FIELD: cosmonautics.
SUBSTANCE: invention relates to space engineering, particularly, to hydraulic systems incorporated with thermal control systems of spacecraft. Thermal control system of space object contains interconnected closed circulation circuits of heating and cooling, control system. Heating circuit contains in-series connected to each other hydraulic unit with differential pressure sensor, gas-liquid heat exchangers, controller-switch and fluid flow controller, made with step motors, temperature sensors are electrically connected to the switch regulator and the fluid flow regulator through the control system, a coil heat exchanger, thermal boards, a hydraulic compensator with a drain valve. Cooling circuit contains in-series connected to each other by pipelines a hydraulic unit with a differential pressure sensor and a radiation heat exchanger. Narrowing device is installed in the cooling circuit between the lines of connection to the cooling circuit from the regulator-switch and the flow rate regulator.
EFFECT: increased reliability of space object thermal control system operation at long service life.
2 cl, 4 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| SYSTEM OF SPACE OBJECT THERMAL CONTROL | 2009 |
|
RU2404092C1 |
| METHOD OF HEATING OF LUNAR ROCKET LAUNCHER COMPLEX | 2012 |
|
RU2539675C2 |
| TEMPERATURE CONTROL SYSTEM OF SPACECRAFT AND ORBITAL STATION | 1999 |
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|
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| TEMPERATURE CONTROL SYSTEM OF SPACECRAFT THERMAL MOCK-UP | 1996 |
|
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| SPACECRAFT EQUIPMENT THERMAL CONTROL SYSTEM | 2012 |
|
RU2494933C1 |
| METHOD OF CONTROL OF PRESSURE IN HYDRAULIC TEMPERATURE CONTROL SYSTEM WITH GAS-AND-LIQUID COMPENSATOR OF SPACECRAFT | 1999 |
|
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| METHOD OF THERMO-STABILISATION OF ELECTRONIC EQUIPMENT | 2016 |
|
RU2630948C1 |
| SPACECRAFT | 2013 |
|
RU2543433C2 |
