Abstract
Thermal stability is an important indicator to measure the reliability of aerospace equipment, and the space thermal environment is complex, and the commonly used thermal analysis software for ground equipment can no longer meet the needs. For this reason, based on the thermal design analysis software SINDA/FLUINT, taking a spacecraft as the research object, the thermal balance equation is first established. Then, use the thermal desktop software to establish a numerical model, and use the SINDA/FLUINT software to solve the heat transfer process. Finally, the thermal desktop is used to post-process the calculation results and analyse the thermal radiation of the spacecraft.
Highlights
On September 21, 1992, the Chinese government decided to implement the manned space project and decided on a three-step development strategy
It makes up for the shortcomings of the traditional method, such as long time-consuming, poor accuracy, and many constraints. It is an effective method for the thermal radiation analysis of complex space targets 7
The steps for analysing the thermal radiation of spacecraft based on SINDA/FLUINT are as follows: (1) Build the spacecraft model based on the geometry and material properties of the spacecraft by using Thermal Desktop; (2) Perform thermal meshing on the established spacecraft model, establish boundary nodes and set boundary conditions based on its thermal load information; (3) Set the orbital parameters of the spacecraft; (4) Use SINDA/FLUINT software to perform on-orbit thermal radiation calculations of the spacecraft thermal model; (5) Analyze the thermal radiation of the spacecraft in orbit based on the calculation results
Summary
On September 21, 1992, the Chinese government decided to implement the manned space project and decided on a three-step development strategy. With the rapid development of infrared technology, the use of infrared radiation characteristics to detect space targets is an effective method[1] Faced with this situation, the common analysis methods conclude formula derivation, model simplification, solving the heat balance equation of nodes, space target temperature distribution calculation, and according to the surface material temperature distribution and emissivity to solve the infrared radiation characteristics of space target. The common analysis methods conclude formula derivation, model simplification, solving the heat balance equation of nodes, space target temperature distribution calculation, and according to the surface material temperature distribution and emissivity to solve the infrared radiation characteristics of space target This method is easy to understand, but different calculation models need to be established for different targets in different environments. Calculation results can be directly imported into SINDA/FLUINT software
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