FIELD: space conditions simulation stands.
SUBSTANCE: proposed test stand includes vacuum chamber, cryogenic shield, external thermal flux simulator and control system. Vacuum chamber is connected with pressure sensor. Cryogenic shield is provided with temperature sensor. Outputs of pressure sensor and pressure setter which excludes convective heat exchange in vacuum chamber are connected to inputs of one of comparison circuits. Outputs of cold space temperature sensor and temperature setter are connected to inputs of second comparison circuit. Outputs of both comparison circuits are connected to inputs of AND gate. AND gate output is connected to control system of voltage regulator unit. Voltage regulator outputs are connected to sections of external thermal flux simulator.
EFFECT: enhanced reliability of simulation of space conditions; reduced power requirements.
1 dwg
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