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借力飞行轨道设计是一个多变量强约束的非线性优化问题,初始方案通常采用不需要初值猜测的全局优化算法进行优化,但是借力点处的C3匹配原则等较强的约束条件极大影响了全局算法的收敛性能.针对这一问题,研究了附加深空机动的借力飞行模型,在借力点处引入B平面和辅助转角,推导了离开超越速度的解析表达式,通过求解Lambert问题和轨道递推得到日心转移段的深空机动脉冲.利用微分进化算法对问题进行优化,结合木星探测算例,对VEE(Venus-Earth-Earth),VEME(Venus-Earth-Mars-Earth)和VEVE(venus-Earth-Venus-Earth)三种深空机动借力飞行方案进行优化,给出了优化结果.
Leveraging Flight Orbit Design is a nonlinear optimization problem with strong constraint and multivariable constraints. The initial scheme is usually optimized by a global optimization algorithm that does not require initial guess. However, the strong constraint such as C3 matching principle at the leveraging point is extremely large Which affects the convergence performance of the global algorithm.According to this problem, the leaping flight model with additional deep space maneuver is studied, the B plane and the auxiliary turning angle are introduced at the leveraging point, and the analytic expression of departure overrun speed is deduced. And the recursion of the heliocentric motions in the heliocentric segment of the deep-space maneuvering pulse of the heliocentric transiting segment is proposed. The differential evolution algorithm is used to optimize the problem and the algorithm of Venus-Earth-Earth VEME (Venus-Earth-Mars-Earth ) And VEVE (venus-Earth-Venus-Earth) three deep-space maneuvering leaps and bounds, and gives the optimization results.