1. Lunar Exploration Transportation System (LETS) MAE 491 / 492 2008 IPT Design Competition Instructors: Dr. P.J. Benfield and Dr. Matt Turner Team Frankenstein Final Review Presentation 4/29/08

2. Team Disciplines The University of Alabama in Huntsville –Team Leader: Matt Isbell –Structures: Matthew Pinkston and Robert Baltz –Power: Tyler Smith –Systems Engineering: Kevin Dean –GN&C: Joseph Woodall –Thermal: Thomas Talty –Payload / Communications: Chris Brunton –Operations: Audra Ribordy Southern University –Mobility: Chase Nelson and Eddie Miller ESTACA –Sample Return: Kim Nguyen and Vincent Tolomio

3. Overview Mission Statement The Need The Solution Performance Schedule Operations Structures GN&C Communications Payload Power Thermal Risk Management Conclusions Questions

4. Mission Statement To provide NASA with a reliable and multi- faceted lander design that will provide the flexibility to conduct CDD requirements, scientific investigations, and technology validation tasks at different areas on the moon

5. The Need Only 6% of lunar surface explored –Apollo missions Only orbital visits since Apollo Mobile lunar laboratory with return capabilities is vital to the exploration and understanding of the lunar surface The lunar surface is an unexploited record of the history of the solar system Sample polar sites and crater floors

6. The Solution Lander/Rover Penetrators RTG Cyclops

7. Performance CDD RequirementRequirementAssessmentRemark Landed Mass932.8 kgExceedsActually 810 kg Survive Lunar Cruise28 daysMeetsCapable of surviving lunar cruise exceeding 28 days Operational Period1 yearMeetsTRL 9 materials will remain functional beyond 1 year Sample Lunar Surface15 darkExceedsMobility allows roving to as many sites as is needed Communication Send and Receive (real time)ExceedsCapable of sending data at 150 Mbps Landing Parameters12º slope within 100 mExceeds Six wheel rocker bogey system allows landing on slopes greater than 12 degrees Survive Launch of 6 G's6 G'sExceedsCyclops structure will handle g-loads exceeding 6 g’s Technology RequirementsTRL9MeetsMaterials used are TRL 9 Power Requirements Store Power in Dark ConditionsExceedsRTG can provide the power needed during dark conditions Thermal Conditions Survive Temperature ChangesExceeds Materials used will withstand temperatures exceeding the 50K to 380K range Sample Return VehicleSample Return (Goal)MeetsExceeds the sample return expectations Mobile Roving/Real-Time MobilityExceeds6 wheel rocker bogey allows roving in real-time

8. Schedule

9. Operations Cyclops Penetrators 2.5km 1.6km 1. 5km 2. Deploy Penetrators 3-4. Decent 5. Land 6. Release Propulsion System 7. Rove To Edge of Crater

10. Operations Launch - September 30, 2012 Arrive at moon - October 6, 2012 Operations start 5km from lunar surface October 8, 2012 –Decent Shoot 15 penetrators into Shackleton Crater for dark region sampling –Landing Drop off “single site box” to accomplish single site goals October 9, 2012 –Rove to rim of Shackleton Crater October 11 - 18, 2012 –Receive all data from penetrators October 19, 2012 –Relay all data from penetrators to LRO for transmission to Mission Control 5 orbits needed

11. Operations October 22, 2012 – March 4, 2013 –Rove to, collect and relay data from 29 lighted sites March 5 – March 7, 2013 –Rove to, collect sample, and launch SRV March 8 – July 22 –Rove to, collect and relay data from Lighted sites 30 - 59 July 23 – 25 –Rove to rim of Shackleton crater July 26 – September 27 –Rove to, collect and relay data from Dark Sites (if penetrators fail) September 30, 2013 –System Shut Down

12. Structures System Specifications (Auxiliary Systems) Penetrator Ring Platform –Outer Diameter- 3.189 m. –Aluminum Construction (6061 T6) -Mounted penetrators (spring released at a 4 degree dispersion angle) Attitude Control –Main thrusters- MR 80B –Attitude Control Thrusters- MR 106 –Hydrazine Tank x 2- 0.549 m. Outer Diameter –Aluminum Frame (6061 T6) Single Site Box –Max Box Dimensions – 1.54 x 0.688 x 0.356 m. –Integrated Sample Return Vehicle Penetrator Ring Platform Attitude Control System Cyclops

13. Structures System Specifications (Main) –Main Chassis Dimensions – 1.54 x 1.54 x 0.356 m. Aluminum Frame (6061 T6) Carbon composite exterior MLI Insulation –6 Wheel Passive Rocker Bogie Mobility System Proven Transportation Platform (MER, Pathfinder) 0.33 m. Outer Diameter Wheels Can navigate up to a 45 degree angle Max speed of 90 m/hr. Aluminum construction (6061 T6) Maxon EC 60 Brushless DC motor (60mm) x 6 Maxon EC 45 Brushless DC motor (45mm) x 8 –Camera (SSI) Dimensions – 0.305 x 0.203 x 0.152 m. –Scoop Arm Max Reach- 1.727 m. Before Deployment After Deployment

14. Structures Maxon 60mm EC 60 x 6 Nominal torque 830 mNm Maxon 45mm EC 45 x 8 Nominal torque 310 mNm Wheel MotorsSteering Motors

15. GN&C Decent/Landing –A LIDAR system will be used to control, navigate, and stabilize while in descent Post Landing –An operator at mission control will manually navigate lander/rover A Surface Stereo Imager (SSI) periscopic, panoramic camera will be used to survey the lunar surface, provide range maps in support of sampling operations, and to make lunar dust cloud measurements

16. GN&C Descent Imaging –A Mars Descent Imager (MARDI) will be used to view both the penetrator dispersion and the landing/descent of the Cyclops Processor –A BAE RAD750 will be used for all controls processing

17. Communications Rover –Parabolic Dish Reflector Antenna (PDRA) T-712 Transmitter –Communication Bandwidth : X-band –Data Transmission Rate : 150 Mbps –Data Storage Capacity: 10 GB Penetrators –Omnidirectional Antenna Communication Bandwidth: S-band Data Transmission Rate: 8 Kbps –Data Storage Capacity: 300 MB

18. Communications/Payload Single Site Box (SSB) –Determines lighting conditions every 2 hours for one year, micrometeorite flux, and assess electrostatic dust levitation –Omnidirectional Antenna Communication Bandwidth: S-band Data Transmission Rate: 8 Kbps –Data Storage Capacity: 1Gb –Surface Stereo Imager (SSI) –Mass: 10 Kg –Dimensions: 155x68.5x35.5 cm –Power: Solar Panel

19. Payload Gas Chromatograph Mass Spectrometer (GCMS) –Performs atmospheric and organic analysis of the lunar surface –Mass: 19 Kg –Dimensions: 10x10x8 cm –Power: Rover Surface Sampler Assembly (SSA) –Purpose is to acquire, process and distribute samples from the moon’s surface to the GCMS –Mass: 15.5 Kg –Dimensions: 110X10X10 cm –Power: Rover

20. Payload Penetrators (Deep Space 2 ) –Mission’s main source of data acquisition in the permanent dark regions –Mass (15 Penetrators): 53.58 Kg –Dimensions: 13.6Dx10L cm –Power: 2 Lithium Ion Batteries Each Miniature Thermal Emission Spectrometer (Mini-TES) –Objective to provide measurements of minerals and thermo physical properties on the moon –Mass: 2.4 Kg –Dimensions: 23.5x16.3x15.5 cm –Power: Rover

21. Power RTG –TRL9 –Constant power supply –Thermal output can be utilized for thermal systems Lithium-Ion Batteries –Commercially available –Easily customizable –Rechargeable Solar –Used for Single Site Box –Conventional –Increasingly efficient in well light areas POWER SUBSYSTEM Type (solar, battery, RTG)Solar, Lithium-ion, RTG Total mass47.63 kg Total power required643.525 W Number of solar arrays1 Solar array mass/solar array1.13 kg Solar array area/solar array0.12 square meter Number of batteries2 Battery mass/battery3.25 kg Number of RTGs1 RTG Mass/RTG40 kg

22. Power Power Analysis ComponentSubcomponentsConsumption (W) Mobility 342.625 SRV 25 GN&C 115.5 Payload 34.6 Communications 70.8 Thermal 55 Operations 0 Power Supply 865 RTG400 Li-ion Battery455 Solar Cell10 (Not in Total) Minimum Totals 643.525 Contingency Supply33%212.36325 Total 855 Total Power Required –643.525 W Peak Power –Mobility 342.625 W –Data Collection/Transfer 276.2 W –Single Sight Box 7.8 W RTG –400 W Lithium-Ion Batteries –455 W for both Solar Cells –10 W (SSB - Not included in Total) 33% Contingency Power Total Power Supplied to Lander –855 W

23. Thermal Cyclops uses three types –Heat transfer pipes –Paraffin heat switches Radiator heat switches Diaphragm heat switches –Multi-Layer Insulation

24. Thermal Two standard types of switches are used as a redundant check to prevent over heating

25. Thermal Heat is well controlled –MLI has low heat absorbance –Heat switches allow close tolerance control

26. Risk Management

27. Conclusions “There’s no place this thing can’t go” If penetrators fail, remaining mission will not be compromised Reliable multi-faceted design

28. Questions