Preparation method of aviation spring tempering tool

Abstract

The invention relates to the technical field of equipment manufacturing, and particularly discloses a preparation method of an aviation spring tempering tool, which comprises the following steps: S1, investigating and researching the tool used in the tempering process of the existing aviation spring, and knowing the technical defects of the existing tool; s2, according to the technical defects existing in an existing tool, the tool is improved, and corresponding structural design is provided; s3, after experimental manufacturing is conducted, the device is applied to the actual tempering process of the spring; and S4, whether the designed and manufactured tool can overcome the technical defects of a traditional tool or not is verified, then the tool is structurally improved in a targeted mode, finally, a finished product tool is obtained, a corresponding mold is manufactured, and batch production and manufacturing are conducted. According to the tool prepared through the method, the clamping mode is simple, the labor intensity of an operator can be relieved, the clamping efficiency is improved, the stress change of the spring is stable, the size of the spring is stable after tempering, and the tool is suitable for wide application and popularization.

Description

Technical Field

[0001] The invention relates to the technical field of equipment manufacturing, and in particular to a method for preparing an aviation spring tempering tool. Background Art

[0002] In aircraft, whether mechanical or electrical airborne equipment, precision springs are indispensable. The dampers, valves, and switches of various functional systems all have springs at work. Selecting springs with good mechanical properties and high precision is conducive to reducing the failure rate and making the functional parts of aircraft safer and more reliable. The quality of the comprehensive mechanical properties of springs is determined by both internal and external factors. The material of the spring determines its internal factors, and the load, free height, verticality, residual stress level, etc. determine its external factors. The external factors are mostly affected by the manufacturing process. In the manufacturing process, compression tempering is the process of "setting" the spring, which is particularly important for the quality of the spring. On the one hand, compression tempering needs to ensure the verticality of the spring to avoid lateral bending of the spring; on the other hand, it needs to eliminate compressive stress, ensure the total length of the spring, and improve stability. As the key process equipment for spring compression tempering, it plays a vital role in the quality of the spring mechanical properties, dimensional accuracy, and operational stability. With the continuous development and progress of aviation technology, the precision requirements of springs used in aircraft are becoming more and more stringent, and the requirements for their stability are becoming higher and higher. How to efficiently prepare aviation springs with stable quality is a technical problem that needs to be solved urgently. Summary of the invention

[0003] The object of the present invention is to provide a method for preparing an aviation spring tempering tooling which is capable of manufacturing the spring with simple clamping, stability and reliability, high efficiency and stable spring size after compression tempering.

[0004] The present invention is achieved through the following technical solution: a method for preparing an aviation spring tempering tooling, comprising the following steps:

[0005] Step S1: Investigate and study the tooling used in the tempering process of existing aviation springs to understand the technical defects of the existing tooling;

[0006] Step S2: improving the existing tooling according to the technical defects thereof and providing corresponding structural design;

[0007] Step S3: Experimentally manufacture the provided structural design and then apply it to the actual tempering process of the spring;

[0008] Step S4: Verify whether the designed and manufactured tooling can overcome the technical defects of traditional tooling, and then improve the structure of the tooling in a targeted manner, finally obtain the finished tooling, manufacture the corresponding mold, and carry out mass production.

[0009] In order to better implement the method of the present invention, further, in the step S1, the tempering tooling used in the existing aviation spring is a structure in which a bolt and a nut cooperate. The existing technical defects include that the spring to be tempered nested on the bolt is compressed by screwing the nut into the bolt, and the clamping efficiency of the spring is low; and the bolt size and the inner diameter of the spring are too different, resulting in the spring being easily bent sideways during the compression tempering process; in addition, during the process of screwing the nut into the spring, the spring rotates due to the force and is subjected to compressive stress and shear stress at the same time. The stress is not completely eliminated after tempering, and the comprehensive residual stress is complex.

[0010] In order to better implement the method of the present invention, further, in the step S4, the finished tooling finally obtained includes a lower positioning mandrel and an upper pressing sleeve, the positioning mandrel is sequentially nested with a spring and a pressing sheet that need to be tempered, the pressing sleeve is inserted from the upper part of the positioning mandrel, the bottom of the pressing sleeve abuts against the upper part of the pressing sheet, and the pressing sleeve compresses the lower spring through the pressing sheet; a plurality of slots are provided on the upper part of the positioning mandrel, and an opening is provided on one side of the pressing sleeve. When the pressing sleeve compresses the lower spring into place through the pressing sheet, the limiting sheet is embedded into the slot on the positioning mandrel through the opening on the side of the pressing sleeve. At this time, the limiting sheet abuts against the lower pressing sheet to limit the spring from bouncing upward, and there is no need to apply pressure to the pressing sheet through the pressing sleeve to keep the spring compressed.

[0011] The working principle of the finished tooling is to control the travel of the compression sleeve and the pressing plate during the spring compression process, and maintain the spring compression through the limit plate. The spring is only subjected to axial compressive stress during the whole process, and the single stress is eliminated more thoroughly during the tempering process, which improves the batch stability of the spring quality.

[0012] In order to better implement the method of the present invention, further, the positioning core shaft 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 upper groove of the positioning core shaft is arranged on the upper part of the shaft core.

[0013] In order to better implement the method of the present invention, further, the core of the positioning mandrel is cylindrical, the through hole in the middle of the pressing sheet is circular, and the diameter of the through hole in the middle of the pressing sheet is not less than the diameter of the core of the positioning mandrel.

[0014] In order to better implement the method of the present invention, further, the pressing sleeve is a cylinder with a cylindrical through hole arranged inside, the diameter of the through hole inside the pressing sleeve is larger than the diameter of the core of the positioning core shaft, and the outer diameter of the pressing sleeve is not larger than the outer diameter of the pressing sheet.

[0015] In order to better implement the method of the present invention, further, the lower portion of the pressing sleeve is an open cylindrical through groove, and the diameter of the cylindrical through groove is not greater than the outer diameter of the pressing sheet.

[0016] In order to better implement the method of the present invention, further, the opening on one side of the pressing sleeve is a rectangular strip hole, and the limiting plate is embedded in the groove on the upper part of the shaft core through the strip hole on one side of the pressing sleeve, and the limiting plate does not contact the inner wall of the pressing sleeve.

[0017] In order to better implement the method of the present invention, further, the opening on one side of the pressing sleeve is an axial through groove, and the limiting plate is embedded in the groove on the upper part of the shaft core through the through groove on one side of the pressing sleeve.

[0018] In order to better implement the method of the present invention, further, the limiting piece is U-shaped.

[0019] Compared with the prior art, the present invention has the following advantages and beneficial effects:

[0020] (1) The present invention aims at the defects of existing aviation springs and provides a more perfect tool for aviation spring tempering. The tool 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 pressing sheet. The dimensional accuracy is reliable. Compared with the traditional tempering tool, the spring is only subjected to axial compressive stress during the compression process without tangential stress superposition. The stress change of the spring is stable, so that the size of the spring is stable after tempering.

[0021] (2) The present invention aims to address the defects of existing aviation springs and provides a more perfect tool for aviation spring tempering. The tool has a simple clamping method and only takes 0.5 to 1 minute to clamp each spring. Compared with the traditional tempering tool for bolts and nuts, the clamping efficiency is increased by more than 2 times;

[0022] (3) In view of the defects of existing aviation springs, the present invention provides a more perfect tool for aviation spring tempering. The tool adopts a positioning mandrel, whose outer diameter is slightly smaller than the inner diameter of the spring, to avoid the center line deviation caused by the pressure on the spring and ensure the verticality of the spring. The operation is very simple and convenient, which can reduce the labor intensity of the operator and improve the clamping efficiency, and is suitable for wide promotion and application. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments with reference to the following drawings:

[0024] Figure 1 A schematic diagram of the cross-sectional structure of the tooling for preparing the present invention;

[0025] Figure 2 A schematic diagram of the three-dimensional structure of a pressure sleeve in a tooling for preparing the present invention;

[0026] Figure 3 Another schematic diagram of the three-dimensional structure of the pressure sleeve in the tooling for preparing the present invention;

[0027] Figure 4 The figure is a schematic diagram of the planar structure of the limiting member in the tooling for preparing the present invention.

[0028] Among them: 1-positioning mandrel, 11-base, 12-shaft core, 2-spring, 3-pressing piece, 4-limiting piece, 5-pressing sleeve. DETAILED DESCRIPTION

[0029] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be understood as limiting the present invention.

[0030] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0031] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0032] Embodiment 1:

[0033] This embodiment provides a method for preparing an aviation spring tempering tool, comprising the following steps:

[0034] Step S1: Investigate and study the tooling used in the tempering process of existing aviation springs to understand the technical defects of the existing tooling;

[0035] Step S2: improving the existing tooling according to the technical defects thereof and providing corresponding structural design;

[0036] Step S3: Experimentally manufacture the provided structural design and then apply it to the actual tempering process of the spring;

[0037] Step S4: Verify whether the designed and manufactured tooling can overcome the technical defects of traditional tooling, and then improve the structure of the tooling in a targeted manner, finally obtain the finished tooling, manufacture the corresponding mold, and carry out mass production.

[0038] Among them, in the step S1, the tempering tooling used in the existing aviation spring is a structure in which a bolt and a nut are matched. The existing technical defects include that the spring to be tempered nested on the bolt is compressed by screwing the nut into the bolt, and the clamping efficiency of the spring is low; and the difference between the bolt size and the inner diameter of the spring is too large, resulting in the spring being easily bent sideways during the compression tempering process; in addition, during the process of screwing in the nut, the spring rotates due to the force and is subjected to compressive stress and shear stress at the same time. The stress is not completely eliminated after tempering, and the comprehensive residual stress is complex.

[0039] In step S4, the main structure of the finished tooling is finally obtained, such as Figure 1 As shown, it includes a lower positioning core shaft 1 and an upper pressing sleeve 5, on which the spring 2 and the pressing sheet 3 to be tempered are nested in sequence, and the pressing sleeve 5 is inserted from the upper part of the positioning core shaft 1, and the bottom of the pressing sleeve 5 abuts against the upper part of the pressing sheet 3, and the pressing sleeve 5 compresses the lower spring 2 through the pressing sheet 3; a plurality of slots are provided on the upper part of the positioning core shaft 1, and an opening is provided on one side of the pressing sleeve 5. When the pressing sleeve 5 compresses the lower spring 2 into place through the pressing sheet 3, the limiting sheet 4 is embedded into the slot on the positioning core shaft 1 through the opening on the side of the pressing sleeve 5. At this time, the limiting sheet 4 abuts against the lower pressing sheet 3 to limit the spring 2 from bouncing upward, and there is no need to apply pressure to the pressing sheet 3 through the pressing sleeve 5 to keep the spring 2 compressed.

[0040] The specific use process of the tempering tool is to radially insert the spring 2 into the positioning core shaft 1, and then insert the pressing plate 3 and the pressing sleeve 5 in turn, and through the external force, push the pressing sleeve 5 and the pressing plate 3 to compress the spring 2 to the size position, insert the limit plate 4 into the groove on the positioning core shaft 1 at the notch of the pressing sleeve 5, remove the pressing sleeve 5, and keep the spring 2 in a compressed state by the limit plate 4, so as to complete the clamping process, and then carry out the tempering operation of the spring 2.

[0041] Embodiment 2:

[0042] Based on the above embodiments, this embodiment further defines the structure of the positioning mandrel 1, such as Figure 1 As shown, the positioning mandrel 1 includes a base 11 at the bottom and an axis core 12 at the top, the spring 2 is nested on the axis core 12, and the bottom of the spring 2 abuts against the top of the base 11, and the upper slot of the positioning mandrel 1 is arranged on the top of the axis core 12. The other parts of this embodiment are the same as the above embodiment and will not be described again.

[0043] Embodiment 3:

[0044] Based on the above embodiment, this embodiment further defines the shapes of the positioning mandrel 1 and the pressing sheet 3, such as Figure 1 As shown, the core 12 of the positioning mandrel 1 is cylindrical, the through hole in the middle of the pressing sheet 3 is circular, and the diameter of the through hole in the middle of the pressing sheet 3 is not less than the diameter of the core 12 of the positioning mandrel 1. The other parts of this embodiment are the same as the above embodiment and will not be repeated.

[0045] Embodiment 4:

[0046] Based on the above embodiment, this embodiment further defines the structure of the pressing sleeve 5, such as Figure 2 As shown, the pressing sleeve 5 is a cylinder with a cylindrical through hole inside, the through hole inside the pressing sleeve 5 has a diameter larger than the diameter of the shaft core 12 of the positioning mandrel 1, and the outer diameter of the pressing sleeve 5 is not larger than the outer diameter of the pressing sheet 3. The other parts of this embodiment are the same as the above embodiment and will not be repeated.

[0047] Embodiment 5:

[0048] Based on the above embodiment, this embodiment further defines the structure of the pressing sleeve 5, such as Figure 1 , Figure 3 As shown, the lower part of the pressing sleeve 5 is an open cylindrical through groove, and the diameter of the cylindrical through groove is not greater than the outer diameter of the pressing sheet 3. The other parts of this embodiment are the same as the above embodiment and will not be repeated.

[0049] Embodiment 6:

[0050] Based on the above embodiment, this embodiment further defines the structure of the pressing sleeve 5, such as Figure 2 As shown, the opening on one side of the pressing sleeve 3 is a rectangular strip hole, and the limiting piece 4 is embedded in the slot on the upper part of the shaft core 12 through the strip hole on one side of the pressing sleeve 3, and the limiting piece 4 does not contact the inner wall of the pressing sleeve 3. The other parts of this embodiment are the same as the above embodiment and will not be repeated.

[0051] Embodiment 7:

[0052] Based on the above embodiment, this embodiment further defines the structure of the pressing sleeve 5, such as Figure 1 , Figure 3 As shown, the opening on one side of the pressing sleeve 3 is an axial through slot, and the limiting piece 4 is embedded in the slot on the upper part of the shaft core 12 through the through slot on one side of the pressing sleeve 3. The other parts of this embodiment are the same as the above embodiment and will not be repeated.

[0053] Embodiment 8:

[0054] Based on the above embodiment, this embodiment further defines the structure of the limiting piece 4, such as Figure 4, the limiting piece 4 is U-shaped. In order to facilitate the limiting piece 4 to be inserted into the slot on the upper part of the shaft core 12, it is preferred that the limiting piece 4 is U-shaped. 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 the above embodiment and will not be repeated.

[0055] It is understandable that the working principles and working processes of the aviation spring tempering tooling structure according to an embodiment of the present invention, such as the pressing sheet 3 and the pressing sleeve 5, are prior art and well known to those skilled in the art, and will not be described in detail here.

[0056] Although the embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the claims and their equivalents.

Claims

1. A method for preparing an aviation spring tempering tool, characterized in that: The following steps are involved: Step S1: Investigate and study the tooling used in the tempering process of existing aviation springs to understand the technical defects of the existing tooling; Step S2: improving the existing tooling according to the technical defects thereof and providing corresponding structural design; Step S3: Experimentally manufacture the provided structural design and then apply it to the actual tempering process of the spring; Step S4: Verify whether the designed and manufactured tooling can overcome the technical defects of traditional tooling, and then improve the structure of the tooling in a targeted manner, finally obtain the finished tooling, manufacture the corresponding mold, and carry out mass production.

2. The method for preparing an aviation spring tempering tool according to claim 1, characterized in that: In step S1, the tempering tooling used in the existing aviation spring is a structure in which a bolt and a nut cooperate. The existing technical defects include that the spring to be tempered and nested on the bolt is compressed by screwing the nut into the bolt, and the clamping efficiency of the spring is low; and the difference between the bolt size and the inner diameter of the spring is too large, resulting in the spring being easily bent sideways during the compression tempering process; in addition, during the process of screwing in the nut, the spring rotates due to the force and is subjected to compressive stress and shear stress at the same time. The stress is not completely eliminated after tempering, and the comprehensive residual stress is complex.

3. The method for preparing an aviation spring tempering tool according to claim 1 or 2, characterized in that: In the step S4, the finished tooling finally obtained comprises a lower positioning mandrel (1) and an upper pressing sleeve (5), the positioning mandrel (1) being nested with a spring (2) and a pressing sheet (3) to be tempered in sequence, the pressing sleeve (5) being inserted from the upper part of the positioning mandrel (1), the bottom of the pressing sleeve (5) being in contact with the upper part of the pressing sheet (3), and the pressing sleeve (5) compressing the lower spring (2) through the pressing sheet (3); a plurality of slots are provided on the upper part of the positioning mandrel (1), and an opening is provided on one side of the pressing sleeve (5). When the pressing sleeve (5) compresses the lower spring (2) into place through the pressing sheet (3), the limiting sheet (4) is embedded into the slot on the positioning mandrel (1) through the opening on the side of the pressing sleeve (5), and at this time, the limiting sheet (4) is in contact with the lower pressing sheet (3), limiting the spring (2) from bouncing upward, and there is no need to apply pressure to the pressing sheet (3) through the pressing sleeve (5) to keep the spring (2) compressed.

4. The method for preparing an aviation spring tempering tool according to claim 3, characterized in that: 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); and the upper groove of the positioning mandrel (1) is arranged on the upper part of the shaft core (12).

5. The method for preparing an aviation spring tempering tool according to claim 4, characterized in that: The shaft core (12) of the positioning shaft (1) is cylindrical, the through hole in the middle of the pressing sheet (3) is circular, and the diameter of the through hole in the middle of the pressing sheet (3) is not less than the diameter of the shaft core (12) of the positioning shaft (1).

6. The method for preparing an aviation spring tempering tool according to claim 5, characterized in that: 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 larger than the diameter of the shaft core (12) of the positioning core shaft (1). The outer diameter of the pressing sleeve (5) is not larger than the outer diameter of the pressing sheet (3).

7. The method for preparing an aviation spring tempering tool according to claim 6, characterized in that: The lower part of the pressing sleeve (5) is an open cylindrical through groove, and the diameter of the cylindrical through groove is not greater than the outer diameter of the pressing sheet (3).

8. The method for preparing an aviation spring tempering tool according to any one of claims 4 to 7, characterized in that: The opening on one side of the pressing sleeve (3) is a rectangular strip hole, and the limiting piece (4) is embedded in the slot on the upper part of the shaft core (12) through the strip hole on one side of the pressing sleeve (3), and the limiting piece (4) does not contact the inner wall of the pressing sleeve (3).

9. A method for preparing an aviation spring tempering tool according to any one of claims 4 to 7, characterized in that: The opening on one side of the pressing sleeve (3) is an axial through slot, and the limiting piece (4) is embedded in the slot on the upper part of the shaft core (12) through the through slot on one side of the pressing sleeve (3).

10. A method for preparing an aviation spring tempering tool according to any one of claims 3 to 7, characterized in that: The limiting piece (4) is U-shaped.

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