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对于固体火箭发动机羽焰温度的测量是困难的,了解其温度分布对于研究发动机内燃烧流场的特性有重要价值。考虑到固体火箭发动机羽焰高温、高压和高速燃烧流场的测试要求,使用哈尔滨工业大学研制的6目标8波长高温计进行了地面搭载试验,成功地实现了对固体火箭发动机羽焰温度的测量,并提出了多光谱测温法的新数据处理方法,即基于BP神经网络预估计固体火箭发动机羽焰的发射率与波长之间函数关系,再由逐步回归法实现真温的自动识别。实验结果表明,其真温计算值与火箭发动机设计者提供的理论值之差在±100K以内,说明多光谱法是一种测量固体火箭发动机羽焰温度的可行方法。
It is difficult to measure the plume temperature of a solid rocket engine. It is of great value to understand its temperature distribution for studying the characteristics of the combustion flow field in the engine. Taking into account the test requirements of high temperature, high pressure and high velocity combustion plume of solid rocket engine plume, ground-mounted test was carried out using a 6-target 8-wavelength pyrometer developed by Harbin Institute of Technology, successfully measuring the plume temperature of a solid rocket motor , And proposed a new data processing method of multi-spectral temperature measurement method, that is, based on BP neural network to predict the solid rocket engine plume emissivity and wavelength as a function of wavelength, and then step by step regression method to achieve real temperature automatic identification. The experimental results show that the difference between the calculated value of true temperature and the theoretical value provided by the rocket engine designer is within ± 100K, indicating that multi-spectral method is a feasible method to measure the plume temperature of solid rocket motors.