Tempering tool for aviation spring low-stress manufacturing
By designing a positioning mandrel and pressure sleeve structure, and using a limiting plate to achieve axial compression of the aerospace spring, the problems of low efficiency and unstable quality of traditional tempering tooling are solved, and a highly efficient and stable spring manufacturing process is realized.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-20
- Publication Date
- 2026-03-06
AI Technical Summary
Traditional aerospace spring tempering fixtures are inefficient and have poor quality stability. Furthermore, they are prone to introducing complex residual stresses during compression tempering, making it difficult to meet the requirements for high precision and high stability.
The spring is axially compressed by using a positioning mandrel and pressure sleeve structure and a limiting plate to avoid tangential stress. This ensures that the spring is only subjected to axial compressive stress during tempering. Combined with a simplified clamping method, this improves clamping efficiency and spring quality stability.
It achieves efficient clamping and stable compression of springs, improves the dimensional stability and quality consistency of springs, increases clamping efficiency by more than 2 times, and avoids problems such as spring bending and incomplete stress.
Smart Images
Figure CN223974151U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of equipment manufacturing technology, specifically to a low-stress tempering tooling for manufacturing aviation springs. Background Technology
[0002] In aircraft, precision springs are indispensable for both mechanical and electrical airborne equipment. Springs function in dampers, valves, and switches in various functional systems. Selecting springs with good mechanical properties and high precision helps reduce the failure rate, making aircraft components safer and more reliable. The overall mechanical performance of a spring is determined by both internal and external factors. The spring material determines its internal properties, while load, free altitude, perpendicularity, and residual stress level determine its external properties, which are largely influenced by the manufacturing process. In the manufacturing process, compression tempering is the spring's "shaping" process, which is particularly important for spring quality. Compression tempering must ensure the spring's perpendicularity to prevent lateral bending and eliminate compressive stress to ensure the spring's overall length and improve stability. As a key process equipment for spring compression tempering, it plays a crucial role in the spring's mechanical properties, dimensional accuracy, and operational stability. With the continuous development and advancement of aviation technology, the precision requirements for springs used in aircraft are becoming increasingly stringent, and the stability requirements are becoming increasingly stringent. The manufacturing process of aerospace springs suffers from low efficiency and poor quality stability, primarily due to the following reasons: ① Traditional tempering fixtures use a bolt-nut assembly, requiring manual tightening of the nut to achieve the preset stroke, resulting in low clamping efficiency; ② The bolt size differs significantly from the spring's inner diameter, causing the spring to easily bend during compression tempering; ③ During nut tightening, the spring rotates under stress, experiencing both compressive and shear stresses simultaneously, leading to incomplete stress elimination after tempering and complex residual stress. Traditional tempering fixtures result in low processing efficiency and introduce stress, leading to poor spring quality stability and contradicting the low-stress manufacturing philosophy. The demand for low-stress tempering fixtures for aerospace springs is increasingly evident. Utility Model Content
[0003] The purpose of this utility model is to provide a low-stress manufacturing tempering fixture for aerospace springs that is simple to clamp, stable and reliable, highly efficient, and whose spring dimensions are stable after compression tempering.
[0004] This utility model is achieved through the following technical solution: a low-stress manufacturing tempering fixture for aviation springs, comprising a lower positioning mandrel and an upper pressure sleeve. The positioning mandrel is sequentially nested with a spring and a pressure plate to be tempered. The pressure sleeve is inserted from the upper part of the positioning mandrel, with the bottom of the pressure sleeve abutting against the upper part of the pressure plate. The pressure sleeve compresses the lower spring through the pressure plate. The upper part of the positioning mandrel is provided with several slots, and one side of the pressure sleeve is provided with an opening. When the pressure sleeve compresses the lower spring into position through the pressure plate, a limiting piece is inserted into the slot on the positioning mandrel through the opening on the side of the pressure sleeve. At this time, the limiting piece abuts against the lower pressure plate, restricting the spring from springing upward, and there is no need to apply pressure to the pressure plate through the pressure sleeve to maintain the spring compression.
[0005] The working principle of this technical solution is as follows: during the spring compression process, the stroke of the pressure sleeve and the pressure plate is controlled, and the spring compression is maintained by the limiting plate. Throughout the entire process, the spring is only subjected to axial compressive stress, and this single stress is eliminated more thoroughly during the tempering process, thereby improving the batch-to-batch stability of spring quality.
[0006] To better realize this utility model, the positioning mandrel further includes a lower base and an upper shaft core, the spring is nested on the shaft core, and the lower part of the spring abuts against the upper part of the base, and the slot on the upper part of the positioning mandrel is provided on the upper part of the shaft core.
[0007] To better realize this utility model, the core of the positioning mandrel is cylindrical, the through hole in the middle of the pressure plate is circular, and the diameter of the through hole in the middle of the pressure plate is not less than the diameter of the core of the positioning mandrel.
[0008] To better realize this utility model, the pressure sleeve is further defined as a cylinder with an internal cylindrical through hole, the diameter of the through hole inside the pressure sleeve is larger than the diameter of the core of the positioning mandrel, and the outer diameter of the pressure sleeve is not larger than the outer diameter of the pressure plate.
[0009] To better realize this utility model, the lower part of the pressure sleeve is an open cylindrical through groove, and the diameter of the cylindrical through groove is not greater than the outer diameter of the pressure plate.
[0010] To better realize this utility model, the opening on one side of the pressure sleeve is a rectangular strip hole, and the limiting piece is embedded in the slot on the upper part of the shaft core through the strip hole on one side of the pressure sleeve, and the limiting piece does not contact the inner wall of the pressure sleeve.
[0011] To better realize this utility model, the opening on one side of the pressure sleeve is an axial through groove, and the limiting piece is embedded in the slot on the upper part of the shaft core through the through groove on one side of the pressure sleeve.
[0012] To better realize this utility model, the limiting piece is further U-shaped.
[0013] Compared with the prior art, this utility model has the following advantages and beneficial effects:
[0014] (1) This utility model determines the position of the slot on the positioning mandrel by calculating the size of the spring after compression and adding the thickness of the pressure plate. The dimensional accuracy is reliable. Compared with the traditional tempering tooling, the spring is only subjected to axial compressive stress during the compression process, without the superposition of tangential stress. The stress change of the spring is stable, so that the size of the spring is stable after tempering.
[0015] (2) The clamping method of this utility model is simple, and each spring only needs 0.5 to 1 minute to clamp. Compared with the traditional tempering tooling for bolts and nuts, the clamping efficiency is increased by more than 2 times.
[0016] (3) This utility model adopts a positioning mandrel with an outer diameter slightly smaller than the inner diameter of the spring to avoid the center line from shifting due to pressure on the spring and to ensure the perpendicularity of the spring. Its operation is very simple and convenient, which can reduce the labor intensity of the operator and improve the clamping efficiency. It is suitable for widespread application. Attached Figure Description
[0017] Other features, objects, and advantages of this invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:
[0018] Figure 1 This is a cross-sectional structural diagram of the present invention;
[0019] Figure 2 This is a three-dimensional structural diagram of the pressure sleeve in this utility model;
[0020] Figure 3 This is a schematic diagram of another three-dimensional structure of the pressure sleeve in this utility model;
[0021] Figure 4 This is a schematic diagram of the planar structure of the limiting component in this utility model.
[0022] Wherein: 1—positioning mandrel, 11—base, 12—shaft, 2—spring, 3—pressure plate, 4—limiting plate, 5—pressure sleeve. Detailed Implementation
[0023] The embodiments of this utility model are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain this utility model, and should not be construed as limiting this utility model.
[0024] In the description of this utility model, it should be understood that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", and "outer" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.
[0025] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.
[0026] Example 1:
[0027] The main structure of this embodiment is as follows: Figure 1 As shown, the device includes a lower positioning mandrel 1 and an upper pressure sleeve 5. A spring 2 and a pressure plate 3, which need to be tempered, are nested sequentially on the positioning mandrel 1. The pressure sleeve 5 is inserted from the upper part of the positioning mandrel 1, and the bottom of the pressure sleeve 5 abuts against the upper part of the pressure plate 3. The pressure sleeve 5 compresses the lower spring 2 through the pressure plate 3. The upper part of the positioning mandrel 1 is provided with several slots, and the pressure sleeve 5 is provided with an opening on one side. When the pressure sleeve 5 compresses the lower spring 2 into place through the pressure plate 3, a limiting piece 4 is inserted into the slot on the positioning mandrel 1 through the opening on the side of the pressure sleeve 5. At this time, the limiting piece 4 abuts against the lower pressure plate 3, restricting the spring 2 from springing up. It is not necessary to apply pressure to the pressure plate 3 through the pressure sleeve 5 to keep the spring 2 compressed.
[0028] The specific usage process is as follows: insert the spring 2 radially into the positioning mandrel 1, and then insert the pressure plate 3 and the pressure sleeve 5 in sequence. Through external force, push the pressure sleeve 5 and the pressure plate 3 to compress the spring 2 to the size position. Insert the limiting piece 4 into the slot on the positioning mandrel 1 at the notch of the pressure sleeve 5. Remove the pressure sleeve 5. The limiting piece 4 keeps the spring 2 in a compressed state. This completes the clamping process. Then, the spring 2 can be tempered.
[0029] Example 2:
[0030] This embodiment, based on the above embodiments, further defines the structure of the positioning mandrel 1, such as... Figure 1As shown, the positioning mandrel 1 includes a lower base 11 and an upper shaft 12. The spring 2 is nested on the shaft 12, and the lower part of the spring 2 abuts against the upper part of the base 11. The slot on the upper part of the positioning mandrel 1 is provided on the upper part of the shaft 12. The other parts of this embodiment are the same as those in the above embodiment, and will not be described again.
[0031] Example 3:
[0032] This embodiment, based on the above embodiment, further defines the shapes of the positioning mandrel 1 and the pressure plate 3, such as... Figure 1 As shown, the core 12 of the positioning mandrel 1 is cylindrical, and the through hole in the middle of the pressure plate 3 is circular, with the diameter of the through hole in the middle of the pressure plate 3 not less than the diameter of the core 12 of the positioning mandrel 1. Other parts of this embodiment are the same as those in the above embodiments and will not be repeated.
[0033] Example 4:
[0034] This embodiment further defines the structure of the pressure sleeve 5 based on the above embodiment, such as... Figure 2 As shown, the pressure sleeve 5 is a cylinder with an internal cylindrical through hole. The diameter of the through hole inside the pressure sleeve 5 is larger than the diameter of the core 12 of the positioning mandrel 1, and the outer diameter of the pressure sleeve 5 is not larger than the outer diameter of the pressure plate 3. Other parts of this embodiment are the same as those in the above embodiment and will not be described again.
[0035] Example 5:
[0036] This embodiment further defines the structure of the pressure sleeve 5 based on the above embodiment, such as... Figure 1 , Figure 3 As shown, the lower part of the pressure sleeve 5 is an open cylindrical through groove, the diameter of which is not greater than the outer diameter of the pressure plate 3. Other parts of this embodiment are the same as those in the above embodiment and will not be described again.
[0037] Example 6:
[0038] This embodiment further defines the structure of the pressure sleeve 5 based on the above embodiment, such as... Figure 2 As shown, the opening on one side of the pressure sleeve 5 is a rectangular slot. The limiting piece 4 is embedded in the groove on the upper part of the shaft core 12 through the slot on one side of the pressure sleeve 5, and the limiting piece 4 does not contact the inner wall of the pressure sleeve 5. The other parts of this embodiment are the same as those in the above embodiment, and will not be described again.
[0039] Example 7:
[0040] This embodiment further defines the structure of the pressure sleeve 5 based on the above embodiment, such as... Figure 1 , Figure 3As shown, the opening on one side of the pressure sleeve 5 is an axial through groove, and the limiting piece 4 is embedded into the slot on the upper part of the shaft core 12 through the through groove on one side of the pressure sleeve 5. The other parts of this embodiment are the same as those in the above embodiment, and will not be described again.
[0041] Example 8:
[0042] This embodiment further defines the structure of the limiting piece 4 based on the above embodiment, such as... Figure 4 The limiting piece 4 is U-shaped. To facilitate the insertion of the limiting piece 4 into the slot on the upper part of the shaft core 12, a U-shaped limiting piece 4 is preferred. Other limiting piece 4 structures that can keep the spring 2 in a compressed state can also be selected. The other parts of this embodiment are the same as those in the above embodiments and will not be described again.
[0043] It is understood that the working principle and process of the low-stress manufacturing tempering fixture structure for aviation springs according to one embodiment of the present invention, such as the pressure plate 3 and the pressure sleeve 5, are existing technologies and are well known to those skilled in the art, and will not be described in detail here.
[0044] Although embodiments of the present invention have been shown and described, those skilled in the art will understand that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the claims and their equivalents.
Claims
1. An aircraft spring low stress manufacturing tempering tooling characterized by, The positioning mandrel (1) comprises a lower part and a pressing sleeve (5), the spring (2) to be tempered and the pressing piece (3) are nested on the positioning mandrel (1) in sequence, the pressing sleeve (5) is sleeved on the upper part of the positioning mandrel (1), the bottom of the pressing sleeve (5) abuts against the upper part of the pressing piece (3), and the lower spring (2) is compressed by the pressing sleeve (5) through the pressing piece (3); a plurality of clamping grooves are arranged on the upper part of the positioning mandrel (1), an opening is arranged on one side of the pressing sleeve (5), when the lower spring (2) is compressed in place by the pressing sleeve (5) through the pressing piece (3), the limiting piece (4) is inserted into the clamping groove on the positioning mandrel (1) through the opening on the side of the pressing sleeve (5), at this time, the limiting piece (4) abuts against the lower pressing piece (3), and the spring (2) is prevented from being bounced up, so that the pressing piece (3) does not need to be pressed by the pressing sleeve (5) to keep the spring (2) compressed.
2. An aircraft spring low stress manufacturing and tempering tooling as defined in claim 1 wherein, The positioning mandrel (1) comprises a lower base (11) and an upper shaft core (12), the spring (2) is nested on the shaft core (12), and the lower part of the spring (2) abuts against the upper part of the base (11); the clamping grooves on the upper part of the positioning mandrel (1) are arranged on the upper part of the shaft core (12).
3. An aircraft spring low stress manufacturing and tempering tooling as defined in claim 2 wherein, The shaft core (12) of the positioning mandrel (1) is in a cylindrical shape, the through hole in the middle of the pressing piece (3) is in a circular shape, and the diameter of the through hole in the middle of the pressing piece (3) is not less than the diameter of the shaft core (12) of the positioning mandrel (1).
4. An aircraft spring low stress manufacturing and tempering tooling as defined in claim 3 wherein, The pressing sleeve (5) is a cylinder with a cylindrical through hole arranged inside, the diameter of the through hole inside the pressing sleeve (5) is greater than the diameter of the shaft core (12) of the positioning mandrel (1), and the outer diameter of the pressing sleeve (5) is not greater than the outer diameter of the pressing piece (3).
5. An aircraft spring low stress manufacturing and tempering tooling as defined in claim 3 wherein, The lower part of the pressing sleeve (5) is an open cylindrical through slot, and the diameter of the cylindrical through slot is not greater than the outer diameter of the pressing piece (3).
6. The low stress manufacturing and tempering tool for aircraft springs according to any one of claims 2 to 5, characterized in that, The opening on one side of the pressing sleeve (5) is a rectangular strip hole, the limiting piece (4) is inserted into the clamping groove on the upper part of the shaft core (12) through the strip hole on one side of the pressing sleeve (5), and the limiting piece (4) does not contact the inner wall of the pressing sleeve (5).
7. The low stress manufacturing and tempering tool for aircraft springs according to any one of claims 2 to 5, characterized in that, The opening on one side of the pressing sleeve (5) is an axial through slot, and the limiting piece (4) is inserted into the clamping groove on the upper part of the shaft core (12) through the through slot on one side of the pressing sleeve (5).
8. The low stress manufacturing and tempering tool for aircraft springs according to any one of claims 1 to 5, characterized in that, The limiting piece (4) is in a U shape.