THERMAL CONTROL MODE OF STRUCTURAL ELEMENTS OF SPACECRAFT WITH IN-BUILT STRUCTURAL ELEMENTS OF PROPULSION SYSTEM WITH GAS ROCKET ENGINES Russian patent published in 2008 - IPC B64G1/00 

FIELD: heating; transportation.

SUBSTANCE: method includes measurement, comparison and maintenance of temperatures within their upper and lower allowed values in elements of working substance feed system, gas rocket engines (GRE), within areas of elements of feed system and GRE on structural elements of spacecraft. These procedures are carried out while working substance is stored and delivered to operating GRE. Before GRE is turned on, if measured temperatures prior to working substance feed less than upper limit values, elements of feed system and GRE are heated until specified temperatures reaches upper limit values. At operation of GRE temperatures are maintained in elements of feed system and GRE at their upper allowed values. Upon completion of GRE operation and by starting of working substance storage mode elements of feed system, GRE and areas thereof on structural elements are cooled to lower limit temperatures.

EFFECT: higher performance and reliability of propulsion systems with gas rocket engines during long operation of spacecraft.

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