In the technical development of unmanned aerial vehicles - UAVs, the success of theoretical modeling of flight control of these robotic systems is of great importance. Several tasks related to one of the functional purposes of the UAV are presented using the example of a quadrocopter. In particular, an engineering approach to solving the issue of its carrying capacity is presented, and the influence of the dynamic characteristics of a load suspension to a quadcopter on the behavior of such a mechanical system is considered.
In this regard, the purpose of the work was to theoretically and experimentally study the carrying capacity of a quadrocopter during its vertical takeoff and hovering at a given height to determine the necessary change in the values of the lift of the quadcopter propellers at a given flight time interval and also the effect on it of the dynamic characteristics of the suspension of the transported load. At the same time, based on the formulations and solution of direct and inverse problems of theoretical mechanics using single-mass and two-mass transportation models with viscoelastic coupling, the possibility of calculating the flight regime of a quadrocopter is considered.