|
Deflection warhead control is a new control . Unlike traditional rudder control guided weapons , the deflection warhead control guided weapons without a rudder , but on the deflection of the head relative to the projectile axis control . Its shape is simple , compact structure, the influence of air resistance is small , suitable for tubular emission . In this paper, the numerical simulation of the aerodynamic characteristics of the tail MISSILES head declination study and analyze deflection warhead control mechanism . This selection of elliptic differential equations method to generate around with an Angle tail MISSILES structured grid . Euler equations using the AUSM differential format, and LU-SGS implicit time marching method , the numerical simulation of the flow field MISSILES , get to Mach number M ∞ = 2.0, 3.0, 4.0 , angle of attack α = -8 ° - 4 °, -2 °, 0 °, 4 °, 8 °, head in the pitch plane deflection angle β = 0 ° , 4 ° , 8 ° state flow field parameters . Integrating the pressure field of numerical simulation to calculate the various aerodynamic coefficients under various flight status : axial force coefficient CA , the normal force coefficient CN drag coefficient CD and lift coefficient CL, pitching moment coefficient Cm, and the experimental results contrast, the analysis of the aerodynamic characteristics of the tail head declination MISSILES . The pressure coefficient distribution given head angle of attack plane pressure contours and a head flow field section of the aerodynamic characteristics of the head . The calculation results in line with the basic aerodynamic law , consistent with experimental data . In the case of the 0 ° angle of attack , the head deflection 8 ° pitching moment coefficient is a large positive MISSILES in an unstable state , increasing the angle of attack . Deflection warhead control the way it is in order to control MISSILES .
|