TEMPERATURE-CONTROL ENGINEERING OF A NUCLEAR-ELECTRIC SPACECRAFT
A study is presented of the significance of temperature in the design of spacecraft components and its effect on the over-all performance and operational range of a nuclearelectric ion-propelled spacecraft. A conceptual 70-kwe spacecraft configuration for an Earth-to-Venus deep-space mission is selected for this study. Expected operating steady-state temperatures of the spacecraft subsystems are examined. Environmental factors including solar, nuclear, and planetary thermal energies are shown to have considerable effect on component or system temperature. Spacecraft subsystems and components are briefly discussed with regard to system requirements, specifications, and configuration. The expected temperature gradients and proposed methods for temperature control are surveyed. Major temperature-control problems of spacecraft subsystems and their interrelated effects are discussed. Suggested methods to lessen the environmental and interrelated effects and to prevent a component from approaching a critical operating condition are discussed. (auth)
- Research Organization:
- California Inst. of Tech., Pasadena. Jet Propulsion Lab.
- DOE Contract Number:
- NAS 7-100
- NSA Number:
- NSA-16-025031
- OSTI ID:
- 4804808
- Report Number(s):
- JPL-TR-32-232
- Resource Relation:
- Other Information: Orig. Receipt Date: 31-DEC-62
- Country of Publication:
- United States
- Language:
- English
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