基于落角约束的超声速导弹制导方案研究  

Research on Super-Sonic Missile Guidance Plan Based on the Terminal Angular Constraint

作　　者：张汝川[1] 顾文锦[1] 赵红超[2] 

机构地区：[1]海军航空工程学院三系,山东烟台264001 [2]海军航空工程学院七系,山东烟台264001

出　　处：《飞行力学》2009年第3期45-49,共5页Flight Dynamics

基　　金：总装备部预研项目(2002装计字第1468号)

摘　　要：针对超声速导弹具有落角约束条件下的制导问题,提出了一种新的设计方案。首先,在中制导俯冲过程中,采用攻击预先设定的虚拟目标方案,达到期望的中制导末端性能指标;然后,开始末制导俯冲段,雷达开机实时攻击实际目标,使导弹在需用过载和导引头框架角约束条件下,以期望落角命中目标。仿真结果表明,该制导律具有期望的性能要求,易于工程实现。A new guidance plan was proposed in this study, which can make a super-sonic missile an realize expected terminal azimuth angle against fixed targets. Firstly, during the midcoure guidance dive phase, the guid- ance plan that the missile attacks a virtual target, which was contrived, was adopted, and it can make the missile realize ideal performance index. Next, during the terminal guidance dive phase, the missile can attack and hit the actual target with an expected terminal azimuth angle on real time after radar had turned on. Finally, the simulation results were presented to show the validity of the proposed method in practice.

关 键 词：制导 虚拟目标 俯冲 落角约束 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]