Modular reconfigurable satellite thermal control method based on repeatable separation thermal interfaces
A modularization and thermal control technology, applied in the direction of the control device of the living conditions of the aerospace vehicle, etc., can solve the problem that the thermal communication of the modular reconfigurable satellite cannot be established, achieve high-efficiency thermal conduction, and make up for the low allowable heat flux density , to achieve the effect of collaborative heat dissipation
Active Publication Date: 2019-12-20
CHINA ACADEMY OF SPACE TECHNOLOGY
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Problems solved by technology
[0006] The technical problem solved by the present invention is: in view of the current prior art, the satellite thermal control design only supports the independent thermal control of a single module, and it is impossible to establish a modular reconfigurable satellite that can repeat and separate thermal communication, and realize distributed heat consumption and collaborative heat dissipation. problem, a modular reconfigurable satellite thermal control method based on a repeatable separable thermal interface is proposed
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[0040] A modular and reconfigurable approach to satellite thermal control based on repeatable separable thermal interfaces such as figure 1 As shown, by modularizing the satellite equipment according to the heat consumption level and load heat flux density, two levels of classification can be carried out, and different heat control measures can be taken. The specific steps are as follows:
[0041] (1) Carry out modular division according to the heat consumption of satellite equipment and load heat flux;
[0042] In the modular division, the following principles are followed:
[0043] Classify the modules of the modular reconfigurable satellite according to the heat consumption level and load characteristics, the heat consumption is less than 150W, and the load heat flux density is less than 1W / cm 2 The module is the first type of module; the heat consumption is less than 150W, and the load heat flux is between 1W / cm2 with 3W / cm 2 The modules in between are the second type mo...
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The invention discloses a modular reconfigurable satellite thermal control method based on repeatable separation thermal interfaces. A modular reconfigurable satellite system is designed from the beginning, according to the heat dissipation level and the load characteristics of a module, classification is carried out, different thermal control measures are adopted, the three repeatable separationthermal interfaces such as a solid-solid heat conduction interface, a liquid path interface and a gas-liquid interface and strengthened heat transfer measures such as graphene coatings and flat heat pipes are correspondingly designed, thermal communication of an assembly and reconstruction system is established, the whole satellite system provides heat dissipation paths for disperse distributed heat dissipation so as to realize cooperative heat dissipation, and the heat dissipation capability of the single module and the heat dissipation capability of the satellite system are enhanced.
Description
technical field [0001] The invention relates to a modular reconfigurable satellite thermal control method based on a repeatable separable thermal interface, which belongs to the field of thermal control. Background technique [0002] With the gradual expansion of the breadth and depth of space utilization in my country and other countries in the world, the demand for satellite development has been continuously enriched and improved. On the one hand, the demand for large or super-large satellites continues to emerge, including super-large telescopes, super-large space antennas, and long-baseline space survey missions. 100 tons, due to the limitation of the envelope of the launch vehicle fairing and launch weight, it is difficult to meet the development needs of this type of satellite; The one-time working method of the end has not adapted to the rapid development of space technology. In this case, reconfigurable satellites have gradually become an important direction for th...
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IPC IPC(8): B64G1/50
CPCB64G1/50
Inventor 胡帼杰陈余军王敏彭真陶家生王大鹏刘百麟闫森浩
Owner CHINA ACADEMY OF SPACE TECHNOLOGY