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针对嫦娥三号探测器在软着陆过程中主减速阶段的运动轨道问题建立数学模型。在合理的假设下,对该阶段探测器进行受力分析,建立动力学微分方程模型。以始末状态为约束条件,以消耗燃料最少为优化目标,将最优轨道控制策略转化为主发动机推力控制函数的参数优化问题,运用Runge-Kutta法进行数值求解,并采用遗传算法搜索最优参数。在保证算法可靠性的前提下,利用神经网络拟合出约束条件与控制参数之间的关系,进而求出严格满足约束条件的参数,最终得到了该阶段的运动规律及最优控制策略。
A mathematical model was established for the orbit of Chang’e III during the main deceleration phase during soft landing. Under reasonable assumption, the force analysis of the detector at this stage, the establishment of dynamic differential equation model. Based on the condition of initial and final conditions, the optimal fuel consumption is minimized, and the optimal orbit control strategy is transformed into the parameter optimization problem of main engine thrust control function. The Runge-Kutta method is used to solve the problem. Genetic algorithm is used to search the optimal parameters . Under the premise of ensuring the reliability of the algorithm, the neural network is used to fit the relationship between the constraints and the control parameters, and then the parameters that strictly meet the constraints are obtained. Finally, the movement law and the optimal control strategy are obtained.