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 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 Sample Return Vehicle Design Southern University Robert Danso McArthur Whitmore Sample Return Vehicle Design ESTACA Julie Monszajin Sebastien Bouvet

CDD Requirements

Daedalus Lander The Need The Mission The Solution

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”

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

Daedalus Mass Statement

Concept of Operations

LPES LPES Payload Design Requirements LUNAR-A 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

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 Power Lithium Ion Batteries Solar Cells 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

Daedalus Thermal Active Systems Passive Techniques 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

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

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

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

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

Daedalus Performance Figures of Merit Goal Daedalus Number of surface objectives accomplished 15 Samples in permanent dark and 5 samples in lighted terrain 16 Samples in permanent dark and 7 samples in lighted terrain Percentage of mass allocated to payload Higher is better 40% of Dry Mass Ratio of objectives (SMD to ESMD) validation 2 to 1 1.95 to 1 Efficiency of getting data in stakeholders hands vs. capability of mission 83.5 % Percentage of mass allocated to power system Lower is better 14% of Dry Mass Ratio of off-the-shelf hardware to new development hardware 1.67 to 1

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

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

Daedalus Vision 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

This is the Vision for Daedalus…. and the Mission of LunaTech 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

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

Questions

Thermal Backup 1

Thermal Backup 2

Thermal Backup 3

Thermal Backup 4

Thermal Backup 5

Thermal Backup 6