Nonlinear aeroelasticity

被引:285
作者
Dowell, E [1 ]
Edwards, J
Strganac, T
机构
[1] Duke Univ, Durham, NC 27708 USA
[2] NASA, Langley Res Ctr, Langley, VA 23681 USA
[3] Texas A&M Univ, College Stn, TX 77843 USA
来源
JOURNAL OF AIRCRAFT | 2003年 / 40卷 / 05期
关键词
D O I
10.2514/2.6876
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
Substantial progress has been made in modeling and understanding nonlinear aeroelastic phenomena. Experimental and theoretical investigations have shown good correlation for a number of nonlinear physical mechanisms. A number of physical mechanisms can lead to nonlinear aeroelastic response including the impact of static fluid or static structural nonlinearities in changing the flutter boundary of an aeroelastic system. The good news is that finite amplitude oscillations can in some cases replace what would otherwise be the rapidly growing and destructive oscillations of classical flutter behavior.
引用
收藏
页码:857 / 874
页数:18
相关论文
共 116 条
[1]  
*AGARD, 1974, AGARD SPEC M WINGS S
[2]  
[Anonymous], 1997, DISSERTATION
[3]   ROLE OF SHOCKS IN THE SUB-TRANSONIC FLUTTER PHENOMENON [J].
ASHLEY, H .
JOURNAL OF AIRCRAFT, 1980, 17 (03) :187-197
[4]   Comparison of two Navier-Stokes methods with benchmark active control technology experiments [J].
Bartels, RE ;
Schuster, DM .
JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, 2000, 23 (06) :1094-1099
[5]  
BENDIKSEN O, 2002, 20021488 AIAA
[6]   Energy approach to flutter suppression and aeroelastic control [J].
Bendiksen, OO .
JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, 2001, 24 (01) :176-184
[7]  
BENDIKSEN OO, 2001, INT FOR STRUCT DYN 2, V11
[8]   Computational test cases for the benchmark active controls model [J].
Bennett, RM ;
Scott, RC ;
Wieseman, CD .
JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, 2000, 23 (05) :922-929
[9]  
BENNETT RM, 1991, 104180 NASA TM
[10]  
BENNETT RM, 1998, 982421 AIAA