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民用飞机翼梢小翼多约束优化设计
引用本文:张雨,孙刚,张淼.民用飞机翼梢小翼多约束优化设计[J].空气动力学学报,2006,24(3):367-370.
作者姓名:张雨  孙刚  张淼
作者单位:1. 上海交通大学工程力学系,上海,200240
2. 上海飞机设计研究所,上海,200232
摘    要:采用Lagrange乘数优化方法,约束升力系数和机翼翼根弯矩,通过修改机翼 翼梢小翼组合体的结构外形,减小机翼的诱导阻力和形状阻力,提高机翼的展向效率和升阻比的大小。成功的实例设计结果表明,本文方法对民用飞机机翼-翼梢小翼的设计具有应用价值。

关 键 词:翼梢小翼  优化设计  诱导阻力  形状阻力  翼根弯矩
文章编号:0258-1825(2006)03-367-04
收稿时间:2005-09-11
修稿时间:2005-09-112005-11-17

The optimal design of civil aircraft winglet with multiple constraint
ZHANG Yu,SUN Gang,Zhang Miao.The optimal design of civil aircraft winglet with multiple constraint[J].Acta Aerodynamica Sinica,2006,24(3):367-370.
Authors:ZHANG Yu  SUN Gang  Zhang Miao
Institution:1.Dept. of Engineering Mechanics, Shanghai Jiao Tong University, Shanghai 200240,China; 2. Shanghai Institute of Design Aircraft, Shanghai 200232, China
Abstract:The Lagrange multipliers optimization method is presented for wing winglet configuration with constraint for lifting coefficient and wing root bending moment.By shaping the wing with winglet,decrease the sum of induced drag and profile drag,increase span efficiency and lift-drag ratio.The results of practical design showed that this method can be used in the design of winglet.
Keywords:winglet  optimal design  induced drag  profile drag  wing root bending moment
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