CN110481812B - Trial repairing method for buffering support of undercarriage of certain type machine - Google Patents
Trial repairing method for buffering support of undercarriage of certain type machine Download PDFInfo
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- CN110481812B CN110481812B CN201910726496.3A CN201910726496A CN110481812B CN 110481812 B CN110481812 B CN 110481812B CN 201910726496 A CN201910726496 A CN 201910726496A CN 110481812 B CN110481812 B CN 110481812B
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- landing gear
- strut
- undercarriage
- buffer
- parts
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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
- B64F5/40—Maintaining or repairing aircraft
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- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
- Fluid-Damping Devices (AREA)
Abstract
The invention discloses a trial repair method for a certain type of undercarriage buffer strut, which comprises the following steps of 1) decomposing undercarriage buffer strut components one by one, numbering the components one by one, and drawing a structural drawing of the undercarriage buffer strut so as to determine the internal structure of the undercarriage buffer strut; ) Determining the whole piece performance test parameters of the undercarriage buffer strut, and determining the test conditions and the test method of the whole piece performance test parameters, wherein the test conditions and the test method comprise two main functional units, namely a nose undercarriage buffer strut and a main undercarriage buffer strut; 3) The internal structure of the landing gear strut obtained and the test results confirm that the landing gear strut has to be overhauled for replacement parts, and replacement parts for these parts, the delicate and consumable parts in the internal structure of the landing gear strut being the parts that have to be replaced.
Description
Technical Field
The invention relates to the field of airplane research and repair, in particular to a trial repair method for a buffering support column of a certain type undercarriage.
Background
The landing gear buffer strut is used for supporting and absorbing energy during takeoff and landing of an airplane, is a foreign design-shaped product, is firstly repaired at home, and has no relevant detailed technical data and requirements when being repaired, so that the work of confirming the technical state, formulating the technical requirements, perfecting the process method and the like needs to be carried out in the whole repairing process.
Disclosure of Invention
The invention aims to provide a trial repair method for a buffering support of an undercarriage, which can realize trial repair of the buffering support of the undercarriage.
Specifically, the method is realized through the following technical scheme:
1) Decomposing the landing gear buffer support component assemblies one by one, numbering the landing gear buffer support component assemblies one by one, and drawing a landing gear buffer support structure drawing so as to determine the internal structure of the landing gear buffer support;
when the landing gear buffer support is disassembled, decomposition is carried out according to functions and internal and external relations, namely, the decomposition process is gradually decomposed according to a hierarchical structure, the determination of the hierarchical structure is not limited as long as the order can be achieved, the number is decomposed while the structural drawing is drawn, namely, the number can be carried out according to the hierarchical structure, and the structural drawing is drawn according to the hierarchical structure;
drawing a part drawing for a vulnerable and consumable part;
the landing gear buffer strut internal structure is determined by progressively collapsing the landing gear buffer strut.
2) The method comprises the steps of determining the whole performance test parameters of the undercarriage buffer support column through the principle analysis of the undercarriage buffer support column, the collection and statistics of the original performance parameters and the practice verification method of the performance parameter boundary range, and determining the test conditions and the test method of the whole performance test parameters.
3) And determining parts of the landing gear buffer strut which must be overhauled and replaced and replacing parts of the parts according to the obtained internal structure of the landing gear buffer strut and the test result.
The delicate and consumable parts in the internal structure of the landing gear cushion strut are parts that must be replaced.
Compared with the prior art, the invention has the following beneficial effects:
the gap of repairing the series of aircraft landing gear buffer struts in China is filled, and the three-dimensional model, the technical requirements of test and maintenance, the model selection design of replaceable parts in China and the like all lay the foundation for subsequent repair. The cost of the invention is about 30% when the invention is applied to the outward delivery repair after production, and the repair cost of a single airplane is reduced by about 80 ten thousand yuan compared with RMB.
Detailed Description
The present invention will be further described with reference to the following examples.
1) Determination of technical solutions
1.1 repair procedure determination
Because the product has no pattern data in China, the contents such as an internal structure, a working principle, a main size, design indexes and the like need to be determined in the repair process, and the process design is carried out from the contents such as decomposition, tool manufacturing, part mapping, reverse design of design size and the like in order to ensure that the repair process is combed effectively.
1.2 determination of filling requirement
The filling of oil and gas in the product is a key link for ensuring the working performance, the product is easy to damage due to incorrect operation, the numerical value of the filling oil and the numerical value of the inflation pressure have reference approximate numerical values, and the influence on the temperature and the actual working performance needs to be repeatedly adjusted to determine a proper index.
1.3 determination of Performance Curve indicators
The performance curve is an important judgment basis for qualified working performance of products, the determination of performance indexes needs to be specifically determined according to requirements in use, needs to be distinguished and determined from the requirements of a system, and finally is determined by combining with the requirements of filling.
1.4 determination of specific technical requirements such as matching requirements, tolerance, surface treatment and the like
In the repairing process, technical indexes such as the matching requirement of key parts, the size tolerance of the parts, the surface treatment requirement of the parts and the like need to be determined, the sizes need to be determined one by using a mapping method, the inverse design of general requirements of working conditions and precision needs to be combined with mapping determination for the matching tolerance, and the surface treatment is combined with the surface state and the use environment to be determined.
1.5 design of replaceable parts
During the trial repair process, more than 30 necessary replacement parts, including the sealing part and the locking part, need to be replaced, and all the parts need to be redesigned to meet the actual use requirement.
2) Establishment of product repair model
The product repair process needs construction according to the decomposed three-dimensional model and the assembly drawing, and the assembly drawing and the three-dimensional model in the product repair process need to be completed on the basis of surveying and mapping.
The trial repair method for the undercarriage buffer strut can realize trial repair of the undercarriage buffer strut.
The trial repair method of the landing gear buffer strut comprises the following steps of:
1) Decompose undercarriage buffering pillar spare part one by one, serial number one by one to draw undercarriage buffering pillar structure drawing and partial part drawing, with this definite undercarriage buffering pillar inner structure.
When disassembling undercarriage buffer support, decompose according to function and inside and outside relation, the decomposition process progressively decomposes according to certain hierarchy promptly (hierarchy is definite not injectd, as long as can accomplish orderly), and the limit is decomposed the limit and is numbered, the limit draws the structure drawing, and the numbering can be gone on according to hierarchy promptly, draws the structure drawing according to hierarchy.
Drawing a part drawing for the easily damaged and consumed part.
The landing gear buffer strut internal structure may be determined by progressively collapsing the landing gear buffer strut.
2) The whole performance test parameters of the undercarriage buffer support are determined by the methods of undercarriage buffer support principle analysis, original performance parameter collection statistics, performance parameter boundary range practice verification and the like, and the test conditions and the test method of the whole performance test parameters are determined. The main functional units comprise a nose landing gear buffer strut and a main landing gear buffer strut.
The performance test parameters of the whole piece of the buffering support of the nose landing gear are shown in the table 1:
TABLE 1 nose landing gear cushion strut Performance test parameters
The performance test parameters of the whole main landing gear buffer strut are shown in the table 2:
TABLE 2 Performance test parameters for main landing gear buffer strut
3) And determining parts of the landing gear buffer strut which must be repaired and replaced according to the obtained internal structure of the landing gear buffer strut and the test result, and replacing the parts.
The delicate and consumable parts in the internal structure of the landing gear cushion strut are parts that must be replaced.
In this embodiment, the nose gear cushion strut replacement parts list is shown in table 3, and the main gear cushion strut replacement parts list is shown in table 4.
TABLE 3 nose landing gear cushion strut replacement parts List
| Serial number | Name (R) | Number of single pieces | Replacement part |
| 1 | Sealing ring | 2 | 013-017-25-1-013-0CT1 00980-80 |
| 2 | Copper gasket | 1 | 03Д2.4111-0/01CHT-HY302 |
| 3 | Sealing ring | 1 | 013-016-19-1-013-0CT1 00980-80 |
| 4 | Multi-claw stop washer | 1 | 03Д2.4111-0/01CHT-HY301 |
| 5 | Sealing ring | 2 | 016-020-25-1-013-ОСТ1 00980-80 |
| 6 | Stop screw | 2 | 330.4201-0-024ZBT |
| 7 | Sealing ring | 2 | 072-080-46-2-013-A-ОСТ1 00980-80 |
| 8 | Sealing ring | 2 | 065-073-46-1-013-A-ОСТ1 00980-80 |
| 9 | Special-shaped guard circle | 2 | 03Д2.4211-0/01CHT-HY101 |
| 10 | Duplex stop washer | 1 | 03Д2.4211-0/01CHT-HY102 |
| 11 | Protective ring | 4 | 03Д2.4211-0/01CHT-HY103 |
| 12 | Sealing ring | 2 | 044-052-46-1-013-A-0CT1 00980-80 |
| 13 | Sealing ring | 1 | 007-011-25-1-013-0CT1 00980-80 |
| 14 | Felt ring | 1 | 03Д2.4211-0/01CHT-HY104 |
TABLE 4 Main landing gear Bumper strut Change List
Claims (3)
1. A trial repairing method for a buffering support column of an undercarriage of a certain type is characterized by comprising the following steps:
1) Decomposing the landing gear buffer support component assemblies one by one, numbering the landing gear buffer support component assemblies one by one, and drawing a landing gear buffer support structure drawing so as to determine the internal structure of the landing gear buffer support;
2) Determining whole piece performance test parameters of the undercarriage buffer support, and determining test conditions and test methods of the whole piece performance test parameters, wherein the undercarriage buffer support comprises two main functional units, namely a nose undercarriage buffer support and a main undercarriage buffer support;
3) Determining parts which need to be overhauled and replaced for the landing gear buffer strut according to the obtained internal structure of the landing gear buffer strut and the test result, and replacing the parts, wherein the easily damaged and consumable parts in the internal structure of the landing gear buffer strut are the parts which need to be replaced;
1) When the landing gear buffers the strut, decomposing according to the function and the internal and external relation, namely, decomposing gradually according to the hierarchical structure in the decomposition process, determining the hierarchical structure is not limited as long as the hierarchical structure can be ordered, and simultaneously decomposing, numbering and drawing the structure drawing, namely, numbering can be carried out according to the hierarchical structure, and drawing the structure drawing according to the hierarchical structure; drawing a part drawing for a vulnerable and consumable part;
2) The method comprises the steps of determining the whole performance test parameters of the undercarriage buffer support through the principle analysis of the undercarriage buffer support, the collection and statistics of original performance parameters and the practice verification method of the boundary range of the performance parameters, and determining the test conditions and the test method of the whole performance test parameters.
2. A trial repair method for a landing gear strut of a certain type according to claim 1, wherein:
2) In the middle, testing parameters of the performance of a buffering support column of the nose landing gear;
when the piston rod is completely extended out and the buffer strut is in a vertical state, about 1800mL of No. 15 aviation hydraulic oil is injected into the upper cavity through a hole below the filling valve, the final oil amount is adjusted according to a curve value, and the oil amount is kept for 30min in the vertical state; installing the oil injection elbow nozzle, slowly compressing the piston rod to the full stroke, and keeping the buffer strut at the position until the residual oil is completely discharged through the oil injection elbow nozzle, wherein if the oil discharge does not occur, the working procedures are repeated; drawing a performance curve under the condition of normal temperature, wherein the speed of vertically compressing the piston rod is not more than 20mm/min; compressing the piston rod by 335mm, pre-compressing and stretching for 5 times, then formally compressing, keeping the time for not less than 10min during the full stroke, and checking that each sealing position can not leak gas or oil.
3. A trial maintenance method for a landing gear cushion strut of a certain type according to claim 1, characterised in that:
2) In the middle, the performance test parameters of the whole main landing gear buffer strut are measured;
when the piston rod is completely extended out and the buffer strut is in a vertical state, injecting more than 2680mL of No. 15 aviation hydraulic oil into the upper cavity through a hole below the filling valve, and keeping for 30min in the vertical state; the final oil amount of the upper cavity is adjusted according to a curve value, a performance curve is drawn under the normal temperature condition, the speed of vertically compressing the piston rod is not more than 20mm/min, the stroke of the compression piston rod is 290-295 mm, after pre-compression and stretching are carried out for 5 times, formal compression is carried out, the time of the full stroke is not less than 10min, and air leakage and oil leakage at each sealing position are checked.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910726496.3A CN110481812B (en) | 2019-08-07 | 2019-08-07 | Trial repairing method for buffering support of undercarriage of certain type machine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910726496.3A CN110481812B (en) | 2019-08-07 | 2019-08-07 | Trial repairing method for buffering support of undercarriage of certain type machine |
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| CN110481812A CN110481812A (en) | 2019-11-22 |
| CN110481812B true CN110481812B (en) | 2022-12-06 |
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Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105173115A (en) * | 2015-04-23 | 2015-12-23 | 南京王行航空附件维修工程有限公司 | Method for maintaining airplane wheel assembly of airplane landing gear |
| CN106143946B (en) * | 2015-04-24 | 2018-05-01 | 上海海鹰机械厂 | Method is repaiied in rudder system examination |
| ES2910081T3 (en) * | 2017-12-13 | 2022-05-11 | Safran Landing Systems Uk Ltd | Maintenance method of an aircraft landing gear shock absorber strut |
| CN109959491B (en) * | 2018-10-26 | 2020-12-29 | 中国飞行试验研究院 | Method for diagnosing air leakage fault of buffer in landing gear load test flight |
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