Design And Aerodynamic Performance Study Of Bionic Variant Of Ballistic Correction Fuse

As modern warfare continues to evolve,the requirements for battlespace and combat-ready weapons are increasing,and the need to destroy the enemy while reducing damage to non-military facilities and avoiding casualties among non-military personnel has become a pressing issue.This paper adopts the engineering bionic research method of"functional homogeneity and institutional alienation",based on the inspiration of the configuration characteristics and dexterous movement behaviour of the silkworm chrysalis,to design a fuse capable of full circumferential rotation around the axis,and change the aerodynamic performance of the projectile by deflecting the fuse in different directions to make ballistic correction and achieve the function of avoiding obstacles during flight.The fuze is deflected in different directions to change the aerodynamic properties of the projectile and to make ballistic corrections to avoid obstacles during flight.The designed fuze deflection mechanism is applied to the AGARD-B model,and the effect of fuze deflection on aerodynamic performance is investigated by means of experimental design and numerical simulation.The main elements are as follows.(1)Design the fuze deflectable mechanism according to the shape characteristics of the silkworm pupa.The external contour of the pupa is extracted using Matlab,the external contour points are fitted,and the fitted equation is used as the design standard for the shape contour of the shell;the shells are connected to each other by a ball pair to ensure that the shells can rotate in the full circumferential direction;the driving device of the fuze deflector is designed,and the strength of the support rod and the driving rod are checked,and the positive stress and bending stress of the support rod and the torsional stress of the driving rod are all less than Through the static analysis of the fuze deflector mechanism during flight,the minimum value of the safety coefficient for both the undeflected and 6°deflected fuze deflector mechanism is 2.0954,which is in line with the design standard.(2)The dynamics of the fuze deflection mechanism was investigated by means of Adams simulation.With the drive function of the drive rod set to a trigonometric function with the independent variable being time,the designed fuze deflection mechanism is able to achieve full circumferential motion around the axis;the drive function is set to IF function and STEP function respectively,and the forces on the support rod and the drive rod are compared between the two;when the drag load applied to the flight,if the IF function is used,the maximum contact force between the drive rod and the support rod is 134.09 N,and the maximum torque applied to the drive rod is 537.47 N·mm;if the STEP function is used,the maximum contact force between the drive rod and the support rod is 118.47 N·mm.The DS3135 micro servo was selected for the maximum torque applied to the drive rod.(3)Introduce the test equipment and model for the wind tunnel test;describe the numerical simulation method and finally select the SST k-ωmodel;carry out grid division by STAR-CCM+and set up three sets of grids with 2 2 The maximum relative error of the medium grid was 1.05%,and the medium grid(about 7.1 million)was chosen as the grid for the numerical simulation;the feasibility of the numerical simulation method was verified by comparing the numerical simulation and wind tunnel test data.The maximum relative error of the drag coefficient is 5.9%,the maximum relative error of the lift coefficient is 5.7%,and the maximum relative error of the pitch moment coefficient is 2.2%under six working conditions of Mach 0.8 and angles of attack of 0°,2°,4°,6°,8°and 10°.(4)Using the Design Expert software,a quadratic regression orthogonal rotational combination test design with the factors of fuze deflection angle,incoming flow velocity and angle of attack was prepared,and the drag coefficients and yaw moment coefficients of the 18 sets of tests in the test design were obtained by numerical simulation and flow field analysis was carried out.angle,and the final equation for drag isCd=0.51342-0.97683v+0.888v~2,where v represents the incoming flow speed,the correlation between the three factors is fuze deflection angle>angle of attack>incoming flow velocity,and the final equation for the yaw moment coefficient is Cmy=-0.0002342+0.000405β+0.000121α-0.0000125α·β-0.0000117α~2,where α and β represent the angle of attack and the fuze deflection angle,respectively.