Analysis of the Thermal Effect on Satellite and Rocket Separation Switch of the Sinosat-2 Satellite Orbit Transfer Engine

Paper number

IAC-07-C2.7.08

Author

Prof. Guobiao Cai, Beijing University of Aeronautics and Astronautics, China

Coauthor

Mr. He Bijiao, Beijing University of Aeronautics and Astronautics, China

Coauthor

Dr. Zhang Xiaoying, China

Coauthor

Prof. Xu Xu, Beijing University of Aeronautics and Astronautics, China

Coauthor

Mr. Zhu Dingqiang, Beijing University of Aeronautics and Astronautics, China

Year

2007

Abstract

The SINOSAT-2 satellite is a new generation commercial communications satellite developed by China. The Satellite and Rocket Separation Switch (SRSS) of the SINOSAT-2 satellite is a key component which is used to control the unfolding of the communication antennas and the solar panels. As the SRSS is near the satellite orbit transfer engine and outside the thermal baffle, it could be influenced by the impingement thermal effect of the plume backflow, thermal radiation effect of the plume, thermal radiation effect of the engine wall and reflected radiation of the thermal baffle. The value of heat flux on the SRSS is always concerned for the satellite design institute. Therefore, an overall analysis of the thermal effect on the SRSS is very necessary.
  In this paper, three thermal effect ways on the SRSS are studied by numerical simulation. First of all, finite difference method for solving N-S equations and the Direct Simulation Monte Carlo (DSMC) method are integrated to calculate the plume field and the plume backflow thermal effect. Secondly, discrete element method and the integrated radiation transfer equation method are used to calculate the plume core region radiation effect on the SRSS. Finally, radiation effect of the orbit transfer engine and reflected radiation effect of the thermal baffle are obtained by analyzing the angle factors and visibility between SRSS and them. As the SINOSAT-2 satellite uses the same orbit transfer engine with the DFH-3 satellite, the thermal effect on the SRSS of the DFH-3 satellite is studied by numerical simulation, and the results are compared with that of the SINOSAT-2.
  The study shows that, for both SINOSAT-2 and DFH-3, the solid radiation heat flux value of engine the outside wall is the largest and must be paid more attention to; and there is a slightly thermal effect on the SRSS by the backflow of plume, while the thermal flux value is small; and the plume thermal radiation effect can be neglected. However, the heat flux value of SINOSAT-2 satellite is larger than that of the DFH-3. The study in this paper provides a support for the further temperature analysis and improvement of thermal protection for the design institute.

Abstract document

IAC-07-C2.7.08.pdf

Manuscript document

IAC-07-C2.7.08.pdf (🔒 authorized access only).

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