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本文应用现代控制理论的状态空间技术进行倾斜-转弯导弹自动驾驶仪设计方法的研究。该方法能够适应俯仰轴和偏航轴之间的陀螺仪和科里奥利交叉耦合。交叉耦合是由可能出现的高滚动角速度引起的。在设计中,可假定滚动角速度是常数,但不是零,这样的自动驾驶仪结构,其俯仰和偏航通道之间的交叉耦合取决于滚动角速度。自动驾驶仪增益也可预定为动压的函数。具有固定增益的降阶广义卡尔曼滤波器可用于估算执行机构的状态和指令加速度。按照这种方法设计的自动驾驶仪的性能,可用典型的高性能战术导弹动力学通过六自由度仿真来评估。从小的脱靶量和侧滑角来看,所获得的性能是优良的。
In this paper, state space technology of modern control theory is applied to the design of tilt-turn missile autopilots. This method is able to accommodate the gyroscope and Coriolis cross-coupling between the pitch and yaw axes. Cross-coupling is caused by the high rolling angular velocity that may occur. In the design, it can be assumed that the roll angular velocity is constant, but not zero, and the cross-coupling between pitch and yaw paths of such an autopilot structure depends on the roll angular velocity. Autopilot gain can also be predetermined as a function of dynamic pressure. The reduced-order generalized Kalman filter with a fixed gain can be used to estimate the actuator status and command acceleration. The performance of the autopilot designed in this way can be evaluated by six-degree-freedom simulations using typical high-performance tactical missile dynamics. The resulting performance is excellent from small miss distances and side slip angles.