Stress analysis of the wing of non-standard morphology airplane

U ovom završnom radu izvršena je analiza čvrstoće nestandardne konfiguracije krila aviona te usporedba iste sa konvencionalnom konfiguracijom krila putničkog aviona srednjeg dometa. Prethodno je obavljen pregled literature, prikazani su koncepti novih pogona zrakoplova te trendovi u zrakoplovnim konstrukcijama. S obzirom na količinu dostupnih podataka te kompleksnosti konstrukcije, za analizu čvrstoće odabrana je Strut braced wing konfiguracija. Proračun započinje modeliranjem geometrije krila konvencionalnog zrakoplova, Airbus-a A320, u 3D programskom paketu Solidworks 2018. Krilo Strut braced wing koncepta konstruirano je tako da ostvaruje približno jednak iznos sile uzgona u režimu krstarenja kao i krilo Airbus-a A320 kako bi se mogla nanijeti ista opterećenja. To je izračunato jednostavnim aerodinamičkim proračunima u programu XFLR 5. Modeli napravljeni u Solidworks-u su spremljeni u STEP formatu i prebačeni u program Abaqus/Standard za analizu čvrstoće primjenom metode konačnih elemenata. Prvo su na oba modela nanesene aluminijske legure standardne u zrakoplovstvu, a nakon toga je konceptualna konfiguracija modelirana i sa kompozitnim materijalima. Sljedeći korak je zadavanje rubnih uvjeta i opterećenja u obliku konstantnog tlaka uslijed sile uzgona i težine motora. Zadnji korak prije samog proračuna je zadavanje mreže konačnih elemenata. Nakon više provedenih analiza te promjena debljina elemenata prikazani su rezultati u obliku ekvivaletnih naprezanja, Tsai-Wu kriterija popuštanja za kompozitne konstrukcije te su uspoređene mase analiziranih modela.In this Bachelor thesis, a structural analysis of the non-standard configuration of an aircraft wing and a comparison with the conventional wing of a medium-range passenger aircraft is performed. Previously, a review of the literature was done, where concepts of new aircraft propulsion and trends in aircraft construction were presented. Given the amount of data available and the complexity of the structures, Strut braced wing configuration was selected for analysis. The calculation begins by modeling the geometry of the wing of a conventional aircraft, the Airbus A320, in the 3D software package Solidworks 2018. The Strut braced wing is conceptually designed to achieve approximately the same lift force in cruising mode as the wing of the Airbus A320, so the same loads can be applied. These simple aerodynamic calculations were done in XFLR 5. Models made in Solidworks were then saved in STEP format and transferred to Abaqus/Standard for structural analysis with use of finite element method. Firstly, standard aluminum alloys were applied to both models, and then the conceptual configuration was modeled with composite materials as well. The next step is to assign boundary conditions and loads in the form of constant pressure due to lift force and engine weight. The last step before starting the calculation was creation of mesh. After several analyzes and changes in the thickness of the elements, the results in the form of equivalent stresses, Tsai-Wu yielding criteria for composite construction and masses of the analyzed models are presented