Cook-off Characteristics of Solid Rocket Motor with Star-configuration Propellant Charge

被引：0
|
作者：
Ye Q. [1 ]
Yu Y. [1 ]
机构：
[1] School of Energy and Power Engineering, Nanjing University of Science and Technology, Nanjing
来源：
Yu, Yonggang (yygnjust801@163.com) | 1970年 / China Ordnance Industry Corporation卷 / 41期
关键词：
Ammonium perchlorate/hydroxylhydroxyl-terminated polybutadiene; Cook-off; Numerical simulation; Solid rocket motor;
D O I：
10.3969/j.issn.1000-1093.2020.10.006
中图分类号：
学科分类号：
摘要：
The thermal security of a solid rocket motor with ammonium perchlorate/hydroxyl-terminated polybutadiene (AP/HTPB) is studied. A 3D cook-off model of a rocket motor with star-configuration propellant is established. The reaction kinetic for cook-off is two-step global chemical mechanism. Numerical predictions of cook-off behavior are conducted at fast heating rates, medium heating rates and slow heating rates, respectively. The results show that the heating rate has a certain influence on the ignition temperature and delay period, and has a great impact on the ignition position, shape and size. At fast heating rate of 0.55-1.45 K/s, the ignition is closer to the right end face and the radial section area increases as the heating rate is higher. At medium heating rates of 0. 005-0. 011 K/s, the ignition zone is distributed with discontinuous point-like rings. The ignition center is located in the midline of wing groove, and the radial section area becomes larger with the increase in heating rate; at slow heating rate of 2.4-3.3 K/h, the ignition positions are symmetrically distributed on the centerline of wing groove. The ignition temperature has a quadratic function relationship with the heating rate, namely, Ti=516.659 36-1.267 8k+7.479 4k2. © 2020, Editorial Board of Acta Armamentarii. All right reserved.
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页码：1970 / 1978
页数：8
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