CN211076380U - Hydraulic rear wheel steering system for aircraft traction device - Google Patents
Hydraulic rear wheel steering system for aircraft traction device Download PDFInfo
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- CN211076380U CN211076380U CN201921640929.5U CN201921640929U CN211076380U CN 211076380 U CN211076380 U CN 211076380U CN 201921640929 U CN201921640929 U CN 201921640929U CN 211076380 U CN211076380 U CN 211076380U
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- rear wheel
- piston rod
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Abstract
The utility model discloses a hydraulic pressure rear wheel steering system for aircraft draw gear, including directive wheel assembly, flexible hydro-cylinder and rack and pinion mechanism, the directive wheel assembly includes directive wheel, steering support and slew bearing, steering support passes through the wheel fork to be fixed on the wheel hub of directive wheel, slew bearing fixes on the steering support, and flexible hydro-cylinder includes piston rod joint, piston rod and hydro-cylinder, piston rod joint fixes on the slew bearing lateral wall, piston portion joint and piston rod swing joint, rack and pinion structure include rack bar, gear and connecting rod, rack bar includes pole portion and rack, pole portion one end cup joints in the hydro-cylinder, the pole portion other end and rack fixed connection, be fixed with supporting mechanism on the hydro-cylinder outer wall, be fixed with supporting mechanism on the rack outer wall; the utility model discloses a rear wheel hydraulic steering system can realize controlling independent overall arrangement, and makes rear wheel steering friction bigger, turns to more in a flexible way, and it is little to turn to the radius.
Description
Technical Field
The utility model relates to an aircraft tractor field especially relates to a hydraulic pressure rear wheel steering system for aircraft draw gear.
Background
At present, in the field of aircraft tractors, particularly, rear wheel steering systems are rarely adopted when rodless negative-carrying type online devices are adopted, mainly because a traction device can only adopt a rear wheel layout in a left-right independent separation mode when being connected with front wheels or front landing gears of an aircraft, a steering shaft is lacked between the left rear wheel and the right rear wheel, synchronous steering of the steering wheels needs to be controlled by a synchronous system, and other traction devices generally adopt front wheel steering to avoid similar problems, so that the development risk can be greatly reduced, and the manufacturing cost can be controlled. However, the front wheel steering system is prone to the phenomena of head pushing (insufficient steering), so that the turning radius is increased, the operation procedure of the aircraft traction device is complex, the efficiency is low, the accuracy is insufficient, the man-machine effect is low, and the like.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a hydraulic pressure rear wheel steering system for aircraft draw gear to solve the problem that above-mentioned prior art exists, make rear wheel hydraulic pressure steering system can realize controlling independent overall arrangement, and make rear wheel steering friction bigger, turn to efficiently, turn to more nimble, turn to the radius little, under the unchangeable circumstances of efficiency of guaranteeing to turn to, the directive wheel can be more miniaturized, reduces whole car weight.
In order to achieve the above object, the utility model provides a following scheme: the utility model provides a hydraulic pressure rear wheel steering system for aircraft draw gear, its characterized in that: the steering wheel assembly comprises a steering wheel assembly, a telescopic oil cylinder and a rack and pinion mechanism, wherein the steering wheel assembly comprises a wheel hub of a steering wheel, a steering support and a rotary bearing, the steering support is fixed on the steering wheel through a wheel fork, the rotary bearing is fixed on the steering support, the telescopic oil cylinder comprises a piston rod joint, a piston rod and an oil cylinder, the piston rod joint is fixed on the side wall of the rotary bearing, the piston part joint is movably connected with the piston rod, the rack and pinion structure comprises a rack rod, a gear and a connecting rod, the rack rod comprises a rod part and a rack, one end of the rod part is sleeved in the oil cylinder, the other end of the rod part is fixedly connected with the rack, a supporting mechanism is fixed on the outer walls of the oil cylinder and the rack, the supporting mechanism comprises a first fastening part, a second fastening part and a supporting part, the first fastening part is fixed on the supporting, the supporting part is fixed on the outer wall of the rack.
Preferably, the first fastening part includes two side plates fixed relatively to the support part.
Preferably, the first fastening portion is integrally formed with the support portion.
Preferably, a plurality of second fastening portions are buckled on the supporting portion, and the number of the second fastening portions is 2-4.
Preferably, a rubber pad is fixed on the inner wall of the first fastening part and the inner wall of the supporting part.
The utility model discloses a following technological effect: the utility model discloses a hydraulic pressure rear wheel steering system adopts the mode that the left and right wheels separately independent overall arrangement, and it is big to solve aircraft draw gear turn radius in the past, and operating procedure is complicated, and is inefficient, and the precision is not enough, and man-machine effect hangs down the scheduling problem, realizes aircraft draw gear's nimble quick traction aircraft, promotes the improvement of aircraft ground guarantee quality, especially has higher military value in the military aviation field, adopts the utility model discloses rear wheel steering system left and right wheels separately independent overall arrangement's mode for the rear steering wheel is closer with the distance that is lifted up between aircraft wheel or the undercarriage, and aircraft fuselage weight more is close to directive wheel (rear wheel), and rear wheel steering friction is bigger, and steering efficiency is higher, turns to more in a flexible way, and turn to the radius for a short time, under the unchangeable circumstances of assurance steering efficiency, the directive wheel can be more miniaturized, reduces.
In addition, it has been found through research that a vehicle employing a rear wheel steering system is prone to "drift" during turning, which reduces the steering accuracy of the vehicle. Because the utility model discloses an aircraft draw gear of rear wheel steering system belongs to the rodless aircraft draw gear that adopts the negative online device of carrying, at the traction aircraft in-process, draw gear and aircraft nose wheel or nose landing gear interact, the nose landing gear of aircraft lifts off the ground, some quality of aircraft shifts to on the draw gear, at this moment the rear steering wheel is because more being close to the new focus of aircraft, the atress increases, and frictional force between the ground also increases, make the draw gear's of adopting rear wheel steering system "tail flick" effort weaken greatly, turn to accurate nature and obtain promoting by a wide margin.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without inventive labor.
Fig. 1 is a schematic structural view of a rear wheel steering system of the present invention;
fig. 2 is a front view of the support mechanism of the present invention;
fig. 3 is a top view of the support mechanism of the present invention;
fig. 4 is a left side view of the support mechanism of the present invention;
wherein, 1-a steering support; 2-a steering wheel; 3-a piston rod joint; 4-a piston rod; 5-oil cylinder; 6-rack bar; 7-a slew bearing; 8-a first fastening portion; 9-a second fastening portion; 10-a support; 11-a connecting rod; 12-a gear; 13-a rack; 14-a stem portion; 15-a support mechanism; 16-a rubber pad; 17-wheel fork.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
In order to make the above objects, features and advantages of the present invention more comprehensible, the present invention is described in detail with reference to the accompanying drawings and the detailed description.
As shown in fig. 1-4, the present invention provides a hydraulic rear wheel steering system for an aircraft towing device, comprising a steering wheel assembly, a telescopic cylinder and a rack-and-pinion mechanism, wherein the steering wheel assembly comprises a steering wheel 2, a steering bracket 1 and a rotary bearing 7, the steering bracket 1 is fixed on a wheel hub of the steering wheel 2 through a wheel fork 17, the rotary bearing 7 is fixed on the steering bracket 1, the telescopic cylinder comprises a piston rod joint 3, a piston rod 4 and a cylinder 5, the piston rod joint 3 is fixed on a side wall of the rotary bearing 7, the piston part joint 3 is movably connected with the piston rod 4, the rack-and-pinion mechanism comprises a rack rod 6, a gear 12 and a connecting rod 11, the rack rod 6 comprises a rod part 14 and a rack 13, one end of the rod part 14 is sleeved in the cylinder 5, the other end of the rod part 14 is fixedly connected with the rack 13, so that the hydraulic, meanwhile, the same steering wheel assemblies and telescopic oil cylinders are arranged at the two ends of the connecting rod 11, and the hydraulic rear wheel steering system in a left-right independent layout mode is obtained by matching the same steering wheel assemblies and telescopic oil cylinders at the left and right sides with the gears 12 and the racks 13 at the two ends, so that the balance of the vehicle during turning can be kept when the vehicle turns, and the vehicle turns more stably; and a supporting mechanism 15 is fixed on the outer walls of the oil cylinder 5 and the rack 13 so as to improve the stability of the hydraulic rear wheel steering system, the supporting mechanism 15 comprises a first fastening part 8, a second fastening part 9 and a supporting part 10, the first fastening part 8 is fixed on the supporting part 10, and the second fastening part 9 is buckled on the supporting part 10.
Further optimization scheme, in order to make rack and pinion mechanism and flexible hydro-cylinder be connected more tightly, in order to guarantee that the vehicle is when turning, the turning strength can be guaranteed to hydraulic rear wheel steering system, rack and pinion mechanism and with flexible hydro-cylinder difficult separation and not fragile, be fixed with supporting part 10 on the 13 outer walls of rack, and the supporting part 10 other end is fixed in hydro-cylinder 5 below, make rack and pinion mechanism and be connected more firmly with flexible hydro-cylinder like this, when the realization turns to, make the vehicle more steady and can guarantee that the vehicle keeps balanced when turning.
Furthermore, in order to connect the rack 13 and the support portion 10 more stably, a plurality of second fastening portions 9 are fastened on the support portion 10, wherein the number of the second fastening portions 9 is 2-4, preferably 3, the second fastening portions 9 are fixed at equal intervals, and the distance between the second fastening portions 9 is 1cm-5cm, preferably 3 cm.
In a further preferred embodiment, in order to fasten the supporting mechanism 15 to the cylinder, the first fastening portion 8 is provided as two side plates oppositely disposed on the supporting portion 10, so that the two side plates can be tightly fastened to the cylinder 5.
Further optimize the scheme, for preventing the support mechanism 15 the condition of splitting appears when the vehicle takes place to turn to, set up first fastening 8 and supporting part 10 into integrated into one piece structure, simultaneously, in order to prevent to appear wearing and tearing between hydro-cylinder 5 and the supporting part 10, be fixed with rubber pad 16 on first fastening 8 and the supporting part 10 inner wall, when hydro-cylinder 5 relative motion like this, difficult emergence wearing and tearing improve hydro-cylinder 5 and support mechanism 15's life.
When the steering wheel synchronous steering device works, the steering wheel drives the steering column, the steering column is connected with the steering control oil valve, the steering control oil valve controls the oil inlet and outlet quantity of the left and right wheels to the two sides of the telescopic oil cylinder piston according to the rotation angle of the steering column, the left and right movement of the telescopic oil cylinder piston rod 4 is realized, the left and right steering wheel assemblies are driven to rotate, the steering is realized, meanwhile, the movement stroke of the left and right telescopic oil cylinder pistons is forced to be synchronous by utilizing the gear-rack meshing principle, the consistency of the rotation angles of the left and right steering wheel assemblies is achieved, and.
The utility model discloses a hydraulic pressure rear wheel steering system adopts the mode that the left and right wheels separately independent overall arrangement, and it is big to solve aircraft draw gear turn radius in the past, and operating procedure is complicated, and is inefficient, and the precision is not enough, and man-machine effect hangs down the scheduling problem, realizes aircraft draw gear's nimble quick traction aircraft, promotes the improvement of aircraft ground guarantee quality, especially has higher military value in the military aviation field, adopts the utility model discloses rear wheel steering system left and right wheels separately independent overall arrangement's mode for the rear steering wheel is closer with the distance that is lifted up between aircraft wheel or the undercarriage, and aircraft fuselage weight more is close to directive wheel (rear wheel), and rear wheel steering friction is bigger, and steering efficiency is higher, turns to more in a flexible way, and turn to the radius for a short time, under the unchangeable circumstances of assurance steering efficiency, the directive wheel can be more miniaturized, reduces.
In the description of the present invention, it is to be understood that the terms "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are merely for convenience of description of the present invention, and do not indicate or imply that the device or element so referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.
The above-mentioned embodiments are only intended to describe the preferred embodiments of the present invention, but not to limit the scope of the present invention, and those skilled in the art should also be able to make various modifications and improvements to the technical solution of the present invention without departing from the spirit of the present invention, and all such modifications and improvements are intended to fall within the scope of the present invention as defined in the appended claims.
Claims (5)
1. A hydraulic rear wheel steering system for an aircraft towing installation, characterized by: including directive wheel assembly, flexible hydro-cylinder and rack and pinion mechanism, the directive wheel assembly includes directive wheel (2), steering support (1) and slewing bearing (7), steering support (1) is fixed on the wheel hub of directive wheel (2) through wheel fork (17), slewing bearing (7) are fixed on steering support (1), flexible hydro-cylinder includes piston rod joint (3), piston rod (4) and hydro-cylinder (5), piston rod joint (3) are fixed on slewing bearing (7) lateral wall, piston rod joint (3) and piston rod (4) swing joint, rack and pinion structure includes rack bar (6), gear (12) and connecting rod (11), rack bar (6) includes pole portion (14) and rack (13), pole portion (14) one end cup joints in hydro-cylinder (5), pole portion (14) other end and rack (13) fixed connection, supporting mechanisms (15) are fixed on the outer walls of the oil cylinder (5) and the rack (13), each supporting mechanism (15) comprises a first fastening portion (8), a second fastening portion (9) and a supporting portion (10), the first fastening portions (8) are fixed on the supporting portions (10), the second fastening portions (9) are buckled on the supporting portions (10), and the supporting portions (10) are fixed on the outer walls of the racks (13).
2. The hydraulic rear wheel steering system for an aircraft towing attachment according to claim 1, wherein: the first fastening portion (8) comprises two side plates fixed relatively on the support portion (10).
3. The hydraulic rear wheel steering system for an aircraft towing attachment according to claim 1, wherein: the first fastening portion (8) is integrally formed with the support portion (10).
4. The hydraulic rear wheel steering system for an aircraft towing attachment according to claim 1, wherein: a plurality of second fastening parts (9) are buckled on the supporting part (10), and the number of the second fastening parts (9) is 2-4.
5. The hydraulic rear wheel steering system for an aircraft towing attachment according to claim 1, wherein: rubber pads (16) are fixed on the inner walls of the first fastening part (8) and the supporting part (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921640929.5U CN211076380U (en) | 2019-09-29 | 2019-09-29 | Hydraulic rear wheel steering system for aircraft traction device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921640929.5U CN211076380U (en) | 2019-09-29 | 2019-09-29 | Hydraulic rear wheel steering system for aircraft traction device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211076380U true CN211076380U (en) | 2020-07-24 |
Family
ID=71635806
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921640929.5U Active CN211076380U (en) | 2019-09-29 | 2019-09-29 | Hydraulic rear wheel steering system for aircraft traction device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211076380U (en) |
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2019
- 2019-09-29 CN CN201921640929.5U patent/CN211076380U/en active Active
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