CN108100293B - Method for dismounting main undercarriage of airbus A330 aircraft - Google Patents
Method for dismounting main undercarriage of airbus A330 aircraft Download PDFInfo
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- CN108100293B CN108100293B CN201711142748.5A CN201711142748A CN108100293B CN 108100293 B CN108100293 B CN 108100293B CN 201711142748 A CN201711142748 A CN 201711142748A CN 108100293 B CN108100293 B CN 108100293B
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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
- B64F5/40—Maintaining or repairing aircraft
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Abstract
A dismounting method of a main undercarriage of an airbus A330 airplane is characterized in that the lower structure of the main undercarriage (7) is in a horizontal big I shape, and the middle of a middle connecting rod of two shaft-shaped cross beams is vertically provided with an upper structure; the disassembling and assembling method comprises the following steps: s1, placing the main landing gear of the airplane on the main landing gear bracket; s2, connecting the aircraft main landing gear bracket with cobra equipment; s3, operating the cobra device to lift the main landing gear of the airplane; s4, connecting the main landing gear with the airplane large wing structure; s5, disconnecting the main landing gear from the main landing gear bracket; s6, operating the cobra device to lower the main landing gear bracket to the ground; s7, removing the cobra device and the main landing gear bracket and cleaning the site; two cobra devices are arranged in each set, and two vertical and parallel upright posts and a hydraulic lifting cross beam are arranged on a movable base of each cobra device. The A330 main landing gear can be disassembled and assembled without a special lifting platform for the A330 main landing gear, and the labor and the working time are obviously saved, so that the working efficiency is improved.
Description
Technical Field
The invention relates to a method for disassembling and assembling a main undercarriage of an airbus A330 airplane.
Background
The lower structure of the main landing gear of the airbus A330 series airplane is in a horizontal big I shape, and the middle of the middle connecting rod of the two-shaft-shaped cross beam is provided with an upper structure in a vertical mode.
The main landing gear of the current air passenger A330 series airplane needs to be disassembled and assembled by using a special lifting platform for the main landing gear. The platform is large in size, heavy by 5 tons, inconvenient to move, complex to operate, high in price and large in required manpower and working hours. And because the main landing gear dedicated lifting platform is expensive, a plurality of airplane maintenance companies generally only have one lifting platform. With the development of the aviation industry in China and the large increase of the number of airplanes of airlines, the business of replacing A330 landing gear is more and more. For example, the business of replacing the a330 landing gear in south navigation 2017 has increased substantially. However, only one lifting platform special for the south navigation A330 landing gear is provided at present, and if the platform is occupied, the work of replacing the main landing gear by other A330 landing gears cannot be carried out.
On the other hand, general aircraft maintenance engineering companies are equipped with two sets of hydraulic equipment TP91-E COBRA (commonly called COBRA equipment) specially used for disassembling and assembling aircraft engines, and two sets of the hydraulic equipment are arranged on a movable base of the COBRA equipment, wherein two vertical and parallel upright posts and a hydraulic lifting cross beam are arranged on the movable base of the COBRA equipment. The cobra device has the advantages of convenient movement, electric operation, accurate action, small size and capability of completing the functions of lifting, front-back left-right movement only by one person.
Although both the main landing gear dedicated lifting platform and the cobra device are hydraulic lifting devices, they are specially designed for specific purposes, and even the process steps used are well specified in the manual, and cannot be easily changed in purpose and in disassembly and assembly processes. Up to now, no aircraft maintenance company has found a combination of the two.
Disclosure of Invention
The invention aims to solve the technical problem of providing a method for dismounting and mounting a main undercarriage of an airbus A330 airplane, which can dismount and mount the A330 main undercarriage without using a special lifting platform for the A330 main undercarriage, obviously saves manpower and labor hour and improves work efficiency.
The technical scheme adopted by the invention is as follows.
A dismounting method of the main undercarriage of an airbus A330 aircraft, the lower structure of the main undercarriage 7 of the airbus A330 series aircraft is a horizontal big I shape, and the middle of the middle connecting rod of two axial cross beams is erected with an upper structure; the method is characterized in that: the disassembling and assembling method comprises the following steps:
s1, placing the main landing gear of the airplane on the main landing gear bracket;
s2, connecting the aircraft main landing gear bracket with cobra equipment;
s3, operating the cobra device to lift the main landing gear of the airplane;
s4, connecting the main landing gear with the airplane large wing structure;
s5, disconnecting the main landing gear from the main landing gear bracket;
s6, operating the cobra device to lower the main landing gear bracket to the ground;
s7, removing the cobra device and the main landing gear bracket and cleaning the site;
two cobra devices are arranged, and two vertical and parallel upright posts and a hydraulic lifting cross beam are arranged on a movable base of the cobra device.
The step S1 includes the following sub-steps:
s1-1, manufacturing a main landing gear bracket, wherein the structure of the main landing gear bracket is as follows: the two ends of the top surface of the frame are provided with 4 bearing seats 2 and safety locks, the two end journals correspond to two large I-shaped two-shaft-shaped cross beams at the lower part of the main undercarriage, two sides of the top surface of the frame are provided with hinged support rods 3, the top ends of the support rods can be correspondingly supported on a vertical upper structure of the frame of the main undercarriage, two ends of the frame are inclined upwards and are provided with parallel rod-shaped lifting lugs 4, and the lower surface of the frame is provided with a travelling wheel 5;
and S1-2, locking journals at two ends of a large I-shaped two-shaft cross beam at the lower part of the main landing gear by using safety locks, fixedly supporting the journals on a bearing seat on the top surface of the bracket, turning up a hinged support rod on the top surface of the bracket, and supporting and fixing the top end of the hinged support rod on two sides of the upper structure of the main landing gear frame.
The step S2 is specifically as follows:
two cobra equipment are put face to face, establish two lifting hooks 6 on the hydraulic pressure lifting beam of cobra equipment, correspond and hang the parallel shaft-like lifting lug at the both ends of main undercarriage bracket uses the fixed pin to link cobra equipment lifting hook and main undercarriage bracket lifting lug to installation safety pin takes notes main undercarriage bracket initial position.
The step S3 is specifically as follows:
the main landing gear is lifted by the two operating cobra devices at the same lifting speed, and the lifting process needs to be kept horizontal to prevent collision with airplane parts.
After the aircraft is lifted to the required height, the cobra device is set to a height keeping state, and the main landing gear and the aircraft large wing structure can be connected at the moment.
The two ends of the frame are provided with parallel rod-shaped lifting lugs (4) of which the structures are as follows: the inner end of a rod-shaped lifting lug with a non-circular cross section is inserted into corresponding longitudinal holes formed in two ends of the frame and is fixed by a bolt; the main landing gear bracket bearing seat is a half-section type bearing seat.
Has the advantages that: by adopting the dismounting method of the invention, the A330 main landing gear can be dismounted only by using the existing equipment without using the special lifting platform of the A330 main landing gear, and because the mobility, the operability, the accuracy and the economy of the special lifting platform of the A330 main landing gear are all inferior to those of the cobra equipment, the use of the cobra equipment can also omit the link of landing gear passing through the frame, thereby obviously saving the labor and the working hours.
In addition, the cobra device is a tool for international comparison, and is popularized to the replacement of an undercarriage, so that the utilization rate of the cobra device is improved, and the cost is reduced.
Drawings
The invention is described in further detail below with reference to the figures and the specific embodiments.
FIG. 1 is a schematic perspective view of the main landing gear of an airbus A330 aircraft;
FIG. 2 is a schematic side view of a two-piece COBRA apparatus TP91-E COBRA;
FIG. 3 is a schematic front view of a COBRA apparatus TP91-E COBRA;
FIG. 4 is a schematic view of a main landing gear carrier;
FIG. 5 is a cross-sectional schematic view of FIG. 4;
FIG. 6 is one of the schematic views of the lifting gear of the cobra device;
fig. 7 is a second schematic view of the lifting gear of the cobra device (the support rod and the cobra device are not shown).
Detailed Description
Referring to fig. 1, the lower structure of the main landing gear 7 of the airbus a330 series airplane is a horizontal big I shape, and the middle of the middle connecting rod of the two-shaft cross beam is provided with an upper structure.
Fig. 2 and 3 show a two-piece COBRA device, model TP91-E COBRA, 8, with two vertical and parallel uprights and a hydraulic lifting beam on the movable base.
The embodiment of the method for dismounting and mounting the main undercarriage of the airbus A330 airplane is characterized in that: the disassembling and assembling method comprises the following steps:
s1, placing the main landing gear of the airplane on the main landing gear bracket;
s2, connecting the aircraft main landing gear bracket with cobra equipment;
s3, operating the cobra device to lift the main landing gear of the airplane;
s4, connecting the main landing gear with the airplane large wing structure;
s5, disconnecting the main landing gear from the main landing gear bracket;
s6, operating the cobra device to lower the main landing gear bracket to the ground;
s7, removing the cobra device and the main landing gear bracket and cleaning the site;
referring to fig. 4 and 5, step S1 includes the following sub-steps:
s1-1, manufacturing a main landing gear bracket, wherein the structure of the main landing gear bracket is as follows: a plane frame 1 with walking wheels, wherein two ends of the top surface of the frame are provided with 4 bearing seats 2 and a safety lock, the bearing seats are semi-split bearing seats and correspond to two end journals of a large I-shaped two-shaft beam at the lower part of a main undercarriage 7, two sides of the top surface of the frame are provided with hinged support rods 3, the top ends of the support rods can correspondingly support the vertical upper structure of the frame of the main undercarriage, two ends of the frame are inclined upwards and are provided with parallel rod-shaped lifting lugs 4, the inner ends of the rod-shaped lifting lugs with non-circular cross sections are inserted into corresponding longitudinal holes formed at two ends of the frame and are fixed by bolts, and the walking wheels 5 are arranged below the frame;
s1-2, locking the journals at two ends of a large I-shaped two-shaft cross beam at the lower part of the main landing gear by using safety locks, fixedly supporting the journals on a bearing seat on the top surface of the bracket, turning up a hinged support rod on the top surface of the bracket, and supporting the top end of the hinged support rod on two sides of the upper structure of the main landing gear frame and fixing the hinged support rod.
Step S2 is specifically as follows:
two cobra equipment are put face to face, establish two lifting hooks 6 on the hydraulic pressure lifting beam of cobra equipment, correspond and hang the parallel shaft-like lifting lug at the both ends of main undercarriage bracket uses the fixed pin to link cobra equipment lifting hook and main undercarriage bracket lifting lug to installation safety pin takes notes main undercarriage bracket initial position.
Step S3 is specifically as follows:
the main landing gear is lifted by the two operating cobra devices at the same lifting speed, and the lifting process needs to be kept horizontal to prevent collision with airplane parts.
After the aircraft is lifted to the required height, the cobra device is set to a height keeping state, and the main landing gear and the aircraft large wing structure can be connected at the moment.
Claims (1)
1. A dismounting method of the main landing gear of an airbus A330 airplane, the lower structure of the main landing gear (7) of the airbus A330 series airplane is a horizontal big I shape, and the middle of the middle connecting rod of two shaft-shaped cross beams is provided with an upper structure; the method is characterized in that: the disassembling and assembling method comprises the following steps:
s1, placing the main landing gear of the airplane on the main landing gear bracket;
s2, connecting the aircraft main landing gear bracket with cobra equipment;
s3, operating the cobra device to lift the main landing gear of the airplane;
s4, connecting the main landing gear with the airplane large wing structure;
s5, disconnecting the main landing gear from the main landing gear bracket;
s6, operating the cobra device to lower the main landing gear bracket to the ground;
s7, removing the cobra device and the main landing gear bracket and cleaning the site;
two cobra devices are arranged for each set, and two vertical and parallel upright posts and a hydraulic lifting cross beam are arranged on a movable base of each cobra device;
the step S1 includes the following sub-steps:
s1-1, manufacturing a main landing gear bracket, wherein the structure of the main landing gear bracket is as follows: a plane frame (1) with traveling wheels, wherein 4 bearing seats (2) and safety locks are arranged at two ends of the top surface of the frame, the bearing seats correspond to two end journals of a large I-shaped two-shaft-shaped cross beam at the lower part of the main undercarriage, two sides of the top surface of the frame are provided with hinged support rods (3), the top ends of the support rods can correspondingly support the vertical upper structure of the frame of the main undercarriage, two ends of the frame are inclined upwards and are provided with parallel rod-shaped lifting lugs (4), and the traveling wheels (5) are arranged below the frame;
s1-2, locking journals at two ends of a large I-shaped two-shaft-shaped cross beam at the lower part of the main landing gear by using safety locks, fixedly supporting the journals on a bearing seat on the top surface of a bracket, turning up a hinged support rod on the top surface of the bracket, and supporting and fixing the top end of the hinged support rod on two sides of the upper structure of the main landing gear frame;
the step S2 is specifically as follows:
the two cobra devices are arranged face to face, two lifting hooks (6) are arranged on a hydraulic lifting cross beam of the cobra devices and correspondingly hang parallel rod-shaped lifting lugs at two ends of the main undercarriage bracket, a fixing pin is used for connecting the cobra device lifting hooks and the main undercarriage bracket lifting lugs, a safety pin is installed, and the initial position of the main undercarriage bracket is recorded;
the step S3 is specifically as follows:
the two operating cobra devices are enabled to lift the main undercarriage at the same ascending speed, after the main undercarriage is lifted to the required height, the cobra devices are set to the height maintaining state, and at the moment, the main undercarriage can be connected with the airplane large wing structure;
the two ends of the frame are provided with parallel rod-shaped lifting lugs (4) of which the structures are as follows: the inner end of a rod-shaped lifting lug with a non-circular cross section is inserted into corresponding longitudinal holes formed in two ends of the frame and is fixed by a bolt; the main landing gear bracket bearing seat is a half-section type bearing seat.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711142748.5A CN108100293B (en) | 2017-11-17 | 2017-11-17 | Method for dismounting main undercarriage of airbus A330 aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711142748.5A CN108100293B (en) | 2017-11-17 | 2017-11-17 | Method for dismounting main undercarriage of airbus A330 aircraft |
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| Publication Number | Publication Date |
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| CN108100293A CN108100293A (en) | 2018-06-01 |
| CN108100293B true CN108100293B (en) | 2021-07-16 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201711142748.5A Active CN108100293B (en) | 2017-11-17 | 2017-11-17 | Method for dismounting main undercarriage of airbus A330 aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112441252A (en) * | 2020-10-14 | 2021-03-05 | 广州飞机维修工程有限公司 | Dismounting method of aircraft engine |
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| CN202461919U (en) * | 2012-05-25 | 2012-10-03 | 北京飞机维修工程有限公司 | Disassembly and assembly vehicle for landing gear of Boeing B737-800 airplane |
| CN102785236A (en) * | 2012-06-19 | 2012-11-21 | 中国民航大学 | Multifunctional mounting and dismounting vehicle for aircraft landing gear |
| CN105345420A (en) * | 2015-11-11 | 2016-02-24 | 北京特种机械研究所 | Dismounting and mounting device of undercarriage |
| CN205043440U (en) * | 2015-10-10 | 2016-02-24 | 中航飞机股份有限公司西安飞机分公司 | Dismouting device of undercarriage uplock |
| EP3109154A1 (en) * | 2015-06-23 | 2016-12-28 | Messier-Dowty Limited | A method of preloading an aircraft assembly, a preloading tool and an aircraft assembly |
| CN106347709A (en) * | 2016-11-07 | 2017-01-25 | 华东交通大学 | Civil aircraft undercarriage assembling and disassembling vehicle suitable for multiple aircraft types |
| CN106379392A (en) * | 2016-11-17 | 2017-02-08 | 中航通飞华南飞机工业有限公司 | Flexible mounting and storage dual-purpose device for nose landing gear |
| CN206407165U (en) * | 2017-01-19 | 2017-08-15 | 陕西理工学院 | A kind of undercarriage erecting device |
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2017
- 2017-11-17 CN CN201711142748.5A patent/CN108100293B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202461919U (en) * | 2012-05-25 | 2012-10-03 | 北京飞机维修工程有限公司 | Disassembly and assembly vehicle for landing gear of Boeing B737-800 airplane |
| CN102785236A (en) * | 2012-06-19 | 2012-11-21 | 中国民航大学 | Multifunctional mounting and dismounting vehicle for aircraft landing gear |
| EP3109154A1 (en) * | 2015-06-23 | 2016-12-28 | Messier-Dowty Limited | A method of preloading an aircraft assembly, a preloading tool and an aircraft assembly |
| CN205043440U (en) * | 2015-10-10 | 2016-02-24 | 中航飞机股份有限公司西安飞机分公司 | Dismouting device of undercarriage uplock |
| CN105345420A (en) * | 2015-11-11 | 2016-02-24 | 北京特种机械研究所 | Dismounting and mounting device of undercarriage |
| CN106347709A (en) * | 2016-11-07 | 2017-01-25 | 华东交通大学 | Civil aircraft undercarriage assembling and disassembling vehicle suitable for multiple aircraft types |
| CN106379392A (en) * | 2016-11-17 | 2017-02-08 | 中航通飞华南飞机工业有限公司 | Flexible mounting and storage dual-purpose device for nose landing gear |
| CN206407165U (en) * | 2017-01-19 | 2017-08-15 | 陕西理工学院 | A kind of undercarriage erecting device |
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| Publication number | Publication date |
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| CN108100293A (en) | 2018-06-01 |
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