基于任务安全性的亚轨道飞行器返回轨迹优化  

Entry trajectory optimization for suborbital launch vehicle based on mission safety

作　　者：王文虎[1] 李新国[1] 

机构地区：[1]西北工业大学航天学院,陕西西安710072

出　　处：《飞行力学》2012年第3期284-288,共5页Flight Dynamics

摘　　要：基于高斯伪谱法,结合亚轨道飞行器返回段特点,从任务安全性的角度出发进行了返回轨迹优化研究。出于实际控制能力及安全性的考虑,采用伪控制量作为最优控制变量,摒弃了再入分段、末端区域能量管理段、航向校正圆锥等概念,引入"末端进场走廊"来描述性能指标及终端约束。仿真结果表明,在满足各种约束条件下,能够快速准确地生成亚轨道飞行器返回轨迹,同时验证了结果的可行性与最优性。The purpose of this paper is to apply Gauss pseudospectral method（GPM） to entry trajectory optimization with some mission safety constrains for a suborbital launch vehicle（SLV）.To model the physical system more accurately and improve safety,pseudo controls were used as control variables in optimal control problem.The traditional notions of TAEM and HAC are discarded;instead,whole entry trajectory was generated by a single algorithm.The concept of final approach corridor（FAC） was introduced to formulate performance index and endpoint conditions.The final results were verified for their feasibility and optimality.Simulations show that the method performs well with respect to execution time,convergence and optimality.

关 键 词：亚轨道飞行器 高斯伪谱法 轨迹优化 伪控制量 末端进场走廊 

分 类 号：V412[航空宇航科学与技术—航空宇航推进理论与工程]