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Aircraft inlet lip structure

An air intake and aircraft technology, which is applied to the combustion of the air intake of the power unit, aircraft parts, and power units on the aircraft, etc., can solve the problems of icing on the lip of the air intake port of the aircraft, so as to solve the icing problem and reduce the Structural weight, effect of enhancing structural strength

Active Publication Date: 2019-01-04
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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Problems solved by technology

[0004] The purpose of this application is to provide an aircraft intake lip structure to solve the problem of icing that may occur on the aircraft intake lip

Method used

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Embodiment Construction

[0031] In order to make the purpose, technical solution and advantages of the application more clear, the technical solution in the embodiment of the application will be described in more detail below in conjunction with the drawings in the embodiment 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 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 embodiments in this application, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the scope of protection of this application. Embodiments of the present application will be described in detail below in conjunction...

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Abstract

The present application belongs to the field of aircraft structure, in particular to an aircraft inlet lip structure, which needs to solve the problem of aircraft inlet lip icing. A plurality of partitions are arranged between an outer skin and an inner skin of the airplane inlet lip to form a plurality of heating channels, and a heating gas is introduced into the heating flow channel through an air inlet nozzle (4) and an air outlet nozzle (5) arranged at both ends of each of the heating flow channels, the aircraft inlet lip is heated to solve the problem of icing of the aircraft inlet lip, and the aircraft inlet lip structure of the present invention can be integrally formed by laser selective melting and material addition manufacturing technology to reduce the number of parts and reducethe weight of the structure.

Description

technical field [0001] The application belongs to the field of aircraft structure design, in particular to an aircraft inlet lip structure. Background technique [0002] When the aircraft is flying, due to the influence of the airflow, the air intake lip of the aircraft may experience icing, especially for low Mach number subsonic aircraft, the icing phenomenon is more serious, so the air intake lip structure needs to have anti-icing function, while the traditional design of the air intake lip structure cannot achieve effective deicing. [0003] Therefore, it is desirable to have a technical solution to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art. Contents of the invention [0004] The purpose of this application is to provide an aircraft intake lip structure to solve the problem of possible icing on the aircraft intake lip. [0005] The technical scheme of the application is: [0006] An aircraft intake lip structure, c...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D33/02
CPCB64D33/02B64D2033/0233
Inventor 胡宗浩王向明吴斌苏亚东邢本东
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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