CONTROLLABLE SYSTEM FOR THERMOSTATTING OF LIQUID COMPONENT OF ROCKET PROPELLANT OF SPACECRAFT ENGINE PLANT Russian patent published in 2007 - IPC B64G1/50 F25B21/02 

FIELD: temperature control units for rocketry and space engineering.

SUBSTANCE: proposed thermostatting system includes propellant tank, heat-transfer loop with heat exchanger and supercharger, cooling radiator and two thermo-electric batteries. "Cold" commutating plates of these batteries on which first temperature sensors are mounted form thermal contact with external surface of tank over entire external surface. "Hot" commutating plates on which second temperature sensor (common for two sensors) is mounted form similar thermal contact with heat exchanger. Thermo-electric batteries are energized from self-contained power supply units whose voltage may be changed on signal received from control units. Control units receive signals from first individual temperature sensors and from common second temperature sensor. In case any "hot" commutating plate gets overheated, thermo-electric battery is disconnected by signal from second temperature sensor and is connected again as soon as temperature drops. Supply voltage is changed by signals of first temperature sensors.

EFFECT: increased term of storage of liquid component of rocket propellant at retained characteristics of engines.

1 dwg