激波管模拟研究火箭推进剂中铝高温高压燃烧的机理

A SIMULATION STUDY OF COMBUSTION MECHANISM OF ALUMINUM IN SOLID ROCKET PROPELLANT AT HIGH TEMPERATURES AND PRESSURES IN A SHOCK TUBE

一、引言 利用激波管反射激波后高温高压的环境（可达5000K及40大气压）研究铝在纯氧以及在N2-H2-Cl2-O2混合气中的燃烧,可以作为固体火箭推进剂添加铝粉燃烧机理的模拟研究。对不同情况下的燃烧反应,计算了平衡组分,指出了可能出现的中间产物及最终产物。用摄谱仪鉴别出铝燃烧的一些主要中间产物,并记录了AlO的时间历史。

The study of aluminum combustion in pure oxigen and mixture (N2-H2-C12-O2) at high temperatures and pressures provides a simulation of combustion mechanism study of aluminum in solid rocket propellant. Computations were performed for predicting possible intermediate species and products. Emission spectra of important intermediate species were identified by using a spectrometer. Time histories of the A10 emission, band show the continuum radiation of A12O2, which indicates that A10 is a precursor to A12O2 in the reaction scheme. The solid and liquid products were observed and analyzed iby electron diffraction, X ray diffraction, transmission and scanning eletroa microscopes. The gaseous products were detected by using infrared speetrometry. These measurements are in good agreement with the computations and provide useful chemical kinetic data.