为了研究弹头偏转角对弹箭外弹道的影响,进行了弹头可偏转火箭弹的气动特性和弹道特性研究。首先利用流体力学软件对不同弹头偏转角的弹箭模型在不同马赫数飞行的情况进行绕流流场数值模拟,获得各弹箭模型的气动力参数,然后通过六自由度弹道模型对弹头可偏转火箭弹的外弹道进行数值计算,并进行典型试验验证。试验结果与仿真结果吻合良好,弹头偏转角可以提供有效的弹箭落点横向偏移距离,研究结果可为自适应智能弹箭的研制与工程应用提供理论与技术支持。

In order to study effect of nose deflection angle on missile's external ballistics, research on aerodynamic and ballistic characteristics of rocket projectile with deflectable nose was conducted.Flow field numerical simulation for rocket projectile with different nose deflection angle flying under different Mach number was made by CFD software and aerodynamic parameters of each rocket projectile model was obtained, and then six degrees of freedom exterior ballistic calculation was made for rocket projectile with different nose deflection nose, typical experiment was done for verifying the results of numerical simulation.The simulation results coincide well with the experimental results and nose deflection angle can provide falling point lateral migration distance effectively, research results can provide theoretical and technical support for adaptive intelligent missile and its engineering applications.