lpsc 2013 poster
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Mars Geophysical Lander Mission A Mission Concept from the 2003 NASA Planetary Science Summer School
Emily M. Craparo Naval Postgraduate School emcrapar@nps.edu
An Early Insight… Mission Design
Conclusions
Landing Sites
During an intensive week in summer 2003, the PSSS team developed the Mars Geophysical Lander (MGL) mission concept and gained valuable interdisciplinary skills in mission design. The recently selected NASA InSight mission shares MGL’s seismometer payload and lander design.
Acknowledgements: The PSSS MGL team would like to thank JPL’s Team X, CoCo Karpinski, Anita Sohus, Jason Andringa, Jean Clough, Daniel Sedlacko, and Bruce Banerdt for their assistance with this project.
Abstract #1706
Ground Penetrating Radar
Thrusters
GRP Thin Walled Tube
Medium Gain Antenna Panning Camera UHF Antenna
Solar Arrays
Dart Antennae (5 Each)
Seismograph
Met Station
Pressurant and Fuel Tanks
• La#tude: between 30-‐60°S for power constraints, poleward of 30°S for near surface water
• Geologic se1ng: sites of recent fluvial acWvity where subsurface water may be expected (i.e. gully locaWons), sites of predicted seismic acWvity
• Eleva#on: maximum 1.3 km above the MOLA datum
• Site roughness: smooth flat plains relaWvely devoid of large obstacles
• Landing ellipse: must fit within flat plateau region
MGL was designed to be a Discovery class mission proposed for the Mars Scout Program. The esWmated mission cost without launch vehicle was $415M in FY2003 dollars. In comparison, InSight is capped at $425M in FY2010 dollars. MGL borrows from the Phoenix Mars Lander heritage. It is not surprising that the upcoming InSight mission shares this lander design heritage. Basing the spacecraa on Phoenix provides for low risk entry, descent, landing, and mission operaWons.
The Mars Geophysical Lander (MGL) is aimed at studying the MarWan interior in search of past habitability and future exploraWon support. Some of the design elements proposed for MGL have now been realized in NASA’s recently selected InSight (Interior ExploraWon using Seismic InvesWgaWons, Geodesy and Heat Transport) mission, which is scheduled to go to Mars in 2016. This poster summarizes the work of the 2003 NASA Planetary Science Summer School (PSSS) student team 10 years aaer creaWng a mission proposal authorizaWon review for the Mars Geophysical Lander. 2013 marks the 25th anniversary of the NASA Planetary Science Summer School (PSSS), which is held every summer at the NASA Jet Propulsion Laboratory to provide postdocs and Ph.D. students with an intensive interdisciplinary experience in planetary roboWc mission design under the tutelage of JPL's Advanced Projects Design Team ("Team X").
5 kg tungsten sphere • Released from spacecraa 10 weeks
prior to Mars landing • Impacts at a known locaWon to
provide a large seismic source • Seismic waves recorded by VBBS to
help study the MarWan interior
Very Broadband Seismometer (VBBS) • 3-‐axis, low-‐power broadband sensor • Frequency range 0.05 mHz – 50 Hz • Developed by IPGP, NetLander heritage • Operates for 1 MarWan year • Measures Wdes, free oscillaWons, and
seismicity to characterize the MarWan core, mantle, and crust
Tunable Diode Laser Spectrometer (TDLS) • ConWnuously tunable • Narrow spectral linewidth • Wavelengths 0.5 – 3.5 µm • SensiWve to organic molecules
High Res. CCD Camera (HRCC) • 1024 x 1024 pixel resoluWon • ObservaWon of dust dissipaWon
and selling, charge detonaWon • OrientaWon of TDLS and MAM
Payloads and Experiments
Daniel W. Kwon Orbital Sciences Corp. dankwon@alum.mit.edu
Samantha L. Infeld AnalyWcal Mechanics Assoc. s.infeld@ama-‐inc.com
Jennifer L. Heldmann NASA Ames Research Center Jennifer.L.Heldmann@nasa.gov
Fraser S. Thomson Space Systems Loral fraser.thomson@gmail.com
Brian R. Shiro University of Hawaii bshiro@hawaii.edu
2003 Planetary Science Summer School Team
Figure 1: MGL Mission Goals
Figure 2: MGL lander
MGL explores geophysical properWes of Mars uWlizing a suite of instruments for determining the nature of the MarWan subsurface, and for characterizing the interacWon of the atmosphere with the MarWan surface. It carries five scienWfic experiments.
Parachute deployment (L - 2 min)!8800 m!490 m/s!
Heat shield jettison (L – 110 s)!7500 m!250 m/s!
Radar ground acquisition !(altitude mode)! (L – 58 s)!2500 m!85 m/s!
Radar ground acquisition (Doppler speed and direction mode) (L – 44 s)!1400 m!80 m/s!
Lander separation & !powered descent (L – 43 s)!1300 m!80 m/s!
Turn to entry attitude!(L - 12 min)!3000 km!4800 m/s!
Cruise solar array separation!(L - 10 min)!2300 km!4800 m/s!
Atmospheric entry (L - 5 min)!125 km!5600 m/s!
Touchdown!2.5 m/s!
Solar panel & instrument deployments!
1600$m$
h$=$1300$m$v$=$80$m/s$L$.$43$s$
h$=23$m$v$=$9$m/s$L$.$5$s$
v$=$30$m/s$
Figure 4: Entry, Descent, and Landing
Figure 5: Geodart deployment
Launch and Earth-‐Mars Transit: The PSSS team calculated a trajectory based upon a Delta II-‐2925H launch from Cape Canaveral in Sept. 2011 to deliver the 1069 kg fueled MGL spacecraa to Mars in Sept. 2012 using MER heritage cruise and landing sensors.
Figure 3: MGL spacecraV
GESA – Geophysical Explora#on for Shallow Aquifers
SEMI – Seismic Explora#on of the Mar#an Interior
ISIE – Inert Seismic Impactor Experiment
MACE – Minor Atmospheric Cons#tuents Experiment
BLAME – Boundary Layer Meteorology Experiment
distance during which Wme it drops the 5 kg geodarts for the GESA experiment (see below). Each geodart has its own 1.5 m diameter parachute to ensure it touches down at 30 m/s, which is sufficient velocity to provide safe penetraWon into the substrate. This penetrator concept was developed by the 2003 PSSS team.
Geodart Deployment: Aaer parachute separaWon, the lander trajectory covers approximately 1.6 km of ground surface
Figure 13: Candidate Landing Sites
PotenWal Landing Site LocaWon Dao Vallis 33°S, 267°W Gorgonum Chaos 37°S, 168°W Nirgal Valles 30°S, 39°W Elysium PlaniWa 37°N, 252°W Newton Crater 41°S, 160°W
Name PSSS Team Role 2003 AffiliaWon 2013 AffiliaWon
Brian (White) Shiro Principal InvesWgator Washington U. NOAA/U. of Hawaii
Elena Adams Program Manager U. of Michigan JHU/APL
Daniel Kwon Systems MIT Orbital Sciences
Jennifer Heldmann Science U. of Colorado NASA Ames
Everel Salas Instruments USC Photon Systems
René Elms ProgrammaWcs Texas A&M Bryan Res. Eng.
Samantha Infeld Mission Design Stanford U. NASA Langley
Christopher Wyckham EDL Princeton U. Heli-‐One
Brel Williams Structures Virginia Tech Raytheon/USC
Esperanza Núñez Computer/Data Sys. UC Berkeley UCSD
Fraser Thomson Telecom Stanford U. Space Sys. Loral
Emily Craparo Awtude Control Sys. MIT Naval Postgrad Scl.
Kelly Pennell Propulsion Purdue U. U. MA Dartmouth
Jonathan Sheffield Power U. of Virginia Space Sys. Loral
Michael McElwain Thermal UCLA NASA Goddard
Melissa (Franzen) Jones Soaware U. of Arkansas NASA JPL
Colleen (Henry) Reiche Ground Systems Purdue U. AvMet Appl. Julien-‐Alexandre Lamamy Cost and Budget MIT Orbital Sciences
2003 PSSS Team
Nirgal Valles
• AcWve seismic refracWon, ground penetraWng radar
• Long-‐term passive seismic monitoring of mars quakes and impacts
• Search for liquid water aquifer
• Characterize crustal structure
• Characterize seismicity
• Long-‐term monitoring of temperature, pressure, wind velocity, solar flux, and humidity
• Infrared spectrometry
• Characterize the atmospheric boundary layer
• Constrain global climate models
• Search for minor organic consWtuents
Approach Objectives
Follo
w th
e W
ater
G
eolo
gy"
Clim
ate"
Meteorological & Atmospheric Monitor (MAM) • Characterize variaWons in temp,
humidity, pressure, wind velocity, and solar flux
• Calibrate global climate models • Developed by CSA, Phoenix heritage
Figure 8: VBBS
Figure 9: ISIE
Figure 10: TDLS
Figure 11: HRCC
Figure 12: MAM
SPMS or explosive"
Parachute Deployment Hardware"
Telecommunication Antenna"
Telecommunication Hardware"
Li-SOCl2 Batteries"
Penetrator"
Short Period Micro-‐Seismometer (SPMS) • 3-‐axis, low-‐power MEMS sensor • Frequency range 0.1 – 10 Hz • Developed by JPL, NetLander heritage • Deployed within 12 “geodart” penetrators
Ground Penetra#ng Radar (GPR) • Frequency of operaWon 15 MHz • Depth range: 10s of meters • Developed by CETP, NetLander heritage
(LeV) Figure 6: GESA and Geodart design
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