复合材料机翼翼梁回弹研究

玻璃钢/复合材料 ›› 2018, Vol. 0 ›› Issue (2): 70-73.

复合材料机翼翼梁回弹研究

黄钢华¹, 贾丽杰², 徐鹏²

1.中国商用飞机有限责任公司,上海200126;
2.中国商飞上海飞机制造有限公司,上海200436

收稿日期:2017-08-18 出版日期:2018-02-28 发布日期:2018-02-28
作者简介:黄钢华(1984-),男,硕士研究生,工程师,主要从事复合材料研究和科技管理方面的工作,huangganghua@comac.cc。

SPRING-BACK STUDY FOR COMPOSITES SPAR

HUANG Gang-hua¹, JIA Li-jie², XU Peng²

1.Commercial Aircraft Corporation of China, Ltd., Shanghai 200126, China;
2.Shanghai Aircraft Manufacturing Co.,Ltd., Shanghai 200436, China

Received:2017-08-18 Online:2018-02-28 Published:2018-02-28

摘要/Abstract

摘要： 复合材料具有比强度和比模量高、抗疲劳性能好等特点,被广泛应用于航空航天领域,但复合材料在成型过程中受材料特性、铺层取向、固化制度和模具材料等因素的综合影响,会产生回弹变形,严重情况下可引起尺寸超差致制件和模具报废。通过回弹试验,采用有限元模拟试验件的回弹量,与实测结果比对后进行线性修正,得出修正公式,并在3 m机翼翼梁上进行验证。

关键词: 复合材料, 翼梁, 回弹, 修正

Abstract: Composite materials have been widely used in aerospace field for its high strength to weight ratio, high modulus, desirable fatigue resistance properties and other fine qualities. But, it is influenced by a variety of factors, such as material properties, ply orientations, curing system, mould material and so on. As a matter of fact, the shape of the composites after curing is not certain, spring-back may be caused, and even lead to scrapping of the cured part and mould due to deformation over tolerance. This article, through spring-back experiments on different parts of wing spar, simulates the spring-back of the demonstrator by finite element method. Then, we linearly amend it by comparing with the actual measured result, and acquire the amendatory formula, finally calculate the amendatory value, use it in the research and manufacturing of 3 m spar, and validate the amendatory formula.

Key words: composites, spar, spring-back, correction

中图分类号:

TB332

黄钢华, 贾丽杰, 徐鹏. 复合材料机翼翼梁回弹研究[J]. 玻璃钢/复合材料, 2018, 0(2): 70-73.

HUANG Gang-hua, JIA Li-jie, XU Peng. SPRING-BACK STUDY FOR COMPOSITES SPAR[J]. Fiber Reinforced Plastics/Composites, 2018, 0(2): 70-73.

参考文献

[1] 唐占文, 张博明. 复合材料收集制造一体化中的固化变形预报技术[J]. 航空制造技术, 2014(15): 32-37.
[2] 李建川, 何凯, 彭建, 等. 纤维增强热固性复合材料构件的固化变形研究进展[J]. 纤维复合材料, 2013(1): 45-48.
[3] 闫磊. 航空航天复合材料应用状况研究[J]. 工程技术: 文摘版, 2016(8): 273.
[4] 黄钢华, 张冬梅, 晏冬秀, 等. Invar钢模具制造工艺研究[J]. 航空工程进展, 2011(4): 485-488.
[5] 魏冉, 贾丽杰, 晏冬秀, 等. 热固性复合材料结构固化回弹变形研究进展[J]. 航空制造技术, 2013(Z2): 104-107.
[6] 贾丽杰. 树脂基复合材料结构固化变形的研究进展[J]. 航空制造技术, 2011(15): 102-105.
[7] Radford DW, Diefendorf R J. Shape instabilities in composites resulting from laminate anisotropy[J]. Journal of Reinforced Plastics and Composites,1993(12): 58-75.
[8] Wisnom Michael R., Potter Kevin D., Ersoy Nuri. Shear-lag analysis of the effect of thickness on spring-in of curved composites[J]. Journal of Composite Materials , 2007(41): 1311-1324.
[9] Bogetti TA, Gillespie JW. Process-induced stress and deformation in thick-section thermoset composite laminates[J]. Journal of Composite Materials, 1992, 26(5): 626-660.
[10] Bogetti TA, Gillespie JW. Two-dimensional cure simulation of thick thermosetting composites[J]. Journal of Composite Materials, 1991, 25(3): 239-273.
[11] Prasatya P, McKenna GB, Simon SL. A viscoelastic model for predicting isotropic residual stresses in thermosetting materials: effects of processing parameters[J]. Journal of Composite Materials, 2001, 35(10): 826-849.
[12] 王晓霞. 热固性树脂基复合材料的固化变形数值模拟[D]. 济南: 山东大学, 2012.
[13] 张吉. 基于有限元模拟的复合材料构件热压罐成型工艺研究[D]. 南京: 南京航空航天大学, 2012.
[14] 北京航空航天大学, 上海飞机制造有限公司.复合材料典型结构件的固化变形预测与控制自开发软件报告[R]. 2013.
[15] 蔡晓江, 邱坤贤, 王呈栋, 等. 航空高强度碳纤维单向层合结构复合材料在切削过程中的各向异性行为研究[J]. 南京航空航天大学学报, 2014(10): 684-693.