Konstrukční návrh vysílačů palivoměrů v integrovaném křídle letounu

Abstract

After the introduction, which clearly indicates all used methods of measuring the amount of fuel in the airplane, the thesis analyzes optimal positioning of fuel transmitters inside the integrated wing from the measurement error point of view in specific conditions like takeoff, landing and horizontal flight. By using 3D design systems it is specified the amount of usable fuel for aircraft wings and the fuel level during the longitudinal tilt of an airplane is simulated. The modern fuel tank is integrated into the aircraft wing which complements the existing rubber and marginal fuel tanks – during the design and construction of a new fuel transmitter the effort is focused on using already mass-produced parts and subassemblies. The results of this thesis can be directly applicable in the research and development project, which is solved in the contracting company.