火箭燃气射流温度分布的实验研究

Experimental study on temperature distribution in rocket exhausted flow field

为了优化火箭发射承载设备的设计,使其避免燃气射流的热损坏。采用细丝热电偶测温的方法,实验研究了某型火箭固体发动机燃气射流的总温分布。结果表明,温度-时间历程曲线中存在若干相对稳定状态,对应于发动机的工作过程的不同阶段,得到了可能发生热损坏的温度分布区域。实验得到的温度分布与理论结构基本相符,与数值模拟存在一定差异。文中简要分析了细丝热电偶的测量误差。

Temperature distribution of solid rocket exhausted plume was studied to optimize the loading equipment design and avoid the thermal damage. Fine wire thermocouples were used to measure the total temperature distribution of the rocket engine. There are several stages in temperature-time history corresponding to the work procedure of the rocket engine. Thermal damage zone was obtained. This distribution pattern is the same as theoretical structure, but it differs with numerical simulation result in some degree. The measurement error of fine wire thermocouples is discussed briefly.