Hybrid Simulation Software Scheme for Validation of a Launcher Control System

Abstract

This work describes the strategy of a hybrid simulation program to be used in order to assess the performance of a satellite launcher control system. The hybrid simulation starts with two simulation programs, one that simulates the on board computer with control laws and the other that simulates the rest of the system. After validation of these two programs the hardware interfaces are then included. After a new validation, the real actuators are included in the system, and finally the real sensors are included. So in the final phase only the vehicle dynamics is simulated digitally, and as this is the most real condition possible before the real flight, it represents the best condition to assess the flight control system performance and to detect possible problems not clear at the design phase. The work describes mainly the method used in order to obtain a very reliable hybrid simulation program for a satellite launcher control system.