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由于人们对研制无喷管和高性能固体火箭发动机的兴趣越来越大,所以在确定装药设计程序时,透彻了解固体推进剂在高速横向流下的侵蚀燃烧特性是十分重要的。本研究中用一个基于紊流作用附面层分析,并经实验数据验证过的理论模型来进行范围广泛的各种马赫数、压力、表面粗糙度、压力梯度、通道直径以及推进剂初始温度等条件下的参数研究。采用非线性回归分析法,得出了一个以上述所引用参数表示的侵蚀燃烧速度关系式。并用两种发动机药型上应用的结果证实了这个关系式对装药设计的适用性。
Due to growing interest in developing nozzleless and high performance solid rocket motors, it is important to understand thoroughly the erosive combustion behavior of solid propellants at high speed and lateral flow in the design of the charge. In this study, a wide range of Mach number, pressure, surface roughness, pressure gradient, channel diameter, initial propellant temperature, etc. were developed using a turbulent overburden analysis and a theoretical model validated by experimental data Study of parameters under condition. Using non-linear regression analysis, a relation of erosion rate of combustion, expressed as the above cited parameters, is derived. And the results of the two kinds of engine drug application confirmed the applicability of this relation to charge design.