Research On The Guidance Method Of Air-to-Ground Guided Missile

Set in the requirements of high precision attack against low collateral damage in modern battlefields and on the basis of the development trend of space-based guided missiles,this dissertation has systematically studied the proportional guidance guidance law and biased proportional guidance guidance law which are used by air-to-ground weapons.Firstly,three typical ultra-lightweight space-to-ground missiles were used as an example to illustrate the development trend of air-to-ground weapons.Specifically,the development process and trend of open space weapon guidance law are discussed in details.By introducing a small-angle hypothesis,the linearized model of the proportional navigation guidance law has been obtained which elaborates the principle of the adjoint method.Through the adjoint method and the time-scale transformation,the dimensionless adjoint model of the proportional guidance guidance law has been obtained.This model study shows different guidance parameters in the proportional guidance exert an influence on the miss distance caused by the initial speed pointing error signal,the receiver angular noise signal,and the target flicker noise signal.The research results show that the miss distance caused by the initial speed pointing error changes fluctuates until it converges to zero with the increase of the terminal guidance time.The larger the dynamic order of the guidance system,the larger the oscillation amplitude is.Unlike the missed amount due to deterministic error,the miss distance generated by the angular noise and flicker noise does not converge to zero with the increase of the terminal guide time.The miss distance generated by the above two signals varies with the guidance coefficient and the dynamic order of the guidance system and the value increases.A bullet kinematics model for a fixed target biased proportional guidance guidance law has been established.By introducing a small-angle hypothesis,the analytical solution of biased proportional guidance under this model has been obtained.The ballistic stability domain has been discussed.Two kinds of bias item allocation schemes has been designed,which shows that the larger the target constraint angle,the larger guide coefficient,the higher the missile’s degree of lift during flight.When setting the time-varying bias term,the missile lifting height is greater.When setting the constant bias term,the overload command will undergo an overshoot during flight.Therefore,from the perspective of stability,it is more reasonable to set the time-varying bias term.The target kinematics model of the biased proportional guidance guidance law for uniform linear motion has been established,and the trajectory and various guidance parameters has been simulated and analyzed over time.The study shows that the biased proportional guidance guidance law for uniform linear motion of the target can still meet the need to use the bias integral amount to achieve the control for falling angle by designing a reasonable bias term allocation scheme.The larger the constrained angle of attack,the larger the coefficient of guidance,the higher the degree of missile lift during flight.The influence of gravity on the biased proportional guidance guidance law has been studied,which shows that gravity has less effect on the accuracy of the missile’s hit target’s position and its trajectory.When the target moves,there will be a falling angle error due to the influence of gravity.