final presentation at the 2003 NASA Planetary Science Summer School. Presented on August 8, 2003 at the Jet Propulsion Laboratory.

1. August 8, 2003 Principal Investigator: Brian White Proposal Manager: Elena Adams MARS GEOPHYSICAL LANDER PROPOSAL AUTHORIZATION REVIEW 2011 MARS SCOUT AO

2. Team Members Cost MIT Julien-Alexandre Lamamy Ground Systems Purdue University Colleen Henry Software University of Arkansas Melissa Franzen Thermal UCLA Mike McElwain Power University of Virginia Jonathan Sheffield Propulsion Purdue University Kelly Pennell Attitude Control System MIT Emily Craparo Telecommunications Stanford Fraser Thomson Computer & Data Systems Berkeley Esperanza Nunez Structures Virginia Tech Brett Williams Entry, Descent, & Landing Princeton Chris Wyckham Mission Design Stanford Samantha Infeld Programmatics Texas A&M René Elms Instruments USC Everett Salas Science University of Colorado Jen Heldmann Systems MIT Daniel Kwon Program Manager University of Michigan Elena Adams Principal Investigator Washington University Brian White

6. Water on Mars Valley networks Gullies Subsurface ice Polar caps Rampart craters Streamlined islands Outflow channels Layered terrain Follow the Water

22. Trajectory If clicking the image doesn’t start the movie, click here.

23. EDL Profile 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

24. Geodart Deployment Sequence 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

26. Lander Design MPL/Phoenix heritage Ground Penetrating Radar Thrusters (4 each) GRP Thin Walled Tube Medium Gain Antenna Panning Camera UHF Antenna Solar Arrays (2 Each) Dart Antennae Array (5) Seismograph Met Station Pressurant and Fuel Tanks (2 Each)

31. Cruise, EDL, and Surface Block Diagram HGA SDST X-band Tx/Rx Lander SDST X-band Tx/Rx Quad. Electra UHF Only X-band Hybrid SSPA LGA Assy Backshell 0.29 m 15 W 15 W CMD & Cntrl High Rate I/F Clock Valid Line POR Sleep Wake-Up Cntrl & Engr. Tlm. RS-422 CMD 5 V Reboot External Analog Tlm. Ext. Digital Tlm. (RS-422) SSPA Gimbal Waveguide Coax. Coax. Switch HGA 0.29 m LGA Assy To C&DH TLM To C&DH Pol. Pol. Trans. Trans. Trans. W/G to Coax. Transition. Mono Array Phase Detect

36. Programmatics Schedule

43. Science Traceability SCIENCE OBJECTIVES MEASUREMENT REQUIREMENTS INSTRUMENT REQUIREMENTS MISSION REQUIREMENTS DATA PRODUCED Search for subsurface water sources at the landing site Seismic data, ground penetrating radar during first 10 days of mission Active seismic array (operates from 0.01 Hz-10 Hz). Ground penetrating radar measurements (15 MHz, sensitive up to a depth of 2 km) Instruments must be operational for first 10 days after landing. Map variation of S and P wave velocity and dielectric constant with depth in shallow crust (< 500m). Determine crustal structure and thickness Active seismic data, ground penetrating radar. Seismic data from Inert Seismic Impactor Active seismic array, seismometer (operates from 0.05 mHz-50 Hz). Ground penetrating radar measurements (15 MHz, sensitive up to a depth of 2 km) Active seismic instruments must be operational for first 10 days after landing. Map variation of S and P wave velocity and dielectric constant with depth in shallow and deep crust, down to Moho. Characterize deep planetary structure Passive seismic data from natural sources. Passive seismic monitoring (operates from 0.05 mHz-50 Hz) with intelligent event-detection software Instruments must monitor seismic activity continuously at landing site for one Martian year. Mantle from body waves and normal modes Core from gravitational Love number (Phobos tide) Characterize seismic activity and meteoroid influx Passive seismic data for one Martian year Passive seismic monitoring (operates from 0.05 mHz-50 Hz) Instruments must monitor seismic activity continuously at landing site for one Martian year. Long term record of seismic activity due to marsquakes and meteorite impact events.

44. Science Traceability ( cont. ) SCIENCE OBJECTIVES MEASUREMENT REQUIREMENTS INSTRUMENT REQUIREMENTS MISSION REQUIREMENTS DATA PRODUCED Characterize atmospheric boundary layer and long term climatic conditions Temperature, pressure, wind speed and direction, relative humidity, solar flux for one Martian year, CCD images of dust behavior in atmosphere after explosive darts detonated Temperature (resolution=0.5 K), pressure (resolution=0.5 Pa), humidity (resolution 0.1%), wind direction (resolution=15 degrees), wind speed (resolution=TBD), CCD camera images Meteorological instruments must monitor atmospheric conditions on Martian surface continuously for one Martian year, CCD camera must image area of explosive darts after detonation. Temperature and wind boundary layer profiles. Long term monitoring of temperature, pressure, humidity, and solar flux. Search for minor atmospheric species Atmospheric composition species for one Martian year IR spectrometer (operates between 0.5-3.5 microns) Instrument will measure atmospheric composition for 10 minutes per day for one Martian year. IR spectra for an air column. Shallow subsurface liquid water aquifer Calibration of Mars crater counting Crustal thickness and mantle/core properties Diurnal/Seasonal weather variations at site Current seismic/tectonic activity of Mars Detection of H 2 O and/or organics in atmosphere Some Possible Exciting Results