration damping
• Very durable
• System includes non-rotating spool, a shroud, and
  passive braking system
• No communications or power necessary along tether
• Suspension System
• Attached to tether above CG of gondola
• Geometric center of gondola must be inline with
  CG
• Connection points must swivel to allow for
  maneuverability
• Fits in a canister the size of a Coke can

The Hoytether
Credit Tethers Unlimited Inc.
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Baseline ArchitectureInstrumentation
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Baseline Architecture Tempest Balloon Weight
Breakdown Structure
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Baseline ArchitectureTempest Balloon Power
Summary
Margin 80 W (30)
Margin 80 W (30)
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Baseline Architecture Cruise Stage Weight
Breakdown Structure
Launch Vehicle Adapter / Tempest Umbilical
Connection
Sun Sensors (2 of 4)
Medium Gain Antenna
Omni-directional Antenna
He Pressurant Tank
Mars Exploration RoverEntry Mass 835
kg Cruise Stage Mass 193 kgPropellant
50 kg
Solar Panels (transparent)
Hydrazine Propellant Tank (1 of 2)
Star Tracker (1 of 2)
27/40 N Thruster Bank (2 of 4)
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Baseline ArchitectureCruise Stage Power Summary
Margin 91 W (50)
Margin 63 W (30)
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Education / Public Outreach

• Students
• Interactive presentations to schools of levels
• K-12 throughout mission
• Models and videos will be used to engage open
  discussion
• Public
• Museum visits and exhibitions
• Local newspaper and television stations for
  mission coverage

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Observing Atmospheric Events Dust Devil
Background

• Convective vortices from unstable warm air due to
  insolation
• Characteristics
• 15 m across and 350 m high to
• 5 km across and 8 km high
• Usually travel 0.5 km (up to 2 km)
• Typically occur in early afternoon
• and rarely occur at night

Credit Malin Space Science Systems
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Observing Atmospheric Events Probability of
Finding a Dust Devil
Mission simulation calculates the probability of
encountering a dust devil Data based on an
average of two dust devils per square km every 65
sols
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Baseline ArchitectureTelecommunications

• Capabilities
• Deep Space Network (34m and 70m antennae)
• Critical event monitoring
• Science return backup
• Low data rate of 400 bps
• Orbital Assets
• MTO (64 kbps) and MRO (256 kbps)
• Electra UHF Telecomm Package
• Doppler data for navigation
• Critical event monitoring
• Main science data return link
• Onboard
• HGA, 0.4 m diameter
• UHF, Omni-directional LGA

Credit NASA-JPL
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Instrumentation Microlidar and LAMDA

• Doppler Wind LIDAR (Mars Microlidar)
• Measures the Doppler shift from the
  backscattering of light to obtain wind speeds
• Currently a prototype at JPL
• CBE Mass 2 kg
• CBE Power 2 W
• Maximum Range 5 km
• Laser Anemometer and Martian Dust
• Accumulator (LAMDA)
• Measures wind speed and direction, dust
  concentration, deposition rate, electrical
  charge, magnetic susceptibility and spectroscopy
• CBE Mass 100 g
• CBE Power 1 W
• Maximum Range 3 cm

LAMDA
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Instrumentation EFM and Conductivity Probe

• Electric Field Mill (EFM)
• Measures the electric field as the aircraft flies
  in the vicinity of electrified clouds
• CBE Mass 3.6 kg
• CBE Power 5.6 W
• Conductivity Probe
• Dual Channel Gerdien Conductivity Probe
• Measures the conductivity of the atmosphere and
  combined with EFM can determine storm electric
  currents
• CBE Mass 2.3 kg
• CBE Power 2.8 W

Electric Field Mill
Gerdien Conductivity Probe
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Other Instrumentation

• ASI/MET
• Determines local atmospheric pressure,
  temperature, and wind speeds
• CBE Mass 2 kg
• CBE Power 3.2 W
• Dosimeter
• Exposure to ionizing radiation causes the voltage
  to change
• CBE Mass 300 g
• CBE Power 0.5 W

ASI/MET Sensor