000			03200cam a2200385Mi 4500
001			on1285783061
003			OCoLC
005			20240726104845.0
008			211120s2021 gw o ||| 0 eng d
040			_aEBLCP _beng _erda _cEBLCP _dYDX _dSFB _dOCLCQ _dOCLCF _dNT
020			_a3736965168
020			_a9783736965164 _q((electronic)l(electronic)ctronic)
050	0	4	_aHD9711 _b.I545 2021
049			_aMAIN
100	1		_aNazzeri, Rahmetalla. _e1
245	1	0	_aInfluence of flight control laws on structural sizing of commercial aircraft
300			_a1 online resource (181 pages)
336			_atext _btxt _2rdacontent
337			_acomputer _bc _2rdamedia
338			_aonline resource _bcr _2rdacarrier
347			_adata file _2rda
500			_aDescription based upon print version of record.
504			_a2
505	0	0	_aIntro -- _tList of Figures -- _tList of Tables -- _tList of symbols -- _t1 Introduction -- _t1.1 The need for a new simulation framework -- _t1.2 State of the art -- _t1.3 Objectives and thesis overview -- _t2 Multidisciplinary analysis andoptimization framework -- _t2.1 Developed process and mixture of competences -- _t2.2 General process overview -- _t3 Loads calculation process -- _t3.1 Scope of computed load conditions -- _t3.2 Loads calculation model -- _t3.3 Electronic Flight Control System -- _t4 Structural property optimization andmass penalty estimation -- _t4.1 Modeling aspects of global FEM representation
505	0	0	_a4.2 Global FEM external loading -- _t4.3 Linear static analysis and results management -- _t4.4 Wing structural property optimization -- _t4.5 Fuselage mass penalty estimation -- _t5 Feedback loop -- _t5.1 Starting approach -- _t5.2 Main process steps of the feedback loop -- _t5.3 Update of stiffness values -- _tequivalent beamapproach -- _t5.4 Update of mass values -- _tgrid point weight generator -- _t5.5 Global convergence criteria -- _t5.6 Impact of wing stiffness changes on the jig and flightshape -- _t6 Design studies -- _t6.1 Influence of the load alleviation function on thecalculated flight loads
505	0	0	_a6.2 First design study with reduced load case set -- _t6.3 Design study with complete load case set -- _t7 Summary, discussion of methods andresults, outlook -- _t7.1 Summary -- _t7.2 Discussion of methods -- _t7.3 Discussion of results -- _t7.4 Outlook -- _tBibliography -- _tA Loads calculation and structuralassessment -- _tB Feedback loop -- _tmain process steps -- _tC Equivalent beam approach -validation -- _tD Equivalent beam approach -influence of skin and stringer -- _tE Grid Point Weight Generator -- _tbasics -- _tF Influence of the load alleviationfunction on the calculated flightloads
505	0	0	_aG Structural baseline generation -- _tH Influence of load alleviation functionon structural components
530			_a2 _ub
650		0	_aAircraft industry.
655		1	_aElectronic Books.
856	4	0	_zClick to access digital title | log in using your CIU ID number and my.ciu.edu password. _uhttpss://search.ebscohost.com/login.aspx?direct=true&scope=site&db=nlebk&db=nlabk&AN=3100193&site=eds-live&custid=s3260518
942			_cOB _D _eEB _hHD. _m2021 _QOL _R _x _8NFIC _2LOC
994			_a92 _bNT
999			_c80694 _d80694
902			_a1 _bCynthia Snell _c1 _dCynthia Snell