Quasi-Static Acoustic Mapping of Helicopter Blade-Vortex Interaction Noise

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dc.contributor.advisorSchmitz, Fredric Hen_US
dc.contributor.authorGopalan, Gauraven_US
dc.contributor.departmentAerospace Engineeringen_US
dc.contributor.publisherDigital Repository at the University of Marylanden_US
dc.contributor.publisherUniversity of Maryland (College Park, Md.)en_US
dc.date.accessioned2004-08-27T05:25:56Z
dc.date.available2004-08-27T05:25:56Z
dc.date.issued2004-07-27en_US
dc.description.abstractThis research extends the applicability of storage-based noise prediction techniques to slowly maneuvering flight. The quasi-static equivalence between longitudinal decelerating flight and steady-state longitudinal descent flight, and its application to the estimation of BVI noise radiation under slow longitudinal maneuvering flight conditions, is investigated through various orders of flight dynamics modeling. The entire operating state of the helicopter is shown to be similar during equivalent flight conditions at the same flight velocity. This equivalence is also applied to the prediction of control requirements during longitudinal maneuvers. Inverse simulation based flight dynamics models of lower order are seen to capture many important trends associated with slow maneuvers, when compared with higher order modeling. The lower order flight dynamics model is used to design controlled maneuvers that may be practically flown during descent operations or as part of research flight testing. A version of a storage-based acoustic mapping technique, extended to slowly maneuvering longitudinal flight, is implemented for helicopter main rotor Blade-Vortex Interaction (BVI) noise. Various approach trajectories are formulated and analytical estimates of the BVI noise radiation characteristics associated with a full-scale two-bladed rotor are mapped to the ground using this quasi-static mapping approach. Multi-segment decelerating descent approaches are shown to be effective in ground noise abatement. The effects of steady longitudinal winds are investigated on radiated and ground noise. Piloting trim choices are seen to dominate the noise radiation under these flight conditions.en_US
dc.format.extent4872254 bytes
dc.format.mimetypeapplication/pdf
dc.identifier.urihttp://hdl.handle.net/1903/1757
dc.language.isoen_US
dc.subject.pqcontrolledEngineering, Aerospaceen_US
dc.subject.pquncontrolledBlade-Vortex Interaction Noiseen_US
dc.subject.pquncontrolledAcousticsen_US
dc.subject.pquncontrolledHelicoptersen_US
dc.subject.pquncontrolledRotorcraften_US
dc.subject.pquncontrolledFlight Trajectory Managementen_US
dc.subject.pquncontrolledOperational Noiseen_US
dc.titleQuasi-Static Acoustic Mapping of Helicopter Blade-Vortex Interaction Noiseen_US
dc.typeDissertationen_US

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