基于实测数据的复合材料构件装配干涉与间隙计算
作者:
作者单位:

1.航空工业济南特种结构研究所,高性能电磁窗航空科技重点实验室,济南 250023;2.南京航空航天大学,南京 210016

作者简介:

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中图分类号:

TP391

基金项目:

具有复杂装配界面的飞机复合材料结构装配应力产生机理及其控制


Interference and Gap Calculation for Composite Component Assembly Based on Measured Data
Author:
Affiliation:

1.AVIC Research Institute for Special Structures of Aeronautical Composite, Aviation Key Lab of Science and Technology onHigh Performance Electromagnetic Windows,Jinan 250023;2.Nanjing University of Aeronautics And Astronautics,Nanjing 210016

Fund Project:

Stress generation mechanism and control of aircraft composite structure with complex assembly interface

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    摘要:

    针对因成型误差引起的复合材料构件装配干涉问题,本文基于激光测量设备获取装配件点云数据,提出一种基于实测数据的复合材料构件装配干涉与间隙的降维求解方法,将三维装配的干涉与间隙计算转化为二维边界距离计算。以某型飞机雷达罩装配为例,通过实验验证了本文所提出的方法与算法的可行性,相较于原有装配工艺,装配精度与装配效率得到了提升。

    Abstract:

    For the composite component assembly interference problem caused by molding errors, this paper proposed a method of dimensional reduction of composite component assembly interference and clearance based on point cloud data obtained from laser equipment, it converts the interference and clearance calculation of the three-dimensional assembly into the calculation of the two-dimensional boundary distance. Taking a certain type of aircraft random assembly as an example,the feasibility of the proposed method and algorithm is verified through experiments, and the assembly accuracy and efficiency are improved compared with the original assembly process.

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引用本文

王琦,张聘,仲钰,衡兴波,张德伟.基于实测数据的复合材料构件装配干涉与间隙计算[J].宇航材料工艺,2024,54(3):22-29.

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历史
  • 收稿日期:2023-08-10
  • 最后修改日期:2023-10-29
  • 录用日期:2023-10-30
  • 在线发布日期: 2024-07-01
  • 出版日期: