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基于改进高斯法(IGM)和遗传算法(GA)的混合优化算法,为解决空间拦截轨道燃料消耗和转移时间的综合最优问题,提出一种空间拦截轨道设计方法.首先,引入牛顿-拉夫逊迭代法对原始高斯法进行改进,解决原始高斯法在解算空间拦截轨道时收敛速度慢、转移角范围小等问题;接着,给出并证明改进高斯法迭代方程有唯一解的充分必要条件.当给定初始轨道参数时,用此条件判断可否用椭圆轨道进行转移;然后给出转移时间,最大脉冲速度等约束条件,对编码方式进行改进,给出混合优化算法的计算步骤;最后以空间拦截轨道优化问题为例,进行仿真分析.仿真结果表明,与传统优化算法相比,混合优化算法收敛的遗传代数少,耗时短,能够较好地运用于空间拦截轨道的设计.
A hybrid optimization algorithm based on improved Gaussian method (IGM) and genetic algorithm (GA) is proposed to solve the integrated optimal problem of space-intercepting orbit fuel consumption and transfer time.At first, the introduction of Newton-Raphson The iterative method is used to improve the original Gaussian method to solve the problem that the original Gaussian method converges slowly and the transition angle is small when solving the orbiting space. Then, the necessary and sufficient conditions for the unique solution to the improved Gaussian iteration equation are given and proved. When the initial orbital parameters are given, the condition can be used to determine whether the elliptical orbit can be used for the transfer. Then the constraints such as the transfer time and the maximum pulse velocity are given, and the encoding method is improved to give the calculation steps of the hybrid optimization algorithm. Finally, Simulation results show that, compared with the traditional optimization algorithm, the hybrid optimization algorithm has less genetic algebra and less time consuming and can be applied to the design of space intercept trajectory.