True proportional navigation system with acceleration saturation constraint (Q2735068)

The chasing missile and the target are modelled by two material points, moving in the plane under accelerations, with a special structure. The pursuer acceleration is governed by the true proportional navigation guidance law. This acceleration is constrained by a certain maximum amplitude due to saturation effects. The pursuer operations can be categorized into four cases, corresponding to the non saturation mode, two modes of partial saturation, and the saturation mode throughout. The interception conditions are derived for these four cases. The observability of the system is considered with the use of the range observability index.NEWLINENEWLINEFor the entire collection see [Zbl 0962.00004].