Aircraft front wheel control anti-sway channel switching device and method

Abstract

The invention discloses a switching device and method for steering and reducing sway channels of front wheels of an aircraft, comprising a switching housing, a steering housing, a reducing sway housing, first and second brakes, a steering input shaft, a steering input gear, first and second steering transmission gears, a steering shaft, a reducing sway output shaft, a reducing sway output gear, first and second reducing sway transmission gears, a reducing sway shaft, a central wheel shaft, a double gear, first to third input-stage planetary gears, first to third output-stage planetary gears, first to third planetary shafts, a sun gear, a planet carrier, a transmission cylinder, a gear ring, and first to second bidirectional transmission gears. The invention comprises a turning channel and a reducing sway channel, and the switching of the two transmission channels is realized by controlling the braking of a motor and a reducing sway device, thereby completing the steering and reducing sway steering of the front wheels of the aircraft. Compared with the traditional hydraulic actuating mechanism, the weight of the additional actuating mechanism of the invention is reduced, and the ground maneuverability and reliability of the aircraft can be improved.

Description

Technical Field

[0001] The invention relates to the field of flight, and in particular to a device and method for switching a sway reduction channel for a front wheel control of an aircraft. Background Art

[0002] The all-electric aircraft front wheel turning control technology is a key technology for ground maneuvering of aircraft. During the take-off and landing process of the aircraft, the turning channel and the sway reduction channel are switched according to actual needs to complete the turning and sway reduction control of the aircraft front wheel. In the switching of the turning control and sway reduction control of the aircraft front wheel, the transmission mechanism is required to be small in size, light in weight, stable in transmission, strong in impact and vibration resistance, and the transmission ratio from the sway reducer to the aircraft front wheel must be met.

[0003] The existing aircraft front wheel control mechanisms are mainly of two types: double-actuator type and rack and pinion type. In the double-actuator type front wheel control mechanism, the thrust direction of the actuator is always changing during movement, which makes the transmission efficiency unstable and affects the reliability of the turning mechanism. In addition, due to the complexity of the rotation process, the required hydraulic control system is also relatively complex, requiring designers to have sufficiently high professional qualities to ensure the reliability of the system. In the rack and pinion type front wheel control mechanism, since the torque transmitted from the rack only acts on a few teeth, only a few teeth are stressed, and the stress concentration phenomenon at the root of the teeth is obvious, the service life is greatly reduced under the action of repeated bending stress. In addition, the existing aircraft front wheel control mechanism mainly adopts a hydraulic actuation system, which has a complex structure, a large weight, and a low comprehensive energy utilization efficiency. Summary of the invention

[0004] The technical problem to be solved by the present invention is to provide a device and method for switching an aircraft front wheel control anti-sway channel in view of the defects involved in the background technology.

[0005] The present invention adopts the following technical solutions to solve the above technical problems:

[0006] A switching device for steering and reducing sway of a front wheel of an aircraft comprises a switching housing, a steering housing, a reducing sway housing, a first brake, a second brake, a steering input shaft, a steering input gear, a first steering transmission gear, a second steering transmission gear, a steering rotating shaft, a reducing sway output shaft, a reducing sway output gear, a first reducing sway transmission gear, a second reducing sway transmission gear, a reducing sway rotating shaft, a central wheel shaft, a double gear, first to third input stage planetary gears, first to third output stage planetary gears, first to third planetary shafts, a sun gear, a planet carrier, a transmission cylinder, a gear ring, a first two-way transmission gear and a second two-way transmission gear;

[0007] The switching housing is a hollow cylinder, and through holes are provided at the center of the upper and lower end surfaces of the switching housing; the transmission cylinder is a hollow cylinder with an upper opening, which is arranged in the switching housing, and a through hole is provided at the center of the lower end surface of the transmission cylinder;

[0008] The upper end of the central wheel shaft is rotatably connected to the through hole at the center of the upper end surface of the shell through the bearing, and the lower end passes through the through hole at the center of the lower end surface of the transmission cylinder and the through hole at the center of the lower end surface of the shell in sequence, and the central wheel shaft is rotatably connected to the through hole at the center of the lower end surface of the transmission cylinder and the through hole at the center of the lower end surface of the shell respectively through the bearing and the through hole at the center of the lower end surface of the transmission cylinder and the through hole at the center of the lower end surface of the shell;

[0009] The first bidirectional transmission gear is coaxially fixedly connected to the lower end of the central wheel shaft; the second bidirectional transmission gear is sleeved outside the rotating sleeve of the front landing gear of the aircraft, and is coaxially fixedly connected to the rotating sleeve of the front landing gear of the aircraft, and the second bidirectional transmission gear is meshed with the first bidirectional transmission gear;

[0010] The second control transmission gear, the second swing reduction transmission gear, the double gear, the first to third input stage planetary gears, the first to third output stage planetary gears, the first to third planetary shafts, the sun gear, the planet carrier, and the ring gear are all arranged in the transmission cylinder;

[0011] The duplex gear and the sun gear are both arranged on the central wheel shaft, wherein the duplex gear is connected to the central wheel shaft through a bearing, the large gear of the duplex gear is located at the top and the small gear is located at the bottom; the sun gear is located below the duplex gear and is coaxially fixed to the central wheel shaft;

[0012] The planet carrier is arranged between the duplex gear and the sun gear;

[0013] The first input stage planetary gear and the first output stage planetary gear are coaxially fixedly connected through the first planetary shaft, and the first planetary shaft is rotatably connected to the planetary carrier and the lower end surface of the transmission cylinder through the bearing respectively;

[0014] The second input stage planetary gear and the second output stage planetary gear are coaxially fixedly connected through the second planetary shaft, and the second planetary shaft is rotatably connected to the planetary carrier and the lower end surface of the transmission cylinder through the bearing respectively;

[0015] The third input stage planetary gear and the third output stage planetary gear are coaxially fixedly connected through the third planetary shaft, and the third planetary shaft is rotatably connected to the planetary carrier and the lower end surface of the transmission cylinder through bearings respectively;

[0016] The first to third input stage planetary gears are evenly arranged in the circumferential direction and are all meshed with the sun gear; the first to third output stage planetary gears are all meshed with the pinion gear of the duplex gear;

[0017] The gear ring is arranged on the inner wall of the transmission cylinder and is coaxially fixedly connected with the transmission cylinder;

[0018] One end of the sway reduction shaft is coaxially fixedly connected to the second sway reduction transmission gear, and the other end passes through the upper end surface of the switching housing and is coaxially fixedly connected to the first sway reduction transmission gear, and the sway reduction shaft is rotatably connected to the upper end surface of the switching housing through the shaft;

[0019] The second sway reduction transmission gear is meshed with the ring gear;

[0020] The sway reduction housing and the upper end surface of the switching housing are fixedly connected, and the sway reduction output gear and the first sway reduction transmission gear are contained therein, wherein the sway reduction output gear and the lower end of the sway reduction output shaft are coaxially fixedly connected, and the sway reduction output gear and the first sway reduction transmission gear are meshed; the upper end of the sway reduction output shaft passes through the sway reduction housing and is rotatably connected to the sway reduction housing through a bearing;

[0021] The upper end of the sway reduction output shaft is connected to an external sway reduction device through the second brake;

[0022] One end of the operating shaft is coaxially fixedly connected to the second operating transmission gear, and the other end passes through the upper end surface of the switching housing and is coaxially fixedly connected to the first operating transmission gear, and the operating shaft is rotatably connected to the upper end surface of the switching housing through the shaft;

[0023] The second operating transmission gear is meshed with the large gear of the double gear;

[0024] The control housing and the upper end surface of the switching housing are fixedly connected, and the control output gear and the first control transmission gear are contained therein, wherein the control output gear and the lower end of the control output shaft are coaxially fixedly connected, and the control output gear and the first control transmission gear are meshed; the upper end of the control output shaft passes through the control housing and is rotatably connected to the control housing through a bearing;

[0025] The upper end of the control output shaft is connected to the external motor through the first brake;

[0026] The switching housing is fixedly connected to the outer cylinder of the front landing gear of the aircraft through a bracket.

[0027] The present invention also discloses a switching method of the aircraft front wheel steering anti-sway channel switching device, comprising the following steps:

[0028] If you need to turn the aircraft's front wheels:

[0029] The first brake is closed and the second brake is activated, the sway reduction output shaft, the sway reduction output gear, the first sway reduction transmission gear, the second sway reduction transmission gear, and the ring gear are all braked, and the power and motion of the external motor are transmitted to the large gear of the double central gear through the control input shaft, the control input gear, the first control transmission gear, and the second control transmission gear, and then transmitted to the rotating sleeve of the front landing gear of the aircraft through the first to third output stage planetary gears, the first to third input stage planetary gears, and the sun gear, so as to realize the turning control of the front wheel of the aircraft;

[0030] If you need to reduce the shimmy of the aircraft's front wheels:

[0031] The second brake is closed and the first brake is started, the operating input shaft, the operating input gear, the first operating transmission gear, the second operating transmission gear, and the double central gear are all braked, and the swing torque of the front wheel of the aircraft is transmitted to the sun gear through the second two-way transmission gear and the first two-way transmission gear, so that the first to third input-stage planetary gears drive the first to third output-stage planetary gears to revolve around the double gears, and then drive the gear ring to rotate around the central wheel shaft through the transmission cylinder, and transmit the motion to the swing reduction output shaft through the second swing reduction transmission gear, the first swing reduction transmission gear, and the swing reduction output gear. Finally, the swing reduction output shaft transmits the swing torque to the external swing reducer to eliminate the swing vibration, thereby realizing the swing reduction of the front wheel of the aircraft.

[0032] Compared with the prior art, the present invention adopts the above technical solution and has the following technical effects:

[0033] The present invention combines the turning mechanism and the sway reduction mechanism into one mechanism through the design of external meshing double-row planetary gear transmission, so that during the take-off and landing of the aircraft, the turning channel and the sway reduction channel can be switched according to actual needs to complete the turning and sway reduction operation of the front wheels of the all-electric aircraft, reduce the weight of the front wheel turning and sway reduction mechanism, reduce the volume of the front wheel turning and sway reduction mechanism, and improve the stability of the aircraft's front wheel operation. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 It is a schematic diagram of the structure of the present invention in cooperation with an external motor and a shimmy damper;

[0035] Figure 2 It is a schematic diagram of the structural principle of the present invention;

[0036] Figure 3 It is a schematic structural diagram of the internal structure of the present invention viewed obliquely from top to bottom;

[0037] Figure 4 It is a structural schematic diagram of the inner wall structure of the present invention viewed obliquely from bottom to top;

[0038] Figure 5 It is a structural schematic diagram of the present invention installed on the front wheel of an aircraft.

[0039] In the figure, 1-switching housing, 2-bracket, 3-control housing, 4-sway reduction housing, 5-first brake, 6-second brake, 7-sway reducer, 8-motor, 9-rotating sleeve of front landing gear of aircraft, 10-second two-way transmission gear, 11-first two-way transmission gear, 12-center wheel shaft, 13-dual gear, 14-sun gear, 15-first output stage planetary gear, 16-first input stage planetary gear, 17-first planetary shaft, 18-ring gear, 19-second sway reduction transmission gear, 20-first sway reduction transmission gear, 21-sway reduction output gear, 22-sway reduction output shaft, 23-second control transmission gear, 24-first control transmission gear, 25-control input gear, 26-control input shaft, 27-planet carrier, 28-outer cylinder of front landing gear of aircraft. DETAILED DESCRIPTION

[0040] The technical solution of the present invention is further described in detail below in conjunction with the accompanying drawings:

[0041] The present invention can be implemented in many different forms and should not be considered to be limited to the embodiments described herein. On the contrary, these embodiments are provided to make this disclosure thorough and complete, and will fully express the scope of the present invention to those skilled in the art. In the accompanying drawings, components are enlarged for clarity.

[0042] It should be understood that although the terms first, second, third, etc. can be used here to describe various elements, components and / or parts, these elements, components and / or parts are not limited by these terms. These terms are only used to distinguish elements, components and / or parts from each other. Therefore, the first element, component and / or part discussed below can become the second element, component or part without departing from the teaching of the present invention.

[0043] like Figure 1 As shown, the present invention discloses a switching device for steering and reducing sway channels of a front wheel of an aircraft, comprising a switching housing, a steering housing, a reducing sway housing, a first brake, a second brake, a steering input shaft, a steering input gear, a first steering transmission gear, a second steering transmission gear, a steering rotating shaft, a reducing sway output shaft, a reducing sway output gear, a first reducing sway transmission gear, a second reducing sway transmission gear, a reducing sway rotating shaft, a central wheel shaft, a double gear, first to third input stage planetary gears, first to third output stage planetary gears, first to third planetary shafts, a sun gear, a planet carrier, a transmission cylinder, a gear ring, a first two-way transmission gear and a second two-way transmission gear;

[0044] like Figure 2 , Figure 3 , Figure 4 As shown, the switching housing is a hollow cylinder, and through holes are provided at the center of the upper end surface and the lower end surface of the switching housing; the transmission cylinder is a hollow cylinder with an upper end opening, which is arranged in the switching housing, and a through hole is provided at the center of the lower end surface of the transmission cylinder;

[0045] The upper end of the central wheel shaft is rotatably connected to the through hole at the center of the upper end surface of the shell through the bearing, and the lower end passes through the through hole at the center of the lower end surface of the transmission cylinder and the through hole at the center of the lower end surface of the shell in sequence, and the central wheel shaft is rotatably connected to the through hole at the center of the lower end surface of the transmission cylinder and the through hole at the center of the lower end surface of the shell respectively through the bearing and the through hole at the center of the lower end surface of the transmission cylinder and the through hole at the center of the lower end surface of the shell;

[0046] The first bidirectional transmission gear is coaxially fixedly connected to the lower end of the central wheel shaft; the second bidirectional transmission gear is sleeved outside the rotating sleeve of the front landing gear of the aircraft, and is coaxially fixedly connected to the rotating sleeve of the front landing gear of the aircraft, and the second bidirectional transmission gear is meshed with the first bidirectional transmission gear;

[0047] The second control transmission gear, the second swing reduction transmission gear, the double gear, the first to third input stage planetary gears, the first to third output stage planetary gears, the first to third planetary shafts, the sun gear, the planet carrier, and the ring gear are all arranged in the transmission cylinder;

[0048] The duplex gear and the sun gear are both arranged on the central wheel shaft, wherein the duplex gear is connected to the central wheel shaft through a bearing, the large gear of the duplex gear is located at the top and the small gear is located at the bottom; the sun gear is located below the duplex gear and is coaxially fixed to the central wheel shaft;

[0049] The planet carrier is arranged between the duplex gear and the sun gear;

[0050] The first input stage planetary gear and the first output stage planetary gear are coaxially fixedly connected through the first planetary shaft, and the first planetary shaft is rotatably connected to the planetary carrier and the lower end surface of the transmission cylinder through the bearing respectively;

[0051] The second input stage planetary gear and the second output stage planetary gear are coaxially fixedly connected through the second planetary shaft, and the second planetary shaft is rotatably connected to the planetary carrier and the lower end surface of the transmission cylinder through the bearing respectively;

[0052] The third input stage planetary gear and the third output stage planetary gear are coaxially fixedly connected through the third planetary shaft, and the third planetary shaft is rotatably connected to the planetary carrier and the lower end surface of the transmission cylinder through bearings respectively;

[0053] The first to third input stage planetary gears are evenly arranged in the circumferential direction and are all meshed with the sun gear; the first to third output stage planetary gears are all meshed with the pinion gear of the duplex gear;

[0054] The gear ring is arranged on the inner wall of the transmission cylinder and is coaxially fixedly connected with the transmission cylinder;

[0055] One end of the sway reduction shaft is coaxially fixedly connected to the second sway reduction transmission gear, and the other end passes through the upper end surface of the switching housing and is coaxially fixedly connected to the first sway reduction transmission gear, and the sway reduction shaft is rotatably connected to the upper end surface of the switching housing through the shaft;

[0056] The second sway reduction transmission gear is meshed with the ring gear;

[0057] The sway reduction housing and the upper end surface of the switching housing are fixedly connected, and the sway reduction output gear and the first sway reduction transmission gear are contained therein, wherein the sway reduction output gear and the lower end of the sway reduction output shaft are coaxially fixedly connected, and the sway reduction output gear and the first sway reduction transmission gear are meshed; the upper end of the sway reduction output shaft passes through the sway reduction housing and is rotatably connected to the sway reduction housing through a bearing;

[0058] The upper end of the sway reduction output shaft is connected to an external sway reduction device through the second brake;

[0059] One end of the operating shaft is coaxially fixedly connected to the second operating transmission gear, and the other end passes through the upper end surface of the switching housing and is coaxially fixedly connected to the first operating transmission gear, and the operating shaft is rotatably connected to the upper end surface of the switching housing through the shaft;

[0060] The second operating transmission gear is meshed with the large gear of the double gear;

[0061] The control housing and the upper end surface of the switching housing are fixedly connected, and the control output gear and the first control transmission gear are contained therein, wherein the control output gear and the lower end of the control output shaft are coaxially fixedly connected, and the control output gear and the first control transmission gear are meshed; the upper end of the control output shaft passes through the control housing and is rotatably connected to the control housing through a bearing;

[0062] The upper end of the control output shaft is connected to the external motor through the first brake;

[0063] The switching housing is fixedly connected to the outer tube of the front landing gear of the aircraft through a bracket. Figure 5 shown.

[0064] The present invention also discloses a switching method of the aircraft front wheel steering anti-sway channel switching device, comprising the following steps:

[0065] If you need to turn the aircraft's front wheels:

[0066] The first brake is closed and the second brake is activated, the sway reduction output shaft, the sway reduction output gear, the first sway reduction transmission gear, the second sway reduction transmission gear, and the ring gear are all braked, and the power and motion of the external motor are transmitted to the large gear of the double central gear through the control input shaft, the control input gear, the first control transmission gear, and the second control transmission gear, and then transmitted to the rotating sleeve of the front landing gear of the aircraft through the first to third output stage planetary gears, the first to third input stage planetary gears, and the sun gear, so as to realize the turning control of the front wheel of the aircraft;

[0067] If you need to reduce the shimmy of the aircraft's front wheels:

[0068] The second brake is closed and the first brake is started, the operating input shaft, the operating input gear, the first operating transmission gear, the second operating transmission gear, and the double central gear are all braked, and the swing torque of the front wheel of the aircraft is transmitted to the sun gear through the second two-way transmission gear and the first two-way transmission gear, so that the first to third input-stage planetary gears drive the first to third output-stage planetary gears to revolve around the double gears, and then drive the gear ring to rotate around the central wheel shaft through the transmission cylinder, and transmit the motion to the swing reduction output shaft through the second swing reduction transmission gear, the first swing reduction transmission gear, and the swing reduction output gear. Finally, the swing reduction output shaft transmits the swing torque to the external swing reducer to eliminate the swing vibration, thereby realizing the swing reduction of the front wheel of the aircraft.

[0069] It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as generally understood by those skilled in the art in the art to which the present invention belongs. It should also be understood that terms such as those defined in common dictionaries should be understood to have meanings consistent with the meanings in the context of the prior art, and will not be interpreted with idealized or overly formal meanings unless defined as herein.

[0070] The specific implementation methods described above further illustrate the objectives, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above description is only a specific implementation method of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. An aircraft front wheel control anti-sway channel switching device, characterized in that: It includes a switching housing, a manipulation housing, a sway reduction housing, a first brake, a second brake, a manipulation input shaft, a manipulation input gear, a first manipulation transmission gear, a second manipulation transmission gear, a manipulation rotating shaft, a sway reduction output shaft, a sway reduction output gear, a first sway reduction transmission gear, a second sway reduction transmission gear, a sway reduction rotating shaft, a central wheel shaft, a double gear, first to third input stage planetary gears, first to third output stage planetary gears, first to third planetary shafts, a sun gear, a planet carrier, a transmission cylinder, a gear ring, a first two-way transmission gear and a second two-way transmission gear; The switching housing is a hollow cylinder, and through holes are provided at the center of the upper and lower end surfaces of the switching housing; the transmission cylinder is a hollow cylinder with an upper end opening, which is arranged in the switching housing, and a through hole is provided at the center of the lower end surface of the transmission cylinder; The upper end of the central wheel shaft is rotatably connected to the through hole at the center of the upper end surface of the shell through the bearing, and the lower end passes through the through hole at the center of the lower end surface of the transmission cylinder and the through hole at the center of the lower end surface of the shell in sequence, and the central wheel shaft is rotatably connected to the through hole at the center of the lower end surface of the transmission cylinder and the through hole at the center of the lower end surface of the shell respectively through the bearing and the through hole at the center of the lower end surface of the transmission cylinder and the through hole at the center of the lower end surface of the shell; The first bidirectional transmission gear is coaxially fixedly connected to the lower end of the central wheel shaft; the second bidirectional transmission gear is sleeved outside the rotating sleeve of the front landing gear of the aircraft, and is coaxially fixedly connected to the rotating sleeve of the front landing gear of the aircraft, and the second bidirectional transmission gear is meshed with the first bidirectional transmission gear; The second control transmission gear, the second swing reduction transmission gear, the double gear, the first to third input stage planetary gears, the first to third output stage planetary gears, the first to third planetary shafts, the sun gear, the planet carrier, and the ring gear are all arranged in the transmission cylinder; The duplex gear and the sun gear are both arranged on the central wheel shaft, wherein the duplex gear is connected to the central wheel shaft through a bearing, the large gear of the duplex gear is located at the top and the small gear is located at the bottom; the sun gear is located below the duplex gear and is coaxially fixed to the central wheel shaft; The planet carrier is arranged between the duplex gear and the sun gear; The first input stage planetary gear and the first output stage planetary gear are coaxially fixedly connected through the first planetary shaft, and the first planetary shaft is rotatably connected to the planetary carrier and the lower end surface of the transmission cylinder through the bearing respectively; The second input stage planetary gear and the second output stage planetary gear are coaxially fixedly connected through the second planetary shaft, and the second planetary shaft is rotatably connected to the planetary carrier and the lower end surface of the transmission cylinder through the bearing respectively; The third input stage planetary gear and the third output stage planetary gear are coaxially fixedly connected through the third planetary shaft, and the third planetary shaft is rotatably connected to the planetary carrier and the lower end surface of the transmission cylinder through bearings respectively; The first to third input stage planetary gears are evenly arranged in the circumferential direction and are all meshed with the sun gear; the first to third output stage planetary gears are all meshed with the pinion gear of the duplex gear; The gear ring is arranged on the inner wall of the transmission cylinder and is coaxially fixedly connected with the transmission cylinder; One end of the sway reduction shaft is coaxially fixedly connected to the second sway reduction transmission gear, and the other end passes through the upper end surface of the switching housing and is coaxially fixedly connected to the first sway reduction transmission gear, and the sway reduction shaft is rotatably connected to the upper end surface of the switching housing through the shaft; The second sway reduction transmission gear is meshed with the ring gear; The sway reduction housing and the upper end surface of the switching housing are fixedly connected, and the sway reduction output gear and the first sway reduction transmission gear are contained therein, wherein the sway reduction output gear and the lower end of the sway reduction output shaft are coaxially fixedly connected, and the sway reduction output gear and the first sway reduction transmission gear are meshed; the upper end of the sway reduction output shaft passes through the sway reduction housing and is rotatably connected to the sway reduction housing through a bearing; The upper end of the sway reduction output shaft is connected to an external sway reduction device through the second brake; One end of the operating shaft is coaxially fixedly connected to the second operating transmission gear, and the other end passes through the upper end surface of the switching housing and is coaxially fixedly connected to the first operating transmission gear, and the operating shaft is rotatably connected to the upper end surface of the switching housing through the shaft; The second operating transmission gear is meshed with the large gear of the double gear; The control housing and the upper end surface of the switching housing are fixedly connected, and the control output gear and the first control transmission gear are contained therein, wherein the control output gear and the lower end of the control output shaft are coaxially fixedly connected, and the control output gear and the first control transmission gear are meshed; the upper end of the control output shaft passes through the control housing and is rotatably connected to the control housing through a bearing; The upper end of the control output shaft is connected to the external motor through the first brake; The switching housing is fixedly connected to the outer cylinder of the front landing gear of the aircraft through a bracket.

2. The switching method of the aircraft nose wheel control anti-sway channel switching device according to claim 1 is characterized in that: The following steps are involved: If you need to turn the aircraft's front wheels: The first brake is closed and the second brake is activated, the sway reduction output shaft, the sway reduction output gear, the first sway reduction transmission gear, the second sway reduction transmission gear, and the ring gear are all braked, and the power and motion of the external motor are transmitted to the large gear of the double central gear through the control input shaft, the control input gear, the first control transmission gear, and the second control transmission gear, and then transmitted to the rotating sleeve of the front landing gear of the aircraft through the first to third output stage planetary gears, the first to third input stage planetary gears, and the sun gear, so as to realize the turning control of the front wheel of the aircraft; If you need to reduce the shimmy of the aircraft's front wheels: The second brake is closed and the first brake is started, the operating input shaft, the operating input gear, the first operating transmission gear, the second operating transmission gear, and the double central gear are all braked, and the swing torque of the front wheel of the aircraft is transmitted to the sun gear through the second two-way transmission gear and the first two-way transmission gear, so that the first to third input-stage planetary gears drive the first to third output-stage planetary gears to revolve around the double gears, and then drive the gear ring to rotate around the central wheel shaft through the transmission cylinder, and transmit the motion to the swing reduction output shaft through the second swing reduction transmission gear, the first swing reduction transmission gear, and the swing reduction output gear. Finally, the swing reduction output shaft transmits the swing torque to the external swing reducer to eliminate the swing vibration, thereby realizing the swing reduction of the front wheel of the aircraft.

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