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. 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. 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. 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. 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 Specification Summary –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. 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. 7 Design Process Outline Results System Simulation CDD/Customer Project Office Systems Engineer Thermal Power GN&COperationsPayloads StructuresMobilitySample Return

8. 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. 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. 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. 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. 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. 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. 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. 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. 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. 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. 18 Selection of Final Concept 560

19. 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. 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. 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. 22 Questions