基于光学诊断的某新型含铝推进剂燃烧特性分析

杨云杰; 邢时越; 张少华; 余西龙; 王泽众; 王海燕

doi:10.11883/bzycj-2022-0316

基于光学诊断的某新型含铝推进剂燃烧特性分析

doi: 10.11883/bzycj-2022-0316

杨云杰^{1, 2,},
邢时越^{1, 2},
张少华^2, ,,
余西龙²,
王泽众²,
王海燕¹

1.
中国矿业大学（北京），北京 100083
2.
中国科学院力学研究所，北京 100190

基金项目: 国家自然科学基金（11672359）

详细信息

作者简介:
杨云杰（1997－　），男，硕士研究生，yyjmail88@163.com

通讯作者:
张少华（1982－　），女，博士，副研究员，shzh@imech.ac.cn

中图分类号: O383；TJ55
计量
- 文章访问数: 367
- HTML全文浏览量: 177
- PDF下载量: 53
- 被引次数: 22
出版历程
- 收稿日期: 2022-07-21
- 修回日期: 2023-02-07
- 网络出版日期: 2023-02-23
- 刊出日期: 2023-04-05

Investigation of combustion characteristics of a new aluminum-containing propellant based on optical diagnosis

YANG Yunjie^{1, 2
,},
XING Shiyue^{1, 2},
ZHANG Shaohua^{2
, ,},
YU Xilong²,
WANG Zezhong²,
WANG Haiyan¹

1.
China University of Mining and Technology (Beijing), Beijing 100083, China
2.
Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China

摘要

摘要: 为探究某新型含铝固体推进剂燃烧特性和规律，在模拟固体发动机的高压条件下，采用可调功率激光器结合高速摄影、发射光谱等光学诊断技术对该新型含铝固体推进剂开展了系统的点火及燃烧过程研究。通过对该推进剂的点火延迟、退移速率、燃烧温度以及团聚物颗粒尺寸的定量测量和分析，明确了该推进剂的点火延迟量级；证实此推进剂的退移速率严格遵循Summerfield燃速公式；判断出其最高燃烧温度高于3 300 K，且随压力增大而升高；通过对燃烧过程中发光凝聚相产物面积的量化分析得出推进剂产物中团聚物粒径尺寸受环境参数的影响规律。
- 固体推进剂 /
- 铝 /
- 激光点火 /
- 燃烧特性 /
- 光学诊断
Abstract: In order to investigate the combustion characteristics of a new aluminum-containing solid propellant, the ignition and combustion process of the propellant at elevated pressure for simulating the solid propellant rocket engine were systematically studied by using a variable power fiber-laser and optical diagnostic techniques. The near-infrared fiber laser was employed to ignite the propellant slices placed in a high-pressure optical tank which was designed and manufactured for simulating solid propellant rocket engine conditions. The successive images of the laser-ignition and combustion process were captured by a high-speed camera while the optical emission spectroscopy was recorded with fiber-based spectrometers. Therewith, the regression rate, the ignition delay, and agglomerate particle size of the propellant were determined from the quantitative measurement and analysis of the former, likewise, the combustion temperatures were deduced by the latter. Accordingly, the maximum combustion temperature, the magnitude of the ignition delay, and rules of regression rate were mastered, as well as their dependence on laser power and ambient pressure. Firstly, the analysis of emission spectra shows that the maximum combustion temperature of this propellant should be higher than 3 300 K which grows with pressure. It reveals that the fundamental mechanisms of the propellant receding rate and ignition delay are affected by the ambient pressure from the perspective of chemical reaction dynamics. Meantime, the exponential decay law of ignition delay is determined while its formation mechanism is explored, based on the real-time monitoring of the propellant burning surface with high spatial and temporal resolution. Furthermore, it is also found that the regression rate of this propellant increases rapidly at low pressure, but appears to be saturated gradually when the ambient pressure exceeds 4 MPa. Whereafter, it is confirmed that the receding rate rules strictly follow the Summerfield burning rate equation. Finally, through the quantitative analysis of the luminous area of agglomerates in the combustion process, the effects of the agglomerate particle size in the propellant product by environmental parameters are concluded.
- solid propellant /
- aluminum /
- laser ignition /
- combustion characteristics /
- optical diagnosis

HTML全文

图 1 固体推进剂激光点火燃烧特性光学研究实验系统

Figure 1. Optical experimental system for laser ignition combustion characteristics of solid propellant

下载: 全尺寸图片幻灯片

图 2 新型含铝高能推进剂的激光点火及燃烧过程

Figure 2. Laser ignition and combustion process of a new aluminum-containing high-energy propellant

下载: 全尺寸图片幻灯片

图 3 含铝固体推进剂点火燃烧模型

Figure 3. Ignition combustion model of aluminum-containing solid propellant

下载: 全尺寸图片幻灯片

图 4 新型含铝高能推进剂燃烧发射光谱

Figure 4. Combustion emission spectra of the new aluminum-containing high energy propellant

下载: 全尺寸图片幻灯片

图 5 不同压力条件下点火延迟的变化规律

Figure 5. Variation of ignition delay time with pressure

下载: 全尺寸图片幻灯片

图 6 Δt随p的变化规律

Figure 6. Variation law of Δt with p

下载: 全尺寸图片幻灯片

图 7 不同压力下退移速率的变化规律

Figure 7. Variation of regression rate under different pressures

下载: 全尺寸图片幻灯片

图 8 不同压力下AlO光谱强度曲线

Figure 8. Spectral intensity curves of AlO under different pressures

下载: 全尺寸图片幻灯片

图 9 不同压力条件下燃烧温度

Figure 9. Combustion temperature diagram under different pressure conditions

下载: 全尺寸图片幻灯片

图 10 不同压力条件下凝聚相颗粒平均面积

Figure 10. Average area of condensed phase particles under different pressure conditions

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表 1 激光点火的实验参数

Table 1. Experimental parameters of laser ignition

序号点火功率/W 点火时间/ms 环境压力/MPa

1 200 200 0.1, 1, 2, 3, 4, 5
2 400 200 0.1, 1, 2, 3, 4, 5

下载: 导出CSV

表 2 不同点火延迟时间 $t ({\rm{ms}})$ 随压力 $p ({\rm{MPa}})$ 变化规律公式

Table 2. Formula of variation of ignition delay time $t ({\rm{ms}})$ with pressure $p ({\rm{MPa}})$

点火功率/W 拟合公式 R²

200 t = 0.16 p^−0.060 0.97
400 t = 0.13 p^−0.018 0.96

下载: 导出CSV

表 3 燃速公式的参数

Table 3. Parameters of burning rate formula

激光功率/W a_s b_s R²

200 0.00458 0.42468 0.99371
400 −0.01364 0.37591 0.99777

下载: 导出CSV

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