飞机复合材料壁板装配中临时紧固件数量与布局优化方法

黎雪婷; 安鲁陵; 岳烜德; 周来水; 卫炜

doi:10.13801/j.cnki.fhclxb.20210913.003

飞机复合材料壁板装配中临时紧固件数量与布局优化方法

doi: 10.13801/j.cnki.fhclxb.20210913.003

南京航空航天大学　机电学院，南京 210016

详细信息

通讯作者:
安鲁陵，博士，教授，博士生导师，研究方向为飞机装配技术　 E-mail: anllme@nuaa.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: 2021-07-23
- 修回日期: 2021-08-22
- 录用日期: 2021-08-28
- 网络出版日期: 2021-09-14
- 刊出日期: 2022-08-31

Optimization method of the number and layout of temporary fasteners in composite panel assembly of aircraft

College of Mechanical and Electrical Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 在飞机装配中，广泛采用安装临时紧固件的方式，对构件进行预连接，以固定构件之间的相对位置，并起到消除构件接触面间的间隙、增强结构稳定性等作用。针对飞机复合材料壁板装配，为了提升预连接效率与装配质量，结合有限元法与遗传算法，提出了一种考虑复合材料损伤的临时紧固件数量与布局优化方法。该优化方法以提高复合材料壁板与骨架间的间隙消除率、减少临时紧固件安装数量为优化目标，以临时紧固件的安装数量、布局与预紧力为控制变量，并根据三维Hashin准则预测复合材料壁板损伤状态，以复合材料壁板不发生损伤为约束条件。并通过复合材料壁板预连接实验，证明该优化方法能在避免复合材料壁板损伤的前提下，用较少数量的临时紧固件实现较高的间隙消除率。
- 复合材料 /
- 飞机装配 /
- 临时紧固件 /
- 预连接 /
- 遗传算法 /
- 损伤起始判据
Abstract: In aircraft assembly, it is widely used to install temporary fasteners to fix the relative position between components, which is called pre-joining. This pre-joining operation can also eliminate the gap between the contact surfaces and enhance the stability of the structure. Aiming at aircraft composite panel assembly, in order to improve the pre-joining efficiency and assembly quality, an optimization method of the number and layout of temporary fasteners considering composite material damage was proposed. Combining the finite element method and genetic algorithm, this optimization method aimed at improving the elimination rate of gap between panels and frames, and reducing the number of temporary fasteners installed. In this optimization method, the number, layout and load of temporary fasteners were taken as control variables, and the damage state of the composite panel predicted by 3D Hashin criterion was taken as constraint conditions. An experimental model of pre-joining of compo-site panel was taken as an example to demonstrate that this optimization technology can avoid the damage of composite panels, and achieve a higher gap elimination rate with less temporary fasteners.
- composite materials /
- aircraft assembly /
- temporary fasteners /
- pre-joining /
- genetic algorithms /
- damage initiation criterion

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图 1 飞机壁板与骨架装配的常见形式

Figure 1. Common forms of aircraft panel and frame assembly

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图 2 典型临时紧固件连接方式示意图

Figure 2. Schematic diagram of typical temporary fasteners

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图 3 某型壁板装配模型的单元设置示例

Figure 3. Example of element setting of a certain type of panel assembly model

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图 4 临时紧固件的约束与载荷设置示意图

Figure 4. Schematic diagram of constraint and load setting of temporary fasteners

MPC—Multi-point constraint

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图 5 壁板与骨架接触面的间隙测量点

Figure 5. Gap measurement points between panel and frame

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图 6 设计变量与临时紧固件加载参数设置之间的关系

Figure 6. Relationship between design variables and setting of temporary fastener loading parameters

h—Layout component of design variables X; F—Load component of design variables X

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图 7 基于遗传算法的优化路线

Figure 7. Optimization route based on genetic algorithm

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图 8 复合材料壁板预连接实验模型

Figure 8. Experimental model of pre-joining of composite panel

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图 9 复合材料壁板实验模型的安装与优化前预连接布局

Figure 9. Installation of the composite panel experimental model and the pre-joining layout before optimization

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图 10 3D-数字图像相关法(DIC)技术基本流程

Figure 10. Basic process of 3D-digital image correlation (DIC) technology

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图 11 T300碳纤维增强环氧树脂基复合材料壁板在优化前预连接方案下的FEA与DIC测得的法向位移云图比较

Figure 11. Comparison of normal displacement nephogram by FEA and DIC measurement under the pre-joining scheme before optimization of T300 carbon fiber reinforced epoxy resin matrix composite panel

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图 12 T300碳纤维增强环氧树脂基复合材料壁板在优化前后预连接方案下的法向位移云图比较

Figure 12. Comparison of normal displacement nephogram under pre-joining schemes before and after optimization of T300 carbon fiber reinforced epoxy resin matrix composite panel

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图 13 T300碳纤维增强环氧树脂基复合材料壁板的优化实验的迭代曲线

Figure 13. Iteractive curves of optimization experiment of T300 carbon fiber reinforced epoxy resin matrix composite panel

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表 1 T300碳纤维增强环氧树脂基复合材料壁板性能参数

Table 1. Performance parameters of T300 carbon fiber reinforced epoxy resin matrix composite panel

E₁/GPa	E₂/GPa	E₃/GPa	ν₁₂	ν₁₃	ν₂₃	G₁₂/GPa	G₁₃/GPa	G₂₃/GPa
156	8.35	8.35	0.33	0.33	0.55	4.2	4.2	2.25
X_1T/MPa	X_1C/MPa	X_2T/MPa	X_2C/MPa	X_3T/MPa	X_3C/MPa	X₁₂/MPa	X₁₃/MPa	X₂₃/MPa
1050	750	20	106	20	106	72	72	72
Notes: E₁, E₂, E₃—Elasticity modulus in fiber direction (i.e. vector 1), perpendicular to fiber direction (i.e. vector 2) and in thickness direction (i.e. vector 3); ν₁₂, ν₁₃ , ν₂₃—Poisson's ratio of a plane with normal vector 3, 2 and 1; G₁₂, G₁₃, G₂₃—Shear modulus of a plane with normal vector 3, 2 and 1; X_1T/X_1C, X_2T/X_2C, X_3T/X_3C—Tensile strength/compressive strength in vector 1, 2 and 3; X₁₂, X₁₃, X₂₃—Shear strength of plane with normal vector 3, 2 and 1.

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表 2 遗传算法参数设置

Table 2. Parameter settings of genetic algorithm

Parameter	Value
Initial population size	10
Population size maintained during iteration	12
Probability of a single mutation in an individual	0.2
Magnitude of a single mutation	0.1
New individuals created by mutation	5
New individuals randomly generated	5
Good individuals retained to the next generation	2
Good individuals output to file in each iteration	10

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表 3 T300碳纤维增强环氧树脂基复合材料壁板在优化前预连接方案下的有限元分析(FEA)与DIC测量结果的比较

Table 3. Comparison of finite element analysis (FEA) and DIC measurement results under the pre-joining scheme before optimization of T300 carbon fiber reinforced epoxy resin matrix composite panel

Result		FEA		DIC (Average value)
Result		Gravity (g=9.8 m/s²)	No gravity	DIC (Average value)
Normal displacement	Max/mm	0.7478	0.7477	0.7300
Normal displacement	Min/mm	−0.3640	−0.3640	−0.4500
Normal strain in the horizontal direction		0.0006	0.0006	0.0003
Normal strain in the gravity direction		0.0006	0.0006	0.0002
Shear strain on the plane of panel		0.0023	0.0023	0.0005

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表 4 T300碳纤维增强环氧树脂基复合材料壁板在迭代次数为3时的优化结果比较

Table 4. Comparison of optimization results of T300 carbon fiber reinforced epoxy resin matrix composite panel when the number of iterations is 3

Serial number		1	2	3	4	5	6	7	8
Specified initial individual		None						Good individual of 1
Optimized pre-joining scheme	F(X)	0.12	0.14	0.14	0.12	0.13	0.12	0.14	0.14
	R(X)	0.95	0.85	0.84	0.85	0.88	0.93	0.84	0.85
	n	8	6	6	7	7	8	6	6
	H	{6,11,13, 16,17,19, 21,24}	{5,8,16, 17,20,22}	{3,13,15, 18,22,23}	{3,5,13, 14,17, 21,23}	{3,8,14, 15,17, 20,21}	{4,9,13, 16,18,19,21,24}	{3,13,15, 18,22,23}	{5,8,16, 17,20,22}
	F/N	700	600	750	650	500	800	1000	1000
Notes: F(X)—Fitness function (i.e. objective function); R(X)—Elimination rate of gap between panels and frames; n—Number of temporary fasteners; H—Layout of temporary fasteners; F—Load of temporary fasteners.

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