大离轴角发射导弹的制导律研究  

Feedback Linearized Guidance Law (FLGL) for High Off-Boresight Launch Conditions

作　　者：李新国[1] 周国财[1] 曾颖超[1] 

机构地区：[1]西北工业大学航天工程学院,陕西西安710072

出　　处：《西北工业大学学报》2003年第4期432-434,共3页Journal of Northwestern Polytechnical University

基　　金：航天科技创新基金 ( 2 0 0 1CH0 80 4 )

摘　　要：讨论了战术寻的导弹加速度受限、大离轴角发射的导引、制导问题。基于反馈线性化原理 ,提出了一种新的制导方案。在大离轴角发射条件下 ,应用反馈线性化制导律 ( FLGL)和比例导引方法 ( PN)进行了仿真计算。结果表明 。Proportional navigation (PN) law is the optimal guidance law for high off boresight conditions of short range air to air missile when the following assumptions hold: constant missile velocity, instantaneous missile response, nonmaneuvering target, and intercepts close to the collision course. When these assumptions do not hold, we propose a new feedback linearized guidance law (FLGL). Section 2 gives an important conclusion after applying to the missile target motion system the feedback linearized method of Ref.4 based on differential geometry nonlinear control theory. Section 3 uses this important conclusion to define the proper guidance strategy: when ｜Δ ψ m｜<α , PN law, eq.(6b), should be used; when ｜Δ ψ m｜>α , FLGL, eq.(6a), should be used. Section 4 gives simulation results, shown in Figs.2 and 3. These results show preliminarily that FLGL can provide significant improvements over traditional PN law for high off boresight conditions of short range air to air missile.

关 键 词：大离轴角 非线性系统 反馈线性化 制导律 

分 类 号：V448.133[航空宇航科学与技术—飞行器设计]