北京航空航天大学学报 ›› 2014, Vol. 40 ›› Issue (6): 782-787.doi: 10.13700/j.bh.1001-5965.2013.0391

• 论文 • 上一篇    下一篇

民用飞机机身结构快速设计及自动化调整

陈稗, 罗明强, 武哲   

  1. 北京航空航天大学 航空科学与工程学院, 北京 100191
  • 收稿日期:2013-07-02 出版日期:2014-06-20 发布日期:2014-07-03
  • 作者简介:陈 稗(1987- ),女,北京人,博士生,chenbai214@126.com.
  • 基金资助:

    工业和信息化部“民用飞机总体设计支撑软件”基金资助项目

Rapid structure design and automated adjustment of civil aircraft fuselage

Chen Bai, Luo Mingqiang, Wu Zhe   

  1. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
  • Received:2013-07-02 Online:2014-06-20 Published:2014-07-03

摘要: 为了在飞机设计前期对结构进行较详细的考虑,满足在设计前期进行以强度为约束的重量特性评估、方案评估等方面的需求,研究了民用飞机机身结构快速设计、建模以及模型自动化调整的方法,并运用该方法在一个开放式飞机总体设计环境中开发实现了此功能.定义了飞机机身坐标系,提出了机身各类结构件的参数化描述及构建模型的方法,建立了交互式机身结构设计环境,可自动获取结构的体积、重量和惯性矩等信息.在此基础上实现了模型自动化调整和重量特性的同步更新,为总体设计阶段进行飞机重量、气动和结构的多学科设计优化奠定了基础.最后,用设计实例验证了该方法的有效性.

Abstract: To improve the quality and efficiency of civil aircraft design, it would be better to take structure design into account earlier, instead of beginning structure design in later preliminary design phase or detail design phase. A method to implement fuselage structure rapid design, modeling, and automated adjustment for civil aircraft was studied. The parametric modeling method of fuselage structure was represented, and a functionality of rapid fuselage structure design for civil aircraft, which can obtain the characteristics including mass, centre of gravity and inertia, was developed in an open aircraft conceptual/preliminary design system. In addition, the automatic adjustment of fuselage structure model and automatic update of mass property data were implemented, which contribute to multidisciplinary optimization work. An instance was presented to illustrate that this implementation method is feasible and effective.

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