The Aerodynamic Research On Pitching Motion Of Wingless Guied Rocket Under The Supersonic

In recent years,wingless type configuration is widely used in guided rockets because of it's simple structure,high efficiency of rudder-face and excellent processing property.The cancellation of the main wing can decreats the aerodynamic drag greatly and increase the performance of stability when without control flight.However,this aerodynamic layout also exist some problems:during the supersonic flight course,the pressure center of rockets is in advance which result in the declined of the performance of stability.Morever,with the change of Mach number,the pressure center change obviously.In order to solve this problem,this paper combining with experimental research and numerical simulation method,by improving the aerodynamic configuration layout to improve the stability of the wingless type rockets.And explore the method of improve the performance of maneuverability with the guarantee of stability.Firstly,in order to research which is the aerodynamic characteristics effect of the noseof wingless type rockets,we launch a wind tunnel experimental to analyse aerodynamic characteristic of three different nose of wingless type rocket.Then we analyse the transformation law of the aerodynamic characteristics.Research shows that the rocket model using single cone nose has a better stability than two double conical,it also have a good effectiveness on drag reduction at the same time.Sceondly,in order to research which is the aerodynamic characteristics effect of the wing of wingless type rockets,we launch a wind tunnel experimental to analyse three different wing of wingless type rocket,and obtain the ransformation law of aerodynamic characteristics of drag coefficient,normal force coefficient,pitch moment coefficient and pressure center coefficient of different model under supersonic.Research shows that rocket model with the wing of largest area has a better dirigibility,but it has no use for the effect of drag reduction.Finally,with method of numerical simulation,we analyses aerodynamic contribution of different parts to the whole rockets to explain the experimental results.With the method of flow field analyse to show the change of flow condition and the cause of aerodynamic characteristics change.