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介绍了直接配点法在空间飞行器远程轨道交会最优化问题中的应用.首先给出了空间飞行器远程轨道交会最优化控制问题模型,其中运动方程在地心惯性坐标系下建立;性能指标选为轨道交会过程中燃料消耗最小;控制变量为推力、方位角和高低角;终端状态受到位置和速度的约束.然后,采用直接配点法将最优控制问题离散化为非线性规划问题,选取各配点上的状态量争控制量作为优化参数.最后应用适合求解大型非线性规划问题的SNOPT软件包对参数最优化问题进行求解.仿真结果表明直接配点法对于空间飞行器远程交会轨道初始参数取值不敏感,具有一定的鲁棒性,且求解过程具有一定的实时性.“,”The application of direct collocation method to space vehicle long-range orbital rendezvous with finite thrust optimization problem was introduced. Firstly, the model of long-range orbital rendezvous optimization control problem was established, while motion equation of the state variables was built in geocentric-equatorial inertial coordinate system. Performance was selected to minimize the total fuel consumption. The control variables are thrust, azimuth angle and elevation angle. Terminal state variable constraints are position and velocity constraints. Than, the optimal control problem was transformed into nonlinear programming problem (NLP) using direct collocation method. And the state variables and control variables were selected as optimal parameters at all collocation nodes. At last, parameter optimization problem was solved using the SNOPT software package. The simulation results demonstrate that direct collocation method is not sensitive to orbital rendezvous initial conditions; they also show that the optimal solutions of long-range orbital rendezvous optimization problem are fairly good in robustness.