AUTHORS: Lucjan Setlak, Rafal Kowalik

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ABSTRACT: The subject of this article is to analyze and select simulation tests in the field of issues related to flight control systems for micro-class aircraft. The main purpose of the work is to develop an algorithm for the flight control system, taking into account both the speed and direction of the wind acting on the UAV, which are the key attributes that play a decisive impact on the disturbance of flight parameters and its correct performance. What is more, atmospheric conditions determined by the influence of wind can produce phenomena dangerous to aviation in the form of wind shear or blast from the back during the landing process of the aircraft. The occurrence of the above situation may be the cause of stall phenomenon, which in turn may be the cause of a dangerous aviation phenomenon (accident, incident, etc.). For the purposes of solving the research problem, the article uses a mathematical apparatus in the form of equations describing the movement of the aircraft and the forces and moments acting on it. Based on the mathematical analysis of the UAV object, in the further part of the article, an algorithm was developed to estimate the impact of wind and an analysis of measurement errors occurring during flights and their impact on the measured values, as well as the values calculated on their basis. On this basis, charts have been developed defining clearly the various relationships. In the final part of the thesis, based on the mathematical analysis, simulation tests and analysis of the results obtained, the final conclusions and observations were formulated, which are reflected in practical applications.

KEYWORDS: Control model, micro class UAV object, equations of motion, strong wind influence

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