technology applications assessment team t a a t nautilus - x n on – a tmospheric u niversal t...

Technology Applications Assessment Team

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NAUTILUS - NAUTILUS - XX

Non –

Atmospheric

Universal

Transport

Intended for

Lengthy

United

Space

- - - - - - - - - -

X-ploration

M.L. Holderman JSC/SSP

Multi-Mission Space Exploration Vehicle


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M.L. HoldermanJSC/SSP



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



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


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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



System Goals


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• 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


Attributes



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•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 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 -

XX


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•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




Full Operational Status: CIS-Lunar & NEO Mission

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Industrial Airlock slide-out Unit

Command/Control &Observation Deck



Orion &Commercial Docking Port

PV Array deployed: Core Module

- 6.5m -

14m


Completed Centrifuge w/ External Flywheel


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External “Dynamic” Ring-flywheel


Start-up Thrusters

Hoberman Circumferential Stabilizing Ring(s)

Soft-wall Inflatablesection(s)


View looking “Forward”


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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




Initial Operation(s) Concept


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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)



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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 Development



• 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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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


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• Inflatable Based (TransHab)• Hoberman Ring Stabilized• External Ring-flywheel • ISS micro-(g) experiment compatible

2013 DEMO COST: $84M - $143M


• 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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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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Orbiter External Airlock Overview:

COST

: $84

-143

M

DCT

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Design, Construct, Test & Implement: DCT&I

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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

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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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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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• 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]



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• Inflatable Based (TransHab)• Hoberman Ring Stabilized• External Ring-flywheel • ISS micro-(g) experiment compatible



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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



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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


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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


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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


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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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• 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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Radiation Mitigation Chamber




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



Science Probe Craft &Mini Service-EVA-Pods



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Extended Duration Explorer





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Extended Duration ExplorerExtended Duration Explorer


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Hanger Detail

• Reinforced fabric• Auto-deployment• Low mass, Small Volume• Airlock Access• Multipurpose• Asset Housing

• Descent Craft• Scientific Platforms



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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


LEMLEM Concept Evolution

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Design Philosophy• Purposeful• Accommodation• Minimalism


LEM LEM Design DetailsDesign Details


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technology applications assessment team t a a t nautilus - x n on – a tmospheric u niversal t...

Documents

duration space journey

international space

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crew health eclss

support crew

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specific propulsionunitsmulti

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