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. Agenda Project Office Systems Engineering The Need The Requirements The Solution Performance Operations Structures GN&C Communications Payload Power Thermal Risk Management Conclusions Closing Thoughts Questions

4. Project Office

5. Systems Engineering

6. The Need Only 6% of lunar surface explored – Apollo missions Only orbital visits since Apollo –Galileo 1990, 1992, Clementine 1994 Lunar Topography & multispectral imaging of surface – water at poles –Lunar Prospector 1998 – 1999 Global surface contents– hydrogen at poles Lunar geochemistry – iron, thorium, and other elements An in-situ, 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 Need to sample polar sites and crater floors

7. The Requirements Launch vehicle - Atlas V – 401 EPF –Landed mass 997.4kg Launch Date September 12, 2012 Propulsion –159.5 kg of hydrazine (N2H4) propellant 2 Spherical tanks 0.55m in diameter –2.0 kg of helium 2 Spherical tanks 0.4m in diameter –2 MR-80B monopropellant liquid rocket engines –12 MR-106 monopropellant thrusters Survivability –Temperature range -153°C to 107°C –Launch g-loads –Radiation –Micrometeoroid flux Surface Operations –15 permanently dark sites, 500m apart –5 lighted sites, 500m apart –Land on 12° slope –must land within 100m ± 3 sigma of intended landing site –Control starts 5km from lunar surface

8. The Solution

9. Performance

10. Operations

11. Launch - September 30, 2012 Arrive at moon - October 6, 2012 Operations start 5km from lunar surface October 8, 2012 –Decent Shoot 15 penatrators 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 penatrators October 19, 2012 –Relay all data from penatrators to LRO for transmission to Mission Control 5 orbits needed

12. 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 penatrators fail) September 30, 2013 –System Shut Down

13. Operations Cyclops Penetrators 2.5km.325km 1.6km

14. Structures

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 the 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: 6 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 Ea. 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

24. Conclusions

25. Risk Management

26. Closing Thoughts We would like to thank you for this great learning opportunity. IPT introduced a real-world, working environment for us to learn and work as a team to meet a customer's requirements which is something that can not be taught in the classroom. We appreciate your contribution in our education and enthusiasm to instruct us on how to become more productive engineers.

27. Questions