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针对未来高机动目标的拦截 ,运用非线性系统几何理论中的精确线性化方法 ,设计了一种空空导弹非线性末制导系统加速度指令。假设目标做逃逸机动 ,弹体 -自动驾驶仪响应用一个二阶环节描述 ,建立了导弹目标三维相对运动方程。根据终端约束直接选取系统输出阵 ,经动态反馈线性化 ,将非线性系统模型转化为线性方程 ,求得了目标任意机动时的非线性末制导系统的加速度指令。以纵向平面为例进行了仿真计算 ,结果表明该方法是行之有效的 ,得到的解可以用来改进导弹大离轴发射角时的进攻能力。
For the interception of high maneuvering targets in the future, an accurate linearization method of nonlinear system geometry is used to design a non-linear acceleration guidance system of air-to-air missile. Assuming that the target is an escape maneuver, the projectile-autopilot response uses a second-order link description to establish the three-dimensional missile’s relative motion equation. According to the terminal constraint, the system output array is selected directly. The nonlinear system model is transformed into the linear equation by dynamic feedback linearization, and the acceleration command of the nonlinear end-guidance system with any target maneuver is obtained. Taking the longitudinal plane as an example, the simulation results show that the method is effective, and the solution obtained can be used to improve the offensive capability of the missile when it is at a large off-axis launch angle.