Razvoj algoritma za avtonomno pristajanje letal

Trojer, Jonas (author), Šajn, Viktor (mentor), Brojan, Miha (comentor)

V delu je predstavljen razvoj algoritma za avtonomno pristajanje letal. Izpeljan je matematični model gibanja masne točke v šestih prostostnih stopnjah ter njegova linearizacija okrog ravnovesne lege leta letala. Na podlagi dobljenih nelinearnih gibalnih enačb je izdelana simulacija leta, ki zajema tudi pomembnejše nelinearnosti aktuatorjev ter zaznaval, kot so omejeno območje delovanja, temperaturna odvisnost, učinki digitalizacije in šum, ter služi kot okolje za razvoj in preizkušanje razvitega algoritma. Podrobneje je raziskan vpliv merilnega šuma na dosegljivo natančnost vodenja in uporaba Kalmanovega filtra za omilitev njegovih učinkov.

• Language: Slovenian
• Keywords: mehanika leta letal pristajanje letal avtomatsko vodenje simulacije natančnost vodenja merilni šum Kalmanovi filtri
• Work type: Master's thesis
• Typology: 2.09 - Master's Thesis
• Organization: FS - Faculty of Mechanical Engineering
• Publisher: [J. Trojer]
• Year: 2018
• PID: 20.500.12556/RUL-102932
• UDC: 629.7.05:681.5(043.2)
• COBISS.SI-ID: 16427547
• Publication date in RUL: 12.09.2018

TROJER, Jonas, 2018, Razvoj algoritma za avtonomno pristajanje letal [online]. Master’s thesis. J. Trojer. [Accessed 31 March 2025]. Retrieved from: https://repozitorij.uni-lj.si/IzpisGradiva.php?lang=eng&id=102932

Secondary language

• Language: English
• Title: Development of an algorithm for autonomous aircraft landing

Abstract

In this thesis the development of an algorithm for autonomous landing of aircraft is presented. First, a mathematical model for the motion of a point mass with six degrees of freedom is derived, along with its linearization about a reference trajectory. Based on these nonlinear equations of motion a flight simulation is designed, that also takes major sensor and actuator nonlinearities, such as limited range of operation, temperature dependency, effects of digitalization and noise into account. It serves as an environment for the development and testing of the proposed algorithm. A more thorough investigation into the influence of measurement noise on the achievable guidance accuracy is undertaken, as well as into the utilization of a Kalman filter for the mitigation of its effects.

• Keywords: aircraft flight mechanics aircraft landings automatic control simulations control performance measurement noise Kalman filters