Numerical simulation and experimental validation of slender wings flutter behaviour

被引：11

作者：

Cestino, E. ^{[1
]}

Frulla, G. ^{[1
]}

Spina, M. ^{[1
]}

Catelani, D. ^{[2
]}

Linari, M. ^{[2
]}

机构：

[1] Politecn Torino, DIMEAS, Corso Duca Abruzzi 24, I-10129 Turin, Italy

[2] MSC Software Corp, Turin, Italy

来源：

PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING | 2019年 / 233卷 / 16期

关键词：

Aeroelastic analysis; flutter; high altitude long endurance aircraft; non-linear flutter; numerical validation; slender structures; UNMANNED AIR VEHICLE; HIGH-ALTITUDE; AEROELASTIC BEHAVIOR; NONLINEARITIES; UAV;

D O I：

10.1177/0954410019879820

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

The flutter instability of high aspect ratio wings is numerically investigated by means of finite element aeroelastic analysis. The effect of static equilibrium deflection as well as the additional differential stiffness was introduced in the calculation by a new procedure based on MSC Nastran (TM) commercial code. The difference between the classic linear flutter calculation and the new procedure presented has been demonstrated numerically and also experimentally. The main parameters that influence the aeroelastic phenomenon were also highlighted and used to define the aeroelastic similarity model related to a typical aircraft of the high altitude long endurance aircraft category.

引用

页码：5913 / 5928

页数：16

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