1 / 22

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 Phase 2 Presentation 3/6/08. Team Disciplines. The University of Alabama in Huntsville Team Leader: Matt Isbell

freja
Download Presentation

Lunar Exploration Transportation System (LETS)

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript


  1. Lunar Exploration Transportation System (LETS) MAE 491 / 492 2008 IPT Design Competition Instructors: Dr. P.J. Benfield and Dr. Matt Turner Team Frankenstein Phase 2 Presentation 3/6/08

  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 Abstract Phase 2 Overview Design Process Outline Concepts Subsystems of Concepts • Selection of Final Concept • Phase 3 Planning • Phase 3 Schedule • Conclusions • Questions

  4. Abstract • Multifaceted and reliable design • System meets all CDD requirements • Two concepts developed in Phase 2 using the Viking Lander as a baseline • Each design assessed based on the specifications of the CDD • Both were assessed and ranked • The best design, Cyclops, was chosen to be carried into Phase 3 • Designs ranked by: ability to meet scientific objectives, weight, ease of design and mobility, etc.

  5. Phase 2 Overview • Deliverables • White paper • Compare baseline, the Viking Lander, with two alternative concepts • Strategy for selecting alternative systems • Qualitative and quantitative information to evaluate each idea • A logical rationale for selecting one concept from among the presented options • Oral presentation • SpecificationSummary • Lander and rover is required to meet the CDD requirements for the mission • The CDD requirements are the foundation for the lander/rover design • Each subsystem is also directly affected by the requirements and lunar environment

  6. Phase 2 Overview Cont. • Approach to Phase 2 • Team Structure • Team Frankenstein is born • Team split up into separate disciplines • Concerns • Harsh lunar environment – Electrically charged dust, temperature, radiation, micro meteoroids, etc. • 15 Samples in permanent dark – Extreme temperature of -223 C • Mobility - non-existent on the baseline lander and LETS CDD requires mobility • Concept Design • Review baseline lander for detailed information about the customer’s specific requirement • Investigated possible solutions to meet the given CDD requirements • Each discipline presented design ideas to the team • Team revised these possibilities and created two design concepts • Evaluated the concepts based on the weighted values for desired criteria and chose the winning concept

  7. Design Process Outline CDD/Customer Project Office Systems Engineer Structures Power Mobility Sample Return Payloads Operations GN&C Thermal System Simulation Results

  8. Baseline Concept: Viking Lander • First robotic lander to conduct scientific research on another planet • Total Dry Mass: 576 kg • Science: 91kg (16% of DM) • Dimensions 3 x 2 x 2 m • Power: • 2 RTG • 4 NiCd • Survivability: -90 days expected -V1:6yrs 3mo -V2:3yrs 7mo

  9. Alternative 1 Concept: Cyclops • Single rover landing on wheels • Total Dry Mass: 810.5 kg • Science: 320 kg (40% of DM) • Penetrators • SRV • Single site box • Dimensions 2 x 1.5 x 1 m • Power: • 8 Lithium Ion Batteries • 2 Radioisotope Thermoelectric Generators (RTG) • Solar Cells • Survivability: At least 1 yr

  10. Alternative 2 Concept: Medusa • Stationary lander with rover deployment • Total Dry Mass: 932.8 kg • Science: 195 kg (21% of DM) • Penetrators • Dimensions 2 x 1.5 x 1 m • Rover 1 x 0.5 x 0.5 m • Power: • 8 Lithium Ion Batteries • 3 Radioisotope Thermoelectric Generators (RTG) • Survivability: At least 1 yr

  11. Guidance & Navigation • Viking • Guidance, Control, and Sequencing Computer utilized the flight software to perform guidance, steering, and control from separation to landing • Cyclops • Decent/Landing • An altitude control system will be used to control, navigate, and stabilize while in descent • Post Landing • Operator at mission control navigating rover • Uses a camera system to obtain terrain features of its current environment • Rover orientation will be accomplished by a technique known as Visual Localization • Uses a camera image to determine its change in position in the environment • Medusa • Decent/Landing • An altitude control system will be used to control, navigate, and stabilize while in descent • Post Landing • Ground command inputs to the rover will be provided by onboard planning • Autonomous Path Planning will be used to navigate the rover • Uses a camera system to obtain terrain features of its current environment • Rover orientation will also be accomplished by Visual Localization

  12. Communications • Viking • Communications were accomplished through a two-axis steerable high-gain antenna • A low-gain S-band antenna also extended from the base • Both of these antennas allowed for communication directly with Earth • Cyclops • Surface communications between penetrators and lander/rover will be done using a UHF antenna mounted on the lander/rover • Communications to mission control will be done by using a radio utilizing power amplifiers and medium gain antennas on the lander/rover, which will relay the data back to Earth via LRO • Medusa • Surface communications between penetrators, rover, and Medusa will be done using a UHF antenna mounted on the rover • Communications to mission control will be done by using a radio utilizing power amplifiers and medium gain antennas on the lander, which will relay the data back to Earth via LRO

  13. Structures • Viking • Used a silicon paint to protect the surfaces from Martian dust • Structural frame used lightweight aluminum • Cyclops • Six wheeled rover • Structural frame built from Aluminum 6061-T6 • Lightweight properties • Low cost • Composites (Various components) • Carbon fiber, phenolic, etc. • Excellent thermal insulation • Excellent strength to weight ratio • Lower density • Medusa • Four legged lander • Deployed six wheel rover • Structural frame built from Aluminum 6061-T6 • Composites

  14. Power • Viking • Bioshield Power Assembly (BPA), Power Control and Distribution Assembly (PCDA), Nickel Cadmium batteries, RTG, and Load Banks • Cyclops • PCDA • Load Banks • 8 Lithium Ion Batteries • Best energy to weight ratio • 2 RTG • Constant power supply • Thermal output can be utilized for thermal systems • Solar cells for single site box • Medusa • PCDA • Load Banks • 8 Lithium Ion Batteries • 3 RTG • One RTG is needed for Medusa’s rover

  15. Thermal • Viking • Thermal insulations and coatings, electrical heaters, thermal switches, and water cooling • Cyclops • 2 RTG • Each RTG will deliver a maximum of 7.2 kW of heat • Multi-Layer Insulation • Lightweight • Multiple layers of thin sheets can be added to reduce radiation • Marshall Convergent Coating-1 (MCC-1) • Forms a radiant heat barrier on surfaces that are painted • Medusa • 3 RTG • Utilizes heat output • Multi-Layer Insulation • Marshall Convergent Coating-1 (MCC-1)

  16. Payload • Viking • Gas Chromatography-Mass Spectrometry (GC-MS), camera system, meteorology equipment, seismometer, surface sampler assembly, fluorescent x-ray spectrometer, and magnets • Cyclops • GC-MS • Multi-spectral Imager • Miniature Thermal Emission Spectrometer (Mini-TES) • Single site box • Meteorology equipment • Camera system • Penetrators • Pressure sensors, atmospheric accelerometer, communication equipment, seismometer, meteorology equipment, and surface sampler assembly • SRV • Solar System Research Analysis (SSRA) that includes a boom, collector head, and shroud unit, capable of collecting a variety of material elements • Medusa • GC-MS • Multi-spectral Imager • Miniature Thermal Emission Spectrometer (Mini-TES) • Penetrators • Rover

  17. Operations • Upon reaching the Moon • Decent • CONOPS takes over 5km from lunar surface • Upon decent, shoot 15 penetrators into permanently dark regions of the moon • Dark regions in the Shackleton crater • Landing • Drop off “sample box” for single site goals • Micrometeorite flux • Lighting conditions • Assess electrostatic dust levitation and its correlation with lighting conditions • Have 14 days of guaranteed light conditions • Lunar Surface Mobility • Have rover move to the rim of the Shackleton crater • Have the penetrators relay the data to the rover • The rover will send the data to LRO • Send data from LRO to mission control • Visit lit regions and collect samples • Relay data to mission control via LRO • The Cyclops SRV will take samples and send to Earth

  18. Selection of Final Concept 560

  19. Phase 3 Planning • Key Issues to Address • TRL of 9 vs. New Technology • Penetrators • Meets all challenges • Design basis is new • Expectations • Provide innovative ideas that meet or exceed the base requirements set out by the team • Partner Tasks • ESTACA • Sample Return Vehicle • Southern University • Mobility

  20. Phase 3 Schedule • Subsystems • Each subsystem must develop a unique design that best fits the requirements for the chosen concept • Design Critical systems • Con-ops • Reliant on subsystems to provide direction for daily tasks • GN&C • Reliant on subsystems to provide basis for equipment needed • System Integration • Systems will be reviewed for feasibility • Compromises will be made on each design to create the most beneficial product

  21. Conclusions • The best design Cyclops • “There’s no place this thing can’t go!” • Provide superior functionality and reliability • Develop innovative and cutting edge ideas and designs to overcome the objectives • Concerns of penetrator use and trajectory

  22. Questions

More Related