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LETS Phase 3 Review 4/29/08

LETS Phase 3 Review 4/29/08. Agenda. Team Introduction Daedalus Concept Concept of Operations Subsystem Overview Daedalus Performance Daedalus Vision Public Outreach Questions. Team LunaTech. Nick Case, Project Manager Morris Morell, Systems Engineer Travis Morris, GN&C

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LETS Phase 3 Review 4/29/08

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  1. LETS Phase 3 Review4/29/08

  2. Agenda • Team Introduction • Daedalus Concept • Concept of Operations • Subsystem Overview • Daedalus Performance • Daedalus Vision • Public Outreach • Questions

  3. 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

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

  5. CDD Requirements

  6. Daedalus Lander • The Need • The Mission • The Solution

  7. Daedalus Lander • Simple, Adaptable, Autonomous Lander • Solar Cell and Li-Ion Battery Power • Semi-passive Thermal System • Ka-Band and UHF Communications System • Lunar Penetrator Exploration System (LPES) “Fire and Forget”

  8. Daedalus Heritage Structure based on Viking Lander Communication based on MER Penetrators based on LUNAR-A Power System based on Mars Phoenix & Venus Express DSMAC Technology for GN&C based on Cruise Missile

  9. Daedalus Mass Statement

  10. Concept of Operations

  11. LPES • LPES • 22 Penetrators • 16 Launched into Shackleton Crater • 6 Launched into Lighted Region • Spring-Loaded Ejection System • Payload • Micro-Seismometers • Impact Accelerometer and Tilt Sensors • Heat Flow Probe • Geochemistry Package • Water/Volatiles Detector LUNAR-A • Design Requirements • 1-1.2 Year Lifetime • Impact Velocity: ~350 m/s • Impact Force: ~4500 G’s • Impact Depth: 1~2 m • Scatter Distance: 500 m Penetration Web • ESTIMATED PENETRATOR SIZE • Length: 480mm to 600mm • Diameter: 60mm • Estimated Mass: 14kg

  12. 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

  13. Daedalus Power • Lithium Ion Batteries • Total of 9 Sony 1860HC • Total mass of 42.24 kg • Total Volume of 1.341 ft^3 • Solar Cells • Total of 3 Gallium Arsenide Panels • Total mass of 46 kg • Total Surface area of 6.161 ft^3 • Total Power of 937 Watts • Power Regulation and Control • 6 Auxiliary Power Regulators. 2 per Solar Cell • 1 Battery Charge/Discharge Regulator per battery • ON Semiconductor LM350 Positive Voltage Regulators • STM Microelectronix ST0269 Digital Signal/Microprocessor • Crydom CMX60D10 Solid State Relays

  14. Daedalus Thermal • Active Systems • Electrical Resistance Heaters • Tayco solid-state controller • Variable Radioisotope Heater Units • 50 Employed (50 Watts) • Cassini-Huygens (117) • 10 VRHU containers • Variable Conductance Heat Pipes • Aluminum(1.27cm) & Ammonia • Integrated with radiator panels • Axial groove composite wick • Passive Techniques • Paints – White and Black • Multi-layered Insulation • 15 layers • Betacloth, aluminized Kapton • Dacron Netting, Kapton laminate • Thermal Switches • Diaphragm Thin Plate Switch (Paraffin) • Between heat generators and sinks MLI – exposed separator layers shown

  15. GN&C Objective: To deliver Daedalus from 5km altitude safely and accurately to the lunar surface • Provides Completely Autonomous Landing sequence • Very Precise landing location • Landing location determined before launch • Hazard Avoidance

  16. Daedalus Communications Earth Receiver and Transmitter LRO to Earth using Ka-band Data Rate: 100 Mbps LRO Daedalus to LRO using Ka-Band Data Rate: 100 Mbps View Time: 1 Hour per Day (approx) Penetrators to LRO using UHF Data Rate: 2 Kbps Daedalus Lunar Penetrators

  17. Daedalus Structures Landing Scenario • A 8200 Newton load was applied to the foot of the leg assembly. • Loads were then transferred to the chassis • Results indicate the Minimum Factor of Safety is 1.15

  18. Daedalus Structures Launch Scenario • To simulate loads experienced at launch a 54000 Newton load was applied. • Results indicate the Minimum Factor of Safety is 1.3

  19. Daedalus Performance

  20. Mariner 7 & 9 Mars Exploration Rovers Mars Phoenix Lander 2001 Mars Odyssey Mars Global Surveyor Mars Science Laboratory Mars Express Orbiter Mars Reconnaissance Orbiter Viking 1 & 2 Mars Pathfinder 1970 1980 1990 2000 Present Daedalus Vision Mars Exploration Roadmap

  21. Daedalus Vision Proposed LPRP Timeline Using Daedalus SRV (ESTACA) LRO (2008) LCS (2011) Daedalus I (2012) Daedalus II (2014) Rover (Southern) LCROSS (2008)

  22. Daedalus I Mission to Shackleton Crater Lunar South Pole Reconnaissance achieved by LPES Single Site Science Conducted Scientific data used to justify funding for Daedalus II Daedalus II Return Mission to Shackleton Crater Further Investigation based on LPES findings Robotic Rover and Sample Return Vehicle Capability Daedalus Vision

  23. 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 for Daedalus…. and the Mission of LunaTech

  24. Public Outreach • Union Hill School • May 8, 2008 • 4th Grade • Presentation about the Moon, LPRP and Daedalus • Launch a Model Rocket

  25. Questions

  26. Thermal Backup 1

  27. Thermal Backup 2

  28. Thermal Backup 3

  29. Thermal Backup 4

  30. Thermal Backup 5

  31. Thermal Backup 6

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