导弹的直接力/气动力控制系统设计  

Design of control system with direct thrust and aerodynamic force for a missile

作　　者：杨文骏[1] 张科[1] 张云璐[1] 

机构地区：[1]西北工业大学航天学院,陕西西安710072

出　　处：《飞行力学》2012年第4期349-353,共5页Flight Dynamics

基　　金：航空科学基金资助(20090153003);航天支撑基金资助(N9XW0002)

摘　　要：针对临近空间大气稀薄、防空导弹获得气动力较小的问题,提出了一种直接力/气动力复合控制系统设计方案。首先建立了导弹的气动控制系统模型,然后建立了采取轨控方式的直接力控制系统模型。以弹目相对距离作为直接力控制系统开启的判断条件,输出脉冲直接力,将气动力和直接力的控制作用叠加,构成了直接力/气动力复合控制系统,弥补了导弹末制导末段气动过载较小的不足,提高了导弹的制导精度。通过具体的仿真实例及定性分析,验证了该复合控制系统设计方案的有效性和可行性。A design scheme of compound control system with direct thrust and aerodynamic force is presented in this paper according to the problem that the anti-aircraft missile gets less aerodynamic force because of the rarefied atmosphere of near space.First,the model of aerodynamic control system of the missile was established,and the model of the direct thrust control system using orbit control was established.The relative distance between the missile and target was taken as the judging condition of starting the direct thrust control system,and the system outputs pulse direct thrust.Superimposing these two control effects composes the compound control system with direct thrust and aerodynamic force.It can make up for the deficiency of the low aerodynamic load at the end of terminal guidance and improve the guidance accuracy of the missile.The results and qualitative analysis show that the design scheme of the compound control system is effective and feasible.

关 键 词：临近空间 防空导弹 复合控制 直接力 

分 类 号：TJ765.2[兵器科学与技术—武器系统与运用工程]