计及弯折波的舰载飞机偏心拦阻动力学分析

谢朋朋; 彭一明; 魏小辉; 聂宏

doi:10.13700/j.bh.1001-5965.2019.0516

计及弯折波的舰载飞机偏心拦阻动力学分析

doi: 10.13700/j.bh.1001-5965.2019.0516

谢朋朋^{1, 2, 3},
彭一明^{1, 2},
魏小辉^{1, 2, ,},
聂宏^{1, 2}

1.
南京航空航天大学机械结构力学及控制国家重点实验室, 南京 210016
2.
南京航空航天大学飞行器先进设计技术国防重点学科实验室, 南京 210016
3.
上海卫星装备研究所, 上海 200240

基金项目:

国防卓越青年科学基金 2018-JCJQ-ZQ-053

机械结构力学及控制国家重点实验室（南京航空航天大学）自主研究课题 MCMS-0217G01

中央高校基本科研业务费专项资金 NP2017401

江苏省博士后科研资助计划 2018K042B

中国博士后科学基金 2019M651827

江苏高校优势学科建设工程资助项目

详细信息

作者简介:
谢朋朋  男, 硕士研究生。主要研究方向:飞行器起落装置设计

彭一明  男, 博士研究生。主要研究方向:飞行器起落装置设计

魏小辉  男, 博士, 教授, 博士生导师。主要研究方向:飞行器起落装置设计

聂宏  男, 博士, 教授, 博士生导师。主要研究方向:飞行器起落装置设计

通讯作者:
魏小辉. E-mail:wei_xiaohui@nuaa.edu.cn

中图分类号: V245
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- 文章访问数: 642
- HTML全文浏览量: 151
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- 被引次数: 0
出版历程
- 收稿日期: 2019-09-19
- 录用日期: 2019-11-29
- 网络出版日期: 2020-08-20

Dynamic analysis of off-center arrest for carrier-based aircraft considering kink-wave

XIE Pengpeng^{1, 2, 3},
PENG Yiming^{1, 2},
WEI Xiaohui^{1, 2
, ,},
NIE Hong^{1, 2}

1.
State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
3.
Shanghai Institute of Spacecraft Equipment, Shanghai 200240, China

Funds:

National Defense Excellence Youth Science Fund 2018-JCJQ-ZQ-053

the Research Fund of State Key Laboratory of Mechanics and Control of Mechanical Structures(Nanjing University of Aeronautics and Astronautics) MCMS-0217G01

the Program the Central Universities NP2017401

Jiangsu Planned Projects for Research Funds for Postdoctoral Research Funds 2018K042B

China Postdoctoral Science Foundation 2019M651827

Project Funded by the Priority Academic Program Development of Jiangsu Higher Education Institutions

More Information

Corresponding author: WEI Xiaohui. E-mail:wei_xiaohui@nuaa.edu.cn

摘要

摘要:
为分析偏心度对舰载飞机拦阻过程的安全特性的影响，以某舰载飞机为研究对象，建立了拦阻系统动力学模型，研究舰载飞机在偏心状态下的拦阻动力学特性。基于离散的弯折波模型，进行了计及弯折波的对中拦阻动力学仿真，仿真结果与相关标准的试验数据进行了对比，变化规律基本一致。在此基础上进行了偏心拦阻动力学仿真，并研究了偏心度对于弯折波的影响，结果表明：因偏心拦阻，两侧拦阻索初始长度和拉伸速度不同，导致弯折波产生的载荷波动产生差异。当偏心度超过20%时，一侧拦阻索拉力不再呈现波动增大趋势，超过24%时，拦阻索拉力会出现负载和接近破断拉力。随着偏心度的增加，偏心侧的拦阻索承受更多的拦阻冲击载荷，偏心度过大会对拦阻系统的安全特性产生不利影响。
- 拦阻系统 /
- 动力学 /
- 弯折波 /
- 偏心 /
- 拦阻索
Abstract:
In order to analyze the influence of eccentricity on the safety characteristics of carrier-based aircraft in the process of arresting, a complete dynamic model of arresting system of a certain type of carrier-based aircraft is developed to know more about the dynamic property of aircraft in eccentric arrest. Based on the discrete kink-wave model, the simulation of central arrest with kink-wave is conducted. The simulation results are compared with the experimental data of the related standard and it comes out that the basic changing laws are the same. On the basis of central arrest, the dynamic simulation of off-center arresting is carried out, and the influence of eccentricity on bending wave is studied. The results show that due to eccentric arrest, the initial length and tensile speed of the arresting cables on both sides are different, resulting in the difference of load fluctuation caused by kink-wave. When the eccentricity is more than 20%, the tension of one side of the arresting cable no longer shows an increasing trend of fluctuation, and it will be negative and near breaking tension when the eccentricity is more than 24%.With the increase of eccentricity, the arresting cable on the eccentric side bears more arresting impact load, and the eccentricity will produce negative effects on the arresting system when it becomes too large.
- arresting system /
- dynamics /
- kink-wave /
- off-center /
- arresting cable

HTML全文

图 1 舰载飞机着舰挂索示意图

Figure 1. Schematic diagram of landing and cable hanging of carrier-based aircraft

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图 2 拦阻力示意图

Figure 2. Schematic diagram of arresting force

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图 3 偏心拦阻示意图

Figure 3. Schematic diagram of off-center arrest

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图 4 拦阻装置吸能器工作原理

Figure 4. Working principle of arresting gear energy absorber

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图 5 对中拦阻时拦阻索形式

Figure 5. Form of arresting cable in centering arrest

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图 6 偏心拦阻时拦阻索形式

Figure 6. Form of arresting cable in off-center arrest

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图 7 模型求解流程图

Figure 7. Flowchart of model calculation

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图 8 对中拦阻时拦阻力-位移曲线

Figure 8. Arresting force-displacement curve in centering arrest

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图 9 仿真与试验拦阻力-位移曲线对比

Figure 9. Comparison of arresting force-displacement curve between simulation and test

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图 10 弯折波期间左右侧带拉力

Figure 10. Port tape and starboard tape tension during kink-wave period

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图 11 偏心拦阻左右侧带拉力

Figure 11. Port tape and starboard tape tensionin off-center arrest

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图 12 偏心拦阻左右侧带拉力对比

Figure 12. Comparison of port and starboard tape tension in off-center arrest

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图 13 不同偏心度飞机响应

Figure 13. Aircraft response with different eccentricity

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表 1 舰载飞机及拦阻装置参数^[22]

Table 1. Parameters of carrier-based aircraft and arresting gear^[22]

参数	数值
舰载飞机质量/kg	22 680
着舰速度/(m·s^-1)	63
最大拦阻距离/m	104
吸能器活塞面积/m²	0.28
吸能器活塞行程/m	5
蓄能器气囊体积/m³	2
蓄能器气囊初始压强/MPa	3
蓄能器活塞面积/m²	1
甲板上两滑轮距离/m	34

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表 2 弯折波时长对比

Table 2. Comparison of duration of kink-wave

偏心度/%	侧带	弯折波时长/s
偏心度/%	侧带	第一重	第二重	第三重
0	左	0.099 3	0.205 4	0.332 0
0	右	0.099 3	0.205 4	0.332 0
10	左	0.109 0	0.225 7	0.365 3
10	右	0.089 3	0.184 7	0.298 2
20	左	0.118 9	0.246 4	0.399 4
20	右	0.079 4	0.164 2	0.264 8
24	左	0.122 9	0.254 8	0.413 2
24	右	0.075 4	0.155 9	0.254 9
25	左	0.123 9	0.256 8	0.416 6
25	右	0.074 4	0.153 8	0.256 9

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表 3 不同偏心度左右侧最大带拉力对比

Table 3. Comparison of maximum port and starboard tape tension under different eccentricity

参数	对中	偏心度为10%	偏心度为20%	偏心度为24%
左侧最大带拉力/kN	373.76	355.35	336.29	328.53
右侧最大带拉力/kN	373.76	395.93	455.14	481.79

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表 4 不同偏心度仿真结果对比

Table 4. Comparison of simulation results under different eccentricity

参数	对中	偏心度为10%	偏心度为20%	偏心度为24%
航向拦阻力峰值/kN	698.78	698.27	698.21	702.00
航向加速度峰值/(m·s^-2)	30.81	30.79	30.78	30.95
航向拦阻位移/m	86.76	86.40	85.48	85.03

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