Low-Thrust Interplanetary Orbit Transfers Using Hybrid Trajectory Optimization Method with Multiple Shooting
Low-Thrust Interplanetary Orbit Transfers Using Hybrid Trajectory Optimization Method with Multiple Shooting
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DOI：
10.2514/6.2004-5088
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发表时间：
2004-08
期刊：
影响因子：
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通讯作者：
Yang Gao;C. Kluever
中科院分区：
文献类型：
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作者：
Yang Gao;C. Kluever
*†已开发出一种具有多次发射技术的混合轨道优化方法（HTOM），并用于计算各种最佳小推力行星际轨道转移。与直接方法不同，HTOM采用系统的拉格朗日状态方程来管理最优控制，这是来自两点边值问题，并表示为一组二分元素。HTOM将最优控制问题转化为参数优化问题，进而通过非线性规划求解。提出了一种灵活的多次打靶技术，大大提高了收敛的鲁棒性。该方法能够模拟多个动力和海岸弧，行星重力辅助，中间交会，和现实的电力推进系统。的HTOM的优点包括显着减少设计空间，提高解决方案的精度相比，直接的方法，大的收敛域的帮助下，多个拍摄，处理离散系统参数的灵活性，和快速的问题收敛，允许更多的试验，以找到全局最优解的初始猜测。给出了几个行星际使命例子的数值结果。
*† A hybrid trajectory optimization method (HTOM) with multiple-shooting techniques has been developed and utilized to compute a variety of optimal low-thrust interplanetary orbit transfers. Unlike direct methods, HTOM employs the system Lagrange costate equations to govern the optimal control, which are derived from the two-point boundary-value problem and expressed by a set of equinoctial elements. HTOM converts the optimal control problem to the parameter optimization that in turn is solved by nonlinear programming. A flexible multiple-shooting technique is developed to greatly improve robustness of convergence. This method is capable of modeling multiple powered and coast arcs, planetary gravity assists, intermediate rendezvous, and realistic electric propulsion systems. The advantages of the HTOM include significant reduction in the design space, improved solution accuracy compared with direct methods, large convergence domain with the aid of multiple shooting, flexibility for handling discrete system parameters, and rapid problem convergence that allows more trials of initial guesses in order to locate global optima. Numerical results are presented for several interplanetary mission examples.