Title: TEMPEST
1TEMPEST
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
2Agenda
- Science Objectives
- Baseline Architecture
- Risk
- Schedule
- Cost
Credit Visination.com
3Tempest 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
4Science 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.
5Potential 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
6Science Baseline Performance Floor
Mars Roadmap Committee Meeting Released
February 14, 2005
Performance Floor
Descope
7Platform Selection
Performance Floor
Descope
8Landing Site SelectionHellas Basin
- 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.
9Baseline 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
10Baseline ArchitectureEntry and Deployment
11Baseline 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
12Baseline Architecture Tempest Mass Power
Summary
Cruise Stage
Backshell
Heat Shield
13Baseline 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
14Mission Risk Mitigation
15History 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
16Current 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
17Balloon 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
18Project 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
19Project Cost Estimate
Margin 104 M (30)
20Questions
21TEMPEST
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
22Introduction
- Mars Scout 2011
- Augment or complement NASAs MEP
- Must launch by December 31, 2011
- Cost cap at 450 M (FY07)
23VEGA Program
24Baseline ArchitectureMajor Completed Trade
Studies
25Baseline ArchitectureTrajectory
December 14, 2011 Departure C3 10.58 km2/s2
January 1, 2013 Arrival C3 29.14 km2/s2
26Baseline Architecture Launch Vehicle Selection
Delta II 7925 990 kg at C3 10.58 km2/s2
Credit NASA-KSC
27Baseline Architecture Cruise
- Type II, 384 day cruise
- TCM-1 through TCM-6 planned in DV budget
28Baseline ArchitectureMars Entry
- Cruise stage separates prior to entry
- Ablative heat shield for direct entry
Credit NASA-JPL
29Baseline 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
30Baseline 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.
31Baseline ArchitectureInstrumentation
32Baseline Architecture Tempest Balloon Weight
Breakdown Structure
33Baseline ArchitectureTempest Balloon Power
Summary
Margin 80 W (30)
Margin 80 W (30)
34Baseline 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)
35Baseline ArchitectureCruise Stage Power Summary
Margin 91 W (50)
Margin 63 W (30)
36Education / 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
37Observing 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
38Observing 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
39Baseline 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
40Instrumentation 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
41Instrumentation 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
42Other 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