载人运载火箭全要素约束迭代制导技术  

The Iterative Guidance Method with All-elements Constrained for Manned Launch Vehicle

作　　者：施国兴[1] 柴嘉薪 胡海锋 Shi Guo-xing;Chai Jia-xing;Hu Hai-feng(Beijing Aerospace Automatic Control Institute,Beijing,100854;National Key Laboratory of Aerospace Intelligent Control Technology,Beijing,100854)

机构地区：[1]北京航天自动控制研究所,北京100854 [2]宇航智能控制技术国家级重点实验室,北京100854

出　　处：《导弹与航天运载技术》2022年第1期47-52,共6页Missiles and Space Vehicles

摘　　要：运载火箭使用的制导技术目前有摄动制导和迭代制导。摄动制导方法无法满足载人火箭的高精度入轨要求,而迭代制导方法能满足高精度入轨要求,但无法约束其终端姿态。提出了一种载人运载火箭用全要素约束迭代制导技术,通过优化终端姿态反馈算法和精细化考虑迭代末段的速度和位置约束量,使得运载火箭以期望终端姿态角实现高精度入轨。算例表明,该算法解决了载荷在入轨时刻有高分离姿态约束需求的工程实际问题,具有很高的工程应用价值。There are two kinds of guidance technologies commonly used in launch vehicles:perturbation guidance method(PGM)and iterative guidance method(IGM).PGM cannot meet the high-precision orbit requirements of the manned launch vehicles.IGM can meet the high-precision orbit requirements,but it cannot constrain the terminal attitude.Therefore,an all-element constrained IGM for the manned launch vehicle is proposed.This technology optimizes the terminal attitude feedback algorithm and finely considers the speed and position constraints at the end of the flight stage.This allows the launch vehicle to achieve high-precision orbit at the desired attitude angle.Simulation results show that this algorithm solves the practical engineering problem that the load has a high separation attitude constraint requirement when the load enters the orbit.It has high engineering application value.

关 键 词：姿态约束 迭代制导 二次曲线 制导算法 

分 类 号：V448[航空宇航科学与技术—飞行器设计]