A pluggable satellite thermal control system and method

Abstract

The invention provides a pluggable satellite thermal control system, which includes an operating robot, a heat insulation component and a heat dissipation component. The operating robot is connected to the surface of the satellite main body for clamping and installing the heat insulation component and the heat dissipation component; the heat insulation component is arranged on the sun receiving surface of the satellite main body, and is connected to the surface of the satellite main body through a standard interface; and the heat dissipation component is arranged on the The back side of the satellite body is connected to the surface of the satellite body through a standard interface.

Description

technical field [0001] The invention relates to the technical field of aerospace, in particular to a pluggable satellite thermal control system and method. Background technique [0002] With the continuous development of satellite technology, more and more functions can be achieved by a single satellite. In order to achieve more functions, the number of subsystems or functional modules configured in the satellite increases accordingly. This also makes the heat emitted by the satellite as a whole higher and higher. In addition, during the operation of the satellite in orbit, it will also be affected by external heat such as sunlight. In practical applications, once the temperature of the satellite is too high, it is very likely to cause damage to each functional module, thereby affecting the normal operation of the satellite. [0003] Based on this, how to design the thermal control system of the satellite is very important. For example, Patent No. 2019107847488 mentions ...

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Problems solved by technology

For example, patent 2019107847488 mentions a modular and reconfigurable satellite thermal control method based on repeatable separation of thermal interfaces, which uses different heat dissipation modules for the specific heat consumption level and load of different modules of the satellite, but its installation Complicated and difficult to achieve on-rail plugging and unplugging

Another example is patent 2020224362293, which provides a satellite thermal control energy storage module based on welding adhesive sealing technology, which solves the problem of insufficient sealing durability, and patent 2016101473622, which solves the problem of small The key stand-alone thermal control problem in the satellite, neither of these two methods adopts a modular design, it is difficult to maintain and replace, and the flexibility is poor

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