气囊硬度对固化后帽型长桁厚度的影响

doi:10.7527/S1000-6893.2018.22667

材料工程与机械制造

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气囊硬度对固化后帽型长桁厚度的影响

马成¹, 赵聪¹, 刘兴宇², 张建宝³, 王显峰¹

1. 南京航空航天大学材料科学与技术学院, 南京 210016;
2. 上海飞机设计研究院, 上海 201210;
3. 中国运载火箭技术研究院航天材料与工艺研究所, 北京 100076

收稿日期:2018-09-11 修回日期:2018-10-15 出版日期:2019-06-15 发布日期:2018-12-24
通讯作者: 王显峰 E-mail:wx2003_999@126.com
基金资助:
一院高校联合创新基金（F19171246）；江苏省高校优势学科建设工程；中国博士后科学基金（2018M642250）；江苏省博士后科研资助计划（2018K064C）

Effect of airbag hardness on thickness of hat-shaped stringer

MA Cheng¹, ZHAO Cong¹, LIU Xingyu², ZHANG Jianbao³, WANG Xianfeng¹

1. College of Materials Science and Technology, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. Shanghai Aircraft Design and Research Institute, Shanghai 201210, China;
3. Aerospace Materials and Technology Research Institute, China Academy of Launch Vehicle Technology, Beijing 100076, China

Received:2018-09-11 Revised:2018-10-15 Online:2019-06-15 Published:2018-12-24
Supported by:
China Academy of Launch Vehicle Technology Funds Project(F19171246); the Priority Academic Program Development of Jiangsu Higher Education Institutions; China Postdoctoral Science Foundation(2018M642250); Jiangsu Planned Projects for Postdoctoral Research Funds(2018K064C)

摘要/Abstract

摘要： 为满足宽体客机机身轻质高强的要求，机身复合材料蒙皮需要长桁的支撑以提高复合材料壁板的刚度。为获得厚度均匀性良好的帽型长桁加筋壁板，对帽型长桁加筋壁板成型工艺中真空袋囊芯模的方法进行了改进，提出了一种硅橡胶囊芯模与真空袋囊芯模相结合的方法，获得了厚度均匀性良好的帽型长桁壁板，满足机身复合材料帽型长桁-蒙皮共固化成型时尺寸精度的要求。利用有限元仿真方法，研究了硅橡胶囊芯模截面尺寸、硅橡胶材料属性对长桁厚度均匀性的影响，结果发现所用硅橡胶囊芯模硬度越大，长桁尺寸均匀性越差。不同条件下所得长桁厚度对理论分析的准确性进行了验证。考虑硅橡胶硬度对长桁尺寸均匀性及工艺操作性的影响，最终选定所用硅橡胶气囊硬度为50HA，所得蒙皮-长桁实际测量的平均厚度与理论厚度偏差小于6%，细观分析发现蒙皮-长桁连接处纤维走向没有发生变形。

关键词: 帽型长桁加筋壁板, 共固化成型, 硅橡胶芯模, 厚度均匀性, 尺寸稳定性

Abstract: To obtain the hat-stiffened stringer wall plate with high quality, the forming method of vacuum bag core mould is improved. This paper presents a method to combine the silicon rubber core module with the vacuum core module, obtaining the hat-shaped stringer wall plate with high surface quality. It meets the requirement of dimension accuracy of composite hat-shaped stringers-skin with co-curing molding. Using the finite element simulation method, this paper studies the influence of the size of silicon rubber core mould and the properties of silicon rubber material on the thickness uniformity of stringer. The results show that the harder the core mold is, the less uniform the stringer is. The accuracy of the theoretical analysis is verified by the stringer thickness obtained under different conditions. Taking the influence of silicone rubber hardness on the uniformity of stringer dimension and process operation into consideration, finally, 50HA is selected as the hardness of the silicon rubber, and the measured average thickness of the skin-stringer deviates less than 6% from the theoretical thickness. The microanalysis shows that the fiber trend of the connection between skin and hat-shaped stringer has no deformation.

Key words: wall plate with hat-stiffened, co-curing molding, silicon rubber core mould, thickness uniformity, dimensional stability

中图分类号:

V260.6

马成, 赵聪, 刘兴宇, 张建宝, 王显峰. 气囊硬度对固化后帽型长桁厚度的影响[J]. 航空学报, 2019, 40(6): 422667-422667.

MA Cheng, ZHAO Cong, LIU Xingyu, ZHANG Jianbao, WANG Xianfeng. Effect of airbag hardness on thickness of hat-shaped stringer[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(6): 422667-422667.

参考文献

[1] 肖军, 李勇, 李建龙. 自动铺放技术在大型飞机复合材料结构件制造中的应用[J]. 航空制造技术, 2008(1):50-51. XIAO J, LI Y, LI J L. The application of automatic laying technology in the manufacture of large aircraft composite structural parts[J]. Aeronautical Manufacturing Technology, 2008(1):50-51(in Chinese).
[2] 杜芳静, 王亮. 复合材料长桁终止端设计[J]. 沈阳航空航天大学学报, 2016, 33(2):36-37. DU F J, WANG L. Composite stringer runout design[J]. Journal of Shenyang Aerospace University, 2016, 33(2):36-37(in Chinese).
[3] 罗辑, 辛朝波, 顾轶卓, 等. 热膨胀工艺硅橡胶芯模对复合材料圆管成型的影响[J]. 复合材料学报, 2012, 29(2):40-45. LUO J, XIN C B, GU Y Z, et al. Effect of thermal expansion process silicon rubber core mould on circular tube formation of composite materials[J]. Acta Materiae Compositae Sinica, 2012, 29(2):40-45(in Chinese).
[4] DONG O K, KEUM S W, LEE J H, et al. Thermally- expandable elastomer molding process for thermoset composite materials[J]. Composites Part Applied Science & Manufacturing, 2006, 37(11):2121-2127.
[5] 刘钧, 彭超义, 杜刚, 等. 膨胀芯模法制备炭/环氧主承力管件研究[J]. 材料工程, 2007, 25(9):37-41. LIU J, PENG C Y, DU G, et al. Fabricating carbon/epoxy primary-load bearing cylinders by thermal expansion mould method[J]. Journal of Materials Engineering, 2007, 25(9):37-41(in Chinese).
[6] 尹昌平, 刘钧, 刘卓峰, 等. 用于RTM工艺的软模材料的工艺性能[J]. 纤维复合材料, 2006, 23(1):3-5. YIN C P, LIU J, LIU Z F, et al. Study on the thermal expansion properties of flexible mold material for RTM process[J]. Fiber Composites, 2006, 23(1):3-5(in Chinese).
[7] 卢鑫, 孙志杰, 李超, 等. 硅橡胶热膨胀工艺预浸料铺层内树脂压力变化规律[J]. 复合材料学报, 2011, 28(3):50-55. LU X, SUN Z J, LI C, et al. The change law of resin pressure in the prepreg layer of silicone rubber thermal expansion process[J]. Acta Materiae Compositae Sinica, 2011, 28(3):50-55(in Chinese).
[8] 蒲永伟, 湛利华. 航空先进复合材料帽型加筋构件制造关键技术探究[J]. 航空制造技术, 2015, 473(4):78-81. PU Y W, ZHAN L H. Research on the key technology of manufacturing the cap type stiffener of aviation advanced composite materials[J]. Aeronautical Manufacturing Technology, 2015, 473(4):78-81(in Chinese).
[9] 曹晓明, 顾轶卓, 李超, 等. 碳纤维复合材料方管硅橡胶热膨胀成型工艺研究[J]. 玻璃钢/复合材料, 2012(6):64-68. CAO X M, GU Y Z, LI C, et al. Study on thermal expansion forming process of square tube silicon rubber of carbon fiber composite material[J]. Fiber Reinforced Plastics/Composites, 2012(6):64-68(in Chinese).
[10] 夏景云. 复合材料硅橡胶膨胀加压成型模具的设计与制造[J]. 玻璃钢/复合材料, 2015(5):81-84. XIA J Y. Design and manufacture of silica rubber pressure mold for composite manufacturing[J]. Fiber Reinforced Plastics/Composites, 2015(5):81-84(in Chinese).
[11] 靳武刚, 高建军, 吴利英. 热膨胀成型工艺应用于碳纤维复合材料[J]. 现代塑料加工应用, 2003, 15(1):19-21. JIN W G, GAO J J, WU L Y. Thermal expansion molding process is applied to carbon fiber composites[J]. Modern Plastics Processing and Applications, 2003, 15(1):19-21(in Chinese).
[12] 张钟. 热膨胀模压法成型复合材料夹层结构工艺及其性能研究[D]. 南京:南京航空航天大学, 2007:29-39. ZHANG Z. Research on the process and properties for foam core sandwich with thermal expansion molding[D]. Nanjing:Nanjing University of Aeronautics and Astronautics, 2007:29-39(in Chinese).
[13] 马刚, 唐文峰. 民用航空含Ω型长桁复合材料加筋壁板制造技术研究[J]. 航空制造技术, 2017, 60(12):74-77. MA G, TANG W F. Study on manufacturing technology of Ω type stiffened panel of civil aviation[J]. Aeronautical Manufacturing Technology, 2017, 60(12):74-77(in Chinese).
[14] 黄雨霓. 复合材料帽型长桁稳定性研究[J]. 科技视界, 2018,19(1):24-27. HUANG Y N. Research on the stability of composite omega stringer[J]. Science & Technology Vision, 2018, 19(1):24-27(in Chinese).
[15] 吴承思. 复合材料帽型长桁承载能力研究[J]. 装备制造技术, 2016(2):155-158. WU C S. Research on carrying capacity of composite map stringer[J]. Equipment Manufacturing Technology, 2016(2):155-158(in Chinese).
[16] 吴承思, 李穆生. 复合材料帽型长桁末端结构研究[J]. 纤维复合材料, 2014(2):22-25. WU C S, LI M S. Research on composite map stringer bottom[J]. Fibrous Composite, 2014(2):22-25(in Chinese).
[17] 荣海波. 复合材料长桁压缩稳定性方法研究[J]. 科技创新与应用, 2017(14):33-34. RONG H B. Study on compression stability of composite stringer[J]. Technological Innovation and Application, 2017(14):33-34(in Chinese).
[18] 葛东云, 莫与明, 何柏灵, 等. 复合材料帽型加筋板轴压试验及承载能力预测[J]. 复合材料学报, 2016, 33(7):1531-1539. GE D Y, MO Y M, HE B L, et al. Test and ultimate load capacity prediction of hat-stiffened composite panel under axial compression[J]. Acta Materiae Compositae Sinica, 2016, 33(7):1531-1539(in Chinese).
[19] 仲晓春, 宛静, 肖军. 橡胶绝热层的热膨胀成型工艺[J]. 宇航材料工艺, 2009, 39(3):61-63. ZHONG X CH, WAN J, XIAO J. Thermal expansion molding process of rubber insulation[J]. Aerospace Materials & Technology, 2009, 39(3):61-63(in Chinese).
[20] 金晶, 梁伟阁, 张振山. 橡胶隔振圈的结构刚度性能[J]. 海军工程大学学报, 2013, 25(5):43-44. JIN J, LIANG W G, ZHANG Z S. Performance analysis of structure stiffness of rubber isolator ring[J]. Journal of Naval Engineering University, 2013, 25(5):43-44(in Chinese).

E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

气囊硬度对固化后帽型长桁厚度的影响

Effect of airbag hardness on thickness of hat-shaped stringer

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