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|a 3736965168
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|a 338.4762913334
|2 23
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| 049 |
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|a UAMI
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| 100 |
1 |
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|a Nazzeri, Rahmetalla.
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| 245 |
1 |
0 |
|a Influence of flight control laws on structural sizing of commercial aircraft
|h [electronic resource].
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| 260 |
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|a Göttingen :
|b Cuvillier Verlag,
|c 2021.
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| 300 |
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|a 1 online resource (181 p.)
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| 500 |
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|a Description based upon print version of record.
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0 |
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|a Intro -- 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
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| 505 |
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|a 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
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| 505 |
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|a 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
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| 505 |
8 |
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|a G Structural baseline generation -- H Influence of load alleviation functionon structural components
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| 590 |
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|a ProQuest Ebook Central
|b Ebook Central Academic Complete
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| 650 |
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0 |
|a Aircraft industry.
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| 650 |
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6 |
|a Industrie aéronautique.
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| 650 |
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7 |
|a Aircraft industry
|2 fast
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| 758 |
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|i has work:
|a Influence of flight control laws on structural sizing of commercial aircraft (Text)
|1 https://id.oclc.org/worldcat/entity/E39PCXhppkmfk964gd4q8rWrqP
|4 https://id.oclc.org/worldcat/ontology/hasWork
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| 776 |
0 |
8 |
|i Print version:
|a Nazzeri, Rahmetalla
|t Influence of flight control laws on structural sizing of commercial aircraft
|d Göttingen : Cuvillier Verlag,c2021
|z 9783736975163
|
| 856 |
4 |
0 |
|u https://ebookcentral.uam.elogim.com/lib/uam-ebooks/detail.action?docID=6805965
|z Texto completo
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|a ProQuest Ebook Central
|b EBLB
|n EBL6805965
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|a YBP Library Services
|b YANK
|n 302585004
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|b EBSC
|n 3100193
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|b IZTAP
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