Matches in SemOpenAlex for { <https://semopenalex.org/work/W3199672009> ?p ?o ?g. }
Showing items 1 to 86 of
86
with 100 items per page.
- W3199672009 endingPage "012006" @default.
- W3199672009 startingPage "012006" @default.
- W3199672009 abstract "The use of finite element analysis is increasingly gaining popularity in the design and analysis of aircraft structures. Also, composite materials in the manufacturing and design of aircraft structures are increasing due to their exceptional properties of high stiffness to weight ratio. Applications include Composite structures are made up of laminates with different fibre orientations, which adversely affects the property of the composites formed. For this study, the three main parts of the aircraft wing are considered for designing: the spars, the ribs, and the aircraft's skin. The spars and made up of aluminium alloy, and the ribs are made up of structural steel. Two different wing models are designed. For Model 1, the skin is assigned Titanium alloy as a material, and for Model 2, CFRP (Carbon Fibre Reinforced Polymer) with resin epoxy is used as the skin material. The ribs are made of structural steel and the spars of titanium alloy for both models. This paper aims to compare the materials mentioned above to find the optimum strength to weight ratio. It was found that, for a given uniform load on the bottom of the aircraft's skin, a weight reduction of 2.37 % was observed in favour of Model 2, the deformation was reduced by 51 per cent, and the von-Mises stress was reduced by ≈ 85%. This paper's results can be used in manufacturing structural components of UAV, especially the wings due to lighter weight and more flexibility and durability than standard titanium alloys and the significant role played by the orientation of the plies in deciding the strength of the composite." @default.
- W3199672009 created "2021-09-27" @default.
- W3199672009 creator A5022652060 @default.
- W3199672009 creator A5029765407 @default.
- W3199672009 creator A5030154214 @default.
- W3199672009 creator A5051550576 @default.
- W3199672009 creator A5091859361 @default.
- W3199672009 date "2021-09-01" @default.
- W3199672009 modified "2023-10-16" @default.
- W3199672009 title "Modelling and Finite Element Analysis of an Aircraft Wing using Composite Laminates" @default.
- W3199672009 cites W1984359065 @default.
- W3199672009 cites W2000647517 @default.
- W3199672009 cites W2061817389 @default.
- W3199672009 cites W2317574806 @default.
- W3199672009 cites W2624045800 @default.
- W3199672009 cites W2733727433 @default.
- W3199672009 cites W2735656556 @default.
- W3199672009 cites W2746394940 @default.
- W3199672009 cites W2760962840 @default.
- W3199672009 cites W2767480150 @default.
- W3199672009 cites W2805649080 @default.
- W3199672009 cites W2898384566 @default.
- W3199672009 cites W2905027441 @default.
- W3199672009 cites W2969363865 @default.
- W3199672009 cites W3010609636 @default.
- W3199672009 doi "https://doi.org/10.1088/1757-899x/1183/1/012006" @default.
- W3199672009 hasPublicationYear "2021" @default.
- W3199672009 type Work @default.
- W3199672009 sameAs 3199672009 @default.
- W3199672009 citedByCount "0" @default.
- W3199672009 crossrefType "journal-article" @default.
- W3199672009 hasAuthorship W3199672009A5022652060 @default.
- W3199672009 hasAuthorship W3199672009A5029765407 @default.
- W3199672009 hasAuthorship W3199672009A5030154214 @default.
- W3199672009 hasAuthorship W3199672009A5051550576 @default.
- W3199672009 hasAuthorship W3199672009A5091859361 @default.
- W3199672009 hasBestOaLocation W31996720091 @default.
- W3199672009 hasConcept C104779481 @default.
- W3199672009 hasConcept C127413603 @default.
- W3199672009 hasConcept C135628077 @default.
- W3199672009 hasConcept C155165730 @default.
- W3199672009 hasConcept C159985019 @default.
- W3199672009 hasConcept C166595027 @default.
- W3199672009 hasConcept C192562407 @default.
- W3199672009 hasConcept C204366326 @default.
- W3199672009 hasConcept C2779372316 @default.
- W3199672009 hasConcept C2780026712 @default.
- W3199672009 hasConcept C33759916 @default.
- W3199672009 hasConcept C66938386 @default.
- W3199672009 hasConcept C8953137 @default.
- W3199672009 hasConcept C97257150 @default.
- W3199672009 hasConceptScore W3199672009C104779481 @default.
- W3199672009 hasConceptScore W3199672009C127413603 @default.
- W3199672009 hasConceptScore W3199672009C135628077 @default.
- W3199672009 hasConceptScore W3199672009C155165730 @default.
- W3199672009 hasConceptScore W3199672009C159985019 @default.
- W3199672009 hasConceptScore W3199672009C166595027 @default.
- W3199672009 hasConceptScore W3199672009C192562407 @default.
- W3199672009 hasConceptScore W3199672009C204366326 @default.
- W3199672009 hasConceptScore W3199672009C2779372316 @default.
- W3199672009 hasConceptScore W3199672009C2780026712 @default.
- W3199672009 hasConceptScore W3199672009C33759916 @default.
- W3199672009 hasConceptScore W3199672009C66938386 @default.
- W3199672009 hasConceptScore W3199672009C8953137 @default.
- W3199672009 hasConceptScore W3199672009C97257150 @default.
- W3199672009 hasIssue "1" @default.
- W3199672009 hasLocation W31996720091 @default.
- W3199672009 hasOpenAccess W3199672009 @default.
- W3199672009 hasPrimaryLocation W31996720091 @default.
- W3199672009 hasRelatedWork W1995958177 @default.
- W3199672009 hasRelatedWork W2003266812 @default.
- W3199672009 hasRelatedWork W2029945387 @default.
- W3199672009 hasRelatedWork W2073593360 @default.
- W3199672009 hasRelatedWork W2117665458 @default.
- W3199672009 hasRelatedWork W2344923355 @default.
- W3199672009 hasRelatedWork W2363311282 @default.
- W3199672009 hasRelatedWork W2376820830 @default.
- W3199672009 hasRelatedWork W2593200884 @default.
- W3199672009 hasRelatedWork W3121051381 @default.
- W3199672009 hasVolume "1183" @default.
- W3199672009 isParatext "false" @default.
- W3199672009 isRetracted "false" @default.
- W3199672009 magId "3199672009" @default.
- W3199672009 workType "article" @default.