低温下三组元固体推进剂燃烧波阵面变化规律实验研究

Experiment on Change Law of Combustion Wavefront of Three-Component Solid Propellant under Low-Temperature Conditions

深入了解高能固体推进剂在低温条件下燃烧性能,获得燃烧波阵面变化规律,对评估推进剂在低温条件下的适应性能力具有重要指导意义。本文设计了燃烧波狭缝观测实验装置,采用高速摄影观测技术,对三组元HTPB固体推进剂在常温和低温条件下的燃烧过程进行了观测,获得了燃烧过程中波阵面的图像。结果表明,相比于在常温条件下,固体推进剂在低温条件下出现了燃烧波不稳定的情况。根据燃烧波图像计算出了推进剂的燃速,并与靶线法燃速测量结果进行比较。结果表明,两种方法测量的结果差异较小,推进剂在低温条件下的燃烧速度明显低于在常温条件下,常温条件的燃速在1.717~2.127mm/s,低温条件下的燃速在1.252~1.583mm/s。

An in-depth understanding of the combustion performance of the propellants in low-temperature conditions and collecting the change law of combustion wavefront can porvide a significant guidance for evaluating the adaptability of the propellants in low-temperature conditions. A slit observation device that can improve the observation quality of combustion waves was designed. The rapid phothograph method was carried out to collect the combusiton process of the three-component HTPB solid propellant in normal-temperature and low-temperature conditions and the images of the combustion waves were obtained. The results show that,compared with the normal-temperature conditions,the combusiton wavefront of the propellants is unstable in low-temperature conditions. The combusiton velocity of propellant was calculated based on the images taken by the rapid photograph method,which was compared with the results of the target line method. The results show that the difference between the results from the two methods was small,and the combustion velocity in the low-temperature conditions is significantly lower than that in normal-temperature conditions. The combusiton velocity of the propellant is between 1.717~2.127mm/s in normal-temperature conditions,and is between 1.252~1.583mm/s in the lowtemperature conditions.