When designing aircraft, all integrated systems must be tested in all flight modes before being implemented in the aircraft, to which these systems will later be exposed. As part of the thesis, we designed a laboratory test facility for rotational electromechanical actuators intended for the control of primary control surfaces. We determined the geometric and operational characteristics for the selected wing and its control surface, and performed analytical calculations of the aerodynamic and mechanical loads to which the actuator will be exposed, taking into account the EASA CS-23 standard. Based on this, we defined the structural and functional elements of the testing site. We also demonstrated ways to reduce the necessary torque of the actuator. The task includes a comprehensive theoretical calculation, component selection, and a 3D model that can serve as the basis for the actual construction of the test site.
|
