Aircraft nose landing gear device and unmanned aerial vehicle

Abstract

According to the unmanned aerial vehicle nose landing gear device and the unmanned aerial vehicle, in an oil gas buffering structure, an oil seal cover assembly is located at the lower end of an oil cylinder assembly, the upper end of a piston rod assembly is inserted into the oil cylinder assembly through the oil seal cover assembly, and a cavity used for storing hydraulic oil and high-pressure nitrogen is formed in the oil cylinder assembly; the air tap fixing pipe is fixedly connected with the oil cylinder, the upper end of the air tap fixing pipe penetrates through the oil cylinder and is connected with the nitrogen charging connector, and the throttling valve is located in the oil cylinder and is connected with the lower end of the air tap fixing pipe; the installation support structure comprises an installation support assembly used for being fixedly connected with an unmanned aerial vehicle body, and the installation support assembly is fixedly connected with an oil cylinder assembly. The main wheel structure comprises a front fork assembly connected with the lower end of the piston rod assembly and a front wheel assembly rotationally connected with the front fork assembly, the front fork assembly is connected with the lower end of the piston rod assembly, and the steering structure is used for enabling the front fork assembly to rotate in the axial direction of the piston rod assembly so as to adjust steering of the front wheel assembly.

Description

Technical Field

[0001] The present invention relates to the technical field of flight devices, and particularly relates to a nose landing gear device for an unmanned aerial vehicle and an unmanned aerial vehicle. Background Art

[0002] At present, the nose landing gear structures of small and medium-sized unmanned aerial vehicles are mainly two types: spring shock absorbers and rubber shock absorbers. The spring shock absorber produces a shock-absorbing effect by compressing a spring, and the damper provides damping characteristics for the system. The shock-absorbing effect is within an acceptable range, and the structure is relatively simple with a relatively small number of parts. However, the disadvantage is that the manufacturing cost of the spring is relatively high in the scenario of large-load unmanned aerial vehicles, and the spring shock absorber is prone to bouncing during landing, and the spring is prone to non-return phenomenon when the compression time is too long. The rubber shock absorber produces a shock-absorbing effect by compressing industrial shock-absorbing rubber. The manufacturing cost of the rubber shock absorber is relatively low, and the engineering implementation difficulty is not great, but there are problems such as poor shock-absorbing effect and no damping characteristics.

[0003] Therefore, how to improve the shock-absorbing effect is an urgent problem to be solved by those skilled in the art. Summary of the Invention

[0004] In view of this, the present invention provides a nose landing gear device for an unmanned aerial vehicle to improve the shock-absorbing effect. The present invention also discloses an unmanned aerial vehicle having the above-mentioned nose landing gear device for an unmanned aerial vehicle.

[0005] To achieve the above object, the present invention provides the following technical solutions:

[0006] A nose landing gear device for an unmanned aerial vehicle, comprising:

[0007] An oil-gas buffer structure, the oil-gas buffer structure includes an oil cylinder assembly, an oil seal cover assembly and a piston rod assembly. The oil seal cover assembly is located at the lower end of the oil cylinder assembly. The upper end of the piston rod assembly is inserted into the oil cylinder assembly through the oil seal cover assembly. The oil cylinder assembly has a cavity for storing hydraulic oil and high-pressure nitrogen. The oil cylinder assembly includes an oil cylinder, a gas nozzle fixing pipe, a nitrogen filling nozzle and a throttle valve. The gas nozzle fixing pipe is fixedly connected to the oil cylinder. The upper end of the gas nozzle fixing pipe passes through the oil cylinder and is connected to the nitrogen filling nozzle. The throttle valve is located in the oil cylinder and is connected to the lower end of the gas nozzle fixing pipe;

[0008] An installation bracket structure, the installation bracket structure includes an installation bracket assembly for fixedly connecting with the main body of the unmanned aerial vehicle. The installation bracket assembly is fixedly connected to the oil cylinder assembly;

[0009] Main wheel structure, the main wheel structure includes a front fork assembly connected to the lower end of the piston rod assembly and a front wheel assembly rotatably connected to the front fork assembly, and the front fork assembly is connected to the lower end of the piston rod assembly;

[0010] Steering structure, the steering structure is used to rotate the front fork assembly along the axial direction of the piston rod assembly to adjust the steering of the front wheel assembly.

[0011] Optionally, in the above-mentioned unmanned aerial vehicle front landing gear device, the piston rod assembly includes a piston rod and a damping ring arranged on the piston rod, and the damping ring can cooperate with the oil cylinder assembly to provide a rebound damping force.

[0012] Optionally, in the above-mentioned unmanned aerial vehicle front landing gear device, the damping ring is detachably arranged on the piston rod;

[0013] The piston rod assembly further includes:

[0014] Limit hole ring, the limit hole ring is sleeved outside the piston rod from the upper end of the piston rod and is axially limited to the piston rod;

[0015] Piston hole ring, the piston hole ring is sleeved outside the piston rod from the upper end of the piston rod, and the outer wall of the piston hole ring has a guide ring groove for assembling the hole ring guide ring, and the damping ring is limited between the limit hole ring and the piston hole ring;

[0016] Piston nut, the piston nut is detachably connected to the upper end of the piston rod.

[0017] Optionally, in the above-mentioned unmanned aerial vehicle front landing gear device, the damping ring is sleeved outside the piston rod from the upper end of the piston rod and is connected to the limit hole ring;

[0018] The piston rod assembly further includes:

[0019] Spacer ring, the spacer ring is sleeved outside the piston rod from the upper end of the piston rod and is located above the damping ring;

[0020] Pad ring, the pad ring is sleeved outside the piston rod from the upper end of the piston rod and is located above the spacer ring, and the upper end surface of the pad ring contacts the lower end surface of the piston hole ring.

[0021] Optionally, in the above-mentioned unmanned aerial vehicle front landing gear device, the piston rod assembly further includes:

[0022] Support tube, the support tube is placed inside the piston rod and the lower end of the support tube passes through the lower end of the piston rod;

[0023] Hydraulic oil filling nozzle, the hydraulic oil filling nozzle is connected to the lower end of the support tube;

[0024] A betting oil pipe, the betting oil pipe is located inside the support pipe and the lower end is fixedly connected to the support pipe;

[0025] An oil seal push rod, the lower end of the oil seal push rod is matched with the upper end of the support pipe and fixedly connected to the upper end of the betting oil pipe.

[0026] Optionally, in the above-mentioned front landing gear device of the unmanned aerial vehicle, the steering structure includes:

[0027] A steering ring assembly rotatably arranged outside the oil cylinder assembly, and the axis of the steering ring assembly coincides with the axis of the piston rod assembly;

[0028] An anti-torsion arm mechanism connecting the steering ring assembly and the front fork assembly, and the front fork assembly is rotatably matched with the lower end of the piston rod assembly;

[0029] A servo motor assembly, and the axis of the servo motor assembly is parallel to the axis of the piston rod assembly;

[0030] A rocker arm mechanism connecting the steering ring assembly and the servo motor assembly.

[0031] Optionally, in the above-mentioned front landing gear device of the unmanned aerial vehicle, the anti-torsion arm mechanism includes:

[0032] An upper anti-torsion arm assembly, the upper anti-torsion arm assembly is rotatably connected to the steering ring assembly along a first axis, and the first axis is perpendicular to the axis of the piston rod assembly,

[0033] A lower anti-torsion arm assembly, one end of the lower anti-torsion arm assembly is hinged to the upper anti-torsion arm assembly through a connecting shaft assembly, the axis of the connecting shaft assembly is parallel to the first axis, and the other end of the lower anti-torsion arm assembly is rotatably connected to the front fork assembly along a second axis, and the second axis is parallel to the first axis.

[0034] Optionally, in the above-mentioned front landing gear device of the unmanned aerial vehicle, the connecting shaft assembly is a quick-insert shaft assembly, including:

[0035] A quick-insert shaft, one end of the quick-insert shaft has an anti-disengagement head, and the other end of the quick-insert shaft can penetrate the rotation connection holes of the lower anti-torsion arm assembly and the upper anti-torsion arm assembly;

[0036] A gap adjusting piece sleeved on the quick-insert shaft, and the number of the gap adjusting pieces is at least one;

[0037] A quick-insert shaft sleeve sleeved on the other end of the quick-insert shaft;

[0038] Quick-insert shaft pin, which is used for plugging and mating with the other end of the quick-insert shaft and the pin hole of the quick-insert shaft sleeve.

[0039] Optionally, in the above unmanned aerial vehicle front landing gear device, the rocker mechanism includes:

[0040] A rocker assembly, one end of which is connected to the driving end of the servo assembly;

[0041] A rocker link assembly, one end of which is rotatably connected to the other end of the rocker assembly along a third axis parallel to the axis of the piston rod assembly, and the other end of the rocker link assembly is rotatably connected to the steering ring assembly along a fourth axis parallel to the third axis.

[0042] The present invention also provides an unmanned aerial vehicle, including an unmanned aerial vehicle main body and an unmanned aerial vehicle front landing gear device, and the unmanned aerial vehicle front landing gear device is the unmanned aerial vehicle front landing gear device as described in any one of the above.

[0043] As can be seen from the above technical solutions, in the unmanned aerial vehicle front landing gear device provided by the present invention, when the front wheel assembly touches the ground (such as when an unmanned aerial vehicle with the unmanned aerial vehicle front landing gear device lands), the front wheel assembly moves towards the oil-gas buffer structure, pushing the piston rod assembly to contract into the oil cylinder assembly, so that the hydraulic oil inside the oil cylinder assembly flows through the throttle valve - generating heat to absorb energy. When the compression process reaches equilibrium under the action of high-pressure nitrogen, the high-pressure nitrogen inside the oil cylinder assembly will apply pressure to the hydraulic oil, causing the piston rod assembly to extend out of the oil cylinder assembly. Since the oil cylinder assembly includes an oil cylinder -, a nozzle fixing tube -, and a nitrogen filling nozzle -, therefore, according to the actual load situation, nitrogen can be filled and discharged into the cavity of the oil cylinder assembly through the nitrogen filling nozzle -, thereby realizing the function of adjusting the bearing capacity of the unmanned aerial vehicle front landing gear device, and effectively improving the shock absorption effect.

[0044] The unmanned aerial vehicle provided by the present invention has the above unmanned aerial vehicle front landing gear device. Since the above unmanned aerial vehicle front landing gear device has the above technical effects, the unmanned aerial vehicle with the above unmanned aerial vehicle front landing gear device should also have the same technical effects, which will not be repeated here one by one. Description of the Drawings

[0045] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the following drawings are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0046] Figure 1 Schematic front view structure diagram of the nose landing gear device of the unmanned aerial vehicle provided by the embodiment of the present invention;

[0047] Figure 2 Schematic side view structure diagram of the nose landing gear device of the unmanned aerial vehicle provided by the embodiment of the present invention;

[0048] Figure 3 Explosion structure diagram of the nose landing gear device of the unmanned aerial vehicle provided by the embodiment of the present invention;

[0049] Figure 4 Schematic diagram of the nose landing gear device of the unmanned aerial vehicle provided by the embodiment of the present invention during the landing process;

[0050] Figure 5 First axonometric structure diagram of the nose landing gear device of the unmanned aerial vehicle provided by the embodiment of the present invention;

[0051] Figure 6 Second axonometric structure diagram of the nose landing gear device of the unmanned aerial vehicle provided by the embodiment of the present invention;

[0052] Figure 7 Explosion structure diagram of the oil cylinder assembly provided by the embodiment of the present invention;

[0053] Figure 8 Structure diagram of the oil cylinder assembly provided by the embodiment of the present invention;

[0054] Figure 9 Structure diagram of the oil cylinder provided by the embodiment of the present invention;

[0055] Figure 10 Structure diagram of the air nozzle fixing pipe provided by the embodiment of the present invention;

[0056] Figure 11 Structure diagram of the throttle valve provided by the embodiment of the present invention;

[0057] Figure 12 Half structure diagram of the steering bushing provided by the embodiment of the present invention;

[0058] Figure 13 Explosion structure diagram of the oil seal cover assembly provided by the embodiment of the present invention;

[0059] Figure 14 Structure diagram of the oil seal cover assembly provided by the embodiment of the present invention;

[0060] Figure 15 Three-dimensional structure diagram of the oil seal cover assembly provided by the embodiment of the present invention;

[0061] Figure 16Explosion structure diagram of the piston rod assembly provided by the embodiment of the present invention;

[0062] Figure 17 Schematic diagram of the assembly process of the piston rod assembly provided by the embodiment of the present invention;

[0063] Figure 18 Schematic diagram of the structure of the piston rod assembly provided by the embodiment of the present invention;

[0064] Figure 19 Schematic diagram of the structure of the front fork assembly provided by the embodiment of the present invention;

[0065] Figure 20 Explosion structure diagram of the steering ring assembly provided by the embodiment of the present invention;

[0066] Figure 21 Schematic diagram of the structure of the steering ring assembly provided by the embodiment of the present invention;

[0067] Figure 22 Explosion structure diagram of the upper anti-torsion arm assembly provided by the embodiment of the present invention;

[0068] Figure 23 Schematic diagram of the structure of the upper anti-torsion arm assembly provided by the embodiment of the present invention;

[0069] Figure 24 Explosion structure diagram of the connecting shaft assembly provided by the embodiment of the present invention;

[0070] Figure 25 Schematic diagram of the structure of the connecting shaft assembly provided by the embodiment of the present invention;

[0071] Figure 26 Explosion structure diagram of the rocker link assembly provided by the embodiment of the present invention;

[0072] Figure 27 Explosion structure diagram of the servo assembly provided by the embodiment of the present invention;

[0073] Figure 28 Schematic diagram of the structure of the servo assembly provided by the embodiment of the present invention;

[0074] Figure 29 Explosion structure diagram of the rocker assembly provided by the embodiment of the present invention;

[0075] Figure 30 Schematic diagram of the structure of the rocker assembly provided by the embodiment of the present invention;

[0076] Figure 31 Schematic diagram of the structure of the front wheel assembly provided by the embodiment of the present invention;

[0077] Figure 32This is a schematic structural diagram of the mounting bracket assembly provided by the embodiment of the present invention. Detailed implementation manners

[0078] The present invention discloses a nose landing gear device for an unmanned aerial vehicle to improve the shock absorption effect. The present invention also discloses an unmanned aerial vehicle having the above-mentioned nose landing gear device for an unmanned aerial vehicle.

[0079] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0080] As Figures 1 - 7 shown, the embodiment of the present invention provides a nose landing gear device for an unmanned aerial vehicle, including an oil-gas buffer structure, a mounting bracket structure, a main wheel structure, and a steering structure. The oil-gas buffer structure includes an oil cylinder assembly 1, an oil seal cover assembly 2, and a piston rod assembly 3. The oil seal cover assembly 2 is located at the lower end of the oil cylinder assembly 1. The upper end of the piston rod assembly 3 is inserted into the oil cylinder assembly 1 through the oil seal cover assembly 2. The oil cylinder assembly 1 has a cavity for storing hydraulic oil and high-pressure nitrogen. The oil cylinder assembly 1 includes an oil cylinder 1-1, a nozzle fixing pipe 1-2, a nitrogen filling nozzle 1-12, and a throttle valve 1-8. The nozzle fixing pipe 1-2 is fixedly connected to the oil cylinder 1-1. The upper end of the nozzle fixing pipe 1-2 passes through the oil cylinder 1-1 and is connected to the nitrogen filling nozzle 1-12. The throttle valve 1-8 is located in the oil cylinder 1-1 and is connected to the lower end of the nozzle fixing pipe 1-2. The mounting bracket structure includes a mounting bracket assembly 13 for fixedly connecting to the unmanned aerial vehicle body. The mounting bracket assembly 13 is fixedly connected to the oil cylinder assembly 1. The main wheel structure includes a front fork assembly 4 connected to the lower end of the piston rod assembly 3 and a front wheel assembly 12 rotatably connected to the front fork assembly 4. The front fork assembly 4 is connected to the lower end of the piston rod assembly 3. The steering structure is used to rotate the front fork assembly 4 along the axial direction of the piston rod assembly 3 to adjust the steering of the front wheel assembly 12.

[0081] The nose landing gear device provided by the embodiment of the present invention, when the front wheel assembly 12 touches the ground (such as when the unmanned aerial vehicle with this nose landing gear device lands), the front wheel assembly 12 moves towards the oil-gas buffer structure, pushing the piston rod assembly 3 to contract into the oil cylinder assembly 1, so that the hydraulic oil inside the oil cylinder assembly 1 flows through the throttle valve 1-8 to generate heat and absorb energy. When the compression process reaches equilibrium under the action of high-pressure nitrogen, the high-pressure nitrogen inside the oil cylinder assembly 1 will apply pressure to the hydraulic oil, causing the piston rod assembly 3 to extend out of the oil cylinder assembly 1. Since the oil cylinder assembly 1 includes an oil cylinder 1-1, a nozzle fixing pipe 1-2 and a nitrogen filling nozzle 1-12, therefore, according to the actual load condition, nitrogen can be filled and discharged into the cavity of the oil cylinder assembly 1 through the nitrogen filling nozzle 1-12, so as to realize the function of adjusting the bearing capacity of the nose landing gear device of the unmanned aerial vehicle, thereby effectively improving the shock absorption effect.

[0082] The function of the oil cylinder assembly 1 is to provide a cavity for storing hydraulic oil and high-pressure nitrogen for the nose landing gear device of the unmanned aerial vehicle, and at the same time bear the nitrogen pressure, provide throttling to absorb energy, and can also perform functions such as nitrogen pressure adjustment.

[0083] Among them, the mounting bracket assembly 13 can be fixedly connected to the unmanned aerial vehicle body by bolts or welding.

[0084] The above-mentioned nose landing gear device of the unmanned aerial vehicle may further include a nozzle cap 1-6, and the nozzle cap 1-6 is detachably arranged on the nitrogen filling nozzle 1-12 to close the nitrogen filling nozzle 1-12 when the nitrogen filling nozzle 1-12 is not inflated or deflated.

[0085] Such as Figures 7 - 11 As shown, in some embodiments, the oil cylinder assembly 1 may further include at least one of a nozzle fixing pipe gasket ring 1-3, a nozzle fixing pipe gasket 1-4, a nozzle fixing pipe nut 1-5, a buffer pad 1-7, a nozzle fixing pipe end face seal ring 1-10, a nozzle fixing pipe vertical seal ring 1-11, a nozzle fixing pipe lower oil seal 1-13, a nozzle fixing pipe guide ring 1-14 and a throttle valve seal ring 1-15.

[0086] Among them, the buffer pads 1-7 are placed inside the inner hole of the oil cylinder 1-1. The vertical seal ring 1-11 of the air nozzle fixing pipe is arranged in the upper vertical seal groove of the air nozzle fixing pipe 1-2. The end face seal ring 1-10 of the air nozzle fixing pipe is arranged in the upper end face seal groove of the air nozzle fixing pipe 1-2. The guide ring 1-14 of the air nozzle fixing pipe is arranged in the lower guide ring groove of the air nozzle fixing pipe 1-2. The lower oil seal 1-13 of the air nozzle fixing pipe is arranged in the lower oil seal groove of the air nozzle fixing pipe 1-2. The throttle valve 1-8 can be in threaded fit with the air nozzle fixing pipe 1-2, so that the throttle valve 1-8 is screwed into the lower threaded hole of the air nozzle fixing pipe 1-2 in a clockwise or counterclockwise direction. The number of the throttle valve seal rings 1-15 can be at least one (such as one or two, etc.). The throttle valve seal rings 1-15 are arranged in the inner seal groove openings of the throttle valve 1-8. During the specific installation process, the air nozzle fixing pipe 1-2 can be inserted into the inside of the oil cylinder 1-1 from below the oil cylinder 1-1. The upper end of the air nozzle fixing pipe 1-2 can pass through the upper part of the oil cylinder 1-1. The air nozzle fixing pipe gasket ring 1-3 and the air nozzle fixing pipe gasket 1-4 are sleeved on the air nozzle fixing pipe 1-2 from above the oil cylinder 1-1. At least one air nozzle fixing pipe nut 1-5 (such as one or two, etc.) is used to fasten the upper end of the air nozzle fixing pipe 1-2 from above the oil cylinder 1-1. The nitrogen filling nozzle 1-12 can be in threaded fit with the air nozzle fixing pipe 1-2, so that the nitrogen filling nozzle 1-12 is screwed into the threaded hole above the air nozzle fixing pipe 1-2 in a clockwise or counterclockwise direction. The air nozzle cover 1-6 can be screwed into the upper threaded part of the nitrogen filling nozzle 1-12 in a clockwise or counterclockwise direction.

[0087] The steering bushing 1-9 can cooperate with the steering structure. The number of the steering bushings 1-9 can be at least one (such as one or two, etc.) and is placed in the steering chute on the outer side of the lower part of the oil cylinder 1-1. As Figure 12 shown, the steering bushing 1-9 can be composed of two semi-circular arc structures on both sides, which facilitates the assembly of the steering bushing 1-9.

[0088] The function of the oil seal cover assembly 2 is to provide a sealing effect for the hydraulic oil and nitrogen in the oil-gas buffer structure. The oil seal cover assembly 2 includes an oil cylinder cover 2-1. The outer wall of the oil cylinder cover 2-1 can cooperate with the oil cylinder assembly 1, and the inner wall of the oil cylinder cover 2-1 can cooperate with the piston rod assembly 3.

[0089] As Figure 13 、 Figure 14 and Figure 15 shown, the oil seal cover assembly 2 can also include at least one of an oil seal cover vertical seal ring 2-2, an oil seal cover end face seal ring 2-3, an oil seal cover inner oil seal 2-4, an oil seal cover inner dust seal 2-5 and a cover inner guide ring 2-6.

[0090] Among them, the end face seal ring 2-3 of the oil seal cover is arranged in the seal groove on the end face of the oil cylinder cover 2-1. The number of the vertical face seal rings 2-2 of the oil seal cover can be at least one (such as one or two, etc.). The vertical face seal rings 2-2 of the oil seal cover are arranged in the seal groove on the vertical face (outer peripheral face) of the oil cylinder cover 2-1. The number of the inner oil seals 2-4 of the oil seal cover can be at least one (such as one or two, etc.). The inner oil seals 2-4 of the oil seal cover are arranged in the inner oil seal groove of the oil cylinder cover 2-1. The number of the inner guide rings 2-6 of the oil seal cover can be at least one (such as one or two, etc.). The inner guide rings 2-6 of the oil seal cover are arranged in the inner guide ring groove of the oil cylinder cover 2-1. The inner dust seal 2-5 of the oil seal cover is arranged in the inner dust seal groove of the oil cylinder cover 2-1.

[0091] The functions of the piston rod assembly 3 are as follows: a. It plays a role in bearing buffering and supporting during the landing and takeoff process of the unmanned aerial vehicle. b. It provides a rebound damping effect during the buffering process. C. It plays a role in filling hydraulic oil during daily maintenance.

[0092] The above function a can be achieved through the cooperation between the piston rod assembly 3 and the oil cylinder assembly 1.

[0093] Such as Figure 16 、 Figure 17 and Figure 18 As shown, in some embodiments, in order to achieve the above function b, the piston rod assembly 3 may include a piston rod 3-1 and a damping ring 3-6 arranged on the piston rod 3-1. The damping ring 3-6 can cooperate with the oil cylinder assembly 1 to provide a rebound damping force. That is, during the shock absorption process of the above oil-gas buffer structure, the high-pressure nitrogen will absorb energy and slowly release it through the action of the damping ring 3-6 during the release process, thereby avoiding the rebound of the piston rod 3-1 and achieving the functions of shock absorption and damping rebound.

[0094] In the unmanned aerial vehicle front landing gear device provided by the embodiment of the present invention, different rebound damping forces can be provided by replacing different types of damping rings 3-6, so as to facilitate the realization of the function of adjustable rebound speed.

[0095] In some embodiments, the piston rod assembly 3 further includes a limit hole ring 3-2, a piston hole ring 3-4 and a piston nut 3-5. Among them, the limit hole ring 3-2 is sleeved outside the piston rod 3-1 from the upper end of the piston rod 3-1 and is axially limited with the piston rod 3-1; the piston hole ring 3-4 is sleeved outside the piston rod 3-1 from the upper end of the piston rod 3-1, and the outer wall of the piston hole ring 3-4 has a guide ring hole groove for assembling the hole ring guide ring 3-14, and the damping ring 3-6 is limited between the limit hole ring 3-2 and the piston hole ring 3-4; the piston nut 3-5 is detachably connected to the upper end of the piston rod 3-1. Since the damping ring 3-6 is limited between the limit hole ring 3-2 and the piston hole ring 3-4, the two end faces of the damping ring 3-6 only need to be in contact with the limit hole ring 3-2 and the piston hole ring 3-4 respectively to realize the limit of the damping ring 3-6 on the piston rod 3-1. By relatively disassembling the piston nut 3-5 and the piston rod 3-1, the limit hole ring 3-2, the damping ring 3-6 and the piston hole ring 3-4 can be removed from the piston rod 3-1, so as to facilitate the replacement of the damping ring 3-6.

[0096] Further, the damping ring 3-6 is sleeved outside the piston rod 3-1 from the upper end of the piston rod 3-1 and is in contact with the limit hole ring 3-2;

[0097] The piston rod assembly 3 further includes a spacer ring 3-7 and a cushion ring 3-3. The spacer ring 3-7 is sleeved outside the piston rod 3-1 from the upper end of the piston rod 3-1 and is located above the damping ring 3-6; the cushion ring 3-3 is sleeved outside the piston rod 3-1 from the upper end of the piston rod 3-1 and is located above the spacer ring 3-7, and the upper end face of the cushion ring 3-3 is in contact with the lower end face of the piston hole ring 3-4.

[0098] During the assembly process, the limit hole ring 3-2 can be assembled into the shaft tube above the piston rod 3-1 and slide down to the limit position of the piston rod 3-1, the damping ring 3-6 is assembled above the limit hole ring 3-2, the spacer ring 3-7 is assembled into the shaft tube above the piston rod 3-1 and slides down above the limit hole ring 3-2, the cushion ring 3-3 is assembled into the shaft tube above the piston rod 3-1 and slides down above the spacer ring 3-7, the piston hole ring 3-4 is assembled into the shaft tube above the piston rod 3-1 and slides down above the cushion ring 3-3, the piston nut 3-5 is screwed into the threaded part above the piston rod 3-1 in a clockwise or counterclockwise direction and tightened. The number of the hole ring guide rings 3-14 can be at least one (such as one or two), and the hole ring guide rings 3-14 are assembled into the guide ring hole grooves of the piston hole ring 3-4 to complete the assembly operation.

[0099] To achieve the above function c, in the nose landing gear device of the unmanned aerial vehicle provided by the embodiment of the present invention, the piston rod assembly 3 further includes a support tube 3-8, a hydraulic oil filling nozzle 3-16, a lower injection oil pipe 3-10, and an oil seal push rod 3-9. The support tube 3-8 is placed inside the piston rod 3-1, and the lower end of the support tube 3-8 passes through the lower end of the piston rod 3-1; the hydraulic oil filling nozzle 3-16 is connected to the lower end of the support tube 3-8; the lower injection oil pipe 3-10 is located inside the support tube 3-8 and is fixedly connected to the lower end of the support tube 3-8; the oil seal push rod 3-9, the lower end of the oil seal push rod 3-9 is matched with the upper end of the support tube 3-8 and is fixedly connected to the upper end of the lower injection oil pipe 3-10. That is, hydraulic oil can be filled into the cavity of the oil cylinder assembly 1 through the hydraulic oil filling nozzle 3-16.

[0100] The piston rod assembly 3 may further include at least one of a sealing snap ring 3-11, a sealing rubber ring 3-12, a sealing gasket ring 3-13, a hydraulic oil combined sealing gasket 3-15, a push rod oil seal 3-17, a push rod guide ring 3-18, a push rod vertical sealing ring 3-19, a support tube end face sealing ring 3-20, a lower injection oil pipe vertical sealing ring 3-21, and a lower injection oil pipe end face sealing ring 3-22.

[0101] Among them, during the assembly process, the number of vertical sealing rings 3-21 of the lower injection oil pipe can be multiple (such as three), which are respectively assembled into the vertical (outer peripheral surface) sealing grooves above and below the lower injection oil pipe 3-10. The number of end surface sealing rings 3-22 of the lower injection oil pipe can be multiple (such as two) and are respectively assembled into the end surface sealing grooves above and below the lower injection oil pipe 3-10. The lower injection oil pipe 3-10 and the support pipe 3-8 can be connected by threads. For example, the lower injection oil pipe 3-10 is inserted from above the support pipe 3-8 and tightened clockwise or counterclockwise. The support pipe end surface sealing ring 3-20 is assembled into the end surface sealing groove below the support pipe 3-8. The push rod vertical sealing ring 3-19 is assembled into the vertical (outer peripheral surface) sealing groove below the oil seal push rod 3-9. The push rod guide ring 3-18 is assembled into the guide ring groove below the oil seal push rod 3-9. The push rod oil seal 3-17 is assembled into the oil seal groove below the oil seal push rod 3-9. And the lower injection oil pipe 3-10 and the oil seal push rod 3-9 can be connected by thread fitting. For example, the assembled support pipe 3-8 and the lower injection oil pipe 3-10 are screwed in and tightened clockwise or counterclockwise from below the oil seal push rod 3-9. The assembled support pipe 3-8, oil seal push rod 3-9, and lower injection oil pipe 3-10 are installed into the shaft hole of the piston rod 3 from above the piston rod 3 and sunk to the bottom of the piston rod 3, so that the threaded head below the support pipe 3-8 completely or at least partially extends out of the lower end of the piston rod 3. At least one of the sealing snap ring 3-11, sealing rubber ring 3-12, sealing gasket ring 3-13, and hydraulic oil combined sealing gasket 3-15 is assembled onto the threaded head below the support pipe 3-8. The hydraulic oil injection nozzle 3-16 is assembled onto the threaded head below the support pipe 3-8 and tightened by rotating clockwise or counterclockwise.

[0102] In the nose landing gear device of the unmanned aerial vehicle provided by the embodiment of the present invention, in order to facilitate the control of the steering of the front wheel assembly 12, the steering structure includes a steering ring assembly 5, an anti-torsion arm mechanism, a servo motor assembly 10, and a rocker arm mechanism. Among them, the steering ring assembly 5 is rotatably arranged outside the oil cylinder assembly 1, and the axis of the steering ring assembly 5 coincides with the axis of the piston rod assembly 3; the anti-torsion arm mechanism connects the steering ring assembly 5 and the front fork assembly 4, and the front fork assembly 4 is rotatably matched with the lower end of the piston rod assembly 3; the axis of the servo motor assembly 10 is parallel to the axis of the piston rod assembly 3; the rocker arm mechanism connects the steering ring assembly 5 and the servo motor assembly 10.

[0103] It can be controlled by a program or an operator, so that the servo motor in the servo motor assembly 10 rotates at a specific angle to drive the rocker arm mechanism to rotate, so that the rocker arm mechanism drives the steering ring assembly 5 to rotate. The rotation of the steering ring assembly 5 will drive the anti-torsion arm mechanism to rotate, thereby driving the front fork assembly 4 to rotate along the piston rod assembly 3, so that the front wheel assembly 12 steers.

[0104] Among them, the anti-torsion arm mechanism includes an upper anti-torsion arm assembly 6 and a lower anti-torsion arm assembly 7. The upper anti-torsion arm assembly 6 is rotationally connected to the steering ring assembly 5 along a first axis, and the first axis is perpendicular to the axis of the piston rod assembly 3. One end of the lower anti-torsion arm assembly 7 is hinged to the upper anti-torsion arm assembly 6 through a connecting shaft assembly 8, and the axis of the connecting shaft assembly 8 is parallel to the first axis. The other end of the lower anti-torsion arm assembly 7 is rotationally connected to the front fork assembly 4 along a second axis, and the second axis is parallel to the first axis. As Figure 4 shown, in the state where the oil cylinder assembly 1 and the piston rod assembly 3 are telescopically engaged, the upper anti-torsion arm assembly 6 and the lower anti-torsion arm assembly 7 rotate relative to each other, that is, the anti-torsion arm mechanism will not affect the telescopic movement of the oil cylinder assembly 1 and the piston rod assembly 3.

[0105] As Figure 22 and Figure 23 shown, among them, the upper anti-torsion arm assembly 6 may include at least one or more of an anti-torsion arm 6-1, an anti-torsion arm link bushing 6-2, an anti-torsion arm connecting screw 6-3, an anti-torsion arm connecting shaft 6-4, a split pin 5-9, a slotted nut 5-10, an anti-torsion arm bushing 4-8, and a grease nipple 4-9.

[0106] The function of the upper anti-torsion arm assembly 6 is to ensure that the front wheel maintains its heading without torsion during the aircraft's taxiing process, and to transmit the steering torque during the steering process.

[0107] During the assembly process, the number of anti-torsion arm bushings 4-8 can be one or more and they are assembled into the corresponding bushing hole grooves of the anti-torsion arm 6-1. The number of grease nipples 4-9 can be at least one (such as one, two, or three) and they are assembled into the corresponding grease nipple threaded holes of the anti-torsion arm 6-1, and are tightened clockwise or counterclockwise. The anti-torsion arm connecting shaft 6-4 is assembled into the hole of the anti-torsion arm bushing 4-8 on the upper part of the anti-torsion arm 6-1, and the anti-torsion arm link bushing 6-2 is arranged in the holes at both ends of the anti-torsion arm connecting shaft 6-4. The anti-torsion arm connecting screw 6-3 passes through the middle hole of the two anti-torsion arm link bushings 6-2, and the slotted nut 5-10 is screwed clockwise or counterclockwise until the split pin hole is exposed. The split pin 5-9 is inserted into the upper split pin hole of the anti-torsion arm connecting screw 6-3, and the split pin 5-9 is adjusted with a split pin special tool so that it cannot be taken out.

[0108] Similarly, the function of the lower anti-torsion arm assembly 7 is to ensure that the front wheel maintains its heading without torsion during the aircraft's taxiing process, and to transmit the steering torque during the steering process.

[0109] It is possible to make the structure of the lower anti-torsion arm assembly 7 the same as that of the upper anti-torsion arm assembly 6 to reduce the types of parts, thereby reducing the processing cost.

[0110] Among them, the lower anti-torsion arm assembly 7 may include at least one or more of an anti-torsion arm 6-1, an anti-torsion arm link bushing 6-2, an anti-torsion arm connection screw 6-3, an anti-torsion arm connection shaft 6-4, a split pin 5-9, an opening nut 5-10, an anti-torsion arm bushing 4-8, and a grease injection nozzle 4-9. For the specific assembly process, refer to the assembly process of the upper anti-torsion arm assembly 6, which will not be repeated here.

[0111] Further, in order to reduce wear, the oil cylinder assembly 1 further includes a steering bushing 1-9; the outer wall of the oil cylinder 1-1 has a steering chute, and the steering bushing 1-9 is rotatably arranged in the steering chute, and the steering ring assembly 5 is sleeved outside the steering bushing 1-9.

[0112] As Figure 19 shown, in some embodiments, the front fork assembly 4 includes a front fork 4-1 and an anti-torsion arm bushing 4-8. Among them, the front fork 4-1 has two support arms, the rotating shaft of the front wheel assembly 12 is rotatably matched with the two support arms, and the front wheel of the front wheel assembly 12 is located between the two support arms. The front fork 4-1 has an upper bushing hole groove that is rotatably connected to the other end of the lower anti-torsion arm assembly 7 through an anti-torsion arm rotating shaft: the anti-torsion arm bushing 4-8 is located in the upper bushing hole groove and is matched with the anti-torsion arm (the other end of the lower anti-torsion arm assembly 7) rotating shaft. It can play a role in reducing wear to improve the service life and rotation accuracy. During the assembly process, the number of anti-torsion arm bushings 4-8 can be at least one (such as one or two) and is assembled into the upper bushing hole groove of the front fork 4-1.

[0113] Further, the front fork assembly 4 may further include at least one or more of a front fork spacer ring 4-2, a drag link bushing 4-3, a wheel axle rod 4-4, a wheel axle rod gasket 4-5, a wheel axle rod nut 4-6, a drag link bushing fixing screw 4-7, and a grease injection nozzle 4-9.

[0114] The function of the front fork assembly 4 is to connect the oil-gas buffer structure and the main wheel structure together and provide a steering function.

[0115] During the assembly process, the grease injection nozzle 4-9 is assembled into the upper oil injection nozzle threaded hole of the front fork 4-1 and tightened clockwise or counterclockwise. The number of drag link bushings 4-3 can be multiple (such as two) and are respectively assembled into the bushing hole grooves at both ends of the front fork 4-1 and fixed by drag link bushing fixing screws 4-7. The wheel axle rod 4-4 is assembled into the lower shaft rod hole of the front fork 4-1. The wheel axle rod gasket 4-5 is assembled to one end of the wheel axle rod 4-4 and fixed by using the wheel axle rod nut 4-6 by tightening clockwise or counterclockwise. The front fork spacer ring 4-2 is assembled into the lower hole of the front fork 4-1.

[0116] In some embodiments, the connecting shaft assembly 8 is a quick-insert shaft assembly. The function of the quick-insert shaft assembly is to quickly unlock or lock the connection between the upper anti-torsion arm assembly 6 and the lower anti-torsion arm assembly 7, so as to realize functions such as manual dragging steering or electric control steering when the aircraft is on the ground.

[0117] As Figure 24 and Figure 25 shown, the quick-insert shaft assembly (connecting shaft assembly 8) includes a quick-insert shaft 8-1, a gap adjustment piece, a quick-insert shaft sleeve 8-4 and a quick-insert shaft pin 8-5. Among them, one end of the quick-insert shaft 8-1 has an anti-disengagement head, and the other end of the quick-insert shaft 8-1 can penetrate through the rotation connection holes of the lower anti-torsion arm assembly 7 and the upper anti-torsion arm assembly 6; the gap adjustment piece sleeved on the quick-insert shaft 8-1, and the number of gap adjustment pieces is at least one (such as one or two). In this embodiment, the number of gap adjustment pieces is two and they are the first gap adjustment piece 8-2 and the second gap adjustment piece 8-3 respectively. The number of gap adjustment pieces can play the role of adjusting the gap, and the specific number is not limited and is within the protection scope. The quick-insert shaft sleeve 8-4 is sleeved on the other end of the quick-insert shaft 8-1; the quick-insert shaft pin 8-5 is used for plugging and matching with the pin holes of the other end of the quick-insert shaft 8-1 and the quick-insert shaft sleeve 8-4.

[0118] During the assembly process, the first gap adjustment piece 8-2 and the second gap adjustment piece 8-3 are assembled onto the shaft rod of the quick-insert shaft 8-1, the quick-insert shaft sleeve 8-4 is assembled onto the shaft rod of the quick-insert shaft 8-1 (the other end of the quick-insert shaft 8-1), and the quick-insert shaft pin 8-5 is inserted into the quick-insert shaft hole of the quick-insert shaft 8-1 and the quick-insert shaft sleeve 8-4 and locked. During the unlocking process, only need to pull out the quick-insert shaft pin 8-5 from the quick-insert shaft hole of the quick-insert shaft 8-1 and the quick-insert shaft sleeve 8-4, and after disassembling the gap adjustment piece and the quick-insert shaft sleeve 8-4, the other end of the quick-insert shaft 8-1 can be disengaged from the rotation connection holes of the lower anti-torsion arm assembly 7 and the upper anti-torsion arm assembly 6.

[0119] In some embodiments, the rocker mechanism includes a rocker assembly 11 and a rocker link assembly 9. Among them, one end of the rocker assembly 11 is connected to the driving end of the servo actuator assembly 10; one end of the rocker link assembly 9 is rotationally connected to the other end of the rocker assembly 11 along a third axis, the third axis is parallel to the axis of the piston rod assembly 3, and the other end of the rocker link assembly 9 is rotationally connected to the steering ring assembly 5 along a fourth axis, and the third axis is parallel to the fourth axis.

[0120] During the steering process, it can be controlled by a program or an operator, so that the servo actuator in the servo actuator assembly 10 rotates at a specific angle to drive the rocker assembly 11, the rocker link assembly 9 and the steering ring assembly 5 to rotate. The rotation of the steering ring assembly 5 will drive the upper anti-torsion arm assembly 6, the quick-insert shaft assembly (connecting shaft assembly 8), the lower anti-torsion arm assembly 7, the front fork assembly 4 and the front wheel assembly 12 to realize the steering function around the axis of the piston rod assembly 3 (the axis of the oil-gas buffer structure).

[0121] Among them, the function of the rocker link assembly 9 is to transmit the steering torque output by the servo assembly 10 to the steering ring assembly 5, so as to realize the controllable steering function of the nose landing gear.

[0122] As Figure 26 shown, the rocker link assembly 9 may include a link joint bearing 9-1, a link gasket 9-2, a link nut 9-3 and a link lead screw 9-4.

[0123] During the assembly process of the rocker link assembly 9, the number of link nuts 9-3 may be two and both are screwed and assembled to the vicinity of the middle position of the link lead screw 9-4. Two link gaskets 9-2 are respectively assembled to both ends of the link lead screw 9-4, and two link joint bearings 9-1 are respectively assembled to both ends of the link lead screw 9-4. By tightening the link nuts 9-3 clockwise or counterclockwise, the link gasket 9-2 is located between the link nut 9-3 and the link joint bearing 9-1.

[0124] The function of the servo assembly 10 is to provide a steering torque to the front wheel assembly 12 under control, realize the steering function of the front wheel assembly 12, and can monitor the steering angle of the front wheel assembly 12 in real time.

[0125] The servo assembly 10 includes a servo actuator. The axis direction of the drive shaft of the servo actuator is parallel to the axis direction of the piston rod assembly 3. Among them, the servo actuator of the servo assembly 10 drives the rocker assembly 11 to rotate, drives the rocker link assembly 9 to pull the steering ring assembly 5 to rotate along the axis of the piston rod assembly 3, drives the upper anti-twist arm assembly 6, the lower anti-twist arm assembly 7, the connecting shaft assembly 8 and the front fork assembly 4 to rotate along the axis of the piston rod assembly 3, so as to adjust the steering of the front wheel assembly 12.

[0126] As Figure 27 and Figure 28 shown, in some embodiments, the servo assembly 10 may include a servo bracket 10-1, a servo bushing 10-2, an angle sensor gear 10-3, a steering servo 10-4, an angle sensor 10-5, a gear setscrew 10-6, a servo fixing screw 10-7 and an angle sensor fixing screw 10-8.

[0127] During the assembly process, the number of servo bushings 10-2 may be multiple (such as four) and are installed in the bushing mounting holes of the steering servo 10-4. The steering servo 10-4 is assembled to the servo bracket 10-1 and the steering servo 10-4 is fastened with the servo fixing screw 10-7. The angle sensor 10-5 is assembled in the sensor mounting groove on the servo bracket 10-1 and the angle sensor 10-5 is fastened with the angle sensor fixing screw 10-8. The angle sensor gear 10-3 is inserted into the rotating shaft of the angle sensor 10-5 and the angle sensor gear 10-3 is fastened with the gear setscrew 10-6.

[0128] The servo support 10-1 can be connected to the side of the oil cylinder assembly 1 by welding methods such as laser welding. Among them, the servo support 10-1 can have a concave arc surface that fits the outer wall of the oil cylinder assembly 1. The servo support 10-1 can also have a receiving groove for setting the angle sensor 10-5. The servo support 10-1 can also have a recessed structure that fits the outer wall of the steering servo 10-4, etc.

[0129] The rocker arm assembly 11 can be installed on the steering wheel of the steering servo 10-4. The function of the rocker arm assembly 11 can be: when the steering servo 10-4 outputs torque, the rocker arm assembly 11 can transmit the steering torque to the steering ring assembly 5.

[0130] As Figure 29 and Figure 30 shown, the rocker arm assembly 11 can include a servo rocker arm 11-1, a rocker arm bushing 5-3, a rocker arm bolt 5-4, a rocker arm gasket 5-5, a split pin 5-9 and a lock nut 5-10.

[0131] During the assembly process, two rocker arm bushings 5-3 are assembled into the corresponding bushing hole grooves of the servo rocker arm 11-1, and a rocker arm gasket 5-5 is placed above and below the rocker arm bushing 5-3. The rocker arm bolt 5-4 passes through the rocker arm bushing 5-3 and the rocker arm gasket 5-5, and a lock nut 5-10 is used below the rocker arm bolt 5-4 to be screwed clockwise or counterclockwise until the split pin socket is exposed. The split pin 5-9 passes through the split pin hole in the lower part of the rocker arm bolt 5-4, and a special split pin tool is used to adjust the split pin 5-9 so that it cannot be taken out.

[0132] As Figure 20 and Figure 21 shown, for the convenience of disassembly and assembly, the steering ring assembly 5 can be set as an annular structure formed by combining at least two components. In some embodiments, the steering ring assembly 5 can include a steering arm bushing 5-1 and an anti-torsion arm bushing 5-2. The steering arm bushing 5-1 has a rocker arm mounting slot for connecting with the rocker arm mechanism; the anti-torsion arm bushing 5-2 has an anti-torsion arm mounting hole groove for connecting with the anti-torsion arm mechanism. The anti-torsion arm bushing 5-2 is detachably connected to the steering arm bushing 5-1 to form an annular structure. Among them, the steering ring assembly 5 can be a structure similar to a hoop, and the steering arm bushing 5-1 and the anti-torsion arm bushing 5-2 are respectively two semi-circular half-hoop structures.

[0133] It can be understood that the function of the steering ring assembly 5 is to transmit the steering torque output by the servo assembly 10 to the anti-torsion arm mechanism through the rocker arm mechanism, realize the transmission of the steering torque, and control the steering of the front wheel assembly 12.

[0134] The steering ring assembly 5 may further include at least one or several of a rocker arm bushing 5-3, a rocker arm bolt 5-4, a rocker arm gasket 5-5, an angle sensor drive gear 5-6, a steering ring fixing bolt 5-7, a gear fixing bolt 5-8, a split pin 5-9, an open nut 5-10, an anti-twist arm bushing 4-8, and a grease injector 4-9.

[0135] During the assembly process, the number of anti-twist arm bushings 4-8 can be at least one (such as one or two) and assembled into the corresponding bushing holes of the anti-twist arm bushing 5-2. The number of grease injectors 4-9 can be multiple (such as two or four) and are respectively assembled into the grease injector threaded holes of the steering arm bushing 5-1 and the anti-twist arm bushing 5-2. By tightening clockwise or counterclockwise, the number of rocker arm bushings 5-3 can be at least one (such as one or two) and assembled into the corresponding bushing hole slots of the steering arm bushing 5-1. A rocker arm gasket 5-5 is placed above and below the rocker arm bushing 5-3. The other end of the rocker arm link assembly 9 is connected by passing a rocker arm bolt 5-4 through the rocker arm bushing 5-3 and the rocker arm gasket 5-5. An open nut 5-10 is used below the rocker arm bolt 5-4 and tightened clockwise or counterclockwise until the split pin socket is exposed. A split pin 5-9 is inserted through the split pin socket at the lower part of the rocker arm bolt 5-4, and a special split pin tool is used to adjust the split pin 5-9 so that it cannot be removed. The angle sensor drive gear 5-6 is set above the steering arm bushing 5-1 and aligned with two mounting holes, and fastened with a gear fixing bolt 5-8. The mounting holes of the assembled steering arm bushing 5-1 and the anti-twist arm bushing 5-2 are aligned, and fastened with a steering ring fixing bolt 5-7 to complete the assembly of the steering ring assembly 5.

[0136] In this embodiment, the function of the front wheel assembly 12 is to provide ground sliding support and landing buffer functions.

[0137] As Figure 31 shown, the front wheel assembly 12 may include a first front wheel axle seat 12-1, a second front wheel axle seat 12-2, a front wheel axle 12-3, a bearing fixing sleeve 12-4, a front wheel bearing 12-5, a front wheel axle seat fixing screw 12-6, and a front wheel 12-7.

[0138] During the assembly of the front wheel assembly 12, the front wheel bearing 12-5 is assembled into the bearing notch of the first front wheel axle seat 12-1, the front wheel bearing 12-5 is assembled into the bearing notch of the second front wheel axle seat 12-2. The front wheel axle 12-3 is arranged in the central hole of the front wheel 12-7. The first front wheel axle seat 12-1 and the second front wheel axle seat 12-2 are respectively assembled to both ends of the front wheel axle 12-3, and the first front wheel axle seat 12-1 and the second front wheel axle seat 12-2 are fixed relative to the front wheel 12-7 using the front wheel axle seat fixing screw 12-6. Two bearing fixing sleeves 12-4 are respectively assembled to both ends of the front wheel axle 12-3.

[0139] The function of the mounting bracket assembly 13 is to connect the main body of the unmanned aerial vehicle and the nose landing gear device of the unmanned aerial vehicle, and bear the overload force during landing.

[0140] As Figure 32 shown, the mounting bracket assembly 13 may include a bracket 13-1, a bracket bushing 13-2, and a bracket spacer 13-3.

[0141] During the assembly process of the mounting bracket assembly 13, two bracket bushings 13-2 are respectively assembled into the two bushing holes of the bracket 13-1, and two bracket spacers 13-3 are respectively assembled into the mounting holes on both sides of the bracket 13-1.

[0142] Among them, the bracket 13-1 may have an opening through which the oil cylinder assembly 1 passes. The oil cylinder assembly 1 has two connecting columns arranged non-coaxially, and the mounting holes on both sides of the bracket 13-1 are respectively connected to the two connecting columns.

[0143] The embodiment of the present invention also provides an unmanned aerial vehicle, including the main body of the unmanned aerial vehicle and the nose landing gear device of the unmanned aerial vehicle. Among them, the nose landing gear device of the unmanned aerial vehicle is the nose landing gear device of any one of the above.

[0144] Since the above-mentioned nose landing gear device of the unmanned aerial vehicle has the above technical effects, the unmanned aerial vehicle with the above-mentioned nose landing gear device should also have the same technical effects, which will not be repeated here one by one.

[0145] In this specification, each embodiment is described in a progressive manner. The key point of each embodiment is to illustrate the differences from other embodiments. The same or similar parts among the embodiments can be referred to each other.

[0146] The above description of the disclosed embodiments enables those skilled in the art to implement or use the present invention. Various modifications to these embodiments will be obvious to those skilled in the art. The general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention will not be limited to these embodiments shown herein, but will be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. An unmanned aerial vehicle nose landing gear device, characterized in that, Comprising: An oil-gas buffer structure, the oil-gas buffer structure includes an oil cylinder assembly (1), an oil seal cover assembly (2) and a piston rod assembly (3). The oil seal cover assembly (2) is located at the lower end of the oil cylinder assembly (1). The upper end of the piston rod assembly (3) is inserted into the oil cylinder assembly (1) through the oil seal cover assembly (2). The oil cylinder assembly (1) has a cavity for storing hydraulic oil and high-pressure nitrogen. The oil cylinder assembly (1) includes an oil cylinder (1-1), a gas nozzle fixing pipe (1-2), a nitrogen filling nozzle (1-12) and a throttle valve (1-8). The gas nozzle fixing pipe (1-2) is fixedly connected to the oil cylinder (1-1). The upper end of the gas nozzle fixing pipe (1-2) passes through the oil cylinder (1-1) and is connected to the nitrogen filling nozzle (1-12). The throttle valve (1-8) is located in the oil cylinder (1-1) and is connected to the lower end of the gas nozzle fixing pipe (1-2); An installation bracket structure, the installation bracket structure includes an installation bracket assembly (13) for fixedly connecting with the main body of the unmanned aerial vehicle. The installation bracket assembly (13) is fixedly connected to the oil cylinder assembly (1); A main wheel structure, the main wheel structure includes a front fork assembly (4) connected to the lower end of the piston rod assembly (3) and a front wheel assembly (12) rotatably connected to the front fork assembly (4). The front fork assembly (4) is connected to the lower end of the piston rod assembly (3); A steering structure, the steering structure is used to rotate the front fork assembly (4) along the axial direction of the piston rod assembly (3) to adjust the steering of the front wheel assembly (12).

2. The nose landing gear device of the unmanned aerial vehicle according to claim 1, characterized in that The piston rod assembly (3) includes a piston rod (3-1) and a damping ring (3-6) arranged on the piston rod (3-1). The damping ring (3-6) can cooperate with the oil cylinder assembly (1) to provide a rebound damping force.

3. The nose landing gear device of the unmanned aerial vehicle according to claim 2, characterized in that, The damping ring (3-6) is detachably arranged on the piston rod (3-1); The piston rod assembly (3) further includes: A limit hole ring (3-2), the limit hole ring (3-2) is sleeved outside the piston rod (3-1) from the upper end of the piston rod (3-1) and is axially limited with the piston rod (3-1); A piston hole ring (3-4), the piston hole ring (3-4) is sleeved outside the piston rod (3-1) from the upper end of the piston rod (3-1). The outer wall of the piston hole ring (3-4) has a guide ring hole groove for assembling the hole ring guide ring (3-14). The damping ring (3-6) is limited between the limit hole ring (3-2) and the piston hole ring (3-4); A piston nut (3-5), the piston nut (3-5) is detachably connected to the upper end of the piston rod (3-1).

4. The nose landing gear device of the unmanned aerial vehicle according to claim 3, characterized in that, The damping ring (3-6) is sleeved outside the piston rod (3-1) from the upper end of the piston rod (3-1) and is connected with the limit hole ring (3-2); The piston rod assembly (3) further includes: A spacer ring (3-7), the spacer ring (3-7) is sleeved outside the piston rod (3-1) from the upper end of the piston rod (3-1) and is located above the damping ring (3-6); A spacer ring (3-3), the spacer ring (3-3) is sleeved on the upper end of the piston rod (3-1) outside the piston rod (3-1) and is located above the spacer ring (3-7), and the upper end surface of the spacer ring (3-3) contacts the lower end surface of the piston hole ring (3-4).

5. The nose landing gear device of the unmanned aerial vehicle according to claim 3, characterized in that, The piston rod assembly (3) further includes: A support pipe (3-8), the support pipe (3-8) is placed inside the piston rod (3-1) and the lower end of the support pipe (3-8) passes through the lower end of the piston rod (3-1); A hydraulic oil injection nozzle (3-16), the hydraulic oil injection nozzle (3-16) is connected to the lower end of the support pipe (3-8); A lower injection oil pipe (3-10), the lower injection oil pipe (3-10) is located inside the support pipe (3-8) and the lower end is fixedly connected to the support pipe (3-8); An oil seal push rod (3-9), the oil seal push rod (3-9), the lower end of the oil seal push rod (3-9) is matched with the upper end of the support pipe (3-8) and is fixedly connected to the upper end of the lower injection oil pipe (3-10).

6. The nose landing gear device of the unmanned aerial vehicle according to claim 1, characterized in that The steering structure includes: A steering ring assembly (5) rotatably arranged outside the oil cylinder assembly (1), and the axis of the steering ring assembly (5) coincides with the axis of the piston rod assembly (3); An anti-torsion arm mechanism connecting the steering ring assembly (5) and the front fork assembly (4), and the front fork assembly (4) is rotatably matched with the lower end of the piston rod assembly (3); A steering gear assembly (10), the axis of the steering gear assembly (10) is parallel to the axis of the piston rod assembly (3); A rocker arm mechanism connecting the steering ring assembly (5) and the steering gear assembly (10).

7. The nose landing gear device of the unmanned aerial vehicle according to claim 6, characterized in that, The anti-torsion arm mechanism includes: An upper anti-torsion arm assembly (6), the upper anti-torsion arm assembly (6) is rotatably connected to the steering ring assembly (5) along a first axis, and the first axis is perpendicular to the axis of the piston rod assembly (3), A lower anti-torsion arm assembly (7), one end of the lower anti-torsion arm assembly (7) is hinged to the upper anti-torsion arm assembly (6) through a connecting shaft assembly (8), the axis of the connecting shaft assembly (8) is parallel to the first axis, and the other end of the lower anti-torsion arm assembly (7) is rotatably connected to the front fork assembly (4) along a second axis, and the second axis is parallel to the first axis.

8. The nose landing gear device of the unmanned aerial vehicle according to claim 7, characterized in that, The connecting shaft assembly (8) is a quick-insert shaft assembly, including: A quick-insert shaft (8-1), one end of the quick-insert shaft (8-1) has an anti-disengagement head, and the other end of the quick-insert shaft (8-1) can penetrate through the rotation connection holes of the lower anti-torsion arm assembly (7) and the upper anti-torsion arm assembly (6); A gap adjusting piece sleeved on the quick-insert shaft (8-1), and the number of the gap adjusting pieces is at least one; A quick-insert shaft sleeve (8-4), the quick-insert shaft sleeve (8-4) is sleeved on the other end of the quick-insert shaft (8-1); A quick-insert shaft pin (8-5), the quick-insert shaft pin (8-5) is used for plugging and matching with the other end of the quick-insert shaft (8-1) and the pin holes of the quick-insert shaft sleeve (8-4).

9. The nose landing gear device of the unmanned aerial vehicle according to claim 6, characterized in that, The rocker arm mechanism includes: The rocker arm assembly (11), one end of the rocker arm assembly (11) is connected to the driving end of the servo assembly (10); The rocker arm link assembly (9), one end of the rocker arm link assembly (9) is rotatably connected to the other end of the rocker arm assembly (11) along a third axis, the third axis is parallel to the axis of the piston rod assembly (3), and the other end of the rocker arm link assembly (9) is rotatably connected to the steering ring assembly (5) along a fourth axis, the third axis is parallel to the fourth axis.

10. An unmanned aerial vehicle, comprising an unmanned aerial vehicle main body and an unmanned aerial vehicle front landing gear device, characterized in that, The unmanned aerial vehicle front landing gear device is the unmanned aerial vehicle front landing gear device according to any one of claims 1-9.

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