大型民用飞机机身对接区双面均衡夹紧装置设计

doi:10.3969/j.issn.1004-132X.2025.10.034

摘要/Abstract

摘要：

为提高机身对接区装配效率，拟采用一体化的挤胶制孔装配工艺，该工艺需实现对接区的均衡夹紧，保证密封胶的均匀挤出并有效抑制孔加工导致的层间间隙。以某大型民用飞机机身对接区典型工况特征为例，设计了一种双面均衡夹紧装置，通过有限元仿真量化表征区间载荷不均匀度，结合最小单孔夹紧力，对装置均衡压紧模块布局及主体材料进行优化，开展了装置在对接区的均衡载荷测试与一体化挤胶制孔验证。结果表明，均衡压紧模块能够显著提高装置夹紧载荷的均匀性，且随着中间橡胶压紧环硬度的提高，夹紧载荷均匀性进一步改善；装置主体选用刚度更好的Q235材料后，对接区最小单孔夹紧力达到403 N，区间载荷不均匀度为1.4%，密封胶能够充分均匀挤出，且层间未形成明显毛刺和卷入切屑。

关键词: 机身对接, 航空叠层结构, 均衡载荷, 产品设计

Abstract:

To enhance the assembly efficiency of the fuselage docking areas， an integrated assembly process of sealant extrusion and hole-making was proposed. The process was required to achieve balanced clamping of the docking areas， ensuring the uniform extrusion of the sealant and effectively suppressing the interlaminar gaps caused by hole machining. The typical working condition characteristics of a large civil aircraft fuselage docking areas were taken as an example， and a dual-sided equilibrium clamping device was designed. Using finite element simulation to quantify the unevenness of the interlaminar loads， combined with the minimum single-hole clamping force， the layout of the device's balanced pressing module and the main body materials were optimized. The balanced load tests of the device's docking areas and the integrated sealant squeezing and hole making verification were carried out. Results indicate that the balanced pressing module significantly enhances the uniformity of the clamping loads of the devices. Furthermore， when the hardness of the central rubber pressing ring is increased， the uniformity of the clamping loads is further improved. After selecting Q235 material， which offers better rigidity， for the main body of the devices， the minimum single-hole clamping force in the docking areas reaches 403 N， with an interval load unevenness of 1.4%. The sealant is extruded fully and evenly， and no significant burrs or rolled chips are formed between the layers.

Key words: fuselage docking, aerospace stacked structure, equalizing load, product design

中图分类号:

V262.4

许雷, 胡俊山, 凡志磊, 葛恩德, 张胜平, 田威. 大型民用飞机机身对接区双面均衡夹紧装置设计[J]. 中国机械工程, 2025, 36(10): 2444-2452.

Lei XU, Junshan HU, Zhilei FAN, Ende GE, Shengping ZHANG, Wei TIAN. Design of a Dual-sided Equilibrium Clamping Device for Fuselage Docking Areas of Large Civil Aircrafts[J]. China Mechanical Engineering, 2025, 36(10): 2444-2452.

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链接本文: https://www.cmemo.org.cn/CN/10.3969/j.issn.1004-132X.2025.10.034

https://www.cmemo.org.cn/CN/Y2025/V36/I10/2444

图/表 18

图1 某型号客机机身对接区结构示意图

Fig.1 Structural schematic diagram of the docking area of a certain passenger aircraft fuselage

图2 过渡区工艺特征

Fig.2 Process characteristics of transition zone

图3 机身对接区装配工艺流程

Fig.3 Assembly process flow of fuselage docking area

图4 双面均衡夹紧装置装配示意图

Fig.4 Assembly diagram of dual-sided equilibrium clamping device

图5 夹紧装置主体结构图

Fig5 Main body diagram of the clamping device

图6 装置夹紧示意图

Fig.6 Schematic diagram of the clamping of the device

图7 双面均衡夹紧装置有限元模型

Fig.7 Finite element model of dual-sided equilibrium clamping device

表1 曲面叠层结构材料参数

Tab.1 Material parameters of curved laminated structure

	牌号	弹性模量/GPa	泊松比
蒙皮、带板	2系列铝合金	71	0.31
隔框	7系列铝合金	68.9	0.3

表2 夹紧装置材料参数

Tab.2 Material parameters of the clamping device

材料	弹性模量/GPa	泊松比
Q235	210	0.3
HT250	120	0.25

表3 橡胶压紧环材料参数

Tab.3 Material parameters of the rubber compression ring

硬度/HS	52	61
C₁₀	0.380	0.573
C₂₀	0.011	0.024
C₃₀	0.000 004	-0.000 17
D₁=D₂=D₃=0

图8 层间均衡应力仿真预测结果

Fig.8 Interlaminar equilibrium stress simulation prediction results

图9 单孔夹紧力仿真结果

Fig.9 Clamping force simulation results of single-hole

图10 均衡载荷测试平台

Fig.10 Equilibrium pressure testing platform

图11 制孔工艺验证平台

Fig.11 Verification platform for drilling process

图12 对接区层间载荷测试结果

Fig.12 Test results of docking area interlaminar load

图13 单孔夹紧力试验结果

Fig.13 Test results of clamping force for single-hole

图14 密封剂挤出效果

Fig.14 Effect of sealant extrusion

图15 制孔后层间质量结果

Fig.15 Interlaminar quality analysis after drilling

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