Distributed Heat Source Centralized Heat Dissipation Technology For Large Space Telescope Based On Loop Heat Pipe

Space telescope is an important means for human to observe cosmic phenomena and explore the operating principle of the universe.A certain type of space telescope is equipped with a 2m magnitude primary mirror,and the fuselage section size is 5m magnitude.At the same time,six high-power devices are installed inside the capsule to ensure the normal operation of the space telescope.The thermal control system is a key part to ensure the normal operation of the space telescope in the complex and changing thermal environment.Therefore,the radiation-cooling system on the space telescope has been studied deeply.In this paper,the significance of the space telescope is summarized and the difficulties faced by large spacecraft in thermal control design are described.On this basis,the research status of related thermal control technology is summarized,and the research status of loop heat pipe technology and radiator applied in the radiating system is summarized,and the difficulty of thermal management of distributed heat source in large spacecraft is put forward.The characteristics of heat source distribution inside the space telescope are introduced.The space environment characteristics,space attitude limitation and heat balance equation of the space telescope are described.Finally,according to the attitude constraints of the space telescope,the external heat flow under all possible attitudes is calculated.According to the calculated results,the final high temperature and low temperature conditions of the space telescope are analyzed.The thermal control design and the thermal control system of each component in the radiation-cooling system are described in detail,and the design criteria that need to be followed in the design of the thermal control system are introduced,and a group of circuits are taken as an example to analyze the structural characteristics,thermal control difficulties and related parameters of each component,according to the factors affecting the heat dissipation efficiency in the whole radiation-cooling system are analyzed.A specific thermal design scheme is presented,and the coordination among the components is described.The thermal simulation analysis was carried out on the radiation-cooling system of the single group of loop heat pipes.Combined with the high and low temperature conditions calculated above,the external heat flux of each radiator was obtained.The finite element thermal model was established according to the simulation software,and the temperature levels of each component under the high temperature,low temperature and storage conditions were calculated.And make the module temperature within the index.Then,the heat balance test of the radiationcooling system is carried out.The comparison between the test and the simulation results shows that the calculation results of the two tend to be consistent,and the overall heat transfer performance is consistent,which proves that the radiationcooling system can effectively heat and dissipate heat.According to the related parameters obtained from the thermal experiment of the single loop heat pipe spoke cooling system studied before,the thermal simulation analysis of the whole radiator system was carried out.According to the temperature of the radiator,the thermal interface temperature range of each module was finally calculated.The results show that all meet the thermal control requirements,and can provide a reference for the heat balance test of the whole machine.Finally,aiming at the difficulties of multi-heat source concentrated heat dissipation technology in the design of large spacecraft,an optimization design method is proposed,the principle and characteristics of related intelligent algorithms are introduced,and the heat transfer path of heat source is planned and optimized by combining the two algorithms.The final results show that the heat transfer path optimized by this method is significantly improved compared with the traditional design method,and can provide feasible ideas and methods to solve the related thermal control problems encountered on other large spacecraft.