Uzdužni linearniI model leta aviona za gašenje požara

master's thesis

• Title (english): Longitudinal linear flight model for firefighting airplane
• Author: Roko Brzić
• Mentor: Milan Vrdoljak (mentor)
• Mentor: Marijan Andrić (komentor)
• Granter: University of Zagreb; Faculty of Mechanical Engineering and Naval Architecture; Zagreb
• Defense date and country: 2024-12-06, Croatia
• Scientific / art field, discipline and subdiscipline: TECHNICAL SCIENCES; Aviation, Rocket and Space Technology

Abstract

Požari otvorenog prostora pravi su izazov za gašenje najčešće zbog nepristupačnog terena te vegetacije zbog koje se brzo šire, stoga je došlo do razvoja zrakoplova čija je svrha gašenje istih. Jedan od tih zrakoplova je i Canadair CL-415 koji je bio bazna referenca pri izradi ovog diplomskog rada.
Tijekom izrade rada procijenjena je geometrija zrakoplova te njegove inercijske značajke za četiri različite konfiguracije s aspekta raspodjele mase. S vrijednostima geometrije zrakoplova napravljen je proračun procjene otpora te procjena potrebnih aerodinamičkih koeficijenata. Nadalje, odrađena je analiza ravnotežnog leta i statičke stabilnosti zrakoplova. Napravljen je uzdužni linearni model zrakoplova te provedena analiza dinamičke stabilnosti i ocjena kvalitete upravljanja prema MIL i DSMU kriteriju. Zbog lošije dinamike zrakoplova uvedena je povratna veza radi njenog poboljšanja te ponovljen postupak ocjenjivanja kvalitete upravljanja.
Izrada i analiza numeričkog dijela rada provedena je u računalnom programu MATLAB prateći navedenu literaturu.

Abstract (english)

Open space fires are a real challenge to put out, usually due to inaccessible terrain and vegetation that causes them to spread quickly, which is why the development of aircraft whose purpose is to extinguish them begun. One of these aircraft is the Canadair CL-415, which was the base reference for the creation of this graduation thesis.
During the making of this master's thesis, the values of aircraft's geometry and moments of inertia were estimated for four different configurations with regard to mass distribution. With the values of the aircraft's geometry, a calculation was made to estimate it's resistance and aerodynamic coefficients. Furthermore, an analysis of the aircraft's equilibrium flight and static stability was performed. A longitudinal linear model of the aircraft was created, and an analysis of aircraft's dynamic stability and the quality control of manoeuvrability was performed according to MIL and DSMU criteria. Due to the poor aircraft's dynamic stability, stabilisation of the flight was introduced to improve the dynamic stability, and the same process of evaluating the quality control of manoeuvrability was repeated.
Creation and analysis of the numerical part of this master's thesis was carried out in the computer program called MATLAB while following the cited literature.

• Keywords: visokokrilac; amfibijski zrakoplov; aeroprofil; otpor; težište; aerodinamička tetiva; neutralna točka; stabilnost; moment propinjanja; normalna sila
• Keywords (english): high-wing configuration; amphibious aircraft; airfoil; drag; center of gravity; aerodynamic chord; neutral point; stability; pitching moment; normal force
• Language: croatian
• URN:NBN: urn:nbn:hr:235:817859
• Study programme: Title: Aeronautical Engineering; Study programme type: university; Study level: graduate; Academic / professional title: sveučilišni/a magistar/magistra inženjer/inženjerka zrakoplovnog inženjerstva (sveučilišni/a magistar/magistra inženjer/inženjerka zrakoplovnog inženjerstva)
• Type of resource: Text
• File origin: Born digital
• Access conditions: Open access
• Created on: 2024-11-28 16:32:14