20.500.12556/RUL-172717 Numerična analiza kompozitnega letalskega krila Numerical analysis of a composite aircraft wing V delu je predstavljena statična mehanska numerična analiza kompozitnega krila radijsko vodenega modelarskega letala, izdelanega za tekmovanje Design/Build/Fly (DBF), v programskem okolju Ansys. Krilo je zasnovano kot sendvič konstrukcija iz ogljikovih in steklenih vlaken z epoksidno smolo. Med preizkusnimi leti smo s pospeškometrom izmerili obremenitve, ki delujejo na letalo med letom. Na podlagi teh meritev smo z Andersenovo metodo določili porazdelitev vzgona po razpetini krila, medtem ko je bila razporeditve vzgona po tetivi krila izračunana na osnovi izračunane porazdelitve koeficientov tlakov s programom XFOIL. Izračunane obremenitve smo prenesli v numerični model krila, kjer smo s statično analizo preučili napetosti in raztezke v krilu v posameznih segmentih. S pomočjo porušitvenih kriterijev za kompozitne materiale smo preverili, ali je prišlo do porušitve strukture. Izdelali smo tudi testno krilo in izvedli tritočkovni porušitveni test, s katerim smo preverili, ali bo prišlo do porušitve strukture. Izmerjene povese med testom smo primerjali z numerično izračunanimi povesi. Na koncu smo na podlagi nove numerične analize krila podali še priporočila za izdelavo izboljšanega krila. The thesis presents a static mechanical numerical analysis of a composite aircraft wing of a radio-controlled model aircraft, built for Design/Build/Fly (DBF) competition, using Ansys software environment. The wing is designed as a sandwich construction out of carbon fibre and fibreglass with epoxy resin. Telemetry data recording loads experienced by the aircraft was obtained using accelerometer during test flights. Based on the collected data, Anderson method was used to calculate lift distribution across wingspan. Lift distribution along chord line was obtained using XFOIL software environment where pressure distribution was calculated. Calculated lift was applied to a statical numerical model of the aircraft wing and displacement and stress in its segments were analysed. Structural integrity of the wing was checked using composite failure criteria. A test wing was constructed and a three point bending test of the test wing was performed to evaluate its strength. Measured displacements during the test were compared to numerically calculated displacements of a test wing at various loads. Finally, recommendations on building an improved aircraft wing were given based on another numerical analysis. letalska krila numerične analize sendvič strukture ogljikova vlakna steklena vlakna aircraft wings numerical analyses sandwich structures carbon fibre fibreglass true false false Slovenski jezik Angleški jezik Diplomsko delo/naloga 2025-09-11 08:31:35 2025-09-11 08:31:39 2025-10-20 03:42:46 0000-00-00 00:00:00 2025 0 0 XIII, 44 f. 2025 0000-00-00 NiDoloceno NiDoloceno NiDoloceno 0000-00-00 0000-00-00 0000-00-00 629.7.025.1:531.3:519.6(043.2) 275996 249284867 43933.pdf 43933.pdf 1 2CAB66E67A3A51C5CB14932696A4CA7C 20440423f36de50ab94f13a3a4da681aab1d3c676301fdaf81fec327df3214ce d04c0aec-8ed8-11f0-9328-0050569b8976 https://repozitorij.uni-lj.si/Dokument.php?lang=slv&id=216747 Fakulteta za strojništvo 0 0 0