CN218317337U - Double-beam type support of airplane - Google Patents
Double-beam type support of airplane Download PDFInfo
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- CN218317337U CN218317337U CN202222674348.1U CN202222674348U CN218317337U CN 218317337 U CN218317337 U CN 218317337U CN 202222674348 U CN202222674348 U CN 202222674348U CN 218317337 U CN218317337 U CN 218317337U
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Abstract
The application provides an aircraft double-beam type support, which comprises an upper supporting surface, wherein a left mounting surface and a right mounting surface are vertically arranged on two sides of the upper supporting surface, two longitudinal beam webs arranged at intervals extend between the left mounting surface and the right mounting surface, one or more reinforcing ribs are arranged on the longitudinal beam webs along the front-back direction, hinge support holes are formed in matched positions of the two longitudinal beam webs, and a double-lug-piece type hinge support is formed in the positions of the hinge support holes; the left mounting surface and the right mounting surface of the airplane double-beam support are fixed on an engine body structure through a left structural framework and a right structural framework respectively, and the hinge support is hinged with an end shaft of the actuating cylinder through a bolt. The application provides an aircraft twin-beam formula support structural style is novel, the location is simple, simple to operate is swift, can be fast effectual will exert concentrated load transmit away, reduce stress concentration and sudden change to rigidity is better, simple to operate is swift.
Description
Technical Field
The application relates to the technical field of airplane structure design, in particular to an airplane double-beam type support.
Background
An aircraft Ram Air Turbine (RAT) pedestal is fixed in a RAT cabin, and the pedestal needs to be fixed to an aircraft main structure. The fixed supporting surface of the support is parallel to the end shaft of the RAT actuating cylinder, so that wind resistance applied to the end part of the RAT actuating cylinder is converted into concentrated load on the supporting structure and is quickly and effectively transmitted to a main structure of the airplane, and the structural form of the support is particularly important. The existing aircraft RAT support has poor force transmission efficiency and weak bearing capacity.
Disclosure of Invention
It is an object of the present application to provide an aircraft dual beam abutment that solves or mitigates at least one of the problems of the background art.
The technical scheme of the application is as follows: the airplane double-beam support comprises an upper supporting surface, wherein a left mounting surface and a right mounting surface are vertically arranged on two sides of the upper supporting surface, two longitudinal webs arranged at intervals extend between the left mounting surface and the right mounting surface, one or more reinforcing ribs are arranged on the longitudinal webs along the front-back direction, hinge support holes are formed in matched positions of the two longitudinal webs, and a double-lug-piece type hinge support is formed in the positions of the hinge support holes;
the left mounting surface and the right mounting surface of the airplane double-beam support are fixed on an engine body structure through a left structural framework and a right structural framework respectively, and the hinge support is hinged with an end shaft of the actuating cylinder through a bolt.
Further, the left mounting surface and the right mounting surface are parallel to each other.
Furthermore, the left mounting surface and the right mounting surface are symmetrical.
Further, the distance between the left mounting surface and the right mounting surface is not less than the thickness of the end shaft of the actuating cylinder.
Further, the left mounting surface and the right mounting surface are mounted on the left structural framework and the right structural framework through connecting pieces.
Furthermore, the reinforcing ribs are distributed on two sides of each longitudinal beam web.
Furthermore, the number of the reinforcing ribs distributed on the outer side of the longitudinal beam web plate is larger than that of the reinforcing ribs distributed on the inner side of the longitudinal beam web plate.
Furthermore, reinforcing ribs distributed on the inner side of the longitudinal web plate are connected with the two longitudinal web plates.
Further, bushings are mounted in the two lugs of the hinge support.
The application provides an aircraft twin-beam formula support structural style is novel, the location is simple, simple to operate is swift, can be fast effectual will exert concentrated load transmit away, reduce stress concentration and sudden change to rigidity is better, simple to operate is swift.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a schematic view of an aircraft dual beam pedestal mounting structure of the present application.
Fig. 2 is a schematic structural diagram of a front surface of an aircraft double-beam support of the present application.
Fig. 3 is a schematic view of the bottom surface structure of the dual beam pedestal of the aircraft of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
As shown in fig. 1 to 3, the aircraft dual beam type cradle 2 provided by the present application includes an upper supporting surface 21, a left mounting surface 22 and a right mounting surface 23 arranged along a vertical direction Z are provided on both sides of the upper supporting surface 21, two longitudinal webs 24 arranged at intervals extend between the left mounting surface 22 and the right mounting surface 23, one or more reinforcing ribs 25 are provided on the longitudinal webs 24 along a front-back direction X, matching hinge cradle holes 26 are provided on the two longitudinal webs 24, and a double-lug plate type hinge cradle 27 is formed at the position of the hinge cradle hole 26.
During installation, the double-beam support 2 of the airplane is installed in the RAT cabin, the left installation surface 22 and the right installation surface 23 on the left side and the right side of the double-beam support are respectively fixed on an airframe structure through the left structure framework 1 and the right structure framework 4, the double-beam support 2 of the airplane extends along the transverse Y direction and is longer, and the transmission of the Y direction concentrated loads is facilitated through the installation of a plurality of fasteners. The structural form of a reinforcing rib 25 extending from front to back X and a transverse Y-shaped longitudinal beam web plate 24 is arranged in the airplane double-beam type support 2, the supporting rigidity of the airplane double-beam type support is improved, a hinge support 27 is formed at the lower end of the airplane double-beam type support through two lug plates on the two longitudinal beam web plates 24 and is installed with the end shaft 3 of the actuating cylinder in a matching mode through hinge bolts, support is provided for the RAT actuating cylinder in the actuating process, and the front-back and transverse reinforcing structures provide supporting rigidity for the support and reduce stress concentration and mutation.
In the present application, the left mounting surface 22 and the right mounting surface 23 are two parallel surfaces. The distance between the left mounting surface 22 and the right mounting surface 23 is not less than the thickness of the ram end shaft 3.
Further, the left mounting surface 22 and the right mounting surface 23 may be two symmetrical surfaces, and the left mounting surface 22 and the right mounting surface 23 may be mounted to the left structural framework 1 and the right structural framework 4 by using a connector such as a bolt or a rivet.
In the preferred embodiment of the present application, the reinforcing ribs 25 may be distributed on both sides of each longitudinal spar web 24. For example, in the embodiment of fig. 3 of the present application, each longitudinal web 24 has three stiffening ribs 25 on the outside and one stiffening rib 25 on the inside of the longitudinal web 24, the stiffening ribs 25 connecting the two longitudinal webs 24.
In the preferred embodiment of the present application, bushings are mounted in the two ears of the hinge mount 27 for centering and wear protection.
In the preferred embodiment of the present application, the dual beam type airplane support 2 can be made of a light metal material, such as an aluminum alloy or a titanium alloy material.
The application provides an aircraft twin-beam formula support structural style is novel, the location is simple, simple to operate is swift, can be fast effectual will exert concentrated load transmit away, reduce stress concentration and sudden change to rigidity is better, simple to operate is swift.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (9)
1. The airplane double-beam support is characterized by comprising an upper supporting surface, wherein a left mounting surface and a right mounting surface which are vertically arranged are arranged on two sides of the upper supporting surface, two longitudinal beam webs which are arranged at intervals extend between the left mounting surface and the right mounting surface, one or more reinforcing ribs are arranged on the longitudinal beam webs along the front-back direction, hinge support holes are formed in matched positions of the two longitudinal beam webs, and a double-lug-piece type hinge support is formed in the positions of the hinge support holes;
the left mounting surface and the right mounting surface of the airplane double-beam support are fixed on an engine body structure through a left structural framework and a right structural framework respectively, and the hinge support is hinged with an end shaft of the actuating cylinder through a bolt.
2. An aircraft dual beam carrier as defined in claim 1, wherein said left and right mounting surfaces are parallel to each other.
3. An aircraft dual beam carrier as claimed in claim 2, wherein said left and right mounting faces are bilaterally symmetrical.
4. An aircraft dual beam mount according to any one of claims 1 to 3 wherein the spacing between said left and right mounting faces is not less than the thickness of the ram end shaft.
5. An aircraft dual beam carrier as claimed in claim 4, wherein said left and right mounting faces are mounted to said left and right structural frames by connectors.
6. An aircraft twin beam abutment as defined in claim 1 in which the reinforcing ribs are distributed on both sides of each longitudinal web.
7. An aircraft dual beam abutment as claimed in claim 6, wherein the number of ribs distributed outboard of said longitudinal web is greater than the number of ribs distributed inboard of said longitudinal web.
8. An aircraft dual beam abutment as claimed in claim 7, wherein reinforcing ribs distributed on the inner side of said longitudinal beam webs connect two of said longitudinal beam webs.
9. An aircraft dual beam mount as defined in claim 1 wherein bushings are mounted within both ears of said hinge mount.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222674348.1U CN218317337U (en) | 2022-10-11 | 2022-10-11 | Double-beam type support of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222674348.1U CN218317337U (en) | 2022-10-11 | 2022-10-11 | Double-beam type support of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218317337U true CN218317337U (en) | 2023-01-17 |
Family
ID=84823812
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222674348.1U Active CN218317337U (en) | 2022-10-11 | 2022-10-11 | Double-beam type support of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218317337U (en) |
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2022
- 2022-10-11 CN CN202222674348.1U patent/CN218317337U/en active Active
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