Forming Process of Glass Fiber/Aluminum-Lithium Laminates Leading Edge Structure

HUA Xiaoge; LI Huaguan; LU Yi; CHEN Yujie

doi:10.16080/j.issn1671-833x.2017.16.058

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Forming Process of Glass Fiber/Aluminum-Lithium Laminates Leading Edge Structure

更新时间：2025-10-30

- Forming Process of Glass Fiber/Aluminum-Lithium Laminates Leading Edge Structure
- Aeronautical Manufacturing Technology Vol. 60, Issue 16, Pages: 58-63(2017)
- 作者机构：
  
  1. 南京航空航天大学材料科学与技术学院,南京,210016
  2. 南京工程学院材料工程学院,南京,211167
- 作者简介：
- 基金信息：
- DOI：10.16080/j.issn1671-833x.2017.16.058
  CLC：
- Published：2017
- 稿件说明：
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华小歌1，李华冠1，2，陆一1，陈虞杰1，孙邓辉2，陶杰1. 玻璃纤维-铝锂合金层板机翼前缘结构的成型工艺研究*[J]. 航空制造技术, 2017, 60(16): 58-63.

HUA Xiaoge1, LI Huaguan1，2, LU Yi1, CHEN Yujie1, SUN Denghui2, TAO Jie1. Forming Process of Glass Fiber/Aluminum-Lithium Laminates Leading Edge Structure. Aeronautical Manufacturing Technology, 2017, 60(16): 58-63.
华小歌1，李华冠1，2，陆一1，陈虞杰1，孙邓辉2，陶杰1. 玻璃纤维-铝锂合金层板机翼前缘结构的成型工艺研究*[J]. 航空制造技术, 2017, 60(16): 58-63. DOI： 10.16080/j.issn1671-833x.2017.16.058.

HUA Xiaoge1, LI Huaguan1，2, LU Yi1, CHEN Yujie1, SUN Denghui2, TAO Jie1. Forming Process of Glass Fiber/Aluminum-Lithium Laminates Leading Edge Structure. Aeronautical Manufacturing Technology, 2017, 60(16): 58-63. DOI： 10.16080/j.issn1671-833x.2017.16.058.

摘要

以机翼前缘典型件为成型目标，研究了玻璃纤维- 铝锂合金超混杂复合层板（NFMLs）大曲率构件的自成形工艺。研究发现，自成形工艺可实现NFMLs 机翼前缘等大曲率构件的成型，贴膜度高、厚度均匀性好、无显著分层缺陷、成型过程未形成较大的残余应力，为超混杂复合材料在飞机机翼蒙皮结构中的应用研究提供参考。

Abstract

Aiming at the large curvature leading edge component

the self-forming characteristic of glass fiber/aluminum- lithium super hybrid laminates (NFMLs) was studied. The results demonstrated that self-forming technology was feasible to manufacture the large curvature NFMLs component such as the leading edge parts. The investigated component exhibited no obvious interlaminar defect

presenting good fittability and thickness uniformity. Meanwhile

the forming process hardly resulted in the generation of large residual stress

which provided a reference for the application of super hybrid composites in the aircraft wing skin structure.

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Related Author

LU Yi

LI Huaguan

HUA Xiaoge

Related Institution

College of Material Science and Technology, Nanjing University of Aeronautics and Astronautics

School of Material Engineering, Nanjing Institute of Technology

Nanjing Fiberglass R & D Institute

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