考虑舵机动力学的旋转弹自适应解耦控制

doi:10.7527/S1000-6893.2021.25068

Abstract

Abstract: An adaptive decoupling control method considering aerodynamic uncertainty and actuator dynamics is proposed to solve the strong coupling problem caused by aerodynamic, inertial and control cross-coupling.Considering a type of canard controlled spinning rockets, an acceleration dynamic model considering actuator dynamics is established under the non-rolling body frame.Using the model reference adaptive control method as the basic framework, the tracking error integral is extended to the controlled system to improve the tracking performance of the closed-loop system.The error signal between the input and output of the actuator is fed back into the reference model to realize the decoupling between the pitch and yaw channels.Theoretical analysis and numerical simulation show the effectiveness of the proposed method.The simulation results show that the adaptive decoupling controller developed in our study can ensure stability of the closed-loop system and realize the decoupling between the pitch and yaw channels.

Key words: spinning rocket, adaptive control, decoupling control, actuator dynamics, quadratic stability

CLC Number:

V249.1

SHI Zhongjiao, ZHU Huajie, ZHAO Liangyu, LIU Zhijie. Adaptive decoupling control for a class of spinning rockets considering actuator dynamics[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(3): 325068-325068.

References

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Adaptive decoupling control for a class of spinning rockets considering actuator dynamics

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