Limiting structure
By designing a limiting structure including the first rib plate, the second rib plate, the limiting pin and the bearing, the problem that the vertical scissor difference cannot be effectively limited at the small gaps in the prior art is solved, and the effective release of the aircraft's spreading extrusion or tensile deformation is achieved, and the installation space is small.
Patent Information
- Application Number
- CN202420905330.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-04-28
- Publication Date
- 2025-06-20
- Estimated Expiration
- 2034-04-28
AI Technical Summary
In the existing aircraft structural design, the components at the docking surface of the aircraft will have a scissor difference under the aerodynamic action. The existing pull rod limit structure requires a wide expansion gap, which cannot effectively limit the vertical scissor difference at the small gap.
A limiting structure is designed, including a first rib, a second rib, a limiting pin and a bearing. The limiting pin is sleeved in the inner ring of the bearing to limit the parallel displacement between the first rib and the second rib, and is suitable for applications at small gaps.
This limiting structure can effectively limit the vertical scissor difference between the components on both sides of the aircraft's docking surface, release the aircraft's expansion extrusion or tensile deformation, and the required installation space is small.
Smart Images
Figure CN223001674U_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the technical field of aircraft structure design, and particularly relates to a limiting structure. Background Art
[0002] In the existing aircraft structure design technology, at the aircraft docking surface, there is lateral deformation extrusion between the components on both sides. The direction perpendicular to the web surface of the vertical rib is the lateral direction, and it is necessary to disconnect at the docking surface. At this time, there will be a shear difference between the components on both sides under the action of aerodynamic force, and a structure is needed to limit the shear difference between the components on both sides.
[0003] Currently, the widely used is the tie rod limiting structure, but this limiting structure requires a relatively wide lateral gap to be used. When the lateral gap is too small, a new limiting structure is needed. Utility Model Content
[0004] To solve the above problems, this application provides a limiting structure, including:
[0005] A first rib, a second rib parallel to the first rib and having a gap, a limiting pin with an axis perpendicular to the first rib and installed on the first rib, and a bearing installed on the second rib. The limiting pin is sleeved in the inner ring of the bearing and is used to limit the displacement parallel to the direction of the first rib and the second rib.
[0006] Preferably, the second rib has a mounting hole, and the mounting hole is used to install a bearing seat for installing the bearing.
[0007] Preferably, one end of the limiting pin has a mounting disc, and the mounting disc has a plurality of bolt holes. The first rib has a mounting table surface corresponding to the mounting disc, and the mounting table surface has a plurality of threaded holes corresponding to the bolt holes. A bolt assembly passes through the bolt holes to fix the mounting disc on the mounting table surface.
[0008] Preferably, the first rib has reinforcing rib strips, and the mounting table surface has radial rib strips connected to the reinforcing rib strips.
[0009] Preferably, the bearing and the bearing seat are a press-fitted bearing assembly.
[0010] Preferably, the bearing seat is in a cylindrical shape, and its outer wall has a plurality of mounting lugs. Bolts pass through the ear holes of the mounting lugs to fix the bearing seat on the second rib.
[0011] Preferably, the first rib and the second rib are in a triangular plate shape, and the plate surface has a plurality of intersecting reinforcing rib strips.
[0012] The advantages of the present application include: The present application is installed at a position with a small space gap between the components on both sides of the aircraft docking surface, which can limit the vertical shear difference between the first rib and the second rib, release the lateral extrusion or tensile deformation of the aircraft, and requires a small installation space. Description of the Drawings
[0013] Figure 1 is a sectional view of the limit structure of a preferred embodiment of the present application;
[0014] Figure 2 is an installation view of the limit structure of a preferred embodiment of the present application;
[0015] Figure 3 is a split view of the limit structure of a preferred embodiment of the present application. Detailed Embodiment
[0016] To make the purpose, technical solution and advantages of the implementation 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 accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, of the embodiments of the present application. The embodiments described below by referring to the drawings are exemplary and are intended to explain the present application and should not be construed as limiting the present application. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present application without creative efforts shall fall within the scope of protection of the present application. The embodiments of the present application will be described in detail below with reference to the drawings.
[0017] To solve the above problems, the present application provides a limit structure, including:
[0018] A first rib 1, a second rib 2 parallel to the first rib 1 and having a gap, a limit pin 3 with an axis perpendicular to the first rib 1 and installed on the first rib 1, and a bearing 6 installed on the second rib 2. The limit pin 3 is sleeved in the inner ring of the bearing 6 and is used to limit the displacement between the first rib 1 and the second rib 2 parallel to the direction of both.
[0019] Preferably, the second rib 2 has a mounting hole, and a bearing seat 5 for mounting the bearing 6 is installed in the mounting hole.
[0020] Preferably, one end of the limit pin 3 has a mounting disc, the mounting disc has a plurality of bolt holes, the first rib 1 has a mounting table surface corresponding to the mounting disc, and the mounting table surface has a plurality of threaded holes corresponding to the bolt holes. A bolt assembly 4 passes through the bolt holes to fix the mounting disc on the mounting table surface.
[0021] Preferably, the first rib plate 1 is provided with reinforcing ribs, and the installation table surface is provided with radial ribs connected to the reinforcing ribs.
[0022] Preferably, the bearing 6 and the bearing seat 5 are a press-fitted bearing assembly.
[0023] Preferably, the bearing seat 5 is cylindrical, and its outer wall is provided with a plurality of mounting lugs. Bolts pass through the ear holes of the mounting lugs to fix the bearing seat 5 on the second rib plate 2.
[0024] Preferably, the first rib plate 1 and the second rib plate 2 are in the shape of triangular plates, and the plate surfaces are provided with a plurality of intersecting reinforcing ribs.
[0025] The advantages of the present application include: The present application is installed at a position with a small space gap between the components on both sides of the aircraft docking surface, which can limit the vertical shear difference between the first rib plate and the second rib plate, release the lateral extrusion or tensile deformation of the aircraft, and requires a small installation space.
[0026] The above is only the specific implementation manner of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed by the present application should be covered by the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.
Claims
1. A limiting structure, characterized in that: include: A first rib (1), a second rib (2) parallel to the first rib (1) and having a gap therebetween, a limit pin (3) with an axis perpendicular to the first rib (1) and mounted on the first rib (1), and a bearing (6) mounted on the second rib (2), wherein the limit pin (3) is sleeved in an inner ring of the bearing (6) and is used to limit the displacement between the first rib (1) and the second rib (2) in a direction parallel to both directions.
2. The limiting structure according to claim 1, characterized in that: The second rib plate (2) is provided with a mounting hole, wherein the mounting hole is used to mount a bearing seat (5) for mounting a bearing (6).
3. The limiting structure according to claim 1, characterized in that: One end of the limit pin (3) has a mounting plate, the mounting plate has a plurality of bolt holes, the first rib plate (1) has a mounting table surface corresponding to the mounting plate, the mounting table surface has a plurality of threaded holes corresponding to the bolt holes, and a bolt assembly (4) passes through the bolt holes to fix the mounting plate on the mounting table surface.
4. The limiting structure according to claim 3, characterized in that: The first rib plate (1) is provided with reinforcing ribs, and the mounting table surface is provided with radial ribs connected to the reinforcing ribs.
5. The limiting structure according to claim 2, characterized in that: The bearing (6) and the bearing seat (5) are a bearing assembly that is press-fitted together.
6. The limiting structure according to claim 2, characterized in that: The bearing seat (5) is cylindrical, and its outer wall is provided with a plurality of mounting lugs. Bolts pass through the lug holes of the mounting lugs to fix the bearing seat (5) on the second rib plate (2).
7. The limiting structure according to claim 1, characterized in that: The first rib plate (1) and the second rib plate (2) are in the shape of a triangular plate, and the plate surface is provided with a plurality of interlaced reinforcing ribs.