CN212667646U - Damping mechanism for aircraft landing gear - Google Patents
Damping mechanism for aircraft landing gear Download PDFInfo
- Publication number
- CN212667646U CN212667646U CN202021697852.8U CN202021697852U CN212667646U CN 212667646 U CN212667646 U CN 212667646U CN 202021697852 U CN202021697852 U CN 202021697852U CN 212667646 U CN212667646 U CN 212667646U
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- wall
- fixedly connected
- cylinder
- landing gear
- piston rod
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- 230000007246 mechanism Effects 0.000 title claims description 21
- 238000013016 damping Methods 0.000 title claims description 18
- 230000035939 shock Effects 0.000 claims description 12
- 238000010521 absorption reaction Methods 0.000 claims description 10
- 239000003921 oil Substances 0.000 abstract description 28
- 239000012530 fluid Substances 0.000 abstract description 3
- 239000010727 cylinder oil Substances 0.000 abstract description 2
- 238000003466 welding Methods 0.000 abstract 1
- 238000000034 method Methods 0.000 description 6
- 238000001125 extrusion Methods 0.000 description 5
- 230000006835 compression Effects 0.000 description 4
- 238000007906 compression Methods 0.000 description 4
- 239000007788 liquid Substances 0.000 description 4
- 230000009471 action Effects 0.000 description 2
- 230000003139 buffering effect Effects 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 230000002452 interceptive effect Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
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- Vibration Dampers (AREA)
Abstract
The utility model discloses a damper for aircraft undercarriage, the utility model discloses a damper, lifting unit and link, damper includes adjustable shelf and stand, stand top outer wall fixed connection is in adjustable shelf bottom outer wall, stand bottom outer wall fixedly connected with bottom plate, bottom plate top outer wall fixedly connected with upper shield, the first cylinder of upper shield top outer wall fixedly connected with, the welding of first cylinder outer wall is violently managed, violently manages one end outer wall fixedly connected with oil pipe, oil pipe one end outer wall fixedly connected with second cylinder, second cylinder one end outer wall fixedly connected with mount. Through setting up damper unit, wherein the gyro wheel receives the impact force, drives the center pin and contracts back, and fixed cover drives first chock plug through the connecting rod and extrudees the interior fluid of second cylinder to make this part oil pressure get into first cylinder through oil pipe, first cylinder oil pressure increase simultaneously with the volume and extrude the air storehouse air, can offset the impact force through compressed air.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle undercarriage technical field especially relates to a damper for aircraft undercarriage.
Background
Along with the more and more general of small aircraft's such as unmanned aerial vehicle application, a great deal of problem can be met to the unavoidable when new hand operation, and this kind of aircraft faces the problem of frequently taking off and land, and this has just provided higher requirement to the shock-absorbing function of undercarriage, but traditional damper generally uses the spring as the core, and the spring is relatively poor in the corrosion resisting property who faces external multiple weather environment itself, and easy corrosion consequently needs to design a neotype undercarriage damper.
Through retrieval, chinese patent publication No. CN108557060B discloses a shock-absorbing landing gear including a support, a shock-absorbing upper support, a compression spring, a shock-absorbing bolt, a shock-absorbing lower support, a connecting rod a, a connecting rod B and a hydraulic push rod, wherein the top of the shock-absorbing upper support is coaxially fitted and mounted on a cylindrical shaft, the shock-absorbing bolt connects the shock-absorbing upper support and the shock-absorbing lower support, and the top of the shock-absorbing bolt passes through the compression spring mounted in the shock-absorbing upper support, one end of the connecting rod a is connected to the shock-absorbing upper support, the other end of the connecting rod a is coaxially fitted with one end of the connecting rod B and also coaxially fitted with the front end of the hydraulic push rod, the rear end of the hydraulic push rod is coaxially fitted with a mounting. The above patents suffer from the following disadvantages: adopt the spring as the one-level and the second grade damper of core, but the spring need expose for a long time and in the air when unmanned aerial vehicle uses, receives easily to corrode and then reduces the life-span, influences the elasticity performance.
SUMMERY OF THE UTILITY MODEL
The utility model aims at solving the shortcoming that exists among the prior art, and the damping mechanism for aircraft undercarriage who proposes.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
a shock absorption mechanism for an aircraft landing gear comprises a shock absorption assembly, a lifting assembly and a connecting frame, wherein the shock absorption assembly comprises a movable frame and a stand column, the outer wall of the top of the stand column is fixedly connected with the outer wall of the bottom of the movable frame, the outer wall of the bottom of the stand column is fixedly connected with a bottom plate, the outer wall of the top of the bottom plate is fixedly connected with a sleeve cover, the outer wall of the top of the sleeve cover is fixedly connected with a first cylinder barrel, the outer wall of the first cylinder barrel is welded with a transverse pipe, the outer wall of one end of the transverse pipe is fixedly connected with an oil pipe, the outer wall of one end of the oil pipe is fixedly connected with a second cylinder barrel, the outer wall of one end of the second cylinder barrel is fixedly connected with a fixing frame, the number of the fixing frames is two, the outer wall of the top of, the fixed cover inner wall is connected with the center pin through the pin rod, center pin bottom outer wall fixedly connected with chassis, chassis bottom outer wall fixedly connected with crossbeam, crossbeam both sides outer wall has the gyro wheel through axle swivelling joint, center pin top outer wall has the swivel nut through threaded connection, the swivel nut inner wall has the second piston rod through threaded connection, second piston rod top outer wall fixedly connected with second chock plug, second chock plug outer wall sliding connection is in first cylinder inner wall.
As a further aspect of the present invention: the fixing frame inner wall is fixedly connected with a first plug sleeve, the outer wall of a first piston rod is connected to the inner wall of the first plug sleeve in a sliding mode, the inner wall of a sleeve cover is fixedly connected with a second plug sleeve, and the outer wall of the second piston rod is connected to the inner wall of the second plug sleeve in a sliding mode.
As a further aspect of the present invention: and vent holes are formed in the inner walls of the first plug sleeve and the second plug sleeve.
As a further aspect of the present invention: and an air bin is arranged on the outer wall of the top of the first cylinder barrel.
As a further aspect of the present invention: the outer wall of the threaded sleeve is provided with an anti-skid bulge.
As a further aspect of the present invention: lifting unit includes backing plate and motor, backing plate one side outer wall fixed connection in link one side inner wall, backing plate one side outer wall fixedly connected with mounting bracket, backing plate one side outer wall fixedly connected with track, the track cooperation is used and is had the slider, slider one side outer wall fixedly connected with movable plate, motor bottom outer wall fixed connection is in mounting bracket top outer wall, the output shaft of motor has the lead screw through the coupling joint, the lead screw outer wall has lead screw nut support through threaded connection, lead screw nut support one side outer wall fixed connection is in movable plate one side outer wall.
As a further aspect of the present invention: the outer wall of one side of the movable frame is fixedly connected to the outer wall of one side of the movable plate.
Compared with the prior art, the utility model provides a damper for undercarriage possesses following beneficial effect:
1. this damper for aircraft undercarriage, through setting up damper, wherein the gyro wheel receives the impact force, and it contracts to drive the center pin, and fluid relies on second chock plug extrusion pressure to increase in the first cylinder, and fixed cover passes through the connecting rod and drives fluid in first chock plug extrusion second cylinder to make this part oil pressure get into first cylinder through oil pipe, first cylinder oil pressure force and volume increase simultaneously and extrude the air storehouse air, can offset the impact force through compressed air.
2. This damper for aircraft landing gear, through setting up first cock cover and second cock cover and inner wall air vent, can ensure that the air smoothly passes in and out the space that second cock top outer wall and first cylinder bottom inner wall constitute and the space two that first cock one side outer wall and second cylinder one side inner wall constitute, can ensure that first piston rod and second piston rod motion are steady, it is further, the operation of first piston rod is smooth and easy, can avoid the clearance difference of the relative second cylinder inner wall of first piston rod to be stable, avoid the center pin to appear crooked.
3. This a damper for aircraft undercarriage, through setting up lifting unit, this kind of mechanism is installed inside unmanned aerial vehicle, when carrying out high altitude flight, need retrieve damping unit inside the aircraft, be used for reducing the air resistance of flight in-process, and need stretch out damping unit at the descending in-process, and provide shock-absorbing function for unmanned aerial vehicle descends, this kind of lifting unit uses the motor to drive lead screw pivoted mode and realizes that the movable plate goes up and down, under the stall state through the motor, can ensure that the lead screw is static, further can fix damping unit's position, make the impact force of descending process receipts eliminate by damping unit is inside, avoid interfering other parts of this kind of mechanism.
The part that does not relate to in the device all is the same with prior art or can adopt prior art to realize, the utility model discloses simple structure, convenient operation.
Drawings
Fig. 1 is a schematic view of the overall structure of a shock-absorbing mechanism for an aircraft landing gear according to the present invention;
fig. 2 is a schematic structural view of a shock-absorbing assembly of a shock-absorbing mechanism for an aircraft landing gear according to the present invention;
fig. 3 is a sectional view of a shock-absorbing assembly structure of a shock-absorbing mechanism for an aircraft landing gear according to the present invention;
fig. 4 is a schematic structural view of a first plug bush of a shock-absorbing mechanism for an aircraft landing gear according to the present invention;
fig. 5 is a schematic structural view of a lifting assembly of a damping mechanism for an aircraft landing gear according to the present invention.
In the figure: 1-damping component, 2-lifting component, 3-connecting frame, 101-movable frame, 102-upright column, 103-first cylinder barrel, 104-oil pipe, 105-second cylinder barrel, 106-bottom plate, 107-fixed frame, 108-first piston rod, 109-roller, 110-central shaft, 11-fixed sleeve, 112-connecting rod, 113-swivel nut, 114-air bin, 115-first plug head, 116-second plug head, 117-second piston rod, 118-first plug sleeve, 119-second plug sleeve, 201-backing plate, 202-moving plate, 203-sliding block, 204-motor and 205-screw rod.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.
A shock absorption mechanism for an aircraft landing gear comprises a shock absorption assembly 1, a lifting assembly 2 and a connecting frame 3, in order to improve the composition of shock absorption components and optimize the shock absorption effect, as shown in figures 1-5, the shock absorption assembly 1 comprises a movable frame 101 and a vertical column 102, the outer wall of the top of the vertical column 102 is fixedly connected with the outer wall of the bottom of the movable frame 101, the outer wall of the bottom of the vertical column 102 is fixedly connected with a bottom plate 106, the outer wall of the top of the bottom plate 106 is fixedly connected with a sleeve cover, the outer wall of the top of the sleeve cover is fixedly connected with a first cylinder 103, the outer wall of the first cylinder 103 is welded with a transverse pipe, the outer wall of one end of the transverse pipe is fixedly connected with an oil pipe 104, the outer wall of one end of the oil pipe 104 is fixedly connected with a second cylinder 105, the outer wall of one end of the second, the outer wall of one side of the first plug 115 is fixedly connected with a first piston rod 108, the outer wall of one end of the first piston rod 108 is rotatably connected with a connecting rod 112 through a shaft, the outer wall of one end of the connecting rod 112 is rotatably connected with a fixing sleeve 111 through a shaft, the inner wall of the fixing sleeve 111 is connected with a central shaft 110 through a pin rod, the outer wall of the bottom end of the central shaft 110 is fixedly connected with a chassis, the outer wall of the bottom of the chassis is fixedly connected with a cross beam, the outer walls of two sides of the cross beam are rotatably connected with a roller 109 through a shaft, the outer wall of the top end of the central shaft 110 is connected with a threaded sleeve 113 through threads, the inner wall of the threaded sleeve 113 is connected with; the inner wall of the fixed frame 107 is fixedly connected with a first plug sleeve 118, and the outer wall of the first piston rod 108 is connected with the inner wall of the first plug sleeve 118 in a sliding manner; the inner wall of the sleeve cover is fixedly connected with a second plug sleeve 119, and the outer wall of the second piston rod 117 is connected with the inner wall of the second plug sleeve 119 in a sliding manner; the inner walls of the first plug sleeve 118 and the second plug sleeve 119 are provided with vent holes; an air bin 114 is arranged on the outer wall of the top of the first cylinder barrel 103; the outer wall of the threaded sleeve 113 is provided with an anti-skid bulge; when the hydraulic buffer is used, the roller 109 is impacted to drive the central shaft 110 to retract, meanwhile, vibration is transmitted to the fixed sleeve 111, the fixed sleeve 111 drives the connecting rod 112 to move, the first piston rod 108 moves, the first plug head 115 moves along the inner wall of the second cylinder 105 and extrudes oil pressure in the second cylinder 105, meanwhile, the central shaft 110 is lifted upwards to drive the second piston rod 117 to move, the second plug head 116 is lifted to extrude oil in the first cylinder 103, the oil in the second cylinder 105 enters the first cylinder 103 through the oil pipe 104, the oil increases the air in the extrusion air bin 114, and buffering is realized by the action of air compression and high-pressure oil; by arranging the damping component 1, wherein the roller 109 is impacted to drive the central shaft 110 to retract, the oil in the first cylinder 103 is increased by the extrusion pressure of the second plug 116, the fixed sleeve 111 drives the first plug 115 to extrude the oil in the second cylinder 105 through the connecting rod 112, and the oil pressure enters the first cylinder 103 through the oil pipe 104, the oil pressure and the volume of the first cylinder 103 are simultaneously increased to extrude the air in the air bin 114, and the impact force can be counteracted by compressed air; meanwhile, by arranging the first plug sleeve 118, the second plug sleeve 119 and the inner wall vent hole, the first space formed by the outer wall at the top of the second plug head 116 and the inner wall at the bottom of the first cylinder 103 and the second space formed by the outer wall at one side of the first plug head 115 and the inner wall at one side of the second cylinder 105 can be ensured, the first piston rod 108 and the second piston rod 117 can be ensured to move stably, further, the first piston rod 108 can run smoothly, the difference of the moving distance of the first piston rod 108 relative to the inner wall of the second cylinder 105 can be avoided being stable, and the central shaft 110 can be prevented from being bent.
In order to realize the lifting of the shock absorption assembly 1, as shown in fig. 1 and 5, the lifting assembly 2 comprises a base plate 201 and a motor 204, the outer wall of one side of the base plate 201 is fixedly connected to the inner wall of one side of a connecting frame 3, the outer wall of one side of the base plate 201 is fixedly connected with a mounting frame, the outer wall of one side of the base plate 201 is fixedly connected with a track, the track is matched with a slide block 203, the outer wall of one side of the slide block 203 is fixedly connected with a moving plate 202, the outer wall of the bottom of the motor 204 is fixedly connected to the outer wall of the top of the mounting frame, an output shaft of the motor 204 is; the outer wall of one side of the movable frame 101 is fixedly connected to the outer wall of one side of the moving plate 202; when the device is used, the motor 204 is started to drive the moving plate 202 to lift, and simultaneously drive the movable frame 101 to lift; through setting up lifting unit 2, this kind of mechanism is installed inside unmanned aerial vehicle, when carrying out high altitude flight, need retrieve damping component 1 inside the aircraft, be used for reducing the air resistance of flight in-process, and need stretch out damping component 1 at the descending in-process, and provide shock-absorbing function for unmanned aerial vehicle descends, this kind of lifting unit 2 uses motor 204 to drive lead screw 205 pivoted mode to realize that movable plate 202 goes up and down, under the stall state through motor 204, can ensure that lead screw 205 is static, further can fix damping component 1's position, make the impact force of descending process receipts eliminate by damping component 1 is inside, avoid interfering other parts of this kind of mechanism.
The working principle is as follows: the motor 204 is started to drive the moving plate 202 to lift and drive the movable frame 101 to lift, when the unmanned aerial vehicle descends, the damping assembly 1 descends, the roller 109 is impacted to drive the central shaft 110 to retract, vibration is transmitted to the fixed sleeve 111, the fixed sleeve 111 drives the connecting rod 112 to move, so that the first piston rod 108 moves, the first plug head 115 moves along the inner wall of the second cylinder 105 and extrudes oil pressure in the second cylinder 105, meanwhile, the central shaft 110 lifts upwards to drive the second piston rod 117 to move, the second plug head 116 is lifted to extrude oil liquid in the first cylinder 103, the oil liquid in the second cylinder 105 enters the first cylinder 103 through the oil pipe 104, the oil liquid increases the air in the extrusion air bin 114, and the buffering is realized by the action of air compression and high-pressure oil liquid; when unmanned aerial vehicle steadily flies, damper assembly 1 is packed up, reduces air resistance.
The above, only be the concrete implementation of the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the utility model, the concept of which is equivalent to replace or change, should be covered within the protection scope of the present invention.
Claims (7)
1. A damping mechanism for an aircraft landing gear comprises a damping component (1), a lifting component (2) and a connecting frame (3), and is characterized in that the damping component (1) comprises a movable frame (101) and an upright post (102), the outer wall of the top of the upright post (102) is fixedly connected to the outer wall of the bottom of the movable frame (101), the outer wall of the bottom of the upright post (102) is fixedly connected with a bottom plate (106), the outer wall of the top of the bottom plate (106) is fixedly connected with a sleeve cover, the outer wall of the top of the sleeve cover is fixedly connected with a first cylinder (103), the outer wall of the first cylinder (103) is welded with a transverse pipe, the outer wall of one end of the transverse pipe is fixedly connected with an oil pipe (104), the outer wall of one end of the oil pipe (104) is fixedly connected with a second cylinder (105), the outer wall of one end of the second cylinder (105), second cylinder (105) inner wall sliding connection has first chock plug (115), first chock plug (115) one side outer wall fixedly connected with first piston rod (108), first piston rod (108) one end outer wall is connected with connecting rod (112) through the axle rotation, connecting rod (112) one end outer wall is connected with fixed cover (111) through the axle rotation, fixed cover (111) inner wall is connected with center pin (110) through the pin rod, center pin (110) bottom outer wall fixedly connected with chassis, chassis bottom outer wall fixedly connected with crossbeam, crossbeam both sides outer wall is connected with gyro wheel (109) through the axle rotation, center pin (110) top outer wall has swivel nut (113) through threaded connection, swivel nut (113) inner wall has second piston rod (117) through threaded connection, second piston rod (117) top outer wall fixedly connected with second chock plug (116), second chock plug (116) outer wall sliding connection is in first cylinder (103) inner wall.
2. A shock-absorbing mechanism for an aircraft landing gear according to claim 1, wherein a first plug sleeve (118) is fixedly connected to the inner wall of the fixing frame (107), the outer wall of the first piston rod (108) is slidably connected to the inner wall of the first plug sleeve (118), a second plug sleeve (119) is fixedly connected to the inner wall of the cover, and the outer wall of the second piston rod (117) is slidably connected to the inner wall of the second plug sleeve (119).
3. A shock absorbing mechanism for an aircraft landing gear according to claim 2, characterised in that the inner walls of the first (118) and second (119) sleeves are provided with vent holes.
4. A shock absorbing mechanism for an aircraft landing gear according to claim 1, wherein the outer wall of the top of the first cylinder (103) is provided with an air chamber (114).
5. A shock-absorbing mechanism for an aircraft landing gear according to claim 1, characterised in that the outer wall of the threaded sleeve (113) is provided with anti-slip projections.
6. The shock absorption mechanism for the aircraft landing gear according to claim 1, wherein the lifting assembly (2) comprises a base plate (201) and a motor (204), the outer wall of one side of the base plate (201) is fixedly connected to the inner wall of one side of the connecting frame (3), the outer wall of one side of the base plate (201) is fixedly connected with a mounting frame, the outer wall of one side of the base plate (201) is fixedly connected with a track, the track is matched with a sliding block (203), the outer wall of one side of the sliding block (203) is fixedly connected with a moving plate (202), the outer wall of the bottom of the motor (204) is fixedly connected to the outer wall of the top of the mounting frame, an output shaft of the motor (204) is connected with a lead screw (205) through a coupler, the outer wall of the.
7. A shock-absorbing mechanism for an aircraft landing gear according to claim 6, wherein the outer wall of the movable frame (101) is fixedly connected to the outer wall of the movable plate (202).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021697852.8U CN212667646U (en) | 2020-08-14 | 2020-08-14 | Damping mechanism for aircraft landing gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021697852.8U CN212667646U (en) | 2020-08-14 | 2020-08-14 | Damping mechanism for aircraft landing gear |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212667646U true CN212667646U (en) | 2021-03-09 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021697852.8U Expired - Fee Related CN212667646U (en) | 2020-08-14 | 2020-08-14 | Damping mechanism for aircraft landing gear |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212667646U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113859519A (en) * | 2021-10-18 | 2021-12-31 | 中国电信股份有限公司 | Undercarriage and unmanned aerial vehicle |
-
2020
- 2020-08-14 CN CN202021697852.8U patent/CN212667646U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113859519A (en) * | 2021-10-18 | 2021-12-31 | 中国电信股份有限公司 | Undercarriage and unmanned aerial vehicle |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20210309 |
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| CF01 | Termination of patent right due to non-payment of annual fee |