A runway-type composite material structure applying a reinforcing ring layer and a manufacturing method thereof

Abstract

The present invention provides a runway - type composite material structure applying a reinforcing ring layer and a manufacturing method. The composite material structure includes a number of reinforcing ring layers and normal plies. One reinforcing ring layer and two normal plies are alternately laid. The reinforcing ring layer is a ring - shaped structure with horizontal upper and lower edges in the middle and semi - circles on both sides. The inner arcs of the two semi - circles are the openings. The relationship between the length L of the reinforcing ring layer and the opening diameter r is: L≥7r. The relationship between the radius of gyration R of the reinforcing ring layer and the opening diameter r is: R≥2r. It solves the problem that since the transverse tensile strength and inter - layer shear strength of the composite material are one order of magnitude lower than the longitudinal tensile strength, it is difficult to meet the design requirements at the opening. The present invention changes the way that the opening bears load relying on the transverse tensile strength and inter - layer shear strength. At the opening, the continuous fiber cloth is precisely arranged around the hole by means of a special - shaped reinforcing ring, maximizing the longitudinal tensile strength of the fiber and perfectly solving the problem of mechanical weakness at the opening.

Description

Technical Field

[0001] The present invention relates to a runway - type composite material structure applying a reinforcing ring layer and a manufacturing method, belonging to the technical field of composite materials. Background Art

[0002] With the continuous improvement of the performance of advanced materials and the enhancement of the design and manufacturing process capabilities of composite material structures, the proportion of the application of composite material structures in the aerospace field is increasing day by day. Due to the anisotropic characteristics of composite materials themselves, there are huge performance differences in different directions. Only by making full use of the designability of fiber composite materials in different directions can the performance of materials be maximally exerted. The opening and reinforcement of composite material structures are one of the calculation difficulties. Especially for large - scale structural parts, the fibers at the end of the composite material have been cut off, but this is often the load - bearing part connected to the next part. It is necessary to connect the two parts with bolts through the opening. During the application of tensile load, since the opening is not composed of continuous fibers, the load - bearing can only be ensured by the transverse tensile strength and interlaminar shear strength. Since the transverse tensile strength and interlaminar shear strength of composite materials are one order of magnitude lower than the longitudinal tensile strength, it is very difficult for the opening to meet the design requirements. Summary of the Invention

[0003] In order to solve the problem mentioned in the above - mentioned background art that due to the fact that the transverse tensile strength and interlaminar shear strength of composite materials are one order of magnitude lower than the longitudinal tensile strength, it is very difficult for the opening to meet the design requirements, the present invention proposes a runway - type composite material structure applying a reinforcing ring layer and a manufacturing method.

[0004] The present invention proposes a runway - type composite material structure applying a reinforcing ring layer, which includes a plurality of reinforcing ring layers and normal plies. One reinforcing ring layer and two normal plies are alternately laid. The reinforcing ring layer is a ring - shaped structure with the upper and lower edges in the middle being horizontal and the two sides being semi - circles. The inner arcs of the two semi - circles are the openings.

[0005] The relationship between the length L of the reinforcing ring layer and the opening diameter r is: L≥7r.

[0006] The relationship between the radius of gyration R of the reinforcing ring layer and the opening diameter r is: R≥2r.

[0007] The relationship between the total distribution thickness D of the reinforcing ring layer and the opening depth d is:

[0008] The manufacturing method of the runway - type composite material structure applying a reinforcing ring layer is as follows: when forming the composite material layer, accurately place the reinforcing ring layer at the opening position, determine the required thickness of the reinforcing ring layer according to the calculated strength required for the opening, and design the laying interval levels of the normal plies. After laying, cure and integrally form.

[0009] The beneficial effects of the runway - type composite material structure and manufacturing method using a reinforcing ring layer according to the present invention are as follows:

[0010] 1. For the runway - type composite material structure and manufacturing method using a reinforcing ring layer according to the present invention, it changes the way that the opening bears load relying on transverse tensile strength and inter - laminar shear strength. At the opening, continuous fiber cloth is precisely arranged around the hole in the form of a special - shaped reinforcing ring, and it will not be cut during machining, maximizing the longitudinal tensile strength of the fiber, avoiding the weaknesses of the composite material, and being able to perfectly solve the problem of mechanical weakness at the opening. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation to the present invention.

[0012] In the drawings:

[0013] Figure 1 is a schematic diagram of the lay - up method of a conventional composite material structure and the stress state of the composite material in the prior art, where the horizontal arrows all represent the stress directions;

[0014] Figure 2 is a cross - sectional schematic diagram of the lay - up method of a conventional composite material structure in the prior art;

[0015] Figure 3 is a schematic diagram of the lay - up method of the runway - type composite material using a reinforcing ring layer according to the present invention and the stress state of the composite material, where the horizontal arrow represents the stress direction, L represents the length of the reinforcing ring layer, r represents the opening diameter of the reinforcing ring layer, and R represents the radius of gyration of the reinforcing ring layer;

[0016] Figure 4 is a cross - sectional schematic diagram of the lay - up method of the runway - type composite material structure using a reinforcing ring layer according to the present invention, where D represents the total thickness of the composite material and d represents the distribution opening depth of the reinforcing ring layer;

[0017] Figure 5 is a schematic diagram of the structure of the annular reinforcing layer according to the present invention;

[0018] Among them, 1 - bolt or opening position, 2 - bolt, 3 - normal lay - up, 4 - annular reinforcing layer. DETAILED DESCRIPTION OF THE INVENTION

[0019] The following further describes in detail the specific embodiments of the present invention with reference to the drawings:

[0020] Specific Embodiment 1: Refer to Figures 1-5Describe this embodiment. The runway-shaped composite material structure applying the reinforcing ring layer includes a plurality of reinforcing ring layers 4 and a plurality of normal laying layers 3. One reinforcing ring layer 4 and two normal laying layers 3 are alternately laid. The reinforcing ring layer 4 is a ring-shaped structure with parallel upper and lower sides in the middle and semi-circular sides on both sides. The inner arcs of the two semi-circles are the openings.

[0021] The relationship between the length L of the reinforcing ring layer 4 and the opening diameter r is: L≥7r.

[0022] The relationship between the radius of gyration R of the reinforcing ring layer 4 and the opening diameter r is: R≥2r.

[0023] The relationship between the total thickness D of the composite material and the distributed opening depth d of the reinforcing ring layer 4 is:

[0024] The runway-shaped composite material structure applying the reinforcing ring layer changes the way of relying on transverse tensile strength and interlaminar shear strength for opening bearing. By means of a special-shaped reinforcing ring at the opening, continuous fiber cloth is accurately arranged around the hole and will not be cut during machining, maximizing the longitudinal tensile strength of the fiber and avoiding the weaknesses of the composite material, and can perfectly solve the problem of mechanical weakness at the opening.

[0025] The manufacturing method of the runway-shaped composite material structure applying the reinforcing ring layer is that when forming the composite material structure, the reinforcing ring layer 4 is accurately laid at the opening position, the thickness of the required reinforcing ring layer 4 is determined according to the calculated strength required for the opening, and the laying interval levels of the normal laying layer 3 are designed. After laying, it is cured and integrally formed.

[0026] The above specific embodiments have further detailed the purpose, technical solution and beneficial effects of the present invention. It should be understood that the above are only specific embodiments of the present invention and are not used to limit the present invention. It can also be a reasonable combination of the features described in the above various embodiments. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A runway - type composite material structure applying a reinforcing ring layer, characterized in that, It includes a number of reinforcing ring layers (4) and a number of normal laying layers (3), where one reinforcing ring layer (4) and two normal laying layers (3) are alternately laid. The reinforcing ring layer (4) is a ring structure with parallel upper and lower sides in the middle and semi-circular sides on both sides. The inner arcs of the two semi-circles are the openings. The relationship between the length L of the reinforcing ring layer (4) and the opening diameter r is: L≥7r. The relationship between the radius of gyration R of the reinforcing ring layer (4) and the opening diameter r is: R≥2r. The relationship between the total thickness D of the composite material and the distributed opening depth d of the reinforcing ring layer (4) is as follows:

2. A manufacturing method of a runway - type composite material structure applying a reinforcing ring layer as described in claim 1, characterized in that, When forming the composite material structure, the reinforcing ring layer (4) is precisely laid at the opening position. The thickness of the required reinforcing ring layer (4) is determined according to the calculated strength required for the opening, and the laying interval levels of the normal laying layer (3) are designed. After laying, it is cured and integrally formed.

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