微小卫星的气动力辅助变轨优化设计

The Optimal Design of Aeroassisted Orbital Transfer for Small Satellite

采用伪谱法对微小卫星气动力辅助变轨问题进行研究,在考虑热流限制、控制约束的条件下进行优化设计,得到微小卫星气动力辅助变轨的最优控制解。在此基础上,通过改变转移轨道的近地点高度,得到卫星的另一组飞行轨迹。比较这2组飞行轨迹,分析了转移轨道近地点高度对气动力辅助变轨的影响:近地点高度越高,依靠气动力辅助所能改变的轨道倾角越小,但是可以减小飞行过程中的最大过载、最大动压和最大驻点热流,因此在微小卫星的总体设计中应该综合考虑任务需求来确定转移轨道近地点的高度。

Based on pseudospectral method, the aeroassisted orbital transfer of small satellite is concerned. By considering the heat flux and control limit, the flight trajectory is optimized and the optimal control result is obtained. Furthermore, another flight simulation result is obtained by changing the perigee height of the transfer orbit. Regarding comparison of two trajectories, the simulation result shows that the capability of aeroassisted orbital transfer can be influenced by the perigee height of transfer orbit ： the perigee height is higher, and then the smaller orbit inclination angle which can be changed by aerodynamic assistance is smaller. But the maximum overload, the maximum dynamic pressure and the maximum heat flux during the flight are reduced under this situation. Therefore, the specific mission requirements should be considered to determine the height of the perigee of the height orbit in the overall design of microsateUite.