考虑终端姿态约束的分段迭代制导方法  

A Segmented Iterative Guidance Method with Terminal Attitude Constraint

作　　者：郝钏钏 周曼娟 修观 匡东政 Hao Chuanchuan;Zhou Manjuan;Xiu Guan;Kuang Dongzheng(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》2022年第2期22-27,共6页Aerospace Control

摘　　要：对有主动段终端姿态约束的运载火箭制导控制问题进行研究,提出一种考虑终端姿态约束的分段迭代制导方法。该方法将末级主动段的制导控制分为2段,占大部分飞行时间的主动段前段采用考虑终端位置、速度约束的迭代制导方法以最大化运载能力,主动段末段采用考虑终端速度、姿态约束的迭代制导方法在实现精确入轨的同时控制终端姿态。仿真结果表明该方法能同时满足轨道根数约束和终端姿态约束,且推进剂消耗量和传统迭代制导方法相当。The guidance of launch vehicle under terminal attitude constraint is studied in this paper. A segmented iterative guidance method under terminal attitude constraint is proposed. The guidance method of the last ascent stage is divided into two segments. The iterative guidance method under terminal position constraint and velocity constraint is adopted in most of the flight time to optimize the launch ability. The iterative guidance method under terminal velocity constraint and attitude constraint is adopted in the last phase to control the terminal attitude. The simulation results show that the proposed method can fulfill both the orbit constraints and the terminal attitude constraint and the propellant consumption is equivalent to the consumption by using traditional iterative guidance method.

关 键 词：运载火箭 迭代制导 终端姿态约束 

分 类 号：V448.13[航空宇航科学与技术—飞行器设计]