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Brief description of the simulation of the external thermal fluxes absorbed in flight by the radiating elements external of a spacecraft and spacecraft for the implementation of this
Brief description of the simulation of the external thermal fluxes absorbed in flight by the radiating elements external of a spacecraft and spacecraft for the implementation of this
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机译：简要描述由航天器和航天器外部的辐射元件在飞行中吸收的外部热通量的仿真，以实现此目的
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摘要
During a thermal equilibrium test it simulates heating of the constituent elements of a spacecraft (11), such as a satellite, under the effect of solar heat flux albedo, terrestrial infrared and, by directly placing the machine in a vacuum chamber, and the walls, at low temperatures, represent the spatial cold. The simulation is ensured by the heating devices (24), integrated between the panels (10) forming the external structure of the spacecraft and the external radiating elements (22) placed in front of the equipment (12), referred to as to dissipate the heat. The heating devices (24), preferably electric, remain in place on the spacecraft during flight.
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