• CN:11-2187/TH
  • ISSN:0577-6686

机械工程学报 ›› 2019, Vol. 55 ›› Issue (13): 144-150.doi: 10.3901/JME.2019.13.144

• 数字化设计与制造 • 上一篇    下一篇


晏梦雪1, 田小永1, 彭刚1, 李涤尘1, 姚瑞娟2, 张薇2, 白锐3, 孟伟杰3   

  1. 1. 西安交通大学机械制造系统工程国家重点实验室 西安 710049;
    2. 北京宇航系统工程研究所 北京 100076;
    3. 达索析统(上海)信息技术有限公司 上海 200120
  • 收稿日期:2018-07-16 修回日期:2018-12-29 出版日期:2019-07-05 发布日期:2019-07-05
  • 通讯作者: 田小永(通信作者),男,1981年出生,博士,副教授,博士研究生导师。主要研究方向为多材料、复合材料3D打印(增材制造)技术及其应用。E-mail:leoxyt@mail.xjtu.edu.cn
  • 作者简介:晏梦雪,女,1985年出生,博士研究生。主要研究方向为复合材料的选择性激光烧结。E-mail:coolsnow@stu.xjtu.edu.cn
  • 基金资助:

Performance Study of Lightweight Composites Equipment Section Support Fabricated by Selective Laser Sintering

YAN Mengxue1, TIAN Xiaoyong1, PENG Gang1, LI Dichen1, YAO Ruijuan2, ZHANG Wei2, BAI Rui3, MENG Weijie3   

  1. 1. State Key Laboratory of Manufacturing Systems Engineering, Xi'an Jiaotong University, Xi'an 710049;
    2. China Academy of Launch Vehicle Technology, Beijing 100076;
    3. Dassault Systems(Shanghai) Information Technology Co., Ltd. Shanghai 200120
  • Received:2018-07-16 Revised:2018-12-29 Online:2019-07-05 Published:2019-07-05

摘要: 针对目前飞行器仪器支架对轻量化、快速开发及结构优化的要求,提出使用选择性激光烧结(SLS)工艺制备轻质复合材料仪器支架,并对其性能进行了综合评估。根据飞行器仪器支架的使用环境,首先对SLS制备短切碳纤维增强尼龙复合材料(CF/PA12)进行了工艺优化并详细研究了复合材料的力学性能、热性能及动态热力学性能,试验结果表明,SLS制备的CF/PA12复合材料的拉伸强度达到63.8 MPa,弹性模量为6.5 GPa,弯曲强度达到118.06 MPa,体积密度仅为1.03 g/cm3,尤其是其损耗因子在0.03~0.06之间,远远大于金属材料,具有更好的减振性能,并对其装配形式进行了评估。最后,以一款火箭仪器支架为例,通过拓扑优化,实现支架进一步减重40%,且都通过了载荷试验(2 000 N),从而证明了SLS制备复合材料在航空航天领域制件轻量化、快速开发及结构优化方面具有明显的技术优势和一定的应用潜力。

关键词: 尼龙复合材料, 拓扑优化, 选择性激光烧结, 仪器支架, 增材制造

Abstract: A novel method to prepare equipment section support for flight vehicle is proposed by using lightweight thermoplastic composites prepared by selective laser sintering (SLS), in order to meet the requirements of lightweight, rapid development and structure optimization in equipment section support. Considering the special service environment of equipment section support, the process parameter optimization for preparing the short carbon fiber reinforced PA12 composites by SLS is carried out and the mechanical property, thermal behavior and dynamic mechanical property of the carbon fiber reinforced nylon12 composites prepared by SLS are studied, and the test results show that the tensile strength is about 63.8 MPa with an elastic modulus of 6.5 GPa, the flexural strength reached to 118.06 MPa and the damping factor is 0.03-0.06, which is much higher than metal material, indicating a better damping performance. The fracture morphology of composites shows massive pores and its bulk density is only about 1.03 g/cm3, which is far lower than metal material. Meanwhile, several assemble methods are used for the composites prepared by SLS, and the pulling-out force and failure behavior are assessed. At last, an equipment section support in rocket and the optimized structural support are prepared by SLS, and the weight of the optimized structural support is only 60% of the original. The results of load experiment shows these two supports both can withstand the load of 2 000 N without destruction and clear deformation, which demonstrated the feasibility and the potentials in the aerospace field of proposed method, as the technical advantage of SLS in the lightweight, rapid development and structure optimization.

Key words: additive manufacturing, carbon fiber reinforced nylon12, equipment section support, selective laser sintering, topology optimization