| 叶青,余永刚.圆孔装药固体火箭发动机的慢速烤燃特性研究[J].装备环境工程,2022,19(3):26-31. YE Qing,YU Yong-gang.Slow Cook-Off Characteristics of Solid Rocket Motor with Round-hole Charge[J].Equipment Environmental Engineering,2022,19(3):26-31. |
| 圆孔装药固体火箭发动机的慢速烤燃特性研究 |
| Slow Cook-Off Characteristics of Solid Rocket Motor with Round-hole Charge |
| 投稿时间：2021-12-24 修订日期：2022-01-24 |
| DOI：10.7643/issn.1672-9242.2022.03.004 |
| 中文关键词: 热安全性 烤燃 推进剂 烤燃数值模拟 |
| 英文关键词:thermal safety cook-off, propellant numerical simulation |
| 基金项目: |
|
|
|
|
| 摘要点击次数: |
| 全文下载次数: |
| 中文摘要: |
| 目的 研究圆孔装药固体火箭发动机的慢速烤燃特性。方法 针对装填高能推进剂的固体火箭发动机，建立了二维瞬态慢速烤燃模型。其中AP/HTPB推进剂的化学动力学模型为两步总包反应模型。在升温速率分别为3.6、7.2、10.8 K/h的工况下，进行固体火箭发动机的烤燃数值模拟，并具体分析慢速烤燃工况下固体火箭发动机的传热特性和烤燃着火特性。结果 3种慢速烤燃工况(3.6、7.2、10.8 K/h)对应的着火响应时间分别为30.96、22.19、18.70 h，着火温度分别为518.84、518.85、519.59 K。随着慢速升温速率的提高，烤燃着火中心向推进剂外壁面和右侧端面移动，着火区域由椭圆形变为半椭圆形。结论 在圆孔装药的固体火箭发动机的慢速烤燃过程中，前期主导推进剂温度变化的是外界热传导，后期则是由推进剂的自热反应主导。 |
| 英文摘要: |
| 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. |
| 查看全文 查看/发表评论 下载PDF阅读器 |
| 关闭 |
|
|
|
