LETS Phase 3 Review 4/29/08

Agenda Team Introduction Daedalus Concept Concept of Operations Subsystem Overview Daedalus Performance Daedalus Vision Questions

Team LunaTech Nick Case, Project Manager Morris Morell, Systems Engineer Travis Morris, GN&C Greg Barnett, Thermal Systems Adam Garnick, Power Systems Katherine Tyler, Power Systems Tommy Stewart, Structures and Mechanisms Julius Richardson, Conops John Grose, Payload and Communications Adam Fanning, Communications Eric Brown, Technical Editor

Partners Mobility Concepts –Southern University Robert Danso McArthur Whitmore Sample Return Vehicle Design –ESTACA Julie Monszajin Sebastien Bouvet

Daedalus Lander

Concept of Operations

Daedalus LPES 22 Penetrators –16 Shakleton Crater (Shaded Region) –6 Sunlight Region (outside rim) Design Requirements –1 year Lifetime –75 cm x 14 cm, 14 kg –Impact: ~350 m/s, 4500 g’s, 1~2 m –500 meter distance between penetrators –Primary Mission: Seismic and Heat Flux Payload/Architecture –Carbon Fiber Reinforced Plastic, Ogive nose –Two component seismometer Rotation mechanism to reorient to desired direction –Heat flow probe –Electronics, tiltmeter, accelerometer –400 MHz UHF hybrid telemetry system (1Kbps) –Powered by Li-SOCL2 (super lithium) batteries with a power density ~430 Wh/kg –Shock protection High rigid epoxy-resin, Glass micro-spheres –Temperature 7 internal sensors, 11 external thermocouples –Data transfer to orbiter 1 hr/day UHF buried in regolith

Daedalus Science Basic Requirements for Single Site Science Box: Determine Lighting conditions every 2 hours over the course of one year Study Micrometeorite flux Observe Electrostatic dust levitation and its correlation with lighting conditions

Daedalus Thermal

Daedalus Power

Daedalus GN&C

Daedalus Communications

Daedalus Structures

Daedalus Performance Figures of MeritGoalDaedalus Number of surface objectives accomplished 15 Samples in permanent dark and 5 samples in lighted terrain 16 Samples in permanent dark and 6 samples in lighted terrain Percentage of mass allocated to payload Higher is better40% of Dry Mass Ratio of objectives (SMD to ESMD) validation 2 to 1 Efficiency of getting data in stakeholders hands vs. capability of mission Higher is betterRedundant Communication Percentage of mass allocated to power system Lower is better17% of Dry Mass Ratio of off-the-shelf hardware to new development hardware Higher is better

Daedalus Vision LCS (2010) Proposed LPRP Timeline Using Daedalus LCROSS (2008) LRO (2008) Daedalus I (2012) Daedalus II (2014)

Daedalus Vision Daedalus I Mission to Shackleton Crater Lunar South Pole Reconnaissance achieved by LPES Single Sight Science Conducted Daedalus II Return Mission to Shackleton Crater Further Investigation based on LPES findings Robotic Rover and Sample Return Vehicle Capability

Daedalus Vision Provide a basic, yet powerful and adaptable Lunar Exploration Transportation System Build upon the design practices and valuable data collected Evolve the Daedalus to accomplish each mission Provide a Low-Cost Solution for LPRP This is the Vision of Daedalus…. and the Mission of LunaTech

Questions