LEADER 03275nam 2200421 450 001 9910815970503321 005 20230630001411.0 010 $a9783736965164$b(electronic bk.) 010 $z9783736975163 035 $a(MiAaPQ)EBC6805965 035 $a(Au-PeEL)EBL6805965 035 $a(OCoLC)1285783061 035 $a(CKB)19434192500041 035 $a(EXLCZ)9919434192500041 100 $a20220811d2021 uy 0 101 0 $aeng 135 $aurcnu|||||||| 181 $ctxt$2rdacontent 182 $cc$2rdamedia 183 $acr$2rdacarrier 200 10$aInfluence of flight control laws on structural sizing of commercial aircraft /$fRahmetalla Nazzeri 205 $a1st ed. 210 1$aGo?ttingen :$cCuvillier Verlag,$d[2021] 210 4$dİ2021 215 $a1 online resource (181 pages) 311 08$aPrint version: Nazzeri, Rahmetalla Influence of flight control laws on structural sizing of commercial aircraft Göttingen : Cuvillier Verlag,c2021 9783736975163 320 $aIncludes bibliographical references. 327 $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. 606 $aAircraft industry 615 0$aAircraft industry. 676 $a338.4762913334 700 $aNazzeri$b Rahmetalla$01644330 801 0$bMiAaPQ 801 1$bMiAaPQ 801 2$bMiAaPQ 912 $a9910815970503321 996 $aInfluence of flight control laws on structural sizing of commercial aircraft$93990139 997 $aUNINA