Aircraft wing plate stress relieving tool
By combining an ultrasonic generator array and a heating wire, the problem of stress relief in wing panels in existing technologies has been solved, achieving a highly efficient and non-destructive stress relief effect, which is applicable to aircraft wing panels made of various materials.
Patent Information
- Application Number
- CN202520519537.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-03-24
- Publication Date
- 2026-02-03
- Estimated Expiration
- 2035-03-24
AI Technical Summary
Existing technologies are insufficient to effectively eliminate internal stress in aircraft wing panels, especially those made of composite materials, and mechanical vibrations can easily lead to deformation, making heat treatment unsuitable.
An ultrasonic generator array combined with a heating wire is used to eliminate stress by optimizing the frequency through multi-frequency resonance and spectrum analysis. The clamping components achieve synchronous clamping to avoid deformation, and the residual stress is released deeply through the heating wire.
It achieves efficient stress relief for flanges of different sizes and shapes, avoids damage to workpiece performance, and is suitable for a variety of materials, including high-strength alloy flanges.
Smart Images
Figure CN223866711U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of tooling technology for aircraft parts production, and in particular to a stress relief tooling for aircraft wing plates. Background Technology
[0002] Aircraft wing panels are typically made of metals or other alloys. These materials may develop internal stresses during processing due to external forces. Eliminating residual stress is crucial for ensuring structural stability and safety. Currently, stress relief in wing panels primarily relies on heat treatment and mechanical vibration. Heat treatment involves heating the wing panel to a specific temperature and holding it there, releasing stress evenly through thermal expansion; this method is suitable for high-temperature resistant materials like aluminum alloys. Mechanical vibration, on the other hand, applies periodic vibrations using specialized equipment, causing the material's internal microstructure to slip and rapidly reducing residual stress by more than 50%. Mechanical vibration is only suitable for stress relief in some beam-like components. However, wing panels, being thin-walled workpieces, are unsuitable because mechanical vibration can easily cause slight deformation. Heat treatment is also unsuitable for stress relief in wing panels made of composite materials. Therefore, improvements are needed. Utility Model Content
[0003] Therefore, it is necessary to provide a stress relief tool for aircraft wing plates to address the above problems.
[0004] An aircraft wingplate stress relief fixture includes a worktable, a clamping assembly, and an ultrasonic generator array. The clamping assembly includes a drive cylinder, a triangular adapter, connecting rods, and a pressure plate. The fixed end of the drive cylinder is hinged to the bottom of the worktable, and the output of the drive cylinder is movably connected to one corner of the triangular adapter. The triangular adapter is movably mounted in the base of the worktable via a pin. The ultrasonic generator array is mounted on the table surface of the base. The other two corners of the triangular adapter are movably connected to the lower ends of two connecting rods, and the upper ends of the connecting rods are movably connected to the rear end of the pressure plate. The middle part of the pressure plate is hinged to the edge of the base, and the front end of the pressure plate extends above the table surface of the base.
[0005] Preferably, the platform has several slots arranged side by side at intervals, and several heating wires are embedded in each slot.
[0006] Preferably, a rubber pad is adhered to the lower end face of the pressure plate.
[0007] Preferably, a positioning pin is also provided on the platform surface of the pedestal.
[0008] The advantages of this invention are: it eliminates workpiece stress through multi-frequency resonance, eliminating the need to design mechanical vibration fixtures for different workpiece models, covering stress relief requirements for wing plates of different sizes and shapes, eliminating the need for customized process parameters, and achieving efficient stress relief through frequency optimization via spectrum analysis. After ultrasonic vibration stress relief, a heating wire is added to heat the workpiece to achieve deep release of residual stress, while avoiding damage to workpiece performance. It is suitable for high-strength alloy wing plate workpieces. Attached Figure Description
[0009] Figure 1 This is a three-dimensional schematic diagram of a stress relief tool for an aircraft wingplate, as one embodiment.
[0010] Figure 2 This is a top view schematic diagram of a stress relief tool for an aircraft wingplate. Detailed Implementation
[0011] To make the above-mentioned objects, features, and advantages of this utility model more apparent and understandable, the specific embodiments of this utility model will be described in detail below with reference to the accompanying drawings. Many specific details are set forth in the following description to provide a full understanding of this utility model. However, this utility model can be implemented in many other ways different from those described herein, and those skilled in the art can make similar modifications without departing from the spirit of this utility model. Therefore, this utility model is not limited to the specific embodiments disclosed below.
[0012] It should be noted that when an element is referred to as being "fixed to" or "set on" another element, it can be directly on the other element or there may be an intervening element. When an element is considered to be "connected to" another element, it can be directly connected to the other element or there may be an intervening element. The terms "vertical," "horizontal," "left," "right," and similar expressions used herein are for illustrative purposes only and do not represent the only possible implementation.
[0013] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.
[0014] like Figures 1-2As shown, an aircraft wingplate stress relief fixture includes a worktable 1, a clamping assembly 2, and an ultrasonic generator array 3. The clamping assembly 2 includes a drive cylinder 21, a triangular adapter 22, connecting rods 23, and a pressure plate 24. The fixed end of the drive cylinder 21 is hinged to the bottom of the worktable 1. The output of the drive cylinder 21 is movably connected to one corner of the triangular adapter 22. The triangular adapter 22 is movably mounted in the base 11 of the worktable 1 via a pin. The ultrasonic generator array 3 is mounted on the table surface of the base 11. The other two corners of the triangular adapter 22 are movably connected to the lower ends of two connecting rods 23, respectively. The upper ends of the connecting rods 23 are movably connected to the rear end of the pressure plate 24, respectively. The middle part of the pressure plate 24 is hinged to the edge of the base 11, and the front end of the pressure plate 24 extends above the table surface of the base 11. Specifically, in this embodiment, the workbench 1 serves as the receiving platform for the clamping assembly 2 and the base 11. The lower part of the base 11 is hollow, and the base 11 is made of metal, resulting in high structural strength, convenient heat conduction, and easy passage of the connecting rod 23. The movement principle of the clamping assembly 2 is as follows: First, the output action of the drive cylinder 21 drives the triangular adapter 22 to rotate around the pin shaft. Specifically, the output end of the drive cylinder 21 extends, and through the rotation of the triangular adapter 22, it drives the two connecting rods 23 of different lengths to move in tandem. This causes the pressure plate 24 to rotate around the connection point with the base 11, pressing down and thus clamping the workpiece placed on the table surface of the base 11. The advantage of this layout is that synchronous clamping can be achieved, requiring only one power source, and the horizontal placement of the drive cylinder 21 facilitates the layout. When it is necessary to release the workpiece, the output end of the drive cylinder 21 retracts, which drives the connecting rod 23 to reset through the triangular adapter 22, causing the front end of the pressure plate 24 to "tilt up," facilitating the loading and unloading of the workpiece. When the workpiece is clamped by the pressure plate 24, the downward pressure from the workpiece pressure plate 24 causes the workpiece plate surface to fit tightly against the table surface of the table 11. At this time, the ultrasonic generator array 3 on the table 11 starts to work, performing ultrasonic vibration on the workpiece plate surface. The stress of the workpiece is eliminated through multi-frequency ultrasonic resonance. There is no need to design mechanical vibration fixtures for different types of workpieces. It can cover the stress relief requirements of wing plates of different sizes and shapes. There is no need for customized process parameters. The frequency is optimized through spectrum analysis to achieve efficient stress relief operation.
[0015] like Figures 1-2 As shown, several slots are arranged side-by-side at intervals on the platform surface of the base 11, and several heating wires 12 are embedded in each slot. Specifically, after ultrasonic vibration relieves stress, the workpiece is clamped by the clamping assembly 2 and in close contact with the platform surface of the base 11. At this time, the heating wires 12 are energized to heat the workpiece. After vibration stress relief, a short-term heat treatment module is added. The power of the heating wires 12 is controlled by a gradient temperature control system to achieve deep release of residual stress in the workpiece while avoiding damage to material properties. This is suitable for high-strength alloy wing plates.
[0016] Specifically, a rubber pad is adhered to the lower end face of the pressure plate 24 to prevent the pressure plate 12 from leaving scratches when it presses against the surface of the workpiece.
[0017] like Figures 1-2 As shown, a positioning pin 13 is also provided on the platform of the base 11 to match the rivet holes on the workpiece, position the workpiece, and prevent the workpiece from shifting during ultrasonic vibration.
[0018] The embodiments described above are merely illustrative of several implementations of this utility model, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the utility model patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this utility model, and these all fall within the protection scope of this utility model. Therefore, the protection scope of this utility model patent should be determined by the appended claims.
Claims
1. A stress-relieving tooling for aircraft wing plates, characterized in that: The device includes a worktable, a clamping assembly, and an ultrasonic generator array. The clamping assembly includes a drive cylinder, a triangular adapter, connecting rods, and a pressure plate. The fixed end of the drive cylinder is hinged to the bottom of the worktable. The output of the drive cylinder is movably connected to one corner of the triangular adapter. The triangular adapter is movably mounted inside the base of the worktable via a pin. The ultrasonic generator array is mounted on the table surface of the base. The other two corners of the triangular adapter are movably connected to the lower ends of two connecting rods, respectively. The upper ends of the connecting rods are movably connected to the rear end of the pressure plate, respectively. The middle part of the pressure plate is hinged to the edge of the base, and the front end of the pressure plate extends above the table surface of the base.
2. The stress relief fixture for an aircraft wingplate as described in claim 1, characterized in that: The platform has several slots arranged side by side at intervals, and several heating wires are embedded in each slot.
3. The stress relief fixture for an aircraft wingplate as described in claim 1, characterized in that: A rubber pad is adhered to the lower end face of the pressure plate.
4. The stress relief fixture for an aircraft wingplate as described in claim 1, characterized in that: The platform surface is also provided with positioning pins.