摘要
摄动制导方法简单、可靠,但其对大初始轨道偏差、大推力偏差或故障工况适应性差,近年来逐渐被迭代制导技术所取代。但迭代制导姿态振荡大、不适用于气动作用强烈飞行段。提出一种基于速度主量在线插值的改进摄动制导方法,从稳定性角度提出导引回路增益及网络参数设计方法。结果表明,本方法显著提升大初始速度偏差、大推力偏差工况下的轨道精度,姿态明显比迭代制导方案平稳。
The perturbation guidance method has been widely used for its simplicity.But it works poor for large initial orbit errors,thrust deviation and other fault condition,so in recent years it has been gradually replaced by iterative guidance law;Large attitude oscillation and not be suited to atmospheric flight limits iterative guidance law’s engineering application.An upgraded perturbation guidance method is presented by interpolating main speed vector online,and puts forward the guidance loop design criterion of gain and network parameters from the stability point of view.Simulation results show this method significantly improving the accuracy of orbit under big initial velocity deviation and thrust deviation,and attitude is more smooth than the iterative guidance law.
作者
李君
张普卓
何兆伟
程兴
董朝阳
Li Jun;Zhang Pu-zhuo;He Zhao-wei;Cheng Xing;Dong Chao-yang(Beijing University of Aeronautics and Astronautics,Beijing,100191;Beijing Institute of Astronautical Systems Engineering,Beijing,100076)
出处
《导弹与航天运载技术》
CSCD
北大核心
2018年第4期70-74,共5页
Missiles and Space Vehicles
关键词
大偏差
运载火箭
摄动制导
Large initial orbit errors
Launch vehicle
Perturbation guidance method
