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| Slow Cook-Off Characteristics of Solid Rocket Motor with Round-hole Charge |
| Received:December 24, 2021 Revised:January 24, 2022 |
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| DOI：10.7643/issn.1672-9242.2022.03.004 |
| KeyWord:thermal safety cook-off, propellant numerical simulation |
| Author | Institution |
| YE Qing |
School of Energy and Power Engineering, Nanjing University of Science and Technology, Nanjing , China |
| YU Yong-gang |
School of Energy and Power Engineering, Nanjing University of Science and Technology, Nanjing , China |
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| Abstract: |
| In order to research on slow Cook-off Characteristics of Solid Rocket Motor with Round-hole Charge. The thermal safety of solid rocket motor has attracted more and more attention with the high energy of propellant. In this paper, a two-dimensional transient slow cook-off model is established for solid rocket motor filled with high energy propellant. The chemical kinetic model of AP/HTPB propellant is a two-step overall reaction model. Under the working conditions of heating rate of 3.6, 7.2 and 10.8 K/h respectively, the numerical simulation of solid rocket motor is carried out, and the heat transfer characteristics and ignition characteristics of solid rocket motor under slow cook-off working conditions are analyzed in detail. The ignition response times corresponding to the three slow cook-off conditions are 30.96, 22.19 and 18.70 h respectively, and the ignition temperatures are 518.84, 518.85 and 519.59 K respectively. With the increase of the slow heating rate, the ignition center of cook-off moves to the outer wall and the right end face of the propellant, and the ignition region changes from an ellipse to a semi-ellipse. The numerical results of cook-off show that in the slow cook-off process of solid rocket motor with round-hole charge, the external heat conduction dominates the temperature change of propellant in the early stage, and the self-heating reaction of propellant dominates in the later stage. |
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