Numerička analiza čvrstoće drvene i kompozitne konstrukcije krila malog aviona

Radošević, Ivan (2018) Numerička analiza čvrstoće drvene i kompozitne konstrukcije krila malog aviona. = Numerical Strength Analysis of a Wooden and a Composite Wing Structure. Master's thesis (Bologna) , Sveučilište u Zagrebu, Fakultet strojarstva i brodogradnje, UNSPECIFIED. Mentor: Ivančević, Darko.

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Abstract (Croatian)

Cilj ovog diplomskog rada je usporedba svojstava drvene i kompozitne konstrukcije krila malog aviona najveće poletne mase do 450 kg. Konstrukcija krila je preuzeta iz besplatnih nacrta za ultralaki avion drvene konstrukcije Chilton DW-1, namijenjen za samogradnju. Prema tehničkoj dokumentaciji izrađen je CAD model krila u programu Solidworks, pri čemu su uvedena pojednostavnjenja i prilagodbe na geometriji u cilju bolje diskretizacije numeričkog modela. Potom je na temelju prvotnog modela izrađen izmijenjeni model krila kojem je dio drvenih komponenata zamijenjen kompozitima. U programu Abaqus/Standard provedena je statička numerička analiza obiju konstrukcija. Iznosi faktora normalnog opterećenja preuzeti su iz karakterističnih točaka V-n dijagrama prema EASA-inim normama. Raspodjela aerodinamičkog opterećenja modelirana je prema podacima dobivenim analizom u programu XFLR5. Na modelu kompozitne konstrukcije krila je zatim provedeno dimenzioniranje komponenata prema Hashinovom kriteriju popuštanja do postizanja željene čvrstoće, nakon čega je uspoređena ukupna masa drvene i kompozitne konstrukcije krila.

Abstract

The aim of this thesis is to make an FEM model of an existing wooden wing design for an aircraft with a MTOW of less than 450kg, and to compare its mechanical properties to those of an equivalent composite wing design. The wooden wing of a Chilton DW.1, a light racing aircraft designed for homebuilding, has been used as a basis for the CAD wing model. The model was designed using Solidworks, with many details simplified to facilitate mesh discretization with a minimum of distorted elements. A second wing model was then designed by replacing the main load-bearing members of the first model with equivalent members made of carbon fibre-epoxy composites. Both models were imported into Abaqus/Standard to perform static FEM analyses. The load factors used in the analysis were obtained from EASA regulations. The wing lift distribution was modeled according to results obtained by a flow analysis performed using XFLR5. The composite components were then sized according to Hashin failure criteria, with the aim to withstand the assigned loads with no damage initiation occurring.

Item Type: Thesis (Master's thesis (Bologna))
Uncontrolled Keywords: konstrukcija krila; ultralaki avion; metoda konačnih elemenata; drvena konstrukcija; kompozit
Keywords (Croatian): wing; finite element method; wooden structure; composites
Subjects: TECHNICAL SCIENCE > Aviation, rocket and space technology
Divisions: 1300 Department of Aeronautical Engineering > 1310 Chair of Aerodynamics
Date Deposited: 17 Jul 2018 11:33
Last Modified: 23 Jul 2018 11:29
URI: http://repozitorij.fsb.hr/id/eprint/8680

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