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为了克服飞机消极、被动式防御手段的缺点,引入主动防御概念,建立了主动防御目标机-攻击导弹-防御导弹的几何模型,提出了三视线重合的主动防御策略,并在此基础上设计了比例-微分主动防御导引律。首先,分别以几何模型中的内角T,M和外角σ作为被控对象,分析其对导引性能的影响,确定了以外角σ作为被控对象的比例-微分主动防御导引律;然后,分析了防御导弹指令加速度在初始时刻振荡的原因,并提出了相应的解决方法;最后,对主动防御导引律进行了修正。仿真分析表明,所提出的主动防御导引律能够有效用于对来袭导弹的拦截。
In order to overcome the shortcomings of the passive and passive defensive aircraft, this paper introduces the concept of active defense, establishes the active defensive target-attacking missile-defensive missile geometry model, puts forward the active defensive tactics of three-line coincidence, and based on this, Differential Active Guidance Law. Firstly, the internal angles T, M and external angle σ in the geometric model are respectively used as controlled objects to analyze the influence on the guiding performance, and the proportional-differential active defense guidance law with external angle σ as the controlled object is determined. Then, the reason why the acceleration of the defensive missile instruction oscillates at the initial moment is analyzed and the corresponding solutions are proposed. Finally, the active defensive guidance law is amended. Simulation analysis shows that the proposed active defense guidance law can effectively be used to intercept incoming missiles.