Study of proportional navigation guidance error caused by angular noise and glint effect

The proportional navigation (PN) guidance error caused by angular noise (thermal noise) and glint effect in radar seeker receiver is studied. According to actual problems, a model of the PN guidance system is established. Considering the bandwidth of the angular noise is much large than the system bandwidth, so it is convenient to regard the angular noise as white noise. Also the low frequency glint is regarded as the white noise having passed through a first order filter. Simulation results demonstrate that the guidance error caused by angular noise and glint effect has a direct bearing on the dynamic characters of the seeker and autopilot. When the guidance time is longer, the miss distance due to angular noise has no relationship with guidance time. And there is a well-known technique called frequency agility which can be used to reduce the guidance error due to glint effect.