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A Feedback Linearization Control of Morphing Missiles

This paper proposes an attitude control method for variable-wing missiles. First, the aerodynamic parameters of the missiles are generated using the Missile DATCOM, and then they are fitted into the polynomial functions for controller design. Due to the morphing structure and strong nonlinearity of variable-wing missiles, working-point-based model linearization will lose model accuracy and consequently degrades the control performance. In this paper, an attitude controller for morphing missiles is proposed by combing the disturbance observer and the feedback linearization (FL) method. Theoretical research and numerical simulations show that the designed control system is suitable for morphing missiles, and has strong robustness to system parameter perturbations and external disturbances.