FIELD: aircraft engineering.
SUBSTANCE: proposed method consists in evacuation of hydraulic thermal control compensator fluid line and fluid chamber and, then, evacuation of compensator gas line and gas chamber. Tightness of said gas cavity and fluid line are defined by the magnitude of gas flows running from gas line with compensator gas cavity and fluid line with compensator gas cavity at their evacuation. Before evacuation, both lines are subjected to pressure leveling, evacuation being executed in two steps. First, evacuation is performed with the help of roughing-down pump to equilibrium pressure stationary magnitudes get with the help of said roughing-down pump. Then, high-vacuum pump is used to continue evacuation to equilibrium pressure stationary magnitudes with the help of high-vacuum pump while tightness of fluid line and gas line with compensator gas cavity is defined at their evacuation by high-vacuum pump.
EFFECT: higher quality of tests, higher reliability and longer life of spacecraft thermal control system.
3 dwg
