大长径比固体火箭发动机工作过程中压力响应的数值研究

Numerical analysis on pressure response of SRM with large aspect ratio

为了研究大长径比固体火箭发动机工作过程中压力响应规律,以两个型面下的准稳态计算作铺垫,采用自主开发的算法对大长径比两端包覆装药发动机在燃面推移过程中的瞬态内流场展开了数值模拟,并将瞬态计算结果与准稳态结果进行了对比。结果表明,注入流体温度会对压力响应频率产生较大影响;瞬态计算不会改变监测点压力频谱分析曲线的变化趋势,但是会令压力峰值及其对应的响应频率产生数值上的差异,并且响应频率的改变是非线性的;在发动机整个工作过程模拟中,其压力响应幅值较单个型面下准稳态计算结果要低很多。

In order to study the pressure responses of the solid rocket motors with large aspect ratios during their operations, paving with quasi steady state calculation under two types of profile,a numerical simulation on the transient internal flow field during the burning surface regression processes of the large aspect ratio coated charge engine was carried out by our newly developed algorithm.The transient results have been compared with the quasi-steady-state results.The results show that the fluid temperature has a greater impact on the pressure response frequency.The transient calculation does not change the pressure spectrum analysis trend of the monitoring points,but it makes the pressure peak and its corresponding response frequency a little different,and the change of the response frequency is nonlinear.In the process of engine simulation,the pressure response amplitude is much lower than the quasi-steady state calculation results under a single profile.