MRAC for A Launch Vehicle Actuation System
Actuators are used to provide Thrust Vector Control (TVC) for lifting the launch vehicle and its payload to reach its space orbits. The TVC comprises actuation and power components for controlling the engines direction and thrust to steer the vehicle. Here the actuator considered is a linear Electromechanical Actuator (EMA) system. The design is based on the Model Reference Adaptive Controller (MRAC) technique. It calculates an error value as the difference between actual system and desired model and attempts to minimize the error by adjusting the controller parameters. Adaptive control laws are established with the gradient method. The experimental result shows that the MRAC has better tracking performance than that with the traditional compensated system when both controllers are subjected to the same parameter variations. The simulation is done using MATLAB/SIMULINK software.
KeywordsEMA Compensator MRAC MIT rule
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