CN111186590A - Multi-supporting-rod type aircraft wheel carrier - Google Patents
Multi-supporting-rod type aircraft wheel carrier Download PDFInfo
- Publication number
- CN111186590A CN111186590A CN202010081295.5A CN202010081295A CN111186590A CN 111186590 A CN111186590 A CN 111186590A CN 202010081295 A CN202010081295 A CN 202010081295A CN 111186590 A CN111186590 A CN 111186590A
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- Prior art keywords
- hub
- limiting
- face
- side plate
- wheel carrier
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- 230000000670 limiting effect Effects 0.000 claims abstract description 58
- 238000001125 extrusion Methods 0.000 claims abstract description 55
- 230000003139 buffering effect Effects 0.000 claims abstract description 19
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 230000003014 reinforcing effect Effects 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 21
- 230000000087 stabilizing effect Effects 0.000 abstract 1
- 239000000872 buffer Substances 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 238000005728 strengthening Methods 0.000 description 3
- 238000003466 welding Methods 0.000 description 3
- 230000007774 longterm Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000969 carrier Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/02—Ground or aircraft-carrier-deck installations for arresting aircraft, e.g. nets or cables
- B64F1/025—Ground or aircraft-carrier-deck installations for arresting aircraft, e.g. nets or cables using decelerating or arresting beds
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Tires In General (AREA)
Abstract
The invention relates to the technical field of airplane wheel frames, in particular to a multi-supporting-rod type airplane wheel frame, which comprises an airplane wheel hub, wherein the airplane wheel hub is arranged at the lower end of a connecting support, the airplane wheel hub is rotationally connected with the connecting support through a bearing rotating shaft, a right limiting frame is arranged on the right side of the airplane wheel hub, and a left limiting frame is arranged on the left side of the airplane wheel hub, and the airplane wheel frame has the advantages that: the left and right positions of the hub are fixed by arranging the pair of limiting frames which are bilaterally symmetrical, and the friction between the hub and the outer wall of the hub is increased by utilizing the movable extrusion block and the protrusions in the rotating clamp, so that the trend of relative rotation of the hub is reduced, and the limiting effect on the hub is improved; through the extrusion of a plurality of draw-in grooves to the wheel hub outer wall, realize stabilizing spacing effect, cooperation spacing bolt avoids wheel hub to rotate because inertia produces, avoids the wheel carrier to be extruded and destroys, utilizes the effect of spring and buffering supporting screw simultaneously, cushions the extrusion force to the protection wheel carrier is indeformable.
Description
Technical Field
The invention relates to the technical field of airplane wheel carriers, in particular to a multi-supporting-rod type airplane wheel carrier.
Background
The landing gear of the airplane is a device for supporting the gravity of the airplane and bearing corresponding loads when the airplane is parked, taxied, taken off, landed and run on the ground.
The aircraft is when stopping, need carry out the position to its undercarriage lower extreme wheel hub and prescribe a limit to, and then prevent that the aircraft from sliding and lead to the incident appearing, current stop device to aircraft wheel hub lacks the safety protection measure, the inertia of aircraft is great, when carrying out the position limit to aircraft wheel hub, in case because the problem of ground slope leads to wheel hub to change and produce relative rotation, under huge inertia effect, cause stop device to be destroyed easily, and can not play safety protection's effect, can't cushion to the effort that wheel hub produced relative rotation trend simultaneously, thereby under the extrusion that lasts, the wheel carrier that leads to spacing protection produces and warp.
Therefore, the multi-strut type aircraft wheel carrier is provided to solve the problems of stable support and buffering of inertia and rotation trend.
Disclosure of Invention
The invention aims to provide a multi-strut type aircraft wheel carrier to solve the problems in the background technology.
In order to achieve the purpose, the invention provides the following technical scheme:
a multi-supporting rod type airplane wheel carrier comprises an airplane wheel hub, wherein the airplane wheel hub is arranged at the lower end of a connecting support, the airplane wheel hub is rotatably connected with the connecting support through a bearing rotating shaft, a right limiting frame is arranged on the right side of the airplane wheel hub, a left limiting frame is arranged on the left side of the airplane wheel hub, a second clamping groove for fitting the right circular arc outer wall of the airplane wheel hub is formed in the left end face of the right limiting frame, a sliding groove is formed in the right side of the upper end face of the left limiting frame, a second side plate is perpendicularly welded on the left side of the upper end face of the left limiting frame, a first side plate is perpendicularly welded in the middle of the upper end face of the left limiting frame, a through hole penetrates through the left side and the right side of the middle position of the first side plate, a movable extrusion block is installed at the upper end of the sliding groove, a first clamping groove is formed in, the vertical welding in up end left side of activity extrusion piece has spacing curb plate, and the rotation clamp is installed on the upper end right side of activity extrusion piece, and the up end right side of activity extrusion piece is provided with first locating hole, the fixed platform that rotates that is provided with of right side lower extreme of spacing curb plate, rotate the clamp and rotate and install on the right side of rotating the platform, rotate the right side of clamp and be provided with the third draw-in groove, rotate the left side circular arc outer wall intermediate position of clamp and offer horizontal screw hole left, rotate the lower extreme intermediate position of clamp and offer the second locating hole, screw hole internal thread rotates and is connected with buffering supporting screw, the coincidence of second locating hole and first locating hole, and the second locating hole and the first locating hole interpolation install the spacer pin.
Preferably, the right side of the right limiting frame and the left side of the left limiting frame are both provided with triangular reinforcing ribs, and the right side of the right limiting frame and the upper end face of the left side of the left limiting frame are both provided with fixing screws connected with the ground.
Preferably, the first clamping groove, the second clamping groove and the third clamping groove are all attached to the arc outer wall of the airplane hub, and a plurality of bulges distributed in a circumferential array are arranged in the inner cavities of the first clamping groove, the second clamping groove and the third clamping groove.
Preferably, the lower end face of the movable extrusion block is provided with a sliding block, and the sliding block is slidably mounted inside a sliding groove with a T-shaped section.
Preferably, the cylinder is fixedly installed on the right end face of the second side plate, the telescopic rod of the cylinder penetrates through the through hole in the middle of the first side plate, and the end part of the telescopic rod of the cylinder is fixedly connected to the middle of the left end face of the movable extrusion block.
Preferably, the upper end of the first side plate is provided with a limiting hole in a left-right penetrating mode, the limiting rod penetrates through the inner cavity of the limiting hole in an inserting mode, and the left end of the limiting rod is fixedly installed on the left end face of the first side plate through a locking nut.
Preferably, the inner chamber fixed mounting who rotates the platform has the connecting rod, the left side of rotating the clamp is provided with rotates the ear seat, it rotates the outer wall of installing at the connecting rod to rotate the ear seat.
Preferably, the upper end of the limiting side plate is provided with a through hole penetrating through the left and right at the same height as the threaded hole, the left end of the buffering support screw rod is inserted into an inner cavity of the through hole, and the left end of the buffering support screw rod is fixedly mounted on the left end face of the limiting side plate through a locking nut.
Preferably, the middle end of the buffering support screw rod is sleeved with a spring, one end of the spring is abutted to the right end face of the limiting side plate, and the other end of the spring is abutted to the arc outer wall of the rotating hoop.
Compared with the prior art, the invention has the beneficial effects that:
1. the left and right positions of the hub are fixed by arranging the pair of limiting frames which are bilaterally symmetrical, and the friction between the hub and the outer wall of the hub is increased by utilizing the movable extrusion block and the protrusions in the rotating clamp, so that the trend of relative rotation of the hub is reduced, and the limiting effect on the hub is improved;
2. the invention realizes the effect of stable limit by extruding the outer wall of the hub through the plurality of clamping grooves, avoids the rotation of the hub due to inertia by matching with the limit bolt, avoids the wheel carrier from being damaged by extrusion, and simultaneously buffers the extrusion force by utilizing the action of the spring and the buffer support screw rod, thereby protecting the wheel carrier from deformation.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic perspective view of a movable extrusion block according to the present invention;
FIG. 3 is a schematic perspective view of a rotating yoke according to the present invention;
FIG. 4 is a schematic view of a three-dimensional structure of the connection between the rotating clamp and the movable extrusion block of the present invention;
FIG. 5 is a schematic view of a right stop frame according to the present invention;
fig. 6 is a schematic perspective view of the left stop of the present invention.
In the figure: 1. an aircraft hub; 2. connecting a bracket; 3. a bearing shaft; 4. a right limit bracket; 5. a left limiting frame; 6. a movable extrusion block; 7. rotating the clamp; 8. a triangular reinforcing rib; 9. a set screw; 10. a slider; 11. a chute; 12. a first side plate; 13. a second side plate; 14. a cylinder; 15. a through hole; 16. a limiting rod; 17. a connecting rod; 18. a spacing pin; 19. a buffer support screw; 20. a spring; 21. a limiting side plate; 22. a through hole; 23. a rotating table; 24. a first positioning hole; 25. a first card slot; 26. a protrusion; 27. a threaded hole; 28. a second positioning hole; 29. rotating the ear seat; 30. a second card slot; 31. a limiting hole; 32. and a third card slot.
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.
Referring to fig. 1 to 6, the present invention provides a technical solution:
a multi-supporting-rod type airplane wheel carrier comprises an airplane wheel hub 1, wherein the airplane wheel hub 1 is installed at the lower end of a connecting support 2, and the airplane wheel hub 1 is rotatably connected with the connecting support 2 through a bearing rotating shaft 3.
Aircraft wheel hub 1's right side is provided with right spacing 4, aircraft wheel hub 1's left side is provided with left spacing 5, right spacing 4's right side and left spacing 5's left side all are provided with triangle strengthening rib 8, and right spacing 4's right side and left spacing 5's left up end all are provided with set screw 9 and are connected with ground, utilize the anti extruded intensity of triangle strengthening rib 8 increase left and right sides, utilize right spacing 4's right side and left spacing 5 to realize the injecing to aircraft wheel hub 1 left and right sides position.
The right side of the upper end face of the left limiting frame 5 is provided with a sliding groove 11, a movable extrusion block 6 is installed at the upper end of the sliding groove 11, a sliding block 10 is arranged on the lower end face of the movable extrusion block 6, the sliding block 10 is installed inside the sliding groove 11 with the T-shaped cross section in a sliding mode, and the sliding installation of the movable extrusion block 6 is achieved through the cooperation of the sliding block 10 and the sliding groove 11.
The second curb plate 13 has vertically been welded in the up end left side of left spacing 5, vertically welded first curb plate 12 in the middle of the up end of left spacing 5, it is provided with through-hole 15 to run through about the intermediate position of first curb plate 12, the left side of activity extrusion piece 6 is connected with cylinder 14 perpendicularly, 14 fixed mounting of cylinder is at the right-hand member face of second curb plate 13, the telescopic link of cylinder 14 runs through the through-hole 15 of first curb plate 12 intermediate position, 14 telescopic link tip fixed connection of cylinder is in the middle of the left end face of activity extrusion piece 6, utilize cylinder 14 to promote the motion left of activity extrusion piece 6, thereby make the extrusion of activity extrusion piece 6 fix the outer wall at aircraft wheel hub 1 left side lower extreme.
The left end face upper end of activity extrusion piece 6 is fixed welding perpendicularly left has gag lever post 16, runs through about the upper end of first curb plate 12 and is provided with spacing hole 31, gag lever post 16 runs through the inner chamber of grafting at spacing hole 31, and the left end of gag lever post 16 passes through lock nut fixed mounting at the left end face of first curb plate 12, utilizes gag lever post 16 and lock nut's cooperation, realizes further locking the 6 extrusion positions of activity extrusion piece to improve the stability of injecing aircraft wheel hub 1 position.
The right side of the upper end face of the movable extrusion block 6 is provided with a first positioning hole 24, the right side of the rotary clamp 7 is provided with a third clamping groove 32, a second positioning hole 28 is formed in the middle of the lower end of the rotary clamp 7, the second positioning hole 28 coincides with the first positioning hole 24, a limiting pin 18 is inserted in the second positioning hole 28 and the first positioning hole 24, the limiting pin 18 is used for limiting the rotation angle of the rotary clamp 7, and therefore the rotary clamp 7 is fixedly extruded on the outer wall of the upper end of the left side of the airplane hub 1.
The middle position of the left arc outer wall of the rotary hoop 7 is provided with a horizontal leftward threaded hole 27, a buffering support screw 19 is rotatably connected in the threaded hole 27, a left through hole 22 which penetrates through the upper end of the limiting side plate 21 and the threaded hole 27 in the same height is formed, the left end of the buffering support screw 19 is inserted into the inner cavity of the through hole 22, the left end of the buffering support screw 19 is fixedly installed on the left end face of the limiting side plate 21 through a locking nut, the rotation of the rotary hoop 7 is further limited by the buffering support screw 19, meanwhile, horizontal supporting force is provided for the rotary hoop 7, therefore, the airplane hub 1 can not rotate freely, and the purpose that the wheel carrier is protected from being damaged by rotary extrusion is.
The middle end of the buffering support screw rod 19 is sleeved with a spring 20, one end of the spring 20 abuts against the right end face of the limiting side plate 21, the other end of the spring 20 abuts against the arc outer wall of the rotating hoop 7, the spring 20 is used for buffering the extrusion force generated when the aircraft hub 1 generates a relative rotation trend, effective buffering of the extrusion force is achieved, and the wheel carrier deformation caused by long-term extrusion is avoided.
The left end face of the right limiting frame 4 is provided with a second clamping groove 30 which is attached to the right circular arc outer wall of the airplane hub 1, the right side of the movable extrusion block 6 is provided with a first clamping groove 25, the second clamping groove 30 and the third clamping groove 32 are attached to the circular arc outer wall of the airplane hub 1, the first clamping groove 25, the inner cavities of the second clamping groove 30 and the third clamping groove 32 are provided with a plurality of bulges 26 distributed in a circumferential array mode, the bulges 26 are utilized to increase friction with the outer wall of the airplane hub 1, therefore, the trend of relative rotation of the airplane hub 1 is reduced, and the limiting effect on the airplane hub 1 is improved.
The working principle is as follows: at first, utilize triangle strengthening rib 8 to increase the anti extruded intensity of the left and right sides, utilize the right side of right spacing frame 4 and left spacing frame 5 to realize injecing aircraft wheel hub 1 left and right sides position, utilize the cooperation of slider 10 and spout 11, realize the slidable mounting of activity extrusion piece 6, utilize cylinder 14 to promote activity extrusion piece 6 and move left, thereby make activity extrusion piece 6 extrusion fix the outer wall at aircraft wheel hub 1 left side lower extreme, utilize the cooperation of gag lever post 16 and lock nut, realize further locking activity extrusion piece 6 extrusion position, thereby improve the stability of injecing aircraft wheel hub 1 position.
The rotating installation of the rotating hoop 7 at the upper end of the movable extrusion block 6 is realized by utilizing the rotating fit between the connecting rod 17 on the rotating table 23 and the rotating lug seat 29, the rotating angle of the rotating hoop 7 is limited by utilizing the limiting pin 18, so that the rotating hoop 7 is fixedly extruded on the outer wall at the upper end of the left side of the airplane hub 1, the rotation of the rotating hoop 7 is further limited by utilizing the buffering support screw rod 19, meanwhile, the transverse supporting force is provided for the rotating hoop 7, the airplane hub 1 can not rotate freely, the aim of protecting the wheel frame from being damaged by rotating extrusion is achieved, the extrusion force generated when the airplane hub 1 generates a relative rotation trend is buffered by utilizing the spring 20, the effective buffering of the extrusion force is realized, the deformation of the wheel frame caused by long-term extrusion is avoided, the friction between the bulge 26 and the outer wall of the airplane hub 1, the limiting effect on the airplane hub 1 is improved.
The cylinder 14 adopts the following types: SC 40-25-S.
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 (9)
1. A multi-strut aircraft wheel carrier comprises an aircraft wheel hub (1), and is characterized in that: the aircraft hub (1) is arranged at the lower end of the connecting support (2), the aircraft hub (1) is rotatably connected with the connecting support (2) through the bearing rotating shaft (3), the right side of the aircraft hub (1) is provided with a right limiting frame (4), the left side of the aircraft hub (1) is provided with a left limiting frame (5), the left end face of the right limiting frame (4) is provided with a second clamping groove (30) which is attached to the right circular arc outer wall of the aircraft hub (1), the right side of the upper end face of the left limiting frame (5) is provided with a sliding groove (11), the left side of the upper end face of the left limiting frame (5) is vertically welded with a second side plate (13), a first side plate (12) is vertically welded in the middle of the upper end face of the left limiting frame (5), through holes (15) are arranged on the left and right sides of the middle position of the first side plate (12), and, the right side of the movable extrusion block (6) is provided with a first clamping groove (25), the left side of the movable extrusion block (6) is vertically connected with an air cylinder (14), the upper end of the left end face of the movable extrusion block (6) is vertically and leftwards fixedly welded with a limiting rod (16), the left side of the upper end face of the movable extrusion block (6) is vertically welded with a limiting side plate (21), the right side of the upper end of the movable extrusion block (6) is provided with a rotating hoop (7), the right side of the upper end face of the movable extrusion block (6) is provided with a first positioning hole (24), the lower end of the right side of the limiting side plate (21) is fixedly provided with a rotating table (23), the rotating hoop (7) is rotatably arranged on the right side of the rotating table (23), the right side of the rotating hoop (7) is provided with a third clamping groove (32), and the, second locating hole (28) have been seted up to the lower extreme intermediate position of rotating clamp (7), screw hole (27) internal thread rotates and is connected with buffering supporting screw (19), second locating hole (28) and first locating hole (24) coincidence, and second locating hole (28) and first locating hole (24) interpolation are installed and are spacing round pin (18).
2. The multi-strut aircraft wheel carrier of claim 1, wherein: the right side of the right limiting frame (4) and the left side of the left limiting frame (5) are provided with triangular reinforcing ribs (8), and the right side of the right limiting frame (4) and the left upper end face of the left limiting frame (5) are provided with fixing screws (9) which are connected with the ground.
3. The multi-strut aircraft wheel carrier of claim 1, wherein: the first clamping groove (25), the second clamping groove (30) and the third clamping groove (32) are attached to the outer wall of an arc of the airplane hub (1), and a plurality of protrusions (26) distributed in a circumferential array mode are arranged in inner cavities of the first clamping groove (25), the second clamping groove (30) and the third clamping groove (32).
4. The multi-strut aircraft wheel carrier of claim 1, wherein: the lower end face of the movable extrusion block (6) is provided with a sliding block (10), and the sliding block (10) is slidably mounted inside a sliding groove (11) with a T-shaped section.
5. The multi-strut aircraft wheel carrier of claim 1, wherein: the cylinder (14) is fixedly installed on the right end face of the second side plate (13), a telescopic rod of the cylinder (14) penetrates through a through hole (15) in the middle of the first side plate (12), and the end portion of the telescopic rod of the cylinder (14) is fixedly connected to the middle of the left end face of the movable extrusion block (6).
6. The multi-strut aircraft wheel carrier of claim 1, wherein: the left end and the right end of the first side plate (12) are provided with limiting holes (31) in a penetrating mode, the limiting rod (16) penetrates through an inner cavity of the limiting holes (31) in an inserting mode, and the left end of the limiting rod (16) is fixedly installed on the left end face of the first side plate (12) through a locking nut.
7. The multi-strut aircraft wheel carrier of claim 1, wherein: the inner chamber fixed mounting who rotates platform (23) has connecting rod (17), the left side of rotating clamp (7) is provided with rotates ear seat (29), it rotates the outer wall of installing at connecting rod (17) to rotate ear seat (29).
8. The multi-strut aircraft wheel carrier of claim 1, wherein: the upper end of the limiting side plate (21) is provided with a through hole (22) which penetrates through the left and right at the same height position as the threaded hole (27), the left end of the buffering support screw rod (19) is inserted into an inner cavity of the through hole (22), and the left end of the buffering support screw rod (19) is fixedly installed on the left end face of the limiting side plate (21) through a locking nut.
9. The multi-strut aircraft wheel carrier of claim 1, wherein: the middle end of the buffering support screw rod (19) is sleeved with a spring (20), one end of the spring (20) abuts against the right end face of the limiting side plate (21), and the other end of the spring (20) abuts against the arc outer wall of the rotating hoop (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010081295.5A CN111186590A (en) | 2020-02-06 | 2020-02-06 | Multi-supporting-rod type aircraft wheel carrier |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010081295.5A CN111186590A (en) | 2020-02-06 | 2020-02-06 | Multi-supporting-rod type aircraft wheel carrier |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111186590A true CN111186590A (en) | 2020-05-22 |
Family
ID=70705012
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010081295.5A Pending CN111186590A (en) | 2020-02-06 | 2020-02-06 | Multi-supporting-rod type aircraft wheel carrier |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111186590A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030165375A1 (en) * | 2000-06-26 | 2003-09-04 | Magnus Johansson | Traction vehicle for aircraft and engagement and hoisting device therefor |
| US20080089766A1 (en) * | 2006-10-13 | 2008-04-17 | Hammonds Technical Services, Inc. | Omni-Directional Towbarless Aircraft Transporter and Method for Moving Aircraft |
| CN204507249U (en) * | 2015-02-13 | 2015-07-29 | 河南宜和城保装备科技实业有限公司 | What be applied to undercarriage fault emergency rescue device embraces latch mechanism |
| CN204507294U (en) * | 2015-02-13 | 2015-07-29 | 河南宜和城保装备科技实业有限公司 | Aircraft landing gear fault emergency escape runway deliverance apparatus |
| CN107054681A (en) * | 2017-02-28 | 2017-08-18 | 天津航天机电设备研究所 | Non-rod aircraft tractor |
| CN208102373U (en) * | 2018-04-18 | 2018-11-16 | 泊鹭（荆门）飞机有限公司 | A kind of small-sized amphibious aircraft traction device |
| CN110615116A (en) * | 2019-09-29 | 2019-12-27 | 北京航瑞达科技有限公司 | Novel electric traction device of double-rudder hydraulic steering clamp type for airplane |
-
2020
- 2020-02-06 CN CN202010081295.5A patent/CN111186590A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030165375A1 (en) * | 2000-06-26 | 2003-09-04 | Magnus Johansson | Traction vehicle for aircraft and engagement and hoisting device therefor |
| US20080089766A1 (en) * | 2006-10-13 | 2008-04-17 | Hammonds Technical Services, Inc. | Omni-Directional Towbarless Aircraft Transporter and Method for Moving Aircraft |
| CN204507249U (en) * | 2015-02-13 | 2015-07-29 | 河南宜和城保装备科技实业有限公司 | What be applied to undercarriage fault emergency rescue device embraces latch mechanism |
| CN204507294U (en) * | 2015-02-13 | 2015-07-29 | 河南宜和城保装备科技实业有限公司 | Aircraft landing gear fault emergency escape runway deliverance apparatus |
| CN107054681A (en) * | 2017-02-28 | 2017-08-18 | 天津航天机电设备研究所 | Non-rod aircraft tractor |
| CN208102373U (en) * | 2018-04-18 | 2018-11-16 | 泊鹭（荆门）飞机有限公司 | A kind of small-sized amphibious aircraft traction device |
| CN110615116A (en) * | 2019-09-29 | 2019-12-27 | 北京航瑞达科技有限公司 | Novel electric traction device of double-rudder hydraulic steering clamp type for airplane |
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Application publication date: 20200522 |
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