考虑自然对流的某固体火箭发动机慢速烤燃特性数值分析

叶青; 余永刚

doi:10.11883/bzycj-2018-0163

考虑自然对流的某固体火箭发动机慢速烤燃特性数值分析

doi: 10.11883/bzycj-2018-0163

叶青,
余永刚^,

南京理工大学能源与动力工程学院，江苏南京 210094

详细信息

作者简介:
叶　青（1993－　），女，博士研究生，yqnjust@163.comt

通讯作者:
余永刚（1963－　），男，博士，教授，yygnjust801@163.com

中图分类号: O389; TJ7
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- 被引次数: 0
出版历程
- 收稿日期: 2018-05-14
- 修回日期: 2018-07-29
- 网络出版日期: 2019-05-25
- 刊出日期: 2019-06-01

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

YE Qing,
YU Yonggang^,

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

摘要

摘要: 针对某高氯酸铵/端羟基聚丁二烯(AP/HTPB)推进剂固体火箭发动机，采用两步总包反应描述AP/HTPB的烤燃过程，建立了考虑发动机空腔自然对流的二维轴对称烤燃模型，对加热速率分别为3.6、7.2和10.8 K/h时火箭发动机的慢速烤燃行为进行了数值预测，研究了该火箭发动机的热安全性问题。结果表明，固体火箭发动机空腔内的自然对流对AP/HTPB推进剂的着火温度、着火延迟期和着火位置有一定影响，在热安全性精确分析中不可忽略。3种加热速率下，AP/HTPB推进剂的最初着火位置均出现在药柱肩部的环形区域内，3种加热速率对应的着火延迟期、着火温度及着火时壳体温度分别为30.71、20.06、18.68 h，526.52、528.10、530.64 K，和479.56、496.82、508.77 K。随着加热速率的增大，烤燃响应区域向推进剂与绝热层交界处移动，着火位置的二维截面由椭圆形变为半椭圆形。
- 慢速烤燃 /
- 固体火箭发动机 /
- AP/HTPB /
- 加热速率
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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图 1 固体火箭发动机结构简图

Figure 1. Schematic drawing of solid rocket motor

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图 2 实验装置及试件结构示意图

Figure 2. Sketch map of experimental device and specimen structure

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图 3 实验装置着火时刻t=1350.5 min温度云图

Figure 3. Temperature distribution at the ignition time of the test device (t=1 350.5 min)

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图 4 推进剂中心温度随对烤燃装置加热时间的变化

Figure 4. The temperature in the center of the propellant varying with the heating time of the cook-off device

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图 5 固体火箭发动机尺寸及监测点位置

Figure 5. Sizes of the solid rocket motor and locations of monitoring points

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图 6 不同网格下点C处组分X的质量分数随时间变化的曲线

Figure 6. Variation of mass fraction of component X at point C in different grids with time

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图 7 不考虑自然对流不同时刻温度云图

Figure 7. Temperature distribution at different times without natural convection

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图 8 考虑自然对流不同时刻温度云图

Figure 8. Temperature distribution at different times with natural convection

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图 9 不同监测点的温度和监测点C处组分的质量分数的变化曲线

Figure 9. Temperature curves of different monitoring points and mass fraction curves of components at point C

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图 10 在7.2 K/h的加热速率下，着火时刻(t=79 409.5 s)的温度云图

Figure 10. Temperature distribution of propellant at ignition time (t=79 409.5 s) under the heating rate of 7.2 K/h

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图 11 在10.8 K/h的加热速率下，着火时刻(t=67 257.5 s)的温度云图

Figure 11. Temperature distribution of propellant at ignition time (t=67 257.5 s) under the heating rate of 10.8 K/h

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图 12 着火延迟期随升温速率的变化

Figure 12. Ignition delay vaying with heating rate

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表 1 AP/HTPB推进剂化学反应动力学参数^[16]

Table 1. Chemical reaction kinetic parameters of AP/HTPB propellant^[16]

反应步	A/s⁻¹	E/(kJ·mol⁻¹)	Q/(kJ·kg⁻¹)
1	800	137.18	−297
2	1 100	178.45	9 643.2

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表 2 材料物性参数

Table 2. Parameters of materials

材料	ρ/(kg·m⁻³)	c_p/(J·kg⁻¹·K⁻¹)	λ/(W·m⁻¹·K⁻¹)
壳体	8 030	502.48	16.27
绝热层	950	2 860	0.276
环氧树脂挡板	1 800	1 200	0.15
AP/HTPB推进剂	1 826	1 255	0.389

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表 3 不同加热速率下的着火特征参数

Table 3. Ignition characteristic parameters at different heating rates

加热速率/(K·h⁻¹)	着火延迟期/h	着火温度/K	壳体温度/K	着火位置	着火中心位置
3.6	30.71	526.52	479.56	(868～880 mm，143～150 mm)	(874 mm，146 mm)
7.2	22.06	528.10	496.82	(875～887 mm，145～150 mm)	(882 mm，148 mm)
10.8	18.68	530.64	508.77	(877～890 mm，146～150 mm)	(884 mm，148.5 mm)

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