仿生条纹制备顺序对襟翼滑轨表面WC/TC4熔覆仿生耐磨层的残余应力与变形影响的模拟分析

宋袁曾; 刘立君; 武梦瑶; 李亚萍

doi:10.12073/j.hj.20190121002

仿生条纹制备顺序对襟翼滑轨表面WC/TC4熔覆仿生耐磨层的残余应力与变形影响的模拟分析

1. 上海飞机制造有限公司, 上海 201324;
2. 浙江大学宁波理工学院, 浙江宁波 315100;
3. 南京航天航空大学, 南京 211106

基金项目:

商用飞机制造工程技术研究中心创新基金项目(COMAC-SFGS-2017-36736)

详细信息

作者简介:
宋袁曾,1983年出生,高级工程师;主要从事商用飞机表面处理及热加工相关方面工艺和科研工作。

通讯作者:
刘立君,1968年出生,博士,教授。

中图分类号: TG456.7
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出版历程
- 收稿日期: 2019-01-20

Simulated analysis of the influence of the sequence of bionic fringe preparation on residual stress and deformation of WC/TC4 cladding bionic wear-resistant layer on the surface of flaps slide

1. Shanghai Aircraft Manufacturing Co.Ltd, Shanghai 201324, China;
2. Ningbo Institute of Technology,Zhejiang University, Ningbo 315100, Zhejiang, China;
3. Nanjing University of Aeronautics and Astronautics, Nanjing 211106, China

摘要

摘要: 在飞机襟翼滑轨(TC4钛合金)表面激光熔覆制备仿生结构耐磨层试验过程中，由于仿生层结构密集，在激光熔覆过程中易产生较大的残余应力，发生翘曲变形。针对不同的仿生条纹制备顺序导致襟翼滑轨内部的残余应力与变形存在差异化问题，提出了激光仿生条纹制备顺序对襟翼滑轨表面WC/TC4熔覆层残余应力与变形的影响的数值模拟分析方法，通过CATIA建立实体模型，利用HyperMesh软件对实体模型划分网格，然后把网格模型导入MSC.Marc软件并设置各种条件以及仿生条纹制备顺序，建立了4种不同仿生条纹制备顺序的模型，并对不同仿生条纹制备顺序的残余应力和变形进行了模拟。模拟结果表明，残余应力主要集中在装夹点周围与熔覆层上，而变形主要集中在远离装夹点处的基体中心部位，一般在熔覆层上的变形量都较小，采用先两边再中间的仿生条纹制备顺序均可以有效地控制残余应力与变形，更进一步交替仿生条纹制备顺序较逐步仿生条纹制备顺序更优，残余应力和变形分别为792 MPa和1.08 mm。试验结果对飞机襟翼滑轨表面激光熔覆制备仿生结构耐磨层具有指导意义，提高了试验效率。
- TC4钛合金 /
- 仿生层 /
- 仿生条纹制备顺序 /
- 残余应力 /
- 变形
Abstract: In the experiment of fabricating wear-resistant layer of bionic structure by laser cladding on the surface of aircraft flaps slide rail （TC4 titanium alloy）,due to the dense structure of bionic layer,it is easy to produce large residual stress and warpage deformation in the process of laser cladding. According to the difference of residual stress and deformation in the flaps slide caused by different preparation sequence of bionic fringes,a numerical simulation method was proposed to analyze the effect of laser bionic fringes preparation sequence on residual stress and deformation of WC/TC4 cladding layer on the flaps slide surface. Firstly,the laser cladding process was simplified appropriately,and four different models of bionic fringe preparation sequence are established: the first step is to use CATIA software to establish the entity model,the second step is to use Hyper Mesh software to mesh the entity model,and the last step is to import the mesh model into MSC. Marc software and set various conditions and the order of bionic fringe preparation. Then,the residual stresses and deformations of different order of bionic fringe preparation were simulated. The simulation results show that the residual stress mainly concentrates around the clamping point and on the cladding layer,while the deformation mainly concentrates on the central part of the matrix far from the clamping point. Generally,the deformation on the cladding layer is small. The residual stress and deformation can be effectively controlled by using the sequence of bionic fringes preparation from both sides to the middle. Furthermore,the preparation sequence of alternating bionic stripes is better than that of stepby-step bionic stripes,and the residual stress and deformation of the former are 792 MPa and 1. 08 mm,respectively. The experimental results have guiding significance for the fabrication of bionic wear-resistant layer on the surface of aircraft flaps slide rail by laser cladding,and improve the experimental efficiency.
- TC4 titanium alloy /
- bionic layer /
- sequence of bionic stripe preparation /
- residual stress /
- deformation

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参考文献(15)

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