PROCESS QUALITY CONTROL SYSTEM Thermal SPACECRAFT

摘要

FIELD: transport.;SUBSTANCE: invention relates to thermal control systems of, mainly, telecommunication satellites. Proposed method comprises intermittent control over availability of required amount of heat carrier in thermal control liquid circuit. For this, actual dose of heat carried drained from hydraulic accumulator fluid chamber is defined from pressure and temperature measurements of heat carrier in said circuit and those in hydraulic accumulator gas chamber. Besides, working fluid saturated gas elasticity in hydraulic accumulator gas chamber is defined at measured temperature to compare to actual heat carrier drained dose with design magnitude. In fueling of liquid circuit, portions of heat carrier are drained therefrom starting from completely compressed bellow to completely stretched bellow. After draining every portion, heat pressure in liquid circuit an gas chamber pressure in hydraulic accumulator are measured. Dependence of total drained dose on difference between liquid circuit heat carrier pressure and fluid saturated gas elasticity in hydraulic accumulator gas chamber (as-measured after draining) is plotted. In spacecraft operation, said plot is used to define actual heat carried drained doze for given time interval.;EFFECT: simplified control at higher accuracy.;2 dwg