Flexible stretch-bend coupling sliding mechanism
The flexible skin skeleton, composed of sliding translation beams and sliding connecting rods, solves the problems of high material cost and difficult processing in the existing technology, realizes large-angle deformation and high elongation of flexible skin, reduces material cost and improves processing flexibility.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
- Filing Date
- 2024-12-04
- Publication Date
- 2026-06-12
AI Technical Summary
Existing flexible skin manufacturing methods are costly in terms of materials, difficult to process, and can only be used under limited conditions, making it impossible to achieve large-angle deformation.
A flexible skin frame consisting of a sliding translation beam and sliding connecting rods is used to achieve deformable stretching through the connecting rod structure, and to achieve large-angle torsion by utilizing the torsional properties of the material.
It achieves 100% elongation and large-angle torsion of the skin skeleton, reducing material costs and improving processing flexibility.
Smart Images
Figure CN119734819B_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the field of aircraft technology, and specifically relates to a flexible tension-bending coupling sliding mechanism. Background Technology
[0002] Current research on flexible skins mainly utilizes flexible materials, such as thin, highly elastic metal spring frames covered with ultra-elastic silicone rubber sheets; or directly using ultra-elastic metal skins to achieve bending deformation; and also employing lattice structures to achieve overall structural flexibility, with ultra-elastic silicone rubber sheets covering the lattice structure. Flexible variable frames manufactured using these methods can achieve continuous deformation and withstand certain aerodynamic loads.
[0003] However, the above methods all rely on the elasticity or hyperelasticity of the materials, which are expensive, difficult to process, and can only be used under certain conditions, such as low load, normal temperature, and small angle deformation. Summary of the Invention
[0004] To address the aforementioned problems, this application provides a flexible tension-bending coupling sliding mechanism, comprising:
[0005] A first connecting plate, a second connecting plate having relative motion with the first connecting plate, and a flexible skin skeleton connecting the first connecting plate and the second connecting plate;
[0006] The flexible skin frame includes: multiple sliding translation beams and multiple sliding links; the multiple sliding translation beams are parallel to each other, each sliding translation beam has multiple mounting holes, and the sliding links pass through the mounting holes on two adjacent sliding translation beams with gaps to connect the two adjacent sliding translation beams. The two ends of the sliding links are provided with limiting structures to prevent the sliding translation beams from disengaging from the sliding links. The two sides of the flexible skin frame are then connected to a first connecting plate and a second connecting plate respectively through multiple sliding links. The first connecting plate and the second connecting plate are fixed to different load-bearing structures of the aircraft. The first connecting plate, the second connecting plate, and the surface of the flexible skin frame are covered with flexible skin.
[0007] Preferably, the flexible skin comprises a silicone rubber sheet.
[0008] Preferably, the first connecting plate and the second connecting plate are provided with through holes for connecting to the sliding link, and a clearance hole is provided at the position of the through hole to provide the sliding link with a space for movement.
[0009] Preferably, the limiting structure includes a retaining ring, and the two ends of the sliding link each have annular grooves for mounting the retaining ring.
[0010] Preferably, a bushing is provided between the mounting hole of the sliding translation beam and the sliding connecting rod.
[0011] Preferably, the bushing has a retaining ring at one end and an annular groove at the other end. The sliding translation beam is fitted onto the outside of the bushing through the mounting hole, and a retaining spring is installed in the annular groove. The retaining spring and the retaining ring restrict the movement of the sliding translation beam.
[0012] Preferably, bushings are provided in the through holes of the first connecting plate and the second connecting plate.
[0013] The advantages of this application include: This application uses a linkage structure as the skin skeleton to realize the deformable stretching of the skin skeleton, with an elongation rate of up to 100%. At the same time, it utilizes the torsional properties of the material to realize the torsion of the translation beam. The sliding linkage and the sliding translation beam are connected in series and parallel to realize in-plane stretching. Meanwhile, the series-connected sliding translation beam can be twisted and the sliding linkage can be bent, so that the torsion angles are superimposed to achieve a larger angle of torsion. Attached Figure Description
[0014] Figure 1 This is a schematic diagram of the flexible skin skeleton of this application at its tensile limit;
[0015] Figure 2 This is a schematic diagram of the flexible tension-bending coupling sliding mechanism of this application;
[0016] Figure 3 This is a schematic diagram of the flexible skin skeleton of this application at the compression limit;
[0017] Figure 4 This is a schematic diagram of the series and parallel connection of multiple sliding translation beams of the flexible skin skeleton of this application;
[0018] Figure 5 This is a schematic diagram of the sliding link of the flexible skin skeleton of this application;
[0019] Figure 6 This is a schematic diagram of the bushing of the flexible skin skeleton of this application;
[0020] Figure 7 This is a schematic diagram of the multi-sliding translation beam of this application. Detailed Implementation
[0021] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.
[0022] This application provides a flexible tension-bending coupling sliding mechanism, such as Figure 1 - Figure 7 As shown, it includes:
[0023] A first connecting plate 5, a second connecting plate 6 having relative motion with the first connecting plate 5, and a flexible skin skeleton connecting the first connecting plate 5 and the second connecting plate 6;
[0024] The flexible skin frame includes: multiple sliding translation beams 1 and multiple sliding links 2; the multiple sliding translation beams are parallel to each other, each sliding translation beam 1 has multiple mounting holes, the sliding links 2 pass through the mounting holes on two adjacent sliding translation beams with gaps to connect the two adjacent sliding translation beams, and the two ends of the sliding links 2 are provided with limiting structures to prevent the sliding translation beams 1 from disengaging from the sliding links 2. The two sides of the flexible skin frame are then connected to the first connecting plate 5 and the second connecting plate 6 respectively through multiple sliding links 2. The first connecting plate 5 and the second connecting plate 6 are fixed on different load-bearing structures of the aircraft, and the first connecting plate 5, the second connecting plate 6 and the surface of the flexible skin frame are covered with flexible skin.
[0025] Specifically, the first connecting plate 5, the second connecting plate 6 and the flexible skin frame form a flexible transition area, and the first connecting plate 5 and the second connecting plate 6 serve as a transition; on the one hand, the first connecting plate 5 and the second connecting plate 6 can be designed into a shape that is easy to connect with the aircraft load-bearing structure; on the other hand, the first connecting plate 5 and the second connecting plate 6 have space to connect with the flexible skin, and the flexible skin frame serves as a support structure for overlapping the flexible skin.
[0026] In some alternative embodiments, the flexible skin includes a silicone rubber sheet, which covers the first connecting plate 5, the second connecting plate 6, and the flexible skin skeleton, and is connected to the conventional aircraft skin around its perimeter. The flexible skin can be glued to the first connecting plate 5 and the second connecting plate 6 by means of adhesive.
[0027] In some alternative embodiments, the first connecting plate 5 and the second connecting plate 6 are provided with through holes that connect to the sliding link 2, and an avoidance hole 7 is provided at the position of the through hole to provide the sliding link 2 with a space for movement.
[0028] In some alternative embodiments, the limiting structure includes a retaining ring 4, and the two ends of the sliding link 2 have annular grooves for mounting the retaining ring 4.
[0029] In some alternative embodiments, a bushing 3 is provided between the mounting hole of the sliding translation beam 1 and the sliding connecting rod 2. The bushing is placed between the crossbar and the connecting rod to prevent wear, reduce jamming, increase the bending angle of the crossbar, and fix and limit the movement. The bushing is fixed by a snap ring.
[0030] In some alternative embodiments, the bushing 3 has a retaining ring at one end and an annular groove at the other end. The sliding translation beam 1 is sleeved on the outside of the bushing 3 through the mounting hole. The retaining ring 4 is installed in the annular groove, and the retaining ring 4 restricts the movement of the sliding translation beam 1.
[0031] In some alternative embodiments, bushings 3 are provided in the through holes of the first connecting plate 5 and the second connecting plate 6.
[0032] The advantages of this application include: This application uses a linkage structure as the skin skeleton to realize the deformable stretching of the skin skeleton, with an elongation rate of up to 100%. At the same time, it utilizes the torsional properties of the material to realize the torsion of the translation beam. The sliding linkage and the sliding translation beam are connected in series and parallel to realize in-plane stretching. Meanwhile, the series-connected sliding translation beam can be twisted and the sliding linkage can be bent, so that the torsion angles are superimposed to achieve a larger angle of torsion.
[0033] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.
Claims
1. A flexible stretch-bend coupling sliding mechanism, characterized in that, include: A first connecting plate (5), a second connecting plate (6) having relative motion with the first connecting plate (5), and a flexible skin skeleton connecting the first connecting plate (5) and the second connecting plate (6); The flexible skin frame includes: multiple sliding translation beams (1) and multiple sliding links (2); Multiple sliding translation beams are parallel to each other. Each sliding translation beam (1) has multiple mounting holes. A sliding connecting rod (2) passes through the mounting holes on two adjacent sliding translation beams with gaps, connecting the two adjacent sliding translation beams. Limiting structures are provided at both ends of the sliding connecting rod (2) to restrict the sliding translation beam (1) from disengaging from the sliding connecting rod (2). The flexible skin frame is then connected to the first connecting plate (5) and the second connecting plate (6) on both sides through multiple sliding connecting rods (2). The first connecting plate (5) and the second connecting plate (6) are fixed on different load-bearing structures of the aircraft. The first connecting plate (5), the second connecting plate (6), and the surface of the flexible skin frame are covered with flexible skin.
2. The flexible stretch-wrap coupling slip mechanism of claim 1, wherein, The flexible skin comprises a thin sheet of silicone rubber.
3. The flexible stretch-to-couple sliding mechanism of claim 1, wherein, The first connecting plate (5) and the second connecting plate (6) are provided with through holes for connecting to the sliding link (2), and an avoidance hole (7) is provided at the position of the through hole. The avoidance hole (7) is used to provide the sliding link (2) with space for movement.
4. The flexible stretch-wrap coupling slip mechanism of claim 1, wherein, The limiting structure includes a retaining ring (4), and the two ends of the sliding link (2) have annular grooves for mounting the retaining ring (4).
5. The flexible tension-bending coupling sliding mechanism as described in claim 1, characterized in that, A bushing (3) is provided between the mounting hole of the sliding translation beam (1) and the sliding connecting rod (2).
6. The flexible tension-bending coupling sliding mechanism as described in claim 5, characterized in that, The bushing (3) has a retaining ring at one end and an annular groove at the other end. The sliding translation beam (1) is sleeved on the outside of the bushing (3) through the mounting hole. The retaining ring (4) is installed in the annular groove. The retaining ring (4) and the retaining ring restrict the movement of the sliding translation beam (1).
7. The flexible tension-bending coupling sliding mechanism as described in claim 2, characterized in that, Bushings (3) are provided in the through holes of the first connecting plate (5) and the second connecting plate (6).