前喷管燃气流对火箭飞行稳定性的影响

ON THE EFFECTS OF JETS FROM THE FORELOCATED NOZZLES ON THE STABILITY OF A ROCKET

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。

For a rocket provided with fore-located nozzles the system of forces acting on it during the burning stage is analyzed. It is demonstrated that, during supersonic flight there exists a localized area of high pressure on the body surface of the rocket near the fore-located nozzles, forming an overturning moment. This explains the probability of occurance of instability of the rocket in supersonic flight during the burning stage.