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Design of a Piloted Spacecraft to Bridge the Gap between the Space Shuttle and Crew Exploration Vehicle. Michael Seibert University of Colorado at Boulder. Presentation Overview. Motivation Vehicle Requirements Conceptual Design Compatible Launch Vehicles Conclusions. Motivation. - PowerPoint PPT Presentation

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  • Design of a Piloted Spacecraft to Bridge the Gap between the Space Shuttle and Crew Exploration VehicleMichael SeibertUniversity of Colorado at Boulder

    CSGC Undergraduate Research Symposium

  • Presentation OverviewMotivationVehicle RequirementsConceptual DesignCompatible Launch VehiclesConclusions

    CSGC Undergraduate Research Symposium

  • MotivationHiatus in piloted spaceflight capability2010-2014Four OptionsExtend STS operations past 2010Contract with foreign governmentsAccelerate CEV developmentDevelop a new vehicle

    CSGC Undergraduate Research Symposium

  • Vehicle Requirement AreasCrew SizeLaunch Vehicle CompatibilityLaunch AbortOrbital ManeuveringRendezvous and DockingOn Orbit LifeRecoveryReusability

    CSGC Undergraduate Research Symposium

  • Vehicle Requirement SummaryCrew Size5 person crew

    Launch Vehicle CompatibilityAny 2005 existing or final design phase LV

    Launch AbortCapability must be provided

    Orbital Maneuvering300-400m/s VRotation and translation

    CSGC Undergraduate Research Symposium

  • Vehicle Requirements SummaryRendezvous and Docking2 days maximumAutomatedDock with US segment

    On Orbit Lifetime100 day minimum

    RecoveryReentry75nm cross range500nm down rangeRecovery ContinuedControllable DescentLandingNondestructiveConventional Runway

    ReusabilityReturned components only

    CSGC Undergraduate Research Symposium

  • Conceptual DesignWinged VehicleProsHighly maneuverableRunway landingConsHigh temperature reentry

    CapsuleProsLower temperature reentrySimpler designConsLow maneuverabilityRequires parachute for landing

    CSGC Undergraduate Research Symposium

  • Conceptual DesignCrew SizeTwo row arrangementECLSSLiOH scrubbersSeparate ascent and descent air supplies

    CSGC Undergraduate Research Symposium

  • Conceptual DesignRendezvousAutomated approachDeployable radar system

    DockingAPAS-89 docking adapter[1]

    CSGC Undergraduate Research Symposium

  • Conceptual DesignRecoveryLift vector generationOffset center of mass and shaped heat shieldParafoil descent1NM-2NM maneuvering rangeLandingTricycle landing gearControlled rolloutDifferential braking

    CSGC Undergraduate Research Symposium

  • Conceptual DesignReaction Control SystemRoll/translation thruster pairsTranslation only pairsOrbital Maneuvering SystemSingle engine on roll axis

    CSGC Undergraduate Research Symposium

  • Conceptual DesignMiscellaneousS/C CoolingHeat exchangers (water/ammonia)Crew ingress/egressHatch on port side next to rear seatsWindowsFour2 30cm diameter next to rear seat rows2 next to front seats

    CSGC Undergraduate Research Symposium

  • Conceptual Design

    CSGC Undergraduate Research Symposium

  • Compatible Launch VehiclesEstimated Spacecraft Mass11,000kg*Delta IV FamilyMedium+ (4,2)$138MMedium+ (5,4)$160MAtlas V Family400 series$138M

    *Based upon historical spacecraft densities, see accompanying paper

    CSGC Undergraduate Research Symposium

  • ConclusionsIt is possible to develop a new vehicle before 2010The vehicle described will provide unprecedented launch flexibilityThe vehicle describe can be used to complement the resumption of exploration beyond LEO

    CSGC Undergraduate Research Symposium

  • Questions?

    CSGC Undergraduate Research Symposium

  • ReferencesBackground Image: NASA http://solarsystem.nasa.gov/multimedia/gallery/ Columbia_Moon.jpg[1]Portree, D. Mir Hardware Heritage. NASA RP 1357. NASA, Houston. March 1995

    CSGC Undergraduate Research Symposium


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