The space quadrant and intelligent occlusion calculation methods for the external heat flux of China space Station

In the thermal control design of spacecraft and the study of its infrared radiation characteristics, the influence of external heat flux must be considered emphatically. In order to solve the complex space occlusion problem of China Space Station, the centroid ontology coordinate system is first defined as the reference coordinate system in this paper. Then, the space quadrant and intelligent occlusion calculation methods are proposed. The former is mainly to solve the shielding of the external heat flux of spacecraft body. The latter is to solve the shielding of the external heat flux of large external hangings. The results show that the maximum occlusion time is up to 6.5 min and the maximum occlusion difference is about 0.7 in the same quadrant at different solar incident angles. Moreover, if the shielding of external hangings is not considered, the time is more than 15 min when the external heat flux difference exceeds 4000 W in the sunlight area, and the maximum difference is about 6000 W. Meaningfully, the space quadrant and intelligent occlusion calculation methods proposed in this paper can effectively solve most of the occlusion problems and is suitable for various spacecraft.

Automated summary

This paper focuses on the influence of external heat flux in the thermal control design and infrared radiation characteristics of spacecraft. It proposes the space quadrant and intelligent occlusion calculation methods to solve the occlusion problem of China Space Station. The results show that the maximum occlusion time is up to 6.5 min and the maximum occlusion difference is about 0.7 in the same quadrant at different solar incident angles.