CN213472266U

CN213472266U - Runway type composite material structure applying reinforcing ring layer

Info

Publication number: CN213472266U
Application number: CN202022238858.5U
Authority: CN
Inventors: 侯传礼; 吴伟萍; 魏程; 杜政才
Original assignee: Harbin FRP Institute Co Ltd
Current assignee: Harbin FRP Institute Co Ltd
Priority date: 2020-10-10
Filing date: 2020-10-10
Publication date: 2021-06-18
Anticipated expiration: 2030-10-10

Abstract

The utility model provides an use runway formula combined material structure on reinforcement ring layer, this combined material structure include a plurality of reinforcement ring layers and normally spread the layer, and wherein one deck reinforcement ring layer and two-layer normal layer are spread in turn and are laid, and the reinforcement ring layer is middle upper and lower level both sides each other and are semicircular ring structure, and two semicircular inner arcs are the trompil promptly, and the length L on reinforcement ring layer is to the relational expression of trompil diameter r: l is more than or equal to 7R, the turning radius R of the reinforcing ring layer is the relation of the diameter R of the split hole: r is more than or equal to 2R. The invention solves the problem that the transverse tensile strength and the interlaminar shear strength of the composite material are lower by one order of magnitude than the longitudinal tensile strength, and the opening is difficult to meet the design requirement.

Description

Runway type composite material structure applying reinforcing ring layer

Technical Field

The utility model relates to an use runway formula combined material structure on reinforcement ring layer belongs to combined material technical field.

Background

With the continuous improvement of the performance of advanced materials and the improvement of the structural design and manufacturing process capability of composite materials, the proportion of the composite material structure in the aerospace field is increasing day by day. Due to the characteristic of anisotropy of the composite material, the performance difference in all directions is huge, and the performance of the material can be exerted to the maximum extent only by fully utilizing the designability of the fiber composite material in the directions. The opening and reinforcement of the composite material structure are one of the difficulties in calculation, particularly, fibers in the composite material at the end part of a large structural member are cut off, but the fiber is often a bearing part connected with the next part, the two parts need to be connected through the opening by using bolts, in the process of applying tensile load, the bearing force at the opening can only be ensured by the transverse tensile strength and the interlaminar shear strength because the opening is not continuous fibers, and the transverse tensile strength and the interlaminar shear strength of the composite material are lower by one order of magnitude than the longitudinal tensile strength, so that the opening is difficult to meet the design requirements.

SUMMERY OF THE UTILITY MODEL

The utility model discloses a solve mention among the above-mentioned background art because the transverse tensile strength of combined material and the lower order of magnitude of longitudinal tensile strength of interlaminar shear strength, the opening part hardly satisfies the problem of designing requirement, provides a runway formula combined material structure of using reinforcement ring layer.

The utility model provides a runway type composite material structure applying reinforcing ring layers, which comprises a plurality of reinforcing ring layers and normal layers, wherein one layer of reinforcing ring layer and two layers of normal layers are alternately laid, the reinforcing ring layer is a ring structure with the upper and lower edges in the middle horizontal mutually and the two sides are semicircles, the inner arcs of the two semicircles are open holes,

the length L of the reinforcing ring layer is expressed by the following relation of the opening diameter r: l is more than or equal to 7r,

the radius of gyration R of reinforcement ring layer is to trompil diameter R relational expression: r is more than or equal to 2R,

the relation of the total distribution thickness D of the reinforcing ring layers to the depth D of the open hole is as follows:

use runway formula combined material structure on reinforcement ring layer beneficial effect do:

1. use runway formula combined material structure on reinforcement ring layer, changed the opening and born the weight of the mode that leans on horizontal tensile strength and interlaminar shear strength, the mode that passes through heterotypic reinforcement ring at the opening part will be continuous fiber cloth accurate arrange around the hole, machine man-hour is not cut off, fibrous vertical tensile strength of at utmost performance avoids combined material's weak point, can perfectly solve the weak problem of opening part mechanics.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this application, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification.

In the drawings:

FIG. 1 is a schematic diagram of a layering mode of a conventional composite material structure and a stress state of a composite material in the prior art, wherein horizontal arrows indicate stress directions;

FIG. 2 is a schematic cross-sectional view of a prior art conventional composite structure layup approach;

fig. 3 is a schematic diagram of a layer laying mode and a stress state of a composite material of a runway composite material using a reinforcement ring layer according to the present invention, wherein a horizontal arrow indicates a stress direction, L indicates a length of the reinforcement ring layer, R indicates a hole diameter of the reinforcement ring layer, and R indicates a turning radius of the reinforcement ring layer;

fig. 4 is a schematic cross-sectional view of a layer laying manner of a racetrack composite structure using a reinforcing ring layer according to the present invention, wherein D represents a total thickness of the composite material, and D represents a distribution opening depth of the reinforcing ring layer;

FIG. 5 is a schematic structural view of the annular reinforcing layer according to the present invention;

wherein, 1-bolt or open pore position, 2-bolt, 3-normal layer and 4-annular reinforcing layer.

Detailed Description

The following detailed description of the embodiments of the present invention is provided with reference to the accompanying drawings:

the first embodiment is as follows: the present embodiment is explained with reference to fig. 1 to 5. The runway type composite material structure applying the reinforcing ring layers comprises a plurality of reinforcing ring layers 4 and a plurality of normal layers 3, wherein one layer of reinforcing ring layer 4 and two layers of normal layers 3 are alternately laid, the reinforcing ring layer 4 is an annular structure with the upper and lower edges in the middle parallel to each other and two sides as semicircles, the inner arcs of the two semicircles are openings,

the length L of the reinforcing ring layer 4 is expressed by the following relation of the opening diameter r: l is more than or equal to 7r,

the radius of gyration R of reinforcement ring layer 4 is to trompil diameter R relational expression: r is more than or equal to 2R,

the relation of the total thickness D of the composite material to the distribution opening depth D of the reinforcing ring layer 4 is as follows:

the runway type composite material structure with the reinforcing ring layer is applied, the mode that the opening bears the load of the transverse tensile strength and the interlaminar shear strength is changed, the continuous fiber cloth is accurately arranged around the hole in the opening through the mode of the special-shaped reinforcing ring, the continuous fiber cloth is not cut off during machining, the longitudinal tensile strength of the fiber is exerted to the maximum extent, the weakness of the composite material is avoided, and the problem of mechanical weakness of the opening can be perfectly solved.

The manufacturing method of the runway type composite material structure applying the reinforcing ring layer comprises the steps of accurately laying the reinforcing ring layer 4 at the position of the hole when the composite material structure is formed, determining the thickness of the required reinforcing ring layer 4 according to the strength required by calculating the opening, designing the laying interval layer of the normal laying layer 3, and curing and integrally forming after laying is completed.

The above-mentioned embodiments further explain the objects, technical solutions and advantages of the present invention in detail. It should be understood that the above description is only exemplary of the present invention, and is not intended to limit the present invention, and that any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention may be made without departing from the scope of the present invention.

Claims

1. A runway type composite material structure applying reinforcement ring layers is characterized by comprising a plurality of reinforcement ring layers (4) and a plurality of normal layers (3), wherein one layer of reinforcement ring layer (4) and two layers of normal layers (3) are alternately laid, the reinforcement ring layer (4) is an annular structure with upper and lower sides in the middle parallel to each other and two sides in a semicircle shape, the inner arcs of the two semicircles are openings,

the length L of the reinforcing ring layer (4) is in a relation formula with the opening diameter r as follows: l is more than or equal to 7r,

the radius of gyration R of reinforcement ring layer (4) is to trompil diameter R relational expression: r is more than or equal to 2R,

the relation of the total thickness D of the composite material to the distribution opening depth D of the reinforcing ring layer (4) is as follows: