基于数据同化的飞机尾流行为预测

沈淳; 李健兵; 高航; 陈柏纬; 韩启光; 王雪松

doi:10.12000/JR21007

基于数据同化的飞机尾流行为预测

DOI: 10.12000/JR21007

1.
国防科技大学电子科学学院长沙 410073
2.
香港天文台香港 999077

基金项目: 国家自然科学基金(61490649, 61771479, 61625108)，湖南省杰出青年基金(2018JJ1030)

详细信息

作者简介:
沈　淳(1985–)，男，福建漳州人，博士生，工程师，研究方向为空间信息获取与处理

李健兵(1979–)，男，湖南邵东人，博士，国防科技大学电子科学学院教授，主要研究方向为新体制雷达、雷达信号处理

王雪松(1972–)，男，内蒙古人，博士，国防科技大学电子科学学院教授，主要研究方向为极化信息处理、新体制雷达技术、电子对抗

通讯作者:
李健兵 jianbingli@nudt.edu.cn

责任主编：夏海云 Corresponding Editor: XIA Haiyun
中图分类号: TN955⁺.1
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出版历程
- 收稿日期: 2021-01-22
- 修回日期: 2021-03-16
- 网络出版日期: 2021-08-28

Aircraft Wake Vortex Behavior Prediction Based on Data Assimilation

1.
College of Electronic Science and Technology, National University of Defense Technology, Changsha 410073, China
2.
Hong Kong Observatory, Hong Kong 999077, China

Funds: The National Natural Science Foundation of China (61490649, 61771479, 61625108), Hunan Natural Science Foundation for Distinguished Young Scholars (2018JJ1030)

More Information

Corresponding author: LI Jianbing, jianbingli@nudt.edu.cn

摘要

摘要: 飞机尾流是飞机飞行时在其后方产生的一对反向旋转的强烈湍流，对后续飞机飞行以及机场安全起降影响极大，其演化趋势的预测已成为空中交通安全管制的瓶颈，亟需发展基于实时探测数据的飞机尾流行为预测技术。在雷达探测反演得到的尾流涡心位置和速度环量等特征参数基础上，开展飞机尾流行为预测分析，能够预知飞机尾流危害区域，为机场安全起降动态间隔标准制定提供技术支撑。该文结合风场线性切变和最小二乘拟合方法构建了参数化尾流行为预测模型，解决了经典尾流预测模型气象环境参数未随时间演化实时调整的问题。该文根据复杂风场非线性演化特点，设计了基于无迹卡尔曼滤波的数据同化模型，利用雷达探测数据对尾流行为预测进行实时修正。数值仿真验证和实测数据验证结果表明，基于数据同化的飞机尾流行为预测方法能够根据实时探测数据对尾流行为预测轨迹进行修正，得到更加贴近实测的飞机尾流行为预测轨迹。
- 数据同化 /
- 飞机尾流 /
- 行为预测 /
- 激光雷达探测
Abstract: Aircraft wake are a couple of counter-rotating vortices generated by a flying aircraft, which can pose a serious hazard to follower aircraft. The behavior prediction of it is a key issue for air traffic safety management. To this end, we propose a prediction method based on data assimilation, which can be used to predict the evolution and hazard area of aircraft wake vortex from the vortex-core’s positions and circulation. To construct our wake vortex prediction model, we use linear shear and least square estimation. In addition, we use a data assimilation model based on the unscented Kalman filter to instantly correct the predicted trajectories. Our experimental results show that the proposed method performs well and runs steadily, thus, providing an effective tool for aircraft wake vortex prediction and support for the establishment of dynamic wake separation in air traffic management.
- Data assimilation /
- Aircraft wake vortex /
- Behavior prediction /
- Lidar detection

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图 1 飞机尾流形成示意图

Figure 1. Illustration of aircraft wake vortex

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图 2 激光雷达探测飞机尾流场景设置

Figure 2. Geometry configuration for Lidar detection of wake vortex

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图 3 飞机尾流多普勒速度RHI回波分布图

Figure 3. Doppler velocity distribution of wake vortex in an RHI

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图 4 飞机尾流行为预测流程图

Figure 4. Wake vortex behavior prediction flow chart

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图 5 估计背景风场的非尾流区域

Figure 5. Regions free of wake vortex that was used to estimate the background wind

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图 6 切向速度与多普勒速度的几何关系

Figure 6. Relationship between the tangential velocity and Doppler velocity

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图 7 数据融合方法流程

Figure 7. Flowchart of data fusion method

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图 8 飞机尾流行为预测方法对比(水平方向轨迹)

Figure 8. Comparison between different wake vortex behavior prediction (Horizontal trajectories)

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图 9 飞机尾流行为预测方法对比(垂直方向轨迹)

Figure 9. Comparison between different wake vortex behavior prediction (Vertical trajectories)

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图 10 飞机尾流行为预测方法对比(速度环量)

Figure 10. Comparison between different wake vortex behavior prediction (Circulation)

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图 11 香港机场北跑道激光雷达探测场景设置2014

Figure 11. Geometry setup of the observation in north runway of Hong Kong international airport, 2014

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图 12 飞机尾流行为预测方法对比

Figure 12. Comparison between different wake vortex behavior prediction

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图 13 香港机场南跑道激光雷达探测场景设置2018

Figure 13. Geometry setup of the observation in south runway of Hong Kong international airport, 2018

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图 14 飞机尾流行为预测方法对比

Figure 14. Comparison between different wake vortex behavior prediction

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表 1 激光雷达探测参数设置

Table 1. Detection parameters of the Lidar

主要参数	量值
雷达波长	1.55 μm
脉冲宽度	170 ns
时间窗长度	120 ns
距离门宽度	21 m
采样率	50 MHz
脉冲积累数	1500
信号噪声比	–5 dB
扫描速度	2°/s
扫描范围	0～15°

下载: 导出CSV

表 2 飞机尾流预测位置相对误差

Table 2. Relative error of predict trajectories

主要参数			DS method (%)		DA method (%)
横向风 $V_{\rm{c}}^0$ (${\rm{m/s}}$)	切变率$\beta $	纵向风 $V_{\rm{c}}^{\rm{y}}$ (${\rm{m/s}}$)	${E_{r1}}$	${E_{r2}}$	${E_{r1}}$	${E_{r2}}$
–7	0.05	–0.3	17.74	19.63	1.12	1.35
–10	0.05	–0.3	26.83	28.52	2.64	2.41
–5	0.01	–0.3	3.42	3.14	1.98	1.76
–5	0.10	–0.3	4.16	4.71	2.86	2.17
–5	0.05	-0.5	3.59	3.21	1.23	1.01
–5	0.05	–0.8	6.87	6.52	1.36	1.71

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表 3 飞机尾流速度环量相对误差

Table 3. Relative error of wake vortex circulation

主要参数 EDR (${{\rm{m}}^2}/{{\rm{s}}^3}$)	DS method (%)		DA method (%)
主要参数 EDR (${{\rm{m}}^2}/{{\rm{s}}^3}$)	${E_{r1}}$	${E_{r2}}$	${E_{r1}}$	${E_{r2}}$
0.01	3.24	3.58	1.12	1.31
0.03	3.26	3.75	1.25	1.02
0.08	3.04	2.95	1.17	1.16
0.10	3.41	3.25	1.08	1.29

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表 4 香港机场激光雷达探测参数设置

Table 4. Detection parameters of the Lidar in Hong Kong field campaigns

主要参数	量值
雷达波长(μm)	1.54
距离门宽度(m)	25
脉冲宽度(ns)	200
脉冲重复频率(kHz)	20
探测距离(m)	50～6000

下载: 导出CSV

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