FIELD: temperature control of surrounding medium parameters on board manned space object.
SUBSTANCE: proposed device includes absolute pressure gauge, vacuum pump and hermetic reservoir divided into liquid and gas chambers by means of elastic diaphragm. Liquid chamber is filled with working medium and is connected with section of hydraulic line being checked by means of pipe line through first shut-off valve. Gas chamber filled with air at pressure of space object compartment atmosphere is connected with pressure gauge. It is also communicated with vacuum pump inlet and with said compartment via second and third shut-off valves. Vacuum pump outlet is communicated with compartment atmosphere. Pressure and temperature of working medium in hydraulic line are equalized with pressure and temperature of compartment atmosphere. Then, hydraulic line is divided into separate sections which are not connected hydraulically and each section is brought in turn in communication with liquid chamber. Every time after communication with liquid chamber, it is disconnected from section being checked and gas chamber is evacuated till pressure of saturated vapor of working medium corresponds to its temperature. Then, liquid chamber is brought in communication with gas chamber at maintenance of constant temperature and change of air pressure in gas chamber is checked. In case there is no change in pressure, section is considered to be perfectly hermetic and vice versa in case of change in pressure, section is rejected.
EFFECT: enhanced safety for space object crew in finding fault in hydraulic line sections.
3 cl, 1 dwg
