Unmanned aerial vehicle plasma flow control flight test measurement and control system

A plasma and flight test technology, which is applied in the field of plasma flow control UAV flight test measurement and control system, can solve the problems of incomplete flow field data measurement and collection, and cannot quantitatively reflect the plasma flow control effect, etc., to achieve weakening Effects of Electromagnetic Interference
CN108928503AActive Publication Date: 2018-12-04AIR FORCE UNIV PLA
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
AIR FORCE UNIV PLA
Publication Date
2018-12-04

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Abstract

The invention provides an unmanned aerial vehicle plasma flow control flight test measurement and control system which comprises two parts of a sky end and a ground end which are connected through wireless signals. An operator inputs a command into the ground end, the ground end converts the command into the wireless signal and sends the wireless signal to the sky end, and the sky end receives thecommand and executes corresponding operation; and after the sky end measures required data, the sky end converts the data into the wireless signal and sends the wireless signal to the ground end, theground end receives the signal and displays the data contained in the signal. The system can remotely control on-off and parameter change of an onboard plasma power source in the flight process of anunmanned aerial vehicle, record and transmit an airfoil image and an airfoil pressure distribution condition back in real time and test a flow control effect.
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Description

technical field

[0001] The invention relates to plasma flow control technology, in particular to a plasma flow control UAV flight test measurement and control system. Background technique

[0002] The wing is a key component of the aircraft, providing more than 70% of the total lift for the aircraft, and its performance directly determines the aerodynamic performance of the entire aircraft. When the angle of attack of the aircraft is large, the suction surface of the wing will cause the separation of the boundary layer, which will reduce the lift and increase the drag. When the angle of attack exceeds the critical angle of attack, the boundary layer is severely separated, the lift of the wing decreases sharply, the drag increases rapidly, and the aircraft stalls. How to suppress the separation of the wing boundary layer and improve the performance of the aircraft has always been an important issue in the aviation field.

[0003] Plasma flow control technology is a new type...

Claims

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