Lunar Exploration Transportation System LETS MAE 491 492

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 1

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 2

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

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, ability of mobility, etc. 4

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 5

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 6

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

Baseline Concept: Viking Lander • First robotic lander to conduct scientific research on another planet • Total Dry Mass: 576 kg • Science: 91 kg (16% of DM) • Dimensions 3 x 2 m • Power: – 2 RTG – 4 Ni. Cd • Survivability: -90 days expected -V 1: 6 yrs 3 mo -V 2: 3 yrs 7 mo 8

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 9

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 m • Power: – 8 Lithium Ion Batteries – 3 Radioisotope Thermoelectric Generators (RTG) • Survivability: At least 1 yr 10

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 11

Communications – A UHF antenna will provide surface communications for the Lander/Rover – Communications to mission control will be done by medium gain S-Band antennas on the lander/rover 12

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 -T 6 • Lightweight properties • Low cost – Composites • 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 -T 6 Composites 13

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 • Slow loss of charge – 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 14

Thermal • Viking – Thermal insulations and coatings, electrical heaters, thermal switches, and water cooling • Cyclops – 2 RTG • Each RTG will deliver a maximum of 7200 W 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 – Multi-Layer Insulation – Marshall Convergent Coating-1 (MCC-1) 15

Payload – Gas Chromatography-Mass Spectrometry – Multi-spectral Imager – Miniature Thermal Emission Spectrometer – Single site box – Penetrators 16

Operations • Upon reaching the Moon – Decent • CONOPS takes over 5 km 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 lander will relay the information to the LRO when not in direct line of site with mission control – The sample return vehicle will take a sample and send it back to Earth 17

Selection of Final Concept 18

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 19

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 20

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 21

Questions 22