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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。
Aiming at the problem of thinner air near the space and the smaller aerodynamic gain of air defense missiles, a direct force / aerodynamic compound control system design is proposed. First, the aerodynamic control system model of the missile is established, and then a direct force control system model adopting the track control mode is established. With the relative distance of projectile as the judgment condition of the direct force control system opening, the direct force of pulse is output, and the control action of aerodynamic force and direct force is superposed to form the direct force / aerodynamic compound control system, which makes up for the aerodynamic The problem of smaller overload increases the missile guidance accuracy. Through the concrete simulation example and the qualitative analysis, the validity and feasibility of the design scheme of the compound control system are verified.