technology applications assessment team
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Technology Applications Assessment Team
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Non –
Atmospheric
Universal
Transport
Intended for
Lengthy
United
Space
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X-ploration
M.L. Holderman JSC/SSP
Multi-Mission Space Exploration Vehicle
Technology Applications Assessment Team
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Multi-Mission Space Exploration Vehicle
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NAUTI - LEM NAUTI - LEM (Lunar Excursion Module)
The most successfuland versatile “spacecraft”ever built…
• Not a capsule• Not an Orbiter• Designed ONLY for operation in the unique environment of SPACE
Multi-Mission Space Exploration Vehicle
M.L. HoldermanJSC/SSP
Description and Objectives:
Justification:Approach:
Collaborators/Roles:
• Provides Order-of-Magnitude increase in long duration journey capability for sizeable Human Crews
• Exploration & Discovery• Science Packages
• Supports HEDS 2.2.4.2 Habitat Evolution technology development
• Meets the requirement of Sec. 303 MULTIPURPOSE CREW VEHICLE Title III Expansion of Human Space Flight Beyond the International Space Station and Low-Earth Orbit, of the “National Aeronautics and Space Administration Authorization Act of 2010”
• Long-duration space journey vehicle for crew of 6 for periods of 1 -24 months
• CIS-lunar would be initial Ops Zone [shakedown phase]• Exo-atmospheric, Space-only vehicle• Integrated Centrifuge for Crew Health• ECLSS in deployed Large Volume w/ shirt-sleeve servicing• Truss & Stringer thrust-load distribution concept (non-orthogird)• Capable of utilizing variety of Mission-Specific Propulsion Units [integrated in LEO, semi-autonomously]• Utilizes Inflatable & Deployed structures• Incorporates Industrial Airlock for construction/maintenance
• Integrated RMS• Supports Crewed Celestial-body Descent/Return Exploration vehicle(s)• Utilizes Orion/Commercial vehicles for crew rotation & Earth return from LEO
• JPL:Deployment Integ., Communications/Data Transmission• AMES: ECLSS, Bio-Hab• GSFC: GN&C, Independent System Integrator• GRC: PowerPumps, PMD, External Ring-flywheel• LaRC: Hoberman deployed structures & Trusses• MSFC: Propulsion Unit(s) & Integration platform , Fluids Transfer & Mngt.• JSC: Proj. Mngt – SE&I , ECLSS, Centrifuge, Structures, Avionics, GN&C, Software, Logistics Modules• NASA HQTRS: Legislative & International Lead COST: $ 3.7 B DCT & Implementation 64 months
• Multiple HLV (2-3) & Commercial ELV launches• On-orbit LEO Integration/Construction• First HLV payload provides Operational, self-supporting Core• Centrifuge utilizes both inflatable & deployed structures • Aero Braking deployed from Propulsion Integration Platform
M.L. HoldermanJSC/SSP
Non
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- X-
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Technology Applications Assessment Team
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Technology Applications Assessment Team
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M.L. Holderman JSC/SSP
Multi-Mission Space Exploration Vehicle
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Technology Applications Assessment Team
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•Fully exo-atmospheric/Space-only • No entry capability through Earth’s Atmosphere
• Accommodate & Support Crew of 6
• Self-sustaining for months (1-24) of Operation
• Ability to Dock, Berth and/or Interface with ISS & Orion
• Self-reliant Space-Journey capability
• On-orbit semi-autonomous integration of a variety of Mission-specific Propulsion-Units
Multi-Mission Space Exploration Vehicle
M.L. Holderman JSC/SSP
System Goals
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Technology Applications Assessment Team
Multi-Mission Space Exploration Vehicle
• Large volume for logistical stores• FOOD• Medical• Parts• Other
• Provide Artificial Gravity/ Partial(g) for Crew Health & GN&C
• Provide real-time “true” visual Command & Observe capability for Crew
• Capability to mitigate Space Radiation environment
• Ability to semi-autonomously integrate Mission Specific Propulsion-Pods
• Docking capability with CEV/Orion/EAT(European Auto Transfer)/Other
• Robust ECLS System• IVA based for service/maintenance
M.L. Holderman JSC/SSP
Attributes
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Technology Applications Assessment Team
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M.L. Holderman JSC/SSP
Multi-Mission Space Exploration Vehicle
•Robust Communications Suite
• Designed for wide array of Thrust/Isp input(s)• Ion-class• Low level, Long Duration chemical
• Self powered• PV array• Solar Dynamic
• Industrial sized Airlock supports MMU[Manned Maneuvering Unit] • Logistical Point-of-Entry• Intermediate staging point for EVA
• External scientific payloads • Pre-configured support points
• Power, Temp, Data, Command & Control
Attributes
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Technology Applications Assessment Team
Multi-Mission Space Exploration Vehicle
Technology Development • Autonomous Rendezvous & Integration of LARGE structures
• Artificial Gravity/Partial-(g)• Basic design• System Integration and GN&C Impacts & Assessments• Materials• Hub design
• Seals• Carriage Design• Bearings
• Power transfer mechanisms• Flywheel torque-offset
• External dynamic Ring-flywheel• CMG cluster(s)
• Semi-autonomous Integration of MULTIPLE Propulsion Units• Mission SPECIFIC
• Next generation MMU [old free-flyer MMMSS]
• Inflatable and/or Deployable module/structure design(s) • Transhab & Hoberman
M.L. Holderman JSC/SSPNAUTILUS - NAUTILUS -
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Technology Applications Assessment Team
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M.L. Holderman JSC/SSP
•High-gain/High-power Communications
• Radiation mitigation • Structural Integrated• Magnetic Field strategy (MIT)• Individual application augmentation
• Suits & Pods• Safe-Zone [H20/H2-slush strategy]
• Thrust structure integration through-out vehicle and across orbital assembly interfaces
• Deployable exo-truss
• O-(g) & Partial-(g) hydroponics/agriculture
• ECLSS { IVA Maintenance, R&R }• Active membranes• Revitalization methodologies• Atmosphere Circulation • Temperature control• Humidity control
Technology Development
Multi-Mission Space Exploration Vehicle
NAUTILUS - NAUTILUS - XX
M.L. HoldermanJSC/SSP
Full Operational Status: CIS-Lunar & NEO Mission
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Industrial Airlock slide-out Unit
Command/Control &Observation Deck
Multi-Mission Space Exploration Vehicle
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Orion &Commercial Docking Port
PV Array deployed: Core Module
- 6.5m -
14m
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Completed Centrifuge w/ External Flywheel
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Multi-Mission Space Exploration Vehicle
External “Dynamic” Ring-flywheel
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Start-up Thrusters
Hoberman Circumferential Stabilizing Ring(s)
Soft-wall Inflatablesection(s)
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View looking “Forward”
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Multi-Mission Space Exploration Vehicle
NAUTILUS - NAUTILUS - XX
Solar Electric Propulsion Spin out
L1 MMSEVDEPOTLife Boat/Living QuartersStaging location/HospitalWaiting for engines to go to MARS
INSITU (ICE, water)
Lunar Exploration
Crew Transfer
Technology Applications Assessment Team
M.L. HoldermanJSC/SSP
Multi-Mission Space Exploration Vehicle
Initial Operation(s) Concept
NAUTILUS - NAUTILUS - XX
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Multi-Mission Space Exploration Vehicle Technology Applications Assessment TeamT
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Development Challenges
• Potential parallel development with HLV• Resource allocation
• HLV Payload integration•Ascent Vibro-Accoustic P/L environment(s)• Mass growth• Battery performance
• Centrifuge Hub • Torque off-set S/W & external ring flywheel• GN&C impacts [modeling]• Slip-rings• Drive Mechanism• Seals• Carrier design
• Centrifuge Design• Materials• Deployment mechanism(s): Inflatable Section(s)• Stiffening/Load Structure: Hoberman
• Propulsion Pod Integration Platform• Capture & Latch mechanisms• Data/Telemetry/Command & Control strings
• Exo-Thrust-structure
• Structural On-orbit Assembly Interface(s)
Multi-Mission Space Exploration Vehicle
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Partnering & Collaboration
• JPL: Deployment Integ., Communications/Data Transmission
• AMES: ECLSS, Bio-Hab
• GSFC: GN&C, Independent System Integrator
• GRC: Power, Fluid Pumps, PMD, External Ring-flywheel
• LaRC: Hoberman : Deployed structures & Trusses
• NESC: “Shadow” Systems Integrator
• MSFC: Propulsion Unit(s) & Integration platform , Fluids-Transfer & Mngt.
• JSC: Proj. Mngt – SE&I , ECLSS, Centrifuge, Core-Structures, Avionics, GN&C, Software, Logistics Modules
• NASA HQTRS: Legislative & International Relations
• Academia: MIT, Cal-TECH/JPL, Stanford, Georgia Tech
• CIA/NRO/DoD: National Security
• National Institute of Health, NRC, NIST
• Large-Project, Traditionally NON-Aerospace, Program Developers• Power• Shipping• Infrastructure
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Technology Applications Assessment Team
Multi-Mission Space Exploration Vehicle
Technology Development
M.L. Holderman JSC/SSP
NAUTILUS - NAUTILUS - XX
• CENTRIFUGE [HABITABLE] ARTIFICIAL GRAVITY/PARTIAL-(g)• Basic design
• System Integration Impacts & Assessments
• Materials & Deployment strategy• UV, Radiation-mitigation, Self-sealing, Micro-meteoroid defense• Inflatable and Expandable Structure integrated design
• Hub design• Seals• Bearings • Materials• Drive Mechanism
• Power transfer mechanisms
• Centrifuge torque-offset• External dynamic Ring-flywheel
• ISS CMG cluster(s) Control Authority integration
• Control Avionics & Software
• Full-Test & Assay of HUMAN response to Partial-(g)
First TAAT Demonstration
Description and Objectives:
Justification:Approach:
Collaborators/Roles:
• Partial Gravity in space may be critical for enabling Long Term Human exploration within the Solar System
• A Centrifuge must be integrated into the baseline design of any transit or Journey-class spacecraft in order to take advantage of GN&C influences and specific design considerations
• Rotating hub/ transition tunnel• Rotating mass with & w/o Crew present
• Early experience on ISS is critical to assessing and characterizing influences and affects of a Centrifuge relative to
- Dynamic response & Influences- Human reaction(s) data-base
• DDT&E/DCT&I <39 months $84-143M
• Utilize Hoberman-Sphere expandable structures with inflatable & expandable technology Soft-structures to erect a (low mass) structure that provides partial-(g) force for engineering evaluation
• First In-space demonstration of sufficient scale Centrifuge for testing and determination of artificial partial-(g) affects • Impart Zero disturbance to ISS micro-gravity environment
JSC: Design Requirements/Project Mngt., Centrifuge Design/Test, Instrumentation, Control Avionics/SW, Deployment scheme, Structural Design & Materials selection, Crew Training, On-Orbit Test OPS
JSC/Ames: Hub Seal & Bearings, Payload IntegrationDraper Labs: ISS GN&C impactsGRC: Flywheel Design/Integr.LaRC: Hoberman alignment & load Cirlce
• Potentially Off-load duty-cycle on ISS CMGs by introducing constant angular moment to augment GN&C
•Hub design based on Hughes 376 Spin-Sat Tech.• Liquid metal & tensioned material seal design• Low noise/mass thrust and guide bearings
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Technology Applications Assessment Team
Mark L. HoldermanJSC/SSP
• Existing Orbiter External Airlock used to attach Centrifuge to ISS• Also provides a contingency AirLock capability
• (*) Ultimately provide partial-(g) sleep station for ISS Crew• Option for Food-prep station & small Dining area • Potential partial-(g) WC
• Self deployment with IVA for final construction/verification• Engineering pedigree with TransHab and EVA suits
• Two individual ½ Circle deployments• Hoberman based load & deployment ring• Goal: single Delta-IV/Atlas-V launch
Multi-Mission Space Exploration Vehicle
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Technology Applications Assessment Team
• Inflatable Based (TransHab)• Hoberman Ring Stabilized• External Ring-flywheel • ISS micro-(g) experiment compatible
2013 DEMO COST: $84M - $143M
Mark L. HoldermanJSC/SSP
• Smaller diameter Centrifuge incorporates shaped inflatable elements that are deployed from fixed hard nodes
• Max RPM for Centrifuge may require longer acclimation period for crew between partial and zero-(g)
• Well-modeled & Assessed /Analyzed “net” influence on ISS CMGs and GN&C
• Loads not to exceed Dock-port limits
• Hub design utilizes Liquid-metal seals with low-rumble/wobble thrust bearings • Bearing rotational hardware derived from Hughes 376 spin-stabilized ComSats
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Technology Applications Assessment Team
Mark L. HoldermanJSC/SSP
DEMO Aspects:
• 30ft OD with 50in. cross-section ID• All internal dimensions and layout will accommodate EVA suite Astronaut
Partial - (g)RPM 30ft dia. 40ft dia. 4 .08 .11 5 .13 .17 6 .18 .25 7 .25 .33 8 .33 .44 9 .41 .55 10 .51 . 69
SRMS in Berth-mode while Orbiter Air-lock is placedin Soft-Dock during micro-(g)activities on ISS
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Multi-Mission Space Exploration Vehicle
Orbiter External Airlock Overview:
COST
: $84
-143
M
DCT
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<39
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Design, Construct, Test & Implement: DCT&I
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Technology Applications Assessment Team
Mark L. HoldermanJSC/SSP
http://www.hoberman.com/portfolio/hobermansphere-lsc.php?myNum=10&mytext=Hoberman+Sphere+%28New+Jersey%29&myrollovertext=%3Cu%3EHoberman+Sphere+%28New+Jersey%29%3C%2Fu%3E&category=&projectname=Hoberman+Sphere+%28New+Jersey%29
* Te
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Eva
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entr
ifuge
des
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to b
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rew
Hoberman Circular Deployment& Load outer ringNested jacking cylinders for
Transit Tunnel
ex-Orbiter External AirLock
Dynamic external Ring-Flywheel
Astromast w/ Hard-node
Stabilizer Rings
Inner Jack-knife Stabilizer
Soft-Berth mechanism[internal]: Micro-(g)mitigation
Internal Ballast Bladders
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M.L. HoldermanJSC/SSP
Component Detail
Mass “Car”
Linear Motor
Shaft Position Drive
Bearing Cluster
Vari-densityMass module
• Centrifuge can also serve as independent Emergency Shelter node
• Independent internal separation capability from ISS for major contingency situation
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Mark L. HoldermanJSC/SSP
• Kick motor utilized as both primary start-up and spin maintenance mechanism
• Drive motor(s) will be in ISS/Orbiter External Airlock
DEMO Aspects:
* Test & Evaluation Centrifuge designed with capability to become Sleep Module for Crew
• Engineering pedigree with TransHab and EVA suit material(s) & design principles
• Two individual ½ Circle deployments
• Nested cylinder & deployable drawer approach for Transit Tunnel
• Ring Flywheel can be either driven from ex-Orbiter External Airlock or be self-contained on Hub [requires Hub battery-bank]
• CG offset of Centrifuge centerline mitigated with internal ballast bladders [urine/waste fluids]
Mark L. HoldermanJSC/SSP
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• Inflatable Based (TransHab)• Hoberman Ring Stabilized• External Ring-flywheel • ISS micro-(g) experiment compatible
Technology Applications Assessment Team
M.L. Holderman JSC/SSP
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1. Airlock• 1.1Remove from OV Payload Bay• 1.2 Structural mods
• Carriage receiving structure [new]• Side hatch• Centrifuge drive mechanism & motor• Air circulation• Power grid (new)
• 1.3 Sensor Suite• Ring laser gyro• 3 axis strain-guage pkg.• Accelerometer panel• frequency pick-up(s)
• 1.4 Drive Unit• Uniform-load drive input shaft & differential [low rumble]• Crew IVA assembly• S/w for controller
• 1.5 Delta-II integration • Load path attach points• Vertical integration impacts• Primary load mechanism
1. Airlock2. Centrifuge & Deployment3. External Dynamic Flywheel4. Test & Integration
Cost: $19M
1. Airlock2. Centrifuge & Deployment3. External Dynamic Flywheel4. Test & Integration
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M.L. Holderman JSC/SSP
2. Centrifuge & Deployment• 2.1 Ring Stabilizer : Hoberman external & internal[IVA]
• + & - Configuration• Deploy mode & Operation mode
• 2.2 Ring• Material & layout biasing• Deployment bladders• IVA final assembly for circumference inner seal
• 2.3 Hub• Bearing layout• External Dynamic Flywheel integration• Seal material• Seal design w/ redundancy
• 2.4 Carriage• Deployment mechanism(s)
• 2.5 Transit Tunnel• Stowed nested segments• Auto inter-lock pressure seal• Low mass &
• 2.6 Nacelles• 2.7 Astromast & Sizzor Struts• 2.8 Deployment mechanisms & structures• 2.9 Inflation support• 2.10 Ballast System [Bladders, pumps, guages, EMAs]• 2.11 Load sensor Platform
Cost $84M
1. Airlock2. Centrifuge & Deployment3. External Dynamic Flywheel4. Test & Integration
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Technology Applications Assessment Team
M.L. Holderman JSC/SSP
3. External Dynamic Flywheel• 3.1Collar load surface
• Airlock structural integration• 3.2 Electric Linear Drive• 3.3 Controller avionics• 3.4 Controller Software • 3.5 Feedback sensor suite• 3.6 Thrust & Load Bearing layout/design • 3.7 Material selection• 3.8 Variable Mass manipulator system
• Linear drive• Stepper & damper• Position Lock
• 3.9 Mass shape (variable density)
Cost $20
1. Airlock2. Centrifuge & Deployment3. External Dynamic Flywheel4. Test & Integration
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Technology Applications Assessment Team
M.L. Holderman JSC/SSP
4. Test & Integration• 4.1 Centrifuge Ring• 4.2 Transfer Tunnel• 4.3 Deployment
• Structural [Hoberman]• Inflation
• 4.4 Software C/O• 4.5 Dynamic Flywheel
• Safety• Characterization• Operations Scheme & Plan
• Integration w/ Falcon-9 or Ariane• Payload Structure• Transfer Vehicle*
Cost $17
* ATV/HTV not included
Technology Applications Assessment Team
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M.L. HoldermanJSC/SSP
JSC: Design Requirements/Project Mngt., Centrifuge Design/Test, Instrumentation, Control Avionics/SW, Deployment scheme, Structural Design & Materials selection, Crew Training, On-Orbit Test OPS JSC/Ames: Hub Seal & Bearings, Payload IntegrationDraper Labs: ISS GN&C impactsILC Dover: EVA SuitsGRC: Flywheel Design/Integr.LaRC: Hoberman alignment & load CircleESA: ATV(mod) , ArianeJAXA: HTV, H-2Bigelow: Centrifuge
• Tommy Hilfiger: • Ralph Lauren• Gucci• Tire Manufacturers
• Goodyear, Michelin, Bridgestone, Pirelli
• Nike• General Electric• Electric Boat Works
• Submarine Manufacture
Non - TraditionalPartners (Representative)
Collaborators/Partnerships/RolesCollaborators/Partnerships/Roles
•Thermal-Vac chamber would be fully utilized testing proto-type configurations and large-scale operating models of the Centrifuge [CF]
•Bearing and hub design•Seal design•Inflatable/Hoberman deployment testing with mag-lev plates for 0-g simulation
• Bldg.9 would be converted to Full-scale CF lay-out with multiple mock-ups•Air-table for deployment/assembly checkout of CF assembly sequence•Human factor assessment•ECLSS integration•GN&C affects on thrust & control axis’
• Mission Operations Directorate• Emphasis focuses on start-up sequence of CF • Nominal operational influences of CF
• Space & Life-Sci [Dedicated Project]•Partial-(g) / Fractional-(g) effects on the human body
•Repetitious exposure to partial-g and zero-g•Psyche/mood effects•Vascular•Digestive [tendency to vomit during transition]•Excretory•Ocular•Skeletal/Muscular•Sleep
•Sleep chamber coupled to Radiation mitigation•Design of Partial-g toilet and body-wash-station•ECLSS design for IVA [Internal Vehicular Activity]maintenance & repair
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Mark L. HoldermanJSC/SSP
Technology Applications Assessment Team
Mark L. HoldermanJSC/SSP
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• Engineering Directorate undertakes Exo(skeleton)-Truss design•Load distribution•Deployment scheme(s)•Thermal management techniques•Load transmitting Orbital structural interface design
• Engineering Directorate undertakes Flat-Panel Spacecraft design•Partial ortho-grid/iso-grid utilization•Integration of external/internal Exo-Truss•Engineering Directorate undertakes pre-configured Drawer-extension deployment strategy•Track design for Slide-out deployment•Seal & autonomous latch design [internal & external]•Load accommodation•Thermal management•Electrical/Comm/Data/ECLSS integration
•Engineering Directorate undertakes material development for Inflatable Elements of CF
•Engineering Directorate undertakes CF rotating hub design
• Engineering Directorate begins second-generation closed-loop ECLSS design
•Engineering Directorate undertakes Guidance & Control design of Nautilus-X•Accommodation of Multiple Propulsion Pods•Thrust models with operating CF•Software development•Star map generation for multiple MMSEV Missions
•Engineering Directorate undertakes Long-Distance Communications/Data suite design•Radar and Communications range re-activated/expanded•Vibro-Accoustic Lab addresses Propulsion Pod impacts on link stability & integrity
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Back-Up Back-Up Charts Charts
Centrifuge
Command /Control Deck& Manipulator Station
Air-Lock w/ stagingplatform
Inflatable Modules (3)• 2 Logistics• 1 ECLSS, Plant growth & Exercise
Solar ArrayPropulsion IntegrationCollar
• Mission Specific• Electrical & C/C• Thrust Structure
CommunicationsArray
Attitude Control& CMG cluster
Docking Port(Orion, Commercial, Int’l)
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Multi-Mission Space Exploration Vehicle
Radiation Mitigation Chamber
M.L. Holderman JSC/SSP
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M.L. HoldermanJSC/SSP
Folding PV arrays
Descent Vehicle Hangar
Primary Communications Dish
Propulsion
ECLSS Module
Adaptable full-span RMS
Command/Observation Deck
Primary Docking Port
Logistical Stores
Centrifuge
Radiation Mitigation
Extended Duration Explorer
Technology Applications Assessment Team
Multi-Mission Space Exploration Vehicle
Science Probe Craft &Mini Service-EVA-Pods
Technology Applications Assessment Team
M.L. Holderman JSC/SSP
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Multi-Mission Space Exploration Vehicle
Extended Duration Explorer
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Multi-Mission Space Exploration Vehicle
M.L. Holderman JSC/SSP
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Technology Applications Assessment Team
Extended Duration ExplorerExtended Duration Explorer
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M.L. Holderman JSC/SSP
Multi-Mission Space Exploration Vehicle
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Hanger Detail
• Reinforced fabric• Auto-deployment• Low mass, Small Volume• Airlock Access• Multipurpose• Asset Housing
• Descent Craft• Scientific Platforms
Technology Applications Assessment Team
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Multi-Mission Space Exploration Vehicle
M.L. Holderman JSC/SSP
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M.L. Holderman JSC/SSP
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Technology Applications Assessment Team
M.L. Holderman JSC/SSP
The Five legged 1962 model of the then named Lunar Excursion Module
1962 5-Legged initial design
1963 version with Docking node forward
1965 with Docking Portmoved to top and the egress hatch is “square”
Final Version
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LEMLEM Concept Evolution
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Design Philosophy• Purposeful• Accommodation• Minimalism
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LEM LEM Design DetailsDesign Details
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