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本文分析了具有前喷管的火箭弹在主动段的受力情况。指出当超音速飞行时在前喷管附近的弹体表面上将产生一个局部高压区,由此可以形成一个翻转力矩,这可以用来解释在主动段超音速飞行中为什么会出现不稳定飞行的现象。
This paper analyzes the force of the rocket projectile with the front nozzle in the active section. Point out that when supersonic flight will produce a local high pressure area on the surface of the projectile in the vicinity of the front nozzle so as to form an overturning moment which can be used to explain why unstable flight occurs in the active supersonic flight phenomenon.