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在考虑热流、过载、动压以及开伞点参数等多种约束条件下,针对低升阻比返回舱月面返回再入轨迹优化设计问题,基于分段线性倾侧角参数化策略,提出了采用合作进化算法进行参数优化的策略来实现再入轨迹的快速高精度优化设计.首先采用以能量为自变量的分段线性倾侧角控制参数化策略,将连续最优控制问题转化为有限维参数寻优问题,然后基于逃逸粒子群算法和自适应差分进化算法的合作进化算法求解该问题.数值仿真验证了倾侧角参数化策略的正确性,对比试验分析表明合作进化算法较传统进化算法有更快的收敛速度和更高的优化精度的综合性能,更加适合月面返回再入轨迹优化设计问题的求解.
Considering the constraints of heat flow, overload, dynamic pressure and parameters of the parachute point, the optimization design of the lunar surface return reentry trajectory with low lift-drag ratio is studied. Based on the parametric strategy of piecewise linear roll angle, Cooperative evolutionary algorithm to optimize the parameters of the reentry trajectory.Firstly, a parametric strategy of piecewise linear roll angle control with energy as an independent variable is used to convert the continuous optimal control problem into a finite dimensional parameter search And then solve this problem based on the cooperative evolutionary algorithm of escape particle swarm optimization and adaptive differential evolution algorithm.Numerical simulation verifies the correctness of the parametric tipping angle strategy.Comparison experiment shows that the cooperative evolutionary algorithm is faster than the traditional evolutionary algorithm The convergence speed and higher precision of the overall performance of integrated optimization is more suitable for lunar surface reentry trajectory optimization design solution.