Study On Aerodynamic Characteristics And Optimization Method Of A Spin-Stabilized Projectile Equipped With Microspoiler

With the change of modern war mode,the requirements of precision attack for missile and arrow weapons are constantly improved.The simple guidance and intelligent transformation of conventional missiles and arrows are the problems that must be faced to enhance China’s national defense forces.The accuracy level and technology of the existing missiles have been quite mature,which can meet the needs of the battlefield,but its high cost can not meet the requirements of a wide range of equipment.Based on the low-cost standard shells,the intelligent and guidance improvement of ammunition can improve its hit accuracy,reduce costs and reduce collateral damage.The guidance technology of fin stabilized projectile has been relatively mature,but the guidance transformation of high-speed spinning missile relying on gyro stabilization is only in the initial research and development stage in China.In a long period of time in the future,the guidance transformation,pneumatic control actuator research and development,and aerodynamic characteristics research of the spin stabilized projectile still need to be continuously promoted.In this paper,the theoretical and technical problems such as trajectory characteristics,aerodynamic characteristics and aerodynamic shape optimization of a rotating stabilized correction projectile with a spoiler correction control unit are studied:According to the aerodynamic layout and controlled motion characteristics of the spoiler rotating stability correction projectile,based on the momentum theorem and the momentum moment theorem,the six degree of freedom rigid body trajectory model of the correction projectile and the controlled particle trajectory model considering lateral overload are established.By using the established trajectory motion model,the uncontrolled flight,controlled flight and correction ability are simulated and analyzed,and the trajectory characteristics of this kind of correction projectile are improved Preliminary understanding.Referring to the existing foreign spoiler shape design,the following designs are designed:1.Vertical spoiler with three shape variables of spoiler arc length,spoiler height and arc length to tip ratio;2.Two types of inclined vertical spoiler with single slope and double slope.The aerodynamic characteristics of the projectile with the above-mentioned fins are studied.Firstly,the geometric modeling and mesh generation of the uncontrolled bomb and the controlled bomb are carried out,then the aerodynamic simulation calculation of the uncontrolled bomb and the modified bomb with different shapes of spoiler are carried out at the subsonic,transonic and supersonic speeds respectively;then the conventional aerodynamic coefficients such as drag coefficient,lift coefficient and static moment coefficient of the uncontrolled bomb are obtained by post-processing,and the induced drag coefficient,lift coefficient derivative and static moment coefficient are processed Finally,the aerodynamic coefficients and aerodynamic coefficients are obtained by subtracting the aerodynamic coefficients and the aerodynamic coefficients with and without aerodynamic fins.The neural network model and Kriging model are constructed as the surrogate models of aerodynamic calculation.The process of obtaining the aerodynamic coefficient of the spoiler by numerical simulation is predicted,and then the optimization method of the aerodynamic shape of the spoiler is studied.A fast prediction model of aerodynamic coefficient is used to study the trajectory correction characteristics of correction projectile.Under the controlled condition,the trajectory curve and the angle of attack of the projectile at the same control direction and different start-up time are studied.The trajectory characteristics are simulated by changing the control phase,and the influence of different control directions on trajectory correction ability is observed.