非对称因素对舰载机弹射起飞安全的影响

林佳铭; 张轶; 乐挺; 王立新

doi:10.13700/j.bh.1001-5965.2017.0391

非对称因素对舰载机弹射起飞安全的影响

doi: 10.13700/j.bh.1001-5965.2017.0391

北京航空航天大学航空科学与工程学院, 北京 100083

详细信息

作者简介:
林佳铭  男, 博士研究生。主要研究方向:舰载机起降安全与控制

张轶  男, 硕士研究生。主要研究方向:舰载机飞行动力学

乐挺  男, 博士, 讲师。主要研究方向:飞行力学与飞行控制

王立新  男, 教授, 博士生导师。主要研究方向:飞机设计、飞行动力学与控制、飞行安全等

通讯作者:
王立新, E-mail:wlx_c818@163.com

中图分类号: V212.13
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- 被引次数: 6
出版历程
- 收稿日期: 2017-06-09
- 录用日期: 2017-08-31
- 网络出版日期: 2018-02-20

Effect of asymmetric factors on carrier-based aircraft catapult launch safety

School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

More Information

Corresponding author: WANG Lixin, E-mail:wlx_c818@163.com

摘要

摘要:
非对称因素会导致舰载机在弹射后出现横航向偏离，并影响其纵向起飞航迹。针对定位偏心、弹射道偏角、甲板横摇等3类扰动因素，开展了这些非对称因素对飞机弹射起飞特性影响规律的理论分析与仿真计算，掌握了飞机在甲板滑跑段的偏航运动特性以及离舰上升段的横航向偏离特性。基于弹射起飞后飞机航迹下沉量与滚转角2项安全性要求，通过仿真计算建立了安全甲板风（WOD）包线，结果表明：安全甲板风包线的下边界由最大航迹下沉量约束，左右边界由最大滚转角限制确定，上边界由最大海面风速决定；定位偏心、甲板横摇等非对称因素将显著缩小安全甲板风包线的风速和风向角范围。
- 舰载机 /
- 甲板风(WOD)包线 /
- 安全准则 /
- 定位偏心 /
- 弹射道偏角 /
- 甲板横摇
Abstract:
Asymmetric factors lead to lateral-directional departure after catapult launch, and affect longitudinal flyaway characteristics as well. Principle analysis and numerical simulation are conducted to reveal yawing movement characteristics during deck run and lateral-directional departure characteristics in catapult flyaway, with the consideration of three typical factors, such as off-center position, catapult runway angle and deck roll. According to the safety requirements of sink off bow and bank angle, safe wind over deck (WOD) envelope is figured through numerical simulation under different takeoff conditions. Simulation results indicate that lower boundary of the envelope is limited by maximum sink off bow, left and right boundary is restricted to maximum bank angle, and upper boundary is determined by constant wind at sea level. The range of safe WOD's direction and speed would be obviously narrowed due to off-center position or deck roll.
- carrier-based aircraft /
- wind over deck (WOD) envelope /
- safety criteria /
- off-center position /
- catapult runway angle /
- deck roll

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图 1 非对称弹射起飞仿真模型的结构框图

Figure 1. Structure block diagram for asymmetric catapult launch simulation model

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图 2 机轮参考点的受力分解

Figure 2. Forces and moments at wheel reference point

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图 3 起飞甲板坐标系

Figure 3. Coordinate system of takeoff deck

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图 4 典型弹射力-弹射冲程曲线

Figure 4. Typical curve of catapult force versus catapult stroke

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图 5 对称弹射起飞仿真

Figure 5. Simulation of symmetric catapult launch

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图 6 偏心弹射示意图

Figure 6. Schematic diagram of off-center position catapult

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图 7 偏航振荡频率与阻尼比随弹射冲程的变化关系

Figure 7. Yawing fluctuation frequency and damping ratio versus catapult stroke

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图 8 不同偏心距对弹射起飞的影响

Figure 8. Effect of different off-center positions on catapult launch

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图 9 弹射道偏角对弹射起飞的影响

Figure 9. Effect of catapult runway angle on catapult launch

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图 10 甲板横摇对弹射起飞的影响

Figure 10. Effect of deck roll on catapult launch

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图 11 不同海面风速下的作业甲板风范围

Figure 11. Operation WOD range at different sea wind speeds

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图 12 不同海面风速下安全甲板风包线

Figure 12. Safe WOD envelope at different sea wind speeds

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图 13 非对称因素对安全甲板风包线的影响

Figure 13. Effect of asymmetric factors on safe WOD envelope

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表 1 基本仿真工况参数取值

Table 1. Basic working condition parameters for simulation

参数	数值
质量/kg	17 064
转动惯量I_xx/(kg·m²)	31 100
转动惯量I_yy/(kg·m²)	242 865
转动惯量I_zz/(kg·m²)	263 029
转动惯量I_xz/(kg·m²)	-3 399
起飞推力/kN	112.5
航向/(°)	0(正北)
风向/(°)	180(正北风)
典型航速/kn	15
典型风速/kn	10

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表 2 不同弹射道偏角与海面风的组合条件

Table 2. Combined conditions of different catapult runway angles and sea wind

工况	航速/ (m·s^-1)	航向/ (°)	风速/ (m·s^-1)	风向/ (°)	弹射道偏角/ (°)
工况1	10	0	0		0
工况2	10	0	0		-8
工况3	10	0	1.4	90	-8
工况4	10	0	1.4	90	0

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表 3 不同工况的弹射过程分析

Table 3. Catapult process analysis for different working conditions

工况	弹射初始时刻(机舰相对速度为0 m/s)			弹射离舰时刻(机舰相对速度为60 m/s)
工况	甲板风风速	飞机空速	侧向受力分析	飞机空速	侧向受力分析	飞机地速	航迹变化趋势
工况1			侧滑角0°，无侧力		侧滑角0°，无侧力		沿跑道方向离舰，爬升时无侧风影响
工况2			侧滑角8°，机身受到向左的侧力		侧滑角1.1°，机身受到向左的侧力		向跑道右前方离舰，爬升时无侧风影响
工况3			侧滑角0°，无侧力		侧滑角0°，无侧力		向跑道右前方离舰，爬升时有侧风影响
工况4			侧滑角-8°，机身受到向右的侧力		侧滑角-1.1°，机身受到向右侧力		沿跑道前方离舰，爬升时有侧风影响
注：飞机空速按式(21)计算获得。在弹射初始时刻，机舰相对速度为零，故飞机空速(虚线)等于甲板风风速(实线)；在离舰时刻，机舰相对速度指向弹射道方向，故飞机空速(虚线)等于甲板风风速(短实线)与机舰相对速度(长实线)的矢量合成。

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