The stability analysis of a guidance scheme for following a given trajectory

A guidance scheme for following a given trajectory during the powered flight phase is presented, then a closed-loop guidance system is formed with the stability analysis performed. The commanded pitch attitude is a linear combination of a nominal attitude and a term proportional to the velocity and position errors in the vertical direction. The guidance function assigned to the yaw steering is for nullifying the miss distance in the lateral direction. The stability analysis is done by perturbing any state variable of the vehicle at some critical point along the guided flight trajectory. The prefilters, compensators, and gains are designed with the response characteristics of the system calculated.