LPV techniques for the control of an airborne micro launcher

Abstract

This paper addresses the robust control of a micro-launcher. The general framework of this work is a R&D project of the French space agency (CNES) focused on new launchers. The objective was to evaluate the potentialities of Linear Parameter Varying (LPV) techniques for the specific problem of launchers control. As a realistic test case, the micro-launcher preliminary research program, supported by the CNES Launcher Directorate, has been considered. First a Linear Fractional Transformation (LFT) based model of the launcher has been established and validated. Then two strategies have been chosen to design a robust controller of the angle of attack: a complete LPV controller has first been developed; then a controller based on an LFT representation of a classical lead phase controller has been considered. Realistic simulations have been conducted to compare both strategies with a more traditional interpolated lead phase controller. Finally, the simulation results exhibit very promising results, allowing a total respect of the performance specifications