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基于平面内目标-导弹相对运动方程,考虑导弹自动驾驶仪的二阶动态特性,应用动态面控制方法设计了一种新型导引律。在设计过程中,通过引入一阶低通滤波器,使得导引律的最终表达式中不含视线角速率的高阶导数,更易于实际应用。该导引律有效地克服了导弹控制系统的动态延迟对制导精度的影响。将该导引规律与未考虑导弹自动驾驶仪动态的自适应滑模导引律相比较,对目标非机动、阶跃机动和正弦机动三种情况进行仿真。仿真结果表明,在目标机动加速度快速变化,而且导弹自动驾驶仪存在较大滞后情况下,这种导引律仍具有很高的制导精度。
Based on the in-plane target-missile relative motion equation and considering the second-order dynamic characteristics of the missile autopilot, a new guidance law is designed using the dynamic surface control method. In the design process, by introducing a first-order low-pass filter, the final derivative of the steering law does not contain high-order derivative of the line-of-sight angular rate, which is more practical. The guidance law effectively overcome the missile control system dynamic delay on the guidance accuracy. Compared with the adaptive sliding mode guidance law which did not consider the dynamics of the missile autopilot, the guided law was simulated and the three cases of non-maneuver, step maneuver and sine maneuver were simulated. The simulation results show that the guidance law still has a high guidance accuracy under the condition that the target maneuvering acceleration changes rapidly and the missile autopilot has large lag.