The Design Of Air Defense Missile Guidance And Control System At Cape Brewster Is Considered

When air defense missiles intercept ultra-low-altitude targets,in order to effectively improve the ultra-low-altitude interception performance of air defense missiles,the Brewster flight trajectory can be designed to reduce sea clutter interference,and provide effective observation information of ultra-low-altitude flying targets to minimize The effect of multi-path interference on target tracking accuracy improves intercept accuracy.Aiming at the typical anti-ultra-low-altitude air defense missile modeling problem,the definition of each coordinate system and conversion angle is given,and the conversion relationship between each coordinate system is derived;the relative motion relationship between the missile and the target is constructed,and the relative motion is established Model;Taking the shape parameters of the "Sea Sparrow" missile intercepting ultra-lowaltitude targets as a reference,the aerodynamic parameters of a typical anti-ultra-lowaltitude air defense missile are calculated,and the correlation law of aerodynamic parameters varying with the angle of attack and Mach number is analyzed,and the center of mass Parameters,moment of inertia parameters of the missile is obtained..Aiming at the high-precision terminal guidance problem under the constraint of Brewster angle,a three-dimensional smooth super-helical terminal guidance law for antiultra-low-altitude air defense missiles is designed based on a finite-time high-order sliding mode algorithm,which ensures that the line-of-sight angular velocity converges to the desired layout within a finite time.Aiming at the chattering problem of traditional sliding mode control,a homogeneous high-order sliding mode differentiator that estimates the target acceleration is introduced to perform feedforward compensation for the smooth super spiral guidance law.The super spiral algorithm is used to replace the traditional reaching law,which can effectively suppress chattering and ensure higher convergence accuracy of sliding mode variables.Aiming at the high-precision active disturbance rejection controller design problem of the typical anti-ultra-low-altitude air defense missile under complex interference,the tracking differentiator in the auto-disturbance rejection control method is used to achieve fast and non-overshoot tracking of the input signal of the system;The extended state observer realizes the dynamic estimation of the disturbance,and effectively reduces the nonlinear influence of the aerodynamic parameter uncertainty and modeling uncertainty on the control model;the nonlinear error feedback control law is designed to improve the performance of the auto disturbance rejection controller performance.