Lunar Exploration Transportation System (LETS) MAE 491 / 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 –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

Overview Mission Statement The Need The Solution Performance Schedule Operations Structures GN&C Communications Payload Power Thermal Risk Management Mass Allocations Figures of Merit Conclusions Questions

Mission Statement Team Frankenstein’s mission is to provide NASA with a reliable and multi-faceted lander design that will provide the flexibility to conduct CDD requirements, scientific investigations, and technology validation tasks at different areas on the moon.

The Need Only 6% of lunar surface explored –Apollo missions Only orbital visits since Apollo Mobile lunar laboratory with return capabilities is vital to the exploration and understanding of the lunar surface The lunar surface is an unexploited record of the history of the solar system Sample polar sites and crater floors

The Solution Lander/Rover Penetrators RTG Cyclops

Performance CDD RequirementRequirementAssessmentRemark Landed Mass932.8 kgActually 785 kg (16% mass margin) Survive Lunar Cruise28 daysCapable of surviving lunar cruise exceeding 28 days Operational Period1 yearTRL 9 materials will remain functional at least 1 year Sample Lunar Surface 15 dark 5 lightedMobility allows roving to as many sites as needed Communication Send and Receive (real time)Capable of sending data at 150 Mbps Landing Parameters12º slope within 100 m Six wheel rocker bogie system allows landing on slopes greater than 12 degrees Survive Launch of 6 G's6 G'sCyclops structure will handle g-loads exceeding 6 g’s Technology RequirementsTRL 9Materials used are TRL 9 Power Requirements Store Power in Dark ConditionsRTG can provide the power needed during dark conditions Thermal Conditions Survive Temperature Changes Materials used will withstand temperatures exceeding the 50K to 380K range Sample Return VehicleSample Return (Goal)Meets the sample return expectations Mobile Roving/Real-Time Mobility6 wheel rocker bogie allows roving in real-time Exceeds -Meets -

Schedule

Operations Cyclops Penetrators 2.5km 1.6km 1. 5km 2. Deploy Penetrators 3-4. Decent 5. Land 6. Release Propulsion System 7. Rove To Edge of Crater

Structures System Specifications (Auxiliary Systems) Penetrator Ring Platform –Outer Diameter m –Aluminum Construction (6061 T6) –Mounted penetrators (spring released at a 4 degree dispersion angle) Attitude Control –Main thrusters - MR 80B –Attitude Control Thrusters - MR 106 –Hydrazine Tank x m Outer Diameter –Aluminum Frame (6061 T6) Single Site Box –Max Box Dimensions x x m –Integrated Sample Return Vehicle Penetrator Ring Platform Attitude Control System Cyclops

Structures System Specifications (Main) –Main Chassis Dimensions – 1.54 x 1.54 x m Aluminum Frame (6061 T6) Carbon composite exterior MLI Insulation –6 Wheel Passive Rocker Bogie Mobility System Proven Transportation Platform (MER, Pathfinder) 0.33 m Outer Diameter Wheels Can navigate up to a 45 degree angle Max speed of 75 m/hr Aluminum construction (6061 T6) Maxon EC 60 Brushless DC motor (60mm) x 6 Maxon EC 45 Brushless DC motor (45mm) x 8 –Camera (SSI) Dimensions x x m –Scoop Arm Max Reach m Before Deployment After Deployment

Structures Maxon 60mm EC 60 x 6 Nominal torque 830 mNm Maxon 45mm EC 45 x 8 Nominal torque 310 mNm Wheel MotorsSteering Motors

GN&C Decent/Landing –A LIDAR system will be used to control, navigate, and stabilize while in descent Post Landing –An operator at mission control will manually navigate lander/rover A Surface Stereo Imager (SSI) periscopic, panoramic camera will be used to survey the lunar surface, provide range maps in support of sampling operations, and to make lunar dust cloud measurements

GN&C Descent Imaging –A Mars Descent Imager (MARDI) will be used to view both the penetrator dispersion and the landing/descent of the Cyclops Processor –A BAE RAD750 will be used for all controls processing

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

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: 35 kg –Dimensions: 155 x 68.5 x 35.5 cm –Power: Solar Panel (7.8 W)

Payload Gas Chromatograph Mass Spectrometer (GCMS) –Performs atmospheric and organic analysis of the lunar surface –Mass: 19 kg –Dimensions: 10 x 10 x 8 cm –Power: Rover (60 W) 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: 110 x 10 x 10 cm –Power: Rover (3.5 W)

Payload Miniature Thermal Emission Spectrometer (Mini-TES) –Objective is to provide measurements of minerals and thermo physical properties on the moon –Mass: 2.4 kg –Dimensions: 23.5 x 16.3 x 15.5 cm –Power: Rover (5.6 W) Penetrators (Deep Space 2 ) –Mission’s main source of data acquisition in the permanent dark regions –Mass (15 Penetrators): kg –Dimensions: 13.6D x 10L cm –Power: 2 Lithium Ion Batteries Each (0.3 W)

Power RTG –TRL 9 –Constant power supply –Thermal output can be utilized for thermal systems Lithium-Ion Batteries –Commercially available –Easily customizable –Rechargeable Solar Cell –Used for Single Site Box –Conventional –Increasingly efficient in well light areas POWER SUBSYSTEM Type (solar, battery, RTG)Solar, Lithium-ion, RTG Total mass63.62 kg Total power required W Number of solar arrays1 Solar array mass/solar array1.13 kg Solar array area/solar array0.12 square meter Number of batteries2 Battery mass/battery3.25 kg Number of RTGs1 RTG Mass/RTG56 kg

Power Power Analysis ComponentSubcomponentsConsumption (W) Mobility SRV 1 GN&C Payload 76.9 Communications 70.8 Thermal 55 Totals Power Supply RTG300 Li-ion Battery975 W-h Solar Cell10 W Total Power Required – W Peak Power –Roving Mobility, GN&C, and Thermal W –Data Collection/Transfer All subsystems except mobility W –Single Sight Box/Sample Return Vehicle 8.8 W RTG (Cassini) –300 W Lithium-Ion Batteries –975 W-h for both Solar Cells –10 W (SSB and SRV) 7% RTG Contingency Power Total Power Supplied to Lander –300 W constant supply –975 W-h for peak power outputs

Thermal Cyclops uses three forms of heat control –Heat transfer pipes –Paraffin heat switches Radiator heat switches Diaphragm heat switches –Multi-Layer Insulation

Thermal Two standard types of switches are used as a redundant check to prevent over heating

Thermal Heat is well controlled –MLI has low heat absorbance –Heat switches allow close tolerance control

Risk Management LIKELIHOODLIKELIHOOD CONSEQUENCES Likelihood 1improbable 2 3probable 4 5definite Consequences 1 the mission can still be completed 2 3 mission operates at limited capacity 4 5 total mission failure

Mass Allocations SystemMass (kg)Percent Mass GN&C23.53% Payload % Communications202.5% Thermal % Power Supply648.2% Structures % Mobility % Total Mass785 kg100%

Figures of Merit Figure of MeritGoalDesign Number of surface objectives accomplished 15 samples in permanent dark 5 samples in lighted terrain 15 penetrators taking samples in permanent dark and 5 lighted samples taken by Cyclops Percentage of mass allocated to payloadHigher is better35.4% Ratio of objectives (SMD to ESMD) validation2 to 14 to 1 Efficiency of getting data in stakeholders hands vs. capability of missionHigher is better95% Percentage of mass allocated to power systemLower is better8.2% Ratio of off-the-shelf hardware to new development hardwareHigher is better85%

Conclusions “There’s no place this thing can’t go” If penetrators fail, remaining mission will not be compromised Reliable multi-faceted design

Questions