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

A technology with coaxial dual rotors and aerodynamic characteristics, which is used in aircraft component testing, power measurement, force/torque/power measuring instruments, etc. The influence of aerodynamic parameters and aerodynamic characteristics is not considered, and the hovering force measurement of the whole machine system cannot be realized, so as to achieve the effect of reducing ground effect, simple structure and low cost

Active Publication Date: 2017-10-03
CHANGGUANG SATELLITE TECH CO LTD
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  • Summary
  • Abstract
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  • Claims
  • Application Information

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,

Method used

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

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specific Embodiment approach 1

[0030] Specific implementation mode 1. Combination Figure 1 to Figure 5 To illustrate the specific implementation of the present invention, a ground test bench for the aerodynamic characteristics of a ducted coaxial dual-rotor UAV is mainly composed of a test platform outer support 1, an adjustment inner support 2, a ducted propeller system and a measurement display system. The outer support 1 of the test platform of the present invention is constructed by a combination of 40.40 aluminum profiles as a whole, and is fixed by bolt connection. The ground end is equipped with 4 adjustment feet 29, and the inner support 2 is adjusted by the lower positioning frame 13 and the upper positioning frame 10. 30.30 aluminum profiles of the same length are combined and fixed with bolts. One duct 3, two motors 16, two sets of three-blade propellers 27, four steering gears 14, and four deflectors in the ducted propeller system 4 and other components are fixed in the adjustment inner bracket...

specific Embodiment approach 2

[0036] Specific embodiment two, this embodiment adopts three main test forms of the aerodynamic characteristics test bench test of the ducted coaxial dual-rotor UAV described in the specific embodiment one:

[0037] 1. Axial (longitudinal) torque measurement: combined with image 3 , Figure 7 , the adjustment inner bracket 2 is connected and suspended in the middle of the outer bracket of the experimental platform through the upper and lower layers of four evenly distributed vertical leaf springs 7, the static torque sensor is located directly below the adjustment inner bracket 2, and one end of it is connected to the bottom plate 28 through bolts It is connected and fixed on the support beam of the test platform outer support 1, and the other end is fixedly connected with the lower positioning frame 13 of the adjustment inner support 2 through the coupling 5, and the components of the ducted propeller system are installed in the adjustment inner support 2 in sequence , keep...

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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...

Claims

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Application Information

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IPC IPC(8): G01L3/14G01L5/00B64F5/60
CPCB64F5/60G01L3/1407G01L5/00
Inventor 李海关永亮徐畅陈在斌王鹏鹏
Owner CHANGGUANG SATELLITE TECH CO LTD
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