FIELD: transport.
SUBSTANCE: invention relates to manned spacecraft thermal control systems. Proposed device is intended for in-flight top-up of hydraulic line of said thermal control system equipped with working medium hydropneumatic compensator. It includes two-chamber tanks for working medium and air valves to control current volume of compensator gas chamber. Control consists in working medium displacement to thermal control system hydraulic line from said tank by pressure difference between said gas chamber and said line. Note here that gas chamber initial volume
EFFECT: expanded operating performances, multiple use, decreased weight and sizes, higher reliability.
2 cl, 1 dwg
Authors
Dates
2013-11-10—Published
2012-04-02—Filed