Assembly type aviation conduit wall defect repairing device
The kit, consisting of a detachable main body, accessories, and extension parts, solves the problems of inconvenience and high cost of existing aviation duct repair devices, enabling efficient repair of ducts of different specifications and lengths and avoiding secondary damage.
Patent Information
- Application Number
- CN202520620760.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-03
- Publication Date
- 2026-01-02
- Estimated Expiration
- 2035-04-03
AI Technical Summary
Existing aviation duct repair devices are bulky, inconvenient to carry, and require the manufacture of various toolings when repairing ducts of different specifications, resulting in low utilization and high material consumption when repairing long ducts.
The main body, accessories, and extensions are detachably connected and assembled via threaded connections to form a kit that can accommodate the repair needs of catheters of different diameters and lengths.
It enables efficient repair of catheters of various diameters and lengths, avoids secondary damage, is easy to carry and assemble, and improves repair efficiency and utilization.
Smart Images
Figure CN223754969U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to aviation conduit repair technical field more specifically relates to a kind of aviation conduit pipe wall defect repair device of assembly type. BACKGROUND
[0002] Aviation conduit is mainly used to deliver fuel, oil, hydraulic oil, air and oxygen and other working media for engine and aircraft, and any mechanical damage to the pipe wall of the conduit can affect the flow rate of the liquid or gas in the pipe, thereby affecting the flight quality of the aircraft, and in severe cases, can cause the conduit to break and result in a flight accident. Current conduit repair mainly relies on single-specification inner lining tooling, which has the following disadvantages: the inner lining tooling is heavy and difficult to transport and carry; when repairing conduits of different specifications, multiple diameters of tooling need to be manufactured, resulting in low utilization rate; when repairing long conduits, the inner lining tooling needs to be lengthened, resulting in high material consumption rate.
[0003] Therefore, there is a need for a kind of aviation conduit pipe wall defect repair device of assembly type, which can repair aviation conduits of different diameters and has the advantages of convenient assembly, transportation and carrying, and realizes high-quality and high-efficiency conduit defect repair. SUMMARY
[0004] Therefore, the utility model provides a kind of aviation conduit pipe wall defect repair device of assembly type, to solve the above technical problems.
[0005] To achieve the above purpose, the utility model adopts the following technical solutions:
[0006] A kind of aviation conduit pipe wall defect repair device of assembly type, comprising: detachably connected main body, accessory and lengthening piece;
[0007] The main body is used to be connected with clamp, is fixed on the clamp, and the side wall of the main body has first threaded hole;
[0008] One end of the accessory has first threaded column, the first threaded column is used to be fastened with the first threaded hole, the number of the accessory is multiple, and it is different in size and diameter;
[0009] The lengthening piece is selectively configured between the main body and the accessory according to demand, one end of the lengthening piece has second threaded column, the other end of the lengthening piece has second threaded hole, when the lengthening piece is selected to be used, the second threaded column is fastened with the first threaded hole, and the second threaded hole is fastened with the first threaded column.
[0010] Through the technical scheme, the utility model discloses a set of kits are formed through main body spare, accessory and lengthening spare, through the main body spare combination lengthening spare and different specifications' accessory, can effectively repair various diameter's aviation conduit, and the repair efficiency is high, overcomes the traditional conduit defect repair tooling repair efficiency low, cost is high, and the shortcoming of not being convenient for carrying is overcome.
[0011] Preferably, in the above-mentioned aviation conduit wall defect repair device, the main body includes a rectangular body and an arc-shaped head provided on the top surface of the rectangular body, and the arc-shaped head protrudes from the side walls of the rectangular body at both sides of the arc-shaped head, so that when the clamp clamps the two side walls of the rectangular body, the arc-shaped head forms an upper and lower limiting structure.
[0012] Preferably, in the above-mentioned aviation conduit wall defect repair device, the two end surfaces of the rectangular body not clamped by the clamp are each provided with the first threaded hole.
[0013] Preferably, in the above-mentioned aviation conduit wall defect repair device, the end of the accessory away from the first threaded column has a hemispherical head structure.
[0014] Preferably, in the above-mentioned aviation conduit wall defect repair device, the size of the accessory includes Φ14, Φ12, Φ10 and Φ8, which can effectively repair various diameter aviation conduits with high repair efficiency.
[0015] Preferably, in the above-mentioned aviation conduit wall defect repair device, the end of the lengthening spare close to the second threaded column has a radially protruding limiting block.
[0016] Preferably, in the above-mentioned aviation conduit wall defect repair device, the two sides of the limiting block are processed as flat surfaces, and when the lengthening spare is connected with the main body, the two flat surfaces of the limiting block are flush with the two side surfaces of the main body and are clamped together by the clamp.
[0017] Preferably, in the above-mentioned aviation conduit wall defect repair device, the accessory and the lengthening spare are both cylindrical bodies with smooth surfaces and no sharp edges, which will not cause secondary damage to the conduit.
[0018] Through the above technical scheme, compared with the prior art, the utility model discloses a kind of, with following beneficial effects:
[0019] 1. The aviation conduit wall defect repair device can be assembled according to different diameters of the conduit to install different specifications of the accessory.
[0020] 2. The device can install the lengthening spare to repair conduits of different lengths.
[0021] 3. The device has assemblability, is convenient to carry, can realize repair of the inner field conduit, and can also complete the modification of the outer field conduit defect.
[0022] 4. The surface of the main body, the lengthening piece and the accessory is smoothly treated, so as to avoid secondary damage to the conduit. BRIEF DESCRIPTION OF DRAWINGS
[0023] In order to more clearly illustrate the technical scheme in the embodiments of the present application or the prior art, the drawings needed to be used in the embodiment or the prior art description will be briefly introduced as follows. Obviously, the drawings in the following description are only the embodiments of the present application, and for those skilled in the art, other drawings can also be obtained according to the provided drawings without creative labor.
[0024] Figure 1 The drawing is an exploded structure schematic view of the assemblable aviation conduit wall defect repair device provided by the present application;
[0025] Figure 2 The drawing is a structure schematic view of the main body provided by the present application;
[0026] Figure 3 The drawing is a perspective view of the main body provided by the present application;
[0027] Figure 4 The drawing is a structure schematic view of the lengthening piece provided by the present application;
[0028] Figure 5 The drawing is a structure schematic view of the accessory with a diameter of Ф8 provided by the present application;
[0029] Figure 6 The drawing is a structure schematic view of the accessory with a diameter of Ф10 provided by the present application;
[0030] Figure 7 The drawing is a structure schematic view of the accessory with a diameter of Ф12 provided by the present application;
[0031] Figure 8 The drawing is a structure schematic view of the accessory with a diameter of Ф14 provided by the present application.
[0032] Wherein:
[0033] 1. The main body;
[0034] 11. The rectangular body; 111. The first threaded hole; 12. The arc-shaped head;
[0035] 2. The accessory;
[0036] 21. The first threaded column; 22. The half-sphere head structure;
[0037] 3-elongated piece;
[0038] 31-second threaded column; 32-second threaded hole; 33-limiting block; 331-flat surface; DETAILED DESCRIPTION
[0039] The technical solutions in the embodiments of the utility model will be clearly and completely described below with reference to the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the utility model.
[0040] Referring to the drawings, Figure 1 The utility model discloses an aviation guide pipe wall defect repairing device of assembly type, comprising: detachable connection main part 1, accessory 2 and elongated piece 3.
[0041] The main part 1 is used for being connected with the clamp, is fixed on the clamp, and the side wall of the main part 1 is provided with a first threaded hole 111.
[0042] One end of the accessory 2 is provided with a first threaded column 21, and the first threaded column 21 is used for being fastened and connected with the first threaded hole 111, the number of the accessory 2 is multiple, and the size and diameter of the accessory 2 are different.
[0043] The elongated piece 3 is selectively arranged between the main part 1 and the accessory 2 according to requirements, one end of the elongated piece 3 is provided with a second threaded column 31, and the other end of the elongated piece 3 is provided with a second threaded hole 32, when the elongated piece 3 is selected to be used, the second threaded column 31 is fastened and connected with the first threaded hole 111, and the second threaded hole 32 is fastened and connected with the first threaded column 21.
[0044] Referring to the drawings, Figure 2 and the drawings, Figure 3 The main part 1 comprises a rectangular body 11 and an arc-shaped head 12 arranged on the top surface of the rectangular body 11, and the arc-shaped head 12 is protruded from the side wall of the rectangular body 11 at both sides of the arc-shaped head 12, so that when the clamp clamps the two side walls of the rectangular body 11, the arc-shaped head 12 forms the limiting structure upward and downward.
[0045] In the embodiment, the first threaded hole 111 is arranged on the two end surfaces of the rectangular body 11 which are not clamped by the clamp.
[0046] Referring to the drawings, Figure 5 One end of the accessory 2 away from the first threaded column 21 is provided with a hemispherical head structure 22.
[0047] Referring to the drawings, Figure 5 to the drawings, Figure 8 The size and diameter of the accessory 2 include Φ14, Φ12, Φ10 and Φ8.
[0048] Referring to the drawings Figure 4 The lengthening piece 3 has a radial protruding limiting block 33 at one end close to the second threaded column 31.
[0049] To further optimize the above technical solution, the two sides of the limiting block 33 are processed into planes 331, and when the lengthening piece 3 is connected with the main body piece 1, the two side planes 331 of the limiting block 33 are flush with the two side surfaces of the main body piece 1 and are clamped together by the clamp.
[0050] To further optimize the above technical solution, the accessory 2 and the lengthening piece 3 are both cylindrical.
[0051] The specific process of the use method of the detachable aviation conduit wall defect repairing device provided by the embodiment is as follows:
[0052] 1. The main body piece 1 is clamped on the clamp on the workbench;
[0053] 2. The first threaded column 21 of the accessory 2 is inserted into the first threaded hole 111 of the main body piece 1 and is tightened;
[0054] 3. If conduits of different diameters are repaired, different specifications of the accessory 2 are inserted into the two ends of the main body piece 1 and are tightened;
[0055] 4. If long conduits are repaired, the lengthening piece 3 is inserted between the main body piece 1 and the accessory 2.
[0056] The embodiments in the specification are described in a progressive manner, and each embodiment focuses on the difference from other embodiments. The same and similar parts of each embodiment can be referred to each other. For the device disclosed by the embodiments, since it corresponds to the method disclosed by the embodiments, the description is relatively simple, and the related parts can be referred to the method part.
[0057] The above description of the disclosed embodiments enables a person skilled in the art to implement or use the present application. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application will not be limited to the embodiments shown herein, but will conform to the widest scope consistent with the principles and novel features disclosed herein.
Claims
1. An assemblable device for repairing defects in the wall of aviation ducts, characterized in that, The utility model relates to a detachable connecting body piece (1), accessory (2) and lengthening piece (3) are connected, the body piece (1) is used to be connected with clamp, is fixed on the clamp, the side wall of body piece (1) has first threaded hole (111), the accessory (2) one end has first threaded column (21), and first threaded column (21) is used to be fastened with first threaded hole (111) connection, the number of accessory (2) is multiple, and is different size diameter model, lengthening piece (3) is selectively configured between body piece (1) and accessory (2) according to demand, one end of lengthening piece (3) has second threaded column (31), the other end of lengthening piece (3) has second threaded hole (32), when lengthening piece (3) is selected to use, second threaded column (31) is fastened with first threaded hole (111) connection, and second threaded hole (32) is fastened with first threaded column (21) connection. The body piece (1) includes a rectangular body (11) and an arc-shaped head (12) provided on the top surface of the rectangular body (11), the arc-shaped head (12) has two arc-shaped tips protruding from the side walls of the rectangular body (11), so that when the clamp clamps the two side walls of the rectangular body (11), the arc-shaped head (12) forms an upper and lower limiting structure. The rectangular body (11) has two end surfaces not clamped by the clamp, and each end surface is provided with the first threaded hole (111). The accessory (2) has a hemispherical head structure (22) at the end away from the first threaded column (21). The size diameter of the accessory (2) includes Φ14, Φ12, Φ10 and Φ8.
2. An aircraft duct wall defect repair device according to claim 1, wherein, The lengthening piece (3) has a radial protruding limiting block (33) at one end close to the second threaded column (31).
3. An aircraft duct wall defect repair device according to claim 2, wherein, The two sides of the limiting block (33) are processed into flat surfaces (331), and when the lengthening piece (3) is connected with the body piece (1), the two side flat surfaces (331) of the limiting block (33) are flush with the two side surfaces of the body piece (1) and are clamped together by the clamp.
4. The field replaceable aircraft duct wall defect repair device of claim 1, wherein, The accessory (2) and the lengthening piece (3) are both cylindrical.
5. The field replaceable aircraft duct wall defect repair device of claim 1, wherein, 6. The field installable aircraft duct wall defect repair device of claim 1, wherein, 7. An aircraft duct wall defect repair device according to claim 6, wherein, 8. The field-assemblable aircraft duct wall defect repair device of Claim 1, wherein,