Ztráta stability a porucha kompozitní stojiny

Buckling and Failure of Composite Web

článek v časopise - ostatní, Jost

en

The paper describes the strength analysis of composite structures of aircraft wings by FEM and its experimental verification. Modelling and experimental work were done at a wing of all-composite UL aircrafts UFM-10 Samba and TL-2000 Carbon Sting. The first part of the paper demonstrates the creation of the individual structure models of both wings and their analysis followed by the description of a real wing test. The paper compares the computational outputs with the results obtained by experimental measuring done during the tests. The conclusions show the correspondence of the experimental results with the FEM analysis.

V uvedený příspěvek předkládá výsledky MKP analýz kompozitních křídel a srovnává je s výsledky experimentálního ověření pevnosti na Zkušebně letecké techniky VUT v Brně. Jedná se dvě konstrukce, první patří letounu UFM-10 Samba s rozpětím 11 m, což se blíží konstrukcím s vysokou štíhlostí křídel charakterizující kluzáky (konstrukce A) a druhá konstrukce křídla letounu TL – 2000 Sting Carbon s rozpětím 8 m spíše odpovídá konstrukci standardního letounu (konstrukcí B)

The paper describes the strength analysis of composite structures of aircraft wings by FEM and its experimental verification. Modelling and experimental work were done at a wing of all-composite UL aircrafts UFM-10 Samba and TL-2000 Carbon Sting. The first part of the paper demonstrates the creation of the individual structure models of both wings and their analysis followed by the description of a real wing test. The paper compares the computational outputs with the results obtained by experimental measuring done during the tests. The conclusions show the correspondence of the experimental results with the FEM analysis.

FEM, modelling, composite structure, composites, wing

01.01.2003

Vilnius

1648-7788

AVIATION

VII

1

36–39

4