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dc.contributor.advisorWood, E. Roberts
dc.contributor.advisorTischler, Mark B.
dc.contributor.authorTyson, Peter H.
dc.dateMarch, 1999
dc.date.accessioned2012-09-07T15:35:15Z
dc.date.available2012-09-07T15:35:15Z
dc.date.issued1999-03
dc.identifier.urihttp://hdl.handle.net/10945/13648
dc.description.abstractHelicopter/slung load systems are two body systems in which the slung load adds its rigid body dynamics, aerodynamics, and sling stretching dynamics to the helicopter. The slung load can degrade helicopter handling qualities and reduce the flight envelope of the helicopter. Confirmation of system stability parameters and envelope is desired, but flight test evaluation is time consuming and costly. A simulation model validated for handling quality assessments would significantly reduce resources expended in flight testing while increasing efficiency, productivity, and safety by aiding researchers, designers, and pilots to understand factors affecting helicopter-slung load handling qualities. This thesis describes a comprehensive dynamics and aerodynamics model for slung load simulation, obtained by integrating the NASA Ames Gen Hel UH-60A simulation with slung load equations of motion. Frequency domain analysis is used to compare simulation to flight test frequency responses and key system stability parameters. Results are given for no load, a 4K lb Block, and a 4K lb CONEX load. Handling quality parameters, stability margins, and load pendulum motion roots for cases without load aerodynamics and with static wind tunnel data were compared. Results illustrated state-of-the-art simulation modeling of helicopter/slung load dynamics and its accuracy in predicting key dynamic parameters of interest.en_US
dc.description.urihttp://archive.org/details/simulationvalida1094513648
dc.format.extentxviii, 284 p.;28 cm.en_US
dc.language.isoen_US
dc.publisherMonterey, California: Naval Postgraduate Schoolen_US
dc.titleSimulation validation and flight prediction of UH-60A Black Hawk helicopter/slung load characteristicsen_US
dc.typeThesisen_US
dc.description.serviceU.S. Navy (U.S.N.) author.en_US
etd.thesisdegree.nameM.S. in Aeronautical Engineeringen_US
etd.thesisdegree.levelMastersen_US
etd.thesisdegree.disciplineAeronautical Engineeringen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US
dc.description.distributionstatementApproved for public release; distribution is unlimited.


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