Transverse stretching compensation device for aircraft engine room skin part
By designing a transverse stretch compensation device for skin parts of aircraft hair room, the problem of easy orange peel defects during transverse stretching is solved, and processing efficiency and surface quality are improved.
Patent Information
- Application Number
- CN202421091005.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-05-17
- Publication Date
- 2025-04-08
- Estimated Expiration
- 2034-05-17
AI Technical Summary
In the prior art, the skin parts of the aircraft room are prone to orange peel defects when stretched horizontally, resulting in low processing efficiency, poor surface quality, and a high skill level is required.
A transverse stretch compensation device for skin parts in the airplane is designed, including a jaw clamping area and a skin sheet forming work area. The jaw clamping area is clamped on the jaw of the stretcher with the skin sheet. The area where the skin sheet forming work area and the skin sheet contact the skin sheet is rounded, and the upper edge shape surface is an arc-shaped surface recessed in the direction of the jaw clamping area, which is consistent with the shape of the stretch mold used in conjunction.
Through this compensation device, it is ensured that the stretching amount of the skin sheet at all positions is basically consistent during the stretching process, avoid orange peel defects, improve processing efficiency by about 60%, and improve the surface quality of the parts.
Smart Images
Figure CN222725231U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of stretching and forming aircraft engine room skin parts, in particular to a lateral stretching compensation device for aircraft engine room skin parts. Background Art
[0002] Aircraft fuselage skin parts are important components of aircraft structures. The main forming methods are longitudinal stretch forming and transverse stretch forming. Aircraft engine skin parts are the aerodynamic shape of aircraft engines and have an important impact on the product performance of the aircraft itself. According to the existing technology, this type of parts is mainly formed by transverse stretching, such as Figure 1 As shown in the figure, due to the factors of the workbench and jaw shape, stroke, and existing stretch forming auxiliary devices of the transverse skin stretching machine, when the aircraft engine room skin parts are stretched transversely, the convex curve area of the parts is prone to orange peel defects, which is difficult to meet the production requirements. At present, the aircraft engine room skin parts are generally formed by manual preforming and stretching. This method is inefficient, labor-intensive, has poor surface quality of parts, requires a high level of skills, and the quality of skin parts is unstable. Utility Model Content
[0003] Technical problem solved by the utility model: In view of the above-mentioned situation of the prior art, the purpose of the utility model is to provide a lateral stretching compensation device for aircraft engine room skin parts, so as to solve the problem that the existing engine room skin parts are prone to orange peel defects during lateral stretching and improve the processing efficiency.
[0004] The technical solution of this utility model:
[0005] A device for compensating aircraft skin transverse stretching comprises a jaw clamping area and a skin sheet forming work area, wherein the jaw clamping area extends vertically from one side of the skin sheet forming work area. During stretching, the jaw clamping area and the skin sheet are clamped together on the jaws of a skin stretching machine. The area where the skin sheet forming work area contacts the skin sheet is chamfered, and the outer shape of the upper edge of the skin sheet forming work area is an arc-shaped surface that is concave toward the jaw clamping area, which is consistent with the outer shape of a matching stretching die.
[0006] Furthermore, the area where the skin sheet forming work area contacts the skin sheet is rounded, and the rounded corner is R2.
[0007] Furthermore, the selection range of R2 is R20-R50mm.
[0008] Furthermore, the lower edge of the skin sheet forming work area is fitted with the nose of the upper jaw of the skin stretching machine.
[0009] Furthermore, the surface of the jaw clamping area is a rough surface.
[0010] Furthermore, the aircraft engine room skin parts transverse stretch compensation device is made of 45# steel.
[0011] Beneficial effects of the utility model:
[0012] When the compensation device of the utility model is used, it is installed on the jaws of the transverse skin stretching machine together with the skin sheet. The skin sheet is lifted up by the compensation device of the utility model during stretching, so that the skin sheet is arc-shaped (consistent with the shape of the stretching die), and is gradually stretched to fit with the stretching die, ensuring that the stretching amount of each position of the skin sheet is basically consistent, thereby solving the problem of orange peel defects in the hair room skin parts, and improving the processing efficiency of the hair room skin parts by about 60% compared with the existing method, and the parts have good surface quality, simple structure and easy installation. BRIEF DESCRIPTION OF THE DRAWINGS
[0013] Figure 1 This is a schematic diagram of the transverse stretching of a typical hair room skin part;
[0014] Figure 2 This is a schematic diagram of the transverse stretching of the hair room skin parts;
[0015] Figure 3 Schematic diagram of the stretched state of the aircraft engine room skin using the existing stretching technology;
[0016] Figure 4 To adopt Figure 3 Schematic diagram of the stretching forming auxiliary device when the sheet material and the stretch film are stretched in the prior art;
[0017] Figure 5 This is a schematic diagram of the appearance of the auxiliary device proposed by the utility model;
[0018] Figure 6 A side view of the auxiliary device proposed by the utility model;
[0019] Figure 7 This is a schematic diagram of the auxiliary device structure proposed by the utility model;
[0020] Figure 8 A schematic diagram of the stretched state of the aircraft engine room skin using the auxiliary device of the utility model;
[0021] Fig. 9 It is a schematic diagram of the stretching forming auxiliary device for the distance between the bonding area of the sheet material and the stretch film when the auxiliary device of the utility model is used for stretching;
[0022] Among them, 1-stretching die, 2-sheet material, 3-stretching machine jaws, 4-jaw rotating shaft, 5-stretching machine working platform, 6-stretching forming auxiliary device, 7-skin sheet forming working area, 8-jaw clamping area, 9-aircraft skin lateral stretching compensation device. DETAILED DESCRIPTION
[0023] In order to more clearly understand the purpose, technical solutions and advantages of the present invention, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments.
[0024] The aircraft engine room skin sheet with large transverse curvature is usually formed by transverse stretching, that is, the skin sheet is clamped at both ends along the transverse direction, and the skin sheet is made to fit with the stretching die under the top force of the stretching die lifted by the working platform. Figure 1 shown.
[0025] Figure 2 The schematic diagram shows the states of the stretching die 1, the sheet material 2, the stretching machine jaws 3, the jaw rotating shaft 4, the stretching machine working platform 5, and the existing stretching forming auxiliary device 6 before stretching the aircraft launch room skin sheet material using the existing technology. Figure 2 As shown, during stretching, the jaws 3 of the stretching machine clamp the sheet material 2 and the existing stretching forming auxiliary device 6 and then rotate through the jaw rotating shaft 4, and the working platform 5 of the stretching machine drives the stretching die 1 to move up and down.
[0026] Figure 3 , 4 The schematic diagram shows the final state of the sheet material when stretching the aircraft engine room skin using the existing technology. Figure 3 As shown, at this time, the working platform 5 of the stretching machine is adjusted to a suitable position. After the jaws 3 of the stretching machine rotate through the jaw rotating shaft 4, since the side of the stretching die 1 is an arc-shaped surface, during the stretching process, the middle position of the sheet 2 first fits with the vertex of the outer arc-shaped surface of the stretching film 1, as shown in FIG. Figure 4 At this time, the distance between point a and the upper edge of the existing stretch forming auxiliary device 6 is L1. At this time, the parts on both sides of the sheet 2 have not yet contacted the stretching die, and the two sides of the sheet 2 are still far away from the edge of the stretching die 1. At this time, in order to further fit the sheet 2 with the stretching die 1, it is necessary to continue to push up the working platform 5, and at the same time, the rotating shaft 4 continues to rotate inward, and finally the parts on both sides of the sheet 2 contact the stretching die 1, as shown in point b in the figure. At this time, the distance between point b and the upper edge of the existing stretch forming auxiliary device 6 is L2. Figure 3 In the state shown in , after the sheet 2 is completely fitted with the stretching die 1, L2 is greater than L1, so that the sheet at a is stretched more than that at b, and orange peel and excessive stretching defects are prone to appear at a.
[0027] To avoid Figure 3 , 4 The defect shown in Figure 3 In the state shown in , in order to prevent the sheet 2 from being stretched excessively at a, an arc-shaped top block needs to be added at the jaws of the sheet 2, that is, the stretching compensation device of the present application, such as Fig. 9 As shown, L1 and L2 are made the same, and the stretching amounts at a and b are basically the same, thus meeting the stretching requirements.
[0028] Figure 5 , 6 The structure of the transverse stretch compensation device 9 of the aircraft engine room skin part of the utility model is schematically shown. Figure 5 , 6 As shown, the transverse stretching compensation device for aircraft engine room skin parts of the utility model is an integral structure, and the device includes a jaw clamping area 8 and a skin sheet forming work area 7, wherein the jaw clamping area 8 extends vertically from one side of the skin sheet forming work area 7. During stretching, the jaw clamping area 8 and the skin sheet are clamped together on the jaws of the skin stretching machine, the area E where the skin sheet forming work area 7 contacts the skin sheet is rounded, and the upper edge profile surface of the skin sheet forming work area 7 is an arc surface concave toward the jaw clamping area 8, which is consistent with the profile of the stretching die 1 used in conjunction, at this time, it can be ensured that the distance between the middle position of the sheet 2 and the vertex of the outer arc surface of the stretching film 1 to the skin sheet forming work area 7 and the distance between the two sides of the sheet 2 and the outer surface of the stretching film 1 to the skin sheet forming work area 7 are equal, and basically the same stretching amount is ensured, and it will not cause orange peel to appear in the middle position of the sheet 2.
[0029] Figure 7 FIG. 1 is a structural diagram of a lateral stretch compensation device 9 for an aircraft engine room skin part in an embodiment of the present utility model, which specifically shows the compensation device in this embodiment. Figure 5 As shown. A is selected according to the width of the actual equipment jaws when released, B is selected according to the actual equipment jaws depth, C is selected according to the actual equipment jaws height, D, R1, R2 are selected according to actual production needs, and R2 is selected in the range of R20-R50mm. The angle between C and D is selected according to the actual equipment jaw shape. G has no specific requirements, but it should not be too sharp. E is selected according to the arc of the stretching die. The device material is based on the actual on-site use requirements, but the tensile strength should be ≥ the tensile strength of the raw material of the parts. According to the existing hair room skin sheet materials - generally LY12Mδ1.0mm~2mm aluminum alloy materials are used. After checking, the tensile strength of LY12M80.3mm~2.5mm aluminum materials is ob=407MPa. The material of the auxiliary device of the utility model is 45# steel, with a tensile strength of ob=600MPa, which can fully meet the tensile requirements.
[0030] Before stretching, the skin sheet material and the auxiliary device of the utility model are clamped and fixed together at the jaws of the stretching machine, and the nose E of the skin sheet material forming working area is made to fit with the sheet material. Figure 8 , 9 As shown, at this time, since the E profile is an arc surface, which is consistent with the profile of the stretching die, L1 and L2 are always kept the same during the process of the sheet metal and the stretching die being fitted together, the stretching deformation of the sheet metal is further optimized.
Claims
1. A lateral stretch compensation device for aircraft engine room skin parts, characterized in that: It includes a jaw clamping area and a skin sheet forming working area, wherein the jaw clamping area extends vertically from one side of the skin sheet forming working area. During stretching, the jaw clamping area and the skin sheet are clamped together on the jaws of the skin stretching machine. The area where the skin sheet forming working area contacts the skin sheet is chamfered, and the outer shape of the upper edge of the skin sheet forming working area is an arc-shaped surface concave toward the jaw clamping area, which is consistent with the outer shape of the stretching die used in conjunction.
2. The lateral stretch compensation device for aircraft engine room skin parts according to claim 1, characterized in that: The area where the skin sheet forming work area contacts the skin sheet is rounded, and the fillet is R2.
3. The lateral stretch compensation device for aircraft engine room skin parts according to claim 2, characterized in that: The selection range of R2 is R20-R50mm.
4. The lateral stretch compensation device for aircraft engine room skin parts according to claim 1, characterized in that: The lower edge of the skin sheet forming work area is fitted with the nose of the upper jaw of the skin stretching machine.
5. The lateral stretch compensation device for aircraft engine room skin parts according to claim 1, characterized in that: The surface of the jaw gripping area is rough.
6. The lateral stretch compensation device for aircraft engine room skin parts according to claim 1, characterized in that: The aircraft engine room skin parts transverse stretching compensation device is made of 45# steel.