Heat-Pump-Augmented Spacecraft Heat-Rejection Systems

Author(s)

Robert P. Scaringe, Mainstream Engineering Co.
J. A. Buckman, Mainstream Engineering Co.
Lawrence R. Grzyll, Mainstream Engineering Co.
E. T. Mahefkey, Wright-Patterson Air Force Base
John E. Leland, University of DaytonFollow

Document Type

Article

Publication Date

1990

Publication Source

Journal of Spacecraft and Rockets

Abstract

Future military space missions will introduce significant new technological needs for spacecraft energy systems. It is generally accepted that spacecraft heat-rejection systems that use heat pumps to boost the radiator temperature will reduce the radiator area. However, these systems must also result in weight savings and high reliability. This paper discusses several heat-pump configurations and discusses the benefits of a combination of the heat-pump system and the thermal management/thermal transport system.

Inclusive pages

318-323

ISBN/ISSN

0022-4650

Comments

Permission documentation is on file.

Copyright

Copyright © 1990, American Institute of Aeronautics and Astronautics

Publisher

American Institute of Aeronautics and Astronautics

Volume

27

Issue

3

Peer Reviewed

yes

eCommons Citation

Scaringe, Robert P.; Buckman, J. A.; Grzyll, Lawrence R.; Mahefkey, E. T.; and Leland, John E., "Heat-Pump-Augmented Spacecraft Heat-Rejection Systems" (1990). Office for Research Publications and Presentations. 58.
https://ecommons.udayton.edu/ofr_pub/58