考虑机轮形变的车辆-飞机牵引滑出系统运动学特性分析

鲁鑫; 孙宇宁; 唐杰; 张威

doi:10.13700/j.bh.1001-5965.2023.0029

考虑机轮形变的车辆-飞机牵引滑出系统运动学特性分析

doi: 10.13700/j.bh.1001-5965.2023.0029

鲁鑫^{1, 2},
孙宇宁^{1, 2},
唐杰^{1, 2, ,},
张威^{1, 2}

1.
中国民航大学航空工程学院，天津 300300
2.
中国民航航空地面特种设备研究基地，天津 300300

基金项目: 国家自然科学基金(U2033208)；国家自然科学基金民航联合重点项目(U2233212)

详细信息

通讯作者:
E-mail：tangjie_cauc@163.com

中图分类号: V226⁺.7；V351.34
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出版历程
- 收稿日期: 2023-01-31
- 录用日期: 2023-04-07
- 网络出版日期: 2023-04-21
- 整期出版日期: 2025-02-28

Kinematic characteristics analysis of vehicle-aircraft towing taxi system considering wheel deformation

LU Xin^{1, 2},
SUN Yuning^{1, 2},
TANG Jie^{1, 2
, ,},
ZHANG Wei^{1, 2}

1.
College of Aeronautical Engineering，Civil Aviation University of China，Tianjin 300300，China
2.
Aviation Special Ground Equipment Research Base，Civil Aviation Administration of China，Tianjin 300300，China

Funds: National Natural Science Foundation of China (U2033208); National Natural Science Foundation of China Civil Aviation Joint Key Project (U2233212)

More Information

Corresponding author: E-mail：tangjie_cauc@163.com

摘要

摘要:
为探究抱轮机构与飞机前起落架机轮约束关系对牵引系统运动学特性的影响，基于Winkler接触模型建立了飞机前起落架机轮径向受力与径向接触形变的关系，以Douglas TBL-180无杆飞机牵引车和B737-800客机为参考对象，建立牵引车-飞机系统运动学模型，在抱轮机构与飞机前起落架机轮不同约束关系下，探究多种工况下牵引车与飞机加速度偏移的变化规律。结果表明：飞机前起落架机轮径向受力与径向接触形变具有较强的非线性关系，对牵引系统的运动特性具有较大影响；在加速与制动状态下，飞机前起落架机轮两端约束力的增大都将减小牵引车与飞机加速度的偏移，但在加速状态下，约束力的增大为加速度偏移减小的主要影响因素，而在制动状态下，约束力增大到一定值(约10000 N)后对加速度偏移影响很小。
- 牵引滑出 /
- 前起落架机轮 /
- 抱轮机构 /
- Winkler接触模型 /
- 加速度偏移
Abstract:
To explore the influence of the restraint relationship between the wheel-holding mechanism and the nose landing gear wheel on the kinematic characteristics of the towing system, this paper established the relationship between the radial force and radial contact deformation of the aircraft nose landing gear wheel based on the Winkler contact model. With the Douglas TBL-180 towbarless aircraft tractor and B737-800 passenger aircraft as reference objects, the kinematic model of the tractor-aircraft system was established, and under the different constraint relationships between the wheel-holding mechanism and the nose landing gear wheel, the change law of the acceleration bias of the tractor and the aircraft under various operating conditions was explored. The results show that the radial force of the nose landing gear wheel has a strong nonlinear relationship with the radial contact deformation, which greatly influences the motion characteristics of the towing system. Under the acceleration and braking states, the increase in the constraint force at both ends of the nose landing gear wheel will reduce the acceleration bias of the tractor and the aircraft. However, under the acceleration state, the increase in the constraint force is the main influencing factor for the decrease in the acceleration bias, and under the braking state, the constraint force has little effect on the acceleration bias when increasing to a certain value (about 10 000 N).
- towing taxi /
- nose landing gear wheel /
- wheel-holding mechanism /
- Winkler contact model /
- acceleration bias

HTML全文

图 1 飞机牵引系统工作图

Figure 1. Working diagram of aircraft towing system

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图 2 飞机牵引系统Adams运动学仿真模型

Figure 2. Kinematic simulation model of aircraft towing system in Adams

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图 3 夹紧杆与机轮接触模型

Figure 3. Contact model between clamping rod and wheel

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图 4 Winkler简化弹性接触模型

Figure 4. Winkler simplified elastic contact model

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图 5 飞机前起落架机轮径向受力与径向形变

Figure 5. Radial force and radial deformation of nose landing gear wheel

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图 6 无杆飞机牵引系统加速与制动受力分析

Figure 6. Analysis of acceleration and braking force of towbarless aircraft towing system

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图 7 不同加速度牵引力仿真曲线

Figure 7. Simulation curves of traction force with different accelerations

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图 8 牵引车与飞机约束力为0状态

Figure 8. State where constraint force between tractor and aircraft is 0

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图 9 约束力为0时牵引车与飞机加速度偏移量

Figure 9. Acceleration bias of tractor and aircraft when constraint force is 0

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图 10 加速状态下牵引车与飞机加速度最大偏移量

Figure 10. Maximum acceleration bias of tractor and aircraft under acceleration state

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图 11 约束力为0时牵引车与飞机加速度偏移量

Figure 11. Acceleration bias of tractor and aircraft when constraint force is 0

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图 12 制动状态下牵引车与飞机加速度最大偏移量

Figure 12. Maximum acceleration bias of tractor and aircraft under braking state

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表 1 飞机参数设置^[17-18]

Table 1. Aircraft parameters setting^[17-18]

参数	数值
重心距地面的垂直距离/mm	2760.7
重心距主起轮轴水平距离/mm	1267.6
质量/kg	75976.7
飞机x轴转动惯量/(kg·mm²)	1.254×10¹²
飞机y轴转动惯量/(kg·mm²)	4.202×10¹²
飞机z轴转动惯量/(kg·mm²)	5.286×10¹²
两主起落架之间的距离/mm	5714.6
前起到后起水平距离/mm	15596
质心距离地面的垂直距离/mm	2760.7
质心距离前起的水平距离/mm	14328.4
牵引过程中前起被抬起高度/mm	280

下载: 导出CSV

表 2 无杆飞机牵引车的轮胎参数^[17,19]

Table 2. Tire parameters of towbarless aircraft tractor^[17,19]

轮胎	轮胎质量/ kg	自由半径/ mm	胎面宽度/ mm	高宽比	法向刚度系数/ (N·mm⁻¹)	法向阻尼系数/ (N·mm⁻¹)	滚动阻力系数	纵向刚度/ (N·mm⁻¹)	侧偏刚度/ (N·mm⁻¹)	静摩擦因数	动摩擦因数
前轮	140	365.5	250	0.68	1000	25	0.017	5000	1000	0.8	1
后轮	190	421.25	355	0.84	4500	25	0.017	5000	1000	0.8	1

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表 3 B737-800飞机轮胎参数^[17,20]

Table 3. Tire parameters of B737-800 aircraft^[17,20]

轮胎	轮胎质量/ kg	自由半径/ mm	胎面宽度/ mm	高宽比	法向刚度系数/ (N·mm⁻¹)	法向阻尼系数/ (N·mm⁻¹)	滚动阻力系数	纵向刚度/ (N·mm⁻¹)	侧偏刚度/ (N·mm⁻¹)	静摩擦因数	动摩擦因数
前轮	50	343	196.8	0.547	2400	28	0.017	2000	800	0.8	1
后轮	150	568	419	0.74	2800	28	0.017	6000	800	0.8	1

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表 4 牵引车牵引力仿真值与理论值

Table 4. Simulation and theoretical values of traction force of tractor

加速度/ （mm·s⁻²）	牵引车牵引力理论计算值/N	牵引车牵引力仿真平均值/N	仿真值与理论值偏差/%
300	33771.61	33959.8	0.55
450	45168.1	45232.83	0.14
600	56564.6	56975.91	0.72

下载: 导出CSV

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