CN112389641A - Connecting rod transmission type front wheel turning anti-swing mechanism - Google Patents
Connecting rod transmission type front wheel turning anti-swing mechanism Download PDFInfo
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- CN112389641A CN112389641A CN202011200061.4A CN202011200061A CN112389641A CN 112389641 A CN112389641 A CN 112389641A CN 202011200061 A CN202011200061 A CN 202011200061A CN 112389641 A CN112389641 A CN 112389641A
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- landing gear
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- 230000007246 mechanism Effects 0.000 title claims abstract description 66
- 230000005540 biological transmission Effects 0.000 title claims abstract description 47
- 229910000831 Steel Inorganic materials 0.000 claims description 10
- 239000010959 steel Substances 0.000 claims description 10
- 239000000463 material Substances 0.000 claims description 6
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
- 239000003638 chemical reducing agent Substances 0.000 abstract description 4
- 230000033001 locomotion Effects 0.000 description 15
- 238000013016 damping Methods 0.000 description 6
- 239000003921 oil Substances 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009510 drug design Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000010687 lubricating oil Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 230000002441 reversible effect Effects 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/50—Steerable undercarriages; Shimmy-damping
-
- 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
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
- B64C25/36—Arrangements or adaptations of wheels, tyres or axles in general
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Steering-Linkage Mechanisms And Four-Wheel Steering (AREA)
Abstract
The invention discloses a connecting rod transmission type front wheel turning anti-swing mechanism, which comprises a turning actuator torque transmission mechanism, a plane connecting rod mechanism and a swing reducer, wherein the turning actuator torque transmission mechanism is connected with a front wheel through a connecting rod; the torque transmission mechanism of the turning actuator comprises a turning actuator, a torsion bar, a second support and a first support, wherein the turning actuator is connected with the outer barrel of the nose landing gear through the second support, a piston rod of the turning actuator is movably connected with a rocker arm end of the torsion bar, a rod body part of the torsion bar is hinged on the second support and a mounting lug of the outer barrel of the nose landing gear and can rotate around the axis of the turning actuator, the plane link mechanism comprises a double-lug connecting rod, a middle connecting rod, a ring body of the nose landing gear and a torsion arm, the double-lug connecting rod is connected with the bottom end of the rod body part of the torsion bar, an upper lug of the double-lug connecting rod is hinged with a shimmy damper, a lower lug of the double-lug connecting rod is connected with one end of the middle connecting rod, the other end of the middle connecting rod is.
Description
Technical Field
The invention belongs to the technical field of mechanism transmission of a nose wheel turning and anti-swing system of an aircraft landing gear, and particularly relates to a connecting rod transmission type nose wheel turning anti-swing mechanism.
Background
The general airplane realizes the steering control of the nose landing gear in the low-speed running stage through a nose wheel steering system, and prevents the nose wheel of the airplane from shimmy by switching to a shimmy reducing loop or providing enough dynamic damping by a shimmy reducer during high-speed running. At present, a large airplane is mainly provided with 2 turning actuators which are symmetrically arranged on a nose landing gear to drive the nose landing gear to realize turning operation; smaller aircraft usually drive the front wheel through a single turning actuator or a mechanism such as a pull rod and a steel cable which are arranged on the nose landing gear to realize turning operation. In order to achieve a turning angle required for the front wheels and a sufficient turning torque for driving the front wheels to turn, the turning actuator is large in size and length. For the aircraft with retractable landing gear, the motion of most front wheel steering actuators and the motion of a front landing gear ring body are basically in the same motion plane and are outside the aircraft body, and the landing gear retracts to enable the front wheel steering actuators to enter a front landing gear cabin, so that the aerodynamic appearance of the aircraft cannot be influenced. However, for the non-retractable nose landing gear, the front wheel steering actuator arranged outside can destroy the aerodynamic appearance after flying, generate larger aerodynamic resistance, reduce the aircraft range to a certain extent, increase the oil consumption and influence the aesthetic property at the same time. Therefore, for the aircraft with the retractable undercarriage, in order to avoid arranging the turning actuator outside the aircraft body, a transmission mechanism for movement between different planes is needed, so that the turning actuator can be arranged in the aircraft body above the nose undercarriage ring body, and the reasonable arrangement of the turning actuator is realized.
Disclosure of Invention
The purpose of the invention is as follows: to undercarriage extendible aircraft, in order to realize the developments when the turn manipulation of undercarriage and the high-speed of aircraft low-speed when sliding away prevent the pendulum function, and simultaneously, avoid the turn actuator to arrange and cause the turn actuator to be in the aircraft outside at nose undercarriage ring body coplanar, thereby influence the aerodynamic configuration of aircraft, cause great flight resistance, produce fuel economy scheduling problem and holistic aesthetic property, a connecting rod transmission formula nose wheel turns and prevents the pendulum mechanism, realize the rational arrangement of turn actuator. And the arrangement of the nose landing gear shimmy damper is facilitated through mechanisms such as a double-lug connecting rod and the like to realize the shimmy damping function. Meanwhile, through the reasonable design of the link mechanism, different transmission ratios can be realized, and the arrangement requirements of different airplane nose wheel steering systems are met.
The technical scheme of the invention is as follows:
a connecting rod transmission type front wheel turning anti-swing mechanism comprises a turning actuator torque transmission mechanism, a plane connecting rod mechanism and a swing reducer (12); the turning actuator torque transmission mechanism comprises a turning actuator (1), a torsion bar (5), a second support (4) and a first support (3), wherein the turning actuator (1) is connected onto a nose landing gear outer barrel (13) through the second support (4) and the first support (3), a piston rod (2) of the turning actuator is movably connected with a rocker arm end of the torsion bar (5), a rod body part of the torsion bar (5) is hinged onto a third mounting lug (16) of the second support (4) and the nose landing gear outer barrel (13) and can rotate around the axis of the torsion bar, the plane connecting rod mechanism comprises a double-lug connecting rod (7), a middle connecting rod (9), a nose landing gear ring body (10) and a torsion arm (11), the double-lug connecting rod (7) is fixedly connected with the bottom end of the rod body part of the torsion bar (5), an upper connecting lug of the double-lug connecting rod (7) is hinged with a shimmy damper (12), the lower part of the double-lug connecting rod (7) is connected with one end of a middle connecting rod (9), the other end of the middle connecting rod (9) is connected with a nose landing gear ring body (10), the nose landing gear ring body (10) is arranged on a nose landing gear outer cylinder (13) and can rotate around the nose landing gear outer cylinder (13), and one end of a torsion arm (11) is connected outside the nose landing gear ring body (10).
Furthermore, the other end of the torque arm (11) is connected with the inner barrel of the nose landing gear.
Furthermore, the first support (3) is fixed on the outer barrel (13) of the nose landing gear through a first mounting lug (14), and the second support (4) is fixed on the outer barrel (13) of the nose landing gear through a second mounting lug (15).
Furthermore, the double-lug connecting rod (7) is fixedly connected with the bottom end of the rod body part of the torsion rod (5) through a spline.
Furthermore, the bottom end of the rod body part of the torsion rod (5) is also provided with an elastic check ring (8), and the axial limiting is carried out through the elastic check ring (8).
Further, the torsion bar (5) is made of high-strength steel material.
Further, the plane link mechanism is made of high-strength steel materials.
Furthermore, the first bracket (3) and the second bracket (4) are made of steel or aluminum.
Furthermore, the connection point of the turning actuator (1), the first support (3) and the second support (4) is determined by the transmission ratio of the connecting rod transmission type front wheel turning anti-swing mechanism, and the length of the rocker arm end of the torsion bar (5), the length of the double-lug connecting rod (7) and the length of the middle connecting rod (9) are determined by the transmission ratio of the connecting rod transmission type front wheel turning anti-swing mechanism.
The invention has the beneficial effects that:
aiming at the retractable nose wheel steering anti-swing system of the undercarriage, the connecting rod transmission mechanism is adopted to realize the transmission of motion between different planes, so that the turning actuator is prevented from being arranged near the nose wheel ring body, the free and reasonable arrangement of the turning actuator is realized, the retractable airplane of the undercarriage is ensured to have good pneumatic appearance, the pneumatic resistance is reduced, and meanwhile, the retractable nose wheel steering anti-swing system is integrally more attractive.
In the high-speed sliding stage of the airplane, the energy generated by shimmy of the front wheel can be transferred to the shimmy damper and quickly weakened and dissipated by the reverse transfer of the motion of the connecting rod mechanism, so that the turning function is realized, and meanwhile, the anti-shimmy function of the airplane during high-speed sliding is realized. Through reasonable design of the connecting rod mechanism, the force transmission ratio of the connecting rod mechanism is changed, and the requirements of using and arranging mechanisms on different airplanes can be met in a certain range.
Drawings
FIG. 1 is a schematic diagram of the apparatus of the present invention;
FIG. 2 is a schematic view of a turning actuator torque transmitting mechanism;
FIG. 3 is a schematic view of a planar linkage mechanism;
FIG. 4 is a schematic view of a shimmy damper installation;
FIG. 5 is a schematic view of the present invention in use assembled;
wherein, 1, turning actuator; 2 a turning actuator piston rod; 3, a first bracket; 4, a second bracket; 5 a torsion bar; 6, a third bracket; 7 a double-lug connecting rod; 8, a circlip; 9 an intermediate connecting rod; 10 a nose landing gear ring body; 11 a torsion arm; 12 a shimmy damper; 13 a nose landing gear outer barrel; 14, mounting a first connecting lug; 15 mounting a second connecting lug; 16, mounting a third connecting lug; 17, a fourth connecting lug is installed.
Detailed Description
The following detailed description of the embodiments of the present invention, such as the shapes, configurations, mutual positions and connection relationships of the components, the functions and operating principles of the components, the manufacturing processes and the operation and use methods thereof, will be further described in detail with reference to the accompanying drawings, so as to help those skilled in the art to more completely, accurately and deeply understand the concept and technical solutions of the present invention:
as shown in fig. 1, the overall arrangement mode of the connecting rod transmission type front wheel turning anti-swing mechanism comprises a turning actuator torque transmission mechanism, a plane connecting rod mechanism and a swing reducer; the turning actuator torque transmission mechanism shown in fig. 2 mainly comprises a turning actuator 1, a torsion bar 5, a bracket II 4, a bracket I3 and the like. When the piston rod 2 of the turning actuator 1 extends or retracts, the rocker arm of the torsion bar 5 is pushed to move, so that the rod body part of the torsion bar 5 rotates around the axis of the torsion bar, and the output torque of the turning actuator is converted into the torque output of the torsion bar.
As shown in fig. 2, the turning actuator torque transmission mechanism includes a turning actuator 1, a torsion bar 5, a bracket two 4, a bracket one 3, and a bracket three 6, the bracket one 3 is fixed on the outer barrel 13 of the nose landing gear through a mounting lug one 14, the bracket two 4 is fixed on the outer barrel 13 of the nose landing gear through a mounting lug two 15, the turning actuator 1 is connected on the outer barrel of the nose landing gear through the bracket two 4 and the bracket one 3, a piston rod of the turning actuator 1 is movably connected with a rocker arm end of the torsion bar 5, and a rod body part of the torsion bar 5 is hinged on the bracket two 4 and the mounting lug three 16 of the outer barrel 13 of the nose landing gear and can rotate around the axis of the torsion bar.
As shown in fig. 3, the plane linkage mechanism includes a binaural connecting rod 7, a middle connecting rod 9, a nose landing gear ring 10 and a torsion arm 11, the binaural connecting rod 7 is fixedly connected with the bottom end of the rod body part of the torsion bar 5 through splines, the connection is firm and can smoothly transmit torque, an upper connecting lug of the binaural connecting rod 7 is hinged with a shimmy damper shown in fig. 4, a lower connecting lug of the binaural connecting rod 7 is connected with one end of the middle connecting rod 9, the other end of the middle connecting rod 9 is connected with the nose landing gear ring 10, the nose landing gear ring 10 is arranged on an outer nose landing gear barrel 13 and can rotate around the outer barrel, one end of the torsion arm 11 is connected outside the nose landing gear ring 10, and the other end of the torsion arm 11 is connected with an inner nose landing gear barrel.
As shown in fig. 4, the shimmy damping mechanism mainly comprises a shimmy damper 12, and an upper connecting lug of the double-lug connecting rod 7 is connected with a piston rod of the shimmy damper. When the airplane runs at high speed, if the front wheel shimmys, the shimmy energy and the reciprocating swing are reversely transmitted to the double-lug connecting rod 7 through the torsion arm 11 and the nose landing gear ring body 10, the double-lug connecting rod 7 transmits the swing and the energy to the shimmy damper 12 through the upper connecting lug, and the internal damping of the shimmy damper 12 can be quickly weakened and dissipates the motion energy, so that the front wheel shimmy is prevented.
As shown in fig. 1, the bottom end of the body portion of the torsion bar 5 is further provided with a circlip 8, and the axial limitation is performed by the circlip 8.
The torsion bar 5 and the plane link mechanism are made of high-strength steel materials, the high-strength steel has high mechanical strength and good comprehensive mechanical property, can bear large moment transmitted on a machine and keeps the moment not to deform, the first support 3 and the second support 4 are made of steel or aluminum materials, and can effectively support and fix the turning actuator 1.
The connecting point of the turning actuator 1, the first support 3 and the second support 4 is determined by the transmission ratio of the connecting rod transmission type front wheel turning anti-swing mechanism, and the length of the rocker arm end of the torsion bar 5, the length of the double-lug connecting rod 7 and the length of the middle connecting rod 9 are determined by the transmission ratio of the connecting rod transmission type front wheel turning anti-swing mechanism.
As shown in fig. 1, in order to integrally arrange the link transmission mechanism of the front wheel steering anti-swing system, the outer cylinder portion of the steering actuator 1 is connected to the bracket 3 and the bracket 4 by the mount joint. The bracket 3, the bracket 4 and the bracket 6 are respectively fixed on a mounting lug 14, a mounting lug 15 and a mounting lug 17 of the nose landing gear outer barrel 13 through connecting bolts, nuts, washers and the like. The piston rod 2 of the turning actuator 1 is connected to the rocker arm of the torsion bar 5 via an end fitting. The body portion of the torsion bar 5 is retained by guide holes in the brackets 4 and 6. The double-lug connecting rod 7 is connected with the torsion bar 5 through a spline, and the lower end of the double-lug connecting rod is axially limited through an elastic retainer ring 8. The lower connecting lug of the double-lug connecting rod 7 is connected with the middle connecting rod 9 through a connecting bolt, a nut, a washer and the like. The other end of the middle connecting rod 9 is connected with a nose landing gear nose ring body 10 through a connecting bolt, a nut, a washer and the like. The torque arm 11 is movably connected with the nose landing gear ring body 10 through a connecting piece. The upper connecting lug of the double-lug connecting rod 7 is connected with the piston rod of the shimmy damper 12 through a connecting bolt, a nut, a washer and the like. The shimmy damper 12 is connected with a mounting lug 17 on the nose landing gear outer cylinder 13 through a connecting bolt, a nut, a washer and the like. Meanwhile, lubricating oil nozzles are arranged at all the motion connection parts, so that motion clamping stagnation of the mechanism is avoided.
When the airplane runs at a low speed on the ground, a pilot can control the turning actuator 1 through a turning hand wheel or a pedal mechanism, so that a piston rod 2 in the turning actuator 1 extends or retracts under the action of internal hydraulic pressure. The extension or retraction of the piston rod 2 pushes or pulls the rocker arm of the torsion bar 5 to move the torsion bar 5 rotationally about its axis within the mounting holes of the mounting brackets 4 and 6. Because the double-lug connecting rod 7 is connected with the torsion bar through a spline, and the lower end of the double-lug connecting rod is axially limited through the elastic collar 8, the movement of the double-lug connecting rod 7 is kept synchronous with the torsion bar 5, and the double-lug connecting rod 7 also rotates around the axis of the torsion bar 5. Meanwhile, the extension lugs of the double-lug connecting rod 7, the middle connecting rod 9 and the nose landing gear ring body 10 form a plane connecting rod mechanism together. The plane link mechanism realizes that the torsion bar 5 rotates to drive the nose landing gear ring body 10 to rotate around the axis of the nose landing gear outer cylinder. The rotation motion of the nose landing gear ring body 10 drives the outer barrel, the wheel fork, the airplane wheel and the like of the nose landing gear to synchronously rotate through the torsion arm 11, and finally the steering operation of the front wheel is realized. Because the taxiing speed of the airplane is low when the front wheel steering function is used, and the steering speed needs to meet certain requirements, the shimmy damper 12 does not generate large damping force to hinder the steering operation of the front wheel when the front wheel is steered. According to the structural layout requirement, the length of the torsion bar 5 can be changed, and the positions of the first mounting lug 14, the second mounting lug 15 and the third mounting lug 16 can be adjusted according to the requirement, so that the spatial position of the turning actuator 1 can be adjusted and can be arranged in a reasonable space according to the requirement, and the aerodynamic appearance and the aesthetic property of the airplane are not influenced.
When the airplane slides at a high speed, if the front wheel swings at a high speed, the swinging and generated energy is transmitted to the nose landing gear shimmy damper 12 through the torsion arm 11, the nose landing gear ring body 10, the middle connecting rod 9 and the double-lug connecting rod 7, and is quickly weakened or dissipated through an oil piston type damping mechanism inside the nose landing gear shimmy damper 12. The high-speed swing of the front wheel is transmitted to the shimmy damper 12 and also transmitted to the turning actuator 1 through mechanisms such as the torsion bar 5, however, when the airplane slides at a high speed, the oil liquid in the turning actuator 1 does not have hydraulic pressure, so the high-speed swing of the front wheel only enables the turning actuator piston rod 2 to follow up, and the turning actuator 1 does not influence the transmission of the movement.
Example (b):
fig. 5 shows an example of the use of the link transmission mechanism suitable for the front wheel turning anti-swing system. The undercarriage of a certain type is of a non-retractable type structure, and the nose undercarriage is arranged on the frame 3 of the machine body. During the operation of the airplane, a front wheel turning mechanism is additionally arranged according to the needs of a user, and the turning actuator drives the nose landing gear ring body to realize the turning operation of the front wheel. According to calculation, the volume and the length of the front wheel turning actuator 1 are large, the aerodynamic appearance of the airplane is damaged when the front wheel turning actuator is arranged outside the airplane body structure, large aerodynamic resistance is generated, and meanwhile, the attractiveness is seriously affected. Through connecting rod drive mechanism, can realize freely arranging of turning actuator within a certain range to satisfy the motion transmission output between the turning actuator 1 and the nose landing gear ring body that are in different motion planes, through calculating the transmission ratio of back rational design connecting rod drive mechanism, the front wheel turns the actuator and has installed between the compartment frame of fuselage covering top, when realizing the turn function, great assurance the aerodynamic profile and the aesthetic property of aircraft. And moreover, the normal use of the original anti-swing function is ensured through the motion transmission of the double-lug connecting rod.
The invention has been described above with reference to the accompanying drawings, it is obvious that the invention is not limited to the specific implementation in the above-described manner, and it is within the scope of the invention to apply the inventive concept and solution to other applications without substantial modification.
Claims (9)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011200061.4A CN112389641A (en) | 2020-10-30 | 2020-10-30 | Connecting rod transmission type front wheel turning anti-swing mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011200061.4A CN112389641A (en) | 2020-10-30 | 2020-10-30 | Connecting rod transmission type front wheel turning anti-swing mechanism |
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| Publication Number | Publication Date |
|---|---|
| CN112389641A true CN112389641A (en) | 2021-02-23 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011200061.4A Pending CN112389641A (en) | 2020-10-30 | 2020-10-30 | Connecting rod transmission type front wheel turning anti-swing mechanism |
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| CN (1) | CN112389641A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113955091A (en) * | 2021-11-03 | 2022-01-21 | 哈尔滨哈飞航空工业有限责任公司 | Layered torsion transmission type front wheel turning mechanism |
| CN114909445A (en) * | 2022-05-19 | 2022-08-16 | 南京航空航天大学 | Switching device and method for front wheel control swing reducing channel of airplane |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113955091A (en) * | 2021-11-03 | 2022-01-21 | 哈尔滨哈飞航空工业有限责任公司 | Layered torsion transmission type front wheel turning mechanism |
| CN113955091B (en) * | 2021-11-03 | 2023-09-05 | 哈尔滨哈飞航空工业有限责任公司 | Layered torque transmission type front wheel steering mechanism |
| CN114909445A (en) * | 2022-05-19 | 2022-08-16 | 南京航空航天大学 | Switching device and method for front wheel control swing reducing channel of airplane |
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Application publication date: 20210223 |