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001428647 020__ $$a9783736965164
001428647 020__ $$z9783736975163
001428647 035__ $$a(MiAaPQ)EBC6805965
001428647 035__ $$a(Au-PeEL)EBL6805965
001428647 035__ $$a(OCoLC)1285783061
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001428647 050_4 $$aHD9711.A2 N399 2021
001428647 0820_ $$a338.4762913334
001428647 1001_ $$aNazzeri, Rahmetalla.
001428647 24510 $$aInfluence of flight control laws on structural sizing of commercial aircraft.
001428647 250__ $$a1st ed.
001428647 264_1 $$aGöttingen :$$bCuvillier Verlag,$$c2021.
001428647 264_4 $$c©2021.
001428647 300__ $$a1 online resource (181 pages).
001428647 336__ $$atext$$btxt$$2rdacontent
001428647 337__ $$acomputer$$bc$$2rdamedia
001428647 338__ $$aonline resource$$bcr$$2rdacarrier
001428647 5050_ $$aIntro -- List of Figures -- List of Tables -- List of symbols -- 1 Introduction -- 1.1 The need for a new simulation framework -- 1.2 State of the art -- 1.3 Objectives and thesis overview -- 2 Multidisciplinary analysis andoptimization framework -- 2.1 Developed process and mixture of competences -- 2.2 General process overview -- 3 Loads calculation process -- 3.1 Scope of computed load conditions -- 3.2 Loads calculation model -- 3.3 Electronic Flight Control System -- 4 Structural property optimization andmass penalty estimation -- 4.1 Modeling aspects of global FEM representation -- 4.2 Global FEM external loading -- 4.3 Linear static analysis and results management -- 4.4 Wing structural property optimization -- 4.5 Fuselage mass penalty estimation -- 5 Feedback loop -- 5.1 Starting approach -- 5.2 Main process steps of the feedback loop -- 5.3 Update of stiffness values - equivalent beamapproach -- 5.4 Update of mass values - grid point weight generator -- 5.5 Global convergence criteria -- 5.6 Impact of wing stiffness changes on the jig and flightshape -- 6 Design studies -- 6.1 Influence of the load alleviation function on thecalculated flight loads -- 6.2 First design study with reduced load case set -- 6.3 Design study with complete load case set -- 7 Summary, discussion of methods andresults, outlook -- 7.1 Summary -- 7.2 Discussion of methods -- 7.3 Discussion of results -- 7.4 Outlook -- Bibliography -- A Loads calculation and structuralassessment -- B Feedback loop - main process steps -- C Equivalent beam approach -validation -- D Equivalent beam approach -influence of skin and stringer -- E Grid Point Weight Generator - basics -- F Influence of the load alleviationfunction on the calculated flightloads -- G Structural baseline generation -- H Influence of load alleviation functionon structural components.
001428647 506__ $$aAccess limited to authorized users.
001428647 588__ $$aDescription based on publisher supplied metadata and other sources.
001428647 650_0 $$aAircraft industry.
001428647 655_0 $$aElectronic books
001428647 77608 $$iPrint version:$$aNazzeri, Rahmetalla$$tInfluence of flight control laws on structural sizing of commercial aircraft$$dGöttingen : Cuvillier Verlag,c2021$$z9783736975163
001428647 852__ $$bebk
001428647 85640 $$3ProQuest Ebook Central Academic Complete $$uhttps://univsouthin.idm.oclc.org/login?url=https://ebookcentral.proquest.com/lib/usiricelib-ebooks/detail.action?docID=6805965$$zOnline Access
001428647 909CO $$ooai:library.usi.edu:1428647$$pGLOBAL_SET
001428647 980__ $$aBIB
001428647 980__ $$aEBOOK
001428647 982__ $$aEbook
001428647 983__ $$aOnline