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使用高比冲的小推力推进系统为执行机构,设计空间交会问题的燃料最优时间连续制导律.首先给出轨道交会问题的数学模型,并给出最优控制问题的目标函数和约束条件;然后利用直接法将控制变量离散化,通过参数寻优得到对应燃料最优的控制变量参数和转移时间常数;最后针对点火时刻误差问题,分析了实际轨迹与名义最优轨迹的偏差,并利用微分代数工具求取部分控制变量的修正值,以保证航天器满足轨道交会的终端位置约束.
Using the high specific impulse propulsion system as the actuator, the optimal fuel time continuous guidance law for space rendezvous is designed.First, the mathematic model of orbit rendezvous is given and the objective functions and constraints of the optimal control are given. Then, the direct variables are used to discretize the control variables, and the optimal fuel corresponding control variables and transfer time constants are obtained through parameter optimization. Finally, according to the error of ignition timing, the deviation between the actual trajectory and the nominal optimal trajectory is analyzed, Algebraic tools to obtain part of the control variable correction value to ensure that the spacecraft to meet the terminal rendezvous constraints.