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master's thesis
Model leta bespilotne letjelice konfiguracije letećeg krila
Zagreb: University of Zagreb, Faculty of Mechanical Engineering and Naval Architecture, 2014. urn:nbn:hr:235:099098
Andrić, Marijan
University of Zagreb
Faculty of Mechanical Engineering and Naval Architecture

Institutional repository: Repository of Faculty of Mechanical Engineering and Naval Architecture University of Zagreb

Cite this document

Andrić, M. (2014). Model leta bespilotne letjelice konfiguracije letećeg krila (Master's thesis). Zagreb: University of Zagreb, Faculty of Mechanical Engineering and Naval Architecture. Retrieved from https://urn.nsk.hr/urn:nbn:hr:235:099098

Andrić, Marijan. "Model leta bespilotne letjelice konfiguracije letećeg krila." Master's thesis, University of Zagreb, Faculty of Mechanical Engineering and Naval Architecture, 2014. https://urn.nsk.hr/urn:nbn:hr:235:099098

Andrić, Marijan. "Model leta bespilotne letjelice konfiguracije letećeg krila." Master's thesis, University of Zagreb, Faculty of Mechanical Engineering and Naval Architecture, 2014. https://urn.nsk.hr/urn:nbn:hr:235:099098

Andrić, M. (2014). 'Model leta bespilotne letjelice konfiguracije letećeg krila', Master's thesis, University of Zagreb, Faculty of Mechanical Engineering and Naval Architecture, accessed 28 December 2024, https://urn.nsk.hr/urn:nbn:hr:235:099098

Andrić M. Model leta bespilotne letjelice konfiguracije letećeg krila [Master's thesis]. Zagreb: University of Zagreb, Faculty of Mechanical Engineering and Naval Architecture; 2014 [cited 2024 December 28] Available at: https://urn.nsk.hr/urn:nbn:hr:235:099098

M. Andrić, "Model leta bespilotne letjelice konfiguracije letećeg krila", Master's thesis, University of Zagreb, Faculty of Mechanical Engineering and Naval Architecture, Zagreb, 2014. Available at: https://urn.nsk.hr/urn:nbn:hr:235:099098

Metadata
TitleModel leta bespilotne letjelice konfiguracije letećeg krila
Title (english)Flight model for unmanned aircraft with flying wing configuration
AuthorMarijan Andrić
MentorMilan Vrdoljak (mentor)
GranterUniversity of Zagreb
Faculty of Mechanical Engineering and Naval Architecture
Zagreb
Defense date and country2014-07-16, Croatia
Scientific / art field,
discipline and subdiscipline		TECHNICAL SCIENCES
Mechanical Engineering
Abstract
U ovom diplomskom radu napravljen je 6DOF model leta krute letjelice konfiguracije letećeg krila \emph{FW25}, uz zanemaren utjecaj vjetra i zakrivljenost Zemlje. Razvijeni 6DOF model implementiran je u Simulinku, a rezultati su uspoređeni s linearnim modelom uzdužnog i bočnog gibanja. Pri tome je provedena usporedba odziva dvaju sustava na jednaku pobudu u vremenskoj domeni i uz manja očekivana odstupanja potvrđena je ispravnost 6DOF modela. Kompletni linearni aerodinamički model letjelice napravljen je metodom projektne aerodinamike pa zatim i numeričkom metodom uz pomoć XFLR5. Analizirane su specifičnosti upravljanja konfiguracijom letećeg krila te je rješenje implementirano u 6DOF model leta. Pri određivanju značajki pogonske grupe zanemarene su dinamičke pojave uslijed promjene pogonskog momenta motora. U model leta je implementiran sustav upravljanja uz pomoć igraće palice. Također je implementiran i sustav vizualizacije simulacije te je osigurano da se kompletna simulacija izvršava u realnom vremenu.
Abstract (english)
In this thesis a 6DOF ight model of a rigid aircraft with a ying wing configuration called FW25 is made, the influence of the wind and the curvature of the Earth is disregarded. Developed 6DOF model is implemented in Simulink, and the results are compared with a linearized model of longitudinal and lateral motion. Also a comparison between responses to identical disturbance in time domain of the systems is conducted and, with minor expected deviations, correctness of the 6DOF model is confirmed. The complete linearized aerodynamical model of an aircraft is made with an analytic aerodynamic method and then with a numerical method with the help of XFLR5. The specifics of maneuvering a flying wing configuration is analyzed and the solution is implemented in the 6DOF ight model. In analysing characteristics of propulsion, the dynamic effects due to changes of torque are disregarded. In this light model a steering system using a joystick is implemented. Visualisation simulation system is also implemented and it is insured that the complete simulation is executed in real-time.
Keywords
Keywords (english)
Languageenglish
URN:NBNurn:nbn:hr:235:099098
Study programmeTitle: Aeronautical Studies
Study programme type: university
Study level: graduate
Academic / professional title: magistar/magistra inženjer/inženjerka zrakoplovnog inženjerstva (magistar/magistra inženjer/inženjerka zrakoplovnog inženjerstva)
Type of resourceText
File originBorn digital
Access conditionsOpen access
Terms of useLicence In copyright icon
Created on2019-05-22 11:17:50