Integrated satellite cabin plate heat storage device adapted to complex heat flow environment

Abstract

The invention provides an integrated satellite cabin plate heat storage device adapted to a complex heat flow environment, including a skin, a filling skeleton, a phase change material, and a fillingtube, wherein the filling skeleton and the skin are brazed and welded to form a satellite cabin plate by vacuum brazing; the filling skeleton is a filling skeleton with sufficient void ratio, and theouter surface is covered with the skin; the side edge of the satellite cabin plate is welded with the filling tube communicated with the internal void of the satellite cabin plate; the internal void of the filling skeleton is filled with a certain amount of phase change material; and the phase change material is organic or inorganic material with stable solid-liquid phase change temperature and high phase change latent heat. The integrated satellite cabin plate heat storage device adapted to a complex heat flow environment makes the satellite cabin plate have relatively stable temperature, simple structure and high reliability, and is particularly suitable for the satellite cabin plate under the complex external heat flow environment of alternating illumination, thereby effectively reducing the fluctuation of the internal temperature of the satellite and reducing the requirement of the thermal control resources.

Description

technical field [0001] The invention relates to a heat storage device for thermal control of an aircraft, in particular to an integrated satellite deck heat storage device adapted to a complex heat flow environment. Background technique [0002] For low-orbit inclined-orbit satellites, the surface of the satellite is illuminated in turn during its flight, resulting in constant changes in its external heat flow conditions. At the same time, due to the changing working modes of the satellite, the heat consumption of the whole device varies greatly. Therefore, the thermal control design of the satellite is required. High adaptability. [0003] Usually, satellites use aluminum honeycomb panels as the structural panels of the cabin, and set up cooling surfaces in areas with relatively small external heat flow to dissipate excess heat inside the satellite. However, with the continuous development of satellite technology and mission requirements, the orbital attitude of satellites...

AI Technical Summary

Problems solved by technology

However, a large heat dissipation surface area will cause a large heat loss under low temperature conditions, so it needs to consume a very large amount of electric power to compensate for its heat dissipation

In addition, the heat dissipation surface of the inclined orbit may also be irradiated, resulting in failure to dissipate heat normally, or even heat backflow, resulting in the failure of the satellite to operate normally

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