CN112503258A - High-pressure hydraulic pipeline installation structure and method - Google Patents
High-pressure hydraulic pipeline installation structure and method Download PDFInfo
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- CN112503258A CN112503258A CN202011240835.6A CN202011240835A CN112503258A CN 112503258 A CN112503258 A CN 112503258A CN 202011240835 A CN202011240835 A CN 202011240835A CN 112503258 A CN112503258 A CN 112503258A
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- pipeline
- pressure hydraulic
- frame
- machine body
- hydraulic line
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L3/00—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets
- F16L3/08—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets substantially surrounding the pipe, cable or protective tubing
- F16L3/10—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets substantially surrounding the pipe, cable or protective tubing divided, i.e. with two or more members engaging the pipe, cable or protective tubing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L43/00—Bends; Siphons
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L55/00—Devices or appurtenances for use in, or in connection with, pipes or pipe systems
- F16L55/02—Energy absorbers; Noise absorbers
- F16L55/033—Noise absorbers
- F16L55/035—Noise absorbers in the form of specially adapted hangers or supports
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The application belongs to the technical field of hydraulic pipeline installation, and particularly relates to a high-pressure hydraulic pipeline installation structure and method. The structure includes: the machine body comprises a machine body weak frame, a machine body strong frame, a pipeline mounting support and a high-pressure hydraulic pipeline. The machine body weak frame and the machine body strong frame are both arranged on the aircraft skin, and the machine body strong frame is provided with a through hole for a high-pressure hydraulic pipeline to pass through; the pipeline mounting brackets comprise a plurality of pipeline mounting brackets, the pipeline mounting brackets are respectively mounted on the machine body weak frame and the machine body strong frame, metal rubber is arranged at the joint of the pipeline mounting brackets and the machine body strong frame, and pipeline clamps are mounted on the pipeline mounting brackets; the pipe joints are respectively installed at the two ends of the high-pressure hydraulic pipeline, and the high-pressure hydraulic pipeline is sequentially installed on the pipeline hoop of the pipeline installation support at the corresponding position to be connected with the machine body weak frame and the machine body strong frame. This application can reduce the installation stress, reduces the influence of hydraulic system vibration, improves life, ensures aircraft flight safety.
Description
Technical Field
The application belongs to the technical field of hydraulic pipeline installation, and particularly relates to a high-pressure hydraulic pipeline installation structure and method.
Background
The hydraulic system is one of the important systems of modern aircraft, and provides driving force for each movable control surface to realize high-maneuvering flight. In order to improve the working efficiency of the hydraulic system, the modern aircraft adopts a high-pressure hydraulic system, and the system pressure is more than 21 MPa. As a result, the hydraulic system can generate high vibration during operation, which can lead to breakage of the mounting structure or piping if it is improperly installed, thereby affecting flight safety.
In the past, in aircraft design, a high-pressure hydraulic pipeline is usually directly installed or installed on an aircraft body structure through an installation support, so that vibration generated by a hydraulic system is directly transmitted to the installation structures, the body structure, the hydraulic pipeline installation structure and the hydraulic pipeline fracture phenomenon often occur in the use process, and the main reason is that the vibration reduction installation, rigidity matching and other factors are not considered in the installation of the high-pressure pipeline, so that the structures are subjected to dynamic fatigue damage under vibration load.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The application aims to provide a high-pressure hydraulic pipeline installation structure and a high-pressure hydraulic pipeline installation method, so as to solve at least one problem in the prior art.
The technical scheme of the application is as follows:
a first aspect of the present application provides a high-pressure hydraulic line mounting structure, including:
the weak frame is detachably mounted on the aircraft skin;
the aircraft body strong frame is detachably mounted on an aircraft skin, and is provided with a through hole for a high-pressure hydraulic pipeline to pass through;
the pipeline mounting brackets comprise a plurality of pipeline mounting brackets, the pipeline mounting brackets are detachably mounted on the machine body weak frame and the machine body strong frame respectively, metal rubber is arranged at the joint of the pipeline mounting brackets and the machine body strong frame, and pipeline hoops are mounted on the pipeline mounting brackets;
the high-pressure hydraulic line, the coupling is installed respectively at high-pressure hydraulic line's both ends, high-pressure hydraulic line is through installing in proper order corresponding the position the pipeline installing support on the pipeline clamp, realize with the weak frame of organism and the strong frame of organism is connected.
Optionally, the material of the weak frame of organism is the panel beating metal sheet, and thickness is below 2 mm.
Optionally, the weak frame is connected with the aircraft skin through rivets or screws.
Optionally, the body frame is a metal stiffened plate, and the thickness of the body frame is more than 5 mm.
Optionally, the body frame is connected to the aircraft skin by rivets or screws.
Optionally, the pipeline mounting bracket is connected with the body weak frame and the body strong frame through rivets or screws.
Optionally, the thickness of the high-pressure hydraulic line is 1.5mm or less.
A second aspect of the present application provides a high-pressure hydraulic line installation method, based on the high-pressure hydraulic line installation structure as described above, including:
the method comprises the following steps: selecting parameters of the metal rubber through the natural frequency of a finite element analysis system to obtain the thickness parameter of the metal rubber;
step two: realize the assembly of high-pressure hydraulic line, specifically include:
connecting the high-pressure hydraulic pipeline with other high-pressure pipelines through pipe joints at two ends;
the coaxiality of the pipeline mounting bracket and the high-pressure hydraulic pipeline is adjusted by adjusting the position of the pipeline mounting bracket;
assembling a high-pressure hydraulic pipeline with a pipeline hoop and a pipeline mounting bracket;
then respectively installing the pipeline installation supports at corresponding positions on the machine body weak frame and installing the pipeline installation supports on the machine body strong frame in a matching manner with the metal rubber;
step three: and performing modal test on the high-pressure hydraulic pipeline, judging whether the natural frequency domain of the high-pressure hydraulic pipeline avoids the natural frequency of the hydraulic system, and if so, performing vibration and stress test on the high-pressure hydraulic pipeline mounting structure in a ground driving state of the engine.
Alternatively,
assembling a high-pressure hydraulic pipeline with a pipeline hoop and a pipeline mounting bracket through screws;
the pipeline mounting bracket is mounted on the machine body weak frame through screws or rivets, and is mounted on the machine body strong frame in a matched mode through metal rubber.
Optionally, when the screw connection is adopted, in order to ensure that the stress of each screw is uniform, the screw is fastened by using a torque wrench.
The invention has at least the following beneficial technical effects:
the high-pressure hydraulic pipeline mounting structure can avoid mounting stress generated when a hydraulic pipeline is mounted to a great extent, reduces the influence of vibration of a hydraulic system on an engine body structure, the hydraulic pipeline mounting structure and the hydraulic pipeline, prolongs the service life, and ensures the flight safety of an airplane.
Drawings
FIG. 1 is a schematic view of a high pressure hydraulic line installation configuration according to an embodiment of the present application;
fig. 2 is a schematic view of a metal rubber of a high-pressure hydraulic line installation structure according to an embodiment of the present application.
Wherein:
1-a body weak frame; 2-strengthening the body; 3-metal rubber; 4, a pipeline hoop; 5-pipe joint; 6-a pipeline mounting bracket; 7-high pressure hydraulic line.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1-2.
A first aspect of the present application provides a high-pressure hydraulic line mounting structure, including: the machine body comprises a machine body weak frame 1, a machine body strong frame 2, a pipeline mounting bracket 6 and a high-pressure hydraulic pipeline 7.
Specifically, as shown in fig. 1, a weak frame 1 of the aircraft body is mounted on the skin of the aircraft in a detachable mounting manner, a strong frame 2 of the aircraft body is mounted on the skin of the aircraft in a detachable mounting manner, and the strong frame 2 of the aircraft body is provided with a through hole for a high-pressure hydraulic pipeline 7 to pass through; the pipeline mounting brackets 6 comprise a plurality of pipeline mounting brackets 6, the pipeline mounting brackets 6 are respectively detachably mounted on the machine body weak frame 1 and the machine body strong frame 2, metal rubber 3 is arranged at the joint of the pipeline mounting brackets 6 and the machine body strong frame 2, and pipeline hoops 4 are mounted on the pipeline mounting brackets 6; the pipe joints 5 are respectively installed at two ends of the high-pressure hydraulic pipeline 7, and the high-pressure hydraulic pipeline 7 is sequentially installed on the pipeline hoop 4 of the pipeline installation support 6 at the corresponding position to be connected with the machine body weak frame 1 and the machine body strong frame 2.
The utility model provides a high-pressure hydraulic line mounting structure, the weak frame 1 of organism adopts the panel beating metal sheet, and its thickness is generally below 2mm, has sufficient rigidity and intensity to be connected with the aircraft skin through rivet or screw, guarantee that high-pressure hydraulic line 7's vibration load transmits the organism structurally. The strong frame 2 of the aircraft body is a metal stiffened plate, the thickness of the strong frame is generally more than 5mm, the strong frame has enough rigidity and strength, and the strong frame is connected with the aircraft skin through rivets or screws to ensure that the vibration load of the high-pressure hydraulic pipeline 7 is transferred to the structure of the aircraft body.
Furthermore, the metal rubber 3 is a high-damping characteristic structure composed of metal wires, has a vibration damping function and compressibility, can bear the installation deformation of the body frame 2 in the installation process of the high-pressure hydraulic pipeline 7, reduces the installation stress, and reduces the vibration load transmitted from the high-pressure hydraulic pipeline 7 to the high-pressure hydraulic pipeline installation structure and the body structure by utilizing the vibration damping performance.
In an embodiment of this application, pipeline clamp 4 is the metal block of taking the round hole, including two parts, can be connected pipeline clamp 4 with pipeline installation support 6 and high-pressure hydraulic line 7 through the screw, for guaranteeing that high-pressure hydraulic line 7 is firm to be connected with pipeline installation support 6, need adopt torque wrench fastening screw.
In one embodiment of the present application, the pipe joint 5 is a threaded metal joint for connecting the high-pressure hydraulic pipeline 7 with other high-pressure pipelines, and before installing the metal rubber 3, the pipeline clamp 4 and the pipeline installing support 6, the high-pressure pipelines or accessories at two ends of the pipe joint 5 are installed in place, and then the positions of the metal rubber 3, the pipeline clamp 4 and the pipeline installing support 6 are adjusted, so that the installation stress can be further reduced.
In one embodiment of the present application, the pipeline mounting bracket 6 is a metal angle bar with an L-shaped cross section, the thickness is generally 2mm, and the pipeline mounting bracket 6 has sufficient rigidity and strength, and is connected with the machine body weak frame 1 and the machine body strong frame 2 through rivets or screws.
In this embodiment, the high-pressure hydraulic pipeline 7 is a metal pipe, the thickness of which is generally below 1.5mm, and the interior of which is filled with high-pressure hydraulic oil to realize the driving function of each movable control surface, and when the high-pressure hydraulic pipeline is connected with the pipeline hoop 4 and the pipeline mounting bracket 6, the coaxiality should be checked to reduce the accessory mounting stress caused by mounting, and ensure the use safety of the high-pressure hydraulic pipeline 7 and the pipeline mounting bracket 6. The end of the high-pressure hydraulic line 7 may be directly mounted in a mounting hole provided in the line mounting bracket 6 through the pipe joint 5.
Based on the above high-pressure hydraulic pipeline installation structure, a second aspect of the present application further provides a high-pressure hydraulic pipeline installation method, including the following steps:
s101, selecting parameters of the metal rubber 3 through the natural frequency of a finite element analysis system to obtain the thickness parameter of the metal rubber 3;
step S102, implementing the assembly of the high-pressure hydraulic line 7, specifically including:
connecting a high-pressure hydraulic pipeline 7 with other high-pressure pipelines through pipe joints 5 at two ends;
the coaxiality of the pipeline mounting bracket 6 and the high-pressure hydraulic pipeline 7 is adjusted by adjusting the position of the pipeline mounting bracket 6;
assembling a high-pressure hydraulic pipeline 7 with a pipeline hoop 4 and a pipeline mounting bracket 6;
then respectively installing pipeline installation supports 6 at corresponding positions on the machine body weak frame 1 and installing the pipeline installation supports on the machine body strong frame 2 in cooperation with the metal rubber 3;
step S103, performing modal testing on the high-pressure hydraulic pipeline 7, judging whether the natural frequency domain of the high-pressure hydraulic pipeline 7 avoids the natural frequency of the hydraulic system, and if so, performing vibration and stress testing on the high-pressure hydraulic pipeline mounting structure in the ground driving state of the engine to ensure the aerial use safety of the high-pressure hydraulic pipeline mounting structure.
Wherein, the high-pressure hydraulic pipeline 7 is assembled with the pipeline hoop 4 and the pipeline mounting bracket 6 through screws; the pipeline mounting bracket 6 is mounted on the machine body weak frame 1 through screws or rivets, and is mounted on the machine body strong frame 2 in a matching mode through metal rubber 3. When the screws are used for connection, in order to ensure that all the screws are stressed uniformly, the screws are fastened by using a torque wrench.
The high-pressure hydraulic pipeline mounting structure and the method can avoid mounting stress generated when the hydraulic pipeline is mounted to a great extent, reduce the influence of vibration of a hydraulic system on an engine body structure, the hydraulic pipeline mounting structure and the hydraulic pipeline, prolong the service life and ensure the flight safety of an airplane.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. A high-pressure hydraulic line mounting structure, comprising:
the aircraft body weak frame (1), wherein the aircraft body weak frame (1) is detachably mounted on an aircraft skin;
the aircraft body strong frame (2) is detachably mounted on an aircraft skin, and a through hole for a high-pressure hydraulic pipeline (7) to pass through is formed in the aircraft body strong frame (2);
the pipeline mounting supports (6) comprise a plurality of pipeline mounting supports (6), the pipeline mounting supports (6) are respectively detachably mounted on the machine body weak frame (1) and the machine body strong frame (2), metal rubber (3) is arranged at the joint of the pipeline mounting supports (6) and the machine body strong frame (2), and pipeline hoops (4) are mounted on the pipeline mounting supports (6);
high-pressure hydraulic line (7), coupling (5) are installed respectively at the both ends of high-pressure hydraulic line (7), high-pressure hydraulic line (7) are through installing in proper order corresponding the position pipeline installing support (6) on pipeline clamp (4), realize with the organism weak frame (1) and the organism strong frame (2) are connected.
2. The high-pressure hydraulic pipeline installation structure according to claim 1, wherein the weak frame (1) is made of a sheet metal plate and has a thickness of less than 2 mm.
3. The high-pressure hydraulic line installation structure according to claim 2, wherein the weak frame (1) is connected to the aircraft skin by rivets or screws.
4. The high-pressure hydraulic pipeline installation structure according to claim 1, wherein the machine body strong frame (2) is a metal stiffened plate with a thickness of more than 5 mm.
5. The high-pressure hydraulic line installation structure according to claim 4, wherein the body frame (2) is connected to the aircraft skin by rivets or screws.
6. The high-pressure hydraulic line mounting structure according to claim 1, wherein the line mounting bracket (6) is connected to the body weak frame (1) and the body strong frame (2) by rivets or screws.
7. The high-pressure hydraulic line mounting structure according to claim 1, wherein the thickness of the high-pressure hydraulic line (7) is 1.5mm or less.
8. A high-pressure hydraulic line installation method based on the high-pressure hydraulic line installation structure according to any one of claims 1 to 7, characterized by comprising:
the method comprises the following steps: selecting parameters of the metal rubber (3) through the natural frequency of a finite element analysis system to obtain the thickness parameter of the metal rubber (3);
step two: realize the assembly of high-pressure hydraulic line (7), specifically include:
connecting a high-pressure hydraulic pipeline (7) with other high-pressure pipelines through pipe joints (5) at two ends;
the coaxiality of the pipeline mounting bracket (6) and the high-pressure hydraulic pipeline (7) is adjusted by adjusting the position of the pipeline mounting bracket (6);
assembling a high-pressure hydraulic pipeline (7) with a pipeline hoop (4) and a pipeline mounting bracket (6);
then respectively installing pipeline installation supports (6) at corresponding positions on the machine body weak frame (1) and installing the pipeline installation supports on the machine body strong frame (2) in cooperation with the metal rubber (3);
step three: and performing modal testing on the high-pressure hydraulic pipeline (7), judging whether the natural frequency domain of the high-pressure hydraulic pipeline (7) avoids the natural frequency of the hydraulic system, and if so, performing vibration and stress testing on the high-pressure hydraulic pipeline mounting structure in the ground driving state of the engine.
9. The high-pressure hydraulic line installation method according to claim 8,
assembling a high-pressure hydraulic pipeline (7) with a pipeline hoop (4) and a pipeline mounting bracket (6) through screws;
the pipeline mounting bracket (6) is mounted on the machine body weak frame (1) through screws or rivets, and is mounted on the machine body strong frame (2) in a matching mode through metal rubber (3).
10. The method for installing a high-pressure hydraulic pipeline according to claim 9, wherein when the bolts are used for connection, in order to ensure that the bolts are uniformly stressed, the bolts are fastened by using a torque wrench.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011240835.6A CN112503258B (en) | 2020-11-09 | 2020-11-09 | High-pressure hydraulic pipeline installation structure and method |
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| CN202011240835.6A CN112503258B (en) | 2020-11-09 | 2020-11-09 | High-pressure hydraulic pipeline installation structure and method |
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| CN112503258A true CN112503258A (en) | 2021-03-16 |
| CN112503258B CN112503258B (en) | 2022-08-26 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113184215A (en) * | 2021-03-31 | 2021-07-30 | 成都飞机工业（集团）有限责任公司 | Method for installing aircraft skin exhaust guide pipe |
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| CN207527138U (en) * | 2017-10-31 | 2018-06-22 | 奇瑞汽车股份有限公司 | A kind of clutch pipeline assembly with vibration insulation structure |
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| CN110717220A (en) * | 2019-10-15 | 2020-01-21 | 西北工业大学 | Method for verifying aviation hydraulic pipeline model |
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| CN113184215B (en) * | 2021-03-31 | 2022-06-14 | 成都飞机工业（集团）有限责任公司 | Method for installing aircraft skin exhaust guide pipe |
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