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

doi:10.3969/j.issn.1000-1093.2020.10.006

Abstract

Abstract: 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, T_i= 516.659 36- 1.267 8k+7.479 4k².

Key words: solidrocketmotor, cook-off, numericalsimulation, ammoniumperchlorate/hydroxylhydroxyl-terminatedpolybutadiene

CLC Number:

V435⁺.14

YE Qing， YU Yonggang. Cook-off Characteristics of Solid Rocket Motor with Star-configuration Propellant Charge[J]. Acta Armamentarii, 2020, 41(10): 1970-1978.

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