最优真空飞行轨迹设计和制导方法研究  

Optimal Vacuum Flight Trajectory Design and Guidance Method

作　　者：王炀[1] 唐硕[1] 

机构地区：[1]西北工业大学航天学院,陕西西安710072

出　　处：《计算机仿真》2011年第10期78-82,共5页Computer Simulation

摘　　要：研究飞行器燃料最优真空飞行轨迹设计和制导问题,轨迹优化设计和在线制导系统快速性和精确度具有很高的要求。根据典型飞行任务特征,导出具有直观物理意义的横截条件,用无量纲技术建立相应的最优控制模型,分别通过常值和线性引力的假设,给出正则方程的两种近似积分方法,设计相应的制导策略,再利用打靶法和dogleg信赖域法进行数值仿真。通过对运载火箭入轨和卫星轨道转移两类典型实例的应用,结果表明方法具有更好的快速性、精确度和可靠性,为设计提供科学依据。This paper described the propellant-optimal vacuum flight trajectory design and guidance method.Trajectory optimization and on-line guidance system required rapid iteration method with a high degree of accuracy.According to different mission features,the transversally conditions with obvious physical meaning had been derived.Optimal control model had been developed by no dimension technique.Two approximate integration methods had been developed,which applied const-gravity field and linear-gravity field separately.Then the corresponding guidance algorithms were derived.Shooting method and dogleg trust-region method have been employed to numerically solve the problem.These techniques have been utilized to optimal trajectory generation and guidance for rocket orbital insertion and satellite transfer cases,and the numerical results show better efficiency,precision and robustness.

关 键 词：最优控制 轨迹设计 制导 入轨 轨道转移 

分 类 号：V448.1[航空宇航科学与技术—飞行器设计]