FIELD: transport.
SUBSTANCE: invention relates space engineering, particularly to method of filling spacecraft thermal control system hydraulic line with heat carrier. Proposed method comprises measuring hydraulic line dry volume, filling pre-evacuated hydraulic line with deaerated heat carrier at surplus pressure, bleeding a portion of heat carrier from spacecraft volume compensator fluid chamber and measuring its volume with the help of reference vessel. Heat carrier portion drained, volume of not-dissolved gas bubbles in hydraulic line is determined from the measurements results.
EFFECT: higher reliability.
2 dwg
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Authors
Dates
2010-08-20—Published
2008-10-07—Filed