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Influence of flight control laws on structural sizing of commercial aircraft / / Rahmetalla Nazzeri
| Influence of flight control laws on structural sizing of commercial aircraft / / Rahmetalla Nazzeri |
| Autore | Nazzeri Rahmetalla |
| Edizione | [1st ed.] |
| Pubbl/distr/stampa | Göttingen : , : Cuvillier Verlag, , [2021] |
| Descrizione fisica | 1 online resource (181 pages) |
| Disciplina | 338.4762913334 |
| Soggetto topico | Aircraft industry |
| ISBN |
9783736965164
9783736975163 |
| Formato | Materiale a stampa  |
| Livello bibliografico | Monografia |
| Lingua di pubblicazione | eng |
| Nota di contenuto | 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 -- 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. |
| Record Nr. | UNINA-9910795349903321 |
Nazzeri Rahmetalla
|
||
| Göttingen : , : Cuvillier Verlag, , [2021] | ||
| Materiale a stampa | ||
| Lo trovi qui: Univ. Federico II | ||
| ||
Influence of flight control laws on structural sizing of commercial aircraft / / Rahmetalla Nazzeri
| Influence of flight control laws on structural sizing of commercial aircraft / / Rahmetalla Nazzeri |
| Autore | Nazzeri Rahmetalla |
| Edizione | [1st ed.] |
| Pubbl/distr/stampa | Göttingen : , : Cuvillier Verlag, , [2021] |
| Descrizione fisica | 1 online resource (181 pages) |
| Disciplina | 338.4762913334 |
| Soggetto topico | Aircraft industry |
| ISBN |
9783736965164
9783736975163 |
| Formato | Materiale a stampa |
| Livello bibliografico | Monografia |
| Lingua di pubblicazione | eng |
| Nota di contenuto | 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 -- 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. |
| Record Nr. | UNINA-9910815970503321 |
|
Nazzeri Rahmetalla
|
||
| Göttingen : , : Cuvillier Verlag, , [2021] | ||
| Materiale a stampa | ||
| Lo trovi qui: Univ. Federico II | ||
| ||