CN205525031U - Aircraft draw gear - Google Patents
Aircraft draw gear Download PDFInfo
- Publication number
- CN205525031U CN205525031U CN201620109194.3U CN201620109194U CN205525031U CN 205525031 U CN205525031 U CN 205525031U CN 201620109194 U CN201620109194 U CN 201620109194U CN 205525031 U CN205525031 U CN 205525031U
- Authority
- CN
- China
- Prior art keywords
- module
- aircraft
- rod
- traction apparatus
- quick
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Mutual Connection Of Rods And Tubes (AREA)
Abstract
The utility model discloses an aircraft draw gear, it is including pulling the buffer module, and pull the buffer module and pass through quickmelt and connect and link to each other with body of rod module, body of rod module has walking assembly through clamp fixed mounting, and the other end of body of rod module is connected with through the butt joint module and pulls the couple module. This draw gear structure is small and exquisite, light in weight, collapsible transportation, and convenient operation when dock with the aircraft has improved the commonality and the mobility of guarantee equipment.
Description
Technical field
This utility model relates to aircraft support apparatus field, is specifically related to a kind of aircraft traction apparatus.
Background technology
When aircraft traction apparatus is aircraft floor traction, connects aircraft and the device of tractor, be the important equipment of aircraft support.The currently used monoblock type that the aircraft traction apparatus mainly body of rod is low-carbon alloy material or stagewise aircraft traction apparatus, its shortcoming is: monoblock type aircraft traction apparatus, it is primarily present that length length, volume be big, transport difficult, time and effort consuming in actual mechanical process, needs many people to operate and could realize and the defect such as aircraft docks.Stagewise aircraft traction apparatus, main connected mode is that flange bolt connects, and when assembly and connection uses, due to shortcomings such as the body of rod is heavier, flange bolt attended operation inconvenience, have impact on actually used.
Utility model content
Technical problem to be solved in the utility model is for above-mentioned technological deficiency, it is provided that a kind of aircraft traction apparatus, and this traction apparatus compact structure, lightweight, foldable transportation are easy to operate when docking with aircraft, improve versatility and the mobility of Support Equipment.
In order to realize above-mentioned technical characteristic, the purpose of this utility model is achieved in that a kind of aircraft traction apparatus, it includes drawing buffer module, traction buffer module is connected with body of rod module by Quick butt joint, described body of rod module is installed with walking assembly by clip, and the other end of body of rod module is connected by banjo fixing butt jointing module traction Hooking module.
Described traction buffer module includes bail, and bail is connected with connecting rod by safety bolt, connecting rod is set with multiple dividing plate, is provided with cushion pad between dividing plate, and the two ends of cushion pad are positioned by the block being fixed in connecting rod.
Described cushion pad uses vulcanized rubber material to make.
Described body of rod module uses carbon fiber pipe material to make.
Described Quick butt joint includes front band, front band constitutes bearing pin by bearing pin with lower catch hoop and is connected, the other end of described lower catch hoop is hinged with threaded post, described threaded post constitutes screw-driven with the nut sleeve of the front band other end and is connected, described Quick butt joint also includes positioning core axle, positioning core axle location docking between two body of rod modules.
Described walking assembly includes wheel shaft, and the two ends of wheel shaft are provided with wheel, and the center of described wheel shaft is installed with support, and support is connected by Quick-release pin hook, links up with and is connected with the clip being fixed in body of rod module.
Described wheel uses polyurethane material to make.
Being machined with multiple pin shaft hole on described support, Quick-release pin can match from different pin shaft holes and change the setting height(from bottom) of hook.
This utility model has the advantages that:
1, body of rod module uses carbon fiber pipe material to make, and as the stress main pipe of aircraft traction apparatus, effectively alleviates aircraft traction apparatus construction weight.
2, Quick butt joint is used to realize fast decoupled and the assembling of aircraft traction apparatus.
3, composite traction apparatus compact conformation, be conducive to carrying out seriation, General design by key technical index such as the load of aircraft traction apparatus, length, by changing and aircraft interface, appropriately combined body of rod module, change safety bolt etc. and realize the generalization of aircraft traction apparatus.
4, compact structure, lightweight, transportation mobility is good.
5, pull strength can be limited by safety bolt, thus ensure that the safety of distraction procedure.
Accompanying drawing explanation
The utility model is described in further detail with embodiment below in conjunction with the accompanying drawings.
Fig. 1 is overall structure front view of the present utility model.
Fig. 2 is overall structure top view of the present utility model.
Fig. 3 is overall structure axonometric chart of the present utility model.
Fig. 4 is traction buffer module structural representation of the present utility model.
Fig. 5 is the Quick butt joint of the present utility model structural representation when separating.
Fig. 6 is structural representation during Quick butt joint of the present utility model combination installation.
The structural representation that Fig. 7 is Quick butt joint of the present utility model when being attached with body of rod module.
Fig. 8 is body of rod modular structure schematic diagram of the present utility model.
Fig. 9 is walking modular construction schematic diagram of the present utility model.
Figure 10 is walking assembly three dimensional structure schematic diagram of the present utility model.
In figure: traction buffer module 1, Quick butt joint 2, walking assembly 3, body of rod module 4, banjo fixing butt jointing module 5, traction Hooking module 6, clip 7, bail 101, safety bolt 102, connecting rod 103, dividing plate 104, cushion pad 105, block 106, front band 201, bearing pin 202, lower catch hoop 203, threaded post 204, nut sleeve 205, positioning core axle 206, wheel shaft 301, wheel 302, Quick-release pin 303, support 304, hook 305.
Detailed description of the invention
Below in conjunction with the accompanying drawings embodiment of the present utility model is described further.
As Figure 1-10 shows, a kind of aircraft traction apparatus, it includes drawing buffer module 1, traction buffer module 1 is connected with body of rod module 4 by Quick butt joint 2, described body of rod module 4 is installed with walking assembly 3 by clip 7, and the other end of body of rod module 4 is connected by banjo fixing butt jointing module 5 traction Hooking module 6.The aircraft needing traction quickly can be docked with tractor by above-mentioned traction apparatus, and then aircraft is drawn, improve work efficiency.
Further, described traction buffer module 1 includes bail 101, bail 101 is connected with connecting rod 103 by safety bolt 102, multiple dividing plate 104 it is set with in connecting rod 103, being provided with cushion pad 105 between dividing plate 104, the two ends of cushion pad 105 are positioned by the block 106 being fixed in connecting rod 103.The vibration produced in aircraft distraction procedure can be effectively reduced, it is ensured that the safety of distraction procedure by buffer module.
Further, described cushion pad 105 uses vulcanized rubber material to make.Cushion pad can absorb the shock loading produced in aircraft distraction procedure, makes aircraft run under soft state.
Further, described body of rod module 4 uses carbon fiber pipe material to make.Utilize the high specific strength of carbon fiber pipe composite, high-weatherability, low-density feature, it is ensured that while intensity, can effectively alleviate again weight.
Further, described Quick butt joint 2 includes front band 201, front band 201 constitutes bearing pin by bearing pin 202 with lower catch hoop 203 and is connected, the other end of described lower catch hoop 203 is hinged with threaded post 204, described threaded post 204 constitutes screw-driven with the nut sleeve 205 of front band 201 other end and is connected, described Quick butt joint 2 also includes positioning core axle 206, the positioning core axle 206 location docking between two body of rod modules 4.Use Quick butt joint 2 can quickly realize the docking of different length body of rod module 4, thus meet different length
Further, described walking assembly 3 includes that wheel shaft 301, the two ends of wheel shaft 301 are provided with wheel 302, and the center of described wheel shaft 301 is installed with support 304, support 304 is connected by Quick-release pin 303 hook 305, and hook 305 is connected with the clip 7 being fixed in body of rod module 4.
Further, described wheel 302 uses polyurethane material to make.
Further, described support 304 being machined with multiple pin shaft hole, Quick-release pin 303 can match from different pin shaft holes and change the setting height(from bottom) of hook 305.
Specific works process of the present utility model and operation principle be:
Mention one end of the traction Hooking module of aircraft traction apparatus, dock with aircraft nose landing gear axis of traction, move operation handle, drive locking plate to rotate, lock axis of traction；Mentioning one end of the traction buffer module of aircraft traction apparatus, make bail dock with tractor, now walking assembly is liftoff；Towing aircraft preparation terminates.When towing aircraft pressure or moment of flexure reach (90-100%) of rated value, bending resistance safety bolt or tension safety bolt in traction buffer module are cut off, it is ensured that the traction safety of aircraft.
Above-described embodiment is used for illustrating this utility model; rather than this utility model is limited; in spirit of the present utility model and scope of the claims, any modifications and changes that this utility model is made, both fall within protection domain of the present utility model.
Claims (8)
1. an aircraft traction apparatus, it is characterized in that: it includes drawing buffer module (1), traction buffer module (1) is connected with body of rod module (4) by Quick butt joint (2), described body of rod module (4) is installed with walking assembly (3) by clip (7), and the other end of body of rod module (4) is connected by banjo fixing butt jointing module (5) traction Hooking module (6).
A kind of aircraft traction apparatus the most according to claim 1, it is characterized in that: described traction buffer module (1) includes bail (101), bail (101) is connected with connecting rod (103) by safety bolt (102), multiple dividing plate (104) it is set with in connecting rod (103), being provided with cushion pad (105) between dividing plate (104), the two ends of cushion pad (105) are positioned by the block (106) being fixed in connecting rod (103).
A kind of aircraft traction apparatus the most according to claim 2, it is characterised in that: described cushion pad (105) uses vulcanized rubber material to make.
A kind of aircraft traction apparatus the most according to claim 1, it is characterised in that: described body of rod module (4) uses carbon fiber pipe material to make.
A kind of aircraft traction apparatus the most according to claim 1, it is characterized in that: described Quick butt joint (2) includes front band (201), front band (201) constitutes bearing pin by bearing pin (202) with lower catch hoop (203) and is connected, the other end of described lower catch hoop (203) is hinged with threaded post (204), described threaded post (204) constitutes screw-driven with the nut sleeve (205) of front band (201) other end and is connected, described Quick butt joint (2) also includes positioning core axle (206), the positioning core axle (206) location docking between two body of rod modules (4).
A kind of aircraft traction apparatus the most according to claim 1, it is characterized in that: described walking assembly (3) includes wheel shaft (301), the two ends of wheel shaft (301) are provided with wheel (302), the center of described wheel shaft (301) is installed with support (304), support (304) is connected by Quick-release pin (303) hook (305), and hook (305) is connected with the clip (7) being fixed in body of rod module (4).
A kind of aircraft traction apparatus the most according to claim 6, it is characterised in that: described wheel (302) uses polyurethane material to make.
A kind of aircraft traction apparatus the most according to claim 6, it is characterised in that: being machined with multiple pin shaft hole on described support (304), Quick-release pin (303) can match from different pin shaft holes and change the setting height(from bottom) of hook (305).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620109194.3U CN205525031U (en) | 2016-02-03 | 2016-02-03 | Aircraft draw gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620109194.3U CN205525031U (en) | 2016-02-03 | 2016-02-03 | Aircraft draw gear |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205525031U true CN205525031U (en) | 2016-08-31 |
Family
ID=56776635
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620109194.3U Active CN205525031U (en) | 2016-02-03 | 2016-02-03 | Aircraft draw gear |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205525031U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106882396A (en) * | 2017-03-17 | 2017-06-23 | 南京工业职业技术学院 | A kind of traction buffer unit and plane draw bar on plane draw bar |
| CN107117184A (en) * | 2017-06-23 | 2017-09-01 | 中车资阳机车有限公司 | A kind of shipping motor-car even worries leading-in device |
| CN107117185A (en) * | 2017-06-23 | 2017-09-01 | 中车资阳机车有限公司 | A kind of type hand even hangs buffer structure |
| CN107139961A (en) * | 2017-06-23 | 2017-09-08 | 中车资阳机车有限公司 | A kind of semi-automatic even hangs buffer structure |
| CN107386022A (en) * | 2017-01-11 | 2017-11-24 | 中国铁建高新装备股份有限公司 | A kind of online milling car of portable rail of subway |
-
2016
- 2016-02-03 CN CN201620109194.3U patent/CN205525031U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107386022A (en) * | 2017-01-11 | 2017-11-24 | 中国铁建高新装备股份有限公司 | A kind of online milling car of portable rail of subway |
| CN106882396A (en) * | 2017-03-17 | 2017-06-23 | 南京工业职业技术学院 | A kind of traction buffer unit and plane draw bar on plane draw bar |
| CN107117184A (en) * | 2017-06-23 | 2017-09-01 | 中车资阳机车有限公司 | A kind of shipping motor-car even worries leading-in device |
| CN107117185A (en) * | 2017-06-23 | 2017-09-01 | 中车资阳机车有限公司 | A kind of type hand even hangs buffer structure |
| CN107139961A (en) * | 2017-06-23 | 2017-09-08 | 中车资阳机车有限公司 | A kind of semi-automatic even hangs buffer structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN205525031U (en) | Aircraft draw gear | |
| US9132999B2 (en) | Method of connecting crane suspension assembly sections together and frame mounted assembly used therefore | |
| US2260676A (en) | Boat trailer | |
| US20180370618A1 (en) | Heavy-lift unmanned aerial vehicle landing gear system | |
| CN102139758A (en) | Removable support for carrying an external optional equipment on an aircraft and aircraft fitted with the support | |
| CN201647865U (en) | Self lifting expansion crane device | |
| CN211943754U (en) | Device for hanging goods outside helicopter | |
| CN109677584A (en) | DCB Specimen unmanned aerial vehicle body | |
| CN102303625A (en) | Assembling device and disassembling device for split-type traction link of locomotive | |
| CN211139653U (en) | Unmanned aerial vehicle undercarriage with fast structure of rolling over | |
| CN216272659U (en) | Main transformer sleeve hoisting balancing tool | |
| CN210499981U (en) | Front ring dismounting vehicle for aircraft engine | |
| US5873588A (en) | Assembled sail powered vehicle | |
| CN205422554U (en) | From rig unit head slide of taking buffer gear | |
| CN210191663U (en) | Semitrailer bearing gooseneck | |
| CN207000144U (en) | The right suspension of horizontal power assembly | |
| CN109747786A (en) | 400 tons of pulling winch support constructions and installation method in ocean engineering cabin | |
| CN206503084U (en) | A kind of lightweight oil gas platform helicopter deck supporting construction | |
| CN102745604B (en) | Crawler crane | |
| CN205772897U (en) | The movable pulley yoke of marine crane | |
| CN213566546U (en) | Unmanned helicopter test bed | |
| CN211223832U (en) | Composite material telescopic airstairs | |
| CN205273833U (en) | Four rotor craft structure reinforcing apparatus | |
| CN214029190U (en) | Foldable draw bar with buffering function for unmanned aerial vehicle | |
| CN205930072U (en) | Traction device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| CB03 | Change of inventor or designer information |
Inventor after: Tang Wanshou Inventor after: Lai Jianzheng Inventor after: Li Guangyou Inventor after: Lin Fengsen Inventor after: Liu Changbo Inventor before: Tang Wanshou Inventor before: Lai Jianzheng |
|
| COR | Change of bibliographic data | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20160912 Address after: 444100 Hubei province Yichang city mayor of Osaka Dangyang Road No. 2 Patentee after: No.571 Plant of PLA Patentee after: WEIHAI GUANGWEI COMPOSITES CO., LTD. Address before: 444100 Hubei province Yichang city mayor of Osaka Dangyang Road No. 2 Patentee before: No.571 Plant of PLA |