logging in or signing up 1234 Melissa1 Download Post to : URL : Related Presentations : Share Add to Flag Embed Email Send to Blogs and Networks Add to Channel Uploaded from authorPOINTLite Insert YouTube videos in PowerPont slides with aS Desktop Copy embed code: (To copy code, click on the text box) Embed: URL: Thumbnail: WordPress Embed Customize Embed The presentation is successfully added In Your Favorites. Views: 132 Category: Education License: All Rights Reserved Like it (0) Dislike it (0) Added: January 22, 2008 This Presentation is Public Favorites: 0 Presentation Description No description available. Comments Posting comment... Premium member Presentation Transcript 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 Vehicle Michael Seibert University of Colorado at BoulderPresentation Overview: Presentation Overview Motivation Vehicle Requirements Conceptual Design Compatible Launch Vehicles ConclusionsMotivation: Motivation Hiatus in piloted spaceflight capability 2010-2014 Four Options Extend STS operations past 2010 Contract with foreign governments Accelerate CEV development Develop a new vehicleVehicle Requirement Areas: Vehicle Requirement Areas Crew Size Launch Vehicle Compatibility Launch Abort Orbital Maneuvering Rendezvous and Docking On Orbit Life Recovery Reusability Vehicle Requirement Summary: Vehicle Requirement Summary Crew Size 5 person crew Launch Vehicle Compatibility Any 2005 existing or final design phase LV Launch Abort Capability must be provided Orbital Maneuvering 300-400m/s ΔV Rotation and translation Vehicle Requirements Summary: Vehicle Requirements Summary Rendezvous and Docking 2 days maximum Automated Dock with US segment On Orbit Lifetime 100 day minimum Recovery Reentry 75nm cross range 500nm down range Recovery Continued Controllable Descent Landing Nondestructive Conventional Runway Reusability Returned components onlyConceptual Design: Conceptual Design Winged Vehicle Pros Highly maneuverable Runway landing Cons High temperature reentry Capsule Pros Lower temperature reentry Simpler design Cons Low maneuverability Requires parachute for landingConceptual Design: Conceptual Design Crew Size Two row arrangement ECLSS LiOH scrubbers Separate ascent and descent air suppliesConceptual Design: Conceptual Design Rendezvous Automated approach Deployable radar system Docking APAS-89 docking adapter [1]Conceptual Design: Conceptual Design Recovery Lift vector generation Offset center of mass and shaped heat shield Parafoil descent 1NM-2NM maneuvering range Landing Tricycle landing gear Controlled rollout Differential brakingConceptual Design: Conceptual Design Reaction Control System Roll/translation thruster pairs Translation only pairs Orbital Maneuvering System Single engine on roll axisConceptual Design: Conceptual Design Miscellaneous S/C Cooling Heat exchangers (water/ammonia) Crew ingress/egress Hatch on port side next to rear seats Windows Four 2 30cm diameter next to rear seat rows 2 next to front seatsConceptual Design: Conceptual DesignCompatible Launch Vehicles: Compatible Launch Vehicles Estimated Spacecraft Mass 11,000kg* Delta IV Family Medium+ (4,2) $138M Medium+ (5,4) $160M Atlas V Family 400 series $138M *Based upon historical spacecraft densities, see accompanying paperConclusions: Conclusions It is possible to develop a new vehicle before 2010 The vehicle described will provide unprecedented launch flexibility The vehicle describe can be used to complement the resumption of exploration beyond LEOQuestions?: Questions?References: References Background Image: NASA http://solarsystem.nasa.gov/multimedia/gallery/ Columbia_Moon.jpg [1] Portree, D. Mir Hardware Heritage. NASA RP 1357. NASA, Houston. March 1995 You do not have the permission to view this presentation. In order to view it, please contact the author of the presentation.
1234 Melissa1 Download Post to : URL : Related Presentations : Share Add to Flag Embed Email Send to Blogs and Networks Add to Channel Uploaded from authorPOINTLite Insert YouTube videos in PowerPont slides with aS Desktop Copy embed code: (To copy code, click on the text box) Embed: URL: Thumbnail: WordPress Embed Customize Embed The presentation is successfully added In Your Favorites. Views: 132 Category: Education License: All Rights Reserved Like it (0) Dislike it (0) Added: January 22, 2008 This Presentation is Public Favorites: 0 Presentation Description No description available. Comments Posting comment... Premium member Presentation Transcript 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 Vehicle Michael Seibert University of Colorado at BoulderPresentation Overview: Presentation Overview Motivation Vehicle Requirements Conceptual Design Compatible Launch Vehicles ConclusionsMotivation: Motivation Hiatus in piloted spaceflight capability 2010-2014 Four Options Extend STS operations past 2010 Contract with foreign governments Accelerate CEV development Develop a new vehicleVehicle Requirement Areas: Vehicle Requirement Areas Crew Size Launch Vehicle Compatibility Launch Abort Orbital Maneuvering Rendezvous and Docking On Orbit Life Recovery Reusability Vehicle Requirement Summary: Vehicle Requirement Summary Crew Size 5 person crew Launch Vehicle Compatibility Any 2005 existing or final design phase LV Launch Abort Capability must be provided Orbital Maneuvering 300-400m/s ΔV Rotation and translation Vehicle Requirements Summary: Vehicle Requirements Summary Rendezvous and Docking 2 days maximum Automated Dock with US segment On Orbit Lifetime 100 day minimum Recovery Reentry 75nm cross range 500nm down range Recovery Continued Controllable Descent Landing Nondestructive Conventional Runway Reusability Returned components onlyConceptual Design: Conceptual Design Winged Vehicle Pros Highly maneuverable Runway landing Cons High temperature reentry Capsule Pros Lower temperature reentry Simpler design Cons Low maneuverability Requires parachute for landingConceptual Design: Conceptual Design Crew Size Two row arrangement ECLSS LiOH scrubbers Separate ascent and descent air suppliesConceptual Design: Conceptual Design Rendezvous Automated approach Deployable radar system Docking APAS-89 docking adapter [1]Conceptual Design: Conceptual Design Recovery Lift vector generation Offset center of mass and shaped heat shield Parafoil descent 1NM-2NM maneuvering range Landing Tricycle landing gear Controlled rollout Differential brakingConceptual Design: Conceptual Design Reaction Control System Roll/translation thruster pairs Translation only pairs Orbital Maneuvering System Single engine on roll axisConceptual Design: Conceptual Design Miscellaneous S/C Cooling Heat exchangers (water/ammonia) Crew ingress/egress Hatch on port side next to rear seats Windows Four 2 30cm diameter next to rear seat rows 2 next to front seatsConceptual Design: Conceptual DesignCompatible Launch Vehicles: Compatible Launch Vehicles Estimated Spacecraft Mass 11,000kg* Delta IV Family Medium+ (4,2) $138M Medium+ (5,4) $160M Atlas V Family 400 series $138M *Based upon historical spacecraft densities, see accompanying paperConclusions: Conclusions It is possible to develop a new vehicle before 2010 The vehicle described will provide unprecedented launch flexibility The vehicle describe can be used to complement the resumption of exploration beyond LEOQuestions?: Questions?References: References Background Image: NASA http://solarsystem.nasa.gov/multimedia/gallery/ Columbia_Moon.jpg [1] Portree, D. Mir Hardware Heritage. NASA RP 1357. NASA, Houston. March 1995