Design of a Piloted Spacecraft to Bridge the Gap between the Space Shuttle and Crew Exploration...

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...

Documents

Transcript of Design of a Piloted Spacecraft to Bridge the Gap between the Space Shuttle and Crew Exploration...