Analiza stabilnosti i upravljivosti male bespilotne letjelice

Krcatović, Ivan (2015) Analiza stabilnosti i upravljivosti male bespilotne letjelice. = Stability and control analysis for small unmanned aircraft. Master's thesis (Bologna) , Sveučilište u Zagrebu, Fakultet strojarstva i brodogradnje, UNSPECIFIED. Mentor: Vrdoljak, Milan.

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Abstract (Croatian)

U ovom radu napravljen je model bespilotne letjelice maksimalne mase 4 kg, te je provjerena statička i dinamička stabilnost leta. Na temelju poznate geometrije izrađen je 3D model letjelice u programskom paketu SolidWorks iz kojeg su određeni momenti tromost, položaj težišta i ukupna masa letjelice. Metodom projektne aerodinamike procjenjeni su svi aerodinamički koeficijenti letjelice, te kao provjera aerodinamičkog modela napravljen je model letjelice u programskom paketu Xflr5. Zbrajanjem utjecaja aerodinamike i pogona definira se konačni aerodinamički model letjelice. Na konačnom modelu letjelice najprije se vrši analiza statičke uzdužne i bočne stabilnosti kojom se određuje da li je letjelica statički stabilna ili ne. Nakon utvrđivanja statičke stabilnosti analizani su režimi leta u kojima će letjelica provoditi najviše vremena. Na temelju tih režima izrađuju se linearni model letjelice kojim se provjerava da li je letjelica dinamički stabilna. Nakon definiranja sustava jednadžbi za oba režima leta napravljena je analiza dinamičke stabilnost i analiza odziva letjelice. Za kraj rada provedena je analiza ocjene upravljanja uzdužnog i bočnog gibanja. Ocjenom upravljivost je moguće usporediti novu letjelicu s ostalim postojećim letjelicam. Ova analiza daje dobar uvid u moguće promjene prilikom slijedećih koraka u projektiranju letjelice.

Abstract

In this thesis a model of small unmanned aircraft with maximum mass of 4 kg is made. Static and dynamic stability of model is then checked. 3D model of aircraft is made base on previously define geometry, and all inertial moments, masses, and centre of gravity positions are listed from this model made in Solidworks. The aerodynamic model of an aircraft is made using analytic method and then checked with help of the Xflr5 program packet. Effects of the aerodynamic and propulsion are summarize in final model, which longitudinal and lateral static stability is then checked. Aircraft study level flight modes are analyses and determinate, based on those flight modes linear models of aircraft are made. Dynamic stability and system response of linear models is then checked. Criteria for longitudinal and lateral control is then apply on linear model. This criterion is useful because it provides comparison between new aircraft and already existing aircrafts. Control criteria can provides good assumption on next step of designing the aircraft.

Item Type: Thesis (Master's thesis (Bologna))
Uncontrolled Keywords: Bespilotna letjelica; projektna aerodinamika; linearni model; statička stabilnost; dinamička stabilnost
Keywords (Croatian): unmanned aircraft; analitic aerodynamics; linear model; static stability; dynamic stability
Subjects: TECHNICAL SCIENCE > Aviation, rocket and space technology > construction and establishment of a spacecraft
Divisions: 1300 Department of Aeronautical Engineering > 1310 Chair of Aerodynamics
Date Deposited: 16 Jul 2015 06:55
Last Modified: 13 Sep 2019 13:19
URI: http://repozitorij.fsb.hr/id/eprint/4483

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