A booster device for near-space drones

Abstract

The invention relates to a synergistic device of a near space unmanned aerial vehicle. The synergistic device of the near space unmanned aerial vehicle comprises a plurality sets of plasma exciters, a management control system and an external chamber body; the multiple sets of plasma exciters are symmetrically mounted on the upper surfaces of airfoils on the two sides of the unmanned aerial vehicle; in the management control system, pressure sensors are symmetrically distributed on the upper surfaces of the airfoils on the two sides, and the pressure sensors are connected with a system controller through an electrical signal amplifier; the system controller is connected with a plasma exciter power source controller and a high voltage output controller, the plasma exciter power source controller is connected with a plasma exciter power source, an output end of the plasma exciter power source is connected with an input end of the high voltage output controller, and an output end of the high voltage output controller is connected with the plasma exciters; and the external chamber body is used for storing the management control system. The synergistic device is simple in structure, and can effectively solve the problems that the airfoil flow and separation of the near space unmanned aerial vehicle are severe and the flying efficiency is low.

Description

technical field [0001] The application relates to a plasma pneumatic excitation booster device, which is applied to low-speed unmanned aerial vehicles in close space, and belongs to the technical field of plasma flow control, in particular to a booster device for near-space drones. Background technique [0002] The thin air and low density in the adjacent space make the UAV wing surface more prone to boundary layer separation, and the lift-to-drag ratio and flight efficiency of the wing cannot be guaranteed, which seriously affects the UAV's load capacity and long-endurance flight performance. At present, there are a variety of flow control methods to control airfoil flow separation, such as passive flow control technologies such as installing spoilers on the wing, machining a series of grooves on the surface of the wing, or installing vortex generators; synthetic jet flow technology and active flow control technologies such as suction gas control. These control methods hav...

AI Technical Summary

Problems solved by technology

[0005] The purpose of this application is to solve the above-mentioned current problems, and to provide a near-space low-speed UAV efficiency device based on plasma flow control technology, so as to improve the flow field of low-speed UAVs in the adjacent space and reduce the mechanical damage caused by flow separation. The negative effects of increased wing drag and reduced lift can improve the drone's load capacity and long-term cruise performance

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