| The projectile have the intense aero heating problem in the hypersonic flight,not only the temperature of the surface of the projectile increase sharply,but also the internal charge will face strong thermal environment.The 3D unsteady heat conduction equation is solved for aero heating problem,using the GAMBIT software for the projectile mixed mesh generation and boundary setting.In order to verify the validity of the calculation.This paper was verified from two aspects : firstly,comparing the results of the projectile's aerodynamic characteristic with the theoretical value,through the calculation we have found that the results is close to the theory.the value of the drag coefficient decreases with flight Mach increasing;secondly,comparison with literature.The literature has been verified reliability by comparing with experiment,and the results of this paper example are the same as those in the literature,the inaccuracy error is less than 10%,so this method can be used to calculate the aero heating problem.This paper has discussed the thermal temperature of hypervelocity projectile and internal charge from four aspects : 1)the material of projectile.The heat absorption capability and the rate of thermal transmission varies with the character of the material.It also influence the temperature variation of the internal charge;2)wall thickness of the projectile.This paper has discussed the effect of two kinds of wall thickness on temperature of the internal charge;3)the shape parameter of the projectile.The influences of aero heating problem have been discussed from the different projectile head and cone angle.And the temperature rise curve was plotted in this paper;4)flying condition.This paper has calculated and analyzed the aero heating problem from different velocity and flight height.the numerical results provide a reliable foundation for the design of projectile and internal charge,improving the designing efficiency of the projectile and the internal charge. |
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