Study Of Aerodynamic Characteristics For A Fin-Stabilized Projectile With A Deflectable Nose Control

The projectile with deflectable nose control is a new way of controlling. It is governed by the deflectable of the nose as to the axis of the projectile without the rudder, which is different with the conventional weapons controlled by the rudder. The projectile with deflectable nose control is adapted to launch by the tube because of its simple look, compact frame and the small draft. This paper study and analyze the aerodynamic characteristics of the projectile with deflectable nose control.An elliptical differential equation method of grid generation is applied in this paper. The three dimensional Euler equations are solved by implicit LU-SGS and the AUSM different scheme. It can be obtained the pressure of flow field at mach numbers of 2,3,4, angles of attack of-8,-4,-2,0,4and 8 and angles of the nose of 0,4,8 by numerical simulation. The coefficients of drag, lift, pitching moment, roll moment and so on are calculated by the integral of projectile surface force according to the flow field parameters. The results are compared with the data of the experiment, as well as the aerodynamic characteristics of the projectile with deflectable nose control are analyzed. Meanwhile, it can be obtained the pressure of the flat of the deflectable nose in order to analyze aerodynamic characteristics of the nose.The calculated results accord with the aerodynamic theory as well as the data of the experiment. In the case of the angle of attack of 0 and angle of the nose of 8, the number of the coefficient of pitching moment is not small. The projectile is in the state of instability, and the angle increases constantly, which is the way to control the flying posture of the projectile with deflectable nose.