不同制导律下天线罩误差对导弹性能的影响

Effect on Missile Performance Due to Radome Error Under Different Guidance Laws

以反辐射导弹的制导控制系统设计为应用背景,研究不同制导律下天线罩误差对导弹制导控制系统的影响。建立了比例导引律和速度追踪律下的天线罩误差寄生回路模型和制导回路模型,采用伴随法和无量纲方法,仿真分析了2种制导律下天线罩寄生回路的稳定性以及不同噪声源下的无量纲脱靶量,并进行了对比研究。仿真结果表明,比例导引律对应的寄生回路稳定域要小于速度追踪律;在雷达导引头噪声的作用下,比例导引律下的无量纲脱靶量大于速度追踪律,而在目标机动的情况下,比例导引律的制导精度要优于速度追踪律。

Under the application background of guidance and control system design in anti-radiation missile, the effect on missile guidance and control system due to radome error by different guidance laws is studied. The models of radome error parasitic loop and guidance loop under the guidance laws of proportional navigation（PN）and velocity pursuit（VP）are put forward. With the method of adjoint and dimensionless, the stability of radome error parasitic loop and the dimensionless miss distance by different noise sources under two guidance laws are comparatively analyzed in simulation. The simulation results show that the stable region of parasitic loop under PN is smaller than that under VP. With the radar seeker noise, the dimensionless miss distance under PN is smaller than that under VP. With the target maneuvering, the guidance accuracy of PN is better than that of VP.