CN109850184B - Supporting and fixing device for integral delivery of undercarriage and using method - Google Patents
Supporting and fixing device for integral delivery of undercarriage and using method Download PDFInfo
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- CN109850184B CN109850184B CN201910274513.4A CN201910274513A CN109850184B CN 109850184 B CN109850184 B CN 109850184B CN 201910274513 A CN201910274513 A CN 201910274513A CN 109850184 B CN109850184 B CN 109850184B
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Abstract
A supporting and fixing device for the integral delivery of an undercarriage and a using method thereof comprise an eccentric joint component (1), wherein one end of the eccentric joint component is provided with a first mounting hole (11) used for being connected with a mounting hole of a small rocker arm of the undercarriage, the other end of the eccentric joint component is provided with a connecting hole (12), and one end of a connecting rod (3) is inserted into the connecting hole and is fixedly connected with the eccentric joint component; the other end of the connecting rod (3) is in threaded connection with one end of a large nut (5), the other end of the large nut (5) is in threaded connection with an ear-insert connecting rod assembly (7), and an ear insert (72) and a positioning piece assembly mounting section (73) which are abutted against a rib plate on the front face of a rear support of the landing gear are arranged on the ear-insert connecting rod assembly; the positioning piece component (8) encircles the ear-inserted connecting rod component, and the positioning piece component (8) is hinged with the U-shaped clamp component (9); the U-shaped clamp assembly comprises a U-shaped clamp (91) arranged on the top surface of the landing gear rear support in a spanning mode, an upper face compression screw (92) pressing the landing gear rear support, and a back face compression screw (96).
Description
Technical Field
The invention relates to an aircraft landing gear, in particular to a supporting and fixing device for the integral delivery of the landing gear and a using method thereof.
Background
Before a certain undercarriage is delivered to a main engine plant for final assembly, all components (including hydraulic system components, electrical control system components and pneumatic system control components) need to be installed in an assembly plant. When the system element is installed, the system element is installed in place under the condition of completely simulating the installation attitude of the undercarriage; at the moment, in order to simulate the installation posture of the undercarriage, the supporting piece for supporting the small rocker arm and the rear support of the undercarriage is of a simple wood structure, and the length of the supporting piece cannot be adjusted. After all system components are installed in place and need to be checked and accepted by an army representative, the army representative is agreed with a host factory, all joints for connecting the system components are detached, and the system components are bundled and fixed. When the landing gear is transported to a main engine plant, a rear support of the landing gear is placed on a support column for safety, the rear support weighs hundreds of jin, and a wood head block is padded between the rear support and the support column for preventing collision damage. After the landing gear arrives at the main engine plant, workers are dispatched to reconnect all system elements of the landing gear according to the installation attitude of the airplane under the cooperation of the main engine plant.
Therefore, the work of the landing gear before delivery is complicated and repeated, and a large amount of manpower and material resources are consumed.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a supporting and fixing device which can be used for simulating all system elements of an undercarriage to be installed in place in the attitude of an airplane loader and realizing the integral delivery and hoisting of the undercarriage and a using method thereof.
The supporting and fixing device comprises an eccentric joint component, one end of the eccentric joint component is provided with a first mounting hole used for being connected with a small rocker mounting hole of the landing gear, the other end of the eccentric joint component is provided with a connecting hole, one end of a connecting rod is inserted into the connecting hole and is connected and fixed with the eccentric joint component, the eccentric joint component and the connecting rod are connected into a whole through an anti-rotation pin, the included angle between the mounting plane at the two ends of the first mounting hole and the axis of the eccentric joint component is 5.5 degrees, the included angle between the axis of the connecting hole and the axis L of the eccentric joint component is 5.06 degrees, the other end of the connecting rod and one end of a large nut are connected through threads and are fixed through a left locking nut, the other end of the large nut and one end of an ear-inserting connecting rod component are connected through threads and are fixed through a right locking nut, an ear insert and a mounting section of the ear insert and a positioning component used for abutting against the two sides of a rear face rib plate of the landing gear and a rear face of the landing gear are arranged on the positioning component mounting section, the positioning component is encircled on the positioning component mounting section of the ear insert, the positioning component is hinged to the U-shaped clamping component, the U-shaped clamp component is arranged on the top face of the.
Further, the connecting rod is connected with the large nut through a left thread, and the large nut is connected with the ear-inserted connecting rod assembly through a right thread.
Furthermore, polytetrafluoroethylene base plates are respectively arranged on the contact surfaces of the lug plugs and the undercarriage rear support, so that the surface quality of the undercarriage during transportation is ensured.
Further, the length of the positioning piece component mounting section is greater than the mounting length of the positioning piece component.
Furthermore, the positioning element assembly comprises a mounting seat and a pressing plate which are oppositely mounted, a mounting hole surrounding the mounting section of the positioning element assembly is formed between the mounting seat and the pressing plate, a hinge support is arranged at one end of the mounting seat and one end of the pressing plate, one end of the hinge support is hinged with the pressing plate, and the other end of the hinge support is fixedly connected with one end of the mounting seat through threads; and the other ends of the mounting seat and the pressure plate are provided with swing bolts, one ends of the swing bolts are hinged with the other end of the mounting seat, and the other ends of the swing bolts are connected with shoulder nuts through threads.
Furthermore, the U-shaped clamp assembly further comprises an arc pressing block arranged on the head of the pressing screw, a front pressing screw arranged on the front side of the U-shaped clamp and used for pressing a front groove of a rear support of the undercarriage, and a plane pressing block arranged on the front pressing screw and the head of the pressing screw on the back side, wherein the arc pressing block and the plane pressing block are made of polytetrafluoroethylene.
Further, the U-shaped clamp is divided into a left U-shaped clamp and a right U-shaped clamp.
In order to solve the technical problem, the invention also provides a use method of the integral delivery, support and fixing device for the landing gear, which comprises the following steps:
installing a first installation hole of the eccentric joint component into an installation hole of a small undercarriage rocker arm, and hinging the eccentric joint component with the small undercarriage rocker arm by using a connecting bolt on an airplane;
the lug of the lug insertion connecting rod assembly is abutted against two sides of a rib plate on the front face of a rear support of the undercarriage;
adjusting a large nut to enable the connecting rod and the lug insert connecting rod assembly to move outwards simultaneously, so that the rear support of the undercarriage is in an installation posture;
after the rear support of the undercarriage is adjusted to the installation attitude of the airplane, respectively locking a left locking nut and a right locking nut;
mounting the positioning piece assembly on a positioning piece assembly mounting section of the ear-inserting connecting rod assembly, adjusting the positioning piece assembly to a proper position, and then screwing the shoulder nut to fix the positioning assembly;
the U-shaped clamp assembly is hinged with a pressing plate of the positioning piece assembly, a front face compression screw, an upper face compression screw and a back face compression screw on the U-shaped clamp assembly are respectively screwed down and locked by a locking nut, so that the rear support of the undercarriage is subjected to the pulling and jacking forces of the U-shaped clamp assembly, and the correct installation posture of the rear support is completely ensured;
after the installation posture of the landing gear is fixed, all system elements are installed on the landing gear, and the landing gear is integrally transported to a main engine factory for assembly.
Further, the eccentric joint assembly moves within 4mm of the connecting bolt axis.
Furthermore, the lug is inserted into a left gap and a right gap of 5mm for adjustment, and the adjustable length of the threads at the two ends of the large nut is 75 mm.
Compared with the prior art, the invention has the advantages that:
1. the supporting and fixing device for the integral delivery of the undercarriage can completely simulate the installation attitude of the undercarriage on an assembly site, and can be used for carrying out full-open display after all hydraulic system elements, electric appliance control system elements and pneumatic control system elements are installed in place, so that convenience is brought to the military and inspection and acceptance. After the acceptance is qualified, the undercarriage can be transported to a host factory in an installed posture, a lifting point (shown in figure 2) for integrally installing the undercarriage on the airplane is provided, a convenient condition for integrally installing the undercarriage on the airplane is provided for the host factory, the manpower and the financial resources are saved, and the one-time handing-over inspection qualification rate of the undercarriage is ensured to reach 100%.
2. The invention can be used for supporting, fixing and adjusting the left and right parts of the landing gear.
3. The invention designs the eccentric joint component, skillfully converts the spatial double angles of the mounting hole of the small rocker arm of the undercarriage into the angles of two planes, connects the small rocker arm and the rear support which are not connected with the undercarriage into a whole, reliably positions, completely simulates the installation posture of the undercarriage, and reduces the manufacturing and installation difficulty.
4. The positioning piece component capable of rotating 360 degrees is designed, and can move in a certain range along the axial direction of the ear-inserting connecting rod component; a U-shaped clamp assembly is arranged on a pressure plate of the positioning piece assembly to firmly tension the undercarriage rear support, and all hydraulic system elements, electric appliance control system elements, pneumatic system control elements, pipe clamps and pipe supports can be arranged on the undercarriage rear support to completely simulate the undercarriage installation state.
5. The invention is provided with a big nut with left and right threads, a connecting rod and an ear-inserted connecting rod component; the connecting rod is provided with a left thread, the ear insert connecting rod component is provided with a right thread, and the connecting rod and the ear insert connecting rod can be adjusted or adjusted simultaneously or one of the two can be adjusted according to the requirement and locked respectively after being adjusted in place.
6. All parts of the landing gear directly contacted with the landing gear are designed with polytetrafluoroethylene bushings or pressing blocks, so that the surface quality of the landing gear in the transportation process is ensured.
7. The ear-inserted connecting rod assembly of the invention props against two sides of a rib plate on the front surface of the undercarriage rear support, the U-shaped clamping assembly tensions the back surface of the rear support, and meanwhile, a hold-down screw is also designed on a front surface groove of the U-shaped clamping assembly, so that the undercarriage rear support which is easy to turn is tensioned and propped, and the correct position of the rear support is completely ensured.
Drawings
Figure 1 is a three-dimensional schematic view of the support and fixing device for the integral delivery of landing gears according to the invention.
Fig. 2 is a schematic view of the working condition of the support and fixing device for the integral delivery of landing gear according to the invention.
Fig. 3 is a two-dimensional schematic view of an eccentric joint assembly of the present invention.
FIG. 4 is a three-dimensional schematic view of the eccentric joint assembly of the present invention.
Fig. 5 is a two-dimensional schematic of the connecting rod of the present invention.
Fig. 6 is a two-dimensional schematic of a large nut of the present invention.
FIG. 7 is a front view of the ear-pin link assembly of the present invention.
FIG. 8 is a cross-sectional view of the ear-pin link assembly of the present invention.
FIG. 9 is a three-dimensional schematic view of an ear-pin link assembly of the present invention.
Figure 10 is a three-dimensional schematic view of a spacer assembly of the present invention.
Figure 11 is a three-dimensional schematic view of a keeper assembly mount of the present invention.
Figure 12 is a three-dimensional schematic view of a keeper assembly pressure plate of the present invention.
Figure 13 is a three-dimensional schematic view of a hinge bracket of the spacer assembly of the present invention.
Figure 14 is a three-dimensional schematic view of a spacer assembly swing bolt of the present invention.
Figure 15 is a three-dimensional schematic view of a clevis assembly of the present invention.
Figure 16 is a simplified three-dimensional view of a clevis of the clevis assembly of the present invention.
Figure 17 is a cross-sectional view of a shoe of the clevis assembly of the present invention.
Figure 18 is a view of the compression screw (top, front, back) configuration of the clevis assembly of the present invention.
In the figure:
1 eccentric joint assembly, 2 anti-rotation pins, 3 connecting rods, 4 left locking nuts, 5 large nuts, 6 right locking nuts, 7 eared link assemblies, 8 locating piece assemblies, 9U-shaped clamp assemblies, 10 connecting pins, 11 first mounting holes, 12 connecting holes, 13 first anti-rotation pin holes, 31 second anti-rotation pin holes, 32 first left threads, 51 second left threads, 52 first right threads, 71 second right threads, 72 eared inserts, 73 locating piece assembly mounting sections, 81 mounting seats, 82 washers, 83 hinge supports, 84 press plates, 85 first pins, 86 shoulder nuts, 87 swing bolts, 88 second pins, 89U-shaped clamp assembly connecting seats, 91U-shaped clamps, 92 upper press screws, 93 cambered press blocks, 94 locating piece assembly connecting seats, 95 front press screws, 96 back press screws, 97 plane press blocks, A support fixing devices, B rear supports, C buffers, D swing arms, E airplane wheels, F lifting points, G, H lifting points, I supports, J swing arm assemblies, K small support blocks, L eccentric axis blocks.
Detailed Description
The invention is further described below with reference to specific preferred embodiments, without thereby limiting the scope of protection of the invention.
For convenience of description, the description of the relative position of the components (e.g., up, down, left, right, etc.) is described with reference to the layout direction of the drawings, and does not limit the structure of the patent.
Example 1:
as shown in fig. 1 and 2, the supporting and fixing device for the integral delivery of the landing gear of the invention is composed of 10 parts: eccentric joint subassembly 1, stop pin 2, connecting rod 3 (left hand thread), left lock nut 4, big nut 5, right lock nut 6, ear insert link assembly 7 (right hand thread), locating piece subassembly 8, U type clamp subassembly 9, connecting pin 10, and connecting rod 3, big nut 5, ear insert link assembly 7, locating piece subassembly 8, U type clamp subassembly 9 are connected in proper order to one end of eccentric joint subassembly 1. The anti-rotation pin 2 is inserted into the connecting rod 3 through the eccentric joint component 1 to connect the eccentric joint component 1 and the connecting rod 3 into a whole, and the connecting rod 3 cannot rotate in the eccentric joint component 1 during working. The two ends of the big nut 5 are respectively provided with a left locking nut 4 and a right locking nut 6, so that the connecting rod 3 and the ear-inserting connecting rod component 7 are respectively positioned, and the connecting pin 10 is used for connecting the positioning piece component 8 and the U-shaped clamp component 9 into a whole. The left end of the big nut 5 is connected with the connecting rod 3, the right end is connected with the lug-inserted connecting rod assembly 7, and the big nut and the lug-inserted connecting rod assembly are respectively locked by the left locking nut 4 and the right locking nut 6. The positioning member assembly 8 surrounds the ear-insert link assembly 7 and is locked on the ear-insert link assembly 7 by the shoulder nut 86. The U-shaped clamp assembly 9 is connected with the positioning piece assembly 8 by a connecting pin 10 and can rotate around the connecting pin 10.
As shown in fig. 3 and 4, the left end of the eccentric joint assembly 1 is provided with a first mounting hole 11 for realizing connection with a small rocker arm mounting hole of an undercarriage, the right end of the eccentric joint assembly 1 is provided with a connecting hole 12 for connecting with a connecting rod 3 and a first anti-rotation pin hole 13 communicated with the connecting hole 12, an included angle between a mounting plane at two ends of the first mounting hole 11 and an axis L of the eccentric joint assembly is 5.5 degrees, and an included angle between an axis of the connecting hole 12 and an axis L of the eccentric joint assembly is 5.06 degrees, so that a spatial double angle of the small rocker arm mounting hole of the undercarriage can be skillfully converted into an angle of two planes, the possibility is provided for connecting the small rocker arm without connection relation with the undercarriage and a rear bracket into a whole, the positioning is reliable, the installation attitude of the undercarriage is completely simulated.
As shown in fig. 5, the left end of the connecting rod 3 is provided with a second anti-rotation pin hole 31, the right end is provided with a first left thread 32, the left end of the connecting rod 3 is pressed into the connecting hole 12 of the eccentric joint component 1 in a H7/r6 fit manner, and the anti-rotation pin 2 is inserted into the second anti-rotation pin hole 31 through the first anti-rotation pin hole 13, so that the eccentric joint component 1 and the connecting rod 3 are positioned.
As shown in fig. 6, the large nut 5 is provided with a second left thread 51 at the left end and a first right thread 52 at the right end.
As shown in fig. 7-9, the left end of the ear-plug connecting rod assembly 7 is provided with a second right thread 71, the right end is provided with an ear plug 72 and a positioning element assembly mounting section 73 for abutting against two sides of a rib plate on the front face of the landing gear rear bracket, and the contact surfaces of the ear plug 72 and the landing gear rear bracket are respectively provided with a polytetrafluoroethylene base plate, and the length of the positioning element assembly mounting section 73 is greater than the mounting length of the positioning element assembly 8, so that the positioning element assembly 8 can move within a certain range along the positioning element assembly mounting section 73.
As shown in fig. 10-14, the positioning member assembly 8 includes a mounting seat 81 with a semicircular mounting hole and a pressing plate 84, and a complete mounting hole is formed in the middle of the mounting seat 81 and the pressing plate 84 after the mounting seat 81 and the pressing plate 84 are oppositely mounted. A hinge support 83 is arranged at one end of the mounting seat 81 and one end of the pressure plate 84, one end of the hinge support 83 is connected with the pressure plate 84 through a first pin 85, so that the pressure plate 84 can rotate around the first pin 85, and the other end of the hinge support 83 is sleeved with the gasket 82 and then is connected and fixed with a threaded hole arranged at the left end of the mounting seat 81. The other ends of the mounting seat 81 and the pressure plate 84 are provided with a swing bolt 87, the swing bolt 87 is arranged in a right end groove of the mounting seat 81 through a second pin 88, and the swing bolt 87 can rotate around the second pin 88; the threaded end of the swing bolt 87 is tightened against the shoulder nut 86. The upper surface of the pressing plate 84 is provided with a U-shaped clamp assembly connecting seat 89, and the whole positioning member assembly 8 is positioned on the ear-inserting connecting rod assembly 7 through the U-shaped clamp assembly connecting seat 89.
As shown in fig. 15-18, the U-shaped clip assembly 9 includes a U-shaped clip 91 straddling the top surface of the landing gear rear bracket, an upper pressing screw 92 disposed at the top of the U-shaped clip 91 for pressing the top surface of the landing gear rear bracket, a press shoe 93 disposed at the head of the upper pressing screw 92, a spacer assembly connecting seat 94 disposed at the front of the U-shaped clip 91, a front pressing screw 95 for pressing the front groove of the landing gear rear bracket, a back pressing screw 96 disposed at the back of the U-shaped clip 91 for pressing the back surface of the landing gear rear bracket, a plane press shoe 97 disposed at the head of the front pressing screw 95 and the back pressing screw 96, the upper pressing screw 92, the front pressing screw 95 and the back pressing screw 96 are respectively connected with the U-shaped clip 91 by screw threads, the press shoe 93 and the plane press shoe 97 are made of teflon, the press shoe 93 and the plane press shoe 97 are respectively connected with the corresponding pressing screws by, after each compression screw is adjusted in place, each compression screw is locked by a respective locking nut. For the mounting of the left and right landing gear parts, the U-shaped clamp 91 is designed with a left and a right part.
In use, as shown in fig. 1 and 2 (the left part of the landing gear is taken as an example in the figure), the eccentric joint assembly 1 is installed in the mounting hole of the small rocker arm of the landing gear, and the eccentric joint assembly 1 and the small rocker arm of the landing gear are fixed by a connecting bolt on the airplane, so that the eccentric joint assembly 1 cannot fall out of the mounting hole of the small rocker arm, can rotate around the connecting bolt and can move within 4mm along the axial direction of the connecting bolt. The ear insert 72 of the ear insert connecting rod component 7 is supported at two sides of a rib plate at the front face of the rear support of the landing gear (the left and the right of each ear insert connecting rod component have an adjustable gap of 5 mm); adjusting big nut 5 (left and right screw thread each adjustable length 75mm, middle part clearance 20 mm), connecting rod 3 and ear insert link assembly 7 outwards move simultaneously (stretch promptly), when adjusting to undercarriage installation gesture soon, can finely tune connecting rod 3 or ear insert link assembly 7 alone according to on-the-spot actual need, other spare parts can not follow-up. And after the rear support of the undercarriage is adjusted to the installation attitude of the airplane, respectively locking the left locking nut 4 and the right locking nut 6. Mounting the positioner assembly 8 to the positioner assembly mounting section 73 of the ear-pin linkage assembly 7 such that the positioner assembly 8 can move on the positioner assembly mounting section 73 of the ear-pin linkage assembly 7 or rotate 360 ° about the positioner assembly mounting section; after being adjusted in position, the shoulder nut 86 shown in fig. 10 is tightened to secure the positioning assembly 8. The clevis assembly 9 is mounted to the keeper 84 of the keeper assembly 8 by the connector pin 10 and is rotatable about the connector pin 10. The front compression screw, the upper compression screw and the back compression screw on the U-shaped clamp assembly 9 shown in fig. 15 are respectively screwed and locked by locking nuts respectively. At the moment, the rear support of the undercarriage is pulled and pushed, so that the correct installation posture of the rear support is completely ensured. After the installation attitude of the undercarriage is fixed, all system elements are installed on the back face of a rear support of the undercarriage, the small support, the upper surface of a support column and the like, and the whole undercarriage is transported to a main engine plant for assembly. When the right part of the landing gear is supported and fixed, the eccentric joint assembly 1 is rotated by 180 degrees, and the U-shaped clamp assembly 9 is installed on the right part, and the rest parts are installed like the left part of the landing gear.
The above description is only for the preferred embodiment of the present application and should not be taken as limiting the present application in any way, and although the present application has been disclosed in the preferred embodiment, it is not intended to limit the present application, and those skilled in the art should understand that they can make various changes and modifications within the technical scope of the present application without departing from the scope of the present application, and therefore all the changes and modifications can be made within the technical scope of the present application.
Claims (10)
1. A supporting and fixing device for the integral delivery of an undercarriage is characterized by comprising an eccentric joint component (1), wherein one end of the eccentric joint component is provided with a first mounting hole (11) connected with a mounting hole of a small rocker arm (J) of the undercarriage, the other end of the eccentric joint component is provided with a connecting hole (12), one end of a connecting rod (3) is inserted into the connecting hole to be connected and fixed with the eccentric joint component, the eccentric joint component and the connecting rod are connected into a whole through an anti-rotation pin (2), an included angle between a mounting plane at the two ends of the first mounting hole and an axis (L) of the eccentric joint component is 5.5 degrees, an included angle between the axis of the connecting hole (12) and an axis (L) of the eccentric joint component is 5.06 degrees, the other end of the connecting rod (3) is connected with one end of a large nut (5) through threads and is fixed by a left locking nut (4), the other end of the large nut (5) and one end of an ear insertion connecting rod component (7) are connected through threads and fixed by a right locking nut (6), an ear insertion connecting rod component (73) and a rear clamping component mounting section (73) for abutting against the two sides of a rear support bracket (B) is arranged on a rear clamping and a rear clamping component (73) is arranged on a rear clamping and a rear clamping component clamping and a rear clamping part (8).
2. A support and fixing device for the integrated delivery of landing gears according to claim 1, wherein the connecting rod is connected with the large nut through a left thread, and the large nut is connected with the ear-insertion connecting rod assembly through a right thread.
3. A supporting and fixing device for the integral delivery of a landing gear according to claim 1, wherein the contact surfaces of the lug and the landing gear rear bracket are respectively provided with a polytetrafluoroethylene base plate.
4. A support and securement device for the unitary delivery of landing gear according to claim 1, wherein the length of said spacer assembly mounting section is greater than the mounting length of said spacer assembly.
5. The supporting and fixing device for the integral delivery of the landing gear is characterized in that the positioning element assembly comprises a mounting seat (81) and a pressing plate (84) which are oppositely mounted, a mounting hole surrounding the mounting section of the positioning element assembly is formed between the mounting seat and the pressing plate, a hinge support (83) is arranged at one end of the mounting seat and one end of the pressing plate, one end of the hinge support is hinged with the pressing plate, and the other end of the hinge support is fixedly connected with one end of the mounting seat through threads; and the other ends of the mounting seat and the pressure plate are provided with swing bolts (87), one ends of the swing bolts are hinged with the other end of the mounting seat, and the other ends of the swing bolts are connected with shoulder nuts (86) through threads.
6. A supporting and fixing device for the whole delivery of landing gear according to claim 1, characterized in that the clevis assembly further comprises a press-shoe (93) arranged on the upper face of the clevis for pressing the head of the landing gear, a front face pressing screw (95) arranged on the front face of the clevis for pressing the front face slot of the rear landing gear bracket, and a flat press-shoe (97) arranged on the front face pressing screw and the rear face pressing screw head, and the press-shoe and the flat press-shoe are made of teflon.
7. A support and securement device for the unitary delivery of landing gear according to claim 1, wherein said clevis is divided into a left clevis and a right clevis.
8. Use of a landing gear integrated delivery support and fixing device according to any one of claims 1 to 7, characterised in that it comprises the following steps:
a first mounting hole of the eccentric joint component (1) is arranged in a mounting hole of a small undercarriage rocker arm (J), and the eccentric joint component is hinged with the small undercarriage rocker arm by a connecting bolt on an airplane;
the ear insert (72) of the ear insert connecting rod component (7) is supported on two sides of a rib plate on the front face of the rear support of the landing gear;
adjusting a large nut (5) to enable the connecting rod (3) and the lug insert connecting rod assembly (7) to move outwards simultaneously, so that the rear support of the undercarriage is in an installation posture;
after the rear support of the undercarriage is adjusted to the installation attitude of the airplane, a left locking nut (4) and a right locking nut (6) are respectively locked;
mounting the positioning piece assembly (8) on a positioning piece assembly mounting section (73) of the ear-insert connecting rod assembly (7), adjusting the positioning piece assembly to a proper position, and then screwing a shoulder nut (86) to fix the positioning piece assembly;
the U-shaped clamp assembly (9) is hinged with a pressure plate (84) of the positioning piece assembly (8), a front face compression screw, an upper face compression screw and a back face compression screw on the U-shaped clamp assembly are respectively screwed and locked by a locking nut, so that the rear support of the undercarriage is pulled and pushed by the U-shaped clamp assembly, and the correct installation posture of the rear support is completely ensured;
after the installation posture of the landing gear is fixed, all system elements are installed on the landing gear, and the landing gear is integrally transported to a main engine factory for assembly.
9. Use of the landing gear integrated delivery support fixing device according to claim 8, wherein the eccentric joint assembly (1) moves within 4mm of the connecting bolt axis.
10. The use method for the landing gear integral delivery support fixing device according to claim 8, wherein the lug is inserted in a left and right 5mm gap for adjustment, and the adjustable length of the two-end thread of the large nut is 75 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910274513.4A CN109850184B (en) | 2019-04-08 | 2019-04-08 | Supporting and fixing device for integral delivery of undercarriage and using method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910274513.4A CN109850184B (en) | 2019-04-08 | 2019-04-08 | Supporting and fixing device for integral delivery of undercarriage and using method |
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| CN109850184A CN109850184A (en) | 2019-06-07 |
| CN109850184B true CN109850184B (en) | 2020-07-17 |
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| CN111519009B (en) * | 2020-05-11 | 2021-12-03 | 中航飞机起落架有限责任公司 | Pneumatic shot blasting part surface strengthening device |
| CN114408209B (en) * | 2021-12-28 | 2024-01-12 | 中国飞机强度研究所 | Connecting method and connecting structure of resultant force point double ears and lever load transmission system |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US8220740B2 (en) * | 2007-11-06 | 2012-07-17 | Borealis Technical Limited | Motor for driving aircraft, located adjacent to undercarriage wheel |
| FR2987441B1 (en) * | 2012-02-24 | 2014-12-19 | Airbus Operations Sas | DEVICE FOR EXCITATION TO THE GROUND OF A LANDING TRAIN OF AN AIRCRAFT. |
| CN203698083U (en) * | 2013-12-23 | 2014-07-09 | 南京中航特种装备有限公司上海技术中心 | Connecting device for wing engine hanging position |
| CN104773306B (en) * | 2015-04-07 | 2017-02-01 | 中国直升机设计研究所 | Main landing gear three-way loading test device |
| CN106742043A (en) * | 2017-01-19 | 2017-05-31 | 陕西理工学院 | A kind of undercarriage installs car |
| CN108100305A (en) * | 2017-12-29 | 2018-06-01 | 南京航空航天大学 | A kind of new landing gear drop test rotary support and experimental method |
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