固体推进剂非线性压强耦合响应特性分析

Analysis of Nonlinear Pressure Coupled Response

关键词:  固体推进剂  非线性  压强耦合响应  燃烧模型

Key words:  Solid propellant  Nonlinear  Pressure-coupled response function  Combustion model

摘要:

为获得多阶声模态振荡共同作用下的压强耦合响应函数特性，考虑固体火箭发动机中多阶声模态振荡的非线性燃烧不稳定特点，在线性均质推进剂准稳态分析模型(QSHOD)的基础上，建立了二阶声模态作用下的非线性压强耦合响应模型，并对模型进行了理论分析和定性的实验验证。模型分析结果表明，基频振荡幅值对压强耦合响应函数特性影响较大；随着基频振荡幅值的增大，压强耦合响应函数由线性变为非线性，响应函数从单峰变成双峰，在高频区域形成非线性响应函数峰；在基频振荡的同时，二阶模态振荡使得响应函数的非线性特性更加显著，对非线性响应函数峰值影响较大。该模型结果与典型T型燃烧器实验结果基本相同。

Abstract:

In order to obtain the characteristics of the pressure-coupled response function which was influenced by the multi-order modes acoustic frequency oscillation，the nonlinear combustion instability characteristics of the multi-order mode oscillation in the solid rocket motor were considered，and based on the Quasi-Steady，Homogenous，One-Dimensional (QSHOD) model，the second-order (2nd) mode acoustic of the nonlinear pressure-coupled response model was developed. The model was analyzed and verified by experiments. The results of model show that，the oscillation amplitude of the first-order (1st) mode frequency has a great influence on the pressure-coupled response function，and with the amplitude increase，the pressure coupled response function was changed from the linear to the nonlinear，the peak value of response function changed from single-modal to bi-modal，and the nonlinear response function peak value was formed in the high frequency region. During the 1st mode frequency oscillation，the 2nd mode frequency makes the response function more nonlinear significantly，and has a great influence on the peak value of nonlinear pressure coupled response function. The results of the model were basically the same as the experimental results of typical T-burner.