高速旋转固体发动机低燃速推进剂燃速性能的研究  

AN INVESTIGATION ON THE BURNING RATE PERFORMANCE OF LOW BURNING RATE SOLID PROPELLANT APPLIED TO SPIN ROCKET MOTOR

作　　者：汪志清[1] 

机构地区：[1]航空航天部806所

出　　处：《推进技术》1991年第5期45-50,共6页Journal of Propulsion Technology

摘　　要：本文研究了推进剂的降速剂种类及其含量、氧化剂粒度和粒度分布,以及发动机的旋转对低燃速固体推进剂燃速性能的影响.并研究了采用新型药条包覆剂提高推进剂燃速测试精度的方法.在此基础上,研制出稳定的低燃速复合固体推进剂.它具有高的燃速精度,较低的压强指数.文章还指出了发动机的高速旋转(2400r/min)对推进剂的燃速性能和比冲的影响.In this paper,the impact of various burning rate moderators, oxidizer particle size and its distribution, and the spin of the rocket motor on the performance of low burning rate propellant is discussed, A new type of coating agent for improving the measurement accuracy of burning rate is also presented. A steady low burning rate composite solid propellant has been developed,which has low pressure exponent and high accuracy of burning rate. The results show that the high spih speed of rocket motor (2400r/min) have an effect on the burning rate and the specific impulse of solid propellant.

关 键 词：低燃速推进剂 合成推进剂 燃烧速度 火箭发动机 

分 类 号：V512.3[航空宇航科学与技术—航空宇航推进理论与工程]