基于自适应积分的太阳同步轨道发射优化设计  

Optimization of Launch Trajectory for SSO (Sun Synchronous Orbit) Based on Adaptive Transfer Orbit

作　　者：淡雪[1,2] 岳晓奎[1,2] 

机构地区：[1]西北工业大学航天学院,陕西西安710072 [2]航天飞行动力学技术重点实验室,陕西西安710072

出　　处：《西北工业大学学报》2013年第5期701-705,共5页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金(11172235);高等学校博士点专项科研基金(20106102110003)资助

摘　　要：太阳同步轨道(Sun Synchronous Orbit,SSO)发射轨道的优化设计问题是一个具有严格内点约束和终端约束、终端时刻不确定型的最优控制问题,采用最优控制理论求解难度较大。针对此问题,首先将其转化为多重参数优化问题,然后提出一种自适应积分方法,根据高度和速度入轨条件自动确定中间转移轨道,并引入脉冲修正罚函数处理弹道倾角入轨条件,形成无约束最优化问题。借助于MATLAB集成遗传算法,实现了SSO发射轨道的优化设计。算例表明:该优化方法收敛性好,转移轨道的入轨条件能够精确满足,SSO的入轨参数只需较小的速度修正,优化结果曲线符合工程实际情况,得到了工业部门的认可。The optimal ascent trajectory design of the vehicle for Sun Synchronous Orbit （SSO） is an optimal control problem with strict inner and terminal constraints and variable final time; this is difficult for the optimal control theory. To solve this problem, firstly it is translated into a multi-parameter optimization problem, and then an adap- tive integration module is presented to obtain a transfer orbit with altitude and velocity injection constraints automati- cally satisfied, and an impulse modified penalized function is introduced to deal with unsatisfied constraints. Final- ly, with the help of MATLAB integrated genetic algorithm （ GA）, the optimal ascent trajectory is obtained. A sim- ulation example indicates that ： the injection constraints of transfer orbit are met accurately, and those of SSO need a little modification in velocity magnitude. The obtained trajectories are consistent with actual engineering conditions, and have been approved by the administrative department for relevant industry.

关 键 词：SSO发射轨道 优化 自适应积分 脉冲修正罚函数 遗传算法 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]