远程机动飞行器地心角修正的制导方法
Research of Guidance Method with Geocentric Angle Correction for Long Range Maneuvering Vehicle
王煜东 1方岳 1郭珂 1颜楚雄 1李瑾1
作者信息
- 1. 北京航天长征飞行器研究所,北京,100076
- 折叠
摘要
针对远程机动飞行器长时间在大气层内飞行,传统的带落角约束的比例导引法在末制导段的期望落角受飞行航程地心角的影响较大,不能较好地适应远程机动飞行器落角约束的问题,故提出一种地心角修正的落角约束最优制导律.仿真结果表明该制导方法可以使远程机动飞行器的落角满足落角约束,并且具有一定的鲁棒性.
Abstract
The guidance method for long range maneuvering vehicle is focused.The traditional proportional guidance method with falling angle in the terminal guidance phase is greatly affected by the geocentric angle of the flight range and cannot well adapt to the falling angle constraint of long range maneuvering vehicle.An optimal guidance law with falling angle constraint using geocentric angle is proposed.The simulation results show that the guidance method can make the falling angle of long range maneuvering vehicle content the falling angle constraint,and has certain robustness.
关键词
飞行器/比例导引/地心角/落角/最优制导律Key words
vehicle/proportional guidance/geocentric angle/falling angle/optimal guidance law引用本文复制引用
出版年
2024
NETL
NSTL
万方数据