飞航导弹控制律不确定性优化设计  

Uncertain Optimum Design of Control Rule for Cruise Missile

作　　者：李晓斌[1] 江振宇[2] 王澈[3] 

机构地区：[1]中国人民解放军92941部队 [2]国防科学技术大学航天科学与工程学院 [3]空军工程大学科研部

出　　处：《弹道学报》2013年第4期32-37,共6页Journal of Ballistics

基　　金：国家自然科学基金项目(51105368);中国博士后科学基金项目(200801491)

摘　　要：为解决飞航导弹边界发射条件下导引头无法快速捕获跟踪目标的控制律设计问题,建立了控制律不确定性优化设计模型,开展了动力、气动、环境和火控等多学科系统分析模型的不确定性研究,采用基于约束条件转移的不确定性优化设计方法进行求解,得到了稳健、可靠的最优控制律参数。飞行试验结果表明,与原设计方案相比,导弹转平飞结束时间提前了6.1s,保证了导弹转平飞后导引头快速捕获跟踪目标。The seeker can＇t acquire and track target rapidly when the cruise missile is launched under boundary conditions.To solve the problem,the model of the uncertain optimum design for control rule was established,and the uncertainty of the multidisciplinary system analysis models consisting of propulsion,aerodynamics,environment and fire control was systematically studied.A robust and reliable control-rule design was resulted by the method of uncertain optimum design based on transfer constraint conditions.The flight test result shows that,horizontal flight point time of the optimum design is shortened 6.1 s than that of former design,and the seeker can acquire and track target rapidly.

关 键 词：飞航导弹 控制律 不确定性 优化设计 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]