DC ElementWertSprache
dc.contributor.authorNeuheuser, Tom-
dc.contributor.authorCarl, Udo B.-
dc.date.accessioned2006-03-17T13:57:25Zde_DE
dc.date.available2006-03-17T13:57:25Zde_DE
dc.date.issued2004de_DE
dc.identifier.urihttp://tubdok.tub.tuhh.de/handle/11420/212-
dc.description.abstractNowadays helicopter flight control in the most common configurations is realized by collective and cyclic variation of the angle of attack of each rotor blade. The collective blade control pitches the rotor blades to equal angles of attack around their longitudinal axis, changing the rotor thrust at constant rotor speed. Yaw and roll control is realized via cyclic blade motion by changing the angle of attack of every rotor blade locally and periodically during one revolution. Although fly-by-wire and fly-by-light technologies slowly have found entry into helicopter flight control systems in the last years, complex mechanical systems are state-of-the-art to transfer all required control signals and forces from the fuselage into the rotating main rotor system. By Individual Blade Control (IBC) in higher harmonic modes and with additional actuators in the rotating system, fuselage vibrationsand radiated noise can be reduced and as well other IBC effects. This technology is subject of intensive research work. The intention of the research project INHUS ("Innovative Steuerungskonzepte für Hubschrauber") is the identification of a combined actuation system for primary flight control and IBC, which corresponds to the essential requirements of light weight, low control power consumption and high reliability. Therefore, a wide variety of technologies will be evaluated in terms of aforementioned requirements, uneffected by known flight control implementations in helicopters. The content of this paper is the comparison of the required power of different hydraulic and electric actuation systems, designed on the basis of specification data of a 20 tons.helicopter during several steady flight conditions.en
dc.language.isoende_DE
dc.rightsinfo:eu-repo/semantics/openAccess-
dc.subjectelectric controlde_DE
dc.subjectdiplacement controlde_DE
dc.subjecthelicopterde_DE
dc.subjectvalve controlde_DE
dc.subjecthelicopter flight control actuation systemde_DE
dc.titleAssessment of power consumption of helicopter flight control systems without swashplatede_DE
dc.typeinProceedingsde_DE
dc.date.updated2006-03-17T13:57:27Zde_DE
dc.identifier.urnurn:nbn:de:gbv:830-opus-2750de_DE
dc.identifier.doi10.15480/882.210-
dc.type.dinicontributionToPeriodical-
dc.subject.bcl55.50:Luftfahrzeugtechnikde
dc.subject.gndHubschrauberde
dc.subject.gndLuftfahrttechnikde
dc.subject.gndSteuerungde
dc.subject.bclcode55.50-
dc.subject.ddccode620-
dcterms.DCMITypeTextde_DE
tuhh.identifier.urnurn:nbn:de:gbv:830-opus-2750de_DE
tuhh.publikation.typconferenceObjectde_DE
tuhh.opus.id275de_DE
tuhh.oai.showtruede_DE
dc.identifier.hdl11420/212-
tuhh.abstract.englishNowadays helicopter flight control in the most common configurations is realized by collective and cyclic variation of the angle of attack of each rotor blade. The collective blade control pitches the rotor blades to equal angles of attack around their longitudinal axis, changing the rotor thrust at constant rotor speed. Yaw and roll control is realized via cyclic blade motion by changing the angle of attack of every rotor blade locally and periodically during one revolution. Although fly-by-wire and fly-by-light technologies slowly have found entry into helicopter flight control systems in the last years, complex mechanical systems are state-of-the-art to transfer all required control signals and forces from the fuselage into the rotating main rotor system. By Individual Blade Control (IBC) in higher harmonic modes and with additional actuators in the rotating system, fuselage vibrationsand radiated noise can be reduced and as well other IBC effects. This technology is subject of intensive research work. The intention of the research project INHUS ("Innovative Steuerungskonzepte für Hubschrauber") is the identification of a combined actuation system for primary flight control and IBC, which corresponds to the essential requirements of light weight, low control power consumption and high reliability. Therefore, a wide variety of technologies will be evaluated in terms of aforementioned requirements, uneffected by known flight control implementations in helicopters. The content of this paper is the comparison of the required power of different hydraulic and electric actuation systems, designed on the basis of specification data of a 20 tons.helicopter during several steady flight conditions.de_DE
tuhh.publication.instituteFlugzeug-Systemtechnik M-7de_DE
tuhh.identifier.doi10.15480/882.210-
tuhh.type.opusInProceedings (Aufsatz / Paper einer Konferenz etc.)de
tuhh.institute.germanFlugzeug-Systemtechnik M-7de
tuhh.institute.englishAircraft Systems Engineering M-7en
tuhh.institute.id20de_DE
tuhh.type.id16de_DE
tuhh.gvk.hasppnfalse-
dc.type.drivercontributionToPeriodical-
dc.identifier.oclc930768018-
dc.type.casraiConference Paperen
item.fulltextWith Fulltext-
item.creatorGNDNeuheuser, Tom-
item.creatorGNDCarl, Udo B.-
item.creatorOrcidNeuheuser, Tom-
item.creatorOrcidCarl, Udo B.-
item.grantfulltextopen-
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