Download - Design of a Piloted Spacecraft to Bridge the Gap between the Space Shuttle and Crew Exploration Vehicle

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


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


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


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


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


Conceptual DesignWinged VehicleProsHighly maneuverableRunway landingConsHigh temperature reentry

CapsuleProsLower temperature reentrySimpler designConsLow maneuverabilityRequires parachute for landing


Conceptual DesignCrew SizeTwo row arrangementECLSSLiOH scrubbersSeparate ascent and descent air supplies


Conceptual DesignRendezvousAutomated approachDeployable radar system

DockingAPAS-89 docking adapter[1]


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


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


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


Conceptual Design


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


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


Questions?


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
