Design and Simulation of Harmonic Control for a Rolling Airframe R-Han 122 Surface-to-Surface Missile Using MATLAB–X-Plane Integration

Abstract

Rolling motion in airframe missiles improves gyroscopic stability but may also induce control coupling and oscillatory responses that reduce flight stability. This study aims to design and evaluate a harmonic control strategy for the R-Han 122 surface-to-surface missile by integrating MATLAB and X-Plane 10. A numerical simulation based on a six-degree-of-freedom (6-DOF) flight model was conducted by applying harmonic control with various amplitude and frequency combinations. Flight performance was evaluated using telemetry data, including altitude, ground trajectory, roll, pitch, yaw, velocity, and acceleration. The simulation results indicate that harmonic control effectively compensates for roll-induced control coupling, reduces oscillatory behaviour, and improves flight stability. The proposed simulation framework provides a practical basis for future development of indigenous missile guidance and control systems.