Stability augmentation device for undercarriage hub and undercarriage

Abstract

The stability augmentation device for the undercarriage hub comprises a shaft, a stator, a first rotor, a second rotor and an eccentric assembly, the stator is arranged on the shaft in a penetrating mode and can rotate relative to the shaft in the axial direction of the shaft, and the stator can generate a first magnetic field and a second magnetic field; the first magnetic field extends in the radial direction of the shaft, the second magnetic field extends in the axial direction of the shaft, the first rotor is provided with a cavity penetrating through the first rotor in the axial direction of the shaft, the stator is arranged in the cavity so that the first magnetic field can drive the first rotor to rotate in the axial direction of the shaft, the first rotor is suitable for being arranged in a hub, and the second rotor is arranged at the end, close to the second magnetic field, of the stator. The eccentric assembly is arranged on the shaft in a penetrating mode and arranged in the cavity, and the eccentric assembly is connected with the second rotor so that the shaft can drive the eccentric assembly to rotate so that the eccentric assembly can generate vertically-downward acting force. The stability augmentation device for the undercarriage hub has the advantages of being simple in structure, high in stability and the like.

Description

Technical Field

[0001] The utility model relates to the field of landing gears of aircraft, and particularly to a stability-increasing device for a landing gear hub and a landing gear. Background Art

[0002] During the ground takeoff and landing stages of a fixed-wing unmanned aerial vehicle (UAV), there is rarely a stability control system for the fuselage to taxi on the ground. The stability control system during flight in the air and the stability control during ground taxiing cannot be used simultaneously. During the takeoff and landing stages, when the stability of the fuselage is transferred from the control force of the wing surface to ground taxiing, the speed decreases during this distance, the lift generated by the wing surface becomes smaller, and the stability control of the fuselage can no longer be controlled by the flight control system. Instead, the stability of the fuselage can only be controlled by the landing gear and tires.

[0003] In the related art, during the takeoff and landing stages of a fixed-wing UAV, the stability of the fixed-wing UAV is poor, and it is prone to crashing accidents. Summary of the Utility Model

[0004] The present utility model is made based on the inventor's discovery and recognition of the following facts and problems:

[0005] In the related art, during the takeoff and landing stages of a fixed-wing UAV, it generally has a three-point landing gear. Affected by the uneven ground, the center of gravity is prone to shifting, causing the fuselage to lose its center of gravity and resulting in rollovers, and breaking the fuselage and wings are common accidents. Especially during non-professional ground takeoffs and landings, such as on desert ground, water ground, ice ground, grassland ground, or a ground with minor potholes, the contact between the tires and the ground is relatively smooth, and the adhesion of the tires is particularly small. Especially in rainy or windy weather conditions, it is prone to crashing accidents during the takeoff and landing of a fixed-wing UAV.

[0006] The present utility model aims to solve at least one of the technical problems in the related art to a certain extent.

[0007] To this end, an embodiment of the present utility model provides a stability-increasing device for a landing gear hub that can increase the stability of a fixed-wing UAV and reduce accidents of the fixed-wing UAV.

[0008] An embodiment of the present utility model provides a landing gear with a simple structure and a long service life.

[0009] The stability enhancing device for a landing gear wheel hub according to an embodiment of the present utility model includes: a shaft; a stator which is sleeved on the shaft and is rotatable relative to the shaft along the axial direction of the shaft, the stator being capable of generating a first magnetic field and a second magnetic field, the first magnetic field extending along the radial direction of the shaft, and the second magnetic field extending along the axial direction of the shaft; a first rotor which has a chamber axially penetrating the first rotor along the axial direction of the shaft, the stator being disposed in the chamber so that the first magnetic field drives the first rotor to be rotatable about the axial direction of the shaft, the first rotor being adapted to be disposed in the wheel hub so that the first rotor drives the wheel hub to rotate; a second rotor which is disposed at one end of the stator adjacent to the second magnetic field so that the second magnetic field drives the second rotor to rotate about the axial direction of the shaft; an eccentric assembly which is sleeved on the shaft and is disposed in the chamber, the eccentric assembly being connected to the second rotor so that the shaft drives the eccentric assembly to rotate to enable the eccentric assembly to generate a vertically downward acting force.

[0010] For the stability enhancing device for a landing gear wheel hub according to an embodiment of the present utility model, a stator, a first rotor, a second rotor and an eccentric assembly are provided, so that the eccentric assembly only generates a vertically downward acting force, thereby increasing the adhesion force between the tire and the ground, enabling the tire to firmly adhere to the ground, reducing the skidding of the tire, and thus making the operation of the fuselage more stable, preventing the fuselage from losing its center of gravity and causing a rollover to break the fuselage and the wing.

[0011] In some embodiments, the stator includes a body, a first iron core assembly and a second iron core assembly. The body is sleeved on the shaft and is rotatable relative to the shaft along the axial direction of the shaft. The body has an outer peripheral surface, a first end surface and a second end surface. The outer peripheral surface is a closed surface extending circumferentially around the shaft. The first end surface and the second end surface are oppositely disposed at an axial interval along the axial direction of the shaft, and the first end surface and the second end surface are respectively connected to both ends of the outer peripheral surface. The first iron core assembly is disposed on the outer peripheral surface of the body, and the second iron core assembly is disposed on the first end surface of the body. The second rotor is oppositely disposed at an axial interval from the first end surface of the body along the axial direction of the shaft. The first iron core assembly generates the first magnetic field, and the second iron core assembly generates the second magnetic field.

[0012] In some embodiments, there are a plurality of the first iron core assemblies, and the plurality of the first iron core assemblies are circumferentially spaced apart on the outer peripheral surface of the body around the shaft, and / or there are a plurality of the second iron core assemblies, and the plurality of the second iron core assemblies are circumferentially spaced apart on the first end surface of the body around the shaft.

[0013] In some embodiments, the first iron core assembly includes a first magnet and a first coil. The first magnet extends along the radial direction of the axis and is disposed on the outer peripheral surface of the body. The first coil is wound around the first magnet, and / or the second iron core assembly includes a second magnet and a second coil. The second magnet extends along the axial direction of the axis and is disposed on the outer peripheral surface of the body. The second coil is wound around the second magnet.

[0014] In some embodiments, the stability enhancing device for the landing gear hub further includes a wheel axle cover and a wheel seal cover. The wheel axle cover and the wheel seal cover are disposed opposite to each other at an axial interval along the axis. The first rotor is disposed between the wheel axle cover and the wheel seal cover, and both ends of the first rotor are respectively connected to the wheel axle cover and the wheel seal cover. In a projection plane orthogonal to the axial direction of the axis, the first rotor is located within the wheel axle cover and the wheel seal cover. The wheel axle cover and the wheel seal cover are used to enclose the chamber, and the wheel axle cover and the wheel seal cover can be clamped on the outer peripheral surface of the hub, so that the first rotor drives the hub to rotate through the wheel axle cover and the wheel seal cover.

[0015] In some embodiments, the stability enhancing device for the landing gear hub further includes a connecting member. The connecting member is disposed on a side of the wheel axle cover away from the wheel seal cover. One end of the connecting member passes through the wheel axle cover and is connected to the stator. The connecting member is axially rotatable relative to the wheel axle cover along the axis, and the other end of the connecting member is adapted to be connected to the landing gear.

[0016] In some embodiments, the stability enhancing device for the landing gear hub further includes a first bearing and a second bearing. The first bearing is disposed within the wheel seal cover, and the second bearing is disposed within the stator. Both ends of the axis are respectively inserted into the first bearing and the second bearing.

[0017] In some embodiments, the eccentric assembly includes a first eccentric block, a second eccentric block, a third eccentric block, and a retaining pin. The first eccentric block and the second eccentric block are axially spaced apart on the axis, so that the axis drives the first eccentric block and the second eccentric block to be rotatable. The third eccentric block is disposed between the first eccentric block and the second eccentric block. The third eccentric block is inserted through the axis and is axially rotatable relative to the axis around the axis. The retaining pin is disposed between the first eccentric block and the second eccentric block and is connected to the first eccentric block and the second eccentric block, so that when the eccentric assembly rotates, the retaining pin is used to limit the position of the movable third eccentric block.

[0018] In some embodiments, the first eccentric block is connected to the second rotor, so that the second rotor drives the first eccentric block to rotate.

[0019] The landing gear according to an embodiment of the present invention includes: a stability enhancing device for a landing gear wheel hub, and the stability enhancing device for a landing gear wheel hub is the stability enhancing device for a landing gear wheel hub according to any one of the above embodiments. Description of the Drawings

[0020] Figure 1 is an exploded view of the stability enhancing device for a landing gear wheel hub according to an embodiment of the present invention.

[0021] Figure 2 is a schematic structural view of a stator of the stability enhancing device for a landing gear wheel hub according to an embodiment of the present invention.

[0022] Figure 3 is an exploded view of an eccentric assembly of the stability enhancing device for a landing gear wheel hub according to an embodiment of the present invention.

[0023] Figure 4 is a schematic structural view of the stability enhancing device for a landing gear wheel hub according to an embodiment of the present invention installed on a landing gear and a fuselage

[0024] Stability enhancing device 100;

[0025] Shaft 1;

[0026] Stator 2; body 21; outer peripheral surface 211; first end face 212; first iron core assembly 22; first magnet 221; second iron core assembly 23; second magnet 231;

[0027] First rotor 3;

[0028] Second rotor 4;

[0029] Eccentric assembly 5; first eccentric block 51; second eccentric block 52; third eccentric block 53; retaining pin 54; wheel shaft cover 6; wheel seal cover 7; connecting member 8; first bearing 9; second bearing 10; limiting sleeve 11; wheel hub 12; landing gear 13; fuselage 14. Detailed Description of the Embodiment

[0030] The embodiments of the present invention will be described in detail below. The examples of the embodiments are shown in the drawings. The embodiments described below with reference to the drawings are exemplary and are intended to explain the present invention, but should not be construed as limiting the present invention.

[0031] The stability enhancing device 100 for a landing gear wheel hub according to an embodiment of the present invention will be described below with reference to the drawings.

[0032] As Figures 1-4 shown, the stability enhancing device 100 for a landing gear wheel hub according to an embodiment of the present invention includes: a shaft 1, a stator 2, a first rotor 3, a second rotor 4, and an eccentric assembly 5.

[0033] The stator 2 is sleeved on the shaft 1 and is rotatable relative to the shaft 1 along the axial direction of the shaft 1. The stator 2 can generate a first magnetic field and a second magnetic field. The first magnetic field extends along the radial direction of the shaft 1 (such as the inner and outer directions shown in Figure 1 ), and the second magnetic field extends along the axial direction of the shaft 1 (such as the left and right directions shown in Figure 1 ). Specifically, as shown in Figure 1 and Figure 2 , the shaft 1 is a rotating shaft extending in the left and right directions. The stator 2 is sleeved on the shaft 1 and the shaft 1 can rotate freely on the stator 2. The stator 2 can generate a changing first magnetic field and a second magnetic field. The first magnetic field extends towards the inner and outer directions, and the second magnetic field extends towards the left and right directions.

[0034] The first rotor 3 has a chamber that penetrates the first rotor 3 along the axial direction of the shaft 1. The stator 2 is arranged in the chamber so that the first magnetic field drives the first rotor 3 to be rotatable about the axial direction of the shaft 1. The first rotor 3 is adapted to be arranged in the hub 12 so that the first rotor 3 drives the hub 12 to rotate. Specifically, as shown in Figure 1 and 2 , the first rotor 3 is provided with a chamber that penetrates the first rotor 3 in the left and right directions. The stator 2 is arranged in the chamber so that the first rotor 3 generates electromagnetic induction under the action of the changing first magnetic field to make the first rotor 3 rotate about the left and right directions. The first rotor 3 can be arranged in the hub 12 and connected to the hub 12. Thus, the hub 12 is driven to rotate by the first rotor 3.

[0035] The second rotor 4 is arranged at one end of the stator 2 adjacent to the second magnetic field so that the second magnetic field drives the second rotor 4 to rotate about the axial direction of the shaft 1 under the action of electromagnetic induction. Specifically, as shown in Figure 1 and 2 , the second rotor 4 is sleeved on the shaft 1 and the second rotor 4 is arranged on one side of the second magnetic field so that the second rotor 4 generates electromagnetic induction under the action of the second magnetic field to make the second rotor 4 rotate about the left and right directions.

[0036] The eccentric component 5 is sleeved on the shaft 1 and arranged in the chamber. The eccentric component 5 is connected to the second rotor 4 so that the shaft 1 drives the eccentric component 5 to rotate to make the eccentric component 5 generate a vertically downward acting force. Specifically, as shown in Figure 1 and Figure 3 , the eccentric component 5 is arranged on the shaft 1 and located in the chamber. The eccentric component 5 can be connected to the second rotor 4 so that the eccentric component 5 is driven to rotate by the second rotor 4 to make the eccentric component 5 generate a vertically downward acting force.

[0037] The stability-enhancing device 100 for the landing gear hub according to the embodiment of the present utility model is provided with a stator 2, a first rotor 3, a second rotor 4 and an eccentric assembly 5. Through the cooperation of the first magnetic field of the stator 2 and the first rotor 3, the hub 12 and the tire have the functions of driving and braking. The second magnetic field, the second rotor 4 and the eccentric assembly 5 cooperate. The second rotor 4 drives the eccentric assembly 5 to perform a centrifugal motion through the shaft 1. By controlling the rotation phase of the eccentric assembly 5, the eccentric assembly 5 only generates a vertically downward acting force, and this acting force acts on the hub 12, so that the adhesion between the tire and the ground is increased, the tire firmly adheres to the ground, the skidding of the tire is reduced, and thus the operation of the fuselage is more stable, preventing the fuselage from losing its center of gravity and causing a rollover and breaking the fuselage and the wing.

[0038] In some embodiments, the stator 2 includes a body 21, a first iron core assembly 22, and a second iron core assembly 23. The body 21 is sleeved on the shaft 1 and is axially rotatable relative to the shaft 1 along the axial direction of the shaft 1. The body 21 has an outer peripheral surface 211, a first end surface 212, and a second end surface (not shown in the figure). The outer peripheral surface 211 is a closed surface extending circumferentially around the shaft 1. The first end surface 212 and the second end surface are axially spaced apart and opposite to each other, and the first end surface 212 and the second end surface are respectively connected to both ends of the outer peripheral surface 211. The first iron core assembly 22 is provided on the outer peripheral surface 211 of the body 21, and the second iron core assembly 23 is provided on the first end surface 212 of the body 21. The second rotor 4 is axially spaced apart and opposite to the first end surface 212 of the body 21 along the axial direction of the shaft 1. The first iron core assembly 22 generates a first magnetic field, and the second iron core assembly 23 generates a second magnetic field. Specifically, as Figure 1 and Figure 2 shown, the body 21 is generally cylindrical. The first end surface 212 is the left end surface of the body 21, the second end surface is the right end surface of the body 21. The outer peripheral surface 211 of the body 21 is a curved surface closed around the left-right direction. The first end surface 212 is provided at the right end of the outer peripheral surface 211 of the body 21, and the second end surface is provided at the left end of the body 21. The first iron core assembly 22 is provided on the outer peripheral surface 211 of the body 21, and the first iron core assembly 22 can be energized to generate a first magnetic field that changes in the inner-outer direction. The second iron core assembly 23 is provided on the first end surface 212, and the second iron core assembly 23 can be energized to generate a second magnetic field that changes in the left-right direction.

[0039] In some embodiments, there are multiple first iron core assemblies 22, and the multiple first iron core assemblies 22 are circumferentially spaced apart on the outer peripheral surface 211 of the body 21 around the shaft 1. There are multiple second iron core assemblies 23, and the multiple second iron core assemblies 23 are circumferentially spaced apart on the first end surface 212 of the body 21 around the shaft 1. Specifically, as Figure 2As shown, the number of the first iron core assemblies 22 may be equal to the number of the second iron core assemblies 23, or the number of the first iron core assemblies 22 may be different from the number of the second iron core assemblies 23. A plurality of the first iron core assemblies 22 and a plurality of the second iron core assemblies 23 are respectively disposed on the outer peripheral surface 211 and the first end surface 212 of the body 21 in a circumferentially rotatable manner around the body 21. Thereby, the magnetic field intensities of the first magnetic field and the second magnetic field are ensured.

[0040] In some embodiments, the first iron core assembly 22 includes a first magnet 221 and a first coil (not shown in the figure). The first magnet 221 extends in the radial direction of the axis 1 and is disposed on the outer peripheral surface 211 of the body 21. The first coil is wound around the first magnet 221. The second iron core assembly 23 includes a second magnet 231 and a second coil (not shown in the figure). The second magnet 231 extends in the axial direction of the axis 1 and is disposed on the outer peripheral surface 211 of the body 21. The second coil is wound around the second magnet 231. Specifically, as Figure 2 shown, the first magnet 221 is disposed on the outer peripheral surface 211 of the body 21 and extends in the inner and outer direction. The first coil is wound around the outer peripheral side of the first magnet 221. The second magnet 231 is disposed on the first end surface 212 of the body 21 and extends in the left and right direction. The second coil is wound around the outer peripheral side of the second magnet 231. Thereby, the magnetic field intensity of the first magnetic field is ensured through the cooperation of the first coil and the first magnet 221, and the magnetic field intensity of the second magnetic field is ensured through the cooperation of the second coil and the second magnet 231.

[0041] In some embodiments, the landing gear hub stability enhancing device 100 further includes a wheel axle cover 6 and a wheel seal cover 7. The wheel axle cover 6 and the wheel seal cover 7 are disposed opposite to each other at an axial interval along the axis 1. The first rotor 3 is disposed between the wheel axle cover 6 and the wheel seal cover 7, and both ends of the first rotor 3 are respectively connected to the wheel axle cover 6 and the wheel seal cover 7. In the projection plane orthogonal to the axial direction of the axis 1, the first rotor 3 is located within the wheel axle cover 6 and the wheel seal cover 7. The wheel axle cover 6 and the wheel seal cover 7 are used to enclose a chamber, and the wheel axle cover 6 and the wheel seal cover 7 can be clamped on the outer peripheral surface 211 of the hub 12 so that the first rotor 3 drives the hub 12 to rotate through the wheel axle cover 6 and the wheel seal cover 7. Specifically, as Figure 1 shown, both the wheel axle cover 6 and the wheel seal cover 7 are disc-shaped. The wheel axle cover 6 is disposed at the left end of the first rotor 3 and is connected to the left end of the first rotor 3. The wheel seal cover 7 is disposed at the right end of the first rotor 3 and is connected to the right end of the first rotor 3. Thereby, the chamber of the first rotor 3 can be enclosed by the wheel axle cover 6 and the wheel seal cover 7. The diameters of the wheel axle cover 6 and the wheel seal cover 7 are larger than the diameter of the outer peripheral surface 211 of the first rotor 3. Thereby, when the wheel axle cover 6 and the wheel seal cover 7 are installed on the first rotor 3, the hub 12 can be clamped between the wheel axle cover 6 and the wheel seal cover 7, so that the first rotor 3 drives the hub 12 to rotate through the wheel axle cover 6 and the wheel seal cover 7.

[0042] In some embodiments, the stability augmentation device 100 for the landing gear hub further includes a connecting member 8. The connecting member 8 is disposed on the side of the wheel axle cover 6 away from the wheel seal cover 7. One end of the connecting member 8 passes through the wheel axle cover 6 and is connected to the stator 2. The connecting member 8 is rotatable relative to the wheel axle cover 6 along the axial direction of the shaft 1, and the other end of the connecting member 8 is adapted to be connected to the landing gear. Specifically, as Figure 1 shown, the connecting member 8 can be a flange of the hub 12 and is disposed on the left side of the wheel axle cover 6. The right end of the connecting member 8 passes through the wheel axle cover 6 and is limited by a bayonet sleeve with the wheel axle cover 6. The stator 2 is connected to the right end of the connecting member 8 by screws or bolts, whereby the stator 2 is fixed on the connecting member 8. The left end of the connecting member 8 is connected to the landing gear by screws or bolts, so that the stability augmentation device 100 is fixed on the landing gear through the connecting member 8.

[0043] In some embodiments, the stability augmentation device 100 for the landing gear hub further includes a first bearing 9 and a second bearing 10. The first bearing 9 is disposed in the wheel seal cover 7, and the second bearing 10 is disposed in the stator 2. Both ends of the shaft 1 are respectively inserted into the first bearing 9 and the second bearing 10. Specifically, as Figure 1 shown, the first bearing 9 and the second bearing 10 can be ball bearings, roller bearings, etc. and are respectively disposed in the stator 2 and the wheel seal cover 7. The left and right ends of the shaft 1 are respectively disposed in the inner rings of the first bearing 9 and the second bearing 10, so that the shaft 1 is rotatably supported between the stator 2 and the wheel seal cover 7 through the first bearing 9 and the second bearing 10.

[0044] In some embodiments, the eccentric assembly 5 includes a first eccentric block 51, a second eccentric block 52, a third eccentric block 53, and a stop pin 54. The first eccentric block 51 and the second eccentric block 52 are axially spaced apart on the shaft 1 so that the shaft 1 drives the first eccentric block 51 and the second eccentric block 52 to rotate. The third eccentric block 53 is disposed between the first eccentric block 51 and the second eccentric block 52. The third eccentric block 53 is sleeved on the shaft 1 and is rotatable relative to the shaft 1 about the axial direction of the shaft 1. The stop pin 54 is disposed between the first eccentric block 51 and the second eccentric block 52 and is connected to the first eccentric block 51 and the second eccentric block 52. When the eccentric assembly 5 rotates, the stop pin 54 is used to limit the position of the movable third eccentric block 53. Specifically, as Figure 1 and Figure 3As shown in the figure, the first eccentric block 51 and the second eccentric block 52 are arranged at intervals in the left-right direction. The third eccentric block 53 is arranged between the first eccentric blocks 51. The first eccentric block 51, the second eccentric block 52, and the third eccentric block 53 are all sleeved on the shaft 1. The first eccentric block 51 and the second eccentric block 52 can rotate synchronously with the shaft 1, and the third eccentric block 53 can rotate freely on the shaft 1. The retaining pin 54 is arranged between the first eccentric block 51 and the second eccentric block 52, and both ends of the retaining pin 54 are connected to the first eccentric block 51 and the second eccentric block 52. The retaining pin 54 is arranged adjacent to the left end face and the outer peripheral face 211 of the first eccentric block 51 and the second eccentric block 52. The third eccentric block 53 is provided with a groove extending in the left-right direction, and the retaining pin 54 can be arranged in the groove, so as to limit the position of the movable third eccentric block 53 through the retaining pin 54. Thus, by the rotation of the eccentric assembly 5, a vertically downward acting force is generated, improving the stability of the wheel hub 12.

[0045] It should be noted that the eccentric assembly 5 in the embodiment of the present invention is similar in structure and function to the eccentric block of a road roller, and the eccentric assembly 5 in the embodiment of the present invention will not be specifically described.

[0046] In some embodiments, the first eccentric block 51 is connected to the second rotor 4 so that the second rotor 4 drives the first eccentric block 51 to rotate. Specifically, the first eccentric block 51 is connected to the second rotor 4 through a fastener. When the second rotor 4 rotates, it can drive the first eccentric block 51 to rotate, and then drive the eccentric assembly 5 to rotate.

[0047] As Figure 4 shown, the landing gear 13 according to the embodiment of the present invention includes a stability enhancing device 100 for the landing gear wheel hub.

[0048] The stability enhancing device 100 for the landing gear wheel hub is the stability enhancing device 100 in any one of the above embodiments.

[0049] The landing gear in the embodiment of the present invention has the advantages of simple structure and high stability.

[0050] Please refer to Figure 1 shown, the stability enhancing device 100 for the landing gear wheel hub in the embodiment of the present invention includes a connecting piece 8, a stator 2, a second rotor 4, an eccentric assembly 5, a shaft 1, a wheel shaft cover 6, a first rotor 3, a wheel seal cover 7, and a positional relationship.

[0051] As Figure 2 shown, the stator 2 is provided with two-direction magnetic force coils. The first magnet 221 is sleeved on the first coil, and the generated magnetic force direction acts on Figure 1There are 221 inner ring first magnets of the first rotor 3, arranged in a circular array with positive and negative magnetic poles, and there are multiple electrode first magnets 221 arranged in a circular array on the stator 2 disk, with an integrally formed connection structure. The said structure is a hub motor of the prior art. The magnetic force direction generated by the second magnet 231 sleeved on the second coil acts on Figure 1 the 231 second magnets of the second rotor 4. There are multiple second magnets 231 arranged in a circular array on the inner ring of the stator 2 disk, fastened with curing glue, and an integrally formed connection structure. The structure of this stator 2 integrates the hub motor and the disc motor into one.

[0052] Figure 3 As shown, the eccentric assembly 5 is provided with a first eccentric block 51, a second eccentric block 52 and a third eccentric block 53 in three-phase groups, stacked in sequence. The eccentric assembly 5 has two rotation directions. The first eccentric block 51 and the second eccentric block 52 rotate in the same direction as the shaft 1. The third eccentric block 53 is movably sleeved on the shaft 1, and the limit screw pin passes through the shaft 1 from the side hole and is fastened to the nut hole of the shaft 1 hole. The fan ends of the first eccentric block 51 and the second eccentric block 52 are provided with a retaining pin 54 with a phase pin hole. The retaining pin 54 always locks the rotation direction of the third eccentric block 53, and the rotation direction is opposite to that of the first eccentric block 51 and the second eccentric block 52. Both ends of the shaft 1 are sleeved with a first bearing 9 and a second bearing 10. The bearings at both ends of the shaft 1 are respectively placed in the inner holes of the wheel seal cover 7 and the stator 2. From the rotation direction of the eccentric group structure of the above-mentioned eccentric structure, it can be seen that when rotating one cycle, a centrifugal force in one quadrant is obtained, and the direction is always consistent with the direction of gravity. The structure of this eccentric assembly 5 is a prior art and is widely used in the drum structure of a roller.

[0053] Figure 1 As shown, the inner hole of the second rotor 4 is sleeved with the shaft 1, and the limit screw pin passes through the shaft 1 from the side hole and is fastened to the nut hole of the shaft 1 hole and is closely attached to the eccentric assembly 5. Both ends of the shaft 1 are sleeved with fixed bearings. One fixed bearing is connected to the inner hole of the connecting piece 8, and the other fixed bearing is connected to the inner hole of the wheel seal cover 7. The second rotor 4 is provided with a plurality of magnetic holes arranged in a circular array, and the magnet columns with positive and negative magnetic poles are inserted in sequence and fastened with curing glue. The above structure rotates as a whole, and the acting magnetic force is the second iron core of the stator 2 sleeved with the second coil and is placed inside the first rotor 3.

[0054] As Figure 1 shown, both sides of the first rotor 3 are provided with nut flange holes arranged in a circular array, corresponding to Figure 4 the flange holes of the wheel shaft cover 6 and Figure 1 the flange holes of the wheel seal cover 7 are fastened with screws, and the double-sided covers are sealed. Figure 4The bearing sleeved in the shaft hole of the wheel hub cover 6 is sleeved on the shaft diameter of the stator 2. The bearing in the inner hole of the wheel hub cover 6 is limited by the limit sleeve 11. The mounting screw holes of the stator 2 correspond to the fixing holes of the stator 2, and are fastened by screws passing through the corresponding screw holes. The stator 2 is fixedly connected to the connecting member 8 by screws. As Figure 2 shown, the outer diameter of the first rotor 3 is sleeved with a tire, and the tire is clamped by the outer diameters of the wheel seal cover 7 and the wheel hub cover 6.

[0055] Figure 1 shown, the connecting member 8 is sleeved through the wheel hub cover 6 and is limited by a clamping sleeve. The flange holes on the outer ring of the wheel hub cover 6 correspond to the nut flange holes of the first rotor 3 and are fastened by screws. The flange holes of the wheel seal cover 7 correspond to the nut flange holes of the first rotor 3 and are fastened by screws. The wheel hub cover 6 is provided with mounting flange holes, and the inner ring is provided with disc brake flange holes. The connecting member 8 is screwed to fix the stator 2. The coil heads on the stator 2 pass through the side holes of the shaft 1 of the connecting member 8, and the motor wire heads are led out of the inner hole of the flange. The connecting member 8 is provided with fixing holes for the landing gear. The fixing holes of the connecting member 8 are passed through by screws and fastened to the corresponding nuts for mounting the landing gear. The electric hub motor is electrically connected to the disc motor, and the power cord is led out and externally electrically connected to the controller through the holes of the flange plate.

[0056] Working process and principle control: The disc motor drives the eccentric component 5 to rotate. This structure only generates a centrifugal force in one direction of gravity. This centrifugal force acts on the tire of the wheel hub 12 and rotates and limits the rotation of the landing gear through the connecting member 8. The landing gear is connected to the fuselage. By controlling the magnitude of the current supplied to the disc motor, the speed of the motor determines the magnitude of the centrifugal force. The electrical signals of the tilt of the gyroscope sensor module on the fuselage are transmitted electrically to the disc motor controller, thereby controlling the tilt of the fuselage. The hub motor in this structure functions as a brake and a ground drive. When the controller is powered on, the hub motor rotates, enabling the drone to have a moving function on the ground. At the same time, during the landing phase, the commutation circuit of the hub motor controller closes the switch, and the voltage generated by the hub motor when generating electricity is connected in parallel to the resistor of the controller, consuming the generated electrical energy and functioning as a motor brake.

[0057] As Figure 4 shown, the stability-enhancing wheel hubs 12 of the landing gear of this aircraft are installed in the rear three-point type of the landing gear. The two wheel hubs 12 are symmetrical, controlling the stability of the fuselage during ground taxiing. With this structure of the wheel hub 12, through the eccentric component 5 making a centrifugal motion, the tire of the wheel hub 12 obtains adhesion to the ground, and it can be used for the ground tractor of a fixed-wing drone, or the stability control of a tricycle, or the drive wheel of an electric off-road vehicle.

[0058] This technical solution combines the structure of a hub motor (the combination of stator 2 and the first rotor 3) and a disc motor (the combination of stator 2 and the second rotor 4), with the stator 2 integrated. The electromagnetic force of the stator 2 of the hub 12 acts on the magnetic sheet of the wheel rim, enabling the hub 12 and the tire to rotate conventionally, with functions such as driving and braking. The disc rotor drives the eccentric module to perform centrifugal motion and phase control, generating only a pulling force in the direction of gravity. This pulling force acts on the hub 12, and the hub 12 connects the landing gear and the fuselage. When moving on the ground, the controller of the motor is controlled by the signal of the gyro sensor. The controller controls the speed of the disc motor, and the speed controls the magnitude of the centrifugal force, increasing the adhesion between the tire and the ground, making it not easy to slip, and the tire firmly adheres to the ground. Thus, by controlling the hub motors of the rear two sets of the tricycle landing gear, the fuselage is made stable. The advantage of this utility model is to obtain the above-mentioned actual beneficial effects.

[0059] In the description of this utility model, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing this utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model.

[0060] In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one of such features. In the description of this utility model, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise specifically and clearly defined.

[0061] In this utility model, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected with", "fixed", etc. should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection, an electrical connection, or communicable with each other; it can be directly connected, or indirectly connected through an intermediate medium, and it can be the internal communication of two elements or the interaction relationship between two elements, unless otherwise clearly limited. For those of ordinary skill in the art, the specific meanings of the above terms in this utility model can be understood according to specific circumstances.

[0062] In the present utility model, unless otherwise clearly defined and limited, the first feature being "on" or "under" the second feature may mean that the first and second features are in direct contact, or the first and second features are indirectly in contact through an intermediate medium. Moreover, the first feature being "above", "over" and "on top of" the second feature may mean that the first feature is directly above or obliquely above the second feature, or merely indicates that the first feature has a higher level height than the second feature. The first feature being "under", "below" and "beneath" the second feature may mean that the first feature is directly below or obliquely below the second feature, or merely indicates that the first feature has a lower level height than the second feature.

[0063] In the present utility model, the terms "an embodiment", "some embodiments", "examples", "specific examples", or "some examples", etc. mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present utility model. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described may be combined in a suitable manner in any one or more embodiments or examples. In addition, without contradiction, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples.

[0064] Although the embodiments of the present utility model have been shown and described above, it can be understood that the above embodiments are exemplary and should not be construed as limiting the present utility model. Those of ordinary skill in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of the present utility model.

Claims

1. A stabilization device for a landing gear hub, characterized in that: include: axis; a stator, the stator being disposed on the shaft and being rotatable relative to the shaft along the axial direction of the shaft, the stator being capable of generating a first magnetic field and a second magnetic field, the first magnetic field extending along the radial direction of the shaft, and the second magnetic field extending along the axial direction of the shaft; a first rotor, wherein the first rotor has a cavity penetrating the first rotor along the axial direction of the shaft, the stator is arranged in the cavity, so that the first magnetic field drives the first rotor to rotate around the axial direction of the shaft, and the first rotor is suitable for being arranged in a wheel hub, so that the first rotor drives the wheel hub to rotate; a second rotor, the second rotor being arranged at one end of the stator adjacent to the second magnetic field so that the second magnetic field drives the second rotor to rotate axially around the shaft; An eccentric component is provided on the shaft and in the chamber, and the eccentric component is connected to the second rotor so that the shaft drives the eccentric component to rotate so that the eccentric component generates a vertical downward force.

2. The landing gear hub stabilization device according to claim 1, characterized in that: The stator includes a body, a first core assembly, and a second core assembly. The body is inserted into the shaft and is rotatable relative to the shaft along the axial direction of the shaft. The body has an outer circumferential surface, a first end surface, and a second end surface. The outer circumferential surface is a closed surface extending circumferentially around the shaft. The first end surface and the second end surface are arranged opposite to each other along the axial direction of the shaft, and the first end surface and the second end surface are respectively connected to the two ends of the outer circumferential surface. The first core assembly is arranged on the outer circumferential surface of the body, and the second core assembly is arranged on the first end surface of the body. The second rotor and the first end surface of the body are arranged opposite to each other along the axial direction of the shaft. The first core assembly generates the first magnetic field, and the second core assembly generates the second magnetic field.

3. The landing gear hub stabilization device according to claim 2, characterized in that: There are a plurality of first core components, and the plurality of first core components are arranged on the outer peripheral surface of the body at intervals in the circumferential direction around the shaft. And / or, there are a plurality of second core components, and the plurality of second core components are arranged on the first end surface of the body at intervals in the circumferential direction of the axis.

4. The landing gear hub stabilization device according to claim 2, characterized in that: The first core assembly includes a first magnet and a first coil, wherein the first magnet extends in the radial direction of the shaft and is disposed on the outer peripheral surface of the body, and the first coil is wound around the first magnet. And / or, the second core component includes a second magnet and a second coil, the second magnet extends along the axial direction of the shaft and is arranged on the outer circumferential surface of the body, and the second coil is wound around the second magnet.

5. The landing gear hub stabilization device according to claim 1, characterized in that: It also includes a wheel axle cover and a wheel seal cover, wherein the wheel axle cover and the wheel seal cover are arranged opposite to each other along the axial direction of the shaft, the first rotor is arranged between the wheel axle cover and the wheel seal cover, and the two ends of the first rotor are respectively connected to the wheel axle cover and the wheel seal cover, In a projection plane orthogonal to the axial direction of the shaft, the first rotor is located inside the axle cover and the wheel seal cover, the axle cover and the wheel seal cover are used to close the chamber, and the axle cover and the wheel seal cover can be clamped on the outer circumferential surface of the wheel hub, so that the first rotor drives the wheel hub to rotate through the axle cover and the wheel seal cover.

6. The landing gear hub stabilization device according to claim 5, characterized in that: It also includes a connecting member, which is arranged on a side of the axle cover away from the wheel seal cover, one end of the connecting member passes through the axle cover and is connected to the stator, the connecting member is rotatable relative to the axle cover along the axial direction of the shaft, and the other end of the connecting member is suitable for being connected to the landing gear.

7. The landing gear hub stabilization device according to claim 5, characterized in that: It also includes a first bearing and a second bearing, wherein the first bearing is arranged in the wheel cover, and the second bearing is arranged in the stator, and both ends of the shaft are respectively inserted into the first bearing and the second bearing.

8. The landing gear hub stabilization device according to claim 1, characterized in that: The eccentric assembly includes a first eccentric block, a second eccentric block, a third eccentric block and a stop pin. The first eccentric block and the second eccentric block are arranged on the shaft at intervals along the axial direction so that the shaft can drive the first eccentric block and the second eccentric block to rotate. The third eccentric block is arranged between the first eccentric block and the second eccentric block. The third eccentric block is passed through the shaft and can be rotated around the axial direction of the shaft relative to the shaft. The stop pin is arranged between the first eccentric block and the second eccentric block and is connected to the first eccentric block and the second eccentric block so that when the eccentric assembly rotates, the stop pin is used to limit the position of the movable third eccentric block.

9. The landing gear hub stabilization device according to claim 8, characterized in that: The first eccentric mass is connected to the second rotor so that the second rotor drives the first eccentric mass to rotate.

10. A landing gear, characterized in that: include: A stabilizing device for a landing gear hub, wherein the stabilizing device for a landing gear hub is the stabilizing device for a landing gear hub as described in any one of claims 1 to 9.

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