Aeroelastic Tailoring of Helicopter BladesSource: Journal of Computational and Nonlinear Dynamics:;2015:;volume( 010 ):;issue: 006::page 61001DOI: 10.1115/1.4027717Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: The dynamic loads transmitted from the rotor to the airframe are responsible for vibrations, discomfort and alternate stress on components. A new and promising way to minimize vibration is to reduce dynamic loads at their source by performing an aeroelastic optimization of the rotor. This optimization uses couplings between the flapwisebending motion and the torsion motion. The impacts of elastic couplings (composite anisotropy) and inertial couplings (centerofgravity offset) on blade dynamic behavior and on dynamic loads are evaluated in this paper. First, analytical results, based on a purely linear modal approach, are given to understand the influence of these couplings on blade dynamic behavior. Then, a complete nonlinear aeroelastic model of the rotor, including elastic and inertial couplings, is derived. Finally, this last model is used to improve a simplified but representative blade (homogeneous beam with constant chord) and results are presented.
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| contributor author | Cornette, Donatien | |
| contributor author | Kerdreux, Benjamin | |
| contributor author | Michon, Guilhem | |
| contributor author | Gourinat, Yves | |
| date accessioned | 2017-05-09T01:15:55Z | |
| date available | 2017-05-09T01:15:55Z | |
| date issued | 2015 | |
| identifier issn | 1555-1415 | |
| identifier other | cnd_010_06_061001.pdf | |
| identifier uri | http://yetl.yabesh.ir/yetl/handle/yetl/157341 | |
| description abstract | The dynamic loads transmitted from the rotor to the airframe are responsible for vibrations, discomfort and alternate stress on components. A new and promising way to minimize vibration is to reduce dynamic loads at their source by performing an aeroelastic optimization of the rotor. This optimization uses couplings between the flapwisebending motion and the torsion motion. The impacts of elastic couplings (composite anisotropy) and inertial couplings (centerofgravity offset) on blade dynamic behavior and on dynamic loads are evaluated in this paper. First, analytical results, based on a purely linear modal approach, are given to understand the influence of these couplings on blade dynamic behavior. Then, a complete nonlinear aeroelastic model of the rotor, including elastic and inertial couplings, is derived. Finally, this last model is used to improve a simplified but representative blade (homogeneous beam with constant chord) and results are presented. | |
| publisher | The American Society of Mechanical Engineers (ASME) | |
| title | Aeroelastic Tailoring of Helicopter Blades | |
| type | Journal Paper | |
| journal volume | 10 | |
| journal issue | 6 | |
| journal title | Journal of Computational and Nonlinear Dynamics | |
| identifier doi | 10.1115/1.4027717 | |
| journal fristpage | 61001 | |
| journal lastpage | 61001 | |
| identifier eissn | 1555-1423 | |
| tree | Journal of Computational and Nonlinear Dynamics:;2015:;volume( 010 ):;issue: 006 | |
| contenttype | Fulltext |