Design of a Piloted Spacecraft to Bridge the Gap between the Space Shuttle and Crew Exploration Vehicle Michael Seibert University of Colorado at Boulder.

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


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


4

Vehicle Requirement Areas

• Crew Size• Launch Vehicle Compatibility• Launch Abort• Orbital Maneuvering• Rendezvous and Docking• On Orbit Life• Recovery• Reusability


5

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


6

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


7

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


8

Conceptual Design

• Crew Size– Two row arrangement

190cm

265cm 320cm

• ECLSS– LiOH scrubbers– Separate ascent and

descent air supplies


9

Conceptual Design

• Rendezvous– Automated approach– Deployable radar

system

• Docking– APAS-89 docking

adapter

[1]


10

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


11

Conceptual Design

• Reaction Control System– Roll/translation

thruster pairs– Translation only pairs

• Orbital Maneuvering System– Single engine on roll

axis


12

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


13

Conceptual Design


14

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


15

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?


17

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

Design of a Piloted Spacecraft to Bridge the Gap between the Space Shuttle and Crew Exploration Vehicle Michael Seibert University of Colorado at Boulder.

Documents

conceptual design slide

landing slide

new vehicle slide

translation slide

boulder slide

conceptual design crew

vehicle pros

roll axis slide