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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

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Lunar Exploration Transportation System (LETS)

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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

Phase 2 Presentation

3/6/08


Team disciplines

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


Agenda

Agenda

Abstract

Phase 2 Overview

Design Process Outline

Concepts

Subsystems of Concepts

  • Selection of Final Concept

  • Phase 3 Planning

  • Phase 3 Schedule

  • Conclusions

  • Questions


Abstract

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.


Phase 2 overview

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


Phase 2 overview cont

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


Design process outline

Design Process Outline

CDD/Customer

Project Office

Systems Engineer

Structures

Power

Mobility

Sample Return

Payloads

Operations

GN&C

Thermal

System Simulation

Results


Baseline concept viking lander

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


Alternative 1 concept cyclops

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


Alternative 2 concept medusa

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


Guidance navigation

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


Communications

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


Structures

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


Power

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


Thermal

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)


Payload

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


Operations

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


Selection of final concept

Selection of Final Concept

560


Phase 3 planning

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


Phase 3 schedule

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


Conclusions

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


Questions

Questions


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