Aerodynamic characteristic testing stand for ducted coaxial dual-rotor unmanned aerial vehicle

Abstract

The invention, which relates to the field of hovering fore-measuring technology of the unmanned aerial vehicle, provides an aerodynamic characteristic testing stand for a ducted coaxial dual-rotor unmanned aerial vehicle, so that problems of the existing motor thrust testing technique are solved. The aerodynamic characteristic testing stand comprises an external testing platform bracket, an internal adjustment support, a ducted propeller system and a measurement display system. The external testing platform bracket and the internal adjustment support are three-dimensional frames; and the internal adjustment support is fixed inside the external testing platform bracket by flat springs. According to the invention, because straight cantilever type springs are arranged at the same direction, the minimum stiffness plane is easy to bend; with a resistance strain type transducer, displacement during testing is small; because of different flat spring installation and fixation ways, displacement at a certain direction can be restricted and the freedom degree of the sensor measuring direction can be kept; and to-be-measured information generated by the system is transmitted to the sensor and data reading and recording are carried out by a display system, so that different test objectives are achieved.

Description

technical field [0001] The invention relates to the technical field of hovering force measurement of unmanned aerial vehicles, in particular to a test bed for the aerodynamic characteristics of a ducted coaxial double-rotor unmanned aerial vehicle. Background technique [0002] With the continuous development of ducted aircraft, the ducted coaxial dual-rotor mechanism can be used not only as an independent ducted aircraft, but also as a mechanism for providing power, becoming a part of the aircraft. Compared with the ducted single-rotor, the structure of the ducted coaxial dual-rotor is more compact. The two rigid rotors are located in the center of the duct and rotate in opposite directions around the same axis to balance the torque generated by each, so that there is no need for a balancing flow guide In addition, the duct can be regarded as a ring-shaped wing that wraps the rotor. While protecting the rotor, enhancing safety and reducing noise, it can also generate additi...

AI Technical Summary

Problems solved by technology

Existing thrust test devices mostly measure the aerodynamic load (pull force, torque, etc.) Hover force measurement requirements for coaxial dual-rotor UAV

[0004] Chinese invention patent application publication CN103604608A discloses a "light sports aircraft propeller tension test bench", which is mainly used for thrust and dynamic torque measurement in the case of a single propeller motor with variable speed, and a simple and accurate test bench is built. However, the hovering force measurement experiment of the whole machine system cannot be realized

[0005] Chinese utility model patent specification CN202994470U proposes a "unmanned aircraft power performance test system", which can test the output torque, speed, power, thrust, fuel consumption and other driving performance of the unmanned aerial vehicle under various flight conditions Comprehensive testing, but essentially testing only the engine's propulsion characteristics

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