Research Of Several Technical Problems Of The Guided Anti-armor Submunition

Intelligent ammunition is a precise strike munitions formed during the process of the development of traditional munitions.In this paper,the anti armor guided sub munitions are intelligent ammunition.The research focuses on the aerodynamic improvements,guided munition target acquisition probability and the mid-courese guidance law design.It can be mainly divided into the following five parts:First of all,a new method for improving the shape of BAT(Brilliant Anti-Tank Submunition)based on the rudder efficiency is proposed.In the first analysis,the change of the aerodynamic data of changing the wrap-around fininto the flat fin.Secondly,methodusing the wing body parts combined way to calculate the aerodynamic coefficient.The pitch control moment differential coefficient calculation formulawas derived.Be aimed at changing the condition of low rudder efficiency,the appearance of the BAT was modified from the aspect of the aerodynamics,including the change of chord length,wing length and the positionof the rudder.Under the premise that the size of the volume is constant and the carrying ability of the carrier is not influenced,the third plan can greatly improve the submunition's pitch control torque.Secondly,a method of getting the probability of the target acquisition probability in the guided munition terminal guidance is proposed.The trajectory model considering the disturbance factor is given.The zero-effect miss and the maneuvering ability of the guided munition were researched.The addition of the midcourse guidance in the guided munition attack and the geometrical position between the missile and the target during the missile flight were studied.The formula of the field angle of the seeker is obtained by the approximate calculation of the probability ellipsoid and the probability ellipse.Further more,a more general theory of the field of view by analytic methodis established.It uses the confidence interval to determine the probability of terminal guidance.The influence by different disturbance factors of the view angle's confidence interval was calculated.Thirdly,This section proposed a composite improved Monte Carlo method,which can effectively improve the calculation accuracy and reduce the number of simulation.The single factor variance and the double factor variance of line of sight misalignment angle are analyzed.Finally,the section puts forward a importance sampling measure analysis method based on the unknown probability distribution.Using copula sampling method for the factors has interaction.The importance measure of solving method was given in the complex condition in which a variety of interference factors have interaction effect.Forthly,two kinds of midcourse guidance law are proposed,which is used to solve the three dimensional guidance law with high probability target acquisition and terminal angle constraint.In the first place,be aiming at getting the best hand-off position and the attitude angles,the fitting function was got by the orthogonal function least squares method.Two kinds of guidance laws are designed,which are used in different design ideas.One is based on the traditional optimal guidance law and the other is biased proportional navigation.The optimal guidance law is designed to meet the requirements of terminal angle constraint.On the basis of the terminal angle constraint,the biased proportional navigation law of the first order polynomial and the two order polynomial are further designed.The baised proportional guidance law can satisfy the control of the line of sight rate.Furthermore,this part also gets the time-to-go estimation method.Last but not least,Two terminal guidance law with variable coefficients is proposed.In the first place,the non-gravity compensation guidance law and the gravity compensation guidance law are analyzed.Further more,in view of the random occurrence of the target in the actual situation,the variable coefficient guidance law is proposed,and the expression of the variable coefficient gravity compensation term is derived.At the end of the transition conditions of hand off phase is analyzed.A considered shift gradually fade out into terminal guidance law variable coefficient guidance law is proposed.This guidance law changes the acceleration continuously in the whole process.The research results of this paper have some reference value for the design of the aerodynamic design,target acquisition area and middle guidance of guided anti-armor submunition.