Wyniki wyszukiwania - BazTech

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O pewnym zastosowaniu odwzorowań konforemnych w lotnictwie

Bogowski F., Burniak C.

Zeszyty Naukowe / Wyższa Szkoła Oficerska Sił Powietrznych

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2011

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Nr 2

170--182

PL

W artykule autorzy omawiają podstawowe zasady odwzorowań konforemnych oraz przykład ich zastosowania w lotnictwie. Opisana jest metoda otrzymywania profilów skrzydeł samolotu.

EN

This articles discusses basic principles of conformal mapping and an example of their practical implementation. It describes the method of obtaining airplane wing profiles.

2

Symulacja numeryczna wpływu zmiany geometrycznych cech konstrukcyjnych na własności zmęczeniowe skrzydła samolotu

Kaniowski J., Szot A., Wieczorek M., Nowak J.

Zeszyty Naukowe Politechniki Świętokrzyskiej. Mechanika

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2001

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Z. 73

359-366

PL

W pracy przedstawiono symulację numeryczną wpływu zmiany geometrycznych cech konstrukcyjnych na własności zmęczeniowe fragmentu dolnego poszycia skrzydła samolotu I-22 IRYDA. Obliczenia wykonano dla czterech wariantów rozwiązań konstrukcyjnych przy wykorzystaniu metody elementów skończonych. Przy wyznaczaniu trwałości zmęczeniowej zastosowano metodę inicjacji pęknięcia.

EN

The influence of geometry modification of the Iryda aeroplane wing on the stress state and the fatigue life was analysed. Four dimensional discrete models was aplied in calculations with using the finite element method. The crack initiation method was used in numerical calculations of fatigue strength.

3

Modelling of aerodynamic forces on flapping wings - questions and results

Pietrucha J., Sibilski K., Złocka M.

Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics

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2001

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nr 12

45-52

EN

Nowadays, there can be observed a need to understand the mechanisms offeree generation by flapping wings in a more comprehensive way. The paper offers a summary, based on the-state-of-the-art in aerospace engineering and biological literature. The main purpose of the paper is to integrate both of them in the hope of constructing a more synthetic view of force generation in a flapping flight.

4

Structural weight estimation of a flying wing with a pressurized wing box

Rodriquez C., Martinez-Val R., Gutierrez L.

Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics

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2000

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nr 10

177-182

EN

The present paper will introduce a prediction method that will allow for estimation of the structural weight of a transport flying with an approximate capacity of 300 passengers. The flying wing payload will be located between the front and rear spars, and up to half the span approximately, which implies that the study of the wing structure will have two different parts; i.e., the external structure that will be of conventional architecture apart from its dimensions that will be bigger and the internal structure, no conventional, where the torsion box will be pressurized and with all the equipment required for passenger and, cargo transportation.

5

FEM model of composite wing versus experimental measurement

Juracka J.

Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics

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2000

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nr 10

139-144

EN

Co-operation with the company Urban Air has enabled me to compare two approaches the real wing structure testing with the FEM modelling. The deflection and strains measured by the strain gauges installed on the real construction during manufacture were compared to the results of FEM analysis. The FEM model of the wing structure was prepared using the MSC Patran. Models of spars root and tip ribs and skin were generated. At the beginning, approximate properties taken from the literature were used. Response of the structure was determining by the MSC Nastran solving a linear static task. Since differences between the FEM results and measurement were bigger than expected, more accurate values of parameters were determined by experiments and with those new of material properties the task was solved again. The measured wing structure deflection and most of the strain values were very similar to the FEM results. Same strains showed the critical areas on the wing structure. The results and their comparison allow for using the FEM model as an adequate method for stress analysis of composite structures produced using a wet lay-up method.