Three loop topologies scheme of spinning missiles with decoupling control

摘要

Classical three loop topologies have been successfully employed in high performance command and homing guidance missiles. However, for spinning missile the cross-coupling effects between pitch and yaw channels which are induced by periodic rolling around longitudinal axis of missile have to be taken into account and decoupling is necessary in control system design. In this paper, dynamics model of spinning missiles in the form of complex summation is established and the state feedback controller is designed. Parameters of controller are obtained through eigenvalue placement for desired eigenvalues. According to physical components of missile control system, digital state observer is constructed. The control system results in a classical three loop topology autopilot with desired dynamic response. Meanwhile, the controller with complex feedback gains achieves decoupling control of spinning missile through cross-feedback-compensation. Finally, numerical simulation implied that the proposed method is efficient and suitable for engineering applications.