Optimalizace poměru tah-příkon vrtulové pohonné jednotky

Abstract

The thesis deals with the use of the propeller drive unit with variable pitch in order to reduce the power consumption of drones. The introductory part of the work aims at a general mathematical description of the internal structure of the aircraft attitude control. The work also deals with the common problem of the inappropriately chosen combination of motor and propeller. Variable pitch propeller drive is useful to minimize power consumption. The use of these units for the drones is only experimental and in terms of optimization of energy consumption. In terms of the power consumption optimization the ratio of thrust-power T/P_C was calculated. Four control algorithms are presented. The first algorithm takes advantage of the power unit in the fixed mode to adjust the angle of attack. The signal conditioner extends the second algorithm. One input value is used for the two outputs – speed and angle settings. The third algorithm adds a motor speed controller ω. Advantage of the introduction of the inner control loop is the possibility of precise compliance with the desired engine speed. The fourth introduced algorithm is extended with adaptive changes at the angle settings. The simulation model of drive unit including the airfoil model was created. Software on embedded platform of laboratory model provides several functions including calibration of strain gauges and the processing of all inputs connected to the AD converters. All measurements are real-time with transfer to the PC. The results of measurements on the laboratory model brought energy-saving 5.7% compared to the standard power unit.