An analytic solution of the state-dependent Riccati equation (SDRE) method is presented for two-dimensional nonlinear systems, and the closed-loop system of the missile longitudinal autopilot designed by the SDRE method is analyzed using the analytic solution. The analytic solution is obtained using the matrix sign function of the Hamiltonian matrix corresponding to the SDRE, where the matrix sign function is represented using the principal square root of the Hamiltonian matrix. The missile longitudinal acceleration autopilot is designed based on the output feedback SDRE method for command tracking. The asymptotic stability of the closed-loop system and the nonsingularity of the output feedback control command are shown using the analytic solution to the SDRE method. A numerical example of the main results is provided, including the effects of aerodynamic uncertainty. Additionally, a six-degrees-of-freedom simulation for the skid-to-turn missile demonstrates the performance of the proposed acceleration autopilot with the roll stabilization control.
Analysis of Missile Longitudinal Autopilot Based on the State-Dependent Riccati Equation Method
Journal of Guidance, Control, and Dynamics ; 42 , 10 ; 2183-2196
2019-10-01
Article (Journal)
Electronic Resource
English
British Library Conference Proceedings | 1999
|Numerical State-Dependent Riccati Equation Approach for Missile Integrated Guidance Control
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