Wszystkie pola: aircraft structure optimization - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Optimization of wing parameters to achieve minimum weight at defined aerodynamic loads
Optymalizacja parametrów skrzydła minimalnej masy z uwzględnieniem ograniczeń do obciążeń aerodynamicznych
Autorzy:: Kachel, S.
Powiązania:: https://bibliotekanauki.pl/articles/280972.pdf
Data publikacji:: 2013
Wydawca:: Polskie Towarzystwo Mechaniki Teoretycznej i Stosowanej
Tematy:: aircraft structure optimization
parametrical design systems
Opis:: The paper presents the method suitable for optimization of parameters and applied to design aircraft subassemblies on the example of a swept wing. It outlines the assumptions that are necessary to develop a mathematical model and describes constraints that served as the basis to develop an algorithm and describe the corresponding procedures in the GRIP (Graphics Interactive Programming) language that is a part of the CAD/CAM/CAE Unigraphics system. The further part of the study comprises discussion how the wing parameters and the mass functional are affected by the rigidity constraints and strength constraints. The algorithm for designing aircraft components was finally developed with inputs to the multicriteria design process “Web Modelling” of an aircraft body. The study also includes initial assumptions to algorithms originally developed by the author and dedicated to the modelling of components incorporated into aircraft structures.
W artykule zaprezentowano metodykę optymalizacji parametrów w zastosowaniu do projektowania zespołów samolotu na przykładzie skrzydła skośnego. Przedstawiono główne założenia niezbędne do opracowania matematycznego modelu. Opisano ograniczenia będące podstawą do utworzenia algorytmu i opisania procedur w języku GRIP (Graphics Interactive Programming) dla systemu CAD/CAM/CAE Unigraphics. Przeprowadzono dyskusję zmiany parametrów sztywnościowych i masy w zależności od ograniczenia obciążeniami aerodynamicznymi. Opracowano algorytm projektowania zespołów składowych samolotu z uwzględnieniem wejść do wielokryterialnego procesu projektowania Web Modelling bryły samolotu. W pracy zawarto założenia opracowanych przez autora i zastosowanych algorytmów modelowania elementów struktur lotniczych.
Źródło:: Journal of Theoretical and Applied Mechanics; 2013, 51, 1; 159-170
1429-2955
Pojawia się w:: Journal of Theoretical and Applied Mechanics
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: The multi - objective optimization of the air transportation fleet structure
Autorzy:: Majka, A.
Powiązania:: https://bibliotekanauki.pl/articles/246578.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: air transport
small aircraft
aircraft selection
Opis:: One of the most important factors in the development of modern civilization has become the increase in the significance of mobile and fast means of transportation of people and cargo. Aircraft as the fastest available means in the entire transportation system is the basis in places where the distance in the transportation of people is long and the travel time is short. The present work focuses on passenger transport in the European area using light transport aircraft, which may complement existing air transport and can become a real alternative to those who travel by other means of transport. The system of local transportation will become competitive in relation to other means of transport and will find its place on the market only when it has the highest indicators of efficiency. It can be reached by optimally obtaining passenger aircrafts fleet structure performing transportation tasks and optimizing its functioning. One of the basic problems is the rational selection and use of aircrafts, i.e. the minimization of their quantity while at the same time guarantee complete performance of transporting tasks. The selection of the best method of using the means of transport is connected with a large number of alternative variants, which makes it necessary to use special methods of searching for optimal solutions. The quality of the aircraft fleet should be estimated on the basis of several criteria when taking into account the difference in performing tasks. The way to design a competing aircraft fleet is to choose its characteristics by using advanced methods of multiple objective optimization. This work presents the methodology of the optimal designing of the aircraft fleet using the multitask character of the matter which is based on multiple objective mathematical programming in the concept of the set theory.
Źródło:: Journal of KONES; 2013, 20, 4; 261-268
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: New biomimetic approach to the aircraft wing structural design based on aeroelastic analysis
Autorzy:: Gawel, D.
Nowak, M.
Hausa, H.
Roszak, R.
Powiązania:: https://bibliotekanauki.pl/articles/199862.pdf
Data publikacji:: 2017
Wydawca:: Polska Akademia Nauk. Czytelnia Czasopism PAN
Tematy:: optimization
fluid-structure interaction
coupling techniques
biomimetics
optymalizacja
sprzęganie
biomimetyka
Opis:: This paper presents a new biomimetic approach to the structural design. For the purpose of aircraft wing design the numerical environment combining simultaneous structural size, shape, and topology optimization based on aeroelastic analysis was developed. For the design of aircraft elements the optimization process must be treated as a multi-load case task, because during the fluid structure interaction analysis each step represents a different structural load case. Also, considering different angles of attack, during the CFD computation each result is considered. The method-specific features (such as domain independence, functional configurations during the process of optimization, and multiple load case solution implemented in the optimization scenario) enable the optimal structural form. To illustrate the algorithm functionality, the problem of determining the optimal internal wing structure was presented. The optimal internal wing structure resulting from aeroelastic computation with different angles of attack has been presented.
Źródło:: Bulletin of the Polish Academy of Sciences. Technical Sciences; 2017, 65, 5; 741-750
0239-7528
Pojawia się w:: Bulletin of the Polish Academy of Sciences. Technical Sciences
Dostawca treści:: Biblioteka Nauki

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