Measurement of High-pressure Dynamic Burning Rate and Pressure Exponent of Solid Propellants by Impulse Method

被引：0

作者：

Wang Y.-H. ^{[1
]}

Liu C.-Y. ^{[1
,2
]}

Xue Z.-R. ^{[1
]}

Zhang H. ^{[1
]}

Zhu Q.-L. ^{[1
]}

机构：

[1] Science and Technology on Combustion, Internal Flow and Thermo-structure Laboratory, Northwestern Polytechnical University, Xi'an

[2] Xi'an Changfeng Institute of Mechanism and Electricity, Xi'an

来源：

Huozhayao Xuebao/Chinese Journal of Explosives and Propellants | 2019年 / 42卷 / 03期

关键词：

Booster method; High-pressure danamic burning rate; Impulse method; Physical chemistry; Rocket motor; Solid propellant;

D O I：

10.14077/j.issn.1007-7812.2019.03.012

中图分类号：

学科分类号：

摘要：

In order to solve the deficiency of the testing method of burning rate of solid propellant under high pressures, a high-pressure dynamic burning rate test method for solid propellant, impulse burning rate test method, was proposed. In this method, the incremental F-t curve and p-t curve during the motor working process were obtained by increasing surface combustion of solid propellant in the rocket motor. According to the relationship between the impulse generated per unit time and the mass of burned propellant (impulse method), the burning rate values under the corresponding pressure at different time during the whole working process of the motor were calculated and obtained. The burning rate of the conventional propellant SQ-2 in booster was experimentally compared with that measured by impulse method, and the impulse burning rate test method was verified by testing the burning rate of a medium-energy propellant. The results show that the burning rates of propellant SQ-2 measured by impulse method are 12.134mm/s at 10.62MPa, 11.369mm/s at 7.87MPa and 11.258mm/s at 7.63MPa, while those measured by booster method are 12.056, 11.104 and 10.91mm/s under the corresponding pressure. The results obtained by impulse method are slightly higher, with a maximum error of about 3%. The burning rate characteristics of a medium-energy composite propellant measured by impulse method are r=6.46p0.443(p=8-23MPa), r=3.49p0.635(p=23-47MPa). The measurement of burning rate at any pressure point of the solid propellant is realized by a single pressurization experiment. © 2019, Editorial Board of Journal of Explosives & Propellants. All right reserved.

引用

页码：278 / 283and288

共 7 条

[1] Gupta G., Jawale L., Mehilal, Et al., Various methods for the determination of the burning rates of solid propellants-an overview, Central European Journal of Energetic Materials, 12, 3, pp. 593-620, (2015)
[2] Pei Q., Zhao F.-Q., Luo Y., Et al., Research progress of burning rate measurement technology for solid propellants, Chinese Journal of Explosives & Propellants (Huozhayao Xuebao), 38, 3, pp. 9-14, (2015)
[3] Zhang X.-P., Li B.-X., Wang Y., Et al., Study on high pressure combustion characteristics of NEPE propellant, Journal of Propulsion Technology, 29, 4, pp. 508-512, (2008)
[4] Zhao N.A., Cao Y., Dai W., Et al., Combustion experiment of the high bore pressure propellant under high pressure and optimization model of burning rate, 29th International Symposium on Ballistics, 1, 2, pp. 661-675, (2016)
[5] Hu S.-Q., Li B.-X., Li F.-C., Et al., Closed burning method for measuring burning rate of propellant under high pressure, Chinese Journal of Energetic Material, 13, 3, pp. 189-191, (2005)
[6] Wen G., Du P., Liao X., Principles and methods of measuring the actual burning rate of propellants by closed bomb, Chinese Journal of Explosives & Propellants (Huozhayao Xuebao), 34, 3, pp. 57-60, (2011)
[7] Liu K.-X., Zhao L., Li B., Test method for dynamic burning rate of closed self pressurized solid propellants, Chinese Journal of Explosives & Propellants (Huozhayao Xuebao), 37, 1, pp. 78-81, (2014)

← 1 →