Abstract
The use of unmanned vehicles - both civilian and military - is clearly a technological trend today. It is reasonable to assume that this trend will continue in the future. Especially in the military field, an unmanned vehicle can be considered a benefit, especially in applications where the use of "standard" equipment is difficult or impossible. This is especially true of Unmanned Aerial Vehicle (UAV). The flight itself represents a number of different types of stress affecting the design of the unmanned aircraft. Therefore, the design of such a device must be subjected in the first step to a computational strength analysis and subsequently to a real stress test. Our paper deals with the strength analysis of the most exposed structural element - the wing connector. Proper sizing of the wing connector is therefore crucial for the successful operation of the UAV.
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