METHOD FOR EXPERIMENTAL RESEARCH OF AEROMECHANICS AND DYNAMICS OF FLIGHT OF UNMANNED AERIAL VEHICLES AND DEVICE FOR IMPLEMENTATION THEREOF

摘要

FIELD: aviation.;SUBSTANCE: invention relates to the field of aviation test equipment, in particular to methods and means of studying aeromechanics and dynamics of flight of unmanned aerial vehicles. When implementing the method, characteristics of an unmanned aerial vehicle are experimentally investigated at a given increase or decrease in flight speed by performing the following operations: determining the speed of the unmanned aerial vehicle to be analyzed by integrating the equations of motion of the UAV with a given control law; aircraft speed values obtained during integration are used as program settings for air flow rate control means; air flow rates are reproduced by means of a group of motors 6–17; measuring forces and moments acting on aircraft, using six-component dynamometer 48; calculating aerodynamic coefficients of lift and resistance; specified values of aerodynamic resistance of the vehicle and speed of its movement are calculated. At the same time aircraft is installed at pitch angle in the range of −45° up to 45° which, according to readings of six-component dynamometer 48, provides for creation of lift equal to weight by means of automatic control of servomechanisms 61–64. Device comprises means for creating an air flow, means for measuring forces and moments acting on the investigated apparatus, means for controlling the position of the investigated apparatus, at that, the air flow creation means are made in the form of a group of propellers, each of which has an individual high-speed drive consisting of a propeller, a brushless electric motor with a motor rpm controller and sensors for the speed of the air flow generated by the propeller. At the same time, propulsors are arranged in at least three parallel rows to simulate irregular distribution of airflow speed and turbulence. In order to measure forces and moments acting on the investigated vehicle, a six-component dynamometer is installed inside the fuselage of the investigated vehicle, having a statically determined structure consisting of strain-gauge beams. At that, two parallel beams measuring forces directed along vertical axis Z are rigidly fixed by root ends to dynamometer support plate, which is connected to the fuselage frame through four servomechanisms serving for parallel movement of the plate plane along the X axis and along the Y axis, as well as for rotation of the plane of the base plate relative to the plane of the frame by the pitch angle. At that, in the lower part of the dynamometer frame there is a detachable connection with a holder, which is installed on a fixed base.;EFFECT: wider range of speeds and accelerations of air flow, as well as possibility of accurate control of speeds and accelerations of air flow during experimental studies of aeromechanics and dynamics of flight of unmanned aerial vehicles.;8 cl, 3 dwg