Helicopter Vibratory Loads Alleviation through Combined Action of Trailing-Edge Flap and Variable-Stiffness Devices
The aim of this paper is the assessment of the capability of controllers based on the combined actuation of flaps and variable-stiffness devices to alleviate helicopter main rotor vibratory hub loads. Trailing-edge flaps are positioned at the rotor blade tip region, whereas variable-stiffness device...
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| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
| Published: |
Wiley
2015-01-01
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| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2015/485964 |
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| Summary: | The aim of this paper is the assessment of the capability of
controllers based on the combined actuation of flaps and
variable-stiffness devices to alleviate helicopter main rotor
vibratory hub loads. Trailing-edge flaps are positioned at the
rotor blade tip region, whereas variable-stiffness devices are
located at the pitch link and at the blade root. Control laws are
derived by an optimal control procedure based on the best
trade-off between control effectiveness and control effort, under
the constraint of satisfaction of the equations governing rotor
blade aeroelastic response. The numerical investigation concerns
the analysis of performance and robustness of the control
techniques developed, through application to a four-bladed
helicopter rotor in level flight. The identification of the most
efficient control configuration is also attempted. |
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| ISSN: | 1687-5966 1687-5974 |