CN108609164B - Utilize aircraft undercarriage of spring buckle - Google Patents
Utilize aircraft undercarriage of spring buckle Download PDFInfo
- Publication number
- CN108609164B CN108609164B CN201810401008.7A CN201810401008A CN108609164B CN 108609164 B CN108609164 B CN 108609164B CN 201810401008 A CN201810401008 A CN 201810401008A CN 108609164 B CN108609164 B CN 108609164B
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- plate
- shaft
- circular
- connecting rod
- hole
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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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
Abstract
The utility model provides an utilize aircraft undercarriage of spring buckle, belong to the aircraft undercarriage field, including lead screw transmission, the motion piece, damping bolt, the drive plate, the follow-up plate, spring buckle and connecting rod, the screw hole and the lead screw cooperation of motion piece, the drive plate is being connected to the cylinder axle of motion piece, follow-up plate middle part position and the coaxial cooperation of drive plate, damping bolt links together follow-up plate and drive plate top, the spring buckle is installed at follow-up plate and drive plate complex position, and press from both sides between the two, connecting rod one end is being connected and is including lead screw transmission's connecting rod fixed axle A, can rotate, the drive plate is being connected to the other end, also can rotate. The invention comprehensively utilizes the screw rod transmission device, the motion block, the damping bolt, the driving plate, the driven plate, the spring buckle and the connecting rod, and improves the damping performance of the unmanned fixed-wing aircraft on the premise of ensuring the simplicity of the system.
Description
Technical Field
The invention relates to an aircraft landing gear, in particular to an aircraft landing gear utilizing a spring buckle, and belongs to the field of aircraft landing gears.
Background
The unmanned plane is called unmanned plane for short, and is an unmanned aerial vehicle operated by radio remote control equipment and a self-contained program control device. Unmanned aerial vehicles are in fact a general term for unmanned aerial vehicles, and can be defined from a technical perspective as follows: unmanned fixed wing aircraft, unmanned VTOL aircraft, unmanned airship, unmanned helicopter, unmanned multi-rotor aircraft, unmanned paravane, etc.
The invention mainly aims at an unmanned fixed wing aircraft, namely a fixed wing, which is provided with a lifting force by wind flowing through the wing as the name suggests. Like the plane of doing at ordinary times, fixed wing unmanned aerial vehicle need run-up when taking off, must slide when descending, but this type of unmanned aerial vehicle duration is long, flight efficiency is high, load is big.
The landing gear of the unmanned fixed wing aircraft is also an important part of the unmanned fixed wing aircraft, but the size of the landing gear is smaller than that of a passenger aircraft generally, the size of the landing gear of the passenger aircraft is too large, the system is too complex, and the need for the landing gear of the unmanned fixed wing aircraft which can effectively absorb shock and has a very simple structure is urgently needed.
The present invention therefore provides an aircraft landing gear using a spring bayonet to solve the above problems.
Disclosure of Invention
In view of the above-mentioned deficiencies, the present invention provides an aircraft landing gear that utilizes a spring buckle.
The invention is realized by the following technical scheme: the utility model provides an utilize aircraft undercarriage of spring buckle, includes lead screw transmission, motion piece, shock attenuation bolt, initiative board, follow-up plate, spring buckle and connecting rod, its characterized in that: the device comprises a base, a plurality of moving blocks and a plurality of connecting rods, wherein the moving blocks are composed of upright columns and cylindrical shafts, threaded holes are formed in the upper parts of the upright columns, the cylindrical shafts are installed on the lower parts of the upright columns, and the number of the moving blocks is two; the screw rod transmission device comprises two driving motors, a right-angle supporting plate, a screw rod, a fixing plate and a connecting rod fixing shaft A, wherein two ends of the screw rod are respectively installed between the fixing plate and the right-angle supporting plate through bearings; the damping device comprises a driving plate, a driven plate, a damping bolt, a spring buckle, a connecting rod fixing shaft A, a spring and a connecting rod fixing shaft B, wherein the driving plate is connected with the driven plate through the spring buckle, the connecting rod fixing shaft A is connected with a screw rod transmission device and can rotate, the cylindrical shaft of the moving block is connected with the driving plate, the middle position of the driven plate is coaxially matched with the driving plate, the damping bolt is used for connecting the top of the driven plate and the top of the driving plate together, the spring buckle is installed at the matched position of the driven.
Preferably, the damping bolt is composed of a baffle A, a main shaft, a damping compression spring, a baffle B, a threaded column and a nut, the baffle A, the main shaft, the baffle B and the threaded column are integrated, the baffle A is connected with the main shaft, the main shaft is connected with the baffle B, the threaded column is connected with the front end of the baffle B, the damping compression spring is sleeved on the main shaft, and the nut is in threaded fit with the threaded column.
Preferably, the driving plate is composed of a cylindrical hollow structure, a circular through hole A, a support plate A, a matching shaft and a connecting rod fixing shaft B, the cylindrical hollow structure is coaxially matched with the cylindrical shaft on the moving block, a vertical plate is connected to the lower portion of the cylindrical hollow structure and is vertical, two circular through holes A on the horizontal line are formed in the vertical plate, a rectangular neutral position is formed in the middle of the support plate A, the matching shaft is fixed to the middle of the rectangular neutral position, the included angle between the support plate A and the horizontal plane is 50 degrees, and the connecting rod fixing shaft B is welded to the middle of the lowest side of the support plate A and can be coaxially matched with the end portion of a connecting rod.
Preferably, the follow-up plate is composed of a vertical plate, a circular through hole B, a support plate B, a hollow shaft and an airplane wheel, the vertical plate is provided with two circular through holes B on a horizontal line, the lower side of the vertical plate is welded with the support plate B inclined by 50 degrees, the hollow shaft is installed in the middle of the support plate B, the hollow shaft is coaxially matched with the matching shaft, and the airplane wheel is installed at the lower end of the support plate B.
Preferably, the spring buckle comprises compression spring and right angle support, spring buckle quantity is two, the part that extends at compression spring's both ends is the right angle support, and the contained angle between two right angle supports is 80 degrees.
Preferably, the diameters of the main shaft and the baffle B of the damping bolt are smaller than the diameter of the circular through hole A, the diameter of the circular through hole A is equal to the diameter of the circular through hole B, the baffle B is close to one side of the threaded column, a gasket with the diameter larger than that of the circular through hole B is required to be used during installation, the diameter of the baffle A is larger than that of the circular through hole A, and the diameters of the main shaft and the threaded column are smaller than that of the circular through hole A.
The invention has the advantages that:
1. according to the invention, two spring buckles are utilized, when the unmanned aerial vehicle lands, the follow-up plate receives load and vibration, and then the first damping is carried out through the spring buckles, so that the unmanned aerial vehicle lands more stably.
2. The special damping bolt is adopted, the structure is simple, the vibration and the load of the unmanned aerial vehicle during landing are subjected to secondary damping through the damping compression spring on the damping bolt, and the vibration during rising and falling is effectively reduced.
3. The invention comprehensively utilizes the screw rod transmission device, the motion block, the damping bolt, the driving plate, the driven plate, the spring buckle and the connecting rod, and improves the damping performance of the unmanned fixed-wing aircraft on the premise of ensuring the simplicity of the system.
Drawings
FIG. 1 is a schematic representation of the landing gear of the present invention in use;
FIG. 2 is a schematic representation of the landing gear of the present invention in an unused condition;
FIG. 3 is a schematic illustration of the transmission system of the present invention;
FIG. 4 is a schematic diagram of an active plate structure according to the present invention;
FIG. 5 is a schematic view of a follower plate according to the present invention;
FIG. 6 is a schematic view of a shock bolt structure according to the present invention;
FIG. 7 is a schematic view of a spring clip structure of the present invention;
FIG. 8 is an enlarged view of a portion of the spring clip of the present invention;
fig. 9 is a partially enlarged view of the damper spring according to the present invention.
In the figure, 1, a screw transmission device, 101, a driving motor, 102, a right-angle supporting plate, 103, a screw rod, 104, a fixing plate, 105, a connecting rod fixing shaft A, 2, a moving block, 201, a stand column, 202, a cylindrical shaft, 3, a damping bolt, 301, a baffle plate A, 302, a main shaft, 303, a damping compression spring, 304, a baffle plate B, 305, a threaded column, 306, a nut, 4, a driving plate, 401, a cylindrical hollow structure, 402, a circular through hole A, 403, a support plate A, 404, a matching shaft, 405, a connecting rod fixing shaft B, 5, a follow-up plate, 501, a vertical plate, 502, a circular through hole B, 503, a supporting plate B, 504, a hollow shaft, 505, an airplane wheel, 6, a spring buckle, 601, a compression spring, 602, a right-angle support and 7.
Detailed Description
The technical solutions in the present invention will be described clearly and completely with reference to the accompanying drawings, and it is obvious that the described embodiments are only some embodiments of the present invention, not all 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.
Referring to fig. 1 to 9, an aircraft landing gear using a spring clip includes a screw transmission device 1, a motion block 2, a damping bolt 3, a driving plate 4, a driven plate 5, a spring clip 6, and a connecting rod 7, and is characterized in that: the moving block 2 is composed of a vertical column 201 and a cylindrical shaft 202, the upper part of the vertical column 201 is provided with a threaded hole, the lower part of the vertical column is provided with the cylindrical shaft 202, and the number of the moving blocks 2 is two; the screw rod transmission device 1 is composed of two driving motors 101, a right-angle supporting plate 102, a screw rod 103, a fixing plate 104 and a connecting rod fixing shaft A105, two ends of each screw rod 103 are respectively installed between the fixing plate 104 and the right-angle supporting plate 102 through bearings, the driving motors 101 are installed on the right-angle supporting plate 102 and connected with the screw rod 103 through couplers, and the connecting rod fixing shaft A105 is welded on the lower surface of the right-angle supporting plate 102; the threaded hole of the moving block 2 is matched with a lead screw, the cylindrical shaft of the moving block is connected with a driving plate, the middle position of a follow-up plate is coaxially matched with the driving plate 4, the top of the follow-up plate 5 is connected with the top of the driving plate 4 through the damping bolt 3, the spring buckle 6 is installed at the matched position of the follow-up plate 5 and the driving plate 4 and clamped between the follow-up plate 5 and the driving plate 4, one end of the connecting rod 7 is connected with a connecting rod fixing shaft A105 of the lead screw transmission device 1 and can rotate, and the other end of the connecting rod 7 is connected with the driving plate.
Preferably, the damping bolt 3 is composed of a baffle plate a301, a main shaft 302, a damping compression spring 303, a baffle plate B304, a threaded column 305 and a nut 306, the baffle plate a301, the main shaft 302, the baffle plate B304 and the threaded column 305 are integrated, the baffle plate a301 is connected with the main shaft 302, the main shaft 302 is connected with the baffle plate B304, the front end of the baffle plate B304 is connected with the threaded column 305, the damping compression spring 303 is sleeved on the main shaft 302, and the nut 306 is in threaded fit with the threaded column 305.
Preferably, the driving plate 4 is composed of a cylindrical hollow structure 401, a circular through hole a402, a support plate a403, a matching shaft 404 and a connecting rod fixing shaft B405, the cylindrical hollow structure 401 is coaxially matched with the cylindrical shaft 202 on the moving block 2, a vertical plate is connected to the lower side of the cylindrical hollow structure 401, the vertical plate is vertical, two circular through holes a402 on a horizontal line are formed in the vertical plate, a rectangular neutral position is formed in the middle of the support plate a403, the matching shaft 404 is fixed in the middle of the rectangular neutral position, the included angle between the support plate a403 and the horizontal plane is 50 degrees, the connecting rod fixing shaft B405 is welded to the middle of the lowest side of the support plate a403, and the connecting rod fixing shaft B405 can be coaxially matched with the.
Preferably, the follower plate 5 is composed of a vertical plate 501, a circular through hole B502, a support plate B503, a hollow shaft 504 and an airplane wheel 505, wherein two circular through holes B502 are arranged on the vertical plate 501 in a horizontal line, the lower side of the vertical plate 501 is welded with the support plate B503 inclined by 50 degrees, the hollow shaft 504 is arranged in the middle of the support plate B503, the hollow shaft 504 is coaxially matched with the matching shaft 404, and the airplane wheel 505 is arranged at the lower end of the support plate B503.
Preferably, the spring buckle 6 is composed of a compression spring 601 and a right-angle bracket 602, the number of the spring buckles 6 is two, the parts extending out of the two ends of the compression spring 601 are the right-angle brackets 602, and the included angle between the two right-angle brackets 602 is 80 degrees.
Preferably, the diameter of the main shaft 302 and the baffle B305 of the shock-absorbing bolt 3 is smaller than that of the circular through hole a402, the diameter of the circular through hole a402 is equal to that of the circular through hole B503, the baffle B is close to one side of the threaded column, a gasket with the diameter larger than that of the circular through hole B is required to be used during installation, the diameter of the baffle a301 is larger than that of the circular through hole a402, and the diameter of the main shaft 302 and the threaded column 305 is smaller than that of the circular through hole a 402.
The working principle is as follows: when the airplane lands, the driving motor 101 works to drive the screw rod 103 to rotate, so that the moving block 2 is driven to move forwards, the airplane frame is opened under the matching of the driving plate 4 and the connecting rod 7, and the shock absorption is carried out during landing; after the aircraft takes off, the driving motor 101 works to drive the screw rod 103 to rotate, and further drive the moving block 2 to move backwards, and the aircraft frame is folded under the matching of the driving plate 4 and the connecting rod 7.
It will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in the embodiments described above without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims.
Claims (3)
1. The utility model provides an utilize aircraft undercarriage of spring buckle, includes lead screw transmission, motion piece, shock attenuation bolt, initiative board, follow-up plate, spring buckle and connecting rod, its characterized in that: the device comprises a base, a plurality of moving blocks and a plurality of connecting rods, wherein the moving blocks are composed of upright columns and cylindrical shafts, threaded holes are formed in the upper parts of the upright columns, the cylindrical shafts are installed on the lower parts of the upright columns, and the number of the moving blocks is two; the screw rod transmission device comprises two driving motors, a right-angle supporting plate, a screw rod, a fixing plate and a connecting rod fixing shaft A, wherein two ends of the screw rod are respectively installed between the fixing plate and the right-angle supporting plate through bearings; the damping bolt is composed of a baffle plate A, a main shaft, a damping compression spring, a baffle plate B, a threaded column and a nut, the baffle plate A, the main shaft, the baffle plate B and the threaded column are integrated, the baffle plate A is connected with the main shaft, the main shaft is connected with the baffle plate B, the front end of the baffle plate B is connected with the threaded column, the damping compression spring is sleeved on the main shaft, and the nut is in threaded fit with the threaded column, the driving plate consists of a cylindrical hollow structure, a circular through hole A, a support plate A, a matching shaft and a connecting rod fixing shaft B, the cylindrical hollow structure is coaxially matched with a cylindrical shaft on the moving block, a vertical plate is connected below the cylindrical hollow structure and is vertical, the vertical plate is provided with two circular through holes A on the same horizontal line, a rectangular neutral position is arranged in the middle of the support plate A, the matching shaft is fixed in the middle of the rectangular neutral position, the included angle between the support plate A and the horizontal plane is 50 degrees, the connecting rod fixing shaft B is welded in the middle of the lowest side of the support plate A, the connecting rod fixing shaft B is coaxially matched with the end part of a connecting rod, the follow-up plate consists of a vertical plate, a circular through hole B, a support plate B, a hollow shaft and an airplane wheel, the two circular through holes B on the same horizontal line are arranged on the vertical plate, and the support plate B inclined at, a hollow shaft is installed in the middle of the supporting plate B and is coaxially matched with the matching shaft, and an airplane wheel is installed at the lower end of the supporting plate B.
2. An aircraft landing gear with a spring catch according to claim 1, wherein: the spring buckle comprises compression spring and right angle support, spring buckle quantity is two, the part that extends at compression spring's both ends is the right angle support, and the contained angle between two right angle supports is 80 degrees.
3. An aircraft landing gear with a spring catch according to claim 1, wherein: the diameter of a main shaft of the damping bolt and the diameter of a baffle B are smaller than that of the circular through hole A, the diameter of the circular through hole A is equal to that of the circular through hole B, the baffle B is close to one side of the threaded column, a gasket with the diameter larger than that of the circular through hole B is required to be used in installation, the diameter of the baffle A is larger than that of the circular through hole A, and the diameters of the main shaft and the threaded column are smaller than that of the circular through hole A.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810401008.7A CN108609164B (en) | 2018-04-28 | 2018-04-28 | Utilize aircraft undercarriage of spring buckle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810401008.7A CN108609164B (en) | 2018-04-28 | 2018-04-28 | Utilize aircraft undercarriage of spring buckle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108609164A CN108609164A (en) | 2018-10-02 |
| CN108609164B true CN108609164B (en) | 2020-05-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201810401008.7A Active CN108609164B (en) | 2018-04-28 | 2018-04-28 | Utilize aircraft undercarriage of spring buckle |
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| CN (1) | CN108609164B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110733633A (en) * | 2019-08-30 | 2020-01-31 | 南京利剑无人机科技有限公司 | Unmanned aerial vehicle undercarriage with transfer wheel |
| CN111924091B (en) * | 2020-08-18 | 2021-11-16 | 东台汇赢创融科技发展有限公司 | Detachable aircraft landing gear suitable for stop on rough road |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB496080A (en) * | 1937-08-19 | 1938-11-24 | Automotive Prod Co Ltd | Improvements in or relating to retractable undercarriages for aircraft |
| CN105818967A (en) * | 2016-05-19 | 2016-08-03 | 安翔泰岳（镇江）航空科技有限公司 | Undercarriage lifting device |
| CN106143881B (en) * | 2016-07-29 | 2018-09-14 | 江西核工业测绘院 | A kind of unmanned plane deceleration damping undercarriage |
| CN206374976U (en) * | 2016-12-30 | 2017-08-04 | 万丰航空工业有限公司 | A kind of double buffering undercarriage of light aerocraft |
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2018
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| CN108609164A (en) | 2018-10-02 |
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Effective date of registration: 20191226 Address after: Ganquan road Shushan District of Hefei City, Anhui Province, 230000 West hillock road to the South Wild Garden commercial office building room B-1512 Applicant after: Anhui Eagle Dragon Industrial Design Co., Ltd. Address before: 448156 Hubei, Jingmen, Zhanghe new town, Zhanghe Town, Hong Tu community, Hong Tu Road No. 1 Applicant before: Berth (Jingmen) aircraft Co., Ltd. |
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Effective date of registration: 20200421 Address after: 362100 Room 201, 2 / F, science and Technology Service Center, Huidong Industrial Park, Dongling Town, Hui'an County, Quanzhou City, Fujian Province Applicant after: Quanzhou Han mouse Education Consulting Co., Ltd Address before: Ganquan road Shushan District of Hefei City, Anhui Province, 230000 West hillock road to the South Wild Garden commercial office building room B-1512 Applicant before: ANHUI YINGLONG INDUSTRIAL DESIGN Co.,Ltd. |
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