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目前机动弹头大都靠非对称气动力作机动飞行。因此,它的气动力问题比再入弹头复杂、难度大,精度高。 本文提供了带控制翼的机动弹头的数值方法和近似方法的结果,两者较为一致。 利用计算机对这类带控制翼的机动弹头进行了优化设计计算。并且获得了优化值,其结果是令人满意的。
Most current mobile warheads rely on asymmetric aerodynamic maneuver. Therefore, its aerodynamic problems than reentry warhead complex, difficult, high precision. In this paper, the numerical and approximate methods of the projectile-based maneuverable warhead are provided, which are consistent with each other. The computer is used to optimize the design and calculation of such mobile warheads with control wings. And obtained the optimized value, the result is satisfactory.