Boost–glide range-optimal guidance†

Abstract

A simple guidance scheme is proposed which approximately optimizes the range of the glide phase of a boost-glide vehicle's trajectory. The scheme requires only altitude, flight-path angle, and attitude measurements for implementation. The guidance law provides an attitude command based on the actual flight-path angle and on a calculated flight-path angle associated with that of an equilibrium, constant-dynamic-pressure, glide of maximum lift-to-drag ratio. By proper weighting of these two inputs, an approximately optimal guidance control is realized. Two examples are given which demonstrate the trajectory characteristics for a high-performance aircraft and for a missile-type vehicle.