Validation of Structure of the Solar Unmanned Vehicle

Zadatak ovog završnog rada je dimenzioniranje osnovnih konstruktivnih elemenata krila male bespilotne letjelice na solarni pogon uz opterećenje definirano V-n dijagramom. U radu je korišten program za numeričku analizu metodom konačnih elemenata Abaqus/Standrad. U prvom poglavlju se opisuju rezultati prethodne konceptualne razrade [1] bespilotne letjelice na solarni pogon koji su korišteni kao osnova za analizu čvrstoće u ovom radu. Drugo poglavlje opisuje materijal, geometriju i dimenzije polukrila. Detaljnije su opisane solarne ćelije koje su sastavni dio letjelice. Opisan je njihov način rada te njihove karakteristike. Treće poglavlje opisuje aerodinamičku analizu profila i krila u programu XFLR5. Također je napravljen i V-n dijagram koji je podloga u analizi čvrstoće konstrukcije krila. Četvrto poglavlje sadrži analizu čvrstoće konstrukcije krila u programu Abaqus/Standard. Opisani su koraci tijekom izrade modela krila, navedeni su elementi konstrukcije krila, te opis korištenih kriterija popuštanja kompozitnih materijala. Postupak izračuna opterećenja je također opisan. U petom poglavlju navedeni su dobiveni rezultati, a u šestom slijedi Zaključak gdje je cijeli rad ukratko izložen.The aim of this bachelor's thesis work is sizing of the basic structural elements of the wing structure of a small unmanned aircraft powered by solar energy with loads defined in the V-n diagram. The structural strength of the wing was analyzed using Abaqus/Standard. The results of the conceptual design of a solar-powered unmanned aircraft, which was used as a starting point for the structural analysis in this thesis, are presented in the Introduction. In the second chapter the material, geometry and dimensions of the wing structure are described. The work principle and characteristics of solar cells as an important component of the aircraft are described in more detail. In the third chapter an aerodynamic analysis of the wing's profile is presented using program XFLR5. The V-n diagram, which was used for the structural analysis in this work is also described in this chapter. The fourth chapter describes the structural analysis of the wing in the finite element software Abaqus/Standard. The steps for the definition of the numerical model are described in this Chapter. These include the description of the wing structural elements and also the failure criteria applied in the analysis of the composite materials in this work. The process for the definition of the load is also described. The results are presented in the fifth chapter while the Conclusion in which the whole process is recapitulated is the final chapter of this work