摘要
为了研究AF-315液体单元推进剂在高压下的燃烧特性,设计了一种测量液体推进剂高压线燃速的实验装置,采用离子探针测速技术测定了液体推进剂燃烧时火焰面的传播速度.利用此实验装置,测量了AF-315在29.4～55.0MPa压力范围内的表观线燃速.实验结果表明,燃速与压力之间满足指数关系,但燃速系数及燃速指数在29.4～43.1MPa和43.1～55.0MPa内具有不同的值.通过最小二乘法线性拟合,分别得到了两压力区间内AF-315线燃速与压力的经验公式.
To study the high-pressure combustion characteristics of AF-315 liquid monopropellant, a device for measuring linear burning rate of liquid propellants at high pressure was designed. By use of the velocity measurement technology of ion probe, the spread velocity of combustion flame surface was measured. Based on the experimental device,the apparent linear burning-rate of AF- 315 was measured quantitatively at 29. 4 - 55. 0 MPa. The results show that burning rate is exponential to pressure, but the burning-rate coefficients and exponents have respective values at 29.4-43.1 MPa and 43.1-55.0 MPa. By the method of least squares,the empirical formulas for linear burning rate were fitted in the two pressure ranges,respectively.
出处
《弹道学报》
EI
CSCD
北大核心
2012年第2期79-82,共4页
Journal of Ballistics
基金
国家自然科学基金项目(50776048)
关键词
液体单元推进剂
测量装置
燃速
高压
liquid monopropellant
measurement device
burning rate
high pressure
