Flying Attitude Control Principle And Method Of Projectile Based On Inertial Gyro

With the rapid development of modern technology,the requirements of modern warfare for weapons are becoming higher and higher.Ordinary ammunition cannot meet the operational requirements of modern warfare against the precision of weapons and ammunition.The appearance of the ammunition made up for the shortcomings of ordinary ammunition and met the requirements of modern warfare.For the ammunition,the ability of the correction mechanism directly affects the trajectory correction effect and strike ability.This paper proposes a method of controlling the flying attitude of the projectile with the inertial gyro mechanism as the actuator.The control principle of the inertial gyro mechanism,the parameters of the inertial gyro,the precession characteristics,the correction method,and the correction ability of the inertial gyro mechanism are studied.The aerodynamic simulation of the inertial gyro mechanism modified ammunition was performed using FLUEN aerodynamic software.The aerodynamic characteristics of the inertial gyro mechanism ammunition modified ammunition were analyzed,and the wind resistance function equation was fitted according to the simulation data.By analyzing the mechanical characteristics of the gyro,such as the gyro effect,moment of inertia,and momentum moment,the correction principle of the inertial gyro mechanism is studied.Inertial gyro correction mechanisms with different centroid distances,different masses,and different speeds are designed.Kinematics simulations of inertial gyro mechanisms with different speeds are performed,and the optimal inertial gyro correction mechanism is selected based on the simulation data.The kinematics simulation software ADAMS and the control software MATLAB were used to jointly analyze and study the precession characteristics of the inertial gyro mechanism,so that the force and moment generated when the inertial gyro precession acted on the projectile’s center of mass to control the projectile’s attitude.Based on the precession characteristics of the inertial gyro mechanism,four different precession directions are proposed,which are + x,-x,+ y,and-y.The kinematics simulation software ADAMS is used to analyze and study the four different precession directions.It is concluded that when the inertial gyro mechanism moves in the + y and-y directions,it can control the projectile flying attitude.The possible interference of projectiles in the muzzle exit and full ballistic flight is studied,and the errors generated by interference are simulated using kinematics simulation.Through the kinematics simulation,the influence of the inertial gyro mechanism on the projectile trajectory is analyzed,and the maximum correction ability of the inertial gyro mechanism in the lateral and longitudinal directions of the projectile exit from the muzzle and the highest point of the trajectory is analyzed.