Research On Flight Control Method Of Rotary Missile

In modern and information warfare,low-cost guided ammunition can be used to attack many widely distributed targets with insufficient value,and play an important role in combat weapon system.However,the requirement of both low-cost and high-precision poses new challenges to guided ammunition.Rotary missile emerges rapidly because of its advantages of low manufacturing cost and strong flight stability.Then there are strong cross-linking coupling,motion coupling and control coupling in the spin maneuvering process of the rotary missile,which have a serious impact on the flight stability of the rotary missile.Therefore,it is urgent to study flight control methods.Firstly,based on the special motion characteristics and control mechanism of the rotary missile,the mathematical model of the rotary missile motion is constructed.Aiming at the special motion characteristics of rotary missile,the relevant coordinate system is constructed,and the motion equation o f rotary missile's center of mass and the motion equation around the center of mass are deduced in the relevant coordinate system.The control structure of the single-channel actuator of rotary missile is analyzed,and the aerodynamic and aerodynamic moment models of both the homogeneous and transient forms are established.The mathematical models of the motion of the rotary missile in both the homogeneous and transient forms are deduced.Secondly,the cycle average PID control design of rotary missile base d on compound decoupling is carried out.Starting from the mathematical model of rotary missile's homogeneous state,the coupling transfer function is deduced based on Kramer's law.Considering the special control mechanism of rotary missile,a periodic average PID control theory is proposed.The controller parameters are designed under the condition of considering the periodic average control action.The coupling analysis between rotary missile channels is carried out,and the decoupling between control channels is realized based on the composite decoupling method.Coupling design,dual-channel control simulation and non-linear simulation are carried out to verify the feasibility of the scheme.Finally,the sliding mode control design of rotary missile is carried out in view of the complex environmental impact.Considering that there are strong uncertain disturbances and large aerodynamic uncertainties in the flight process of a rotating missile,a sliding mode controller is designed for mismatched disturban ces.A sliding mode observer is designed to compensate the complex disturbances including external disturbances,aerodynamic deviations and coupling effects.At the same time,a nonlinear sliding mode controller is designed based on the motion characteristics and control requirements of the rotating missile to realize the stability control of the rotating missile under strong disturbances and large uncertainties.Through the simulation of two-channel control,the control accuracy and anti-disturbance characteristics of the two control methods are compared,and the practical significance of the scheme is verified by Monte Carlo simulation.