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××火箭的研制经历了二十余年的漫长历程,射击密集度曾长期不过关。我们通过电子数字计算机模拟发射,重现了1981年6～7月发射试验,且确定了各种情况下的特征系数,为分析计算××火箭的方向密集度提供了方便。 本文认定影响××火箭密集度的决定性因素是起始扰动,而影响起始扰动的主要因素是燃气流特别是旋转发动机的燃气流作用力。为了提高××火箭的密集度,重申了在定向器上铺钢板以减小燃气流作用力的意见;提出了降低现有炮口转速(例如折半)和推迟旋转发动机点火的建议,对此作了定量论证。 本文还在一般意义上探讨了弹体自转对推力偏心临界段的影响问题,指出当自转速度较高时,推力偏心临界段长度趋近于半个弹道波长,即趋于与起始扰动临界段长度相等。
The development of the XX rocket has experienced a long course of more than 20 years and the shooting intensity has long been a barrier. We simulated the launching by electronic digital computer and reproduced the launching test from June to July 1981, and determined the characteristic coefficients under various conditions, which provided convenience for the analysis and calculation of the directional density of × rocket. This paper finds that the decisive factor that affects the rocket intensity of XX is the initial disturbance, and the main factor that affects the initial disturbance is the gas flow force of the gas flow, especially the rotating engine. In order to increase the density of the XX rocket, reiteration was made of the steel plate on the deflector to reduce the force of the gas stream; proposals were made to reduce the existing (eg, half) muzzle speed and postpone the ignition of the rotating engine Quantitative argument. The paper also discusses the influence of projectile rotation on the thrust critical section in a general sense. It is pointed out that when the rotation speed is high, the length of the thrust eccentric section approaches to half a ballistic wavelength, that is to say, Equal length.