固体火箭发动机羽流温度和热流密度测量

Solid rocket plume temperature and heat flux measurements

为了获得固体火箭发动机喷管外流场的温度和热流密度,同时提高测量结果的响应程度和准确性,提出了一种固体火箭发动机外流场温度和热流密度新的测量方法。该方法应用了一套相同尺寸不同材料的双热电偶测温装置和热流测量计的组合测量装置,测量了发动机喷管外高温燃烧产物的温度和热流密度。采用FLUENT软件对固体火箭发动机喷管外流场开展了数值仿真,仿真结果与该方法的实测结果近似,进一步验证了该方法的正确性。研究结果表明,固体火箭发动机点火后喷管外部会产生高温高速的羽流,并伴随着一串串明显的激波,随着飞行高度不断攀升,羽流对外充分膨胀做功,其扩张角不断增大,激波也逐渐消失,同时该测量方法也可以为火焰导流槽的结构和热防护设计提供数据支持。

In order to obtain the temperature and heat flux density of the external flow field of the solid rocket engine nozzle with high accuracy,a new method for measurement of the temperature field and heat flux was presented in this article. The experimental device,which consists of two different thermocouple thermometers with the same size and a heat flow meter,was used to measure the temperature and heat flux of the high temperature combustion products in the engine nozzle.Furthermore,simulations of the external flow field of solid rocket motor nozzle were carried out using FLUENT.A moderate discrepancy between the simulations and the experimental results validates the reliability of the proposed method.The results show that the solid rocket can generate high temperature and high velocity two-phase plume,which is accompanied by a string of obvious shock waves.As the flying height continues to rise,the plume fully expands its work and the angle of plume is increasingly larger. This method can provide data support for the structure of the flame deflector and the thermal protection design.