Direction control system for unmanned aircraft with flying wing configuration

Za bespilotnu letjelicu konfiguracije letećeg krila napravljen je linearni model gibanja te su na temelju linearnog bočnog modela modelirani sustavi stabilizacije i sustav upravljanja smjerom leta. Na temelju poznate geometrije je izraden 3D model letjelice u programskom paketu Solidworks iz kojeg su dobiveni podaci o masi, položaju centra težišta i momentima inercije potrebnim za izradu linearnih modela. Potpuni aerodinamički model letjelice je dobiven metodom projektne aerodinamike, a uspoređen je sa rezultatima dobivenim iz modela u programskom paketu XFLR5. Analizirane su specifičnosti upravljanja konfiguracijom letećeg krila zato sto letjelica ima samo dva elevona kojima treba ostvariti sve promjene stava te su uvedeni virtualni otkloni. Za potpuni linearni model bilo je potrebno analizirati utjecaj pogona na aerodinamičke karakteristike letjelice. Na temelju linearnih modela uzdužnog i bočnog gibanja izvršena je analiza uzdužne i bočne dinamičke stabilnosti te je zaključeno da letjelica nije bočno dinamički stabilna. Da bi se letjelica učinila bočno dinamički stabilnom, no i zbog poboljšanja dinamičkih karakteristika, uvedeni su sustavi stabilizacije po kutnim brzinama valjanja i skretanja te po kutu valjanja. Modeliran je i analiziran sustav upravljanja smjerom leta.Linear models were derived for a flying wing aircraft and stability augmentation systems and direction control system were modeled based on lateral linear model. In the beginning, 3D model in Solidworks has been made based on known geometry of the aircraft. Model in Solidworks gave essential data about aircraft mass, center of gravity and moments of inertia. The complete linear aerodynamic model of the aircraft has been made using handbook aerodynamic methods and it was compared with the results of the model of the aircraft made in XFLR5. Analysis of specifics of manouvering with flying wing aircraft has been made and virtual deflections were introduced. For a complete linear model, analysis of propulsion system influence on aerodynamic characteristics had to be done. Analysis of longitudinal and lateral dynamic stability has been performed based on known linear models of the aircraft. Conclusion was that aircraft is not laterally dynamically stable, so stability augmentation systems were introduced with the aim of making aircraft dynamically stable and to improve dynamic characteristics of the aircraft. Direction control system has been modeled and analyzed