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System and method for preventing deicing by using gliding discharge plasma

A discharge plasma and plasma technology, applied in deicing devices, aircraft parts, transportation and packaging, etc., can solve the problems of low heat energy utilization rate and high fuel consumption, and achieve large action area, fast response speed and high conversion efficiency high effect

Active Publication Date: 2018-09-04
XIAN UNIV OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0014] Another object of the present invention is to provide a method for anti-icing by applying sliding discharge plasma, which solves the problems of large fuel consumption and low utilization rate of heat energy in traditional hot gas anti-icing systems on aircraft

Method used

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  • System and method for preventing deicing by using gliding discharge plasma
  • System and method for preventing deicing by using gliding discharge plasma
  • System and method for preventing deicing by using gliding discharge plasma

Examples

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Embodiment

[0048] like Figure 5 As shown, the experimental model 5 is a NACA0015 airfoil with a chord length of 300mm and a span length of 500mm. The electrodes of the sliding discharge plasma exciter 1 are made of copper, and the copper electrodes are inlaid on the surface of a soft thin-film silicon rubber sheet. The upper and lower electrodes are treated the same way, and the thin-film silicon rubber sheet is covered on The surface of the airfoil forms a sliding discharge plasma excitation structure.

[0049] The upper electrode consists of three electrodes, the first upper electrode 1-1 is 200mm long and 5mm wide; the second upper electrode 1-2 is 200mm long and 5mm wide; the third upper electrode 1-3 is the The mirror image centered on the second upper electrode 1-2.

[0050] The insulating dielectric layers 1-4 are made of thin-film silicone rubber sheets with a thickness of 1mm.

[0051] The lower electrode layers 1-5 are composed of monolithic copper electrodes with a length ...

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Abstract

The invention discloses a system for preventing deicing by using a gliding discharge plasma. The system comprises gliding discharge plasma actuators, ice detectors, a power supply system and an anti-icing controller. The power supply system provides working power for all electric equipment. The gliding discharge plasma actuators and the ice detectors are separately connected with the anti-icing controller. A method for applying the gliding discharge plasma to prevent deicing is specifically divided into two working stages of preventing icing and breaking icing, a wide range of sliding discharge is produced by using the gliding discharge plasma actuators, rapid energy injection is generated to rapidly heat the entire area of the upper surfaces of the gliding discharge plasma actuators, iceat the interface between the surfaces of wings and the bottom of an ice layer is melted, the surfaces of the wings are broken away from the ice layer, and the problems of large fuel consumption and low heat utilization rate of a conventional hot air anti-icing system on an aircraft are solved.

Description

technical field [0001] The invention belongs to the technical field of plasma physics and anti-icing, and in particular relates to an anti-icing system using sliding discharge plasma, and also relates to an anti-icing method using sliding discharge plasma. Background technique [0002] After the aircraft encounters supercooled water droplets in the clouds in the air, icing may occur on the leading edge of the wing, tail, rotor, engine intake and windshield. When the shape or distribution of icing is irregular, it will significantly affect the flow field near the airfoil, destroy the streamline shape of the wing, reduce the lift, increase the resistance, reduce the control efficiency, make the control difficult or even fail, and reduce the engine thrust and other technical indicators Deterioration will directly lead to instantaneous deceleration, fall, stall, side roll, and violent bowing, which will damage the aerodynamic performance and operational performance of the aircra...

Claims

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Application Information

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IPC IPC(8): B64D15/00
CPCB64D15/00
Inventor 郑博睿葛畅柯熙政刘宇坤魏玮
Owner XIAN UNIV OF TECH
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