民用飞机复合材料机身壁板装配协调形性调控技术研究

李东升; 杨应科; 翟雨农; 隋毅

doi:10.13801/j.cnki.fhclxb.20220812.002

民用飞机复合材料机身壁板装配协调形性调控技术研究

doi: 10.13801/j.cnki.fhclxb.20220812.002

北京航空航天大学　机械工程及自动化学院，北京 100191

基金项目: 国家自然科学基金 (52105502)；国家商用飞机制造工程技术研究中心创新基金(COMAC-SFGS-2019-263)

详细信息

通讯作者:
李东升，博士，教授，博士生导师，研究方向为飞机制造工艺与装备　E-mail: lidongs@buaa.edu.cn

中图分类号: TB330.1
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- 被引次数: 0
出版历程
- 收稿日期: 2022-07-12
- 修回日期: 2022-07-24
- 录用日期: 2022-08-02
- 网络出版日期: 2022-08-15
- 刊出日期: 2022-08-22

Research on shape and force control technology for commercial aircraft CFRP fuselage panel assembly

School of Mechanical Engineering and Automation, Beihang University, Beijing 100191, China

摘要

摘要: 为了更好地满足飞机安全性、经济性、舒适性和环保性的需求，以碳纤维增强树脂基复合材料为代表的轻质高强先进材料在新一代大型客机机体结构中得到了大量应用。复合材料机身壁板具有不同于传统金属材料机身壁板的装配工艺特点，因此，其对装配协调提出了新的要求。首先，概述了飞机复合材料机身壁板的制造工艺，分析了复合材料机身壁板装配协调技术现状与面临的问题。其次，探讨了适用于复合材料壁板的装配协调方法，并提出了一种面向复合材料机身壁板装配力形协同控制的全主动驱动柔性装配协调方法。最后，通过仿真和物理实验验证了该方法的有效性，实现了复合材料机身壁板力形协同优化控制。
- 碳纤维增强复合材料 /
- 民机机身壁板 /
- 飞机装配 /
- 柔性工装 /
- 力形协同控制
Abstract: In order to meet the requirements of safety, economy, comfortability, and environmental protection, high specific strength advanced material, represented by carbon fiber reinforced plastics (CFRP), has been widely used in the airframe of the new generation commercial aircraft. CFRP composite fuselage panels have different assembly characteristics in comparison with traditional metal fuselage panels, which put forward new requirements for aircraft assembly. This paper firstly summaries the manufacturing process of composite fuselage panel, and analyzes the current status and problems of composite fuselage panel assembly. Then, the methods in composite fuselage panel assembly is discussed, and a fully-active-drive flexible assembly method for force/shape control of composite fuselage panel assembly is proposed. Finally, the feasibility and effectiveness of the proposed method are verified by simulation and physical experiments, with optimized control of force/shape control reached.
- CFRP /
- commercial aircraft fuselage panel /
- aircraft assembly /
- flexible tooling /
- force/shape control

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图 1 飞机机身壁板柔性装配工装

Figure 1. Flexible assembly system of aircraft fuselage panel

下载: 全尺寸图片幻灯片

图 2 三自由度定位器与六自由度定位器对比

Figure 2. 3 degree of freedom linear positioner versus 6 degree of freedom parallel mechanism positioner

RX, RY and RZ—Rotate around the X, Y, and Z axis

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图 3 并联机构柔性装配工装

Figure 3. Flexible assembly system based on parallel mechanism

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图 4 全主动驱动的柔性装配协调方法流程图

Figure 4. Flow chart of the fully-active-drive flexible assembly method

DOF—Degree of freedom

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图 5 碳纤维增强复合材料(CFRP)机身壁板装配协调形性调控仿真环境

Figure 5. Deformation and force control simulation of carbon fiber reinforced plastics (CFRP) fuselage panel assembly

TCP—Tool center point; CP—Control point; CPM—Control point in middle

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图 6 CFRP机身壁板在不同装配协调方法下的应力与位移云图

Figure 6. Stress and displacement contours of CFRP fuselage panel with different assembly methods

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图 7 CFRP机身壁板装配协调实验

Figure 7. Experiment on CFRP fuselage panel assembly

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图 8 CFRP机身壁板外形偏差

Figure 8. Shape deviation of CFRP fuselage panel

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表 1 不同装配协调方法下有限元法(FEM)计算结果

Table 1. Finite element method (FEM) simulation results with different assembly method

	Max displacement/mm	Max mises stress/MPa	Failure index
3 DOF	30.7567	367.6460	0.322
6 DOF	30.7280	192.2145	0.136

下载: 导出CSV

表 2 装配协调过程中各定位器装配力传感器数据

Table 2. Data of force sensors on positioners in assembly process

Positioner	$\Delta {F_x}/{\text{N}}$	$ \Delta {F_y}/{\text{N}} $	$\Delta {F_{\textit{z}}}/{\text{N} }$	$\Delta {T_x}/{\text{N}} \cdot {\text{m}}$	$\Delta {T_y}{\text{/N}} \cdot {\text{m}}$	$\Delta {T_{\textit{z}}}/{\text{N} } \cdot {\text{m} }$
TCP11	−41.961	19.624	3.165	−3.337	12.919	−5.618
TCP12	10.282	39.851	−26.376	4.545	−12.102	2.291
TCP21	−7.256	9.540	48.994	−21.009	−10.124	−4.197
TCP22	−16.925	29.303	57.906	−14.923	9.543	3.445
TCP31	34.738	−47.685	−77.848	−18.173	1.637	5.339
TCP32	19.615	−35.563	−38.065	−14.636	−23.145	−2.430
Notes: $\Delta {F_x}$, $\Delta {F_y}$ and $\Delta {F_z}$—Variation of force in different directions; $\Delta {T_x}$, $\Delta {T_y}$ and $\Delta {T_z}$—Variation of torque in different directions.

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