CN214356633U

CN214356633U - Multi-material composite equal-strength spar

Info

Publication number: CN214356633U
Application number: CN202023305271.8U
Authority: CN
Inventors: 赵铁楠
Original assignee: Liaoning Ruixiang General Aviation Co ltd
Current assignee: Liaoning Ruixiang General Aviation Co ltd
Priority date: 2020-12-31
Filing date: 2020-12-31
Publication date: 2021-10-08
Anticipated expiration: 2030-12-31

Abstract

The utility model discloses a compound uniform strength wing spar of many materials, including the wing spar body, the wing spar body includes that wing inner core alloy board, compound wing outer fringe board and elastic wing follow the rib outward, and wing inner core alloy board is provided with the first protrusion extension board, second protrusion extension board and the third protrusion of a body structure along compound wing outer fringe board length direction and follows the long slab, and it has the rubber layer to fill between compound wing outer fringe board and the wing inner core alloy board. When the model airplane lands, if the wing beam collides with the ground, the wing inner core alloy plate improves the structural strength of the wing beam body and avoids the occurrence of a fracture phenomenon, the elastic wing outer edge rib can effectively buffer the collision force, so that the collision force borne by the composite wing outer edge plate is reduced, and the rubber layer is arranged between the composite wing outer edge plate and the wing inner core alloy plate and can also provide elastic buffering, so that the damage and the deformation of the composite wing outer edge plate are reduced.

Description

Multi-material composite equal-strength spar

Technical Field

The utility model relates to an aircraft wing beam technical field, more specifically say, in particular to compound uniform strength spar of many materials.

Background

With the development of the technology, the composite material is applied more and more in the toy airplane model structure, so that the weight of the toy airplane model can be effectively reduced, and the fatigue life of the structure is prolonged.

However, when the existing toy airplane model flies and lands, the existing toy airplane model is often subjected to air convection, and the wing beam of the existing toy airplane model touches the ground, so that the wing beam is damaged and deformed, and the service life is short.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a compound uniform strength spar of many materials to overcome the defect that prior art exists.

In order to achieve the above purpose, the utility model adopts the following technical scheme:

a multi-material composite equal-strength wing spar comprises a wing spar body, wherein the wing spar body comprises a wing inner core alloy plate, a composite wing outer edge plate and an elastic wing outer edge rib, the composite wing outer edge plate is positioned on the outer side of the wing inner core alloy plate, the wing inner core alloy plate is provided with a first protruding extension plate, a second protruding extension plate and a third protruding edge long plate which are of an integrated structure along the length direction of the composite wing outer edge plate, a rubber layer is filled between the composite wing outer edge plate and the wing inner core alloy plate, the upper end and the lower end of one side surface of the wing inner core alloy plate are provided with integrally-structured convex ribs, the composite wing outer edge plate is fixedly connected with the protruding rib at the corresponding position through a bolt, a hard edge plate is fixedly mounted at one end of the outer edge rib of the elastic wing, a protruding block is fixedly mounted on one side of the hard edge plate, and the protruding block is fixedly inserted into one end of the outer edge plate of the composite wing far away from the position of the inner core alloy plate of the wing.

Further, the wing core alloy plate, the first protruding extension plate, the second protruding extension plate and the third protruding are sequentially reduced along the thickness of the long plate.

Furthermore, alloy columns are fixedly inserted in the middle of the wing inner core alloy plate, the first protruding extension plate, the second protruding extension plate and the third protruding edge long plate, and the wing inner core alloy plate, the first protruding extension plate, the second protruding extension plate and the third protruding edge long plate are fixedly welded with the composite wing outer edge plate through the alloy columns.

Furthermore, a pin shaft is inserted in the middle of the protruding block, and the protruding block is fixedly connected with the outer edge plate of the composite wing through the pin shaft.

Furthermore, the outer edge rib of the elastic wing is of a wear-resistant rubber material structure.

Furthermore, a protruding installation socket is fixedly arranged on one side, away from the outer edge rib position of the elastic wing, of the wing core alloy plate, the protruding installation socket and the wing core alloy plate are of an integral structure, and a threaded hole is formed in the surface of the protruding installation seat.

Compared with the prior art, the utility model has the advantages of:

when the model airplane is in landing, if the wing spar collides with the ground, the wing core alloy plate is provided with the first protruding extension plate, the second protruding extension plate and the third protruding extension plate of an integrated structure along the length direction of the composite wing outer edge plate, the structural strength of the wing spar body is improved, when the wing spar collides with the ground, the phenomenon of breakage is avoided, the elastic wing outer edge rib can effectively buffer the collision force, so that the collision force borne by the composite wing outer edge plate is reduced, and because the rubber layer is arranged between the composite wing outer edge plate and the wing core alloy plate, the rubber layer also can provide elastic buffering, so that the damage and the deformation of the composite wing outer edge plate are reduced.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.

FIG. 1 is a block diagram of a multi-material composite equal strength spar of the present invention;

fig. 2 is an enlarged schematic view of the structure at a in fig. 1.

In the figure: the composite wing comprises a wing inner core alloy plate 1, a rubber layer 2, a composite wing outer edge plate 3, a protruding rib 4, a protruding mounting socket 5, a first protruding extension plate 6, a second protruding extension plate 7, a third protruding extension plate 8, an alloy column 9, an elastic wing outer edge rib 10, a hard edge plate 11, a protruding block 12 and a pin shaft 13.

Detailed Description

The preferred embodiments of the present invention will be described in detail below with reference to the accompanying drawings, so that the advantages and features of the present invention can be more easily understood by those skilled in the art, and the scope of the present invention can be more clearly and clearly defined.

Referring to fig. 1 and 2, the utility model provides a multi-material composite equal-strength wing spar, which comprises a wing spar body, wherein the wing spar body comprises a wing inner core alloy plate 1, a composite wing outer edge plate 3 and an elastic wing outer edge rib 10, the composite wing outer edge plate 3 is positioned at the outer side of the wing inner core alloy plate 1, the wing inner core alloy plate 1 is provided with a first convex extension plate 6, a second convex extension plate 7 and a third convex edge long plate 8 which are of an integrated structure along the length direction of the composite wing outer edge plate 3, the structural strength of the wing spar body 1 is improved, when the wing inner core alloy plate 1 collides with the ground, the wing spar outer edge plate 3 is prevented from being broken, a rubber layer 2 is filled between the composite wing outer edge plate 3 and the wing inner core alloy plate 1, the upper end and the lower end of one side surface of the wing inner core alloy plate 1 are both provided with convex ribs 4 of an integrated structure, the composite wing outer edge plate 3 is fixedly connected with the convex ribs 4 at the corresponding positions through bolts, one end of the outer edge rib 10 of the elastic wing is fixedly provided with a hard edge plate 11, one side of the hard edge plate 11 is fixedly provided with a convex block 12, and the convex block 12 is fixedly inserted into one end of the outer edge plate 3 of the composite wing far away from the position of the inner core alloy plate 1 of the wing.

In this embodiment, the thickness of the wing core alloy plate 1, the first protruding extension plate 6, the second protruding extension plate 7, and the third protruding extension plate 8 decreases in order.

In this embodiment, alloy columns 9 are fixedly inserted in the middle of the wing core alloy plate 1, the first protruding extension plate 6, the second protruding extension plate 7 and the third protruding edge long plate 8, and the wing core alloy plate 1, the first protruding extension plate 6, the second protruding extension plate 7 and the third protruding edge long plate 8 are fixedly welded to the composite wing outer edge plate 3 through the alloy columns 9, so that the strength of connection with the composite wing outer edge plate 3 is improved.

In this embodiment, a pin shaft 13 is inserted in the middle of the protruding block 12, and the protruding block 12 is fixedly connected with the composite wing outer edge plate 3 through the pin shaft 13.

In this embodiment, the outer edge rib 10 of the elastic wing is made of wear-resistant rubber, so that the impact force can be effectively buffered, and the damage can not be caused.

In this embodiment, a protruding installation socket 5 is fixedly arranged on one side of the wing core alloy plate 1 away from the outer edge rib 10 of the elastic wing, the protruding installation socket 5 and the wing core alloy plate 1 are of an integral structure, a threaded hole is formed in the surface of the protruding installation seat 5, and the protruding installation socket 5 is used for fixedly installing the wing spar on the machine body.

When the model airplane lands, if the wing beam collides with the ground, the outer edge rib 10 of the elastic wing can effectively buffer the collision force, so that the collision force borne by the outer edge plate 3 of the composite wing is reduced, and the rubber layer 2 is arranged between the outer edge plate 3 of the composite wing and the inner core alloy plate 1 of the wing, so that the rubber layer 2 can also provide elastic buffering, and the damage and the deformation of the outer edge plate 3 of the composite wing are reduced.

Although the embodiments of the present invention have been described with reference to the accompanying drawings, various changes and modifications can be made by the owner within the scope of the appended claims, and the protection scope of the present invention should not be exceeded by the claims.

Claims

1. The utility model provides a multi-material composite's constant strength spar, includes the spar body, its characterized in that: the wing spar body comprises a wing inner core alloy plate, a composite wing outer edge plate and an elastic wing outer edge rib, the composite wing outer edge plate is located on the outer side of the wing inner core alloy plate, the wing inner core alloy plate is provided with a first protruding extension plate, a second protruding extension plate and a third protruding edge extension plate which are of an integrated structure along the length direction of the composite wing outer edge plate, a rubber layer is filled between the composite wing outer edge plate and the wing inner core alloy plate, protruding ribs of the integrated structure are arranged at the upper end and the lower end of the surface of one side of the wing inner core alloy plate, the composite wing outer edge plate is fixedly connected with the protruding ribs corresponding to the positions through bolts, one end of the elastic wing outer edge rib is fixedly provided with a hard edge plate, a protruding block is fixedly installed on one side of the hard edge plate, and the protruding block is fixedly inserted into one end of the composite wing outer edge plate, which is far away from the wing inner core alloy plate.

2. The multi-material composite equal strength spar of claim 1, wherein: the wing core alloy plate, the first protruding extension plate, the second protruding extension plate and the third protruding are sequentially reduced along the thickness of the long plate in sequence.

3. The multi-material composite equal strength spar of claim 1, wherein: alloy columns are fixedly inserted in the middle of the wing inner core alloy plate, the first protruding extension plate, the second protruding extension plate and the third protruding edge long plate, and the wing inner core alloy plate, the first protruding extension plate, the second protruding extension plate and the third protruding edge long plate are fixedly welded with the composite wing outer edge plate through the alloy columns.

4. A multi-material composite equal strength spar according to claim 3, wherein: and a pin shaft is inserted in the middle of the protruding block, and the protruding block is fixedly connected with the outer edge plate of the composite wing through the pin shaft.

5. The multi-material composite equal strength spar of claim 1, wherein: the outer edge rib of the elastic wing is of a wear-resistant rubber material structure.

6. The multi-material composite equal strength spar of claim 5, wherein: one side of the wing core alloy plate, which is far away from the outer edge rib position of the elastic wing, is fixedly provided with a convex mounting socket, the convex mounting socket and the wing core alloy plate are of an integral structure, and the convex mounting seat surface is provided with a threaded hole.