State Space Analysis and Optimal Control for Aircraft Simulator Pitch Electric Control Loading System

An electric control loading system for aircraft simulation was analyzed and modeled to find a linear state space mathematical model and state feedback. An optimal control scheme based on the minimum integral of the squared difference between desired and actual output was shown to be effective by comparing the output values of the system with previously obtained experimental data. A linear state space mathematical model and state feedback appear to provide satisfactory means for controlling an electric control loading system can be adjusted to simulate a wide variety of real aircraft by altering input and output gains at the force analog computer when aircraft parameters are changed.