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Air blowing rain removal system based on supersonic flow injection effect

A supersonic and effective technology, applied in the aviation field, can solve the problems affecting the rain removal effect, shock wave, and air flow velocity reduction, and achieve a good effect of rain removal

Pending Publication Date: 2022-05-13
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

In fact, the pressure of the air source system of the aircraft will fluctuate. When the pressure of the air source decreases, the outlet pressure of the nozzle will drop, which is lower than the ambient pressure. After the airflow flows out of the nozzle, a shock wave will be formed, resulting in a decrease in the airflow velocity and affecting the rain removal effect.

Method used

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  • Air blowing rain removal system based on supersonic flow injection effect
  • Air blowing rain removal system based on supersonic flow injection effect
  • Air blowing rain removal system based on supersonic flow injection effect

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Embodiment Construction

[0017] In order to make the objectives, technical solutions and advantages of the implementation of the application clearer, the technical solutions in the implementation modes of the application will be described in more detail below with reference to the drawings in the implementation modes of the application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the present application. The embodiments described below by referring to the figures are exemplary and are intended to explain the present application, and should not be construed as limiting the present application. Based on the implementation manners in this application, all other implementation manners obtained by persons of ordinary skill in the art without creative efforts fall within the scope of protection of this application. Embodiments of the pr...

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Abstract

The invention belongs to the technical field of aviation, and relates to an air blowing rain removal system based on a supersonic flow ejection effect, which mainly comprises a first air path and a second air path through which airflow passes, and the first air path and the second air path are sequentially provided with an air source, a pressure regulating valve, a pressure sensor and a nozzle along the airflow direction; the first gas path and the second gas path are connected at the gas source outlet through a third gas path, the third gas path is provided with a cross air-entraining valve, the pressure sensor, the pressure regulating valve and the cross air-entraining valve are all connected with a control device, and the nozzle with the diagonal plane can enable the speed of the sprayed gas flow to reach supersonic speed and does not generate shock waves. The rain removal effect is better, and the air entrainment amount from the air source system can be reduced by injecting air in the surrounding environment.

Description

technical field [0001] The invention belongs to the technical field of aviation, and relates to an air blowing rain removal system based on supersonic flow ejection. Background technique [0002] In order to ensure the flight safety of the aircraft under rainy conditions, it is necessary to remove the rainwater on the windshield of the aircraft. The air blowing rain removal method is a new rain removal method. The principle of rain removal is to form a high-speed, high-temperature air protective wall on the outer surface of the windshield to cover the outer surface of the windshield to prevent rainwater from hitting the windshield. The purpose of the rain. [0003] In order to form a layer of high-speed air layer on the outer surface of the windshield, nozzles are often selected for air blowing and rain removal. The principle of the nozzle is the same as that of the Laval nozzle. The subsonic air flow is continuously accelerated inside the nozzle until it is ejected at a s...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B60S1/54B64C1/14G01D21/02
CPCB60S1/54B64C1/1476G01D21/02
Inventor 党晓民陈若冰苗新宇刘清
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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