分离式飞机应急数据记录跟踪系统设计与试验

张延泰; 孙建红; 侯斌; 王一波

doi:10.13700/j.bh.1001-5965.2020.0624

分离式飞机应急数据记录跟踪系统设计与试验

doi: 10.13700/j.bh.1001-5965.2020.0624

张延泰¹,
孙建红^{1, 2, ,},
侯斌¹,
王一波³

1.
南京航空航天大学飞行器环境控制与生命保障工业和信息化部重点实验室, 南京 210016
2.
南京航空航天大学民航学院, 南京 211106
3.
中国航天科技集团公司上海航天控制技术研究所, 上海 201109

基金项目: 江苏高校优势学科建设工程

详细信息

通讯作者:
孙建红, E-mail: jhsun@nuaa.edu.cn

中图分类号: V244.2
计量
- 文章访问数: 519
- HTML全文浏览量: 106
- PDF下载量: 34
- 被引次数: 0
出版历程
- 收稿日期: 2020-11-09
- 录用日期: 2021-01-08
- 网络出版日期: 2021-11-20

Design and test of the ejection emergency flight data recording and tracking system

1.
Key Laboratory of Aircraft Environment Control, Life Support and Industry and Information Technology, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
College of Civilaviation, Nanjing University of Aeronautics and Astronautics, Nanjing 211106, China
3.
Shanghai Aerospace Control Technology Institute, China Aerospace Science and Technology Corporation, Shanghai 201109, China

Funds: Priority Academic Program Development of Jiangsu Higher Education Institutions

More Information

Corresponding author: SUN Jianhong, E-mail: jhsun@nuaa.edu.cn

摘要

摘要:
分离式飞机应急数据记录跟踪系统具备智能弹射与分离、拖曳式跟踪拍摄、缓降与应急漂浮和数据传输等功能，针对弹射和缓降等过程进行了系统设计和无人机试验验证。同时，针对伞-囊组合体的特点，分析了气囊尾流区中伞衣阻力系数的变化规律。结果表明：气囊半径和伞衣名义直径是影响伞衣阻力系数的主要因素；伞衣阻力系数随气囊半径增大而下降，随伞衣名义直径增大而上升；在气动力分析和数值模拟的基础上，确定了伞衣阻力系数的计算公式。无人机试验完成各项设计功能，系统整体方案合理可行，为后续工程应用提供了重要参考。
- 应急飞行数据记录器 /
- 飞行器安全与救生 /
- 系统设计 /
- 降落伞阻力分析 /
- 无人机试验
Abstract:
The ejection emergency flight data recording and tracking system consists of the intelligent ejection separation, tow-type image tracking, inflatable soft-landing and data transmitting. In this paper, the key subsystem design and UAV test verification are carried out. According to the characteristics of the parachute-airbag module, the variation of the canopy drag coefficient in the airbag wake region is analyzed. The results show that the radius of the airbag and the nominal diameter of the canopy are the main factors affecting the canopy drag coefficient. The canopy drag coefficient decreases with the increase of the radius of airbag, and increases with the increase of the nominal diameter of the canopy. Based on the aerodynamic analysis and the numerical simulation, the canopy drag coefficient formula is obtained. Meanwhile, the full functions are achieved by UAV test, and it is proved that the system scheme is reasonable and feasible. It provides an important reference for the subsequent engineering application.
- emergency flight data recorder /
- aircraft safety and rescue /
- system design /
- parachute drag analysis /
- unmanned aerial vehicle experiment

HTML全文

图 1 分离式飞机应急数据记录跟踪系统工作原理

Figure 1. Schematic diagram of ejection emergency flight data recording and tracking system

下载: 全尺寸图片幻灯片

图 2 系统安装位置、机身下方气流流向与伞运动轨迹

Figure 2. System installation location, air flow direction below the fuselage and parachute trajectory

下载: 全尺寸图片幻灯片

图 3 弹射系统主要结构示意图

Figure 3. Schematic of ejection system with main components

下载: 全尺寸图片幻灯片

图 4 部分设计参数关联图

Figure 4. Relation map of partial design parameters

下载: 全尺寸图片幻灯片

图 5 气囊结构示意图

Figure 5. Schematic of airbag structure

下载: 全尺寸图片幻灯片

图 6 伞与气囊示意图

Figure 6. Schematic of parachute and airbag

下载: 全尺寸图片幻灯片

图 7 伞衣阻力系数随伞衣名义直径的变化

Figure 7. Variation of canopy drag coefficient with canopy nominal diameter

下载: 全尺寸图片幻灯片

图 8 伞-囊组合体对称面压力云图

Figure 8. Pressure contours of parachute-airbag symmetrical plane

下载: 全尺寸图片幻灯片

图 9 伞-囊组合体对称面Lamb矢量散度云图

Figure 9. Lamb vector divergence contours of parachute-airbag symmetrical plane

下载: 全尺寸图片幻灯片

图 10 剪切层的涡量厚度沿流向分布

Figure 10. Streamwise distribution of vorticity thickness inside shear layer

下载: 全尺寸图片幻灯片

图 11 不同工况下伞衣阻力系数随气囊半径、长度和伞衣名义直径的变化

Figure 11. Variation of canopy drag coefficient with radius and length of airbag and canopy nominal diameter in different working cases

下载: 全尺寸图片幻灯片

图 12 伞衣名义直径对伞衣阻力系数的影响

Figure 12. Influence of canopy nominal diameters on canopy drag coefficient

下载: 全尺寸图片幻灯片

图 13 无人机和HBG囊-伞系统

Figure 13. Unmanned aerial vehicle and HBG parachute-airbag system

下载: 全尺寸图片幻灯片

图 14 HBG系统坠地试验

Figure 14. Ground impact testing of HBG system

下载: 全尺寸图片幻灯片

图 15 HBG系统坠水试验

Figure 15. Impact testing on water surface of HBG system

下载: 全尺寸图片幻灯片

参考文献(26)

[1]	WISEMAN Y. Unlimited and protected memory for flight data recorders[J]. Aircraft Engineering and Aerospace Technology, 2016, 88(6): 866-872. doi: 10.1108/AEAT-06-2015-0152
[2]	LIANG G, WAN G, WANG J, et al. A novel underwater location beacon signal detection method based on mixing and normalizing stochastic resonance[J]. Sensors, 2020, 20(5): 1292. doi: 10.3390/s20051292
[3]	LI L, DAS S, JOHN H R, et al. Analysis of flight data using clustering techniques for detecting abnormal operations[J]. Journal of Aerospace Information Systems, 2015, 12(9): 587-598. doi: 10.2514/1.I010329
[4]	王伟, 费益. 民用飞机飞行记录系统研究[J]. 电光与控制, 2013, 20(3): 73-76. doi: 10.3969/j.issn.1671-637X.2013.03.017 WANG W, FEI Y. Flight recording system of civil aircraft[J]. Electronics Optics & Control, 2013, 20(3): 73-76(in Chinese). doi: 10.3969/j.issn.1671-637X.2013.03.017
[5]	ZHU M Y, ZHAO Y F, ZHANG C, et al. High precision positioning for searching airborne black boxes underwater based on acoustic orbital angular momentum[C]//2018 IEEE/AIAA 37th Digital Avionics Systems Conference (DASC). Piscataway: IEEE Press, 2018: 1-9.
[6]	LIU W Y, RICHARD J, CHEN C F. Underwater positioning study of flight recorder[C]//2019 IEEE Underwater Technology (UT). Piscataway: IEEE Press, 2019: 1-5.
[7]	WANG S S, HUNG H S, HO J J, et al. Improving detection technique for flight recorders of the distress airplanes crashed into ocean by integrating inertial navigation system into underwater locator beacon[J]. Journal of Marine Science and Technology, 2015, 23(4): 467-474.
[8]	COLL G T, PELLEGRINO J F, PILCHUK J. Black box: Improving aircraft safety by bringing the black box from the bottom of the sea to outer space[C]//AIAA Space and Astronautics Forum and Exposition. Reston: AIAA, 2017: 5130.
[9]	WANG Y, WAN K, ZHANG C, et al. Optimized real-time flight data streaming via air-to-air links for civil aviation[C]//2019 IEEE International Conference on Communications (ICC). Piscataway: IEEE Press, 2019: 1-6.
[10]	QIN H, KONG X, SHU P. Real-time downloading and analysis of QAR data using air-to-ground wireless communication[C]//2019 IEEE 1st International Conference on Civil Aviation Safety and Information Technology (ICCASIT). Piscataway: IEEE Press, 2019: 519-524.
[11]	YE W, SUN J H. Emergency mechanical and communication systems and methods for aircraft: U.S. Patent 9[P]. 2016-09-13.
[12]	张晓敏. 民机坠撞事故分析及典型吸能结构特性研究[D]. 天津: 中国民航大学, 2013: 7-21. ZHANG X M. Civil aircraft crash accidents analysis and typical energy-absorbing structure characteristics research[D]. Tianjin: Civil Aviation University of China, 2013: 7-21(in Chinese).
[13]	SEIGEL A E. The theory of high speed guns: AD0475660[R]. France: Advisory Group for Aerospace Research and Development, 1964.
[14]	US Department of Defense. Package cushioning design: MIL-HDBK-304 A-1974[S]. Washington, D.C. : US Department of Defense, 1974.
[15]	雷江利, 荣伟, 贾贺, 等. 国外新一代载人飞船减速着陆技术研究[J]. 航天器工程, 2017, 26(1): 100-109. doi: 10.3969/j.issn.1673-8748.2017.01.015 LEI J L, RONG W, JIA H, et al. Resrarch on descent and landing technology for new generation manned spacecraft[J]. Spacecraft Engineering, 2017, 26(1): 100-109(in Chinese). doi: 10.3969/j.issn.1673-8748.2017.01.015
[16]	王利荣. 降落伞理论与应用[M]. 北京: 宇航出版社, 1997: 82-83. WANG L R. Parachute theory and application[M]. Beijing: Astronautics Publishing House, 1997: 82-83(in Chinese).
[17]	孙建红, 周涛, 李名琦, 等. 直升机应急气囊充气及冲击着水过程数值分析[J]. 南京航空航天大学学报, 2012, 44(5): 713-717. doi: 10.3969/j.issn.1005-2615.2012.05.017 SUN J H, ZHOU T, LI M Q, et al. Numerical analysis of emergent airbag deployment and ditching crashworthiness process[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2012, 44(5): 713-717(in Chinese). doi: 10.3969/j.issn.1005-2615.2012.05.017
[18]	王一波, 孙建红, 侯斌, 等. 小型电子设备着陆缓冲气囊的缓冲性能分析[J]. 航天返回与遥感, 2018, 39(5): 25-33. doi: 10.3969/j.issn.1009-8518.2018.05.004 WANG Y B, SUN J H, HOU B, et al. Cushioning performance analysis of landing buffer airbag for small electronic equipment[J]. Spacecraft Recovery & Remote Sensing, 2018, 39(5): 25-33(in Chinese). doi: 10.3969/j.issn.1009-8518.2018.05.004
[19]	HUANG D Z, AVERY P, FARHAT C, et al. Modeling, simulation and validation of supersonic parachute inflation dynamics during Mars landing[EB/OL]. (2020-01-06)[2020-10-11]. https://arxiv.org/abs/1912.01658.
[20]	SHPUND Z, LEVIN D. Forebody influence on rotating parachute aerodynamic properties[J]. Journal of Aircraft, 1997, 34(2): 181-186. doi: 10.2514/2.2170
[21]	TANG J, QIAN L. Numerical study of forebody wake effect on axisymmetric parachute opening shock and drag reduction[J]. Mathematical and Computer Modelling of Dynamical Systems, 2016, 22(2): 141-159. doi: 10.1080/13873954.2016.1149492
[22]	HAMMAN C W, KLEWICKIl J C, KIRBY R M. On the Lamb vector divergence in Navier-Stokes flows[J]. Journal of Fluid Mechanics, 2008, 610: 261-284. doi: 10.1017/S0022112008002760
[23]	FANG M, SUN J H, ZHANG T, et al. Flow characteristics of double-cruciform parachute at inflating and inflated conditions[J]. Transactions of Nanjing University of Aeronautics & Astronautics, 2018, 35(6): 992-999. http://www.cqvip.com/QK/85388X/201806/7001106903.html
[24]	许常悦, 郑静, 王哲, 等. 方柱跨声速流动中的剪切层和尾迹特性[J]. 上海交通大学学报, 2020, 55(4): 9. https://www.cnki.com.cn/Article/CJFDTOTAL-SHJT202104008.htm XU C Y, ZHENG J, WANG Z, et al. The shear layer and wake characteristics of square cylinder in the transonic flow[J]. Journal of Shanghai Jiaotong University, 2020, 55(4): 9(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-SHJT202104008.htm
[25]	刘学翱, 吴宏宇, 王春洁, 等. 着陆器变阻尼缓冲器性能分析及参数优化[J]. 北京航空航天大学学报, 2018, 44(10): 2149-2155. doi: 10.13700/j.bh.1001-5965.2017.0805 LIU X A, WU H Y, WANG C J, et al. Performance analysis and parameter optimization of lander with variable damping buffer[J]. Journal of Beijing University of Aeronautics and Astronautics, 2018, 44(10): 2149-2155(in Chinese). doi: 10.13700/j.bh.1001-5965.2017.0805
[26]	刘帅, 王占学, 周莉, 等. 基于响应面法的短距/垂直起降飞机近地面升力损失[J]. 航空动力学报, 2017, 32(4): 874-881. https://www.cnki.com.cn/Article/CJFDTOTAL-HKDI201704014.htm LIU S, WANG Z X, ZHOU L, et al. Lift loss of short/vertical takeoff and landing aircraft proximity of ground base on response surface method[J]. Journal of Aerospace Power, 2017, 32(4): 874-881(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-HKDI201704014.htm