Wyniki wyszukiwania - BazTech

1

Study on Possible Replacement of the Aluminum Spar with a Composite Structure Illustrated with the Case of Agricultural Aircraft

Fałek M., Szymczyk E., Jachimowicz J.

Fatigue of Aircraft Structures

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2017

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Iss. 9

85--99

EN

Composite materials are increasingly being used in aviation. Specific stiffness and strength of composite materials (especially CFRP laminate, sandwich structure) are higher compared to metal alloys. They are beneficial features of materials used in aviation. Mass reduction of aircraft structures (e.g. due to the use of composite materials) contributes to an aircraft’s better performance in terms of its range, top speed and ceiling and consequently causes an increase in airplanes capacity. Moreover, the use of high-strength and lightweight materials in aviation contributes to longer life time and lower exploitation costs. The aim of the paper was the study the possibilities of replacing the aluminum spar of an airplane wing with a composite structure. In order to compare the mass and strength of the aluminum with the composite spar, the global shell and local solid models were created and finite elements analysis was performed. The analysis was carried out for the front spar of the wing of the agricultural aircraft PZL-106.

2

Analiza połączenia nitowego fragmentu skrzydła samolotu przy wykorzystaniu systemów CAD i MES

Jachimowicz J., Kajka R., Kaniowski J.

Systems : journal of transdisciplinary systems science

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2002

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Vol. 7, No. 1 sp.

264-272

PL

W pracy przedstawiono analizę MES połączenia nitowego fragmentu skrzydła samolotu PZL 1-22 IRYDA. Podjęto próbę zamodelowania połączenia nitowego na podstawie próbki węzła konstrukcyjnego B. Przeanalizowano szereg modeli MES o różnym stopniu skomplikowania. Symulowano stany sprężyste, sprężysto-plastyczne oraz zagadnienia kontaktowe.

EN

A numerical simulation of rivet joint of airplane wing was shown. Analysis was shown using fragment of 1-22 Iryda airplane wing. Many different types of FEM models were analyzed.

3

The modeling of an airplane's wing panel stringer being in a deformed state

Dzvonkovskaya A.L., Gromov V.F., Komarov Y.Y., Puntus A.A.

Zeszyty Naukowe Politechniki Rzeszowskiej. Mechanika

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2000

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z. 54 [179]

21-26

4

Rozwój pęknięcia zmęczeniowego w pokryciu skrzydła

Dorn E., Dymitruk J., Kaniowski J.

Zeszyty Naukowe Politechniki Świętokrzyskiej. Mechanika

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1999

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Z. 68, t. 1

91--96

PL

W pracy przedstawiono opis konstrukcji skrzydła samolotu oraz przebieg pęknięcia, jakie wystąpiło w próbie zmęczeniowej. Wskazano miejsca inicjacji pęknięć i przyczyny ich wystąpienia. Zasygnalizowano zamiar podjęcia próby analitycznego oszacowania rozwoju pęknięć w pokryciu skrzydła.

EN

Paper presents the full-scale fatigue tests of the jet trainer wing. The processes of destruction of the wing skin on its bottom panel, which includes the wing spars and stringers, were investigated. Imposing test which collects successive 8090 flight missions the first crack of the skin (which affected also rear wing spar and stringers) was detected. The fractographic analyses confirmed the fatigue origin of the crack The cracking proces has been initiated at holes of unfitted screws made for attaching the fuel drain valve to the skin. During further procedure the rear spars and two stringers have cracked. It seems that the crack initiation observed in this test becomes typical for airplane wings.