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

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.

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...

AI Technical Summary

Problems solved by technology

At present, the flight test of plasma flow control is in its infancy. The switching of the plasma actuator during the flight, the measurement and collection of flow field data are not perfect, and cannot quantitatively reflect the effect of plasma flow control.

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