Mehanska numerična analiza in izdelava kompozitnega letalskega krila

Štrukelj, Leon (author), Bergant, Zoran (mentor), Petrović, Igor (comentor)

V delu je predstavljena mehanska numerična analiza modelarskega krila za univerzitetno letalsko tekmovanje DBF (Design Build and Fly) izvedeno v programskem okolju Ansys s pomočjo Ansys Composite PrePost (ACP). Namen numerične analize je kontrolirati stanje napetosti in deformacij v kompozitnem letalskem krilu glede na zahtevane obremenitve. S panelno metodo smo s programom XFOIL preračunali osnovne karakteristike izbranega profila NACA 2412. Na osnovi porazdelitve tlaka na profilu smo preračunali obremenitve za izvedbo manevrov ekvivalenta gravitacijske sile 10 g. Preučili smo povese krila ter preverili porazdelitev napetosti in deformacij v posameznih vitalnih delih krila. Za preverjanje nosilnosti smo uporabili različne porušitvene kriterije za kompozitne materiale, kot so kriteriji maksimalne napetosti in deformacij ter Tsai-Wu. V zadnjem delu smo se posvetili še napakam načrtovanja in izdelave, morebitnim izboljšavam ter tehnologiji izdelave, s katero smo izdelali letalsko krilo.

• Language: Slovenian
• Keywords: numerična analiza, kompozitni materiali, analiza obremenitve letalskega krila, gradnja letalskega krila, natezni preizkus
• Work type: Bachelor thesis/paper
• Organization: FS - Faculty of Mechanical Engineering
• Year: 2024
• PID: 20.500.12556/RUL-160463
• Publication date in RUL: 29.08.2024

Secondary language

• Language: English
• Title: Mechanical numerical analysis and fabrication of a composite airfoil

Abstract

The thesis presents a mechanical numerical analysis of a model aircraft wing for the university aviation competition DBF (Design, Build and Fly) in the Ansys software environment using Ansys Composite PrePost (ACP). The purpose of the numerical analysis is to evaluate the state of stress and deformation in the composite aircraft wing under specified loads. Using the XFOIL program, we calculated the characteristics of the selected NACA 2412 airfoil. Based on the pressure distribution on the airfoil, we calculated the loads for performing maneuvers equivalent to a gravitational force of 10 G. We analyzed the wing deflections and evaluated the distribution of stress and deformation in the critical parts of the wing. Various failure criteria, such as the maximum stress, deformation criteria and Tsai-Wu, were applied to verify the load-bearing capacity. In the final section, we addressed design and manufacturing errors, possible improvements and the manufacturing technology employed to produce the aircraft wing.

• Keywords: numerical analysis, composite materials, airfoil load analysis, airfoil fabrication, tensile test