CN111496353A - Method for repairing defects of outer cylinder inner cavity of buffering strut of undercarriage - Google Patents
Method for repairing defects of outer cylinder inner cavity of buffering strut of undercarriage Download PDFInfo
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- CN111496353A CN111496353A CN202010218098.3A CN202010218098A CN111496353A CN 111496353 A CN111496353 A CN 111496353A CN 202010218098 A CN202010218098 A CN 202010218098A CN 111496353 A CN111496353 A CN 111496353A
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- outer cylinder
- inner cavity
- landing gear
- welding
- defects
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K9/00—Arc welding or cutting
- B23K9/16—Arc welding or cutting making use of shielding gas
- B23K9/167—Arc welding or cutting making use of shielding gas and of a non-consumable electrode
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K9/00—Arc welding or cutting
- B23K9/0026—Arc welding or cutting specially adapted for particular articles or work
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- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
- C21D9/50—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for welded joints
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- Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- Plasma & Fusion (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Butt Welding And Welding Of Specific Article (AREA)
Abstract
The invention discloses a method for repairing the defects of the inner cavity of the outer cylinder of a buffer strut of an aircraft landing gear, which comprises the following steps: the method comprises the following steps: observing damage characteristics of defects of an inner cavity of an outer cylinder of a buffering strut of an aircraft landing gear; step two: determining a welding method according to the defect damage characteristics in the step one and the welding characteristics of the outer cylinder base material of the buffering strut of the undercarriage; step three: carrying out repair pre-operation on the prefabricated test piece; step four: welding the defects of the inner cavity of the outer cylinder of the landing gear buffer strut; step five: and after welding, performing heat preservation treatment on the welding seam and the heat affected zone.
Description
Technical Field
The invention relates to the technical field of maintenance of aviation equipment, in particular to a method for repairing defects of an outer cylinder inner cavity of a buffering support column of an aircraft landing gear.
Background
The outer barrel of the landing gear buffer strut is one of the key parts of the landing gear of the airplane, plays roles of supporting, absorbing impact energy and operating the airplane in the processes of taking off, sliding and landing of the airplane, and has extremely strict technical content and configuration requirements, so the performance of the device is directly related to the normal work of the whole airplane. In the process of taking off and landing of the airplane, the buffer strut is greatly impacted, so that the inner cavity of the buffer strut is easily damaged in the long-term service process of the airplane. However, the defects of the inner cavity of the outer barrel of the landing gear buffer strut are positioned on the inner surface, and an operator cannot visually see the positions and shapes of the defects, so that the defects of the inner cavity of the outer barrel of the landing gear buffer strut of the airplane cannot be repaired by adopting a traditional method, and the repairing is difficult to repair.
The technical specification of the aircraft landing gear repair is that when the defect size of the inner cavity of the outer cylinder of the landing gear buffer strut exceeds a set standard, the defect can be eliminated by polishing, and the inner diameter size of the polished cylinder is increased, so that a shaft sleeve and a piston ring matched with the polished cylinder need to be additionally processed and manufactured; the repair cost of the method is greatly increased, the repair risk is high, and the outer cylinder of the landing gear buffer strut is easily scrapped. At present, aiming at the inner cavity defect of the outer cylinder of the landing gear buffer strut, an effective method which can not only meet the requirement of integrity repair of the inner cavity defect of the outer cylinder of the landing gear buffer strut but also reduce the repair risk caused by the increase of the inner diameter size of the cylinder body due to polishing does not exist in the whole technical field of aviation manufacturing and aviation repair.
Disclosure of Invention
In view of the above, the invention provides a method for repairing the defects of the inner cavity of the outer cylinder of the buffering support column of the aircraft landing gear, which can not only repair the defects of the inner cavity of the outer cylinder of the buffering support column of the landing gear efficiently, but also reduce the repairing risk caused by the increase of the inner diameter of the cylinder due to polishing.
The technical scheme of the invention is as follows: a method for repairing the defects of the inner cavity of the outer cylinder of the buffer strut of the landing gear of an airplane comprises the following steps:
the method comprises the following steps: observing damage characteristics of defects of an inner cavity of an outer cylinder of a buffering strut of an aircraft landing gear;
step two: determining a welding method according to the defect damage characteristics in the step one and the welding characteristics of the outer cylinder base material of the buffering strut of the undercarriage;
step three: carrying out repair pre-operation on the prefabricated test piece;
step four: welding the defects of the inner cavity of the outer cylinder of the landing gear buffer strut;
step five: and after welding, performing heat preservation treatment on the welding seam and the heat affected zone.
Preferably, in the first step, an electronic hole detector is used for observing the defects of the inner cavity of the outer cylinder of the landing gear buffer strut, wherein the electronic hole detector is connected with an external display screen.
Preferably, the welding gun is adopted in the welding in the fourth step, and the welding gun and the electronic hole detector are respectively installed on the same extension bar.
Preferably, the damage characteristic in the first step comprises: location of defect, lesion shape and lesion size.
Preferably, the test piece in the third step has the same structure, the same material, the same thickness, the same strength and the same defects as the inner cavity of the outer cylinder of the buffer strut of the landing gear.
Preferably, the welding wire used for welding in the fourth step is fed into the inner cavity defect from the air release valve mounting hole in the outer cylinder of the landing gear buffer strut.
Preferably, the heat preservation treatment in the fifth step adopts hot sand treatment.
Preferably, the temperature of the hot sand treatment is 240-260 ℃.
Preferably, the time of the hot sand treatment is 1-2 h.
Preferably, the hot sand ring is stored in a set vessel, and a resistance heating device is laid in the hot sand for auxiliary heat preservation.
Has the advantages that:
(1) the repairing method disclosed by the invention can be used for efficiently repairing the defects of the inner cavity of the outer cylinder of the landing gear buffer strut and reducing the repairing risk caused by the increase of the inner diameter of the cylinder due to polishing.
(2) The repairing method of the invention can clearly observe the damage characteristics of the defects of the outer cylinder inner cavity of the landing gear buffer strut by using the electronic hole detector, thereby facilitating the development of the subsequent welding repairing work.
(3) According to the repairing method, the welding gun and the electronic hole detector are arranged on the same extension bar, the problem that the defect of the outer cylinder inner cavity of the landing gear buffer support is unknown and poor in accessibility is solved, and the electronic hole detector can be used for effectively ensuring that welding repair of the welding gun can be carried out under a visual condition.
(4) The repair method skillfully utilizes the mounting hole of the air bleed valve on the outer cylinder of the landing gear buffer strut as a welding wire conveying channel, and solves the technical problem of difficult wire feeding in the welding repair process.
(5) The repair method of the invention utilizes the good heat transfer and heat preservation effects of the quartz sand, and after welding repair, the quartz sand with the set temperature is covered on the welding line and the heat affected zone, thereby effectively ensuring that no cold crack is generated.
(6) According to the repairing method, the resistance heating device is paved in the quartz sand, and the resistance heating device has the functions of temperature monitoring and adjustment, so that the problem that the temperature of hot sand is difficult to maintain is solved.
Drawings
FIG. 1 is a schematic diagram of the position of a defect in the inner cavity of an outer cylinder of a buffer strut of an aircraft landing gear.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The embodiment provides a method for repairing the defects of the inner cavity of the outer cylinder of the buffering support column of the aircraft landing gear, which can efficiently repair the defects of the inner cavity of the outer cylinder of the buffering support column of the aircraft landing gear and reduce the repairing risk caused by the increase of the inner diameter of the cylinder due to polishing.
The repairing method comprises the following steps:
the method comprises the following steps: observing and roughly measuring the defects of the inner cavity of the outer cylinder of the landing gear buffer strut by adopting an electronic hole detector provided with an extension rod, and determining damage characteristics such as the positions, damage shapes, damage sizes and the like of the defects, wherein the electronic hole detector is connected with an external display screen, and the display screen can display the damage characteristics of the defects observed by the electronic hole detector in real time;
step two: according to the damage characteristics of the defects determined in the step one and the welding characteristics of an outer cylinder base material (the mark number is 30CrMnSiNi 2A; the tensile strength is 1570-1810 MPa), a precise pulse TIG method (TIG is argon tungsten-arc welding, the defects can be well repaired, and compared with other welding methods, the method has the following three advantages that 1, high-quality welding can be realized, excellent welding seams can be obtained, 2, the adaptability to the outer cylinder base material is good, the width of a heat affected zone can be avoided being too large, brittle tissues can be reduced, and 3, the method is suitable for various space welding seams and welding, such as fillet welding seams, all-position welding seams, space curved surface welding seams and the like, and horizontal welding, overhead welding, vertical welding and the like);
step three: in order to ensure the welding repair quality, test pieces which have the same structure, the same material, the same thickness, the same strength and similar defects as the outer cylinder of the buffer strut are manufactured in advance for pre-operation before repair, so that the skilled repair operation method can be conveniently strengthened and exercised, on one hand, the position accuracy during welding repair can be ensured, and on the other hand, the technological parameters of defect welding repair can be determined in advance;
step four: welding the defects of the inner cavity of the outer barrel of the landing gear buffer support through a welding gun with an extension rod (ensuring that the welding gun can move in the axial direction and the radial direction of the outer barrel of the landing gear buffer support); the electronic hole detector can be additionally arranged on the same extension bar for clamping the welding gun, so that the welding repair of an operator can be guaranteed, and the defect to be repaired can be observed in real time; welding wires used for welding repair are sent to the defect position of the inner cavity from an air release valve mounting hole in the outer cylinder of the landing gear buffer strut for filling repair;
step five: after the outer barrel of the landing gear buffer strut is welded, immediately covering a welding repair area with hot sand (with good heat transfer and heat preservation effects of quartz sand) at 240-260 ℃ for heat preservation treatment for 1-2 h so as to achieve the purpose of local heat preservation treatment and ensure that no cold crack is generated in a welding line and a heat affected zone; the quartz sand ring is stored in a set vessel (such as a wooden box body) in order to control the temperature of the quartz sand to be maintained at 240-260 ℃, and a resistance heating device is laid in the quartz sand and used for auxiliary heat preservation, wherein a temperature sensor and a regulator are arranged in the resistance heating device.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A method for repairing the defects of the inner cavity of the outer cylinder of the buffer strut of the landing gear of the airplane is characterized by comprising the following steps:
the method comprises the following steps: observing damage characteristics of defects of an inner cavity of an outer cylinder of a buffering strut of an aircraft landing gear;
step two: determining a welding method according to the defect damage characteristics in the step one and the welding characteristics of the outer cylinder base material of the buffering strut of the undercarriage;
step three: carrying out repair pre-operation on the prefabricated test piece;
step four: welding the defects of the inner cavity of the outer cylinder of the landing gear buffer strut;
step five: and after welding, performing heat preservation treatment on the welding seam and the heat affected zone.
2. The method for repairing the defects of the inner cavity of the outer cylinder of the buffer strut of the aircraft landing gear according to claim 1, wherein in the first step, the defects of the inner cavity of the outer cylinder of the buffer strut of the aircraft landing gear are observed by using an electronic hole detector, wherein the electronic hole detector is connected with an external display screen.
3. The method for repairing the defects of the inner cavity of the outer cylinder of the buffer strut of the aircraft landing gear according to claim 2, wherein the welding in the fourth step adopts a welding gun, and the welding gun and the electronic hole detector are respectively arranged on the same extension rod.
4. A method of repairing a defect in the internal cavity of an outer barrel of a strut of an aircraft landing gear according to claim 1, wherein the damage characteristic in the first step comprises: location of defect, lesion shape and lesion size.
5. The method for repairing the defects of the inner cavity of the outer cylinder of the buffer strut of the aircraft landing gear according to claim 1, wherein the test piece in the third step has the same structure, the same material, the same thickness, the same strength and the same defects as the inner cavity of the outer cylinder of the buffer strut of the aircraft landing gear.
6. A method for repairing a defect in the inner cavity of an outer cylinder of a landing gear buffer strut of an aircraft according to claim 1, wherein the welding wire used for welding in the fourth step is fed into the defect in the inner cavity from a mounting hole of a bleed valve on the outer cylinder of the landing gear buffer strut.
7. The method for repairing the defects of the inner cavity of the outer cylinder of the buffer strut of the aircraft landing gear according to claim 1, wherein the heat preservation treatment in the fifth step is hot sand treatment.
8. A method for repairing an aircraft landing gear bumper strut outer barrel inner cavity defect according to claim 7, wherein the temperature of the hot sand treatment is 240-260 ℃.
9. A method for repairing defects in an inner cavity of an outer cylinder of a buffer strut of an aircraft landing gear according to claim 7, wherein the hot sand treatment time is 1-2 hours.
10. The method for repairing the defects of the inner cavity of the outer cylinder of the buffer strut of the aircraft landing gear according to claim 7, wherein the hot sand ring is stored in a set vessel, and a resistance heating device is laid in the hot sand for assisting in heat preservation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010218098.3A CN111496353A (en) | 2020-03-25 | 2020-03-25 | Method for repairing defects of outer cylinder inner cavity of buffering strut of undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010218098.3A CN111496353A (en) | 2020-03-25 | 2020-03-25 | Method for repairing defects of outer cylinder inner cavity of buffering strut of undercarriage |
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| Publication Number | Publication Date |
|---|---|
| CN111496353A true CN111496353A (en) | 2020-08-07 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010218098.3A Pending CN111496353A (en) | 2020-03-25 | 2020-03-25 | Method for repairing defects of outer cylinder inner cavity of buffering strut of undercarriage |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0663787A (en) * | 1992-08-14 | 1994-03-08 | Olympus Optical Co Ltd | Endoscope for welding |
| CN103111725A (en) * | 2012-12-07 | 2013-05-22 | 无锡透平叶片有限公司 | Repair welding device of weld joints in cavity |
| CN202963803U (en) * | 2012-11-02 | 2013-06-05 | 浙江久立特材科技股份有限公司 | Off-line inner welding tool for small-diameter stainless steel tube |
| CN204470816U (en) * | 2014-12-31 | 2015-07-15 | 浙江久立特材科技股份有限公司 | Interior protective device reprocessed by stainless steel tube |
| CN107999933A (en) * | 2017-12-26 | 2018-05-08 | 哈尔滨锅炉厂有限责任公司 | Fountain type stringing inner hole welding of rapid cooling structure and welding method |
-
2020
- 2020-03-25 CN CN202010218098.3A patent/CN111496353A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0663787A (en) * | 1992-08-14 | 1994-03-08 | Olympus Optical Co Ltd | Endoscope for welding |
| CN202963803U (en) * | 2012-11-02 | 2013-06-05 | 浙江久立特材科技股份有限公司 | Off-line inner welding tool for small-diameter stainless steel tube |
| CN103111725A (en) * | 2012-12-07 | 2013-05-22 | 无锡透平叶片有限公司 | Repair welding device of weld joints in cavity |
| CN204470816U (en) * | 2014-12-31 | 2015-07-15 | 浙江久立特材科技股份有限公司 | Interior protective device reprocessed by stainless steel tube |
| CN107999933A (en) * | 2017-12-26 | 2018-05-08 | 哈尔滨锅炉厂有限责任公司 | Fountain type stringing inner hole welding of rapid cooling structure and welding method |
Non-Patent Citations (4)
| Title |
|---|
| 堵耀庭: "《异种金属的焊接》", 31 May 1986, 机械工业出版社 * |
| 杨兆军: "某型飞机前起支架焊接修复研究 ", 《中国新技术新产品》 * |
| 江治俊: "TB200型飞机前起落架安装支架焊接修复 ", 《中国民航飞行学院学报》 * |
| 郭必新等: "飞机起落架的TIG焊工艺 ", 《航空制造技术》 * |
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Application publication date: 20200807 |
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