Abstract
The bending-torsional flutter characteristics of a cantilever composite wing subjected to engine thrust are presented. The engine thrust modeled as a follower force and the wing modeled as a two degree of freedom beam. In order to consider the spanwise and chordwise location and the properties of the engine location, the generalized function theory is used. Unsteady Theodorsen aerodynamic theory in time domain, is used. The general laminate composite theory is used for modeling the effects of the ply angles on the flutter boundary. The Ritz method is subsequently applied to convert the partial differential equations into a set of ordinary differential equations. In order to precisely consider the location of the engine Dirac delta function is used. Moreover, the numerical results are compared with the published results and excellent agreement is observed. Numerical results highlighting the effect of engine thrust on the wing instability, is presented.
| Language | English |
|---|---|
| Title of host publication | Advanced Materials Research II |
| Pages | 1568-1572 |
| Number of pages | 5 |
| DOIs | |
| Publication status | Published - 27 Feb 2012 |
| Externally published | Yes |
| Event | 2nd International Conference on Advanced Material Research - Chengdu, China Duration: 7 Jan 2012 → 8 Jan 2012 Conference number: 2 http://www.icamr.org/2012.html |
Publication series
| Name | Advanced Materials Research |
|---|---|
| Volume | 463-464 |
| ISSN (Print) | 1022-6680 |
Conference
| Conference | 2nd International Conference on Advanced Material Research |
|---|---|
| Abbreviated title | ICAMR 2012 |
| Country | China |
| City | Chengdu |
| Period | 7/01/12 → 8/01/12 |
| Internet address |
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Bending-torsional flutter of a composite rectangular cantilever wing subjected to engine thrust. / Amoozgar, Mohammad Reza; Irani, Saied.
Advanced Materials Research II. 2012. p. 1568-1572 (Advanced Materials Research; Vol. 463-464).Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
TY - GEN
T1 - Bending-torsional flutter of a composite rectangular cantilever wing subjected to engine thrust
AU - Amoozgar, Mohammad Reza
AU - Irani, Saied
PY - 2012/2/27
Y1 - 2012/2/27
N2 - The bending-torsional flutter characteristics of a cantilever composite wing subjected to engine thrust are presented. The engine thrust modeled as a follower force and the wing modeled as a two degree of freedom beam. In order to consider the spanwise and chordwise location and the properties of the engine location, the generalized function theory is used. Unsteady Theodorsen aerodynamic theory in time domain, is used. The general laminate composite theory is used for modeling the effects of the ply angles on the flutter boundary. The Ritz method is subsequently applied to convert the partial differential equations into a set of ordinary differential equations. In order to precisely consider the location of the engine Dirac delta function is used. Moreover, the numerical results are compared with the published results and excellent agreement is observed. Numerical results highlighting the effect of engine thrust on the wing instability, is presented.
AB - The bending-torsional flutter characteristics of a cantilever composite wing subjected to engine thrust are presented. The engine thrust modeled as a follower force and the wing modeled as a two degree of freedom beam. In order to consider the spanwise and chordwise location and the properties of the engine location, the generalized function theory is used. Unsteady Theodorsen aerodynamic theory in time domain, is used. The general laminate composite theory is used for modeling the effects of the ply angles on the flutter boundary. The Ritz method is subsequently applied to convert the partial differential equations into a set of ordinary differential equations. In order to precisely consider the location of the engine Dirac delta function is used. Moreover, the numerical results are compared with the published results and excellent agreement is observed. Numerical results highlighting the effect of engine thrust on the wing instability, is presented.
KW - Composite wing
KW - Flutter boundary
KW - Follower force
KW - Unsteady aerodynamic
UR - http://www.scopus.com/inward/record.url?scp=84857241392&partnerID=8YFLogxK
U2 - 10.4028/www.scientific.net/AMR.463-464.1568
DO - 10.4028/www.scientific.net/AMR.463-464.1568
M3 - Conference contribution
SN - 9783037853634
T3 - Advanced Materials Research
SP - 1568
EP - 1572
BT - Advanced Materials Research II
ER -