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Lunar Exploration Transportation System (LETS)

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. Team Disciplines. The University of Alabama in Huntsville Team Leader: Matt Isbell

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Lunar Exploration Transportation System (LETS)

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  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 • GN&C • Communications • Payload • Power • Thermal • Conclusions • Questions • Project Office • Systems Engineering • The Need • The Requirements • The Solution • Performance • Operations • Structures

  4. Project Office

  5. Systems Engineering

  6. The Need

  7. The Requirements

  8. The Solution

  9. Performance

  10. Operations

  11. Structures

  12. GN&C

  13. 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

  14. 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

  15. 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

  16. 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

  17. Power

  18. Thermal

  19. Conclusions

  20. Questions

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