LETS Phase 2 Review 3/6/08

Agenda Team Introduction Overview of Design Process Initial Mass and Power Budgets Trade Tree and Trade Study Concept Overviews Final Concept Selection Final Concept Overview

Team LunaTech Nick Case, Project Manager Morris Morell, Systems Engineer Travis Morris, GN&C Greg Barnett, Thermal Systems Adam Garnick, Power Systems Katherine Tyler, Power Systems Tommy Stewart, Structures and Mechanisms Julius Richardson, Conops John Grose, Payload and Communications Adam Fanning, Communications Eric Brown, Technical Editor

Partners Mobility Concepts –Southern University Robert Danso McArthur Robinson Sample Return Vehicle Design –ESTACA Julie Monszajin Sebastien Bouvet

Concept Design Process CDD/Customer Project Office Subsystems Experts Research Trade Tree Trade Study Engineering Analysis Subsystem Interaction Concept Design

Initial Mass Budget Given Mass Values from CDD SystemMass (kg)% of Total Mass Total Landed Mass Propulsion Dry Mass Propellant Mass Helium20.20 Sample Return Vehicle Lander Dry Mass Initial Mass Budget Derived from Historical Percentages Element of Weight BudgetEst.%of Lander Dry MassEst. Mass Based on Col. (1) (kg) Payload Structures and Mechanisms Thermal537.3 Power GN&C218.7 Communication218.7 Propulsion (dry) Margin (kg) Total Lander Dry Mass

Initial Power Budget Given Mass and Power Values for Payload Units UnitMass (kg)Power (W) Stereo Imaging System (SIS) Mast (SIS)0.86 Drill and Drill Deployment2030 Arm1343 Scoop0.70 Penetrator10 Mass Spectrometer1975 XRD/XRF25 Total Initial Power Budget Based on Payload Power Requirements SystemEst. % of Lander PowerEst. Power Based on Col. (1) (W) Total Budget Payload24168 Structures and Mechanisms17 Thermal25175 Power535 GN&C18126 Communication17119 Margin1070 Total100700

Trade Tree DaedalusLunar Prowler

Land On Wheels 2 Radioisotope Thermoelectric Generators (RTG) Drivetrain based on Mars Science Laboratory (MSL) design Optional Sample Return Vehicle (SRV) Launch System Single Site Science Box (SSSB) Remote System

Daedalus Viking-Style Design Solar Powered with Li-Ion Storage Lunar Penetrator Exploration System Optional Rover and SRV Autonomous Lander

Power Branch Lunar Prowler Daedalus

Thermal Branch Lunar Prowler Daedalus

GN&C Branch Lunar Prowler

GN&C Branch Daedalus

Mobility Branch Lunar Prowler Daedalus

Structures Branch Lunar Prowler Daedalus

Payload Branch Lunar Prowler Daedalus

Communication Branch Lunar Prowler Daedalus

Concept Selection Pugh Selection Matrix Legend Exceeds ++ Meets + Doesn't Meet - Design 1Design 2 WeightLunar ProwlerDaedalus Design Criteria Survive One Year10+++ Minimize Cost10-+ Mobility10+++ Ratio of OTS to New Technology10-+ Mass of Power System3-+ Schedule3-+ Efficiency to collect Data3+++ Cability to Land at Other Locations3++- Mass of Payload System1+++ Landing Precision1++ Complexity Total Points 2552

Power Solar Cells and Batteries –Energy Storage with Lithium Ion Batteries –Output power of 900 Watts in sunlight –Output power of 210 Watts in the dark. (Max 623 Watts) –Total mass of approximately 153 kg –Degradation is expected to be only 3%.

Thermal Passive Techniques Thermal control coatings and paints Multi-layered Insulation blankets High and low thermal conductivity materials Component placement Thermal Switches High conductance cold (mounting) plate Active Systems Solid-State controlled heaters Variable Radioisotope Heater Units (VRHUs) Heat Pipes Design Considerations Conductive losses are driven by structural supports Lithium-ion batteries generate large amount of heat Available space for radiator Cost VRHU Operation Effect of Structural Support Cross-Sectional Area on Heater Power Required

GN&C Provides Completely Autonomous Landing sequence Very Precise landing location Landing location determined before launch Hazard Avoidance Objective: To deliver Daedalus from 5km altitude safely and accurately to the lunar surface

Structures Honeycomb Aluminum Payload Base Honeycomb Aluminum Crush Pads Thermal Compartment High Strength Aluminum or Titanium Folding Landing Legs Atlas Launch Adapter Fitting

Communications Earth Receiver and Transmitter Daedalus Rover Lunar Penetrators LRO Direct Line of Sight Daedalus to Earth high and low gain antenna Daedalus to Rover using S-band Penetrators to LRO using S-band LRO to Earth using Ka-band Daedalus to LRO using S-band Est. 60% visibility time

Penetrator Concept Deep Space 2 Penetrators –2.4 kg –Impact at ~ 180 m/s –Designed to penetrate ~.3 m to 1 m –Science Collects soil sample Analyze for water Properties of soil from temperature sensors Estimate hardness of soil –Communicate with LRO using X-band Launched from lander using light gas gun, after landing

Questions

Power Backup Slide 1 FOR ESTIMATION OF 623 WATTS –14 days = 336 hours –Systems running at 100% during darkness are power and thermal –Estimating 10% duty cycle –Systems running at 1% during darkness are Payload, Communication, and GN&C –estimate 1% duty cycle –Initial approximation of Watts for each system Power – 35 W Thermal – 175 W Payload – 168 W Communications – 119 W GN&C – 126 W –The following calculation gives the amount of power for all systems during the darkness –Total amount of power = 623 Watts

Power Backup Slide 2 Mass of Solar Array (with an estimated specific performance of 25 W/Kg) Mass of Power Control Unit Mass of Regulator/Converter Unit (estimated at 20% of full power, which is converted power) Total Support System Mass = 76.5 kg For Lithium-Ion Batteriesmass = kg Total Mass System is approximately 153 kg

Power Backup Slide 3 From AIAA book, page 315 –Degradation 30% over 10 year life The calculation for solar cell area is based upon a 7% efficiency Cost of System –Estimation of cost is between $800 – $3000 / Watt –The estimation for Daedelus is $2500 / Watt –Cost is $2.25M Dollars

Thermal Backup Slide 1

Thermal Backup Slide 2 Power required will be affected significantly based on the following variables: Penetrations and seems in MLI blankets Internally generated heat due to batteries and components in operation Amount of conductive losses

Thermal Backup Slide 3 Linear relationship Assumed aluminum rod struts with 1cm diameter Cross-section will change and will vary based upon Amount of struts used and components needed to mount Materials used (varying thermal conductivities)

Payload ElementObjectiveMass (kg)Mass with 30% Margin (kg) Power (W)Power 30% Margin (W) Stereo imaging system OR Radar OR Lidar Acquire images of surface for geology, topography and navigation Mast for stereo imaging systemProvide elevation for imaging Drill and drill deployment mechanism Recover regolith samples from depths of 2 m Belly CamImaging of drill interface with surface ArmDeploy instruments, conduct geotechnical experiments, collect regolith samples ScoopRecover surface regolith samples to a depth of TBD cm Mass SpectrometerDetermine the various volatile compounds present and their isotopic composition Sample processing system for MS Process core or scoop material for analysis. Neutron SpectrometerDetermine the flux and energies of neutrons to determine H content of regolith Geotechnical Experiments - cone penetrometer (3) End effector for geotech properties Geotech - bearing plateEnd effector for geotech properties Geotech - shear vaneEnd effector for geotech properties MagnetsDetermine magnetism of regolith particles XRD / XRFMineralogy and chemistry of regolith BeaconNavigation reference Payload Inventory

Scientific Sites –Single site 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

STRUCTURES MATERIAL DENSITY (kg/m^3) YOUNG'S MODULUS (Gpa) YIELD STRENGTH (Mpa) THERMAL EXPANSION (  m/m*K) 6061 T6 Al T6 Al AL4V Ti KEVLAR /EPOXY