多模块航天器转移轨道优化设计  

Application of Global Optimization to Transfer Orbits for Fractionated Spacecraft

作　　者：吴大同[1] 郑莉莉[1] 罗建军[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《科学技术与工程》2011年第9期2048-2051,2056,共5页Science Technology and Engineering

摘　　要：轨道动力学是适用于全局优化的众多应用领域之一。着眼于分布式航天器转移轨道优化,提出了所有航天器模块连续地从停泊轨道转移到目标轨道,并同时保持相对位置的方案。最优控制问题已经确定。性能指标的选取标准是在有限的燃料下将总体轨道转移时间降到最低。总体轨道转移时间是包括消除航天器之间在停泊轨道上的相位差耗费时间和所有模块长距离轨道转移时间之和。当选取位置和速度作为状态时,最优问题就是一个非常复杂的最优控制问题。然而,通过给出合适的常值状态参量,上述问题就会转变成静态参数最优问题。最终采用基于Matlab优化工具拟牛顿方法的最优化算法解决了这个参数最优化问题。当初始估计良好的情况下该最优化算法能够迅速收敛。另一方面,轨道动力学推力假设能够获得最初估计值。仿真结果证明了多模块航天器的轨道设计策略是实用的,同时证明该最优化算法是有效的。The global optimization can be applied to many fields,one of which is orbital dynamics.The optimal transfer orbits of fractionated spacecraft is focused on and proposed a scenario that all the modules transfer from the parking orbit successively,and arrived at the corresponding positions on the object orbit simultaneously.The optimal control problem is established.Performance index is selected to minimize the total orbital transfer time with limited fuel,which is defined as the sum of all the long-distance orbital transfer time of the modules and phase errors eliminating time of the spacecraft on the parking orbit.The optimization problem here is a very complicated dynamic optimal control problem if position and velocity are choosed as the states.However,it is transformed into static parameter optimization problem via the correct steady state parameters.In the end,the parameter optimization problem is solved by optimization algorithm based on Quasi-Newton Method in virtue of Matlab optimization tools.The optimization algorithm can converge promptly with high precision on condition of a favorable initial estimate.On the other hand,the initial guess value can be obtained according to the orbital dynamics with impulse assumption.The simulation demonstrates the availability of the fractionated spacecraft＇s orbit design strategy and the effectiveness of the algorithm.

关 键 词：分布式航天器 多模块 全局最优化 轨道转移 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]