Direct condensation radiator for spacecraft

Cost and weight of a heat transfer structure for a space vehicle can be reduced by an arrangement of redundant channels for the flow of coolant to heat radiating panels, micrometeroid resisting bumpers located adjacent the channels for preventing penetration by all but the most energetic micrometero...

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Bibliographische Detailangaben
Hauptverfasser:	PUSTAY, JOHN J, CHALMERS, DOUGLAS R
Format:	Patent
Sprache:	eng
Schlagworte:	AIRCRAFT AVIATION BLASTING COSMONAUTICS DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OFGENERAL APPLICATION HEAT EXCHANGE IN GENERAL HEATING LIGHTING MECHANICAL ENGINEERING PERFORMING OPERATIONS TRANSPORTING VEHICLES OR EQUIPMENT THEREFOR WEAPONS
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Beschreibung
Zusammenfassung:	Cost and weight of a heat transfer structure for a space vehicle can be reduced by an arrangement of redundant channels for the flow of coolant to heat radiating panels, micrometeroid resisting bumpers located adjacent the channels for preventing penetration by all but the most energetic micrometeroids, and a sensing and control arrangement for sensing the penetration of a coolant channel for shutting off that channel to prevent loss of coolant.