长征运载火箭制导方法  

Guidance Methods of Long-March Launch Vehicles

作　　者：吕新广[1] 宋征宇[1,2] 

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防级重点实验室,北京100854

出　　处：《宇航学报》2017年第9期895-902,共8页Journal of Astronautics

摘　　要：对长征系列运载火箭制导方法的发展和当前最新研究成果进行了综述。为满足轨道控制需求,制导方法起步于外干扰补偿制导,历经隐式和显式的摄动制导,逐步过渡到目前的闭环最优制导,并且发展出多个分支。传统迭代制导通过预测最佳入轨点、实时修正剩余飞行时间以及在线轨迹规划等技术,实现了高精度入轨控制;轨道预测修正迭代制导则通过跨飞行段取消位置与速度约束,并补偿对轨道的影响,实现了大推力直接入轨火箭的高精度控制;二次曲线直接制导通过改变程序角形式,增加控制维数,满足了终端姿态约束要求。最后结合我国未来重型运载火箭的任务特点,提出了在不同任务场景下采用统一的制导方法的设想,并以凸优化和联立法作为实现手段讨论了未来的研究重点。The development of the guidance methods of the Long-March launch vehicles and the latest research results are reviewed. In order to meet the orbit requirements of the payloads,the guidance methods started from the disturbance compensation guidance,followed by the implicit and explicit perturbation guidance,and then the current closed-loop optimal guidance developing many branches. The traditional iterative guidance achieves high-precision orbit by predicting the optimal injection point,real-time correction of the time-to-go and on-line trajectory planning. The iterative guidance with orbit prediction and correction is designed to meet the requirements of the large thrust direct injection,relaxing the position and velocity constraints in different phases,and the errors caused by this way are predicted and compensated. The quadratic function guidance increases the number of the control dimensions by changing the form of the program angle to meet the requirements of the terminal attitude constraints. Finally,according to the characteristics of the Chinese heavy-lift launch vehicles,the idea of a unified guidance method for various scenarios in the future is proposed,and the research emphases,such as convex optimization and simultaneous method,are discussed as the effective means.

关 键 词：运载火箭 制导方法 摄动制导 迭代制导 闭环最优制导 

分 类 号：V448[航空宇航科学与技术—飞行器设计]