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1、前言推进剂的燃烧速度与比冲都是火箭发动机设计方面极为重要的参数。特别是,在固体推进剂的情况下,对于中断燃烧及重新点火等控制燃烧是很难的,因而,在药柱设计时需要推力——燃烧时间的程序。对于处于该条件下的固体推进剂,燃烧速度起着十分重要的作用,要求有高的燃烧速度或者低的燃烧速度的推进剂。即,随着燃烧速度范围的扩大,则推进剂程序的设计变得容易了。不过,对于燃烧速度来说,在技术上有个上限和下限。在目前,通过改变药柱的几何形状,即,通过改变燃烧的表面积,以满足所要求的推力——燃烧时间特性。
1, Foreword Propellant burning rate and specific impulse rocket engine design are extremely important parameters. In particular, in the case of a solid propellant, it is difficult to control the combustion for interrupting and re-igniting, etc. Therefore, a program of thrust-combustion time is required at the time of design of the grain. For solid propellants under these conditions, the rate of combustion plays a very important role, requiring propellants with a high rate of combustion or a low rate of combustion. That is, as the combustion speed range is expanded, the design of the propellant program becomes easy. However, there is a technically upper and lower limit to the rate of combustion. At present, by changing the geometry of the pellets, ie by changing the surface area of the combustion, the required thrust-burning time characteristics are fulfilled.