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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
5 April 2005 2005 CSGC Undergraduate Research Symposium“Tomorrow’s Workforce”
2
Presentation Overview
• Motivation
• Vehicle Requirements
• Conceptual Design
• Compatible Launch Vehicles
• Conclusions
5 April 2005 2005 CSGC Undergraduate Research Symposium“Tomorrow’s Workforce”
3
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 vehicle
5 April 2005 2005 CSGC Undergraduate Research Symposium“Tomorrow’s Workforce”
4
Vehicle Requirement Areas
• Crew Size• Launch Vehicle Compatibility• Launch Abort• Orbital Maneuvering• Rendezvous and Docking• On Orbit Life• Recovery• Reusability
5 April 2005 2005 CSGC Undergraduate Research Symposium“Tomorrow’s Workforce”
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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
5 April 2005 2005 CSGC Undergraduate Research Symposium“Tomorrow’s Workforce”
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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
only
5 April 2005 2005 CSGC Undergraduate Research Symposium“Tomorrow’s Workforce”
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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
landing
5 April 2005 2005 CSGC Undergraduate Research Symposium“Tomorrow’s Workforce”
8
Conceptual Design
• Crew Size– Two row arrangement
190cm
265cm 320cm
• ECLSS– LiOH scrubbers– Separate ascent and
descent air supplies
5 April 2005 2005 CSGC Undergraduate Research Symposium“Tomorrow’s Workforce”
9
Conceptual Design
• Rendezvous– Automated approach– Deployable radar
system
• Docking– APAS-89 docking
adapter
[1]
5 April 2005 2005 CSGC Undergraduate Research Symposium“Tomorrow’s Workforce”
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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 braking
5 April 2005 2005 CSGC Undergraduate Research Symposium“Tomorrow’s Workforce”
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Conceptual Design
• Reaction Control System– Roll/translation
thruster pairs– Translation only pairs
• Orbital Maneuvering System– Single engine on roll
axis
5 April 2005 2005 CSGC Undergraduate Research Symposium“Tomorrow’s Workforce”
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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 seats
5 April 2005 2005 CSGC Undergraduate Research Symposium“Tomorrow’s Workforce”
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Conceptual Design
5 April 2005 2005 CSGC Undergraduate Research Symposium“Tomorrow’s Workforce”
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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 paper
5 April 2005 2005 CSGC Undergraduate Research Symposium“Tomorrow’s Workforce”
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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 LEO
Questions?
5 April 2005 2005 CSGC Undergraduate Research Symposium“Tomorrow’s Workforce”
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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
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