CN220616186U - Dismounting mechanism for nose landing gear of airplane - Google Patents
Dismounting mechanism for nose landing gear of airplane Download PDFInfo
- Publication number
- CN220616186U CN220616186U CN202322325828.1U CN202322325828U CN220616186U CN 220616186 U CN220616186 U CN 220616186U CN 202322325828 U CN202322325828 U CN 202322325828U CN 220616186 U CN220616186 U CN 220616186U
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- landing gear
- nose landing
- assembly
- shaft
- telescopic action
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- 238000009434 installation Methods 0.000 claims abstract description 31
- 239000003638 chemical reducing agent Substances 0.000 claims description 18
- 229910000831 Steel Inorganic materials 0.000 claims description 15
- 239000010959 steel Substances 0.000 claims description 15
- 230000033001 locomotion Effects 0.000 abstract description 6
- 238000000034 method Methods 0.000 description 5
- 238000005452 bending Methods 0.000 description 4
- 230000006378 damage Effects 0.000 description 4
- 208000027418 Wounds and injury Diseases 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 208000014674 injury Diseases 0.000 description 2
- 235000017166 Bambusa arundinacea Nutrition 0.000 description 1
- 235000017491 Bambusa tulda Nutrition 0.000 description 1
- 241001330002 Bambuseae Species 0.000 description 1
- 235000015334 Phyllostachys viridis Nutrition 0.000 description 1
- 230000004308 accommodation Effects 0.000 description 1
- 239000011425 bamboo Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 230000009975 flexible effect Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
- 230000029305 taxis Effects 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
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- Motorcycle And Bicycle Frame (AREA)
Abstract
The technical scheme of the utility model provides an aircraft nose landing gear dismounting mechanism which comprises an installation vehicle body, a rotating mechanism and a pitching mechanism; the rotating mechanism comprises a pair of telescopic action cylinders and a pair of bracket components, the telescopic action cylinders are respectively arranged on two sides of the installation vehicle body, the pair of bracket components are respectively arranged at the movable ends of the telescopic action cylinders, the bracket components are used for being inserted into shaft supporting points on the side surfaces of the landing gear to be connected, and the telescopic action cylinders are used for lifting and driving the bracket components to rotate the landing gear by a rotating angle. The utility model realizes the movement and the adjustment of the space posture of the nose landing gear by installing the vehicle body, the rotating mechanism and the pitching mechanism, solves the installation difficulties of difficult movement of the nose landing gear, difficult entering of the nose landing gear into the hanging point and difficult installation of the nose landing gear, and has simple structure, low cost, simple operation, convenient use and good safety performance.
Description
Technical Field
The utility model relates to the technical field of aircraft maintenance, in particular to an aircraft nose landing gear dismounting mechanism.
Background
Aircraft landing gear is a landing gear for an aircraft that functions to ensure that the aircraft takes off, lands, taxis and parks. The nose landing gear of the aircraft has the characteristics of huge volume, heavy weight and narrow installation position, and the conventional installation method of the nose landing gear of the aircraft is still installed by 13 persons in a purely manual cooperation mode at present.
In the mounting of the nose landing gear, it is necessary to tilt the nose landing gear by 20 ° to 30 °, and to continuously hold the position of the landing gear with force for hole mounting. In practical operation, the manual installation method is difficult to finely adjust the space position of the landing gear, the installation state is difficult to maintain for a long time, and personnel injury and machine part damage are easily caused.
Disclosure of Invention
In view of the foregoing, it is necessary to provide a nose landing gear dismounting mechanism for an aircraft, which solves the technical problems of time and labor waste and easy personnel injury and machine member damage caused by manpower installation of the nose landing gear in the prior art.
In order to achieve the technical purpose, the technical scheme of the utility model provides an aircraft nose landing gear dismounting mechanism, which comprises:
installing a vehicle body;
the rotating mechanism comprises a pair of telescopic action cylinders and a pair of bracket components, the telescopic action cylinders are respectively arranged on two sides of the mounting vehicle body, the pair of bracket components are respectively arranged at the movable ends of the telescopic action cylinders, the bracket components are used for being inserted into shaft supporting points on the side surfaces of the landing gear to be connected, and the telescopic action cylinders are used for lifting and driving the bracket components to rotate the landing gear by a rotating angle;
the pitching mechanism comprises a traction assembly and a connecting piece, wherein the traction assembly is arranged on the installation vehicle body, and the connecting piece is arranged at the traction end of the traction assembly and is used for being detachably connected to a strut of the landing gear.
Further, the installation automobile body includes frame, universal wheel, footboard and installation grillage, the shape of frame is the U-shaped to form the exit and the accommodation space of undercarriage, four the universal wheel sets up the bottom of frame, the footboard with the installation grillage all sets up the top of frame, wherein, every single move mechanism installs on the installation grillage, the footboard is located the both sides of installation grillage.
Further, the support assembly comprises a support arm piece, a pivot shaft piece and a limiting piece, wherein the support arm piece is arranged at the movable end of the telescopic action cylinder, the pivot shaft piece is rotationally connected to the support arm piece and used for supporting the landing gear by inserting a shaft fulcrum of the side face of the landing gear, the pivot shaft piece on one side is further in sliding connection with the support arm piece on the side and used for moving along the left-right direction, and the limiting piece is detachably arranged on the pivot shaft piece and used for limiting the side face of the landing gear in a fitting manner.
Further, the left side the support arm spare includes pole setting and pivot, the pole setting sets up the expansion end of flexible action section of thick bamboo, the pivot sets up the front side and the rear side of pole setting, the left side the fulcrum shaft spare includes slide bar and first location axle, the slide bar cover is established in front side and rear side between the pivot, and with pivot sliding connection, first location axle sets up the right-hand member of slide bar.
Further, the support arm piece on the right side comprises a Z-shaped arm, the top end of the Z-shaped arm is connected with the movable end of the telescopic action cylinder, the fulcrum shaft piece on the right side comprises a second positioning shaft, and the second positioning shaft is rotationally connected with the bottom end of the Z-shaped arm.
Further, the telescopic action cylinder on the left side is arranged on the left side wall of the installation car body.
Further, the limiting piece comprises nuts which are respectively connected to the first positioning shaft and the second positioning shaft in a threaded mode.
Further, the traction assembly comprises a speed reducer, a reel and a pulley assembly, wherein the speed reducer and the pulley assembly are both installed at the top of the installation vehicle body, the reel is arranged on an output shaft of the speed reducer, a handle for driving the speed reducer to rotate is arranged on one side of the speed reducer, a steel cable is arranged on the outer side of the reel, and the steel cable is in sliding connection with the pulley assembly.
Further, the connecting piece comprises a lock hook, and one end of the lock hook is connected with the steel cable.
Further, the pulley assembly comprises a base, a movable frame and a pulley body, wherein the movable frame is rotationally connected to the inner side of the base, the pulley body is rotationally connected to the inner side of the movable frame, and the steel cable is in sliding connection with the pulley body.
Compared with the prior art, the utility model has the beneficial effects that: through installation automobile body, rotary mechanism and every single move mechanism, realized the regulation of the removal of nose landing gear, the difficult, difficult installation difficult of nose landing gear entering suspension point of nose landing gear entering, nose landing gear installation difficulty of nose landing gear, simple structure, low cost, easy operation, convenient to use and security performance are good moreover.
Drawings
FIG. 1 is a structural three-dimensional view of an aircraft nose landing gear removal mechanism according to an embodiment of the present utility model;
FIG. 2 is a front view of an aircraft nose landing gear assembly and disassembly mechanism according to an embodiment of the present utility model;
FIG. 3 is a structural three-dimensional view of a Z-arm according to an embodiment of the present utility model;
in the figure: 1. installing a vehicle body; 11. a frame; 12. a universal wheel; 13. a pedal; 14. installing a plate frame;
2. a rotation mechanism; 21. a telescopic action cylinder; 22. a bracket assembly;
221. a support arm member; 222. a fulcrum shaft member; 223. a limiting piece;
2211. a vertical rod; 2212. a rotating shaft; 2221. a slide bar; 2222. a first positioning shaft;
2213. a Z-shaped arm; 2223. a second positioning shaft;
3. a pitch mechanism; 31. a pulling assembly; 32. a linking member;
311. a speed reducer; 312. a reel; 313. a pulley assembly; 314. a wire rope;
3131. a base; 3132. a movable frame; 3133. a pulley body.
Detailed Description
Preferred embodiments of the present utility model will now be described in detail with reference to the accompanying drawings, which form a part hereof, and together with the description serve to explain the principles of the utility model, and are not intended to limit the scope of the utility model.
As shown in fig. 1-3, the utility model provides an aircraft nose landing gear dismounting mechanism, which comprises a mounting vehicle body 1, a rotating mechanism 2 and a pitching mechanism 3, wherein the mounting vehicle body 1 provides a containing space of the aircraft nose landing gear, the rotating mechanism 2 supports and rotationally adjusts the nose landing gear, and the pitching mechanism 3 adjusts the pitching angle of the nose landing gear; the rotating mechanism 2 comprises a pair of telescopic action cylinders 21 and a pair of bracket components 22, the telescopic action cylinders 21 are respectively arranged on two sides of the installation vehicle body 1, the pair of bracket components 22 are respectively arranged at the movable ends of the telescopic action cylinders 21, the bracket components 22 are used for being inserted into shaft supporting points on the side surfaces of the landing gear for connection, the telescopic action cylinders 21 are used for lifting and driving the bracket components 22 to rotate the landing gear by an angle, one side of the telescopic action cylinders 21 on the left side and the right side is lifted, and the other side of the telescopic action cylinders is positioned at a low point, so that the linkage bracket components 22 drive the front landing gear of the aircraft to incline, and the requirement of the inclination angle is met; the pitching mechanism 3 comprises a traction assembly 31 and an engagement member 32, wherein the traction assembly 31 is arranged on the installation vehicle body 1, the engagement member 32 is arranged at the traction end of the traction assembly 31 and is used for being detachably connected to a strut of the landing gear, and the engagement member 32 is pulled through the traction assembly 31, so that the nose landing gear is pulled forwards, and the pitching angle of the nose landing gear is adjusted.
It will be appreciated that the telescopic cylinder 21 may be a hydraulic ram to raise and lower the telescopic cylinder 21, adjust the attitude of the landing gear on the mounted vehicle body 1, and maintain the attitude of the nose landing gear.
In one embodiment, to facilitate movement of the mounting body 1, the mounting body 1 includes a frame 11, universal wheels 12, pedals 13, and a mounting bracket 14. The frame 11 is in a U shape, and forms an inlet and an outlet of the landing gear and a containing space, and the front landing gear can be in or out from the opening of the U shape. Four universal wheels 12 are arranged at the bottom of the frame 11, and the universal wheels 12 provide a moving function for installing the vehicle body 1. The pedal 13 and the installation grillage 14 are both arranged at the top of the frame 11, wherein the pitching mechanism 3 is installed on the installation grillage 14, the pedal 13 is positioned at two sides of the installation grillage 14, the pedal 13 is convenient to tread on the installation vehicle body 1, and the traction of the traction component 31 is stabilized.
In one embodiment, for the purpose of rotationally adjusting the nose landing gear, the bracket assembly 22 includes a support arm 221, a fulcrum shaft 222 and a limiting member 223, where the support arm 221 is disposed at a movable end of the telescopic action cylinder 21, the fulcrum shaft 222 is rotatably connected to the support arm 221 and is used for inserting a shaft fulcrum on a side of the landing gear to support the landing gear, and the fulcrum shaft 222 on one side is further slidably connected to the support arm 221 on the other side and is used for moving the fulcrum shaft 222 on the other side in a left-right direction so as to avoid interference to rotation, and the limiting member 223 is detachably disposed on the fulcrum shaft 222 and is used for abutting against the side of the landing gear to limit.
It will be appreciated that the cooperating stop 223 on the fulcrum shaft 222 acts to secure the landing gear, since rotation of the landing gear will produce a component along the axis of rotation which will cause the landing gear to slide downwardly along the fulcrum shaft 222; the landing gear is rotated with not only up-down displacement but also left-right displacement, so the fulcrum shaft 222 on the side of the nose landing gear is also slidably connected with the arm 221 on the side to ensure smooth sliding of the landing gear in the left-right direction.
Further, in order to have a space for moving left and right on one side, the left arm 221 includes a vertical rod 2211 and a rotating shaft 2212, the vertical rod 2211 is disposed at a moving end of the telescopic action cylinder 21, the rotating shaft 2212 is disposed at a front side and a rear side of the vertical rod 2211, the left fulcrum shaft 222 includes a sliding rod 2221 and a first positioning shaft 2222, the sliding rod 2221 is sleeved between the front side and the rear side of the rotating shaft 2212 and is slidably connected with the rotating shaft 2212, the first positioning shaft 2222 is disposed at a right end of the sliding rod 2221, a sliding groove is formed in the sliding rod 2221, and the rotating shaft 2212 is inserted into the sliding groove, so that the rotating shaft 2212 can slide along the sliding groove to provide a space for moving left and right, and can rotate around the rotating shaft 2212 as a shaft to perform rotation of the sliding rod 2221.
Further, for better installation when the landing gear wheel is assembled, the support arm 221 on the right side comprises a Z-shaped arm 2213, the top end of the Z-shaped arm 2213 is connected with the movable end of the telescopic action cylinder 21, the fulcrum shaft 222 on the right side comprises a second positioning shaft 2223, the second positioning shaft 2223 is rotatably connected with the bottom end of the Z-shaped arm 2213, and the position of the second positioning shaft 2223 is set lower through the Z-shaped arm 2213, so that the installation can be performed without lifting the nose landing gear.
Further, in order to reduce the height of the mounted vehicle, the telescopic cylinder 21 on the left side is provided on the left side wall of the mounted vehicle body 1.
It will be appreciated that the main factors determining the height of the mounted vehicle are the height of the telescopic action cylinder 21 and the height of the extension rod of the telescopic action cylinder 21, whereas the height of the telescopic action cylinder 21 itself is entirely dependent on the extension height of the telescopic action cylinder 21. The left telescopic cylinder 21 is designed to be positioned inside the vehicle in order to control the extension height of the telescopic cylinder 21, and the shorter the length, the smaller the height to be raised when rotated by the same angle.
Further, the limiting member 223 includes nuts, which are respectively screwed on the first positioning shaft 2222 and the second positioning shaft 2223, so as to facilitate installation and disassembly.
In one embodiment, in order to facilitate the adjustment of the pitching angle, the pulling assembly 31 includes a speed reducer 311, a reel 312 and a pulley assembly 313, the speed reducer 311 and the pulley assembly 313 are both installed at the top of the installation vehicle body 1, the reel 312 is disposed on an output shaft of the speed reducer 311, a handle for driving the speed reducer 311 to rotate is disposed on one side of the speed reducer 311, a steel cable 314 is disposed on the outer side of the reel 312, and the steel cable 314 is slidably connected with the pulley assembly 313, and since the landing gear strut is heavier, the pitching speed is not well controlled, so that the speed reducer 311 is disposed between the reel and the handle to control the pitching speed.
Further, the engagement member 32 includes a latch hook, one end of which is connected to the cable 314, and is connected to the post of the nose landing gear through the latch hook.
Further, in order to prevent the pulley body 3133 from bending the steel cable 314, the pulley assembly 313 includes a base 3131, a movable frame 3132 and a pulley body 3133, the movable frame 3132 is rotatably connected to the inner side of the base 3131, the pulley body 3133 is rotatably connected to the inner side of the movable frame 3132, and the rotation direction corresponds to the left-right movement direction of the steel cable 314, and the steel cable 314 is slidably connected to the pulley body 3133, so that when the steel cable 314 moves left and right, the steel cable 314 can be prevented from bending by the rotation of the pulley body 3133.
It will be appreciated that the nose landing gear assembly process is a complex motion process, the nose landing gear strut not only has pitch motion, but also has yaw when the landing gear is rotated, and the pulley body 3133 is relatively displaced in the lateral direction, and if the pulley body 3133 is stationary, the yaw will cause bending of the cable 314, which not only greatly increases the pitch difficulty of the strut, but also causes the risk of breakage of the cable due to bending of the cable 314. The pulley body 3133 is therefore designed to be rotatable to accommodate the left-right deflection of the strut.
The specific working procedure of the utility model is as follows: the front landing gear is moved into the frame 11, the second positioning shaft 2223 on the right side is spliced with a shaft fulcrum on the side surface of the front landing gear, the first positioning shaft 2222 on the left side is spliced with a shaft fulcrum on the other side of the front landing gear, and the nut is rotated to be attached to the front landing gear to fix the front landing gear; when the rotation angle needs to be adjusted, the nose landing gear can be tilted left and right by the extension and retraction of the extension and retraction action cylinder 21; when the pitching angle needs to be adjusted, the lock hook is hooked to the upright post of the nose landing gear, the speed reducer 311 is driven to drive the reel 312 to rotate through the rotating handle, and the steel cable 314 is pulled, so that the lock hook is driven to pull the nose landing gear, and the pitching angle of the nose landing gear is changed.
The entire workflow is completed and what is not described in detail in this specification is well known to those skilled in the art.
The present utility model is not limited to the above-mentioned embodiments, and any changes or substitutions that can be easily understood by those skilled in the art within the technical scope of the present utility model are intended to be included in the scope of the present utility model.
Claims (10)
1. An aircraft nose landing gear assembly and disassembly mechanism, comprising:
installing a vehicle body;
the rotating mechanism comprises a pair of telescopic action cylinders and a pair of bracket components, the telescopic action cylinders are respectively arranged on two sides of the mounting vehicle body, the pair of bracket components are respectively arranged at the movable ends of the telescopic action cylinders, the bracket components are used for being inserted into shaft supporting points on the side surfaces of the landing gear to be connected, and the telescopic action cylinders are used for lifting and driving the bracket components to rotate the landing gear by a rotating angle;
the pitching mechanism comprises a traction assembly and a connecting piece, wherein the traction assembly is arranged on the installation vehicle body, and the connecting piece is arranged at the traction end of the traction assembly and is used for being detachably connected to a strut of the landing gear.
2. The aircraft nose landing gear assembly and disassembly mechanism according to claim 1, wherein the mounting vehicle body comprises a vehicle frame, universal wheels, pedals and a mounting plate frame, the vehicle frame is U-shaped, an inlet and an outlet of the landing gear and a containing space are formed, the four universal wheels are arranged at the bottom of the vehicle frame, the pedals and the mounting plate frame are arranged at the top of the vehicle frame, wherein the pitching mechanism is mounted on the mounting plate frame, and the pedals are positioned at two sides of the mounting plate frame.
3. The aircraft nose landing gear assembly and disassembly mechanism according to claim 2, wherein the bracket assembly comprises a support arm member, a fulcrum shaft member and a limiting member, the support arm member is arranged at the movable end of the telescopic action cylinder, the fulcrum shaft member is rotatably connected to the support arm member and used for being inserted into a shaft fulcrum of the side face of the landing gear to support the landing gear, the fulcrum shaft member on one side is further slidably connected with the support arm member on the other side and used for being moved in the left-right direction, and the limiting member is detachably arranged on the fulcrum shaft member and used for being attached to the side face of the landing gear to limit.
4. An aircraft nose landing gear assembly and disassembly mechanism according to claim 3, wherein the left-hand arm member includes a vertical rod and a rotary shaft, the vertical rod is provided at a movable end of the telescopic cylinder, the rotary shaft is provided at a front side and a rear side of the vertical rod, the left-hand fulcrum shaft member includes a slide bar and a first positioning shaft, the slide bar is sleeved between the rotary shaft at the front side and the rear side and is slidably connected with the rotary shaft, and the first positioning shaft is provided at a right end of the slide bar.
5. The aircraft nose landing gear assembly and disassembly mechanism of claim 4, wherein the right side arm member includes a Z-shaped arm having a top end connected to the movable end of the telescopic action cylinder, and the right side fulcrum shaft member includes a second positioning shaft rotatably connected to a bottom end of the Z-shaped arm.
6. The aircraft nose landing gear assembly and disassembly mechanism of claim 5, wherein the telescopic actuating cylinder on the left side is provided on a left side wall of the mounting body.
7. The aircraft nose landing gear assembly and disassembly mechanism of claim 6, wherein the stop comprises a nut threadably coupled to the first and second locating shafts, respectively.
8. The aircraft nose landing gear assembly and disassembly mechanism according to claim 7, wherein the pulling assembly comprises a speed reducer, a reel and a pulley assembly, wherein the speed reducer and the pulley assembly are both mounted on the top of the mounting vehicle body, the reel is arranged on an output shaft of the speed reducer, a handle for driving the speed reducer to rotate is arranged on one side of the speed reducer, a steel cable is arranged on the outer side of the reel, and the steel cable is in sliding connection with the pulley assembly.
9. The aircraft nose landing gear assembly and disassembly mechanism of claim 8, wherein the engagement member includes a shackle, one end of which is connected to the cable.
10. The aircraft nose landing gear assembly and disassembly mechanism of claim 9, wherein the pulley assembly comprises a base, a movable frame and a pulley body, the movable frame is rotatably connected to the inner side of the base, the pulley body is rotatably connected to the inner side of the movable frame, and the steel cable is slidably connected to the pulley body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322325828.1U CN220616186U (en) | 2023-08-29 | 2023-08-29 | Dismounting mechanism for nose landing gear of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322325828.1U CN220616186U (en) | 2023-08-29 | 2023-08-29 | Dismounting mechanism for nose landing gear of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220616186U true CN220616186U (en) | 2024-03-19 |
Family
ID=90214009
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322325828.1U Active CN220616186U (en) | 2023-08-29 | 2023-08-29 | Dismounting mechanism for nose landing gear of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220616186U (en) |
-
2023
- 2023-08-29 CN CN202322325828.1U patent/CN220616186U/en active Active
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