OPTIMIZATION OF STRUCTURES TO SATISFY FLUTTER REQUIREMENTS

被引：15

作者：

TURNER, MJ

机构：

来源：

AIAA JOURNAL | 1969年 / 7卷 / 05期

关键词：

D O I：

10.2514/3.5248

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

Numerical procedure is developed for determining relative proportions of selected elements of aircraft structure, to attain specified flutter speed with minimum total mass; procedure is based on finite-element idealization of structure; Lagrange multipliers are employed to introduce conditions for neutral dynamic stability (flutter equations) as dynamic constraints; resulting system of nonlinear equations is solved by Newton-%Raphson process to determine masses of elements of system.

引用

页码：945 / &

共 9 条

[1]

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[2]

BISPLINGHOFF RL, 1962, PRINCIPLES AEROELAST, P417

[3]

BOOTH AD, 1955, NUMERICAL METHODS, P155

[4] NUMERICAL SOLUTION OF SYSTEMS OF NONLINEAR EQUATIONS [J].