导弹三维制导控制一体化设计  

Three-dimensional guidance and control for missile

作　　者：尹永鑫[1] 杨明[2] 王子才[2] 

机构地区：[1]中国航天空气动力技术研究院第十一总体设计部,北京100074 [2]哈尔滨工业大学航天学院,黑龙江哈尔滨150001

出　　处：《电机与控制学报》2010年第3期87-91,共5页Electric Machines and Control

基　　金：国家自然科学基金(60434010);黑龙江省杰出青年基金(JC200606)

摘　　要：针对导弹的三维制导控制一体化设计问题,给出了基于微分几何和特征结构配置的一体化设计方法,以保证导弹能够垂直命中目标。综合考虑制导回路与控制回路之间的耦合关系、纵向通道与侧向通道之间的耦合关系,给出了导弹的三维制导控制一体化模型,使用微分几何方法对一体化模型进行了反馈线性化,基于特征结构配置方法根据期望性能设计三维制导控制系统的结构。仿真结果表明,针对不同的仿真算例脱靶量都小于0.5m,同时弹道倾角都大于83.5°、弹道偏角都小于5.5°,说明该方法满足制导控制精确度要求,而且在命中目标的同时能够满足对攻击角的约束。In order to ensure hit target as well as trajectory constraint, the design method based on differential geometry and eigenstructure assignment theory is presented to solve the problem of missile＇ s threedimensional integrated guidance and control. With a view to coupling between guidance loop and control loop, and coupling between longitudinal channel ometry relation between missile and target, the in and lateral channel, and three-dimensional relative getegrated guidance and control model was presented. According to this model, the feedback linearization method of integrated guidance and control was given using by differential geometry theory. The design method was given based on the eigenstructure assignment theory to ensure anticipant performance of system. Simulation results show that miss distance is less than 0. 5m, and trajectory inclination angle more than 83.5°, and angle of trajectory rotation is less than 5.5°. Therefore this integrated guidance and control method can implement efficiently hitting target as well as ensure attack constraint.

关 键 词：制导控制一体化 反馈线性化 微分几何 特征结构配置 

分 类 号：V448.15[航空宇航科学与技术—飞行器设计]