固液火箭发动机中燃料热解速率的测量与分析

Regression rate measurement and analysis for solid fuel in hybrid rocket motor

关键词:  热解  退移速率  超声波  测量  实验

Key words:  Pyrolysis  Regression rate  Ultrasonic wave  Measurement  Experiment

摘要:

固液火箭发动机中,内弹道的计算、流场与性能分析等都需要确定燃料表面的退移速度,常规的热重分析、差热分析因升温速率太慢,与发动机环境的高升温速率差别很大,得到的热解速率误差大。采用了热板实验装置测量高升温速率环境下的固体燃料退移速率。采用高速摄影和超声波传感器进行动态测量,对比了摄影测量和超声波测量的结果,得到了超声波测量得到了热解过程中的退移速率与低密度聚乙烯表面温度的关系。

Abstract:

In hybrid rocket motor,the regression rate of solid fuel is the most important parameter.The regression rate will be used in inner ballistic calculation,flowfield simulation and rocket motor performance analysis.Generally,the parameters in regression rate equation is measured by pyrolysis device,such as DTG,but the heat environment is different from that in hybrid and this may result in large error.A heat plane device was built to simulate the environment on fuel surface in bybrid rocket motor.High speed video and ultrasonic device were used to measure the regression rate of solid fuel and their results were compared.The relationship between regression rate and surface temperature of the LDPE was obtained.