LETS Phase 3 Review4/29/08

Agenda

• Team Introduction• Daedalus Concept• Concept of Operations• Subsystem Overview • Daedalus Performance• Daedalus Vision• Public Outreach• Questions

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 Whitmore

• Sample Return Vehicle Design– ESTACA

• Julie Monszajin• Sebastien Bouvet

CDD Requirements• Landed Mass 997.4 kg• 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).

Daedalus Lander

1.The Need

2.The Mission

3.The Solution

Daedalus Lander•Simple, Adaptable, Autonomous Lander

•Solar Cell and Li-Ion Battery Power

•Semi-passive Thermal System

•Ka-Band and UHF Communications System

•Lunar Penetrator Exploration System (LPES) “Fire and Forget”

Daedalus Heritage

Structure based on Viking Lander

Communication based on MER

Power System based on Mars

Phoenix & Venus Express

DSMAC Technology for

GN&C based on Cruise Missile

Daedalus Mass Statement

Concept of Operations

LPESPayload•Micro-Seismometers

•Impact Accelerometer and Tilt Sensors

•Heat Flow Probe

•Geochemistry Package

•Water/Volatiles Detector

Design Requirements•1-1.2 Year Lifetime

•Impact Velocity: ~350 m/s

•Impact Force: ~4500 G’s

•Impact Depth: 1~2 m

•Scatter Distance: 500 m Penetration WebESTIMATED PENETRATOR SIZE

•Length: 480mm to 600mm

•Diameter: 60mm

•Estimated Mass: 14kg

LPES•22 Penetrators

•16 Launched into Shackleton Crater

•6 Launched into Lighted Region

•Spring-Loaded Ejection System

Daedalus ScienceDaedalus Payload Mass kg Power W Stereo imaging system or Radar or Lidar 0.8 6 Mast for stereo imaging system 3.5 9.5 Drill and drill deployment mechanism 20 30 Arm 13 43 Scoop 0.5 0 Mass Spectrometer 19 75 Geotechnical Experiments - cone penetrometer 1.5 0 Geotech - bearing plate 1 0 Geotech - shear vane 0.5 0 Magnets 0.5 0 XRD/XRF 2 10 Total 62.3 173.5 Estimated 168

Basic Requirements for Single Site Science Box:Determine Lighting conditions every 2 hours over the course of one yearStudy Micrometeorite fluxObserve Electrostatic dust levitation and its correlation with lighting conditions

Daedalus Power• Lithium Ion Batteries

– Total of 9 Sony 1860HC – Total mass of 42.24 kg– Total Volume of 1.341 ft^3

• Solar Cells– Total of 3 Gallium Arsenide Panels– Total mass of 46 kg– Total Surface area of 6.161 ft^3– Total Power of 937 Watts

• Power Regulation and Control– 6 Auxiliary Power Regulators. 2 per Solar Cell – 1 Battery Charge/Discharge Regulator per battery– ON Semiconductor LM350 Positive Voltage Regulators– STM Microelectronix ST0269 Digital Signal/Microprocessor– Crydom CMX60D10 Solid State Relays

Daedalus Thermal

Passive Systems

• Paints- White and Black

• MLI Blankets

– 15 Layers, Betacloth, Aluminized Kapton

• Thermal Switches

– Diaphragm Thin Plate Switch

• High Conductance Cold Plate

Active Systems

• Solid-State Controlled Heaters

• Variable Radioisotope Heater Units

– 50 Units Provide about 50 W of Heat

• Variable Conductance Heat Pipes

– Aluminum with Ammonia Working Fluid

GN&C

Guidance Computer

ACS

Main Engine

Inertial Measurement

Unit

LiDAR

Long Range Optical Camera

Attitude thrust commands

Altitude thrust commands

high res photograph

Altitude signal

Surface terrain signals

attitude signals

Accelerometer signals

relative vel signal

•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

Daedalus Communications

Earth Receiver and Transmitter

Lunar Penetrators

LRO

Penetrators to LRO using UHF

Data Rate: 2 Kbps

LRO to Earth using Ka-band

Data Rate: 100 Mbps

Daedalus to LRO using Ka-Band

Data Rate: 100 Mbps

View Time: 1 Hour per Day (approx)

Daedalus

Daedalus Structures

To simulate loads experienced at landing a 8200 Newton load was applied to the foot of the leg assembly. These loads were then transferred to the chassisResults indicate the minimum Factor of Safety is 1.15

Daedalus Structures

To simulate loads experienced at takeoff a 54000 Newton load was applied to the payload adapter ringResults indicate the minimum Factor of Safety is 1.3

Daedalus PerformanceFigures of Merit Goal Daedalus

Number of surface objectives accomplished

15 Samples in permanent dark and 5 samples in lighted

terrain

16 Samples in permanent dark and 7 samples in lighted

terrain

Percentage of mass allocated to payload

Higher is better 40% of Dry Mass

Ratio of objectives (SMD to ESMD) validation

2 to 1 1.95 to 1

Efficiency of getting data in stakeholders hands vs. capability of mission

Higher is better 83.5 %

Percentage of mass allocated to power system

Lower is better 14% of Dry Mass

Ratio of off-the-shelf hardware to new

development hardware Higher is better 1.67 to 1

Daedalus Vision

1970 1980 1990 2000

Mariner

7 & 9

Viking

1 & 2

Mars Global Surveyor

Mars Pathfinder

2001 Mars Odyssey

Mars Express Orbiter

Mars Exploration

Rovers

Mars Reconnaissance

Orbiter

Mars Phoenix Lander

Mars Science Laboratory

Present

Mars Exploration Roadmap

Daedalus Vision

Proposed LPRP Timeline Using Daedalus

LCS

(2011)

LCROSS

(2008)

LRO

(2008)

Daedalus I

(2012)

Daedalus II

(2014)

Daedalus Vision

Daedalus I• Mission to Shackleton

Crater• Lunar South Pole

Reconnaissance achieved by LPES

• Single Site Science Conducted

Daedalus II• Return Mission to

Shackleton Crater• Further Investigation

based on LPES findings

• Robotic Rover and Sample Return Vehicle Capability

Daedalus Vision

•Provide a basic, yet powerful and adaptable Lunar Exploration Transportation System

•Build upon the design practices and valuable data collected

•Evolve the Daedalus to accomplish each mission

•Provide a Low-Cost Solution for LPRP

This is the Vision for Daedalus…. and the Mission of

LunaTech

Public Outreach

• Union Hill School• May 8, 2008• 4th Grade• Presentation about

the Moon, LPRP and Daedalus

• Launch a Model Rocket

Questions

Thermal Backup 1MAE 491 Preliminary Calculations for Thermal Control SubsytemLETS Design, Team LunatechGreg Barnett

Ambient Temperature: -173 degC

Worst-Case Cold Scenario

1-D, Steady State Analysis

Information: kal 185.2watt

m K tins 1in tal

1

8in Ti 20 273( )K L 6in

kins_eff 2.5 105

BTU

hr ft R kins_eff 4.327 10

5watt

m K To 110K Tinf 100K

Tsur 100K Eheater 80watt A 20.5m2 tins 0.025m tal 3.175 10

3 m

Calculation of Cross-Sectional Area of Supports: Assumed 8 aluminum rods of 0.25in radius

r 0.25in Arod r2 rods 8 Ac Arod rods

Ac 1.013 103 m

2 Cross-Section of all supports

Thermal Backup 2

Effective Emittance:

fA1

100.373 log 3( )

fA 0.664 fN 1.164 For 15 layers

fP 1.322 For 2% Penetrations

Th 293 Tc 130

Tm

3Th

4Tc

4

4 Th Tc Tm 221.489 5.67108

eff 0.0001361

4 Tm2

0.000121Tm0.667

fN fA fP eff 0.017

Thermal Resistance: Rtotal

tal

kal A

tins

kins_eff A Rtotal 28.636

K

watt 5.6710

8watt

m2

K4

Thermal Backup 3

Energy Balance:

ERHU 50watt

Given

Ti To

Rtotaleff A To

4Tsur

4

Eheater ERHUTi To

Rtotalkal Ac

Ti To

L

To

Eheater

Find To Eheater To 134 C Temperature of outside surface

Erequired Eheater

Erequired 145watt Power required to maintain 20C inside vehicle

Thermal Backup 4

MAE 491 Preliminary Calculations for Thermal Control SubsytemLETS Design, Team LunatechGreg Barnett

Ambient Temperature: 100 degC / 373 K

Worst-Case Hot Scenario

1-D, Steady State Analysis

Albedo Assumed Negligible

Information: kal 185.2watt

m K tins 1in tal

1

8in L 6in Gsolar 1368

watt

m2

kins_eff 2.5 105

BTU

hr ft R kins_eff 4.327 10

5watt

m K Ti 20 273( )K Tsur 373K

A 20.5m2 tins 0.025m tal 3.175 10

3 m mli 0.15 mli 1 mli Atop 6.25m2

Thermal Backup 5

Effective Emittance for MLI:

fA1

100.373 log 3( )

fA 0.664 fN 1.164 For 15 layers

fP 1.322 For 2% Penetrations

Th 373 Tc 293 Hot and Cold Side Temperatures

Tm

3Th

4Tc

4

4 Th Tc Tm 334.594 5.67108

eff 0.0001361

4 Tm2

0.000121Tm0.667

fN fA fP eff 0.011

Thermal Resistancefor Conduction:

Rtotal

tal

kal A

tins

kins_eff A Rtotal 28.636

K

watt 5.6710

8watt

m2

K4

Thermal Backup 6Energy Balance:

To 400K

ERHU 50watt

EVCHP 150watt

Given

To Ti

RtotalmliGsolar Atop eff A To

4Tsur

4

ERHU

To Ti

Rtotal EVCHP

To

EVCHP

Find To EVCHP To 311C Temperature of outside surface

EVCHP 60watt Power that must be removed from cabin by VCHPs tomaintain 20 degC