CN113799973B - A high damping cylinder seat connection structure - Google Patents
A high damping cylinder seat connection structure Download PDFInfo
- Publication number
- CN113799973B CN113799973B CN202111076296.1A CN202111076296A CN113799973B CN 113799973 B CN113799973 B CN 113799973B CN 202111076296 A CN202111076296 A CN 202111076296A CN 113799973 B CN113799973 B CN 113799973B
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- Prior art keywords
- damper
- mounting seat
- high damping
- rubber
- seat
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
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- 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
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/10—Suppression of vibrations in rotating systems by making use of members moving with the system
- F16F15/12—Suppression of vibrations in rotating systems by making use of members moving with the system using elastic members or friction-damping members, e.g. between a rotating shaft and a gyratory mass mounted thereon
- F16F15/121—Suppression of vibrations in rotating systems by making use of members moving with the system using elastic members or friction-damping members, e.g. between a rotating shaft and a gyratory mass mounted thereon using springs as elastic members, e.g. metallic springs
- F16F15/124—Elastomeric springs
- F16F15/126—Elastomeric springs consisting of at least one annular element surrounding the axis of rotation
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Vibration Dampers (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention discloses a high damping cylinder seat connecting structure which comprises a rubber damper, a damper mounting seat and a screw, wherein the damper mounting seat is L-shaped, one surface of the damper mounting seat is provided with a through hole which is symmetrical along a central line, the screw penetrates through the through hole to fix the damper mounting seat on a connecting rod type cylinder seat of an aircraft, the other surface of the damper mounting seat is parallel to the connecting rod hole wall of the connecting rod type cylinder seat, the center of the surface is provided with the through hole, one end of a rubber damper cylinder body is arranged and positioned in a gap between the damper mounting seat and the connecting rod hole wall of the connecting rod type cylinder seat through the through hole, one end of the rubber damper cylinder body extends out of the damper mounting seat to be about 3-4 mm, and the rubber damper is in direct contact with a landing gear torque arm and is in interference fit. According to the invention, through the movement resistance provided, a part of energy transmitted to the torsion arm of the landing gear is dissipated, so that the braking moment is slowly and stably transmitted to the torsion arm of the landing gear, and the shaking phenomenon of the landing gear is eliminated and slowed down.
Description
Technical Field
The invention belongs to the technical field of aviation landing gear systems, and particularly relates to a cylinder seat connecting structure.
Background
The landing gear system is a complex, multiple degree of freedom dynamic system that produces a vibratory response during braking of the braked wheels. With the increasing demand for aircraft design, vibration problems generated by braking systems during normal operation are becoming more and more of a concern. In the working process of the brake wheel, the occurrence of vibration phenomenon can cause discomfort to personnel on the aircraft. If the vibration phenomenon is serious, the amplitude rises sharply, harmful vibration can be generated, the brake wheel and the landing gear are damaged when the vibration phenomenon is light, and the person is destroyed when the vibration phenomenon is heavy. Vibration problems have been present in aircraft braking since the advent of aircraft. There are three general types of avoiding vibration, namely, weakening or eliminating the excitation source, increasing the damping of the system, reducing the transmission of vibration and enhancing the anti-vibration performance of the structure.
The landing gear torque arm is generally made of alloy structural steel, the connecting rod type cylinder seat is generally made of aluminum alloy, a general connecting piece between the cylinder seat and the landing gear torque arm is mainly made of lugs or connecting rod bushings, the lugs are generally made of cast bronze, and the connecting rod bushings are generally made of cast bronze or alloy steel. The cooperation between undercarriage torque arm and the cylinder seat is in the non-static operational environment of high load, and the connecting rod formula cylinder seat needs to transmit the braking moment of tens of thousands of meters to undercarriage torque arm, and in this process, lug and connecting rod bush can play wear-resisting, protect the effect of cylinder seat. As shown in fig. 2, the connection structure between the cylinder seat and the landing gear in the prior art still belongs to a metal-to-metal connection structure, and the connection mode between the cylinder seat and the landing gear torque arm belongs to a rigid connection. In addition, the damper is not independently designed in the structures, so that the damping at the joint is very small, and vibration is easy to generate.
Disclosure of Invention
The invention provides a high damping cylinder seat connecting structure, which aims to overcome the defects of the prior art and comprises a rubber damper, a damper mounting seat and a screw, wherein the damper mounting seat is L-shaped, one surface of the damper mounting seat is provided with through holes symmetrical along a central line, the screw penetrates through the through holes to fix the damper mounting seat on a connecting rod type cylinder seat of an airplane, the other surface of the damper mounting seat is parallel to the connecting rod hole wall of the connecting rod type cylinder seat, the center of the surface is provided with the through holes, one end of a rubber damper cylinder body passes through the through holes to mount and position the rubber damper in a gap between the damper mounting seat and the connecting rod hole wall of the connecting rod type cylinder seat, one end of the rubber damper cylinder body extends out of the damper mounting seat to be about 3-4 mm, and the rubber damper is in direct contact with a landing gear torsion arm and is in interference fit. According to the invention, through the movement resistance provided, a part of energy transmitted to the torsion arm of the landing gear is dissipated, so that the braking moment is slowly and stably transmitted to the torsion arm of the landing gear, and the shaking phenomenon of the landing gear is eliminated and slowed down.
The technical scheme adopted for solving the technical problems is as follows:
a high damping cylinder seat connecting structure comprises a rubber damper, a damper mounting seat and a screw;
the rubber damper is of a T-shaped structure and consists of a flat plate and a column body;
The damper mounting seat is L-shaped, N through holes which are symmetrical along the central line are formed in one surface of the L shape, and the screw penetrates through the through holes to fix the damper mounting seat on the connecting rod type cylinder seat of the airplane;
The other side of the L-shaped damper mounting seat is parallel to the wall of the connecting rod type cylinder seat, a through hole is arranged in the center of the other side of the L-shaped damper mounting seat, and the cylinder of the rubber damper passes through the through hole to directly contact with the torsion arm of the landing gear and is in interference fit with the torsion arm of the landing gear; the flat plate of the rubber damper is clamped in a gap between the damper mounting seat and the connecting rod hole wall of the connecting rod type cylinder seat;
Preferably, the high damping cylinder seat connecting structure is provided with two sets which are symmetrically arranged on the connecting rod type cylinder seat.
Preferably, the rubber damper is made of a high damping rubber material.
Preferably, the high damping rubber material is hard rubber.
Preferably, the flat plate of the rubber damper is square.
Preferably, the cylinder of the rubber damper is a cylinder or a quadrangular prism.
Preferably, the flat plate of the rubber damper has a size of 35mmX35mm and a thickness of 3mm.
Preferably, the length of the cylinder of the rubber damper, which extends out of the damper mounting seat after passing through the through hole of the damper mounting seat, is 3-4 mm.
Preferably, the n=2.
Preferably, the through hole arranged at the center of the other side of the L-shaped damper mounting seat is round or square.
The beneficial effects of the invention are as follows:
According to the invention, the rubber damper is arranged between the connecting rod type cylinder seat and the torsion arm of the landing gear, and in the braking process, the rubber can absorb part of vibration energy due to the internal friction of the high damping rubber macromolecule chain segments and the synergistic effect between the chain segments. Meanwhile, the high damping cylinder seat connecting structure provides movement resistance, and can dissipate part of energy transferred to the landing gear torque arm, so that braking torque is slowly and stably transferred to the landing gear torque arm, and landing gear shaking phenomenon is eliminated and slowed down.
Drawings
FIG. 1 is a schematic view of a high damping cylinder block connection structure according to the present invention.
FIG. 2 is a schematic view of the prior art landing gear torque arm mating with the cylinder block connection.
Fig. 3 is a front view of a rubber damper structure, in which (a) indicates that the cylinder is a cylinder and (b) indicates that the cylinder is a quadrangular prism.
Fig. 4 is a left side view of the rubber damper structure.
Fig. 5 is a front view of the damper mount.
Fig. 6 is a right side view of the damper mount, in which (a) indicates that the through hole is circular and (b) indicates that the through hole is square.
The hydraulic lifting device comprises a 1-connecting rod type cylinder seat, a 2-undercarriage torque arm, a 3-lug structure in the prior art, a 4-rubber damper, a 5-damper mounting seat and a 6-screw.
Detailed Description
The invention will be further described with reference to the drawings and examples.
In order to weaken and eliminate the problem of vibration of the landing gear in the braking process of the aircraft wheel in the prior art, the invention provides a high-damping cylinder seat connecting structure.
As shown in fig. 1, a high damping cylinder block connecting structure comprises a rubber damper 4, a damper mounting seat 5 and a screw 6;
as shown in fig. 3 and 4, the rubber damper 4 has a T-shaped structure and is composed of a flat plate and a column body;
As shown in fig. 5 and 6, the damper mounting seat 5 is L-shaped, one surface of the L-shaped is provided with 2 through holes which are symmetrical along a central line, the screw 6 penetrates through the through holes to fix the damper mounting seat 5 on the connecting rod type cylinder seat 1 of the airplane, the other surface of the L-shaped of the damper mounting seat is parallel to the connecting rod hole wall of the connecting rod type cylinder seat 1, a through hole is arranged in the center position of the other surface of the L-shaped of the damper mounting seat, the column body of the rubber damper 4 penetrates through the through hole to directly contact with the landing gear torque arm 2 and is in interference fit with the landing gear torque arm 2, and the flat plate of the rubber damper 4 is clamped in a gap between the damper mounting seat 5 and the connecting rod hole wall of the connecting rod type cylinder seat 1.
Preferably, the high damping cylinder seat connecting structure is provided with two sets which are symmetrically arranged on the connecting rod type cylinder seat 1.
Preferably, the rubber damper 4 is made of a high damping rubber material.
Preferably, the high damping rubber material is hard rubber.
Preferably, the flat plate of the rubber damper 4 is square.
Preferably, the cylinder of the rubber damper 4 is a cylinder or a quadrangular prism.
Preferably, the flat plate of the rubber damper 4 has a size of 35mmX35mm and a thickness of 3mm.
Preferably, the length of the column body of the rubber damper 4 extending out of the damper mounting seat 5 after passing through the through hole of the damper mounting seat 5 is 3-4 mm.
Preferably, the n=2.
Preferably, the through hole arranged at the center of the other side of the L-shaped damper mounting seat is round or square.
The invention is used for connecting a landing gear torque arm and a connecting rod type cylinder seat, and is a high-damping vibration reduction structure. In the prior art, the landing gear torque arm is connected with the brake wheel by mechanical parts such as pins, and the connection mode belongs to rigid connection, and when the brake torque fluctuates, the landing gear torque arm is immediately affected, so that the landing gear shaking phenomenon is caused. The high damping rubber is an organic matter of a macromolecular chain, and the movement of the macromolecular chain is a relaxation process, so that the high damping rubber can absorb certain mechanical energy when being acted by external force, and has certain damping performance. By installing the rubber damper between the cylinder seat and the landing gear torque arm, the inner friction of the high damping rubber macromolecule chain segments and the synergistic effect between the chain segments in the braking process enable the rubber to absorb part of vibration energy, thereby eliminating and slowing down the landing gear shaking phenomenon.
Claims (8)
1. A high damping cylinder seat connecting structure is used for connecting a landing gear torque arm and a connecting rod type cylinder seat, is a high damping vibration reduction structure and is characterized by comprising a rubber damper, a damper mounting seat and a screw;
the rubber damper is of a T-shaped structure and consists of a flat plate and a column body;
The damper mounting seat is L-shaped, N through holes which are symmetrical along the central line are formed in one surface of the L shape, and the screw penetrates through the through holes to fix the damper mounting seat on the connecting rod type cylinder seat of the airplane;
The other side of the L-shaped damper mounting seat is parallel to the wall of the connecting rod type cylinder seat, a through hole is arranged in the center of the other side of the L-shaped damper mounting seat, and the cylinder of the rubber damper passes through the through hole to directly contact with the torsion arm of the landing gear and is in interference fit with the torsion arm of the landing gear; the flat plate of the rubber damper is clamped in a gap between the damper mounting seat and the connecting rod hole wall of the connecting rod type cylinder seat;
The high damping cylinder seat connecting structure is provided with two sets of connecting structures which are symmetrically arranged on the connecting rod type cylinder seat, and the rubber damper is made of high damping rubber materials.
2. The high damping cylinder block connecting structure according to claim 1, wherein the high damping rubber material is hard rubber.
3. The high damping cylinder block connecting structure according to claim 1, wherein the flat plate of the rubber damper is square.
4. The high damping cylinder block connecting structure according to claim 1, wherein the cylinder of the rubber damper is a cylinder or a quadrangular prism.
5. A high damping cylinder block connecting structure according to claim 1, wherein the flat plate of the rubber damper has a size of 35mmX35mm and a thickness of 3mm.
6. The high damping cylinder block connecting structure according to claim 1, wherein the length of the cylinder body of the rubber damper extending out of the damper mounting seat after passing through the through hole of the damper mounting seat is 3-4 mm.
7. A high damping cylinder block connection structure according to claim 1, wherein n=2.
8. The high damping cylinder block connecting structure according to claim 1, wherein the through hole arranged at the center of the other side of the L-shaped damper mounting base is circular or square.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111076296.1A CN113799973B (en) | 2021-09-14 | 2021-09-14 | A high damping cylinder seat connection structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111076296.1A CN113799973B (en) | 2021-09-14 | 2021-09-14 | A high damping cylinder seat connection structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113799973A CN113799973A (en) | 2021-12-17 |
| CN113799973B true CN113799973B (en) | 2025-05-06 |
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ID=78940970
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111076296.1A Active CN113799973B (en) | 2021-09-14 | 2021-09-14 | A high damping cylinder seat connection structure |
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| CN (1) | CN113799973B (en) |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN216186009U (en) * | 2021-09-14 | 2022-04-05 | 西安航空制动科技有限公司 | High damping cylinder base connecting structure |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR100729408B1 (en) * | 2006-01-13 | 2007-06-18 | 주식회사 캄코 | Housing structure connected to the vehicle power lift motor |
| US8448900B2 (en) * | 2010-03-24 | 2013-05-28 | The Boeing Company | Semi-levered landing gear and associated method |
| GB201209502D0 (en) * | 2012-05-29 | 2012-07-11 | Airbus Operations Ltd | System, kit and method for indicating the pressure in an aircraft landing gear shock absorber |
| CN204250366U (en) * | 2014-10-11 | 2015-04-08 | 中国航空工业集团公司西安飞机设计研究所 | The connecting device of a kind of undercarriage and brake gear |
| US9499261B2 (en) * | 2015-01-20 | 2016-11-22 | Goodrich Corporation | Friction-based shimmy damper for landing gear |
| CN108088732B (en) * | 2017-12-26 | 2019-10-25 | 常州朗锐东洋传动技术有限公司 | A kind of rubber nodal point three directional loads experimental rig |
| US11161599B2 (en) * | 2018-01-26 | 2021-11-02 | The Boeing Company | Landing gear strut assembly and method therefor |
| CN209441619U (en) * | 2018-12-28 | 2019-09-27 | 江西冠一通用飞机有限公司 | A kind of fixed wing aircraft undercarriage |
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- 2021-09-14 CN CN202111076296.1A patent/CN113799973B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN216186009U (en) * | 2021-09-14 | 2022-04-05 | 西安航空制动科技有限公司 | High damping cylinder base connecting structure |
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| Publication number | Publication date |
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| CN113799973A (en) | 2021-12-17 |
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