Study On Rising Segment Flight Trajectory Aerodynamic Of Smoothbore Fin-projectile

In the missile design and test ranges,are required for rapid calculation of dynamic characteristics of rocket gas outer shells,of a type of fin stabilized projectile smoothbore ascent aerodynamic research,using FLUENT and MATLAB software to solve the problem.Firstly,the aerodynamic parameters are calculated.Smoothbore fin stabilized projectiles in outer ballistic flight,with different speed and different attitude motion.The engineering algorithm is studied and calculated by using the component combination method.The zero lift drag coefficient and the lift coefficient are analyzed.Application of FLUENT software to establish the flow field model of fin stabilized projectile smoothbore,analyzes the flow characteristics of the air flow field at subsonic,transonic and supersonic;aerodynamic force and torque on the trajectory of the solution,the characteristics and changes of aerodynamic force,aerodynamic coefficient and aerodynamic moment coefficient on the stability of reserves;calculate,remain at 12%~20%,with better stability of flight.Secondly,the calculation of exterior trajectory is carried out.The conversion between the coordinates used in the exterior ballistics and their.The establishment of the equations of motion in Cartesian coordinates,the zero lift drag coefficient fitting Simulink module using the MATLAN model,given the initial conditions to solve the equation,the change of the projectile trajectory and trajectory angle.The smoothbore fin stabilized projectiles as rigid body,analysis of force and moment during the flight,the decomposition suitable coordinate system,establish the rigid body trajectory equation,the aerodynamic parameters of FLUENT software were fitted using the block modeling method,established a simulation model,by solving the trajectory equation of rigid body the obtained motion track,velocity curve and various azimuth.Finally,the design and the test speed smoothbore fin stabilized projectile,obtained through experiments and initial flight trajectory ascent typical position speed,comparing the simulated data,the error is less than 5%,the accuracy of the model was proved.