000 | 03200cam a2200385Mi 4500 | ||
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001 | on1285783061 | ||
003 | OCoLC | ||
005 | 20240726104845.0 | ||
008 | 211120s2021 gw o ||| 0 eng d | ||
040 |
_aEBLCP _beng _erda _cEBLCP _dYDX _dSFB _dOCLCQ _dOCLCF _dNT |
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020 | _a3736965168 | ||
020 |
_a9783736965164 _q((electronic)l(electronic)ctronic) |
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050 | 0 | 4 |
_aHD9711 _b.I545 2021 |
049 | _aMAIN | ||
100 | 1 |
_aNazzeri, Rahmetalla. _e1 |
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245 | 1 | 0 | _aInfluence of flight control laws on structural sizing of commercial aircraft |
300 | _a1 online resource (181 pages) | ||
336 |
_atext _btxt _2rdacontent |
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337 |
_acomputer _bc _2rdamedia |
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338 |
_aonline resource _bcr _2rdacarrier |
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347 |
_adata file _2rda |
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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 |
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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 |
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994 |
_a92 _bNT |
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999 |
_c80694 _d80694 |
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902 |
_a1 _bCynthia Snell _c1 _dCynthia Snell |