Analysis of the thermal effect on satellite and rocket separation switch of the SINOSAT-2 satellite orbit transfer engine

In this paper, the thermal effects on the satellite-rocket separation switches (SRSS) for SINOSAT-2 orbit transfer engine are investigated. The thermal effects are produced by plume backflow impact, plume gas radiation, and engine surface radiation. The solving process consists of four steps. Firstly the N-S equations are solved by difference method to present the continuous flow field near the nozzle exit of orbit transfer engine. Secondly according to the distribution of Knudsen number, entrance boundary conditions of DSMC simulation particles are confirmed. Then the plume backflow field near the SRSS is calculated by DSMC method, as well as the impact thermal effects on the SRSS. Thirdly, according to the density distribution of plume flow field, effective gas radiation region is validated. Using the method of waveband integral and finite element, the gas radiation effects are solved. 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. Since the orbit transfer engine of SINOSAT-2 is the same with that of DFH-3, the numerical simulation of the plume effects of the SRSS for the DFH-3 is also carried out. The study shows that, for both SINOSAT-2 and DFH-3, the solid radiation heat flux value of engine surface 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 research carried out in this paper can provide reference for the further temperature analysis and thermal protection of the SRSS for design departments. Copyright IAF/IAA. All rights reserved.