HELICOPTER VIBRATION REDUCTION BY LOCAL STRUCTURAL MODIFICATION.
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An efficient numerical method for the computation of the frequency response of a vibrating structure as a function of its structual properties is presented, and the results are applied to the problem of vibration reduction. A senistivity analysis is used to determine which structural element changes are most responsible for vibration reduction. The usefulness of these methods is demonstrated by numerical results for an elastic line helicopter model.
author list (cited authors)
Wang, B. P., Kitis, L., Pilkey, W. D., & Palazzolo, A. B.