摘要
针对复杂多约束条件下空天飞机上升段燃料最优轨迹优化问题,提出一种基于高斯伪谱法的上升段轨迹优化策略.依据发动机的推力特性将上升轨迹合理分段,使原最优控制问题转化为多段最优控制问题后,采用高斯伪谱法进行并行优化计算.数值仿真结果表明采用这种轨迹优化策略能够满足组合动力系统工作模态转换时对飞行状态的约束条件,可以在较短的时间内完成高精度的上升段轨迹优化任务,从而验证了该方法的有效性.
To design the fuel optimal ascent trajectory of space planes under complex and multi-constrained conditions, a strategy is proposed to segment the ascent trajectory according to the thrust characteristics of the engines. When the original optimal control problem is transformed into a multi-stage optimal control problem, the Gauss pseudospectral method is used for parallel optimization. Numerical result shows that this strategy can easily satisfy the constraints of state variables when the engine switches and generates the fuel optimal trajectory within short computing time. It is verified that the optimization strategy proposed is efficient.
出处
《空间控制技术与应用》
CSCD
北大核心
2017年第2期13-20,共8页
Aerospace Control and Application
基金
国家自然科学基金资助项目(11502289)
关键词
空天飞机
燃料最优
分段优化
高斯伪谱法
space planes
fuel optimal
multiple-stage optimization
Gauss pseudospectral method
