1. LETS Phase 3 Review 4/29/08

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 Sample Return Vehicle Design
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 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

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 Solar Cells
Total of 9 Sony 1860HC
Total mass of kg
Total Volume of ft^3
Solar Cells
Total of 3 Gallium Arsenide Panels
Total mass of 46 kg
Total Surface area of 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 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

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 Newton load was applied.
Results indicate the Minimum Factor of Safety is 1.3

19. 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

20. 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

21. 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)

22. 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

23. 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

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