Application of Closed Loop Optimal Guidance for a Constant Thrust Space Vehicle

Abstract

This research presents derivation and implementation of the explicit guidance problem to steer a space vehicle into exo atmospheric phase of flight to develop three-dimensional optimal trajectory. The proposed guidance algorithm is in association with continuous powered flight of the space vehicle in ascent manoeuvre. Stability, accuracy and simplicity of this approach are the improved developments in comparison with the IGM approach. This algorithm uses the calculus of variation method for the two boundary-value injection problem to generate an optimal trajectory of space vehicle with online generation of steering command to inject to any desired orbit. Here the end conditions have been determined as the orbital height, inclination and eccentricity where the initial conditions are fixed. The simulation results are considered which shows the accuracy and simplicity of this method to reach to the desired orbit in minimum fuel.