CN107344614B - Undercarriage buffer - Google Patents
Undercarriage buffer Download PDFInfo
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- CN107344614B CN107344614B CN201710588934.5A CN201710588934A CN107344614B CN 107344614 B CN107344614 B CN 107344614B CN 201710588934 A CN201710588934 A CN 201710588934A CN 107344614 B CN107344614 B CN 107344614B
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- connecting block
- fixedly connected
- buffer
- cylinder
- buffer cylinder
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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
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/62—Spring shock-absorbers; Springs
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Dampers (AREA)
Abstract
The invention discloses an aircraft landing gear buffering device which comprises a bearing support column, wherein the top end of the bearing support column is fixedly connected with a supporting frame, the right end of the supporting frame is fixedly connected with a retraction action cylinder, the bottom end of the bearing support column is fixedly connected with a first buffering cylinder, the inner wall of the first buffering cylinder is movably connected with a first connecting block, the lower surface of the first connecting block is fixedly connected with a connecting column, and the bottom end of the connecting column penetrates through the lower surface of the first buffering cylinder and is spliced with a second buffering cylinder. The first buffer cylinder, the second buffer cylinder, the first connecting block, the second connecting block, the connecting column and the buffer spring are arranged to be matched with each other, so that the shock absorber is effectively protected, the problem that the shock absorber is easily damaged when the undercarriage is suddenly stressed due to overlarge stress is solved, the gravity of the airplane is buffered by the buffer spring through the matching of the limiting rod and the limiting plate, and the problem that the undercarriage buffer device is stressed due to overlarge deformation is solved through the arrangement of the limiting rod and the limiting plate.
Description
Technical Field
The invention relates to the technical field of aerospace equipment, in particular to an undercarriage buffer device.
Background
With the development of society, the economic level of people is continuously improved, an airplane becomes a common tool for people to go out, the airplane is loved by people with unique rapidness and convenience, the safety of the airplane is extremely high at present, in order to ensure the normal flying and landing of the airplane, routine overhaul and maintenance are carried out after each flight is finished, the undercarriage is a device which is used for supporting the gravity of the airplane when the airplane is parked on the ground, slides and takes off and lands, and bears corresponding loads, any artificial aircraft has the process of taking off the ground and lifting off, besides a rocket missile which is used once and a spacecraft which does not need to be recovered, most of the aircrafts have the landing or recovery stage, and for the airplane, the device for realizing the function of taking off and landing (the taking off and landing process of the airplane) together is mainly the undercarriage.
The existing aircraft landing gear generally performs shock absorption through a shock absorber when landing and sliding, and the shock absorber is easy to damage when the pressure of the aircraft which is received in the moment of landing is increased.
Disclosure of Invention
Technical problem to be solved
Aiming at the defects of the prior art, the invention provides a buffering device for an aircraft landing gear, which solves the problem that a shock absorber on the aircraft landing gear is easy to damage.
(II) technical scheme
In order to achieve the purpose, the invention provides the following technical scheme: an aircraft landing gear buffering device comprises a bearing support column, wherein the top end of the bearing support column is fixedly connected with a supporting frame, the right end of the supporting frame is fixedly connected with a retraction action cylinder, the bottom end of the bearing support column is fixedly connected with a first buffer cylinder, the inner wall of the first buffer cylinder is movably connected with a first connecting block, the lower surface of the first connecting block is fixedly connected with a connecting column, the bottom end of the connecting column penetrates through the lower surface of the first buffer cylinder and is spliced with a second buffer cylinder, the tail end of the connecting column is fixedly connected with a second connecting block, the second connecting block is movably connected with the inner wall of the second buffer cylinder, buffering springs are fixedly connected to the upper surface of the first connecting block and the middle position of the lower surface of the second connecting block, the other ends of the two buffering springs are respectively and fixedly connected to the top of an inner cavity of the first buffer cylinder, the utility model discloses a damping device, including first connecting block, second connecting block, first buffer cylinder, first connecting block, the upper surface both sides of first connecting block and the equal fixedly connected with gag lever post in lower surface both sides of second connecting block, the equal fixedly connected with limiting plate in one end that first connecting block and second connecting block were kept away from to the gag lever post, the lower fixed surface of second buffer cylinder is connected with the shock attenuation post, through fixed lantern ring fixedly connected with bumper shock absorber between shock attenuation post and the load pillar, the bottom fixedly connected with gyro wheel support of shock attenuation post, the inboard of gyro wheel support is through connecting pivot fixedly connected with gyro.
Preferably, the limiting rods and the limiting plates on the two sides of the buffer spring are arranged in bilateral symmetry with respect to the buffer spring.
Preferably, the damper is located at a left side of the first cushion cylinder.
Preferably, centers of the first buffer cylinder and the second buffer cylinder are on the same vertical line.
Preferably, the first connecting block and the second connecting block are both square, the length and the width of the first connecting block are both smaller than the length and the width of the inner side of the first buffer cylinder by 2-3 mm, and the length and the width of the second connecting block are both smaller than the length and the width of the inner side of the second buffer cylinder by 2-3 mm.
Preferably, the connecting column is movably connected with the bottom of the first buffer cylinder and the top of the second buffer cylinder.
(III) advantageous effects
The invention provides an aircraft landing gear buffer device. The method has the following beneficial effects:
(1) according to the invention, the first buffer cylinder, the second buffer cylinder, the first connecting block, the second connecting block, the connecting column and the buffer spring are matched with each other, when the airplane slips, runs and lands, the gravity of the airplane is transmitted to the buffer device through the force bearing supporting column, and after the buffer spring of the buffer device absorbs part of the shock force, the shock absorber is damped through the shock absorber, so that the shock absorber is effectively protected, and the problem that the shock absorber is easily damaged when the airplane undercarriage is suddenly stressed too much is solved.
(2) According to the invention, the limiting rod and the limiting plate are matched with each other, the gravity of the airplane is buffered by the buffer spring, and the limiting rod and the limiting plate are arranged, so that when the buffer spring is extruded, the top and the bottom of the limiting plate are respectively contacted with the top of the inner cavity of the first buffer cylinder and the bottom of the inner cavity of the second buffer cylinder, the shock absorber performs shock absorption again, the deformation caused by the overlarge stress of the buffer spring is prevented, meanwhile, the buffer spring absorbs the shock force to the maximum extent, the use of the landing gear shock absorber is protected, and the problem that the landing gear buffer device of the airplane deforms due to the overlarge stress is.
Drawings
FIG. 1 is a schematic structural view of the present invention;
fig. 2 is an enlarged view of a portion a in fig. 1.
In the figure: the roller comprises a force bearing support 1, a support frame 2, a retracting and releasing action cylinder 3, a first buffer cylinder 4, a first connecting block 5, a buffer spring 6, a limiting rod 7, a limiting plate 8, a connecting column 9, a second buffer cylinder 10, a second connecting block 11, a fixed lantern ring 13, a shock absorber 14, a roller support 15 and a roller body 16.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1-2, the present invention provides a technical solution: a buffering device for an aircraft landing gear comprises a bearing support column 1, wherein the top end of the bearing support column 1 is fixedly connected with a support frame 2, the right end of the support frame 2 is fixedly connected with a retraction action cylinder 3, the bottom end of the bearing support column 1 is fixedly connected with a first buffer cylinder 4, the inner wall of the first buffer cylinder 4 is movably connected with a first connecting block 5, the lower surface of the first connecting block 5 is fixedly connected with a connecting column 9, the bottom end of the connecting column 9 penetrates through the lower surface of the first buffer cylinder 4 and is spliced with a second buffer cylinder 10, the tail end of the connecting column 9 is fixedly connected with a second connecting block 11, the second connecting block 11 is movably connected with the inner wall of the second buffer cylinder 10, the connecting column 9 is movably connected with the bottom of the first buffer cylinder 4 and the top of the second buffer cylinder 10, the connecting column 9 is conveniently and fixedly connected with the first connecting block 5 and the second connecting block 11, the centers of the first buffer cylinder, the aircraft gravity stable transmission is convenient, the first connecting block 5 and the second connecting block 11 are both square bodies, the length and the width of the first connecting block 5 are both less than the length and the width of the inner side of the first buffer cylinder 4 by 2-3 mm, the length and the width of the second connecting block 11 are both less than the length and the width of the inner side of the second buffer cylinder 10 by 2-3 mm, the first connecting block 5 moves in the first buffer cylinder 4 and is matched with the buffer spring 6 for shock absorption, the second connecting block 11 moves in the second buffer cylinder 10 and is matched with the buffer spring 6 for shock absorption, the buffer springs 6 are fixedly connected at the middle positions of the upper surface of the first connecting block 5 and the lower surface of the second connecting block 11, the other ends of the two buffer springs 6 are respectively and fixedly connected at the top of the inner cavity of the first buffer cylinder 4 and the bottom of the inner cavity of the second buffer cylinder 10, the aircraft gravity is transmitted to the buffer device through the bearing support column 1, and the buffer spring 6 of the, then the shock is absorbed by the shock absorber 14, the shock absorber 14 is effectively protected, both sides of the upper surface of the first connecting block 5 and both sides of the lower surface of the second connecting block 11 are fixedly connected with limiting rods 7, one ends of the limiting rods 7, far away from the first connecting block 5 and the second connecting block 11, are fixedly connected with limiting plates 8, the limiting rods 7 and the limiting plates 8 on both sides of the buffer spring 6 are symmetrically arranged on the left and right sides of the buffer spring 6, the limiting rods 7 and the limiting plates 8 are symmetrically arranged to facilitate the pressure balance of the first buffer cylinder 4 and the second buffer cylinder 10, the limiting rods 7 and the limiting plates 8 are arranged, when the buffer spring 6 is extruded, the top and the bottom of the limiting plates 8 are respectively contacted with the top of the inner cavity of the first buffer cylinder 4 and the bottom of the inner cavity of the second buffer cylinder 10, the shock absorber 14 absorbs the shock again, the shock of the buffer spring 6 is prevented from being deformed due to overla, the use of protection undercarriage bumper shock absorber 14, the lower fixed surface of second cushion cylinder 10 is connected with shock absorber 12, through fixed lantern ring 13 fixedly connected with bumper shock absorber 14 between shock absorber 12 and the load pillar 1, and bumper shock absorber 14 is located the left side of first cushion cylinder 4, and the bottom fixedly connected with gyro wheel support 15 of shock absorber 12, the inboard of gyro wheel support 15 is through connecting pivot fixedly connected with gyro wheel body 16.
During the use, receive the extrusion when buffer spring 6, the top and the bottom of limiting plate 8 contact the inner chamber top of first buffer cylinder 4 and the 10 inner chamber bottoms of second buffer cylinder respectively after, shock absorber 14 carries out the shock attenuation again, prevent that buffer spring 6 atress is too big to lead to warping, buffer spring 6 furthest's absorption shock absorber power simultaneously, the use of protection undercarriage shock absorber 14, buffer spring 6 of buffer absorbs the partial seismic force after, the shock attenuation of shock absorber 14 again, effectual protection shock absorber 14.
In conclusion, the first buffer cylinder 4, the second buffer cylinder 10, the first connecting block 5, the second connecting block 11, the connecting column 9 and the buffer spring 6 are arranged to be matched with each other, when an airplane runs, lands and lands, the gravity of the airplane is transmitted to the buffer device through the force bearing strut 1, after the buffer spring 6 of the buffer device absorbs part of the shock force, the shock absorber 14 is effectively protected, the problem that the shock absorber 14 is easily damaged when the airplane landing gear is suddenly stressed too much is solved, through the arrangement of the limiting rod 7 and the limiting plate 8 which are matched with each other, the gravity of the airplane is buffered through the buffer spring 6, the limiting rod 7 and the limiting plate 8 are arranged, when the buffer spring 6 is extruded, the top and the bottom of the limiting plate 8 are respectively contacted with the top of the inner cavity of the first buffer cylinder 4 and the bottom of the inner cavity of the second buffer cylinder 10, the shock absorber 14 absorbs the shock again, and the buffer spring 6 is prevented from being deformed due, meanwhile, the buffer spring 6 absorbs the shock force to the maximum extent, the landing gear shock absorber 14 is protected, and the problem that the buffering device of the landing gear of the airplane is deformed due to overlarge stress is solved.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising a reference structure" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (1)
1. The utility model provides an aircraft landing gear buffer, includes load strut (1), its characterized in that: the top end of the bearing support column (1) is fixedly connected with a support frame (2), the right end of the support frame (2) is fixedly connected with a retraction action cylinder (3), the bottom end of the bearing support column (1) is fixedly connected with a first buffer cylinder (4), the inner wall of the first buffer cylinder (4) is movably connected with a first connecting block (5), the lower surface of the first connecting block (5) is fixedly connected with a connecting column (9), the bottom end of the connecting column (9) penetrates through the lower surface of the first buffer cylinder (4) and is inserted with a second buffer cylinder (10), the tail end of the connecting column (9) is fixedly connected with a second connecting block (11), the second connecting block (11) is movably connected with the inner wall of the second buffer cylinder (10), and the middle positions of the upper surface of the first connecting block (5) and the lower surface of the second connecting block (11) are both fixedly connected with a buffer spring (6), the damping device comprises two damping springs (6), wherein the other ends of the two damping springs (6) are fixedly connected to the top of an inner cavity of a first damping cylinder (4) and the bottom of an inner cavity of a second damping cylinder (10) respectively, both sides of the upper surface of a first connecting block (5) and both sides of the lower surface of a second connecting block (11) are fixedly connected with limiting rods (7), one ends, far away from the first connecting block (5) and the second connecting block (11), of the limiting rods (7) are fixedly connected with limiting plates (8), the lower surface of the second damping cylinder (10) is fixedly connected with damping columns (12), dampers (14) are fixedly connected between the damping columns (12) and a bearing strut (1) through fixing lantern rings (13), the bottom ends of the damping columns (12) are fixedly connected with roller supports (15), and the inner sides of the roller supports (15) are fixedly connected with roller bodies (16) through connecting; the limiting rods (7) and the limiting plates (8) on the two sides of the buffer spring (6) are arranged in bilateral symmetry around the buffer spring (6); the shock absorber (14) is positioned on the left side of the first buffer cylinder (4); the centers of the first buffer cylinder (4) and the second buffer cylinder (10) are on the same vertical line; the first connecting block (5) and the second connecting block (11) are both square, the length and the width of the first connecting block (5) are both smaller than the length and the width of the inner side of the first buffer cylinder (4) by 2-3 mm, and the length and the width of the second connecting block (11) are both smaller than the length and the width of the inner side of the second buffer cylinder (10) by 2-3 mm; the connecting column (9) is movably connected with the bottom of the first buffer cylinder (4) and the top of the second buffer cylinder (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710588934.5A CN107344614B (en) | 2017-07-19 | 2017-07-19 | Undercarriage buffer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710588934.5A CN107344614B (en) | 2017-07-19 | 2017-07-19 | Undercarriage buffer |
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| Publication Number | Publication Date |
|---|---|
| CN107344614A CN107344614A (en) | 2017-11-14 |
| CN107344614B true CN107344614B (en) | 2020-08-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710588934.5A Active CN107344614B (en) | 2017-07-19 | 2017-07-19 | Undercarriage buffer |
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| CN (1) | CN107344614B (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107985565A (en) * | 2017-12-07 | 2018-05-04 | 佛山市神风航空科技有限公司 | The unmanned plane undercarriage of taking photo by plane of dual shock absorption |
| CN107972853A (en) * | 2017-12-07 | 2018-05-01 | 佛山市神风航空科技有限公司 | Aerial photography aircraft undercarriage two level shock-damping structure |
| CN108438212A (en) * | 2018-01-18 | 2018-08-24 | 倪惠芳 | A kind of UAV Landing auxiliary device |
| CN108860607A (en) * | 2018-06-19 | 2018-11-23 | 智飞智能装备科技东台有限公司 | It is a kind of from steady wind resistance unmanned plane |
| CN110217382A (en) * | 2019-06-28 | 2019-09-10 | 南京工业职业技术学院 | A kind of unmanned plane damping undercarriage |
| CN110667830A (en) * | 2019-08-30 | 2020-01-10 | 南京精微迅智能科技有限公司 | Many rotor unmanned aerial vehicle for aerial survey |
| CN113264185B (en) * | 2021-07-20 | 2022-04-01 | 江苏南瓯物联网科技有限公司 | Range finding aircraft |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050230201A1 (en) * | 2004-04-16 | 2005-10-20 | Takuhiro Kondou | Electromagnetic shock absorber for vehicle |
| CN202926940U (en) * | 2012-11-07 | 2013-05-08 | 西林钢铁集团有限公司 | Trolley-walking bidirectional spring buffer device for bridge crane |
| CN205315588U (en) * | 2015-12-05 | 2016-06-15 | 重庆创隆实业有限公司 | Car seat bumper shock absorber |
| CN205639442U (en) * | 2016-05-16 | 2016-10-12 | 温州江硕车业股份有限公司 | Two -spring motorcycle rear shock absorber |
| CN206068141U (en) * | 2016-10-11 | 2017-04-05 | 四川建筑职业技术学院 | A kind of fixed-wing model plane preposition undercarriage of employing double damping structure |
| CN206087273U (en) * | 2016-10-12 | 2017-04-12 | 中交遥感载荷（北京）科技有限公司 | Unmanned aerial vehicle hydraulic pressure shock attenuation undercarriage |
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| Publication number | Publication date |
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| CN107344614A (en) | 2017-11-14 |
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Effective date of registration: 20200803 Address after: Room 216, 2 / F, building g, Wenzhou enlightenment future industrial park, 77 Jinyang Road, nanbaixiang street, Ouhai District, Wenzhou City, Zhejiang Province Applicant after: Wenzhou Xuerong Machinery Technology Co.,Ltd. Address before: Comprehensive Utilization Technology Co. Ltd. 241000 Anhui province Wuhu City Sanshan District Spring Chau Road Wuhu New Metallurgical Resources Applicant before: Hu Jun |
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