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A composite empennage based on h-shaped spar reinforcement, manufacturing method and molding die

A technology of composite materials and forming molds, which is applied in the aviation field, can solve the problems of aircraft structure weight reduction, empennage assembly coordination route complexity, and cost increase, so as to optimize the force transmission route, reduce initial and repeated costs, and improve the yield rate Effect

Active Publication Date: 2022-05-10
NO 60 RES INST OF GENERAL STAFF DEPT PLA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Due to the existence of connecting structures such as metal joints and ear forks, it is not conducive to the weight reduction of the aircraft structure, and it also complicates the coordination of the empennage assembly route. It is necessary to coordinate the assembly through the design of jigs or special tooling, thereby increasing the cost of the product

Method used

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  • A composite empennage based on h-shaped spar reinforcement, manufacturing method and molding die
  • A composite empennage based on h-shaped spar reinforcement, manufacturing method and molding die
  • A composite empennage based on h-shaped spar reinforcement, manufacturing method and molding die

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Embodiment 1

[0031] Such as figure 1 As shown, this embodiment provides a composite material integral empennage based on H-shaped spar reinforcement. The integral empennage adopts a wing-body fusion design scheme, and the fuselage shell is designed as a composite material wing-body integrated structure, and its interior adopts an H-shaped wing Beam reinforcement, the integral empennage and the H-shaped spar take the chord line of the empennage airfoil as the separation surface, and are divided into two parts, the wing body integrated empennage panel with cap ribs.

[0032] Further, the H-shaped spar includes a spar shell and a sandwich layer, and the spar shell includes a vertically symmetrical rib structure with caps in the empennage section, and its cross-sectional shape is an H-shaped structure; It is the upper half and the lower half. The upper half and the lower half are both C-shaped rib structures with caps. The space between the spar shell and the outer skin is filled with a sandwi...

Embodiment 2

[0038] The present application also provides the above-mentioned manufacturing method based on the composite empennage reinforced by the H-shaped spar, the manufacturing method comprising the following steps:

[0039] First, lay the layers of the panel skin in the above-mentioned mold body, lay the layers of the spar shell in the spar block assembly and complete the filling and repair of the foam sandwich layer. Block assemblies with layup and core are positioned together on the mold body and assembled with fasteners;

[0040] Then, remove the connecting bolts and lock nuts of the spar block assembly to ensure that the empennage section block and the fuselage section block are in a free state, and complete the co-curing of the wing-body empennage panel after bag sealing forming;

[0041] Finally, in the closing mould, the wing-body-integrated empennage panel is glued along the separation surface to form an integral empennage.

[0042] Based on the design idea of ​​integrated...

Embodiment 3

[0044] The present embodiment provides the forming mold of the aforementioned integral empennage body panel, such as Figure 5 , Image 6 As shown, the forming mold is composed of a mold body and a spar block assembly. The mold body is used for forming the skin of the wing body and empennage. The spar block assembly is installed in the mold body through fasteners. The spar blocks are used for the layup and co-curing of the spar shells, and are divided into blocks in the wing root area according to the structural characteristics of the spar, and are divided into empennage section blocks and fuselage section blocks. The fuselage block is connected by a quick-release structure to form a wing spar block assembly.

[0045] The aforementioned quick-release structure of the spar block is composed of a connecting seat and a connecting block, the connecting seat is connected with the spar block of the empennage section with a fastener, and the connecting block is connected with the spar...

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Abstract

The invention discloses a composite material integral empennage based on H-shaped spar reinforcement, a manufacturing method and a molding die. The empennage and the fuselage shell are designed as an integral structure, and an H-shaped spar is used inside to enhance the strength of the empennage. The H-shaped empennage The spar runs through the empennage and the tail of the fuselage along the span direction; the empennage and the H-shaped spar take the chord line of the empennage airfoil as the separation surface, and are divided into upper and lower parts of the wing-body integrated empennage plate with cap ribs. The integrated empennage adopts the wing-body fusion scheme, and the empennage and the fuselage are designed as a wing-body integrated structure, which simplifies the assembly and coordination route of the empennage, and does not need to design the empennage assembly frame or special tooling, effectively reducing the initial and repeated costs of the aircraft.

Description

technical field [0001] The invention belongs to the field of aviation technology, and in particular relates to a composite empennage based on an H-shaped spar reinforcement, a manufacturing method and a molding die. Background technique [0002] With the development of technology, composite materials are more and more widely used in aircraft structures, effectively reducing the weight of aircraft structures and prolonging the fatigue life of structures. Increasing the application ratio of advanced composite materials is an important way to improve aircraft performance. The integrated design and molding is one of the important development directions for the application of composite materials in aircraft structures. [0003] At present, the wing-body fusion design is more and more widely used in aircraft design, which can effectively improve the flight performance of the aircraft and reduce the RCS of the aircraft to improve the battlefield survivability. However, the wing-bo...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C5/02B64F5/10B29C70/34B29C70/54B29C33/00B29L31/30
CPCB64C5/02B64F5/10B29C70/342B29C70/54B29C33/00B29L2031/3085Y02T50/40
Inventor 姜其用王晓东夏杨沈浩杰吴佳凯叶柄能姜立武
Owner NO 60 RES INST OF GENERAL STAFF DEPT PLA
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