| Citation: | CHEN Wei, SUN Chuanjie, FENG Gaopeng, et al. Design of decoupling controller for spinning missile based on receding horizon optimization[J]. Journal of Beijing University of Aeronautics and Astronautics, 2018, 44(4): 717-724. doi: 10.13700/j.bh.1001-5965.2017.0271(in Chinese)
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The spinning missiles are subjected to external disturbances and uncertainties during flight, and there are the aerodynamic cross-linking, inertial cross-linking and control cross-linking. To realize stable flight, it is necessary to design decoupling controller. Therefore, a decoupling control method based on the receding horizon optimization (RHO) was proposed. The kinematic models of the spinning missile and the servo system were expressed in the form of state space, and the augmented equations of state were obtained based on the equations of state of the spinning missile, the command filters and the integral of the tracking error. The control value was calculated using the RHO based on the command filter, and in order to realize the decoupling control of the spinning missile, the controller gains were adjusted in real time according to the difference between the system output and the command signal. Through the acceleration control simulation results, it can be seen that the designed control system is basically not affected by the spinning rate, the modeling errors and the external disturbances, which has high robustness.
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