北京航空航天大学学报 ›› 2000, Vol. 26 ›› Issue (3): 344-347.

• 论文 • 上一篇    下一篇

机身主要承力框结构优化设计研究

谢永河1, 吴文正2   

  1. 1. 北京航空航天大学 飞行器设计与应用力学系;
    2. 北京航空航天大学 无人驾驶飞行器设计研究所
  • 收稿日期:1999-05-07 出版日期:2000-03-31 发布日期:2010-09-27
  • 作者简介:谢永河(1967-),男,浙江舟山人,讲师,316000,浙江海洋学院机械工程系.

Structure Optimization Design Study of Fuselage Main Frame

XIE Yong-he1, WU Wen-zheng2   

  1. 1. Beijing University of Aeronautics and Astronautics,Dept. of Flight Vehicle Design and Applied Mechanics;
    2. Beijing University of Aeronautics and Astronautics, Research Institute of Unmanned Flight Vehicle Design
  • Received:1999-05-07 Online:2000-03-31 Published:2010-09-27

摘要: 将基于二次规划的准解析法优化理论应用于机身主要承力框的设计中,建立了机身主要承力框的优化模型.以承力框重量为目标函数,考虑了尺寸约束、强度约束和抗弯刚度约束,使优化后的机身结构不但满足强度要求,同时使优化后机翼机身对接接头的抗弯刚度与原准机保持一致.根据优化理论编制了SAAOP(Structure Analyzing and Optimizing Program)程序,计算结果表明该程序可应用于大型薄壁机身主要承力框的初步设计中.

Abstract: The method of optimization theory based on dual method was transplanted to design fuselage main frame, and the optimizing model of fuselage main frame was established. The target function is the weight of fuselage main frame. There are three kinds of constraints: dimension, strength and flexural rigidity constraint. The program(SAAOP) based on optimization theory was designed. The numerical results show that the structural strength after fuselage main frame was optimized is fit, all so the flexural rigidity of wing juncture. So this program can be used to design the main strength frame of large-scale leptodermous fuselage in predesign.

中图分类号: 


版权所有 © 《北京航空航天大学学报》编辑部
通讯地址:北京市海淀区学院路37号 北京航空航天大学学报编辑部 邮编:100191 E-mail:jbuaa@buaa.edu.cn
本系统由北京玛格泰克科技发展有限公司设计开发