摘要
针对没有可供借鉴的重量评估经验公式来用于新式布局飞机研制的现状,为能够给出比较可信的结构重量估算,用于总体设计阶段飞机翼面结构重量指标分配,不仅对研制新机的概念设计与方案论证是十分重要的,也是必不可少的。本文开展了基于“变满应力”优化策略与有限元技术相结合的飞机翼面结构重量估算方法研究,并把这一求解过程搭建在具有自主知识产权的飞机多学科设计平台软件上。以具有大展弦比特征的“环球飞行者”外翼为例进行结构重量估算表明:本文方法不仅可以获得用于总体设计阶段可信的重量结果,同时其中的部件尺寸、应力和位移数据还能为结构与强度专业人员提供一定的参考意见。最后,得出四点结论。
Facing to the status which has no useful weight assessment empirical formula for new layout of aircraft, we didnt have an effective measure to allocate the structural weight for ‘ecentric＇layout at the stage of conceptual design up till now. The situation mentioned above was not only important, but also necessary to conceptual and preliminary design. Firstly, we set forth one kind of structural weight assessment based on the combination of ‘variable fully stress design＇and finite element method. Secondly, we put up this procedure on the aircraft MDO platform. Then, we utilized high -aspect - ratio outer wing of Global Flyer as an example to evaluate its weight. The results showed that the proposed approach could give reliable structural weight for conceptual and preliminary design. Meanwhile, the dimension and stress as well as deformation of some parts could provide some advice for structure designer and strength analyst. Finally, four conclusions were drawn from this paper.
出处
《航空计算技术》
2006年第3期85-89,共5页
Aeronautical Computing Technique
基金
航空科学基金(03B53003)
辽宁省科学技术航空专项基金(20044007)
关键词
总体设计
结构重量估算
满应力
有限元
大展弦比机翼
conceptual design
structural weight evaluation
fully stress design
FEM
high-aspect-ratio wing
