Mission performance simulation of integrated helicopter–engine systems using an aeroelastic rotor model

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dc.contributor.authorGoulos, Ioannis
dc.contributor.authorGiannakakis, Panos
dc.contributor.authorPachidis, Vassilios
dc.contributor.authorPilidis, Pericles
dc.date.accessioned2017-07-28T08:11:04Z
dc.date.available2017-07-28T08:11:04Z
dc.date.issued2013-06-30
dc.description.abstractThis paper presents an integrated approach, targeting the comprehensive assessment of combined helicopter–engine designs, within designated operations. The developed methodology comprises a series of individual modeling theories, each applicable to a different aspect of helicopter flight dynamics and performance. These relate to rotor blade modal analysis, three-dimensional flight path definition, flight dynamics trim solution, aeroelasticity and engine performance. The individual mathematical models are elaborately integrated within a numerical procedure, solving for the total mission fuel consumption. The overall simulation framework is applied to the performance analysis of the Aérospatiale SA330 helicopter within two generic, twin-engine medium helicopter missions. An extensive comparison with flight test data on main rotor trim controls, power requirements and unsteady blade structural loads is presented. It is shown that, for the typical range of operating conditions encountered by modern twin-engine medium civil helicopters, the effect of operational altitude on fuel consumption is predominantly influenced by the corresponding effects induced on the engine, rather than on airframe–rotor performance. The implications associated with the implicit coupling between aircraft and engine performance, are discussed in the context of mission analysis. The potential to comprehensively evaluate integrated helicopter–engine systems within complete three-dimensional operations, using modeling fidelity designated for main rotor design applications, is demonstrated. The proposed method essentially constitutes an enabler in terms of focusing the rotorcraft design process on designated operation types, rather than on specific sets of flight conditions.en_UK
dc.identifier.citationIoannis Goulos, Panos Giannakakis, Vassilios Pachidis and Pericles Pilidis, Mission performance simulation of integrated helicopter–engine systems using an aeroelastic rotor model. ASME Turbo Expo 2013: Turbine Technical Conference and Exposition, 3-7 June 2013, San Antonio, Texas, USA. Paper No. GT2013-94798en_UK
dc.identifier.isbn978-0-7918-5513-3
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/12242
dc.language.isoenen_UK
dc.publisherASMEen_UK
dc.rights©2013 ASME. This is the Author Accepted Manuscript. Please refer to any applicable publisher terms of use.
dc.titleMission performance simulation of integrated helicopter–engine systems using an aeroelastic rotor modelen_UK
dc.typeConference paperen_UK

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