Performance testing device for rotor wing unmanned aerial vehicle power assembly
A technology of unmanned rotor and test device, applied in the direction of aircraft component testing, etc., can solve the problems of large ground effect, single, incomplete test parameters, etc.
Pending Publication Date: 2021-03-23
TIANJIN SINO GERMAN VOCATIONAL TECHNICAL COLLEGE
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Problems solved by technology
However, in the current market, there are few UAV power system test devices; the existing test devices have problems such as incomplete or relatively single test parameters, and large ground effects.
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[0017] The specific implementation manner of the present invention will be described in detail below in conjunction with the accompanying drawings and preferred embodiments.
[0018] In order to solve the problems of incomplete or relatively single test parameters and large ground effect of the existing test device, the present invention provides a power performance test device for the power system of the rotor UAV, which can test the lift, current, voltage, and rotational speed of the power system of the UAV. And other performance parameters, can also carry out the efficiency and propeller efficiency experiments, load factor experiments, etc. of the rotor UAV.
[0019] The inventive idea of the present invention is as follows: the present invention provides a lever-type unmanned aerial vehicle power performance testing device, which keeps the measured object away from the ground through the support rod, and measures the lift force of the unmanned aerial vehicle in a real fli...
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The invention discloses a performance testing device for a rotor wing unmanned aerial vehicle power assembly. The performance testing device comprises an equipment rack, a force measurement unit, a speed measurement unit, a protection assembly and a control display unit. The equipment rack is used for fixing an electrical device, collecting current and voltage parameters of the rotor wing unmannedaerial vehicle power assembly, and supporting the force measurement unit, the speed measurement unit, the protection assembly and the display unit. The force measurement unit is used for fixing the rotor wing unmanned aerial vehicle power assembly and collecting rotor wing lifting force data. The speed measurement unit is used for acquiring rotor wing rotating speed data. The protection assemblyis used for safety protection of operators. The control display unit is used for fixing a power supply, a signal interface and a display assembly. The invention aims to provide the performance testingdevice for the rotor wing unmanned aerial vehicle power assembly, wherein the performance testing device can acquire and measure data information such as lifting force, rotating speed, current, voltage and the like of the power assembly, and provides experimental equipment for analyzing performance experiments and analysis of the rotor wing unmanned aerial vehicle power assembly.
Description
technical field [0001] The invention belongs to the technical field of devices for testing and experimenting with power parameters of a power system of a rotor UAV, and in particular relates to a test device for a power system of a rotor UAV. Background technique [0002] At present, UAV technology is developing rapidly, and UAV application fields are constantly expanding. The power system is a key component of the UAV and a key factor affecting the performance of the UAV. Accurately measuring the performance parameters of UAV power system is the key work to research and improve UAV power performance. However, in the current market, there are few UAV power system test devices; the existing test devices have problems such as incomplete or relatively single test parameters, and large ground effects. Contents of the invention [0003] The purpose of the present invention is to provide a rotor UAV power system testing device to solve the problems in the background technology...
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CPCB64F5/60
Inventor 韩金玉王守志刘琼李磊尹士轩
Owner TIANJIN SINO GERMAN VOCATIONAL TECHNICAL COLLEGE