Processing technology of high-toughness aviation fastener

Abstract

The invention discloses a processing technology of a high-toughness aviation fastener, which relates to the technical field of fasteners, and comprises the following steps: machining a titanium alloy or nickel-based alloy blank to obtain a screw rod piece with a proper size; machining such as turning and milling is conducted on the screw rod piece, and a coarse thread part and a fine thread part are obtained; the method comprises the following steps: respectively carrying out thread processing on a coarse thread part and a fine thread part to obtain a bottom bearing nut and a locking nut, carrying out quality inspection and testing on the processed coarse thread part and fine thread part, including size detection, tensile strength test and corrosion resistance detection, and selecting a high-strength and high-toughness material such as a titanium alloy or a nickel-based alloy as a basis, so as to obtain the high-strength and high-toughness anti-corrosion nut. And the processed high-toughness aviation fastener is subjected to a plurality of processes such as quality inspection, testing, heat treatment and surface treatment, so that the stability and durability of the fastener in high-pressure, high-temperature and high-vibration environments can be remarkably improved, the safety and performance of the fastener can be favorably improved, and the high requirement of the aviation industry on the fastener can be met.

Description

Technical Field

[0001] The invention relates to the technical field of fasteners, in particular to a processing technology for high-toughness aviation fasteners. Background Art

[0002] The processing technology of high-toughness aviation fasteners refers to the production process of fasteners (such as bolts, nuts, etc.) used in the manufacturing of aviation, which aims to improve the toughness and strength of its materials to ensure reliability and durability under high pressure, high temperature and high vibration environments. This processing technology of high-toughness aviation fasteners plays a vital role in the aviation industry and can improve the safety and performance of aircraft and spacecraft.

[0003] In the aviation field, fasteners are important components that connect and fix aircraft structures and are crucial to the safety and performance of aircraft. However, traditional fasteners are prone to loosening and breaking under high pressure, high temperature and high vibration environments.

[0004] Based on this, the present invention designs a processing technology for high-toughness aviation fasteners to solve the above-mentioned problems. Summary of the invention

[0005] The object of the present invention is to provide a processing technology for high-toughness aviation fasteners to solve the above-mentioned problems.

[0006] To achieve the above object, the present invention provides the following technical solution: comprising the following steps:

[0007] S1: machining a titanium alloy or nickel-based alloy blank to obtain a screw member of suitable size;

[0008] S2: turning, milling, etc. are performed on the screw rod to obtain a coarse thread portion and a fine thread portion;

[0009] S3: The coarse thread portion and the fine thread portion are threaded respectively to obtain a bottom bearing nut and a locking nut.

[0010] Based on the above technical features, this solution uses titanium alloy or nickel-based alloy as the raw materials for screw parts. Titanium alloy and nickel-based alloy have the advantages of high strength, corrosion resistance, fatigue resistance, light weight and high temperature resistance in the field of bolt manufacturing, making them an ideal material choice in the aerospace field. Through reasonable material selection and processing technology, it can ensure that the bolts maintain stability and reliability in harsh aviation working environments.

[0011] Preferably, in the above-mentioned processing technology of a high-toughness aviation fastener, in the step S, the processed coarse threaded portion and fine threaded portion are subjected to quality inspection and testing, including dimensional inspection, tensile strength test, and corrosion resistance test.

[0012] Based on the above technical features, this solution can verify whether the key dimensions such as length, diameter, and thread of the coarse thread part and the fine thread part meet the design requirements by performing dimensional inspection on the processed coarse thread part and the fine thread part, thereby ensuring the precise matching and reliable installation of the fasteners. By performing tensile strength tests on the processed coarse thread part and the fine thread part, the maximum load-bearing capacity of the screw under tensile loading can be measured, and its strength and reliability can be evaluated to ensure that it can withstand the designed working load. By performing corrosion resistance testing on the processed coarse thread part and the fine thread part, the corrosion conditions of the screw in the actual working environment can be simulated, and the resistance of the fastener to corrosive media can be evaluated to ensure its long-term stable operation in a corrosive environment.

[0013] Preferably, in the processing technology of the above-mentioned high-toughness aviation fastener, in the step S, the bottom bearing nut and the locking nut are subjected to surface treatment, such as sandblasting, polishing, plating and the like, to improve the surface smoothness and corrosion resistance of the bottom bearing nut and the locking nut.

[0014] Based on the above technical features, this solution can improve the surface quality, corrosion resistance and connection performance of the bottom bearing nut and the locking nut by sandblasting, polishing and plating. These treatment measures help to ensure the reliability and durability of aviation fasteners in harsh environments and high-demand applications.

[0015] Preferably, in the processing technology of the above-mentioned high-toughness aviation fastener, in the step S, advanced heat treatment methods such as surface carburizing, nitriding, etc. are applied to the bottom bearing nut and the locking nut to increase the hardness and wear resistance of the bottom bearing nut and the locking nut.

[0016] Based on the above technical features, this solution can improve the hardness, corrosion resistance, fatigue resistance, friction performance and surface quality of the bottom bearing nut and the locking nut by carburizing and nitriding. These treatment measures can improve the durability and reliability of aviation fasteners in harsh environments and high-demand applications, ensure their normal operation and reduce the risk of failure.

[0017] Preferably, in the processing technology of the above-mentioned high-toughness aviation fastener, a screw head is welded to the bottom of the screw rod, and an anti-slip gasket is also laid on the inner side of the screw head.

[0018] Based on the above technical features, this solution can improve the fastening force, prevent loosening and disengagement, reduce damage, and increase reusability by laying an anti-slip gasket on the inner side of the screw head. These effects help to ensure the reliability and durability of the fasteners in actual use and reduce the safety and quality risks caused by loosening.

[0019] Preferably, in the processing technology of the above-mentioned high-toughness aviation fastener, an annular groove is provided around one side of the bottom bearing nut, a convex block is provided in the middle of one side of the bottom bearing nut close to the annular groove, a first threaded hole is penetrated through the middle of the convex block, the first threaded hole matches the structure of the coarse threaded portion, the first threaded hole and the coarse threaded portion are threadedly matched, and the top of the convex block is also engraved with a first anti-slip pattern around it.

[0020] Based on the above technical features, this solution uses a first threaded hole that penetrates the middle of the convex block. Since the first threaded hole matches the structure of the coarse threaded portion, the bottom bearing nut can be threadedly connected to the top of the coarse threaded portion.

[0021] Preferably, in the processing technology of the above-mentioned high-toughness aviation fastener, an annular clamp is installed around one side of the locking nut, a concave groove is opened in the middle of one side of the locking nut close to the annular clamp, and a second anti-slip pattern is carved around the bottom of the concave groove. A second threaded hole is also opened through the middle of the bottom of the concave groove, and the second threaded hole matches the fine threaded part structure, and the second threaded hole and the fine threaded part are threadedly matched.

[0022] Based on the above technical features, this solution is to thread the locking nut to the bottom end of the coarse threaded portion by opening a second threaded hole through the middle of the bottom of the concave groove. Since the second threaded hole matches the structure of the fine threaded portion, the locking nut is threadedly connected to the bottom end of the coarse threaded portion.

[0023] Preferably, in the processing technology of the above-mentioned high-toughness aviation fastener, the annular clamping plate and the annular clamping groove are plug-fitted, the concave groove and the convex block are transitionally fitted, and the second anti-slip pattern and the first anti-slip pattern are meshingly connected.

[0024] Based on the above technical features, this solution can tightly fit the bottom bearing nut and the locking nut together through the convex block, the concave groove, the annular clamping plate and the annular clamping groove structure, and can also play a role of sealing and protecting the tightly fitted bottom bearing nut and the locking nut, and can effectively prevent dust and other impurities from penetrating into the gap connecting the two groups, thereby avoiding the situation where the bottom bearing nut and the locking nut cannot be separated due to corrosion and rust. Through the first anti-slip texture and the second anti-slip texture, since the second anti-slip texture and the first anti-slip texture are meshingly connected, it can also play a locking role for the tightly fitted bottom bearing nut and the locking nut, and can effectively prevent the bottom bearing nut and the locking nut from loosening in a severe shaking usage scenario.

[0025] Compared with the prior art, the beneficial effects of the present invention are: the high-toughness aviation fastener processing technology of the present invention selects high-strength and high-toughness materials such as titanium alloy or nickel-based alloy as the basis, and performs quality inspection, testing, heat treatment, surface treatment and other processes on the processed high-toughness aviation fasteners, which can significantly improve the stability and durability of the fasteners in high pressure, high temperature and high vibration environments, which will help to improve the safety and performance of the fasteners, thereby meeting the high requirements of the aviation industry for fasteners. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings required for describing the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other accompanying drawings can be obtained based on these accompanying drawings without paying creative work.

[0027] Figure 1 It is a processing flow chart of the present invention;

[0028] Figure 2 It is a schematic diagram of the overall structure of the fastener of the present invention;

[0029] Figure 3 It is a schematic diagram of the structure of the screw rod of the present invention;

[0030] Figure 4 It is a schematic diagram of the bottom bearing nut structure of the present invention;

[0031] Figure 5 It is a schematic diagram of the locking nut structure of the present invention.

[0032] In the accompanying drawings, the components represented by the reference numerals are listed as follows:

[0033] 100, screw member; 101, coarse threaded portion; 102, fine threaded portion; 103, screw head; 104, anti-skid gasket; 200, bottom bearing nut; 201, annular groove; 202, convex block; 203, first threaded hole; 204, first anti-skid pattern; 300, locking nut; 301, annular clamping plate; 302, concave groove; 303, second anti-skid pattern; 304, second threaded hole. DETAILED DESCRIPTION

[0034] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0035] See also Figure 1-3 A processing technology for high-toughness aviation fasteners, the processing technology comprises the following steps:

[0036] S1: machining a titanium alloy or nickel-based alloy blank to obtain a screw member 100 of a suitable size;

[0037] S2: performing turning, milling, and other processing on the screw member 100 to obtain a coarse thread portion 101 and a fine thread portion 102;

[0038] S3: The coarse threaded portion 101 and the fine threaded portion 102 are threadedly processed to obtain a bottom bearing nut 200 and a locking nut 300. In this solution, titanium alloy or nickel-based alloy is used as the raw material of the screw member 100. Titanium alloy and nickel-based alloy have the advantages of high strength, corrosion resistance, fatigue resistance, light weight and high temperature resistance in the field of bolt manufacturing, making them an ideal material choice in the aerospace field. Through reasonable material selection and processing technology, it can ensure that the bolts maintain stability and reliability in harsh aviation working environments.

[0039] In step S2, the processed coarse threaded portion 101 and the fine threaded portion 102 are subjected to quality inspection and testing, including dimension inspection, tensile strength test, and corrosion resistance test. By performing dimension inspection on the processed coarse threaded portion 101 and the fine threaded portion 102, it is possible to verify whether the key dimensions such as the length, diameter, and thread of the coarse threaded portion 101 and the fine threaded portion 102 meet the design requirements, thereby ensuring the precise matching and reliable installation of the fasteners. By performing tensile strength test on the processed coarse threaded portion 101 and the fine threaded portion 102, it is possible to measure the maximum load-bearing capacity of the screw member 100 under tensile loading, evaluate its strength and reliability, and ensure that it can withstand the designed workload. By performing corrosion resistance test on the processed coarse threaded portion 101 and the fine threaded portion 102, it is possible to simulate the corrosion conditions of the screw member 100 in an actual working environment, evaluate the resistance of the fastener to corrosive media, and ensure its long-term stable operation in a corrosive environment.

[0040] In step S3, the bottom bearing nut 200 and the locking nut 300 are subjected to surface treatment, such as sandblasting, polishing, plating and other processes, to improve the surface finish and corrosion resistance of the bottom bearing nut 200 and the locking nut 300. By sandblasting, polishing and plating the bottom bearing nut 200 and the locking nut 300, their surface quality, corrosion resistance and connection performance can be improved. These treatment measures help to ensure the reliability and durability of aviation fasteners in harsh environments and high-demand applications.

[0041] In step S3, advanced heat treatment methods such as surface carburizing and nitriding are applied to the bottom bearing nut 200 and the locking nut 300 to increase the hardness and wear resistance of the bottom bearing nut 200 and the locking nut 300. By carburizing and nitriding the bottom bearing nut 200 and the locking nut 300, their hardness, corrosion resistance, fatigue resistance, friction performance and surface quality can be improved. These treatment measures can improve the durability and reliability of aviation fasteners in harsh environments and high-demand applications, ensure their normal operation and reduce the risk of failure.

[0042] Please refer to the attached figure in the instruction manual Figure 2-5 , a processing technology for high-toughness aviation fasteners, a screw head 103 is welded at the bottom of the screw member 100, and an anti-slip pad 104 is also laid on the inner side of the screw head 103. The anti-slip pad 104 laid on the inner side of the screw head 103 can improve the fastening force, prevent loosening and loosening, reduce damage, and increase reusability. These effects help to ensure the reliability and durability of the fasteners in actual use and reduce the safety and quality risks caused by loosening.

[0043] An annular groove 201 is provided around one side of the bottom bearing nut 200, and a convex block 202 is provided in the middle of one side of the bottom bearing nut 200 close to the annular groove 201. A first threaded hole 203 is penetrated through the middle of the convex block 202. The first threaded hole 203 matches the structure of the coarse threaded portion 101, and the first threaded hole 203 and the coarse threaded portion 101 are threadedly matched. The top of the convex block 202 is also engraved with a first anti-slip pattern 204 around it. Through the first threaded hole 203 penetrated through the middle of the convex block 202, because the first threaded hole 203 matches the structure of the coarse threaded portion 101, the bottom bearing nut 200 can be threadedly connected to the top of the coarse threaded portion 101.

[0044] A concave groove 302 is provided in the middle of one side of the locking nut 300 close to the annular clamping plate 301, and a second anti-slip pattern 303 is carved around the bottom of the concave groove 302. A second threaded hole 304 is also provided through the middle of the bottom of the concave groove 302. The second threaded hole 304 matches the structure of the fine threaded portion 102, and the second threaded hole 304 and the fine threaded portion 102 are threadedly matched. Through the second threaded hole 304 provided through the middle of the bottom of the concave groove 302, the locking nut 300 is threadedly connected to the bottom end of the coarse threaded portion 101 because the second threaded hole 304 matches the structure of the fine threaded portion 102.

[0045] The annular clamping plate 301 and the annular clamping groove 201 are plug-in fit, the concave groove 302 and the convex block 202 are transition fit, and the second anti-skid pattern 303 and the first anti-skid pattern 204 are meshing connection. When the bottom bearing nut 200 and the locking nut 300 are threadedly connected to the coarse threaded portion 101 and the fine threaded portion 102 respectively, the bottom bearing nut 200 and the locking nut 300 can be closely fitted together through the convex block 202, the concave groove 302, the annular clamping plate 301 and the annular clamping groove 201 structure, and the closely fitted bottom bearing nut 200 and the locking nut 300 can also be used to It can achieve the effect of sealing protection and can effectively prevent dust and other impurities from penetrating into the gap between the two groups, thereby avoiding the situation that the bottom nut 200 and the locking nut 300 cannot be separated due to corrosion and rust. Through the first anti-slip pattern 204 and the second anti-slip pattern 303, since the second anti-slip pattern 303 and the first anti-slip pattern 204 are meshed, the bottom nut 200 and the locking nut 300 that are tightly fitted can also be locked, which can effectively prevent the bottom nut 200 and the locking nut 300 from loosening in a severe shaking usage scenario.

[0046] Working principle: When the bottom bearing nut 200 and the locking nut 300 are threadedly connected to the coarse threaded portion 101 and the fine threaded portion 102 respectively, the bottom bearing nut 200 and the locking nut 300 can be tightly fitted together by means of the convex block 202 installed in the middle of one side of the bottom bearing nut 200 and the concave groove 302 opened in the middle of one side of the locking nut 300, because there is a transition fit between the concave groove 302 and the convex block 202, and the first anti-slip lines 204 carved around the top of the convex block 202 and the second anti-slip lines 303 carved around the bottom of the concave groove 302 can also be meshed with the first anti-slip lines 204, so that the tightly fitted bottom bearing nut can be tightened. The nut 200 and the locking nut 300 play a locking role, which can effectively prevent the bottom bearing nut 200 and the locking nut 300 from loosening in a severe shaking usage scenario, and cooperate with the annular groove 201 opened around one side of the bottom bearing nut 200, and the annular clamping plate 301 installed around one side of the locking nut 300. Because the annular clamping plate 301 and the annular groove 201 are plug-in fit, they can also play a sealing and protective role for the tightly fitted bottom bearing nut 200 and the locking nut 300, and can effectively prevent dust and other impurities from penetrating into the gap connecting the two groups, thereby avoiding the situation where the bottom bearing nut 200 and the locking nut 300 cannot be separated due to corrosion and rust.

[0047] In the description of this specification, the description with reference to the terms "one embodiment", "example", "specific example", etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0048] The preferred embodiments of the present invention disclosed above are only used to help illustrate the present invention. The preferred embodiments do not describe all the details in detail, nor do they limit the invention to the specific implementation methods described. Obviously, many modifications and changes can be made according to the content of this specification. This specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the present invention, so that those skilled in the art can understand and use the present invention well. The present invention is limited only by the claims and their full scope and equivalents.

Claims

1. A processing technology for high-toughness aviation fasteners, comprising the following steps: S1: machining a titanium alloy or nickel-based alloy blank to obtain a screw member (100) of suitable size; S2: performing turning, milling, or other processing on the screw member (100) to obtain a coarse threaded portion (101) and a fine threaded portion (102); S3: Thread processing is performed on the coarse threaded portion (101) and the fine threaded portion (102) respectively to obtain a bottom bearing nut (200) and a locking nut (300).

2. The processing technology of a high-toughness aviation fastener according to claim 1 is characterized in that: In the step S2, the processed coarse threaded portion (101) and the fine threaded portion (102) are subjected to quality inspection and testing, including dimensional inspection, tensile strength test, and corrosion resistance test.

3. A processing technology for a high-toughness aviation fastener according to claim 2, characterized in that: In the step S3, the bottom bearing nut (200) and the locking nut (300) are subjected to surface treatment, such as sandblasting, polishing, plating and the like, to improve the surface finish and corrosion resistance of the bottom bearing nut (200) and the locking nut (300).

4. The processing technology of a high-toughness aviation fastener according to claim 3 is characterized in that: In step S3, an advanced heat treatment method, such as surface carburizing, nitriding, etc., is applied to the bottom bearing nut (200) and the locking nut (300) to increase the hardness and wear resistance of the bottom bearing nut (200) and the locking nut (300).

5. The processing technology of a high-toughness aviation fastener according to claim 4 is characterized in that: A screw head (103) is welded to the bottom of the screw rod (100), and an anti-slip pad (104) is laid on the inner side of the screw head (103).

6. A processing technology for high-toughness aviation fasteners according to claim 5, characterized in that: An annular groove (201) is provided around one side of the bottom bearing nut (200); a convex block (202) is provided in the middle of one side of the bottom bearing nut (200) close to the annular groove (201); a first threaded hole (203) is provided through the middle of the convex block (202); the first threaded hole (203) matches the structure of the coarse threaded portion (101); the first threaded hole (203) and the coarse threaded portion (101) are threadedly matched; and first anti-slip patterns (204) are also engraved around the top of the convex block (202).

7. The processing technology of a high-toughness aviation fastener according to claim 6, characterized in that: An annular clamping plate (301) is installed around one side of the locking nut (300), and a concave groove (302) is opened in the middle of one side of the locking nut (300) close to the annular clamping plate (301). The bottom of the concave groove (302) is engraved with a second anti-slip pattern (303) around the bottom, and a second threaded hole (304) is also opened through the middle of the bottom of the concave groove (302). The second threaded hole (304) matches the structure of the fine threaded portion (102), and the second threaded hole (304) and the fine threaded portion (102) are threadedly matched.

8. The processing technology of a high-toughness aviation fastener according to claim 7 is characterized in that: The annular clamping plate (301) and the annular clamping groove (201) are plug-fitted, the concave groove (302) and the convex block (202) are transitionally matched, and the second anti-slip pattern (303) and the first anti-slip pattern (204) are meshingly connected.

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