An aircraft front fuselage integral frame structure

A technology of overall frame and front fuselage, which is applied in the direction of fuselage frame, fuselage, aircraft parts, etc., to achieve the effects of shortening the manufacturing cycle, reducing fatigue weak links, and reducing structural weight

Active Publication Date: 2022-02-22
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] In the traditional front fuselage structure, each component part needs to be manufactured separately, and then connected through a large number of connectors such as corner boxes and corner pieces, and fasteners such as bolts, rivets, and pins; it is affected by the shape, surrounding structures and connections. Influenced by restrictive conditions, many details need to be considered in the design, which also brings many negative effects

Method used

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  • An aircraft front fuselage integral frame structure
  • An aircraft front fuselage integral frame structure
  • An aircraft front fuselage integral frame structure

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Embodiment Construction

[0033] 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 application belongs to the field of aircraft structure design, and in particular relates to an integral frame structure of an aircraft front fuselage. To solve the negative impact of the traditional aircraft front fuselage structure, multiple longitudinal girders, transverse reinforcement frames, and longitudinal plates of the overall frame structure of the aircraft front fuselage in the present application are integrally formed, and the surface of the longitudinal girder facing the outside of the aircraft Conformal with the surface of the transverse reinforcement frame facing the outside of the aircraft, the surface of the longitudinal plate and the surface of the longitudinal girder facing the outside of the aircraft, the surface of the longitudinal plate and the surface of the transverse reinforcement frame facing the outside of the aircraft are in the same shape; Significantly reduce structural weight, reduce fatigue weak links, reduce the number of structural parts, standard parts, and tooling, and shorten the manufacturing cycle.

Description

technical field [0001] The application belongs to the field of aircraft structure design, and in particular relates to an integral frame structure of an aircraft front fuselage. Background technique [0002] The metal main load-bearing skeleton structure is the main part of the airframe structure. The large parts of the front fuselage are an important part of the aircraft body platform. And transfer the corresponding load to provide shelter for the pilot. [0003] In the traditional front fuselage structure, each component part needs to be manufactured separately, and then connected through a large number of connectors such as corner boxes and corner pieces, and fasteners such as bolts, rivets, and pins; it is affected by the shape, surrounding structure and connection. Many details need to be considered in the design, which also brings many negative effects. [0004] Therefore, it is desirable to have a technical solution to overcome or at least alleviate at least one of ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C1/06
CPCB64C1/061
Inventor 吴斌胡宗浩王向明陈旭颜苏亚东
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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