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International Heat Transfer Conference 5

ISSN: 2377-424X (online)
ISSN: 2377-4371 (flashdrive)

SPACE THERMAL SIMULATION FOR SATELLITE HEAT TRANSFER DESIGN EVALUATION

Vasily D. Prian
Mechanical Engineering Dept. California State University San Jose, California, U.S.A.

Andy T. Calimbas
Philco-Ford Corp. WDL Division Palo Alto, California, U.S.A.

Edward A. LaBlanc
Spacecraft Thermodynamics Lockheed Missiles and Space Co. (LMSC) Sunnyvale, California, U.S.A.

DOI: 10.1615/IHTC5.2720
pages 267-271

Abstract

Spacecraft thermal Integrity in orbit is established by analyses with mathematical models validated by tests in space simulation chambers. Additionally, these tests verify the thermal control subsystem and its heat transfer interaction with the spacecraft. Space simulators provide a combined environment of high vacuum and controllable heat flux loading. Substantial progress has been made toward simulating the thermal energy balance of spacecraft without attempting to duplicate the solar spectrum. The present techniques of providing a simulated heat loading are detailed. Methods used at LMSC and at Philco-Ford are discussed with comparisons of predicted-to-flight temperature data to indicate the effectiveness of space thermal simulation tests.

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