Simulation of the Test Bench of Structural Elements of Aircraft Controls

Purpose of reseach. Improving the efficiency of the test benches of the structural elements of the aircraft controls, by taking into account the dynamic features of the electromechanical system, studied using a mathematical model that takes into account the features of the hardware implementation of the drive and measuring systems of the stand. Tasks. Development of a mathematical model of the drive system of the executive link of the test bench, obtaining dynamic characteristics of the controlled movement of the electromechanical system of the stand and the rotary switch from the aircraft crew controls.

Methods. Methods of mathematical modeling of dynamic systems, control theory and theory of mechanisms and machines were used to solve the tasks. When creating software products, Matlab/Simulink mathematical packages were used. To assess the influence of the properties of the elastic coupling on the dynamics of the movement of the executive link, the quadratic error in position and speed, as well as their integral values, were used.

Results. In the course of the research, a mathematical model of the test bench was developed, including the drive and measuring systems, the interface device and the object of the tested equipment. In the course of computational experiments, the maximum values of the torque and the rotational speed of the executive link were established, and the influence of the parameters of the elastic-viscous properties of the interface elements on the movement of the rotary switch was analyzed.

Conclusion. It is established in the work that the pulsed nature of the torque change affects the movement of the executive link of the stand. To reduce the effect, it is proposed to use a viscoelastic coupling element, which reduces the oscillation of the executive link of the stand while maintaining high accuracy of movement.

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