Aviation hydraulic guide pipe assembly structure used under high-voltage and high-frequency pulse condition

Abstract

The aviation hydraulic guide pipe assembly structure used under the high-voltage and high-frequency pulse condition comprises an outer sleeve nut, a non-flaring pipe sleeve, a pipe, a filling tool and a non-flaring plug, one end of the filling tool is connected with an equipment end, and the other end of the filling tool is connected with the non-flaring plug; the filling tool is sleeved with the pipe, the two ends of the pipe are connected with the non-flaring pipe sleeves, the interiors of the non-flaring pipe sleeves are connected with the pipe in a rolling mode, the exteriors of the non-flaring pipe sleeves are connected with the outer sleeve nuts, the outer sleeve nut on one side and the non-flaring pipe sleeve are connected with the equipment end, and the outer sleeve nut on the other side and the non-flaring pipe sleeve are connected with the non-flaring plug. The pipe and the non-flaring pipe sleeve are in non-flaring rolling connection, the outer sleeve nut is in threaded connection with the equipment end and the non-flaring plug, the reliability of assembly connection can be guaranteed under certain tightening torque, and then the excellent sealing effect is guaranteed; the use of the filling tool can reduce the effective flow area of the liquid, so that the high pressure reaching speed is increased, and the accuracy and reliability of the test are effectively ensured.

Description

Technical Field

[0001] The present invention relates to the technical field of hydraulic system pipeline connections, and more particularly, to a structure of an aviation hydraulic conduit assembly under high-pressure high-frequency pulse conditions. Background Art

[0002] With the rapid development of the national aviation transportation industry, higher requirements are put forward for the safety performance of aircraft operation, among which the safety and reliability performance of the aviation pipeline system are extremely important. The hydraulic system on an aircraft is an important part of the pipeline system, and its purpose is to transport necessary materials such as oil, water, and gas for aircraft operation, and the hydraulic pipeline is an important medium for transporting materials such as oil, water, and gas. However, during the operation of the aircraft, the hydraulic pipeline is usually in complex environments such as high temperature, high pressure, and vibration, which requires high performance of the hydraulic pipeline. However, at present, there is less verification of the pipe materials under complex environments such as high temperature, high pressure, and vibration. Especially for large-sized hydraulic conduits, there are problems such as large internal space, inability to meet the pressure grade, slow pressure increase rate, and low frequency under high pressure, which lead to difficulties in verification and low numerical reliability. Summary of the Invention

[0003] In view of the above-mentioned technical problems, a structure of an aviation hydraulic conduit assembly under high-pressure high-frequency pulse conditions is provided. In the present invention, the connection between the pipe material and the non-flared ferrule adopts a non-flared rolling connection form. The outer sleeve nut is threadedly connected to the equipment end and the non-flared plug. Under a certain tightening torque, the reliability of the assembly connection can be ensured, and thus an excellent sealing effect is guaranteed; the O-ring is sleeved on the filling tooling, avoiding damage caused by contact between the filling tooling and the inner wall of the pipe material during the assembly process; at the same time, the use of the filling tooling reduces the effective flow area of the liquid, increasing the speed at which the high pressure is reached, thereby effectively ensuring the accuracy and reliability of the test.

[0004] The technical means adopted by the present invention are as follows:

[0005] A structure of an aviation hydraulic conduit assembly under high-pressure high-frequency pulse conditions, comprising: an outer sleeve nut, a non-flared ferrule, a pipe material, a filling tooling, and a non-flared plug. One end of the filling tooling is connected to the equipment end, and the other end is connected to the non-flared plug; the pipe material is sleeved on the filling tooling, and non-flared ferrules are connected to both ends of the pipe material. The inside of the non-flared ferrule is connected to the pipe material by a non-flared rolling connection. The outer sides of the non-flared ferrules are both connected to the outer sleeve nut. The outer sleeve nut and the non-flared ferrule on one side are both connected to the equipment end, and the outer sleeve nut and the non-flared ferrule on the other side are both connected to the non-flared plug; the installation directions of the outer sleeve nuts on both sides are opposite, and the installation directions of the non-flared ferrules on both sides are opposite.

[0006] Further, a plurality of grooves are formed in the outer wall of the filling tooling, and O-rings are installed in the grooves. The O-rings are fitted and connected between the pipe and the filling tooling, and the O-rings are in contact with the inner wall of the pipe.

[0007] Further, the O-ring is made of fluorosilicone rubber.

[0008] Further, a through hole is provided inside the outer sleeve nut. The inner wall of the front end of the through hole is machined with internal threads, and the internal threads of the two side outer sleeve nuts are used for fitting and connecting with the equipment end and the non-flared plug; a hexagon flange structure Ⅰ is provided at the tail end of the outer sleeve nut.

[0009] Further, a groove structure is provided inside the non-flared pipe sleeve, and the groove structure is used for fitting and connecting with the pipe during the rolling process;

[0010] A sealing structure Ⅰ is provided on the outer side of one side of the non-flared pipe sleeve, and the sealing structures Ⅰ of the two side non-flared pipe sleeves are used for fitting and connecting with the equipment end and the non-flared plug;

[0011] An outer wall Ⅱ is provided on the outer side of the middle of the non-flared pipe sleeve. A parallel end face structure is provided on the other side of the non-flared pipe sleeve. An outer wall Ⅰ is provided on the outside of the parallel end face structure. An inclined surface is provided between the outer wall Ⅱ and the outer wall Ⅰ. The outer diameter of the outer wall Ⅱ is larger than the outer diameter of the outer wall Ⅰ. The outer sleeve nut is in clearance fit with the outer wall Ⅰ. The inclined surface and the outer wall Ⅱ are used for positioning the outer sleeve nut.

[0012] Further, the sealing structure Ⅰ is a 24° conical surface. The front ends of the two side non-flared pipe sleeves are respectively inserted into the equipment end and the non-flared plug, and linear seals are respectively formed between the two 24° conical surfaces and the equipment end and the non-flared plug.

[0013] Further, the pipe is made of stainless steel, aluminum alloy or titanium alloy, and the pipe has an outer wall Ⅲ, and the outer diameter dimension of the outer wall Ⅲ is larger than 14 mm.

[0014] Further, a through hole structure is provided inside the filling tooling, and a plurality of holes communicating with the through hole structure are provided on the side wall of the filling tooling;

[0015] A thread structure Ⅰ is provided on the outer wall of one end of the filling tooling, and the thread structure Ⅰ is used for assembling and connecting with the internal thread inside the equipment end;

[0016] A boss structure is provided at the other end of the filling tooling, and the boss structure is used for clearance fit with the inner hole of the non-flared plug.

[0017] Further, a thread structure Ⅱ is provided on the outer wall of one end of the non-flared plug, and the thread structure Ⅱ is used for assembling and connecting with the internal thread of the other side outer sleeve nut;

[0018] The interior of the non-flared plug has an inner hole, and a sealing structure II is provided on one inner wall of the inner hole. The sealing structure II is used for mating connection with the non-flared tube sleeve on the other side. A hole structure communicating with the inner hole is provided on the other side of the inner hole, and the hole structure is used for clearance fit with the boss structure of the filling tooling.

[0019] The other end of the non-flared plug is provided with a hexagon flange structure II.

[0020] Further, the sealing structure II is a 24° conical surface, which is used to form a line seal with the sealing structure I of the non-flared tube sleeve on the other side.

[0021] Compared with the prior art, the present invention has the following advantages:

[0022] 1. The structure of the aviation hydraulic conduit assembly under high-pressure high-frequency pulse conditions provided by the present invention has excellent sealing performance: The non-flared tube sleeve and the pipe are connected by a non-flared rolling connection form, which increases the connection strength; at the same time, under the action of the tightening force, the outer sleeve nut is threadedly connected with the equipment end and the non-flared plug to drive the 24° conical surface of the non-flared tube sleeve to be closely connected, ensuring the reliability of the assembly connection, thereby improving the sealing performance.

[0023] 2. The structure of the aviation hydraulic conduit assembly under high-pressure high-frequency pulse conditions provided by the present invention has high reliability: The O-ring is sleeved on the filling tooling, avoiding the damage caused by the contact between the filling tooling and the inner wall of the pipe during the assembly process; at the same time, the use of the filling tooling reduces the effective flow area of the liquid, increasing the speed at which the high pressure is reached, and the liquid can reach a higher pressure level in a short time, thereby effectively ensuring the reliability of the test.

[0024] 3. The structure of the aviation hydraulic conduit assembly under high-pressure high-frequency pulse conditions provided by the present invention, the hole structure in the non-flared plug provides support for the embedding of the convex structure of the filling tooling, ensuring that the filling tooling is placed parallel inside the pipe; at the same time, under the action of a certain tightening torque, a line seal is formed at the 24° conical surface of the non-flared plug, thereby improving the sealing performance.

[0025] Based on the above reasons, the present invention can be widely promoted in the fields of hydraulic system pipeline connection and the like. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the following drawings are some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0027] Figure 1This is a schematic structural diagram of the present invention.

[0028] Figure 2 This is a schematic structural diagram of the outer sleeve nut of the present invention.

[0029] Figure 3 This is a schematic structural diagram of the non-flared pipe sleeve of the present invention.

[0030] Figure 4 This is a schematic structural diagram of the pipe material of the present invention.

[0031] Figure 5 This is a schematic structural diagram of the filling tooling of the present invention.

[0032] Figure 6 This is a schematic structural diagram of the O-ring of the present invention.

[0033] Figure 7 This is a schematic structural diagram of the non-flared plug of the present invention.

[0034] In the figure: 1. Outer sleeve nut; 2. Non-flared pipe sleeve; 3. Pipe material; 4. Filling tooling; 5. O-ring; 6. Non-flared plug;

[0035] 11. Through hole; 12. Internal thread; 13. Hexagonal flange structure I;

[0036] 21. Sealing structure I; 22. Groove structure; 23. Outer wall I; 24. Inclined surface; 25. Outer wall II;

[0037] 31. Outer wall III;

[0038] 41. Through hole structure; 42. Thread structure I; 43. Groove; 44. Hole; 45. Boss structure;

[0039] 61. Thread structure II; 62. Sealing structure II; 63. Hole structure; 64. Hexagonal flange structure II. Detailed implementation manners

[0040] It should be noted that, without conflict, the embodiments in the present invention and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0041] To make the objectives, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Apparently, the described embodiments are only a part rather than all of the embodiments of the present invention. The description of at least one exemplary embodiment below is actually only illustrative and in no way limits the present invention and its application or use. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the scope of protection of the present invention.

[0042] It should be noted that the terms used herein are for the purpose of describing particular embodiments only and are not intended to limit the exemplary embodiments of the present invention. As used herein, unless the context clearly dictates otherwise, the singular forms are also intended to include the plural forms. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, they specify the presence of the stated features, steps, operations, devices, components, and / or combinations thereof.

[0043] Unless otherwise specifically stated, the relative arrangements of the components and steps, numerical expressions and values set forth in these embodiments do not limit the scope of the present invention. At the same time, it should be clear that, for the sake of convenience of description, the dimensions of the various parts shown in the drawings are not drawn in actual proportional relationships. Technologies, methods and devices known to those of ordinary skill in the relevant art may not be discussed in detail, but where appropriate, the said technologies, methods and devices should be regarded as part of the description. In all the examples shown and discussed herein, any specific values should be construed as merely exemplary and not as a limitation. Therefore, other examples of the exemplary embodiments may have different values. It should be noted that like reference numerals and letters denote like items in the following drawings, and thus, once an item is defined in one drawing, further discussion thereof is not required in subsequent drawings.

[0044] In the description of the present invention, it should be understood that the orientation or positional relationships indicated by orientation terms such as "front, rear, upper, lower, left, right", "lateral, vertical, perpendicular, horizontal" and "top, bottom", etc. are generally based on the orientation or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description. Without contrary description, these orientation terms do not indicate and imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and thus should not be construed as limiting the scope of protection of the present invention. The orientation terms "inside, outside" refer to inside and outside relative to the contour of each component itself.

[0045] For ease of description, spatial relative terms, such as "above", "over", "on the upper surface", "upper", etc., may be used herein to describe the spatial positional relationship of one device or feature to other devices or features as shown in the figures. It should be understood that the spatial relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is inverted, a device described as "above" or "over" other devices or structures will then be positioned "below" or "under" the other devices or structures. Thus, the exemplary term "above" can include both orientations of "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the corresponding interpretations of the spatial relative descriptions used herein will be made accordingly.

[0046] In addition, it should be noted that the use of terms such as "first" and "second" to limit components is merely for the convenience of differentiating the corresponding components. Without additional statements, the above terms have no special meanings, and thus should not be construed as limiting the protection scope of the present invention.

[0047] The object of the present invention is to strictly control the quality of large-size aviation hydraulic conduits, and to provide a structure of an aviation hydraulic conduit assembly under high-pressure high-frequency pulse conditions, which is a large-size aviation hydraulic conduit structure for high-pressure high-frequency pulse fatigue with advantages such as high reliability, good sealing performance, simple structure, and few structural components.

[0048] As Figure 1 shown, a structure of an aviation hydraulic conduit assembly under high-pressure high-frequency pulse conditions of the present invention includes an outer sleeve nut 1, a non-flared tube sleeve 2, a pipe 3, a filling tooling 4, an O-ring 5, and a non-flared plug 6. The left end of the filling tooling 4 is connected to the equipment end, and the right end is connected to the non-flared plug 6; the pipe 3 is sleeved on the filling tooling 4, and the O-ring 5 is installed on the filling tooling 4 and connected between the pipe 3 and the filling tooling 4. Both ends of the pipe 3 are connected with non-flared tube sleeves 2. The inside of the non-flared tube sleeve 2 is connected with the pipe 3 by non-flared rolling connection. The outside of the non-flared tube sleeve 2 is connected with outer sleeve nuts 1. The left-side outer sleeve nut 1 and non-flared tube sleeve 2 are both connected to the equipment end, and the right-side outer sleeve nut 1 and non-flared tube sleeve 2 are both connected to the non-flared plug 6; the installation directions of the outer sleeve nuts 1 on both sides are opposite, and the installation directions of the non-flared tube sleeves 2 on both sides are opposite. Among them, after the outer sleeve nut 1 is sleeved on the pipe 3, the non-flared tube sleeve 2 and the pipe 3 are connected by non-flared rolling connection. Then, the filling tooling 4 with the O-ring 5 sleeved is first connected to the equipment end, and then the pipe 3 is sleeved on the filling tooling 4. Both ends of the pipe 3 are respectively connected to the equipment end and the non-flared plug 6.

[0049] The outer sleeve nut 1 has a rotary body feature, as shown inFigure 2 The inner part of the outer sleeve nut 1 has a through hole 11, and the inner wall at the front end of the through hole 11 is machined with an internal thread 12, which can be assembled and connected with the external thread of other pipe connection joint components. Figure 1 The internal threads 12 of the outer sleeve nuts 1 on the left and right sides are respectively connected and matched with the equipment end and the non-flared plug 6. The tail end of the outer sleeve nut 1 is provided with a hexagonal flange structure I 13, which is convenient for cooperation with an installation wrench to provide support strength.

[0050] The non-flared pipe sleeve 2 has a rotary body feature, as shown in Figure 3 The outer wall on the left side of the non-flared pipe sleeve 2 has a sealing structure I 21, as shown in Figure 3 The sealing structures I 21 of the non-flared pipe sleeves 2 on the left and right sides are respectively connected and matched with the equipment end and the non-flared plug 6. The sealing structure I 21 is a 24° conical surface. Under the action of the tightening torque, a line seal will be formed at the 24° conical surface position. Among them, the front end of the non-flared pipe sleeve 2 on the left side is inserted into the equipment end, and a line seal is formed between the 24° conical surface on the left side and the equipment end; the front end of the non-flared pipe sleeve 2 on the right side is inserted into the non-flared plug 6, and a line seal is formed between the 24° conical surface on the right side and the non-flared plug 6. The inside of the non-flared pipe sleeve 2 has a plurality of groove structures 22, which ensure that the pipe 3 is embedded in the groove structures 22 during the rolling process, ensuring the connection strength. The right end of the non-flared pipe sleeve 2 is a parallel end face structure, and the outer sleeve nut 1 has a clearance fit with the outer wall I 23 of the parallel end face structure, thereby ensuring the smooth installation of the outer sleeve nut 1. Adjacent to the outer wall I 23 is an inclined surface 24, and adjacent to the inclined surface 24 is the outer wall II 25 of the non-flared pipe sleeve 3. The outer wall II 25 is arranged on the middle outside of the non-flared pipe sleeve 2. The inclined surface 24 is continuously connected between the outer wall II 25 and the outer wall I 23. Under the action of the tightening force, the inclined surface 24 and the outer wall II 25 can better position the outer sleeve nut 1, ensuring the close connection between the internal thread 12 of the outer sleeve nut 1 and the pipe joint at the equipment end, thereby improving the sealing performance.

[0051] The pipe 3 is shown in Figure 4 and its material can be stainless steel, aluminum alloy, titanium alloy, etc. The outer diameter dimension of its outer wall III 31 is greater than 14 mm.

[0052] The filling tooling 4 has a rotary body feature and has a through hole structure 41 inside, as shown in Figure 5。The left end outer wall of the filling tooling 4 has a thread structure Ⅰ 42, which is assembled and connected with the internal thread of the equipment joint component (equipment end) under the action of the tightening torque; the outer wall of the filling tooling 4 has a plurality of grooves 43, and the grooves 43 are for facilitating the placement of the O-ring 5. The filling tooling 4 has a plurality of holes 44 that are connected to and spaced from the through-hole structure 41. The holes 44 are for facilitating the discharge of the high-pressure liquid in the through-hole structure 41, so that the liquid can quickly reach the required pressure, thereby impacting the pipe 3. The right end of the filling tooling 4 is a boss structure 45, and the boss structure 45 has a clearance fit with the inner hole of the non-flared plug 6, aiming to ensure that the filling tooling 4 is parallel inside the pipe 3 after installation.

[0053] The O-ring 5 is made of fluorosilicone rubber, see Figure 6 。Installed at the groove 43 of the filling tooling 4, the O-ring 5 contacts the inner wall of the pipe 3. Its function is to avoid contacting the inner wall of the pipe 3 during the installation of the filling tooling 4 and the test process, thereby reducing the possibility of scratching and bruising the inside of the pipe 3.

[0054] The non-flared plug 6 has a rotary body feature, see Figure 7 。The inside of the non-flared plug 6 has an inner hole. The left end outer wall of the non-flared plug 6 is a thread structure Ⅱ 61, which is assembled and connected with the internal thread 12 of the right-side outer sleeve nut 1 under the action of the tightening torque; at the same time, the left end inner wall of the inner hole of the non-flared plug 6 has a sealing structure Ⅱ 62, and the sealing structure Ⅱ 62 is a 24° conical surface, which is used to cooperate and connect with the sealing structure Ⅰ 21 of the right-side non-flared pipe sleeve 2 to form a line seal; a hole structure 63 communicating with the inner hole is provided on the right side of the inner hole to provide support for the clearance fit with the boss structure 45 in the filling tooling 4; a six-square flange structure Ⅱ 64 is provided at the right end of the non-flared plug 6 to facilitate cooperation with the installation wrench and provide support strength.

[0055] Before the test, first put the outer sleeve nut 1 on the pipe 3, and perform non-flared rolling connection on both sides of the non-flared pipe sleeve 2 and the two ends of the pipe 3. Put the O-ring 5 on the filling tooling 4, and under a certain tightening torque, thread-connect the thread structure I 42 of the filling tooling 4 with the equipment end; after complete connection, put the rolled pipe 3 on the filling tooling 4. Under the action of the O-ring 5, it effectively avoids the contact between the filling tooling 4 and the inner wall of the pipe 3, thereby reducing the possibility of scratching and bruising the inside of the pipe. Connect the internal thread 12 of the left outer sleeve nut 1 sleeved on the pipe 3 with the external thread of the equipment end. Under the action of a certain tightening torque, a line seal will be formed at the position of the sealing structure I 21 of the 24° conical surface of the non-flared pipe sleeve 2. At this time, the boss structure 45 of the filling tooling 4 will protrude from the pipe 3 and be embedded in the hole structure 63 in the non-flared plug 6 to ensure that the filling tooling 4 is parallel inside the pipe 3 after installation. Then connect the internal thread 12 of the right outer sleeve nut 1 sleeved on the pipe 3 with the thread structure II 61 of the non-flared plug 6. Under the action of a certain tightening torque, the 24° conical surface sealing structure I 21 of the non-flared pipe sleeve 2 and the 24° conical surface sealing structure II 62 at the left end of the non-flared plug 6 will form a line seal.

[0056] In the present invention, the non-flared pipe sleeve 2 and the pipe 3 are connected by a non-flared rolling connection form, so that the pipe 3 can be embedded in the internal groove structure 22 of the non-flared pipe sleeve 2, thereby increasing the connection strength and improving the reliability of the test.

[0057] The outer sleeve nut 1 and the equipment end as well as the non-flared plug 6 are thread-connected to drive the 24° conical surface of the non-flared pipe sleeve 2 to be closely connected, ensuring the reliability of the assembly connection, thereby improving the sealing performance.

[0058] The use of the filling tooling 4 reduces the effective flow area of the liquid, enabling the liquid to reach a higher pressure level in a short time, thereby effectively ensuring the reliability of the test.

[0059] The O-ring 5 is sleeved on the prefabricated groove of the filling tooling 4, avoiding the damage caused by the contact between the filling tooling 4 and the inner wall of the pipe 3 during the assembly process, thereby effectively ensuring the reliability of the test.

[0060] The hole structure 63 in the non-flared plug 6 provides support for the embedding of the protruding structure 45 of the filling tooling 4, ensuring that the filling tooling 4 is placed parallel inside the pipe 3; at the same time, under the action of a certain tightening torque, a line seal is formed at the 24° conical surface of the non-flared plug 6, thereby improving the sealing performance.

[0061] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements on some or all of the technical features; and these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. An aviation hydraulic conduit assembly structure for use under high-pressure and high-frequency pulse conditions, characterized in that: include: An outer sleeve nut (1), a non-flaring pipe sleeve (2), a pipe (3), a filling tool (4) and a non-flaring plug (6), wherein one end of the filling tool (4) is connected to the equipment end, and the other end is connected to the non-flaring plug (6); the pipe (3) is sleeved on the filling tool (4), and both ends of the pipe (3) are connected to the non-flaring pipe sleeve (2), the inside of the non-flaring pipe sleeve (2) is connected to the pipe (3) by non-flaring rolling, and the outside of the non-flaring pipe sleeve (2) is connected to the outer sleeve nut (1), the outer sleeve nut (1) and the non-flaring pipe sleeve (2) on one side are connected to the equipment end, and the outer sleeve nut (1) and the non-flaring pipe sleeve (2) on the other side are connected to the non-flaring plug (6); the installation directions of the outer sleeve nuts (1) on both sides are opposite, and the installation directions of the non-flaring pipe sleeves (2) on both sides are opposite.

2. The aviation hydraulic conduit assembly structure for use under high-pressure and high-frequency pulse conditions according to claim 1 is characterized in that: The outer wall of the filling tool (4) is provided with a plurality of grooves (43), an O-ring (5) is installed in the groove (43), the O-ring (5) is connected between the pipe (3) and the filling tool (4), and the O-ring (5) is in contact with the inner wall of the pipe (3).

3. The aviation hydraulic conduit assembly structure for use under high pressure and high frequency pulse conditions according to claim 2 is characterized in that: The O-ring (5) is made of fluorosilicone rubber.

4. The aviation hydraulic conduit assembly structure for use under high pressure and high frequency pulse conditions according to claim 1 is characterized in that: The outer sleeve nut (1) is provided with a through hole (11) inside, and the inner wall of the front end of the through hole (11) is processed with an internal thread (12). The internal threads (12) of the outer sleeve nuts (1) on both sides are used to cooperate with the equipment end and the non-flared plug (6); the tail end of the outer sleeve nut (1) is provided with a hexagonal flange structure I (13).

5. The aviation hydraulic conduit assembly structure for use under high pressure and high frequency pulse conditions according to claim 1, characterized in that: The non-expanded pipe sleeve (2) has a groove structure (22) inside, and the groove structure (22) is used to cooperate with the pipe (3) during the rolling process; The non-flared pipe sleeve (2) has a sealing structure I (21) on one side of the outside, and the sealing structures I (21) on both sides of the non-flared pipe sleeve (2) are used to cooperate with the equipment end and the non-flared plug (6) for connection; The middle outer portion of the non-flared pipe sleeve (2) has an outer wall II (25), and the other side of the non-flared pipe sleeve (2) is provided with a parallel end face structure, and the outer portion of the parallel end face structure has an outer wall I (23), and an inclined surface (24) is provided between the outer wall II (25) and the outer wall I (23), and the outer diameter of the outer wall II (25) is greater than the outer diameter of the outer wall I (23), and the outer sleeve nut (1) is clearance-matched with the outer wall I (23), and the inclined surface (24) and the outer wall II (25) are used to position the outer sleeve nut (1).

6. The aviation hydraulic conduit assembly structure for use under high-pressure and high-frequency pulse conditions according to claim 5 is characterized in that: The sealing structure I (21) is a 24° conical surface, and the front ends of the non-flared pipe sleeves (2) on both sides are respectively inserted into the equipment end and the non-flared plug (6), and the 24° conical surfaces on both sides form a line seal with the equipment end and the non-flared plug (6).

7. The aviation hydraulic conduit assembly structure for use under high pressure and high frequency pulse conditions according to claim 1, characterized in that: The material of the pipe (3) is stainless steel, aluminum alloy or titanium alloy. The pipe (3) has an outer wall III (31). The outer diameter of the outer wall III (31) is greater than 14 mm.

8. The aviation hydraulic conduit assembly structure for use under high pressure and high frequency pulse conditions according to claim 1, characterized in that: The filling tool (4) has a through hole structure (41) formed inside, and a side wall of the filling tool (4) has a plurality of holes (44) connected to the through hole structure (41); The outer wall of one end of the filling tool (4) is provided with a thread structure I (42), and the thread structure I (42) is used for assembly connection with the internal thread inside the equipment end; The other end of the filling tool (4) is provided with a boss structure (45), and the boss structure (45) is used to perform clearance fit with the inner hole of the non-expanded plug (6).

9. The aviation hydraulic conduit assembly structure for use under high pressure and high frequency pulse conditions according to claim 1, characterized in that: The outer wall of one end of the non-flared plug (6) is provided with a thread structure II (61), and the thread structure II (61) is used for assembly and connection with the internal thread (12) of the outer sleeve nut (1) on the other side; The non-expanded plug (6) has an inner hole inside, and a sealing structure II (62) is provided on the inner wall of one side of the inner hole, and the sealing structure II (62) is used to cooperate with the non-expanded pipe sleeve (2) on the other side, and a hole structure (63) connected to the inner hole is provided on the other side of the inner hole, and the hole structure (63) is used to perform clearance cooperation with the boss structure (45) of the filling tool (4); The other end of the non-expanded plug (6) is provided with a hexagonal flange structure II (64).

10. The aviation hydraulic conduit assembly structure for use under high pressure and high frequency pulse conditions according to claim 9, characterized in that: The sealing structure II (62) is a 24° conical surface, and is used to form a line seal with the sealing structure I (21) on the other side without the expanded pipe sleeve (2).

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