The task presents the calculation, design, and testing of a valveless pulsejet thrust device designed to drive an aircraft model. The dimensions and shape of the key components are determined by a semi-empirical approach, taking into account meaningful simplifications. The iterative procedure and the results of the calculations are presented, where the input is the desired thrust, while required dimensions are then calculated and adjusted in accordance with the desired thrust. In the framework of the calculations, an analysis of the sensitivity of the operating parameters to changes in the individual dimensions of the device is made, and thus the determination of the most important design characteristics. An experimental system consisting of a thrust force meter, a high-frequency pressure sensor, temperature gauges and a purpose-built software environment for monitoring key operating parameters is then designed based on the manufactured device. Incandescence estimates the surface temperature of the device. The sound volume produced by the device was also measured. The manufactured device is tested in the interval of continuous operation and shutdown, and each interval is interpreted separately. The propulsion device is proved to operate and succeed in delivering at least 80 N of the thrust when stationary, and operates at a frequency of 163 Hz and fuel mass flow rate of 8,6 g / s. The results indicate a pronounced sensitivity of the dimensions of the device on stability of operation as well as the need to accurately determine the geometry to achieve the stable performance.
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