Correction of calculated dynamic scheme of unmanned aerial vehicle based on results of ground modal tests

Abstract

The problem of correcting of the calculated dynamic scheme of an unmanned aerial vehicle (UAV) based on the results of ground modal tests is considered. The provisions that allow achieving satisfactory results when the UAV calculated dynamic scheme correcting are formulated. Correction criteria are considered. Features of the calculated dynamic scheme correction in the study of the flutter and the aeroelastic stability of the UAV with the automatic control system (ACS) are presented. It is noted that along with the provisions that are universal for dynamical aeroelasticity tasks related to the correction of natural frequencies, forms, and coefficients of structural damping of the UAV on the results of ground modal tests, in the study of aeroelastic stability of the UAV with the ACS is also crucial to correct the transfer function of the UAV body from section, in which the rudder rotation axes are located, up to the cross-section, where ACS sensors are installed. This is because the UAV body is directly part of the UAV stabilization loop and significantly affects to its stability reserves. An example of correcting of the UAV calculated dynamic scheme is given.