Numerical analysis of slow cook-off characteristics for solid rocket motor with natural convection

YE Qing; YU Yonggang

doi:10.11883/bzycj-2018-0163

Volume 39 Issue 6

Jun. 2019

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YE Qing, YU Yonggang. Numerical analysis of slow cook-off characteristics for solid rocket motor with natural convection[J]. Explosion And Shock Waves, 2019, 39(6): 062101. doi: 10.11883/bzycj-2018-0163

Citation:

YE Qing, YU Yonggang. Numerical analysis of slow cook-off characteristics for solid rocket motor with natural convection[J]. Explosion And Shock Waves, 2019, 39(6): 062101. doi: 10.11883/bzycj-2018-0163

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Numerical analysis of slow cook-off characteristics for solid rocket motor with natural convection

doi: 10.11883/bzycj-2018-0163

YE Qing,
YU Yonggang^,

School of Energy and Power Engineering, Nanjing University of Science and Technology, Nanjing 210094, Jiangsu, China

Received Date: 2018-05-14
Rev Recd Date: 2018-07-29

Available Online: 2019-05-25

Publish Date: 2019-06-01

Abstract

Abstract

A two-dimensional axisymmetric model about slow cook-off of solid rocket motor was established, where the process of slow cook-off for ammonium perchlorate/hydroxyl-terminated polybutadiene (AP/HTPB) propellant described by a two-step global chemical reaction kinetics, and natural convection of motor cavity was considered. The purpose of this paper is to study the thermal safety problems of solid rocket motor with ammonium perchlorate/hydroxyl-terminated polybutadiene (AP/HTPB) propellant. Numerical predictions of slow cook-off behavior for a motor were conducted at the heating rate s of 3.6, 7.2 and 10.8 K/h, respectively. The results show that the natural convection in the cavity of the solid rocket motor has a certain influence on the ignition temperature, ignition delay of the AP/HTPB propellant, and cannot be ignored in the accurate analysis of thermal safety. At the three heating rates, the initial ignition position of AP/HTPB propellants appeared in the annular region on the shoulder of the propellant. The ignition delay period, the ignition temperature and the temperature of the shell at the three heating rates were 30.71, 20.06, 18.68 h; 526.52, 528.10, 530.64 K; and 479.56, 496.82, 508.77 K; respectively. With the increase of heating rate, the response area of the cook-off is shifted to the junction between the propellant and the insulation, and the two-dimensional section of the ignition position is changed from ellipse to semi-ellipse.
- slow cook-off,
- solid rocket motor,
- AP/HTPB,
- heating rate

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References(17)

References

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