Lunar Exploration Transportation System (LETS) Baseline Design Presentation 1/31/08

Agenda Current CDD Summary Team Disciplines Technical Description of Baseline Design Assessment of Baseline Design using CDD Recommended Changes to the CDD Statement of Work (SOW) Summary

Team Disciplines CDD Team Technical Assessment Team Eddie Kiessling Technical Assessment Team Nick Case and Matthew Isbell Partnering Universities Team (SOW) Seth Farrington

CDD Summary Level 1 Requirements Figures of Merit Surface Objectives Concept Design Constraints

Level 1 Requirements Landed Mass TBD 1st mission landing site is polar region Design must be capable of landing at other lunar locations Minimize cost across design Launch Date NLT September 30th 2012 Mobility is required to meet objectives Survivability ≥ 1 year Lander/Rover must survive conops. The mission shall be capable of meeting both SMD and ESMD objectives. The lander must land to a precision of ± 100m 3 sigma of the predicted location. The lander must be capable of landing at a slope of 12 degrees (slope between highest elevated leg of landing gear and lowest elevated leg) The lander shall be designed for g-loads during lunar landing not to exceed the worst case design loads for any other phase of the mission (launch to terminal descent). 5

Proposed FOMs Surface exploration Maximized Payload Mass (% of total mass) Objectives Validation: Ratio of SMD to ESMD: 2 to 1. Conops: Efficiency of getting data in stakeholders hands vs. capability of mission. Mass of Power System: % of total mass. Ratio of off-the-shelf to new Development Minimize cost 6

Surface Objectives Single site goals: Mobility goals: Geologic context Determine lighting conditions every 2 hours over the course of one year Determine micrometeorite flux Assess electrostatic dust levitation and its correlation with lighting conditions Mobility goals: Independent measurement of 15 samples in permanent dark and 5 samples in lighted terrain Each sampling site must be separated by at least 500 m from every other site Minimum: determine the composition, geotechnical properties and volatile content of the regolith Value added: collect geologic context information for all or selected sites Value added: determine the vertical variation in volatile content at one or more sites Assume each sample site takes 1 earth day to acquire minimal data and generates 300 MB of data Instrument package baselines: Minimal volatile composition and geotechnical properties package, suitable for a penetrometer, surface-only, or down-bore package: 3 kg Enhanced volatile species and elemental composition (e.g. GC-MS): add 5 kg Enhanced geologic characterization (multispectral imager + remote sensing instrument such as Mini-TES or Raman): add 5 kg

Concept Design Constraints Surviving Launch EELV Interface (Atlas 401) Mass Volume Power Communications Environments Guaranteed launch window Survive Cruise Survive Environment Radiation Thermal Micrometeoroids 8

Concept Design Constraints Lunar Environment (@ poles and equator) Radiation Micrometeoroid Temperature Dust Lighting Maximize use of OTS Technology (TRL 9) Mission duration of 1 year Surface Objectives Reference: Dr. Cohen 9

Mars Viking Lander First robotic lander to conduct scientific research on another planet Dry Mass 576 kg Science 91kg Dimensions 3x2x2m Power: 2 RTG 4 NiCd Survivability: -V1:6yrs 3mo -V2:3yrs 7mo

Baseline Assessment Structures Thermal Systems Payload and Communications Power Systems GN&C Concept of Operations

Structures EELV Interface Titan III which delivered the Viking lander is comparable to the Atlas V-401 The lander shall be designed for g-loads during lunar landing not to exceed the worst case design loads for any other phase of the mission (launch to terminal descent). Comparable G-load launch spikes The lander must be capable of landing at a slope of 12 degrees (slope between highest elevated leg of landing gear and lowest elevated leg) Landing platform designs for Viking could also apply to LETS design

Structures Lunar Environment (Radiation, Micrometeoroid, Temperature, Dust) Thermal cycles vary greatly Viking thermal cycles were approx. max 17°F, min -170°F LETS can expect a thermal cycle approx. max 373 K, min 126 K, Resistance to dust abrasion Viking used a silicon paint to protect the surfaces from Martian dust LETS could use a similar product Landed Mass (TBD) Viking required a bio-shield and a aero-decelerator LETS will not require these items Viking structural frame used lightweight aluminum LETS could benefit from major advances made in materials

Thermal Systems Viking Thermal System Passive Geometry Internal thermally controlled compartment Structurally integrated thermal sinks Increased or Decreased Surface Area where applicable Thermal Coatings Proper infrared emittance Proper solar absorbance Thermal Compartment Critical equipment will be housed in compartment Temperature will be dependent upon operating temperatures of critical equipment Insulation Thermal control between equipment and environment Radiation shield Active Heaters Continuous operation Thermostatically controlled Redundant systems

Thermal Systems LETS Thermal System Different Thermal Cycles Heaters and Insulation changes to accommodate different thermal cycles Statically charged lunar dust increases the absorptance of radiator surfaces Use of polarized surfaces/coatings to reduce lunar dust accumulation

Payload and Mobility Scientific Options Measure 15 samples in the dark and 5 samples in light. The Viking Lander did not move, but it used an SSRA with a boom, collector head, and shroud unit, capable of collecting a variety of material elements. Each sampling site separated by 500 m. The Viking Lander did not have this capability. Determine composition, geotechnical properties, and volatile content of regolith. The Viking Lander used an X-ray Fluorescent Spectrometer (XRFS) to perform a chemical analysis. Enhanced geological characterization (multi-spectral imager & remote sensing instrument). The XRFS plus a remote sensing instrument may be used for this function.

Observation Camera Options Viking Lander camera system Looked at surface and was able to measure optical density of the atmosphere Geologically characterize the surface Look for macroscopic evidence of life LETS camera system Observe electrostatic dust on the horizon Study change in lighting conditions and the effects of surrounding environment Aid in Earth observation and control of data collection

Communication Transmission options Direct transmission used by Viking Relay from Viking Orbiter to Earth UHF linked used to transmit data at speeds of 4000 and 16000bps Transmission Criteria for LETS => 1 Earth day to transmit data Limit of no slower than 4000bps Transmission Path Options Direct transmission from the Moon to Earth Storage of data until DLS is obtained Lunar orbiter to relay data to earth

GN&C The lander must land to a precision of ± 100m 3 sigma of the predicted location. Viking: Orbiter/Lander separation until the Lander was on the Martian surface The propulsion system along with a navigation system consisting of radars, gyros, accelerometers, etc to guide the Lander through Mars atmosphere and a soft accurate landing on the Martian surface. GN&C was not responsible for any operations after landing LETS: Operations will commence upon landing, and will continue for the duration of the mission. The lander must be capable of landing at a slope of 12 degrees GN&C in conjunction with structure will ensure that the Lander can function on a 12 degree slope. Mobility is required to meet objectives GN&C will be responsible for rover and SSR deployment.

Power Systems Operational Period Power Required Systems Viking Mars Lander was 90 days LETS will be 365 days Power Required Systems Viking Lander Telemetry Communication Thermal systems Instrumentation Ascent and descent operations Caution and warning systems Power conditioning Regulate power Power storage LETS will be required to supply power to similar systems

Power Systems Power Supply Options Solar Cell Battery RTG

Power Systems Radioisotope Thermoelectric Generator (RTG) Nuclear Yield: Fuel: Plutonium – 238 Nominal Heat Generation Rate: 682 Watts Weight & Dimensions: 15.4 Kg (34 lbm) 53 cm x 41 cm (23 in x 16 in) Power Output: 35 to 780 Watts

Power Systems Advantages Disadvantages ASRG/SRG (Nuclear) Constant Power Supply Thermal Output can be utilized for thermal systems Requires Fewer Batteries Solar Panels Minimize Cost High Power to Weight Ratio Clean Energy Politically Safe Disadvantages ASRG/SRG (Nuclear) Political Affairs Nuclear Waste Hazardous / Contamination Expensive Solar Panels Degrade Over Time Non-constant Power Supply No Thermal Output Susceptible to Lunar Environmental Conditions Requires Many Batteries

Concept of Operations

Concept of Operations

SOW Committee Statement of Work for Partners Software Communications

Statement of Work ESTACA Southern University (SU) Sample Return Vehicle Southern University (SU) Mobility Concepts

SOW Committee Software Protocols Professional Documents Computer Aided Design (CAD) Unigraphics NX as standard for UAH and Southern University CATIA as standard for ESTACA CAD Translation Options TransMagic MathdataHQ.com Professional Documents MS Office Text Documents – MS Word Spread Sheets – MS Excel Slide Presentation – MS Power Point

SOW Committee Communication Protocols File Sharing Protocols Meetings One meeting per week required Minutes will be required UAH and ESTACA Teleconference, or a web-based video chat UAH and Southern University Video conference, teleconference, or web-based video chat Note: Minute template will be provided File Sharing Protocols WebCT – Primary Basic Email - Secondary

IPT Schedule Spring 2008 Schedules Activity UAH Southern University Classes Start January 7 January 8 MLK Holiday January 21 Mardi Gras Holiday - - - - - - - - January 4-5 Founders Day March 10 Spring Break March 17-23 March 17-24 Last Day of Classes April 22 April 25

CDD Recommendations No Recommended Changes

Questions?