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