Trajectory Optimization for Hypersonic Vehicle Satisfying Maneuvering Penetration

被引：4

作者：

Zhang, Kenan ^{[1
]}

Chen, Wanchun ^{[1
]}

机构：

[1] Beihang Univ, Sch Astronaut, Beijing, Peoples R China

来源：

MECHANICAL AND AEROSPACE ENGINEERING, PTS 1-7 | 2012年 / 110-116卷

关键词：

hypersonic; penetration; trajectory optimization; quasi-equilibrium glide condition;

D O I：

10.4028/www.scientific.net/AMM.110-116.5223

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

A trajectory optimization method for hypersonic vehicle in glide phase satisfying maneuvering penetration is proposed. Divide the dangerous zones that the hypersonic vehicle may encounter during glide phase into avoidable no-fly zones and avoidless no-fly zones. Take the avoidable no-fly zones as path constraints to join the trajectory optimization. To penetrate the avoidless no-fly zones, trajectory is programmed by some maneuvering policy. Direct shooting method is used to discretize the control variable to piecewise constant functions. So the optimal control problem is transferred to a nonlinear programming (NLP) problem, and solved by the serial quadratic program (SQP) method.

引用

页码：5223 / 5231

页数：9