考虑终端姿态约束的自适应迭代制导方法  

An Adaptive Iterative Guidance Method with Terminal Attitude Constraint

作　　者：郝钏钏 司成 周曼娟 Hao Chuanchuan;Si Cheng;Zhou Manjuan(Aerospace System Engineering Shanghai,Shanghai 201109,China)

机构地区：[1]上海宇航系统工程研究所,上海201109

出　　处：《航天控制》2018年第6期14-19,共6页Aerospace Control

摘　　要：为了解决采用经典迭代制导方法时运载火箭主动段终端姿态散布较大的问题,提出一种考虑终端姿态约束的自适应迭代制导方法。该方法将末级主动段分为迭代制导段和姿态快速调整段;在迭代制导段,通过对其终端姿态和姿态快速调整段的估计,自适应调整其制导目标状态;在主动段结束前进入姿态快速调整段,将火箭姿态快速调整至期望姿态。仿真结果表明该方法能同时满足轨道参数约束和终端姿态约束,且仅增加少量的推进剂消耗。In order to solve the problem of the large distribution of the terminal attitude in the launch vehicle by using conventional iterative guidance method,an adaptive iterative guidance method with terminal attitude constraint is proposed.The last ascent stage is divided into iterative guidance phase and fast attitude adjustment phase.In the iterative guidance phase,the guidance target is adaptively adjusted by estimating its terminal attitude and the influence of the fast attitude adjustment phase.Launch vehicle enters the fast attitude adjustment phase before the end of the ascent stage and adjusts the attitude to the desired value.The simulation results show that the proposed method can meet both the orbit constraints and the terminal attitude constraint and the increased propellant consumption is acceptable.

关 键 词：运载火箭 终端姿态约束 迭代制导 自适应 

分 类 号：V448.13[航空宇航科学与技术—飞行器设计]