SPACE VEHICLE HEAT TUBE TESTING METHOD Russian patent published in 2009 - IPC B64G1/50 F28D15/02 

FIELD: aircraft industry.

SUBSTANCE: invention refers to creation and operation of elements of thermostatting systems, and namely telecommunication satellite instruments. Method involves determination of heat tube temperature differential values between evaporation and condensation sections thereof within the range of changing operating temperatures of those sections. At that, to evaporation section there supplied is one and the same required heat power for various amounts of excessive heat carrier wherewith the inner cavity of heat tube housing is filled. In that cavity there made is a wick in the form of longitudinal grooves on the housing inner surface. Temperature differential values between the above heat tube evaporation and condensation sections at maximum operating temperature of evaporation section and for the specified amounts of filled excessive heat carrier are determined at minimum allowable operating temperature of condensation section. At that, amounts of filled excessive heat carrier meet the certain condition expressing the dependence of those amounts on heat carrier densities at maximum and minimum allowable operating temperatures of evaporation and condensation sections.

EFFECT: reliable determination of temperature differentials at heat tube ground test between evaporation and condensation sections thereof, as well as maximum allowable amount of filled excessive heat carrier at which there provided are the above temperature differentials in all heat tube orbital operating conditions.

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