固体火箭发动机喷焰瞬态特性实验

魏天宇; 傅德彬; 刘浩天; 冯自瑞; 刘岭岳

doi:10.13224/j.cnki.jasp.20220088

固体火箭发动机喷焰瞬态特性实验

doi: 10.13224/j.cnki.jasp.20220088

魏天宇¹,
傅德彬^1,*, ,,
刘浩天^{1, 3},
冯自瑞²,
刘岭岳²

1.
北京理工大学宇航学院，北京 100081
2.
西安北方惠安化学工业有限公司，西安 710302
3.
中国工程物理研究院总体工程研究所，四川绵阳 621999

基金项目: 基础计划加强重点基础研究项目（2019-JCJQ-ZD-045-02-02 ）

详细信息

作者简介:
魏天宇（1998-），男，硕士生，主要从事发射及推进系统研究

通讯作者:
傅德彬（1978-），男，副教授、硕士生导师，博士，主要从事发射系统理论研究。E-mail：fdb007@bit.edu.cn

中图分类号: V19
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- 文章访问数: 15
- HTML浏览量: 7
- PDF量: 2
- 被引次数: 0
出版历程
- 收稿日期: 2022-02-27
- 网络出版日期: 2024-04-17

Experimental study on transient characteristics of solid rocket motor exhaust plume

WEI Tianyu¹,
FU Debin^{1,*
, ,},
LIU Haotian^{1, 3},
FENG Zirui²,
LIU Lingyue²

1.
School of Aerospace Engineering，Beijing Institute of Technology，Beijing 100081，China
2.
Xi’an North Huian Chemical Industries Company Limited，Xi’an 710302，China
3.
Institute of Systems Engineering，China Academy of Engineering Physics，Mianyang Sichuan 621999，China

摘要

摘要:
以固体火箭发动机系留实验采集图像数据为基础，采用图像均值与方差分析、喷焰典型位置亮度时间序列的快速傅里叶变换（FFT）、改进Hilbert-Huang变换（改进HHT）等方法对其瞬态特性进行分析处理。分析结果表明：在获取的频带内，喷焰整体不存在明显的主脉动频率，各个频率上均存在较小的脉动分量，且核心区的脉动幅值要小于湍流混合区，同时湍流混合区的脉动与核心区的脉动之间存在相关性，基于改进的自适应噪声完备集合经验模态分解算法（ICEEMDAN）的改进HHT变换可作为分析固体火箭发动机喷焰等非平稳信号瞬态特征变化机理的有效手段。
- 固体火箭发动机 /
- 喷焰脉动 /
- 时频特性 /
- ICEEMDAN算法 /
- HHT变换
Abstract:
Based on the image data collected by the solid rocket motor mooring experiment, the image mean and variance analysis, the fast Fourier transform (FFT) of the time series of the brightness of the typical position of the flame, and the improved Hilbert-Huang transform (improved HHT) are used to analyze the data. Transient characteristics are analyzed and processed. The analysis results show that: in the obtained frequency band, there is no obvious main pulsation frequency in the entire exhaust plume, and there are small pulsation components at each frequency, and the pulsation amplitude in the core area is smaller than that in the turbulent mixing zone. There is a correlation between the pulsations in the core region and that in the turbulent mixing zone, and the improved HHT transform based on the improved adaptive noise complete set empirical mode decomposition algorithm (ICEEMDAN) can be used as an effective means to analyze the transient characteristic change mechanism of non-stationary signals such as solid rocket engine flames.
- solid rocket motor /
- exhaust plume pulsation /
- time-frequency characteristic /
- ICEEMDAN algorithm /
- HHT transform

HTML

图 1 系留实验采集的压强和图像

Figure 1. Pressure and images acquired from tethered experiments

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图 2 图像序列均值与方差

Figure 2. Image sequence mean and variance

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图 3 采样点位置

Figure 3. Sampling point location

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图 4 灰度采样结果

Figure 4. Grayscale sampling result

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图 5 脉动采样点FFT结果

Figure 5. FFT results of pulsating sampling points

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图 6 ICEEMADAN算法示意图

Figure 6. Schematic diagram of ICEEMADAN algorithm

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图 7 湍流混合区重构信号频谱

Figure 7. Reconstructed signal spectrum in turbulent mixing region

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图 8 A点ICEEMDAN分解结果

Figure 8. ICEEMDAN decomposition result at point A

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图 9 C点ICEEMDAN分解结果

Figure 9. ICEEMDAN decomposition result at point C

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图 10 核心区典型模态Hilbert谱

Figure 10. Hilbert spectrum of typical modes in the core area

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图 11 湍流混合区典型模态Hilbert谱

Figure 11. Typical modal Hilbert spectrum in turbulent mixing region

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