Guidance Law Design Using Time-Limited Balanced Autopilot Model Reduction

摘要

The paper compares two types of missile autopilot reduced order mod-els in the setting of OGL guidance law where the target maneuver is astep in the target acceleration. One model approximation is based on theusual innite time Gramians. The second model approximation is basedon Gramians calculated in the interval [t; T_f ] where T_f is the expectedintercept time. Since the characteristics of the autopilot step responseat large time-to-go may be quite dierent from that at short time-to-go,a better approximation is achieved by using Gramians calculated in theinterval [t; T_f ].