CN117382876A - Landing gear shimmy damper and aircraft - Google Patents
Landing gear shimmy damper and aircraft Download PDFInfo
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- CN117382876A CN117382876A CN202311384288.2A CN202311384288A CN117382876A CN 117382876 A CN117382876 A CN 117382876A CN 202311384288 A CN202311384288 A CN 202311384288A CN 117382876 A CN117382876 A CN 117382876A
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- landing gear
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- cylinder barrel
- oil
- groove
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- 238000013016 damping Methods 0.000 claims description 53
- 230000007246 mechanism Effects 0.000 claims description 37
- 230000001105 regulatory effect Effects 0.000 claims description 28
- 238000005452 bending Methods 0.000 claims description 15
- 238000007789 sealing Methods 0.000 claims description 6
- 239000000725 suspension Substances 0.000 claims 2
- 239000003638 chemical reducing agent Substances 0.000 abstract description 6
- 230000009467 reduction Effects 0.000 abstract description 3
- 239000007788 liquid Substances 0.000 description 14
- 238000000034 method Methods 0.000 description 7
- 230000008569 process Effects 0.000 description 7
- 239000012530 fluid Substances 0.000 description 6
- 230000001603 reducing effect Effects 0.000 description 6
- 239000006096 absorbing agent Substances 0.000 description 4
- 230000003139 buffering effect Effects 0.000 description 3
- 230000006835 compression Effects 0.000 description 3
- 238000007906 compression Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000010355 oscillation Effects 0.000 description 2
- 238000001816 cooling Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/50—Steerable undercarriages; Shimmy-damping
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/50—Steerable undercarriages; Shimmy-damping
- B64C25/505—Shimmy damping
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fluid-Damping Devices (AREA)
Abstract
The invention relates to the technical field of aircraft swing reduction, and provides a landing gear swing reducer and an aircraft.
Description
Technical Field
The invention relates to the technical field of aircraft swing reduction, in particular to a landing gear swing reducer and an aircraft.
Background
The damper is mounted on the nose landing gear of the aircraft, is a damping structure arranged for preventing the front wheel from shimmy, does not limit the rotation of the front wheel, only reduces the swinging speed, absorbs the impact energy generated by swinging and prevents shimmy.
At present, a piston type shimmy damper is generally used on a small aircraft, the piston type shimmy damper comprises a cylinder barrel, a piston and a piston rod, oil is filled in the cylinder barrel, the piston is slidably arranged in the cylinder barrel, a damping hole is formed in the piston, the piston rod is hinged to a landing gear, the landing gear swings to drive the piston rod to reciprocate, the piston rod drives the piston to reciprocate in the cylinder barrel, the reciprocating sliding of the piston pushes the oil in the cylinder barrel to reciprocate through the damping hole, and liquid damping is generated, so that impact energy generated by front wheel swing is absorbed, and shimmy is prevented.
However, when the front wheel swings, the piston in the pendulum absorber slides fast due to high-frequency oscillation, and great friction damping is generated when oil flows through the damping hole, so that the temperature of the oil in the cylinder barrel is increased, the volume of the oil expands, the pressure in the cylinder barrel is increased sharply, and the pendulum reducing effect of the pendulum absorber is affected.
Disclosure of Invention
The invention provides a landing gear shimmy damper and an airplane, which are used for solving the problems of high temperature and high pressure of oil in a cylinder barrel in the working process of the existing shimmy damper.
A first aspect of the invention provides a landing gear shimmy damper comprising:
the first cylinder barrel is filled with oil;
the piston column is slidably arranged in the first cylinder barrel, damping holes are formed in the piston column, and oil at two ends of the piston column is communicated through the damping holes;
the rocker arm is hinged with the piston column;
the oil pressure adjusting mechanism is communicated with the damping hole and can be switched between a first state and a second state;
and when the rocker arm drives the piston column to reciprocate in the first cylinder barrel, the oil in the first cylinder barrel enables the oil pressure regulating mechanism to be switched to the first state so as to release pressure.
According to the landing gear shimmy damper provided by the invention, the two ends of the piston column are respectively provided with the first groove and the second groove, and the first groove and the second groove are communicated through the damping hole.
According to the landing gear shimmy damper provided by the invention, the oil pressure adjusting mechanism comprises:
a second cylinder;
the piston is slidably arranged in the second cylinder barrel, the piston divides the second cylinder barrel into a first cavity and a second cavity, and the first cavity is communicated with the damping hole;
the elastic piece is arranged in the second cavity and used for providing acting force for switching the oil pressure regulating mechanism from the first state to the second state.
According to the landing gear shimmy damper provided by the invention, the side wall of the first cylinder barrel is provided with the first notch, and the first notch is arranged corresponding to the damping hole.
According to the landing gear shimmy damper provided by the invention, the first cavity is communicated with the damping hole through the bending joint, and the bending joint is arranged at the first notch.
According to the landing gear shimmy damper provided by the invention, the axial center of the piston column is provided with the third groove, the rocker arm is provided with the rotatable roller, and the roller is arranged in the third groove.
According to the landing gear shimmy damper provided by the invention, the outer side wall of the first cylinder barrel is also provided with the second notch, and the rocker arm is arranged at the second notch.
According to the landing gear shimmy damper provided by the invention, the sealing structure and the guiding structure are arranged between the inner wall of the first cylinder barrel and the outer wall of the piston column.
According to the landing gear shimmy damper provided by the invention, the outer side wall of the first cylinder barrel is provided with the hanging lugs, and the hanging lugs are used for being connected with the fixed support of the landing gear system.
A second aspect of the invention provides an aircraft comprising a landing gear shimmy damper as described above.
The beneficial effects are that: the landing gear shimmy damper comprises a first cylinder barrel, a piston column, a rocker arm and an oil pressure regulating mechanism, wherein the piston column is slidably arranged in the first cylinder barrel, a damping hole is formed in the piston column, two axial ends of the piston column are communicated with each other through the damping hole, the oil pressure regulating mechanism is communicated with the damping hole, the oil pressure regulating mechanism can be switched between a first state and a second state by additionally arranging the oil pressure regulating mechanism, when the temperature of oil in the first cylinder barrel is increased, the oil pressure regulating mechanism is switched to the first state by the oil when the pressure is increased, the oil pressure regulating mechanism provides an oil buffer space for the oil, so that the oil in the first cylinder barrel can be decompressed and cooled, and the shimmy damper is ensured.
Further, the aircraft provided by the invention has the landing gear shimmy damper, so that the aircraft also has various advantages.
Drawings
In order to more clearly illustrate the invention or the technical solutions of the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the invention, and other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a three-dimensional block diagram of a landing gear shimmy damper provided by the present invention;
FIG. 2 is a three-dimensional block diagram of another angle of the landing gear shimmy damper provided by the present invention;
FIG. 3 is a front view of the landing gear shimmy damper provided by the present invention;
FIG. 4 is a cross-sectional view of FIG. 3;
FIG. 5 is a partial block diagram of a rocker arm;
FIG. 6 is a cross-sectional view of a landing gear shimmy damper provided by the present invention;
FIG. 7 is a schematic illustration of a swing arm swing process in a landing gear shimmy damper provided by the present invention;
fig. 8 is another schematic view of the swing process of the swing arm in the landing gear shimmy damper provided by the present invention.
Reference numerals:
1. a first cylinder; 11. a damping hole; 12. a first notch; 13. a second notch; 14. a third notch;
2. a piston column; 21. a first groove; 22. a second groove; 23. a third groove;
3. a rocker arm; 31. a roller;
4. an oil pressure adjusting mechanism; 41. a second cylinder; 42. a piston; 43. a spring;
5. bending the joint;
6. hanging lugs;
7. a U-shaped bracket;
8. a first seal ring;
9. a first guide ring.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings, and it is apparent that the described embodiments are some embodiments of the present invention, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the description of the present invention, it should be understood that the directions or positional relationships indicated by the terms "upper", "lower", "horizontal", "inner", "outer", etc., are based on the directions or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present invention, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.
The present invention will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present invention more apparent.
The damper is mounted on the nose landing gear of the aircraft, is a damping structure arranged for preventing the front wheel from shimmy, does not limit the rotation of the front wheel, only reduces the swinging speed, absorbs the impact energy generated by swinging and prevents shimmy.
At present, a piston type shimmy damper is generally used on a small aircraft, the piston type shimmy damper comprises a cylinder barrel, a piston and a piston rod, oil is filled in the cylinder barrel, the piston is slidably arranged in the cylinder barrel, a damping hole is formed in the piston, the piston rod is hinged to a landing gear, the landing gear swings to drive the piston rod to reciprocate, the piston rod drives the piston to reciprocate in the cylinder barrel, the reciprocating sliding of the piston pushes the oil in the cylinder barrel to reciprocate through the damping hole, and liquid damping is generated, so that impact energy generated by front wheel swing is absorbed, and shimmy is prevented.
However, when the front wheel swings, the piston in the pendulum absorber slides fast due to high-frequency oscillation, and great friction damping is generated when oil flows through the damping hole, so that the temperature of the oil in the cylinder barrel is increased, the volume of the oil expands, the pressure in the cylinder barrel is increased sharply, and the pendulum reducing effect of the pendulum absorber is affected.
According to the embodiment of the invention, the oil pressure regulating mechanism is additionally arranged, so that the oil pressure regulating mechanism can be switched between the first state and the second state, when the temperature of the oil in the first cylinder barrel is increased and the pressure is increased, the oil pressure regulating mechanism is switched to the first state, the oil of the oil pressure regulating mechanism provides an oil buffer space, the oil in the first cylinder barrel can be decompressed and cooled, and the swing reducing effect of the swing reducer is ensured.
The landing gear shimmy damper and aircraft of the present invention are described below in conjunction with fig. 1-8.
As shown in fig. 1 to 4, the landing gear shimmy damper provided by the embodiment of the invention comprises a first cylinder barrel 1, a piston column 2, a rocker arm 3 and an oil pressure regulating mechanism 4, wherein oil is filled in the first cylinder barrel 1, the piston column 2 is slidably arranged in the first cylinder barrel 1, the piston column 2 can reciprocate linearly along the axial direction of the first cylinder barrel 1, a plurality of damping holes 11 are arranged in the piston column 2, the damping holes 11 are uniformly distributed in the piston column 2, the damping holes 11 are arranged along the axial direction of the piston column 2, the damping holes 11 axially penetrate through the piston column 2, the two axial ends of the piston column 2 are communicated through the damping holes 11, and as the oil is filled in the first cylinder barrel 1 and the piston column 2 is slidably arranged in the first cylinder barrel 1, the oil at the two ends of the piston column 2 is communicated through the damping holes 11, the first end of the rocker arm 3 is hinged with the piston column 2, and the second end of the rocker arm 3 is connected with an aircraft landing gear.
The oil pressure regulating mechanism 4 is communicated with the damping hole 11, the oil pressure regulating mechanism 4 can be switched between a first state and a second state, specifically, the oil pressure regulating mechanism 4 can be arranged as a liquid storage tank, high-pressure liquid is stored in the liquid storage tank, the liquid storage tank is respectively communicated with the damping hole 11 through a first pipeline and a second pipeline, a first one-way valve is arranged on the first pipeline and is communicated with the liquid storage tank through the damping hole 11, an electromagnetic valve is arranged on the second pipeline, when the first one-way valve is communicated, the oil pressure regulating mechanism 4 is in the first state, and when the electromagnetic valve is opened, the oil pressure regulating mechanism 4 is in the second state.
When the nose landing gear of the aircraft is subjected to shimmy or tends to shimmy, the rocker arm 3 is driven to perform high-frequency small-amplitude reciprocating rotary motion, the rocker arm 3 drives the piston column 2 to perform high-frequency small-amplitude reciprocating linear motion in the first cylinder barrel 1, namely, in the process that the rocker arm 3 drives the piston column 2 to slide back and forth in the first cylinder barrel 1, oil in the first cylinder barrel 1 flows through the damping hole 11 in a reciprocating manner to generate liquid damping, along with the shimmy of high frequency, the temperature of the oil in the first cylinder barrel 1 rises, the pressure increases, the volume of the oil expands, the oil in the first cylinder barrel 1 enters a first pipeline to enable a first one-way valve to be conducted, the oil enters a liquid storage tank, the liquid storage tank provides an oil buffering space for the oil in the first cylinder barrel 1 and can perform pressure relief and temperature reduction on the oil in the first cylinder barrel 1, otherwise, after the piston column 2 stops sliding in the first cylinder barrel 1, the first one-way valve is closed by itself, the electromagnetic valve in the second pipeline is opened, and the oil in the liquid storage tank returns to the first cylinder barrel 1 to wait for the next shimmy work.
In the embodiment of the invention, the oil pressure regulating mechanism 4 is additionally arranged, so that the oil pressure regulating mechanism 4 can be switched between the first state and the second state, when the temperature of the oil in the first cylinder barrel 1 is increased, and the pressure is increased, the oil enables the oil pressure regulating mechanism 4 to be switched to the first state, the oil pressure regulating mechanism 4 provides an oil buffer space for the oil, the oil in the first cylinder barrel 1 can be decompressed and cooled, and the swing reducing effect of the swing reducer is ensured.
In order to further improve the effect of liquid damping generated by the piston rod 2, in some embodiments of the present invention, the two ends of the piston rod 2 are respectively provided with the first groove 21 and the second groove 22, the first groove 21 and the second groove 22 are communicated through the damping hole 11, and by respectively providing the two ends of the piston rod 2 with the first groove 21 and the second groove 22, the space volume between the two ends of the piston rod 2 and the inner wall of the first cylinder 1 is increased, when the piston rod 2 makes reciprocating rectilinear motion in the first cylinder 1, the volume of oil flowing through the damping hole 11 in the piston rod 2 is larger, the pressure difference generated by the damping hole 11 is larger, and a larger damping force can be provided, thereby further improving the vibration reducing effect of the vibration reducer.
In order to further improve the practicality and space utilization of the damper, the structure of the oil pressure adjusting mechanism 4 is simplified in some embodiments of the present invention, in this embodiment, the oil pressure adjusting mechanism 4 specifically includes a second cylinder 41, a piston 42, and an elastic member, where the piston 42 is slidably disposed in the second cylinder 41, the piston 42 divides the second cylinder 41 into a first cavity and a second cavity, the first cavity is communicated with the damping hole 11, the elastic member is disposed in the second cavity to provide an acting force for switching the oil pressure adjusting mechanism 4 from the first state to the second state, the elastic member may be a compression spring or a spring, etc., in this embodiment, the elastic member is disposed as a spring 43, and the spring 43 is disposed between an inner wall of the second cavity and the piston 42.
In the above-mentioned scheme, when the spring 43 is compressed, the oil pressure adjusting mechanism 4 is in the first state, and when the spring 43 rebounds, the oil pressure adjusting mechanism 4 is in the second state, and the specific process is:
when the nose landing gear of the aircraft is subjected to shimmy or tends to shimmy, the rocker arm 3 is driven to perform high-frequency small-amplitude reciprocating rotary motion, the rocker arm 3 drives the piston rod 2 to perform high-frequency small-amplitude reciprocating linear motion in the first cylinder barrel 1, namely, in the process that the rocker arm 3 drives the piston rod 2 to slide back and forth in the first cylinder barrel 1, the oil in the first cylinder barrel 1 flows through the damping hole 11 in a reciprocating manner to generate liquid damping, along with the shimmy of high frequency, the temperature of the oil in the first cylinder barrel 1 rises, the pressure increases, the volume of the oil expands, the oil in the first cylinder barrel 1 enters a first cavity, the oil compression piston 42 pushes the spring 43 to be compressed, the oil pressure regulating mechanism 4 is in a first state, the volume of the first cavity increases to provide an oil buffering space for the oil, the oil in the first cylinder barrel 1 can be decompressed and cooled, otherwise, after the piston rod 2 stops sliding in the first cylinder barrel 1, the pressure and the temperature of the oil in the first cylinder barrel 1 decline, the elastic restoring force of the spring 43 pushes the piston 42 to return to the first cylinder barrel 1, and the first cylinder barrel 1 waits for the next working time.
In this embodiment, through setting up second cylinder 41, piston 42 and spring 43, make fluid pressure adjustment mechanism 4 can switch between first state and second state, when the fluid temperature risees in first cylinder 1, and when pressure was increased, fluid promoted piston 42 compression spring 43, and first cavity volume increases, provides fluid buffering space for fluid, can carry out pressure release and cooling to the fluid in the first cylinder 1, has guaranteed the pendulum-reducing effect of pendulum-reducing device.
In other embodiments, the outer wall of the first cylinder 1 is provided with a U-shaped bracket 7, and the second cylinder 41 is provided on the U-shaped bracket 7 and is slidable relative to the U-shaped bracket 7, and the U-shaped bracket 7 provides sliding support for the second cylinder 41.
As shown in fig. 3 and fig. 4, in some embodiments of the present invention, a first notch 12 is provided on a side wall of the first cylinder 1, the first notch 12 is provided corresponding to the damping hole 11, and is provided at an axial center position of the first cylinder 1, the first notch 12 is provided along an axial direction of the first cylinder 1, the first cavity is communicated with the damping hole 11 through a bending joint 5, one end of the bending joint 5 is communicated with the first cavity, the other end of the bending joint 5 is communicated with the damping hole 11 provided on the piston post 2, the bending joint 5 follows the piston post 2 to reciprocate synchronously, the bending joint 5 is provided at the first notch 12, the bending joint 5 is bent at 90 °, the bending joint 5 is communicated through the 90 ° bending joint 5, the second cylinder 41 can be axially parallel to the first cylinder 1, a space occupied by the second cylinder 41 is reduced, the first notch 12 is provided along the axial direction of the first cylinder 1, a guide space for the bending joint 5 to reciprocate linearly is provided, on one hand, the piston post 2 can be prevented from rotating in the first cylinder 1, and on the other hand, the bending joint 5 can be ensured to reciprocate synchronously.
As shown in fig. 1, 5 and 6, in order to further ensure the hinging motion between the rocker arm 3 and the piston post 2, in some embodiments of the present invention, a third groove 23 is formed at the axial center position of the piston post 2, the third groove 23 is perpendicular to the central axis of the piston post 2, a rotatable roller 31 is disposed on the first end of the rocker arm 3, the roller 31 is disposed in the third groove 23, and the roller 31 is in high-pair fit connection with the third groove 23.
The roller 31 is rotationally connected with the rocker arm 3, specifically, a connecting hole is formed in the first end of the rocker arm 3, shafts at two ends of the roller 31 are inserted into the connecting hole, and cotter pins are arranged on the shafts at two ends of the roller 31 to axially limit the roller 31, so that connection between the roller 31 and the rocker arm 3 is guaranteed, an aircraft landing gear is arranged to swing, the rocker arm 3 is driven to swing, the rocker arm 3 carries out high pair motion in the third groove 23 through the roller 31 to drive the piston column 2 to slide reciprocally in the first cylinder barrel 1 to generate liquid damping, and the swing reducing effect of the landing gear swing reducer is achieved.
As shown in fig. 1 and fig. 6, in some embodiments of the present invention, a second notch 13 is further formed on the outer side wall of the first cylinder barrel 1, the rocker arm 3 is disposed at the second notch 13, the second notch 13 is disposed at the axial center position of the first cylinder barrel 1, and the second notch 13 is disposed along the axial direction of the first cylinder barrel 1, so as to provide a guiding space for the rocker arm 3 and the piston post 2 to reciprocate in a linear manner, so that on one hand, the piston post 2 can be prevented from rotating in the first cylinder barrel 1, and on the other hand, the rocker arm 3 can be ensured to drive the piston post 2 to reciprocate synchronously.
As shown in fig. 2 and 6, in other embodiments, a third notch 14 is further provided on the outer sidewall of the first cylinder barrel 1, the third notch 14 is disposed corresponding to the second notch 13, the third notch 14 is disposed at an axial center position of the first cylinder barrel 1, the third notch 14 is also disposed along an axial direction of the first cylinder barrel 1, a screw is disposed on the piston post 2 at a position corresponding to the third notch 14, the screw is embedded in the third notch 14, and can slide reciprocally with respect to the third notch 14, and cooperation of the third notch 14 and the screw provides guidance for reciprocal movement of the piston post 2, so as to avoid rotation of the piston post 2 in the first cylinder barrel 1.
As shown in fig. 4, in some embodiments of the present invention, a sealing structure and a guiding structure are disposed between an inner wall of the first cylinder 1 and an outer wall of the piston post 2, specifically, a first sealing ring 8 and a first guiding ring 9 are disposed circumferentially between the inner wall of the first cylinder 1 and the outer wall of the piston post 2, the first sealing ring 8 and the first guiding ring 9 are disposed at intervals, and the first sealing ring 8 is disposed between inner walls of two sides of the first slot 12, the second slot 13, or the third slot 14 in the circumferential direction and the inner wall of the first cylinder 1, so as to ensure that the piston post 2 does not leak oil during the sliding process of the first cylinder 1.
In some embodiments of the invention, as shown in fig. 3, the outer side wall of the first cylinder tube 1 is provided with a hanging lug 6, and the hanging lug 6 is used for being connected with a fixed bracket on the landing gear system, and can be directly connected with the fixed bracket on the landing gear system by a bolt connection or the like.
When the rocker arm 3 swings left as shown in fig. 7, the piston rod 2 is driven to slide left, and when the rocker arm 3 swings right as shown in fig. 8, the piston rod 2 is driven to slide right.
In another aspect, an embodiment of the present invention further provides an aircraft, including the landing gear shimmy damper provided in any one of the embodiments above. The development of the beneficial effects of the aircraft in the embodiments of the present invention is substantially similar to that of the landing gear shimmy damper described above, and therefore will not be described in detail herein.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and are not limiting; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (10)
1. A landing gear shimmy damper, comprising:
the oil filling device comprises a first cylinder barrel (1), wherein the first cylinder barrel (1) is filled with oil;
the piston column (2) is slidably arranged in the first cylinder barrel (1), a damping hole (11) is formed in the piston column (2), and oil at two ends of the piston column (2) is communicated through the damping hole (11);
the rocker arm (3) is hinged with the piston column (2);
the oil pressure regulating mechanism (4) is communicated with the damping hole (11), and the oil pressure regulating mechanism (4) can be switched between a first state and a second state;
when the rocker arm (3) drives the piston column (2) to reciprocate in the first cylinder barrel (1), oil in the first cylinder barrel (1) enables the oil pressure regulating mechanism (4) to be switched to the first state so as to release pressure.
2. Landing gear shimmy damper according to claim 1, characterized in that the piston rod (2) is provided with a first groove (21) and a second groove (22) at both ends, respectively, the first groove (21) and the second groove (22) being in communication through the damping hole (11).
3. The landing gear shimmy damper according to claim 2, characterized in that the oil pressure regulating mechanism (4) comprises:
a second cylinder (41);
the piston (42) is slidably arranged in the second cylinder barrel (41), the piston (42) divides the second cylinder barrel (41) into a first cavity and a second cavity, and the first cavity is communicated with the damping hole (11);
the elastic piece is arranged in the second cavity to provide acting force for switching the oil pressure regulating mechanism (4) from the first state to the second state.
4. A landing gear shimmy damper according to claim 3, characterized in that a first groove (12) is provided in the side wall of the first cylinder (1), the first groove (12) being arranged in correspondence of the damping hole (11).
5. Landing gear shimmy damper according to claim 4, characterized in that the first cavity is in communication with the damping orifice (11) through a bending joint (5), the bending joint (5) being arranged at the first slot (12).
6. Landing gear shimmy damper according to any of claims 1-5, characterized in that a third groove (23) is provided in the axial center of the piston post (2), a rotatable roller (31) is provided on the rocker arm (3), and the roller (31) is provided in the third groove (23).
7. Landing gear shimmy damper according to claim 6, characterized in that the outer side wall of the first cylinder (1) is further provided with a second groove (13), and the rocker arm (3) is arranged at the second groove (13).
8. Landing gear shimmy damper according to claim 1, characterized in that a sealing structure and a guiding structure are provided between the inner wall of the first cylinder (1) and the outer wall of the piston column (2).
9. Landing gear shimmy damper according to claim 1 or 8, characterized in that the outer side wall of the first cylinder (1) is provided with a suspension loop (6), which suspension loop (6) is intended to be connected with a fixed bracket of a landing gear system.
10. An aircraft comprising a landing gear shimmy damper according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311384288.2A CN117382876A (en) | 2023-10-24 | 2023-10-24 | Landing gear shimmy damper and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311384288.2A CN117382876A (en) | 2023-10-24 | 2023-10-24 | Landing gear shimmy damper and aircraft |
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| Publication Number | Publication Date |
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| CN117382876A true CN117382876A (en) | 2024-01-12 |
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|---|---|---|---|
| CN202311384288.2A Pending CN117382876A (en) | 2023-10-24 | 2023-10-24 | Landing gear shimmy damper and aircraft |
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