CN210149548U - Undercarriage with oil gas buffering type longitudinal buffeting vibration damper - Google Patents
Undercarriage with oil gas buffering type longitudinal buffeting vibration damper Download PDFInfo
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- CN210149548U CN210149548U CN201920038818.0U CN201920038818U CN210149548U CN 210149548 U CN210149548 U CN 210149548U CN 201920038818 U CN201920038818 U CN 201920038818U CN 210149548 U CN210149548 U CN 210149548U
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- 230000003139 buffering effect Effects 0.000 title claims abstract description 10
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- 230000000670 limiting effect Effects 0.000 claims description 20
- 238000007789 sealing Methods 0.000 claims description 12
- 238000007667 floating Methods 0.000 claims description 10
- 230000003068 static effect Effects 0.000 claims description 5
- 230000009467 reduction Effects 0.000 claims description 2
- 238000013016 damping Methods 0.000 abstract description 12
- 230000008569 process Effects 0.000 abstract description 9
- 230000002829 reductive effect Effects 0.000 abstract description 8
- 230000007246 mechanism Effects 0.000 abstract description 4
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- 238000006073 displacement reaction Methods 0.000 description 3
- 238000011160 research Methods 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 230000000979 retarding effect Effects 0.000 description 2
- 230000002441 reversible effect Effects 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
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- 230000021715 photosynthesis, light harvesting Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
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- 239000013585 weight reducing agent Substances 0.000 description 1
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Abstract
The utility model discloses an undercarriage with vertical buffeting vibration damper of oil gas buffering formula adopts resistance vaulting pole under the oil gas formula buffer replacement main undercarriage course vaulting pole to increase one set of resistance vaulting pole mechanism between main undercarriage urceolus and course vaulting pole, slow down main undercarriage longitudinal vibration phenomenon with this. The added course stay bar can bear the course torque of the landing gear strut, and the elasticity and the damping characteristics of the oil-gas type buffer are utilized, so that the vibration energy transmitted by the ground and the brake device in the braking and sliding process of the landing gear can be quickly absorbed, the vibration force is reduced, and the dynamic stability of the landing gear system is improved.
Description
Technical Field
The utility model relates to an aircraft undercarriage vertically buffeting field, concretely relates to undercarriage with oil gas buffering formula vertically buffeting vibration damper.
Background
The phenomenon of longitudinal buffeting of the aircraft landing gear is caused by the fact that the braking torque of the wheels is changed due to the operation of an antiskid braking system, so that the rotating speed of the wheels is periodically changed, and the longitudinal shaking of the landing gear is caused. The brake device is usually mounted on the wheels of the main landing gear of the airplane, so that the brake buffeting phenomenon mostly occurs on the main landing gear. With the use of modern aircraft landing gear high-strength steel and weight reduction design requirements, the flexibility problem of the landing gear and the vibration problem caused by the flexible problem are increasingly prominent, the phenomenon of brake buffeting of the landing gear is caused by the models of military aircraft and unmanned aerial vehicles in China, the unfavorable vibration is reduced as much as possible through a vibration damping device and a structural design, and the design method is particularly important in the design process of the landing gear.
The research on the aspect of brake buffeting is less at home and abroad, and the available literature mainly aims at researching the buffeting mechanism, the landing gear structure and the influence of the change of brake control parameters on buffeting. For the method research of reducing the landing Gear buffeting phenomenon, document 1(Gualdi S, morandii M, Ghiringhelli G l, anti-ski-solid Induced aircraft driving Gear stability [ J ]. Aerospace Science and Technology, 2008,12(8):627 637.) researches the adjustment of the braking system control parameters without extracting the damping scheme from the landing Gear structure design. Document 2 (wuhuawei, chente, huchunkia, etc.. resonance solution caused by aircraft brake [ J ] aviation precision manufacturing technology, 2012,48(2): 50-53) describes solutions to the buffeting of the landing gear in a general form, and mentions that vibration and impact during use are reduced by using vibration-proof rubber pads or the like when mounting each part of the landing gear and the brake device, but no specific design scheme is given. At present, the design aspect of the buffeting damping device of the landing gear is still rarely researched at home and abroad.
In order to solve the problem of buffeting of the undercarriage, which often occurs in practical use, the lower resistance stay bar of the main undercarriage course stay bar of the airplane is replaced by a set of oil-gas buffer type vibration damping device, longitudinal buffeting energy can be effectively absorbed through the elasticity and the damping characteristics of an oil-gas buffer, the phenomenon of forward and backward vibration of the undercarriage in the braking process of the airplane is reduced, the resonance problem of a braking device is avoided, and the service lives of the braking device and the undercarriage are prolonged. And the added course stay bar between the buffering vibration damper and the landing gear strut limits the longitudinal displacement freedom degree of the landing gear, and improves the stability of the landing gear structure.
Disclosure of Invention
The purpose of the invention is as follows: the utility model discloses to the main undercarriage vertical buffeting phenomenon of aircraft ground brake race in-process, adopt oil gas formula buffer replacement main undercarriage course vaulting pole under the drag stay pole to increase one set of drag stay mechanism between main undercarriage urceolus and course vaulting pole, slow down main undercarriage longitudinal vibration phenomenon with this.
The undercarriage with the oil-gas buffering type longitudinal buffeting vibration reduction device comprises a main undercarriage and airplane wheels, wherein the top of the main undercarriage is fixedly installed with an airplane body, and the airplane wheels are installed at the movable tail end of the main undercarriage through bearings; the device also comprises an upper resistance stay bar, a course stay bar and an oil-gas type buffer;
the top end of the upper resistance support rod is arranged on the machine body, and the lower end of the upper resistance support rod is respectively hinged with a course support rod and an oil-gas type buffer; the course supporting rod comprises a first course supporting rod and a second course supporting rod; one end of the first course supporting rod is hinged with the upper resistance supporting rod, the other end of the first course supporting rod is hinged with one end of the second course supporting rod, and a locking device is arranged at the hinged position of the first course supporting rod and the second course supporting rod; the other end of the second course supporting rod is hinged to the upper part of the main landing gear;
the lower end of the oil-gas type buffer is hinged to the lower part of the main landing gear and comprises a buffer outer cylinder and a buffer piston rod which is slidably installed in the buffer outer cylinder; an oil needle is fixedly arranged at the center of the top end in the outer cylinder of the buffer, a piston is arranged at the lower part in the outer cylinder of the buffer, a flow limiting hole is arranged at the center of the piston, and the diameter of the flow limiting hole is smaller than the maximum diameter of the oil needle; the piston is also provided with two oil limiting holes; a floating piston is arranged in the piston rod of the buffer, and divides the inner cavity of the piston rod of the buffer into an upper air cavity and a lower oil cavity.
The main landing gear comprises a main landing gear strut outer cylinder and a main landing gear piston rod, and the main landing gear piston rod is slidably mounted in the main landing gear strut outer cylinder; the top of the main landing gear strut outer cylinder is fixedly arranged with the body; the lower end of the main landing gear strut outer cylinder is hinged with an upper torsion arm, the lower end of a main landing gear piston rod is hinged with a lower torsion arm, and the upper torsion arm is hinged with the lower torsion arm.
And a sealing ring is arranged between the buffer piston rod and the buffer outer barrel.
And a static sealing ring is also arranged in the outer barrel of the buffer and is tightly attached to the sealing ring.
The utility model has the advantages that:
(1) the added course stay bar between the buffering vibration damper and the landing gear strut limits the freedom degree of the longitudinal displacement of the landing gear, and can effectively improve the dynamic stability of the landing gear system;
(2) the low-frequency longitudinal vibration energy of the landing gear during braking can be effectively absorbed and dissipated, and the serious longitudinal buffeting phenomenon of the landing gear during ground sliding of the airplane is solved;
(3) the anti-buffeting device can greatly reduce vibration amplitude and vibration load, and solves the problems of the buffeting aggravation of bumping during riding, damage of components and shortened service life.
Drawings
FIG. 1 is a schematic structural view of a landing gear with an oil-gas buffering type longitudinal buffeting vibration damping device;
FIG. 2 is a schematic diagram of an oil and gas type buffer;
FIG. 3 is a sectional view of an oil-gas type damper;
FIG. 4 is a schematic view of the piston mounted to the damper outer cylinder.
Number designation in the figures: 1. the main landing gear strut outer cylinder, 2, an upper torsion arm, 3, a lower torsion arm, 4, an upper resistance stay, 5, a first course stay, 6, a second course stay, A, an oil-gas type buffer, 7, a main landing gear piston rod, 8, a tire, 9, a hub, 10, a buffer outer cylinder, 11, a piston, 12, a floating piston, 13, a sealing ring, 14, an oil needle, 15, a nut, 16, a static sealing ring, 17, a buffer piston rod, 18, a flow limiting hole, 19, an oil limiting hole, 20 and an inflation hole.
Detailed Description
The invention will be further elucidated with reference to the drawings and the specific embodiments.
FIG. 1 is a schematic structural view of a landing gear with an oil-gas buffering type longitudinal buffeting vibration damping device. As shown in fig. 1, the landing gear with the oil-gas buffer type longitudinal buffeting vibration damping device of the utility model comprises a main landing gear, a wheel, an upper resistance stay bar 4, a course stay bar and an oil-gas buffer A; the main landing gear comprises a main landing gear strut outer cylinder 1 and a main landing gear piston rod 7, and the main landing gear piston rod 7 is slidably mounted in the main landing gear strut outer cylinder 1 and can move in the main landing gear strut outer cylinder 1; the top of the main landing gear strut outer cylinder 1 is fixedly installed with the body. A wheel is mounted on the end of the main landing gear piston rod 7 through a bearing, and the wheel comprises a hub 9 and a tire 8 arranged on the hub 9. An upper torsion arm 2 is hinged to the lower end of the main landing gear strut outer cylinder 1, a lower torsion arm 3 is hinged to the lower end of a main landing gear piston rod 7, and the upper torsion arm 2 is hinged to the lower torsion arm 3;
the top end of the upper resistance support rod 4 is arranged on the machine body, and the lower end of the upper resistance support rod is respectively hinged with a course support rod and an oil-gas type buffer A; the course supporting rods comprise a first course supporting rod 5 and a second course supporting rod 6; one end of the first course supporting rod 5 is hinged with the upper resistance supporting rod 4, the other end of the first course supporting rod 5 is hinged with one end of the second course supporting rod 6, a locking device is arranged at the hinged position of the first course supporting rod 5 and the second course supporting rod 6 and used for folding and unfolding, when landing and running are carried out, the first course supporting rod 5 and the second course supporting rod 6 are locked by the locking device to limit the degree of freedom and bear course loads, and after being locked, the locking device is opened and used for folding and unfolding when the undercarriage is folded. In the present invention, the locking device may adopt a locking device that can achieve the purpose of locking in the prior art. The other end of the second course supporting rod 6 is hinged to the middle position of the main landing gear strut outer cylinder 1; the lower end of the oil-gas type buffer A is hinged to the lower end position of the main landing gear strut outer cylinder 1 and comprises a buffer outer cylinder 10 and a buffer piston rod 17 which is slidably installed in the buffer outer cylinder 10; an oil needle 14 is installed at the center of the top end in the buffer outer cylinder 10 through a nut 15, a piston 11 is installed at the lower position in the buffer outer cylinder 10, a flow limiting hole 18 is formed in the center of the piston 11, and the diameter of the flow limiting hole 18 is smaller than the maximum diameter of the oil needle 14. Two oil limiting holes 19 are also provided in the piston 11.
A sealing ring 13 is arranged between the buffer piston rod 17 and the buffer outer cylinder 10, and is mainly used for preventing dust from entering the buffer; the static sealing ring 16 is arranged in the buffer outer cylinder 10 and is tightly attached to the sealing ring 13, and mainly plays a role in preventing oil leakage.
The buffer piston rod 17 is internally provided with a floating piston 12, the floating piston 12 divides the inner chamber of the buffer piston rod 17 into an upper air cavity and a lower oil cavity, and the floating piston 12 prevents gas from being mixed into oil due to repeated actuation. The lower end of the buffer piston rod 17 is also provided with an inflation hole 20.
The working principle of the utility model is as follows:
(a) the aircraft slides on the ground, an upper resistance support rod 4 and an oil-gas type buffer A on a main landing gear, a first course support rod 5 and a second course support rod 6 jointly form a course support rod of a main landing gear system, and the first course support rod 5 and the second course support rod 6 are in a horizontal locking state in the whole ground sliding process and are used for supporting a course load transmitted by the whole ground; the axial force transmitted to the two ends of the oil-gas type buffer A enables the buffer piston rod 17 and the buffer outer cylinder 10 to do compression and stretching movement, and kinetic energy is converted into heat energy to be dissipated through compression of gas and flowing of oil inside the buffer outer cylinder, so that the axial force is offset; the upper drag brace 4 and the oil-gas type buffer A are used for reducing longitudinal buffeting caused by ground running.
(b) When the airplane buffles, the main undercarriage shakes forwards and backwards, force transmitted to the heading support rod of the undercarriage is distributed at two ends of the upper resistance support rod 4 and the oil-gas type buffer A, force acting at two ends of the oil-gas type buffer A can enable the buffer piston rod 17 to compress towards the buffer outer cylinder 10, due to the action of the oil needle 14 and the piston 12, the floating piston 12 can be jacked open, the volume in the oil chamber is changed, oil in the buffer outer cylinder 10 is pressed to flow to an upper air cavity of the buffer piston rod 17 through the oil limiting hole 19 in the piston 11, when the oil passes through the oil limiting hole, a large retarding effect can be formed due to the small oil limiting hole, and kinetic energy in the whole process is converted into heat energy to be dissipated; meanwhile, the gas in the piston rod 17 of the buffer is compressed, the internal pressure rises to store energy, the volume of the oil chamber is increased, the pressure is reduced, the oil flows into the oil chamber from the air chamber through the flow limiting hole 18 on the piston 11, the area of the oil limiting hole on the piston 11 is large, and the retarding effect is small. When the two ends of the oil-gas type buffer A are pulled, the whole process is opposite, the floating piston 12 can block the flow limiting hole 18 due to the action of pressure, oil can only flow from the oil limiting holes 19 on the two sides of the piston 11, a large blocking effect is formed, large damping force is generated, the compression and stretching process ensures that the kinetic energy in the whole process is converted into the dissipation function of heat energy, and therefore the longitudinal buffeting phenomenon of the undercarriage is reduced.
The utility model discloses to the main undercarriage vertical buffeting phenomenon of aircraft ground brake race in-process, adopt oil gas formula buffer replacement main undercarriage course vaulting pole under the drag stay pole to increase one set of drag stay mechanism between main undercarriage urceolus and course vaulting pole, slow down main undercarriage longitudinal vibration phenomenon with this. The added course stay bar can bear the course torque of the landing gear strut, and the elasticity and the damping characteristics of the oil-gas type buffer are utilized, so that the vibration energy transmitted by the ground and the brake device in the braking and sliding process of the landing gear can be quickly absorbed, the vibration force is reduced, and the dynamic stability of the landing gear system is improved. The utility model discloses an oil gas formula buffer, when aircraft ground brake race, ground load transmits the power on the course vaulting pole and makes the buffer inner tube compress, and at this moment, fluid in the oil chamber passes through the limit oil hole on the piston and flows to the air chamber, when fluid passes through the limit oil hole, because the effect of oil needle for the limit oil hole is more and more littleer, thereby the retardation that forms can be bigger and bigger, and gas in the air chamber is compressed simultaneously, and interior pressure risees the savings energy. During reverse stroke, oil flows back to the oil chamber from the air chamber, the floating piston plugs the oil limiting hole in the piston, and the oil can only flow through two very small oil limiting holes, so that large damping force is generated, and continuous reciprocation of the forward stroke and the reverse stroke ensures energy dissipation in the whole process, so that the influence of vibration displacement and load caused by buffeting of the landing gear on the structure is reduced, the ground running stability of the airplane is improved, and the flight safety is ensured.
The above detailed description describes the preferred embodiments of the present invention, but the present invention is not limited to the details of the above embodiments, and the technical concept of the present invention can be implemented with various equivalent transformations (such as quantity, shape, position, etc.), which all belong to the protection of the present invention.
Claims (4)
1. The undercarriage with the oil-gas buffering type longitudinal buffeting vibration reduction device comprises a main undercarriage and airplane wheels, wherein the top of the main undercarriage is fixedly installed with an airplane body, and the airplane wheels are installed at the movable tail end of the main undercarriage through bearings; the method is characterized in that: the device also comprises an upper resistance stay bar (4), a course stay bar and an oil-gas type buffer (A);
the top end of the upper resistance support rod (4) is arranged on the machine body, and the lower end of the upper resistance support rod is respectively hinged with a course support rod and an oil-gas type buffer (A); the course supporting rod comprises a first course supporting rod (5) and a second course supporting rod (6); one end of the first course supporting rod (5) is hinged with the upper resistance supporting rod (4), the other end of the first course supporting rod is hinged with one end of the second course supporting rod (6), and a locking device is arranged at the hinged position of the first course supporting rod (5) and the second course supporting rod (6); the other end of the second course supporting rod (6) is hinged to the upper position of the main landing gear;
the lower end of the oil-gas type buffer (A) is hinged to the lower part of the main landing gear and comprises a buffer outer cylinder (10) and a buffer piston rod (17) which is slidably installed in the buffer outer cylinder (10); an oil needle (14) is fixedly installed at the center of the top end in the buffer outer cylinder (10), a piston (11) is installed at the lower position in the buffer outer cylinder (10), a flow limiting hole (18) is formed in the center of the piston (11), and the diameter of the flow limiting hole (18) is smaller than the maximum diameter of the oil needle (14); two oil limiting holes (19) are also formed in the piston (11); a floating piston (12) is arranged in the buffer piston rod (17), and the floating piston (12) divides the inner cavity of the buffer piston rod (17) into an upper air cavity and a lower oil cavity.
2. A landing gear according to claim 1, wherein: the main landing gear comprises a main landing gear strut outer cylinder (1) and a main landing gear piston rod (7), and the main landing gear piston rod (7) is slidably mounted in the main landing gear strut outer cylinder (1); the top of the main landing gear strut outer cylinder (1) is fixedly arranged with the body; the lower end of the main landing gear strut outer cylinder (1) is hinged with an upper torsion arm (2), the lower end of the main landing gear piston rod (7) is hinged with a lower torsion arm (3), and the upper torsion arm (2) is hinged with the lower torsion arm (3).
3. A landing gear according to claim 1, wherein: and a sealing ring (13) is arranged between the buffer piston rod (17) and the buffer outer cylinder (10).
4. A landing gear according to claim 3, wherein: and a static sealing ring (16) is further installed in the buffer outer cylinder (10), and the static sealing ring (16) is tightly attached to the sealing ring (13).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920038818.0U CN210149548U (en) | 2019-01-10 | 2019-01-10 | Undercarriage with oil gas buffering type longitudinal buffeting vibration damper |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920038818.0U CN210149548U (en) | 2019-01-10 | 2019-01-10 | Undercarriage with oil gas buffering type longitudinal buffeting vibration damper |
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| CN210149548U true CN210149548U (en) | 2020-03-17 |
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| CN201920038818.0U Withdrawn - After Issue CN210149548U (en) | 2019-01-10 | 2019-01-10 | Undercarriage with oil gas buffering type longitudinal buffeting vibration damper |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109747816A (en) * | 2019-01-10 | 2019-05-14 | 南京航空航天大学 | A kind of undercarriage for longitudinally buffeting vibration absorber with oil gas buffer-type |
| CN111536189A (en) * | 2020-04-22 | 2020-08-14 | 南京航空航天大学 | Oil gas and expanding combined type crash-resistant buffer |
| CN111677809A (en) * | 2020-06-11 | 2020-09-18 | 南京航空航天大学 | Oil-gas separation type variable oil hole combined crash-resistant buffer |
| CN112498666A (en) * | 2020-12-07 | 2021-03-16 | 南京航空航天大学 | Vertical undercarriage of unmanned aerial vehicle |
-
2019
- 2019-01-10 CN CN201920038818.0U patent/CN210149548U/en not_active Withdrawn - After Issue
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109747816A (en) * | 2019-01-10 | 2019-05-14 | 南京航空航天大学 | A kind of undercarriage for longitudinally buffeting vibration absorber with oil gas buffer-type |
| CN109747816B (en) * | 2019-01-10 | 2024-04-12 | 南京航空航天大学 | Undercarriage with oil-gas buffer type longitudinal buffeting vibration damper |
| CN111536189A (en) * | 2020-04-22 | 2020-08-14 | 南京航空航天大学 | Oil gas and expanding combined type crash-resistant buffer |
| CN111536189B (en) * | 2020-04-22 | 2022-04-22 | 南京航空航天大学 | Oil gas and expanding combined type crash-resistant buffer |
| CN111677809A (en) * | 2020-06-11 | 2020-09-18 | 南京航空航天大学 | Oil-gas separation type variable oil hole combined crash-resistant buffer |
| CN112498666A (en) * | 2020-12-07 | 2021-03-16 | 南京航空航天大学 | Vertical undercarriage of unmanned aerial vehicle |
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