CN107458584B - Quick-assembly aircraft landing gear assembly - Google Patents
Quick-assembly aircraft landing gear assembly Download PDFInfo
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- CN107458584B CN107458584B CN201710619233.3A CN201710619233A CN107458584B CN 107458584 B CN107458584 B CN 107458584B CN 201710619233 A CN201710619233 A CN 201710619233A CN 107458584 B CN107458584 B CN 107458584B
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- 230000004913 activation Effects 0.000 claims 2
- 230000037431 insertion Effects 0.000 claims 2
- 238000003780 insertion Methods 0.000 claims 2
- 238000009434 installation Methods 0.000 abstract description 3
- 238000000034 method Methods 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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- 238000011084 recovery Methods 0.000 description 1
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Classifications
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- 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
- B64C25/02—Undercarriages
- B64C25/06—Undercarriages fixed
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Snaps, Bayonet Connections, Set Pins, And Snap Rings (AREA)
Abstract
The invention provides a quick-assembly aircraft landing gear assembly, which is used for connecting a landing gear with an aircraft body and comprises a landing gear and an aircraft connecting end arranged on the aircraft, wherein the landing gear comprises a landing gear supporting end and a landing gear connecting end, and the aircraft connecting end is connected with the landing gear connecting end. The T-shaped fixing block arranged at the landing gear connecting end is correspondingly fixed in the T-shaped fixing groove arranged at the aircraft connecting end, and the movable anti-falling pin is correspondingly embedded into the anti-falling hole on the T-shaped fixing groove when the T-shaped fixing block is assembled with the T-shaped fixing groove, so that the quick assembly of the landing gear movable end and the fixed end is realized. Compared with the prior art, the quick assembly connection of the landing gear movable end and the landing gear fixed end can be realized, and the quick assembly connection device has the advantages of being quick in installation, simple in operation and the like.
Description
Technical Field
The invention belongs to a connecting piece, and particularly relates to a quick assembly component which is mainly used for realizing quick connection of a landing gear and an aircraft body.
Background
The landing gear is a device for supporting the gravity of the aircraft and bearing corresponding loads when the aircraft parks on the ground, slides, takes off and lands and slides. The aircraft has landing or recovery stages during the lift off process. Along with the rapid development of aircrafts, the aircraft is widely applied to the fields of civil use, scientific research and the like, and for the convenience of transportation, the fuselage and the landing gear of the aircrafts are separated, and the landing gear is required to be installed when in use, but most aircrafts and landing gears are installed in a screw fixing mode at present, the assembly process is complex, and the disassembly is inconvenient.
Disclosure of Invention
To this end, the object of the present invention is to provide an aircraft landing gear assembly that is simple to assemble and convenient to disassemble.
The aim of the invention is achieved by the following technical scheme.
A fast-assembled aircraft landing gear assembly for connecting a landing gear to an aircraft fuselage, comprising a landing gear and an aircraft connection mounted on the aircraft, the landing gear comprising a landing gear support end and a landing gear connection, the aircraft connection being connected to the landing gear connection, wherein,
the landing gear connecting end comprises a T-shaped fixed block, an anti-falling pin groove is formed in the T-shaped fixed block, the rear end face of the anti-falling pin groove is an anti-falling pin groove rear limiting face, and the front end face of the anti-falling pin groove front limiting face; the front limiting surface of the anti-drop pin slot is provided with a first anti-drop pin movable hole penetrating out from the front end surface of the T-shaped fixed block, and the rear limiting surface of the anti-drop pin slot is provided with a second anti-drop pin movable hole;
the anti-drop pin groove is internally provided with an anti-drop pin and a spring, the anti-drop pin comprises a sliding pin body, a pulling hand is arranged on the sliding pin body, the front end surface of the sliding pin body is provided with a first guide post correspondingly inserted into the first anti-drop pin moving hole, the rear end surface of the sliding pin body is provided with a second guide post correspondingly inserted into the second anti-drop pin moving hole, the second guide post is correspondingly sleeved in the spring, and when the pulling hand is pulled, under the action of the spring, the first guide post can correspondingly extend out or retract from the first anti-drop pin moving hole;
the aircraft connecting end is provided with a T-shaped fixing groove, and an anti-drop hole corresponding to the first anti-drop pin moving hole is arranged in the T-shaped fixing groove;
the spring is compressed by stirring the poking hand, the T-shaped fixing block is correspondingly fixed in the T-shaped fixing groove, the poking hand is loosened, the spring is reset, the first guide column is pushed to extend out of the first anti-drop pin moving hole and correspondingly inserted into the anti-drop hole, and the landing gear connecting end is connected and fixed with the aircraft connecting end; toggle the handle, make the spring compression, first guide post is withdrawed from by the anticreep hole, and the T type fixed block corresponds can follow in the T type fixed slot is taken out to make undercarriage link and aircraft link break away from.
Further, a second limiting hole is formed in the rear limiting surface of the anti-falling pin groove, and the second anti-falling pin moving hole is located in the second limiting hole.
Further, the first anti-derailing pin moving hole and the second anti-derailing pin moving hole are positioned on the same straight line.
Further, a first limiting surface is arranged at the bottom in the T-shaped fixing groove, and a second limiting surface corresponding to the first limiting surface is arranged at the bottom of the T-shaped fixing block.
Further, a third limiting surface is respectively arranged on two sides of the bottom in the T-shaped fixing groove, and a fourth limiting surface corresponding to the third limiting surface is arranged on two sides of the bottom of the T-shaped fixing block.
Further, the inner side wall of the T-shaped fixing groove is provided with a first guide surface, and the front side of the bottom of the T-shaped fixing block is provided with a second guide surface corresponding to the first guide surface.
Further, the front end face of the sliding pin body is a front limiting face corresponding to the front limiting face of the anti-drop pin groove, and the rear end face of the pulling hand is a rear limiting face corresponding to the rear limiting face of the anti-drop pin groove.
Further, the first guide post is arranged on the front limiting surface, and the front end of the first guide post is provided with a ball head which is convenient to insert into the anti-drop hole.
Further, a first limiting hole is formed in the rear end face of the sliding pin body, the second guide column is correspondingly located in the first limiting hole, and a spring sleeved on the second guide column is correspondingly located between the first limiting hole and the second limiting hole.
Further, a chamfer which is convenient to insert into the second anti-derailing pin movable hole is arranged on the second guide post.
According to the quick-assembly aircraft landing gear assembly, the T-shaped fixing blocks arranged at the landing gear connecting ends are correspondingly fixed in the T-shaped fixing grooves arranged at the aircraft connecting ends, and the movable anti-falling pins are correspondingly embedded into the anti-falling holes on the T-shaped fixing grooves when the T-shaped fixing blocks are assembled with the T-shaped fixing grooves, so that quick assembly of the landing gear movable ends and the fixed ends is realized. Compared with the prior art, the quick assembly connection of the landing gear movable end and the landing gear fixed end can be realized, and the quick assembly connection device has the advantages of being quick in installation, simple in operation and the like.
Drawings
FIG. 1 is a schematic perspective view of a quick-assembly landing gear assembly of the present invention;
FIG. 2 is a schematic view of the assembled construction of the quick-assembly landing gear assembly of the present invention;
FIG. 3 is a schematic front view of the landing gear attachment end of the present invention when placed upside down;
FIG. 4 is a schematic rear view of the landing gear attachment end of the present invention when placed upside down;
FIG. 5 is a schematic perspective view of an aircraft connection end of the present invention;
FIG. 6 is a schematic perspective view of the anti-slip pin of the present invention in an upright position;
fig. 7 is a schematic perspective view of the anti-slip pin of the present invention when placed upside down.
The figure identifies the description: landing gear 10, landing gear support end 11, landing gear connection end 12, T-shaped fixed block 1201, first anti-slip pin moving hole 1202, second guide surface 1203, anti-slip pin slot 1204, second limiting hole 1205, second anti-slip pin moving hole 1206, anti-slip pin slot rear limiting surface 1207, anti-slip pin slot front limiting surface 1208, fourth limiting surface 1209, second limiting surface 1210, aircraft connection end 20, T-shaped fixed slot 201, anti-slip hole 202, first limiting surface 203, third limiting surface 204, first guide surface 205, anti-slip pin 30, slip pin body 301, toggle 302, first guide post 303, ball head 304, front limiting surface 305, second guide post 306, first limiting hole 307, rear limiting surface 308, chamfer 309, spring 40.
Detailed Description
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. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.
Aiming at the problems that the existing aircraft and landing gear are complex in installation and assembly process and inconvenient to detach, the invention aims to provide an aircraft landing gear assembly which is simple to assemble and convenient to detach.
Referring now to FIG. 1, FIG. 1 is a schematic perspective view of a quick-assembly landing gear assembly of the present invention. The present invention provides a quick-fit landing gear assembly for connecting a landing gear 10 to an aircraft fuselage, which generally includes a landing gear 10 and an aircraft attachment end 20 mounted on an aircraft.
As shown in fig. 2, fig. 2 is a schematic view of the assembled construction of the quick-assembly landing gear assembly of the present invention. The landing gear 10 includes a landing gear support end 11 for supporting the ground and a landing gear attachment end 12 for attaching an aircraft, the aircraft attachment end 20 being attached to the landing gear attachment end 12.
A release preventing pin 30 and a spring 40 are correspondingly arranged in the landing gear connecting end 12, and the aircraft connecting end 20 and the landing gear connecting end 12 are detachably assembled and connected through the release preventing pin 30 and the spring 40.
As shown in fig. 3 and 4, fig. 3 is a schematic front view of the landing gear of the present invention when the landing gear connecting end is placed upside down; fig. 4 is a schematic rear view of the landing gear attachment of the present invention when placed upside down. In this embodiment, the landing gear connecting end 12 includes a T-shaped fixing block 1201, an anti-disengagement pin slot 1204 is provided on the T-shaped fixing block 1201, a rear end surface of the anti-disengagement pin slot 1204 is an anti-disengagement pin slot rear limit surface 1207, and a front end surface is an anti-disengagement pin slot front limit surface 1208; the front limiting surface 1208 of the anti-drop pin slot is provided with a first anti-drop pin movable hole 1202 penetrating out from the front end surface of the T-shaped fixed block 1201, the rear limiting surface 1207 of the anti-drop pin slot is provided with a second limiting hole 1205, and the second limiting hole 1205 is internally provided with a second anti-drop pin movable hole 1206.
In this embodiment, the first anti-slip pin moving hole 1202 and the second limiting hole 1205 and the second anti-slip pin moving hole 1206 are on the same straight line.
The bottom of the T-shaped fixed block 1201 is provided with a second limiting surface 1210; fourth limiting surfaces 1209 are arranged on two sides of the bottom of the T-shaped fixed block 1201; the bottom front side of the T-shaped fixing block 1201 is provided with a second guide surface 1203.
Fig. 5 is a schematic perspective view of an aircraft connection terminal according to the present invention, as shown in fig. 5. The aircraft connection end 20 is provided with a T-shaped fixing slot 201, the front end of the T-shaped fixing slot 201 is open, the rear end of the T-shaped fixing slot 201 is closed, the rear end of the T-shaped fixing slot 201 is provided with an anti-drop hole 202, and the anti-drop hole 202 corresponds to the first anti-drop pin moving hole 1202.
The bottom of the T-shaped fixing groove 201 is provided with a first limiting surface 203, and the first limiting surface 203 corresponds to a second limiting surface 1210.
A third limiting surface 204 is respectively arranged on two sides of the bottom of the T-shaped fixing groove 201, and the third limiting surface 204 corresponds to the fourth limiting surface 1209.
The opening at the top of the inner side wall of the T-shaped fixing groove 201 is provided with a first guide surface 205 with an inclined angle, the first guide surface 205 corresponds to the second guide surface 1203, and the T-shaped fixing block 1201 can be aligned and assembled with the T-shaped fixing groove 201 more easily through the cooperation of the first guide surface 205 and the second guide surface 1203.
As shown in fig. 6 and 7, fig. 6 is a schematic perspective view of the anti-disengaging pin of the present invention when the pin is placed upright; fig. 7 is a schematic perspective view of the anti-slip pin of the present invention when placed upside down. The anti-slip pin 30 of this embodiment is disposed in the anti-slip pin slot 1204, and includes a slip pin body 301, the front end surface of the slip pin body 301 is a front limiting surface 305 corresponding to a front limiting surface 1208 of the anti-slip pin slot, and a first guiding post 303 is disposed on the front limiting surface 305, and a ball head 304 is disposed at the front end of the first guiding post 303, so that friction resistance can be reduced, so that the first guiding post 303 can correspondingly extend out of the first anti-slip pin moving hole 1202 and correspondingly be embedded into the anti-slip hole 202.
The rear end face of the sliding pin body 301 is provided with a first limiting hole 307, the first limiting hole 307 is provided with a second guide post 306, and the tail end of the second guide post 306 is provided with a chamfer 309, so that friction resistance can be effectively reduced, and the sliding pin body is conveniently correspondingly embedded into a second anti-drop pin movable hole 1206.
The second guide post 306 is sleeved with a spring 40, one end of the spring 740 is assembled in the first limiting hole 307, and the other end is correspondingly assembled in the second limiting hole 1205.
The sliding pin body 301 is provided with a pulling hand 302, the rear end surface of the pulling hand 302 is a rear limit surface 308, and the rear limit surface 308 corresponds to the rear limit surface 1207 of the anti-drop pin groove.
The working principle of the invention is as follows: when the landing gear connecting end 12 is required to be assembled with the aircraft connecting end 20, firstly, the first guide post 303 and the ball head 304 on the anti-drop pin 30 are retracted into the first anti-drop pin moving hole 1202 on the T-shaped fixed block 1201 by pulling back the anti-drop pin pulling hand 302 on the anti-drop pin 30 and compressing the spring 40, then the T-shaped fixed block 1201 of the landing gear connecting end 12 and the T-shaped fixed slot 201 of the aircraft connecting end 20 are aligned, under the combined action of the first guide surface 205 and the second guide surface 1203, the two start to be assembled in a contact way until the second limit surface 1210 and the fourth limit surface 1209 below the T-shaped fixed block 1201 are respectively contacted with the first limit surface 203 and the third limit surface 204 at the bottom of the T-shaped fixed slot 201, to limit the landing gear connecting end 12 to move downwards, the complete contact cooperation of the T-shaped fixing block 1201 and the T-shaped fixing groove 201 limits the landing gear connecting end 12 to move in four directions, namely front, back, left and right, at this time, the anti-drop pin pulling hand 302 is released, the anti-drop pin 30 slides forwards under the action of the elastic force of the spring 40, finally the first guide post 303 and the ball head 304 correspondingly extend into the anti-drop hole 202 on the T-shaped fixing groove 201, and the anti-drop pin 30 cannot retract and disengage from the existing position under the action of no external force because the spring 40 still provides the elastic force at the rear end, so that the upward movement of the landing gear connecting end 12 is also limited, and the assembly connection with the landing gear connecting end 12 and the aircraft connecting end 20 is finally completed.
When the landing gear connecting end 12 needs to be detached from the aircraft connecting end 20, the pulling hand 302 is correspondingly pulled to compress the spring 40, the first guide post 303 is withdrawn from the anti-release hole 202, and the T-shaped fixing block 1201 can be correspondingly taken out from the T-shaped fixing groove 201, so that the landing gear connecting end 12 is separated from the aircraft connecting end 20.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention.
Claims (10)
1. A fast-assembled aircraft landing gear assembly for connecting a landing gear to an aircraft fuselage, comprising a landing gear (10) and an aircraft connection end (20) mounted on the aircraft, said landing gear (10) comprising a landing gear support end (11) and a landing gear connection end (12), said aircraft connection end (20) being connected to the landing gear connection end (12), characterized in that,
the landing gear connecting end (12) comprises a T-shaped fixed block (1201), an anti-drop pin groove (1204) is formed in the T-shaped fixed block (1201), the rear end face of the anti-drop pin groove (1204) is an anti-drop pin groove rear limit face (1207), and the front end face of the anti-drop pin groove front limit face (1208); a first anti-drop pin movable hole (1202) penetrating out of the front end surface of the T-shaped fixed block (1201) is formed in the front limit surface (1208) of the anti-drop pin groove, and a second anti-drop pin movable hole (1206) is formed in the rear limit surface (1207) of the anti-drop pin groove;
the anti-drop pin groove (1204) is internally provided with an anti-drop pin (30) and a spring (40), the anti-drop pin (30) comprises a sliding pin body (301), a poking hand (302) is arranged on the sliding pin body (301), the front end surface of the sliding pin body (301) is provided with a first guide post (303) correspondingly inserted into the first anti-drop pin moving hole (1202), the rear end surface of the sliding pin body (301) is provided with a second guide post (306) correspondingly inserted into the second anti-drop pin moving hole (1206), the second guide post (306) is correspondingly sleeved in the spring (40), and when the poking hand (302) is poked, the first guide post (303) can correspondingly extend or retract from the first anti-drop pin moving hole (1202) under the action of the spring (40);
the aircraft connecting end (20) is provided with a T-shaped fixing groove (201), and an anti-falling hole (202) corresponding to the first anti-falling pin moving hole (1202) is arranged in the T-shaped fixing groove (201);
the poking hand (302) is poked to compress the spring (40), the T-shaped fixing block (1201) is correspondingly fixed in the T-shaped fixing groove (201), the poking hand (302) is loosened, the spring (40) is reset to push the first guide post (303) to extend out of the first anti-drop pin movable hole (1202), the first guide post is correspondingly inserted into the anti-drop hole (202), and the landing gear connecting end (12) is connected and fixed with the aircraft connecting end (20); the poking hand (302) is poked to compress the spring (40), the first guide column (303) is withdrawn from the anti-falling hole (202), and the T-shaped fixing block (1201) can be correspondingly taken out of the T-shaped fixing groove (201) so as to separate the landing gear connecting end (12) from the aircraft connecting end (20).
2. The quick-fit aircraft landing gear assembly of claim 1, wherein the anti-slip pin slot rear stop surface (1207) is provided with a second stop aperture (1205), and wherein the second anti-slip pin clearance aperture (1206) is positioned within the second stop aperture (1205).
3. The quick-fit aircraft landing gear assembly of claim 2, wherein the first anti-slip pin activation hole (1202) is collinear with the second anti-slip pin activation hole (1206).
4. A quick-fit aircraft landing gear assembly according to claim 2, wherein the bottom of the T-shaped fixing groove (201) is provided with a first stop surface (203) and the bottom of the T-shaped fixing block (1201) is provided with a second stop surface (1210) corresponding to the first stop surface (203).
5. The quick-fit aircraft landing gear assembly of claim 4, wherein a third stop surface (204) is provided on each side of the bottom of the T-shaped mounting slot (201), and a fourth stop surface (1209) corresponding to the third stop surface (204) is provided on each side of the bottom of the T-shaped mounting block (1201).
6. A quick-fit aircraft landing gear assembly according to claim 5, wherein the inner side wall of the T-shaped fixing groove (201) is provided with a first guide surface (205) and the bottom front side of the T-shaped fixing block (1201) is provided with a second guide surface (1203) corresponding to the first guide surface (205).
7. The quick-fit aircraft landing gear assembly of claim 2, wherein the front face of the slide pin body (301) is a front stop face (305) corresponding to the anti-slip pin slot front stop face (1208), and the rear face of the hand (302) is a rear stop face (308) corresponding to the anti-slip pin slot rear stop face (1207).
8. A quick-fit aircraft landing gear assembly according to claim 7, wherein the first guide post (303) is provided on the front stop face (305) and the front end of the first guide post (303) is provided with a ball head (304) for facilitating insertion into the anti-release hole (202).
9. The quick-fit aircraft landing gear assembly of claim 7, wherein the rear end face of the sliding pin body (301) is provided with a first limiting hole (307), the second guide post (306) is correspondingly positioned in the first limiting hole (307), and the spring (40) sleeved on the second guide post (306) is correspondingly positioned between the first limiting hole (307) and the second limiting hole (1205).
10. The quick-fit aircraft landing gear assembly of claim 7, wherein the second guide post (306) is provided with a chamfer (309) that facilitates insertion into a second anti-slip pin clearance hole (1206).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710619233.3A CN107458584B (en) | 2017-07-26 | 2017-07-26 | Quick-assembly aircraft landing gear assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710619233.3A CN107458584B (en) | 2017-07-26 | 2017-07-26 | Quick-assembly aircraft landing gear assembly |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107458584A CN107458584A (en) | 2017-12-12 |
| CN107458584B true CN107458584B (en) | 2023-05-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710619233.3A Active CN107458584B (en) | 2017-07-26 | 2017-07-26 | Quick-assembly aircraft landing gear assembly |
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| Country | Link |
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| CN (1) | CN107458584B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109795677A (en) * | 2019-03-22 | 2019-05-24 | 西北工业大学 | A rapid disassembly and assembly landing gear structure of an unmanned aerial vehicle |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB521161A (en) * | 1938-11-09 | 1940-05-14 | George Herbert Dowty | Improvements relating to landing gear of aircraft |
| CN204223174U (en) * | 2014-10-27 | 2015-03-25 | 广州极飞电子科技有限公司 | Rotor craft foot rest fast assembling disassembling structure |
| CN204279925U (en) * | 2014-10-28 | 2015-04-22 | 深圳九星智能航空科技有限公司 | The unmanned vehicle that alighting gear quick release is changed |
| CA2911998A1 (en) * | 2014-11-26 | 2016-05-26 | Gilles Daigle | Unmanned aerial vehicle |
| CN206243458U (en) * | 2016-12-07 | 2017-06-13 | 天津航天中为数据系统科技有限公司 | A kind of new multi-rotor unmanned aerial vehicle linkage undercarriage |
| CN207045707U (en) * | 2017-07-26 | 2018-02-27 | 深圳市科卫泰实业发展有限公司 | A kind of aircraft landing gear component of quick assembling |
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2017
- 2017-07-26 CN CN201710619233.3A patent/CN107458584B/en active Active
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| CN107458584A (en) | 2017-12-12 |
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