UAV front landing gear device and UAV

Abstract

The present application relates to the technical field of unmanned aerial vehicles, and provides a front landing gear device for an unmanned aerial vehicle and an unmanned aerial vehicle, wherein an outer sleeve structural component is fixed to the bottom of a mounting seat structural component, a torque arm structural component and a shock absorber component are fixed to the mounting seat structural component, a connecting rod component is fixed to a steering structural component, and the connecting rod component and the shock absorber component are respectively fixedly connected to the torque arm structural component. The front landing gear device for an unmanned aerial vehicle formed by using the above-mentioned mechanical components does not need to use an oil-gas buffer with a complex structure and a large number of parts, and the shock absorber component in the front landing gear device for the unmanned aerial vehicle is placed on the outside of the outer sleeve structural component, thereby simplifying the structure of the front landing gear device for the unmanned aerial vehicle, reducing the number of parts of the outer sleeve structural component, and reducing the design difficulty of the front landing gear device for the unmanned aerial vehicle.

Description

Technical Field

[0001] The present application relates to the technical field of unmanned aerial vehicles, and in particular to a front landing gear device of an unmanned aerial vehicle and an unmanned aerial vehicle. Background Art

[0002] At present, there are mainly two types of shock-absorbing structures used in the front landing gear structure of small and medium-sized UAVs: oil-gas shock absorbers and rubber shock absorbers. Traditional oil-gas shock absorbers produce shock-absorbing effects through compressed nitrogen, and hydraulic oil provides damping characteristics for the system. The shock-absorbing effect of oil-gas shock absorbers is better than that of rubber shock absorbers, but the structure is relatively complex and has a large number of parts. Summary of the invention

[0003] In order to solve the above problems, the purpose of the embodiments of the present application is to provide a front landing gear device of a UAV and a UAV.

[0004] In a first aspect, an embodiment of the present application provides a front landing gear device for a drone, comprising: a main wheel structure assembly, an outer sleeve structure assembly, a mounting seat structure assembly, a steering structure assembly, a connecting rod assembly, a torque arm structure assembly, and a shock absorber assembly;

[0005] The main wheel structure assembly is installed at the bottom of the outer sleeve structure assembly; one end of the main wheel structure assembly passes through the outer sleeve structure assembly, and the steering structure assembly is installed on one end of the main wheel structure assembly passing through the outer sleeve structure assembly;

[0006] The outer sleeve structural component is fixed to the bottom of the mounting seat structural component;

[0007] The torque arm structure assembly and the shock absorber assembly are fixed on the mounting seat structure assembly;

[0008] The connecting rod assembly is fixed on the steering structure assembly;

[0009] The connecting rod assembly and the shock-absorbing assembly are respectively fixedly connected to the torque arm structure assembly;

[0010] The mounting seat structural component is fixed on the drone.

[0011] In a second aspect, an embodiment of the present application further provides a drone, comprising: the drone front landing gear device described in the first aspect above.

[0012] In the solutions provided in the first aspect to the second aspect of the embodiments of the present application, the outer sleeve structure assembly is fixed at the bottom of the mounting seat structure assembly, the mounting seat structure assembly is fixed with a torque arm structure assembly and a shock absorber assembly, the connecting rod assembly is fixed to the steering structure assembly, the connecting rod assembly and the shock absorber assembly are respectively fixedly connected to the torque arm structure assembly. Compared with the oil-gas shock absorbers in the related technology which are relatively complex in structure and have a large number of parts, the front landing gear device of the UAV formed by using the above-mentioned mechanical components does not need to use an oil-gas buffer with a complex structure and a large number of parts, and the shock absorber assembly in the front landing gear device of the UAV is placed on the outside of the outer sleeve structure assembly, thereby simplifying the structure of the front landing gear device of the UAV, reducing the number of parts of the outer sleeve structure assembly, and reducing the design difficulty of the front landing gear device of the UAV.

[0013] In order to make the above-mentioned objects, features and advantages of the present application more obvious and easy to understand, preferred embodiments are specifically cited below and described in detail with reference to the attached drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0015] Figure 1 A schematic structural diagram of a front landing gear device of a UAV provided in an embodiment of the present application is shown;

[0016] Figure 2 An exploded view of a front landing gear device of a UAV provided in an embodiment of the present application is shown;

[0017] Figure 3 A structural schematic diagram showing a compressed state of a front landing gear device of a UAV provided in an embodiment of the present application is shown;

[0018] Figure 4 A schematic structural diagram of a main wheel structural assembly provided in an embodiment of the present application is shown;

[0019] Figure 5 An exploded view of an outer sleeve structural assembly provided in an embodiment of the present application is shown;

[0020] Figure 6 A side view of an outer sleeve structural assembly provided in an embodiment of the present application is shown;

[0021] Figure 7 A schematic diagram of the structure of the mounting seat structure assembly provided in an embodiment of the present application is shown;

[0022] Figure 8 An exploded schematic diagram of a mounting seat structure assembly provided in an embodiment of the present application is shown;

[0023] Fig. 9 A schematic structural diagram of a steering structure assembly provided in an embodiment of the present application is shown;

[0024] Fig.10 An exploded schematic diagram of a steering structure assembly provided in an embodiment of the present application is shown;

[0025] Fig.11a A three-dimensional diagram of a steering device base provided in an embodiment of the present application is shown;

[0026] Fig.11b A side view of a steering device base provided in an embodiment of the present application is shown;

[0027] Fig.11c A bottom view of a steering device base provided in an embodiment of the present application is shown;

[0028] Fig.11d A front view of a steering device base provided in an embodiment of the present application is shown;

[0029] Fig.12a A three-dimensional diagram of a bearing fixing seat provided in an embodiment of the present application is shown;

[0030] Figure 12b A side view of a bearing fixing seat provided in an embodiment of the present application is shown;

[0031] Fig.12c A bottom view of a bearing fixing seat provided in an embodiment of the present application is shown;

[0032] Fig.12d A front view of a bearing fixing seat provided in an embodiment of the present application is shown;

[0033] Fig.13 An exploded view of a connecting rod assembly provided in an embodiment of the present application is shown;

[0034] Fig.14 An exploded view of a torque arm structure assembly provided in an embodiment of the present application is shown;

[0035] Fig.15 A schematic structural diagram of a torque arm structural assembly provided in an embodiment of the present application is shown;

[0036] Fig.16 The schematic diagram of the structure of the front landing gear device of the drone provided in the embodiment of the present application when turning is shown. Figure 1 ;

[0037] Fig.17The schematic diagram shows the structure of the front landing gear device of the drone provided in the embodiment of the present application when turning. Figure 2 . DETAILED DESCRIPTION

[0038] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0039] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, the meaning of "plurality" is two or more, unless otherwise clearly and specifically defined.

[0040] In this application, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0041] At present, there are mainly two types of shock-absorbing structures used in the front landing gear structure of small and medium-sized UAVs: oil-gas shock absorbers and rubber shock absorbers. Traditional oil-gas shock absorbers produce shock-absorbing effects through compressed nitrogen, and hydraulic oil provides damping characteristics for the system. The shock-absorbing effect of oil-gas shock absorbers is relatively good, but the structure is relatively complex and has a large number of parts.

[0042] Based on this, the present embodiment proposes a front landing gear device for a UAV, wherein an outer sleeve structure assembly is fixed at the bottom of a mounting seat structure assembly, a torque arm structure assembly and a shock absorber assembly are fixed on the mounting seat structure assembly, a connecting rod assembly is fixed on a steering structure assembly, and the connecting rod assembly and the shock absorber assembly are fixedly connected to the torque arm structure assembly respectively. Compared with the oil-gas shock absorbers in the related technology which are relatively complex in structure and have a large number of parts, the front landing gear device for a UAV formed by using the above-mentioned mechanical components does not need to use an oil-gas buffer with a complex structure and a large number of parts, and the shock absorber assembly in the front landing gear device for the UAV is placed on the outside of the outer sleeve structure assembly, thereby simplifying the structure of the front landing gear device for the UAV, reducing the number of parts of the outer sleeve structure assembly, and reducing the design difficulty of the front landing gear device for the UAV.

[0043] In the following embodiments of the present application, the term "hydro-pneumatic shock absorber" has the same meaning as the term "hydro-pneumatic buffer".

[0044] In order to make the above-mentioned objects, features and advantages of the present application more obvious and easy to understand, the present application is further described in detail below with reference to the accompanying drawings and embodiments. Example

[0045] See also Figure 1 The structural diagram of the front landing gear device of the UAV shown in FIG. Figure 2 The exploded view of the front landing gear assembly of the UAV shown in FIG. Figure 3 The schematic diagram of the compressed state of the front landing gear device of the UAV shown in FIG. Fig.16 The structure diagram of the front landing gear of the UAV when turning Figure 1 and see Fig.17 The structure diagram of the front landing gear of the UAV when turning Figure 2 This embodiment proposes a front landing gear device for an unmanned aerial vehicle, including: a main wheel structure assembly 1, an outer sleeve structure assembly 2, a mounting seat structure assembly 3, a steering structure assembly 4, a connecting rod assembly 5, a torque arm structure assembly 6, and a shock absorber assembly 7.

[0046] The main wheel structure assembly 1 is installed at the bottom of the outer sleeve structure assembly 2; one end of the main wheel structure assembly 1 passes through the outer sleeve structure assembly 2, and the steering structure assembly 4 is installed on the end of the main wheel structure assembly 1 passing through the outer sleeve structure assembly 2.

[0047] The outer sleeve structure assembly 2 is fixed to the bottom of the mounting seat structure assembly 3. The torque arm structure assembly 6 and the shock absorber assembly 7 are fixed to the mounting seat structure assembly 3. The connecting rod assembly 5 is fixed to the steering structure assembly 4. The connecting rod assembly 5 and the shock absorber assembly 7 are respectively fixedly connected to the torque arm structure assembly 6. The mounting seat structure assembly 3 is fixed to the drone.

[0048] Among them, the specific structure of the shock-absorbing component 7 is the existing technology and will not be repeated here.

[0049] During the landing process of the drone, at the moment when the front wheel touches the ground, since the drone as a whole is still sinking, the front wheel part will be subjected to a reaction force applied by the ground to the front wheel to offset the potential energy of the drone sinking process. During the sinking process of the drone, the main wheel structure assembly 1 will make an upward linear motion in the outer sleeve structure assembly 2. During this motion, the main wheel structure assembly 1 will push the bottom end of the connecting rod assembly 5 to move upward. During the upward motion of the connecting rod assembly 5, its top end will push the bottom end of the torque arm structure assembly 6 fixed on the mounting seat structure assembly 3 to rotate counterclockwise around the mounting seat structure assembly 3. At this time, the top end of the torque arm structure assembly 6 will compress the shock absorber assembly 7 fixed on the mounting seat structure assembly 3, so that the shock absorber assembly 7 will absorb the potential energy generated during the sinking process of the drone and slowly release it, thereby playing the role of shock absorption and rebound of the front landing gear.

[0050] like Fig.16 and Fig.17 As shown, the steering function can be achieved by controlling the servo motor in the steering structure assembly 4 to drive the gear set to drive the main wheel structure assembly 1 to rotate.

[0051] See also Figure 4 The structural schematic diagram of the main wheel structural assembly shown in the figure, the main wheel structural assembly 1, includes: a main wheel 1-1, a front fork 1-2, a sliding optical axis 1-3, a position indicating ring 1-4, a fixed seat 1-5, a steering driven gear 1-6, a rotating bearing plate 1-7, a main wheel fixing bolt assembly 1-8, a front fork fixing bolt assembly 1-9, a fixed seat fixing bolt assembly 1-10, a sliding optical axis fixing screw assembly 1-11, and a first gear plate fixing screw assembly 1-12.

[0052] The main wheel 1-1 is rotationally connected to the main wheel fixing bolt assembly 1-8, and the main wheel 1-1 is fixed to the front fork 1-2 through the main wheel fixing bolt assembly 1-8. The front fork 1-2 is fixed to the sliding optical axis 1-3 through the front fork fixing bolt assembly 1-9 and the sliding optical axis fixing screw assembly 1-11.

[0053] One end of the sliding optical axis 1 - 3 passes through the outer sleeve structural component 2 , so that the main wheel structural component 1 can perform linear reciprocating motion in the outer sleeve structural component 2 .

[0054] Here, the linear reciprocating motion includes: a downward linear compression motion and an upward linear return motion.

[0055] Among them, the front fork 1-2 is fixed to the end of the sliding optical axis 1-3 that does not pass through the outer sleeve structural component 2.

[0056] The position indicating ring 1-4 is arranged at one end of the sliding optical axis 1-3 passing through the outer sleeve structural assembly 2.

[0057] The fixing seat 1-5 is fixed to one end of the sliding optical axis 1-3 passing through the outer sleeve structure assembly 2 by means of the fixing seat fixing bolt assembly 1-10 and the sliding optical axis fixing screw assembly 1-11.

[0058] The steering driven gear 1-6 and the rotating bearing disk 1-7 are fixed to the fixing seat 1-5 via a first gear disk fixing screw assembly 1-12.

[0059] The steering structure assembly 4 is mounted on the rotating bearing disc 1 - 7 .

[0060] The function of the main wheel structural component 1 is to bear the pressure of the front landing gear when the UAV lands, and transmit the pressure to the shock-absorbing component 7 through the outer sleeve structural component 2 for linear compression movement.

[0061] See also Figure 5 The exploded view of the outer sleeve structural assembly shown and the Figure 6 The side view of the outer sleeve structural assembly shown, the outer sleeve structural assembly 2, includes: a sealing cover plate 2-1, a flat sealing ring 2-2, an optical axis sealing ring 2-3, a linear bearing 2-4, a sliding cover plate 2-5, a sliding sleeve 2-6, an oiling nozzle 2-7, a bearing housing 2-8, a sealing upper cover plate 2-9, a buffer rubber pad 2-10, a buffer rubber pad fixing cover plate 2-11, a cover plate screw assembly 2-12, a buffer rubber pad fixing cover plate screw assembly 2-13, and a support arm assembly 2-14.

[0062] An oiling nozzle mounting hole is provided on the middle outer portion of the bearing housing 2-8.

[0063] The sliding sleeve 2-6 is placed at both ends of the bearing housing 2-8, and the sliding sleeve cover plate 2-5 is used to fix the sliding sleeve 2-6 placed at both ends of the bearing housing 2-8.

[0064] The oiling nozzle 2-7 is installed on the oiling nozzle mounting hole.

[0065] The linear bearings 2-4 are respectively placed at both ends of the bearing housing 2-8, the planar sealing ring 2-2 and the optical axis sealing ring 2-3 are respectively placed in the bearing housing 2-8, and the two ends of the bearing housing 2-8 are fixed using the sealing cover plate 2-1 and the sealing upper cover plate 2-9.

[0066] Place the buffer rubber pad 2-10 onto the sealing upper cover plate 2-9 and fix it using the buffer rubber pad fixing cover plate screw assembly 2-13.

[0067] The support arm assembly 2 - 14 is installed on the bearing housing 2 - 8 , and two connection points on the upper part of the support arm assembly 2 - 14 are fixedly connected to two connection points arranged on the bottom of the mounting seat structure assembly 3 .

[0068] After one end of the sliding optical axis 1-3 on which the rotating bearing disk 1-7 is installed passes through the interior of the linear bearing 2-4, the steering structure assembly 4 is installed on the rotating bearing disk 1-7.

[0069] The sealing cover plate 2-1 is fixedly connected to the bearing housing 2-8 via the cover plate screw assembly 2-12.

[0070] The sealing upper cover plate 2-9 is fixedly connected to the bearing housing 2-8 via the cover plate screw assembly 2-12.

[0071] A flange is provided on the upper part of the bearing housing 2-8, and the bearing housing 2-8 is fixed on the mounting seat structure component 3 through the flange, and the support arm component 2-14 is fixedly connected to the mounting seat structure component 3.

[0072] The function of the outer sleeve structural component 2 is to provide a sliding cavity for the main wheel structural component 1 that can perform linear reciprocating motion.

[0073] See also Figure 7 The structural diagram of the mounting seat structural assembly shown in FIG. Figure 8 An exploded schematic diagram of the mounting seat structure assembly is shown, wherein the mounting seat structure assembly 3 comprises: a structural base 3-1, a spacer bushing 3-2, a landing gear fixing bolt assembly 3-3, an outer sleeve fixing screw assembly 3-4, a support arm front fixing bolt assembly 3-5, a support arm rear fixing bolt assembly 3-6, and a first load-bearing bolt assembly 3-7.

[0074] The flange on the upper part of the bearing housing 2-8 is placed on the structural base 3-1 and fixed using the outer sleeve fixing screw assembly 3-4.

[0075] The support arm front fixing bolt assembly 3-5 and the support arm rear fixing bolt assembly 3-6 are fixedly connected to the support arm assembly 2-14, and the spacer bushing 3-2 is placed on the front fixing point of the structural base 3-1 and fixed using the first load-bearing bolt assembly 3-7.

[0076] The torque arm structure assembly 6 is fixed on the structure base 3 - 1 ; the shock absorber assembly 7 is fixed on the first load-bearing bolt assembly 3 - 7 .

[0077] See also Fig. 9 The structural diagram of the steering structure assembly shown in FIG. Fig.10 The exploded schematic diagram of the steering structure assembly shown in FIG. Fig.11a The three-dimensional view of the steering device base shown in FIG. Fig.11b Side view of the steering gear base shown, see Fig.11c Bottom view of the steering device base shown, see Fig.11d Front view of the steering gear base shown, see Fig.12a The three-dimensional view of the bearing retainer shown in Figure 12b Side view of the bearing housing shown, see Fig.12c The bottom view of the bearing mount shown and the Fig.12d The front view of the bearing fixing seat shown, the steering structure assembly 4, includes: a steering device base 4-1, a bearing fixing seat 4-2, a lower steering gear drive shaft 4-3, a lower bearing cover plate 4-4, a motor fixing bracket 4-5, a steering drive shaft pin 4-6, a support rod 4-7, a steering drive output gear 4-8, a first transmission gear 4-9, a second gear plate fixing screw assembly 4-10, a toothed electromagnetic clutch 4-11, two first lower bearings 4-12, a bearing cover plate fixing screw assembly 4-13, a motor fixing screw assembly 4-14, a motor reducer 4-15, an angle sensor 4-16, an angle sensor fixing screw assembly 4-17, a second load-bearing bolt assembly 4-20, a steering structure fixing screw assembly 4-21, a servo motor 4-22, a motor fixing bracket screw assembly 4-23, two first upper bearings 4-24, an upper bearing cover plate 4-25, an upper steering gear drive shaft 4-26 and a second transmission gear 4-27.

[0078] The connecting rod assembly 5 is rotatably connected to the second load-bearing bolt assembly 4-20; the steering device base 4-1 is installed on the rotating bearing disk 1-7.

[0079] The angle sensor 4-16 is fixed to the steering device base 4-1 using the angle sensor fixing screw assembly 4-17.

[0080] Insert the output shaft slot of the angle sensor 4 - 16 into the corresponding slot of the steering driven gear 1 - 6 .

[0081] The second load-bearing bolt assembly 4-20 is fixed on the steering device base 4-1.

[0082] The two first lower bearings 4-12 are placed in sequence in the bearing grooves provided in the steering device base 4-1, and one end of the lower steering gear transmission shaft 4-3 passes through the steering device base 4-1 from the bottom of the steering device base 4-1, and is inserted into the two first lower bearings 4-12 placed in the steering device base 4-1 at the bearing groove position.

[0083] A bearing groove is arranged on the lower steering gear transmission shaft 4-3.

[0084] The steering transmission shaft pin 4-6 is placed in the bearing groove corresponding to the lower steering gear transmission shaft 4-3, and the steering transmission output gear 4-8 is rotatably connected to the end of the lower steering gear transmission shaft 4-3 that does not pass through the steering device base 4-1, and the steering transmission output gear 4-8 is connected using the second gear plate fixing screw assembly 4-10.

[0085] The lower bearing cover plate 4-4 is placed on the top surface of the bearing groove in the steering device base 4-1, and the lower bearing cover plate 4-4 is fixed to the steering device base 4-1 using the bearing cover plate fixing screw assembly 4-13.

[0086] The bottom of the tooth-type electromagnetic clutch 4-11 is connected to the lower steering gear transmission shaft 4-3 through one end of the steering device base 4-1, and the top of the tooth-type electromagnetic clutch 4-11 is fixed to the lower part of the bearing fixing seat 4-2.

[0087] The steering transmission shaft pin 4-6 is inserted into the tooth-type electromagnetic clutch 4-11.

[0088] One end of the support rod 4-7 is fixedly connected to the steering device base 4-1, and the other end of the support rod 4-7 is fixedly connected to the bearing fixing seat 4-2.

[0089] The bearing fixing seat 4 - 2 is provided with a bearing groove and a motor reducer notch.

[0090] One end of the upper steering gear transmission shaft 4-26 passes through the bearing groove of the bearing fixing seat 4-2 and is connected to the top of the tooth-type electromagnetic clutch 4-11, and the end of the upper steering gear transmission shaft 4-26 that does not pass through the bearing fixing seat 4-2 is rotatably connected to the first transmission gear 4-9; the first transmission gear 4-9 is connected to the end of the upper steering gear transmission shaft 4-26 that does not pass through the bearing fixing seat 4-2 through the second gear plate fixing screw assembly 4-10.

[0091] The two first upper bearings 4-24 are sequentially mounted on one end of the upper steering gear transmission shaft 4-26 passing through the bearing fixing seat 4-2 from the side of the bearing fixing seat 4-2 close to the tooth-type electromagnetic clutch 4-11, so that the two first upper bearings 4-24 are placed in the bearing groove of the bearing fixing seat 4-2, and the upper bearing cover plate 4-25 is placed in the bearing groove of the bearing fixing seat 4-2, and the upper bearing cover plate 4-25 is fixed using the bearing cover plate fixing screw assembly 4-13.

[0092] The motor reducer 4-15 and the servo motor 4-22 are connected together to form a servo motor assembly; the servo motor 4-22 is fixed to the side of the steering device base 4-1 close to the tooth-type electromagnetic clutch 4-11 through the motor fixing bracket 4-5, thereby fixing the servo motor assembly; wherein, the motor fixing bracket 4-5 is fixed using the motor fixing bracket screw assembly 4-23; the steering transmission shaft pin 4-6 is placed at the slot of the motor reducer 4-15.

[0093] The output end of the motor reducer 4-15 passes through the motor reducer slot, so that the motor reducer 4-15 abuts against the bottom surface of the bearing fixing seat 4-2, and the motor fixing screw assembly 4-14 is used to fix the motor reducer 4-15 on the bottom surface of the bearing fixing seat 4-2.

[0094] The second transmission gear 4-27 is rotationally connected to the output end of the motor reducer 4-15, wherein the second transmission gear 4-27 is connected to the output end of the motor reducer 4-15 via the second gear plate fixing screw assembly 4-10.

[0095] The role of the steering structure component 4 is to provide front wheel steering and transmit the shock-absorbing pressure generated by the front wheel touching the ground when the drone lands. In the automatic mode, the flight control computer controls the rotation of the servo motor 4-22 to drive the first transmission gear 4-9 and the steering transmission output gear 4-8 to output the steering torque to the main wheel structure component 1. At the same time, the flight control computer will obtain the parameters of the angle sensor 4-16 in real time to adjust and control the output of the servo motor 4-22, thereby realizing the automatic steering function of the front landing gear device of the drone. In the manual mode, the toothed electromagnetic clutch 4-11 will be in the clutch state, and the ground personnel can install a ground traction device on the main wheel structure component 1 to traction and adjust the steering and movement of the front wheel of the aircraft through an external vehicle or manual control.

[0096] Furthermore, the steering structure assembly 4 also includes: a support rod lower fixing screw assembly 4-18 and a support rod upper fixing screw assembly 4-19.

[0097] The support rod 4-7 is fixedly connected to the steering device base 4-1 through the fixing screw assembly 4-18 under the support rod.

[0098] The support rod 4-7 is fixedly connected to the bearing fixing seat 4-2 via a fixing screw assembly 4-19 on the support rod.

[0099] See also Fig.13 The exploded view of the connecting rod assembly shown in the figure shows that the connecting rod assembly 5 includes: a load-bearing connecting rod 5-1, an upper bearing cover 5-2, a lower bearing cover 5-3 and a bearing 5-4.

[0100] The load-bearing connecting rod 5 - 1 is provided with a plurality of bearing notches.

[0101] The bearings 5-4 are respectively placed into the bearing grooves in the multiple bearing notches of the load-bearing connecting rod 5-1, and the bearing upper outer cover 5-2 and the bearing lower outer cover 5-3 are used to fix the bearings 5-4 in each bearing groove.

[0102] The bearing lower outer cover 5-3 is rotatably connected to the second load-bearing bolt assembly 4-20 through an inner hole provided in the bearing lower outer cover 5-3 itself.

[0103] The bearing upper outer cover 5 - 2 is rotatably connected to the torque arm structure assembly 6 through an inner hole provided in the bearing upper outer cover 5 - 2 itself.

[0104] The function of the connecting rod assembly 5 is to transmit the shock-absorbing pressure generated by the front wheels touching the ground when the UAV lands to the torque arm structure assembly 6 .

[0105] See also Fig.14 The exploded view of the torque arm structural assembly shown and Fig.15The structural schematic diagram of the torque arm structure assembly shown, the torque arm structure assembly 6, includes: two force arm plates 6-1, a lower bearing outer gasket 6-2, a lower bearing inner gasket 6-3, a plurality of support links 6-4, a support link fixing screw assembly 6-5, a second lower bearing 6-6, a torque arm load-bearing bolt assembly 6-7, an upper bearing outer gasket 6-8, a second upper bearing 6-9, an upper bearing inner gasket 6-10, a bushing 6-11, and a shock absorber load-bearing bolt assembly 6-12.

[0106] The two arm pieces 6 - 1 are arranged opposite to each other, and a plurality of bearing notches are respectively arranged at both ends of each arm piece 6 - 1 .

[0107] The two force arm pieces 6-1 are fixedly connected through a plurality of support links 6-4; the two ends of each of the plurality of support links 6-4 are fixedly connected to the two force arm pieces 6-1 through the support link fixing screw assembly 6-5.

[0108] The second lower bearing 6-6 is fixed in the bearing notch at one end of the force arm plate 6-1 through the lower bearing outer gasket 6-2 and the lower bearing inner gasket 6-3.

[0109] The second upper bearing 6-9 is fixed in the bearing slot at the other end of the force arm plate 6-1 through the upper bearing outer gasket 6-8 and the upper bearing inner gasket 6-10.

[0110] The shock absorber assembly 7 is fixed on the shock absorber load-bearing bolt assembly 6-12, and the two ends of the shock absorber load-bearing bolt assembly 6-12 are fixedly connected to the two force arm plates 6-1 through the second upper bearings 6-9 on the two force arm plates 6-1.

[0111] The bushing 6-11 is fixed on the shock absorber load-bearing bolt assembly 6-12.

[0112] The connecting rod assembly 5 is fixed to the torque arm bearing bolt assembly 6-7 through the bearing upper outer cover 5-2, and the two ends of the torque arm bearing bolt assembly 6-7 are fixedly connected to the two force arm plates 6-1 through the second lower bearings 6-6 on the two force arm plates 6-1.

[0113] The function of the torque arm structural component 6 is to transmit the supporting force of the shock absorbing component 7 to the main wheel structural component 1 so that the UAV can obtain a good damping and shock absorbing effect during the landing process.

[0114] This embodiment also provides a UAV, comprising: the above-mentioned UAV front landing gear device, wherein the UAV front landing gear device is installed on the UAV front landing gear structure.

[0115] From the above description, it can be seen that the oil-gas buffer in the prior art is replaced by the mechanical structure design, and the sliding optical axis 1-3 in the main wheel structure assembly 1 is used to transfer the buffer force carried by the landing gear through the steering structure assembly 4 and the connecting rod assembly 5 to the torque arm structure assembly 6, and the torque arm structure assembly 6 compresses the shock absorber assembly 7 to achieve buffering and shock absorption. The low-cost shock absorber assembly is installed at the rear of the mechanical structure, and is not installed outside the outer sleeve structure assembly 2. Under the premise of achieving the same shock absorption function, the cost is reduced to the maximum extent. Standard parts are used to replace a large number of machined parts.

[0116] To summarize, the present embodiment proposes an outer sleeve structure assembly fixed at the bottom of the mounting seat structure assembly, a torque arm structure assembly and a shock absorber assembly are fixed on the mounting seat structure assembly, a connecting rod assembly is fixed on the steering structure assembly, and the connecting rod assembly and the shock absorber assembly are respectively fixedly connected to the torque arm structure assembly. Compared with the oil-gas shock absorbers in the related art which are relatively complex in structure and have a large number of parts, the UAV front landing gear device formed by using the above-mentioned mechanical components does not need to use an oil-gas buffer with a complex structure and a large number of parts, and the shock absorber assembly in the UAV front landing gear device is placed on the outside of the outer sleeve structure assembly, thereby simplifying the structure of the UAV front landing gear device, reducing the number of parts of the outer sleeve structure assembly, and reducing the design difficulty of the UAV front landing gear device.

[0117] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any person skilled in the art who is familiar with the present technical field can easily think of changes or substitutions within the technical scope disclosed in the present application, which should be included in the protection scope of the present application. Therefore, the protection scope of the present application should be based on the protection scope of the claims.

Claims

1. A front landing gear device for an unmanned aerial vehicle, characterized in that: include: A main wheel structural assembly (1), an outer sleeve structural assembly (2), a mounting seat structural assembly (3), a steering structural assembly (4), a connecting rod assembly (5), a torque arm structural assembly (6), and a shock absorbing assembly (7); The main wheel structure assembly (1) is mounted on the bottom of the outer sleeve structure assembly (2); one end of the main wheel structure assembly (1) passes through the outer sleeve structure assembly (2), and the steering structure assembly (4) is mounted on the end of the main wheel structure assembly (1) passing through the outer sleeve structure assembly (2); The outer sleeve structural component (2) is fixed to the bottom of the mounting seat structural component (3); The torque arm structure component (6) and the shock-absorbing component (7) are fixed on the mounting seat structure component (3); The connecting rod assembly (5) is fixed on the steering structure assembly (4); The connecting rod assembly (5) and the shock-absorbing assembly (7) are respectively fixedly connected to the torque arm structure assembly (6); The mounting seat structural component (3) is fixed on the drone; The main wheel structural assembly (1) comprises: a main wheel (1-1), a front fork (1-2), a sliding optical axis (1-3), a position indicating ring (1-4), a fixing seat (1-5), a steering driven gear (1-6), a rotating bearing plate (1-7), a main wheel fixing bolt assembly (1-8), a front fork fixing bolt assembly (1-9), a fixing seat fixing bolt assembly (1-10), a sliding optical axis fixing screw assembly (1-11), and a first gear plate fixing screw assembly (1-12); The main wheel (1-1) is rotatably connected to the main wheel fixing bolt assembly (1-8); the main wheel (1-1) is fixed to the front fork (1-2) via the main wheel fixing bolt assembly (1-8); and the front fork (1-2) is fixed to the sliding optical axis (1-3) via the front fork fixing bolt assembly (1-9) and the sliding optical axis fixing screw assembly (1-11); One end of the sliding optical axis (1-3) passes through the outer sleeve structural component (2), so that the main wheel structural component (1) can move up and down in a straight line inside the outer sleeve structural component (2); The position indicating ring (1-4) is arranged at one end of the sliding optical axis (1-3) passing through the outer sleeve structural component (2); The fixing seat (1-5) is fixed to one end of the sliding optical axis (1-3) passing through the outer sleeve structure assembly (2) via the fixing seat fixing bolt assembly (1-10) and the sliding optical axis fixing screw assembly (1-11); The steering driven gear (1-6) and the rotating bearing disc (1-7) are fixed to the fixing seat (1-5) via a first gear disc fixing screw assembly (1-12); The steering structure assembly (4) is mounted on the rotating bearing disc (1-7).

2. The UAV front landing gear device according to claim 1, characterized in that: The outer sleeve structural assembly (2) comprises: a sealing cover plate (2-1), a plane sealing ring (2-2), an optical axis sealing ring (2-3), a linear bearing (2-4), a sliding sleeve cover plate (2-5), a sliding sleeve (2-6), an oiling nozzle (2-7), a bearing housing (2-8), a sealing upper cover plate (2-9), a buffer rubber pad (2-10), a buffer rubber pad fixing cover plate (2-11), a cover plate screw assembly (2-12), a buffer rubber pad fixing cover plate screw assembly (2-13), and a support arm assembly (2-14); An oil injection nozzle mounting hole is provided on the middle outer portion of the bearing housing (2-8); The sliding sleeve (2-6) is placed at both ends of the bearing housing (2-8), and the sliding sleeve cover plate (2-5) is used to fix the sliding sleeve (2-6) placed at both ends of the bearing housing (2-8); The oil injection nozzle (2-7) is installed on the oil injection nozzle installation hole; The linear bearing (2-4) is respectively placed at both ends of the bearing housing (2-8), the plane sealing ring (2-2) and the optical axis sealing ring (2-3) are respectively placed in the bearing housing (2-8), and the two ends of the bearing housing (2-8) are fixed using the sealing cover plate (2-1) and the sealing upper cover plate (2-9); Placing the buffer rubber pad (2-10) onto the sealing upper cover plate (2-9) and fixing it using the buffer rubber pad fixing cover plate screw assembly (2-13); The support arm assembly (2-14) is mounted on the bearing housing (2-8), and two connection points on the upper portion of the support arm assembly (2-14) are fixedly connected to two connection points provided on the bottom portion of the mounting seat structure assembly (3); After one end of the sliding optical axis (1-3) on which the rotating bearing disk (1-7) is installed passes through the interior of the linear bearing (2-4), the steering structure assembly (4) is installed on the rotating bearing disk (1-7); The sealing cover plate (2-1) is fixedly connected to the bearing housing (2-8) via the cover plate screw assembly (2-12); The sealing upper cover plate (2-9) is fixedly connected to the bearing housing (2-8) via the cover plate screw assembly (2-12).

3. The UAV front landing gear device according to claim 2, characterized in that: The mounting seat structure assembly (3) comprises: a structure base (3-1), a spacer bushing (3-2), a landing gear fixing bolt assembly (3-3), an outer sleeve fixing screw assembly (3-4), a support arm front fixing bolt assembly (3-5), a support arm rear fixing bolt assembly (3-6), and a first load-bearing bolt assembly (3-7); The flange on the upper part of the bearing housing (2-8) is placed on the structural base (3-1) and fixed using the outer sleeve fixing screw assembly (3-4); The support arm front fixing bolt assembly (3-5) and the support arm rear fixing bolt assembly (3-6) are fixedly connected to the support arm assembly (2-14), and the spacer bushing (3-2) is placed on the front fixing point of the structural base (3-1) and fixed using the first load-bearing bolt assembly (3-7); The torque arm structural component (6) is fixed on the structural base (3-1); and the shock-absorbing component (7) is fixed on the first load-bearing bolt component (3-7).

4. The UAV front landing gear device according to claim 1, characterized in that: The steering structure assembly (4) comprises: a steering device base (4-1), a bearing fixing seat (4-2), a lower steering gear transmission shaft (4-3), a lower bearing cover plate (4-4), a motor fixing bracket (4-5), a steering transmission shaft pin (4-6), a support rod (4-7), a steering transmission output gear (4-8), a first transmission gear (4-9), a second gear plate fixing screw assembly (4-10), a toothed electromagnetic clutch (4-11), two first lower bearings (4-12), and a bearing cover plate fixing screw assembly Component (4-13), motor fixing screw assembly (4-14), motor reducer (4-15), angle sensor (4-16), angle sensor fixing screw assembly (4-17), second load-bearing bolt assembly (4-20), steering structure fixing screw assembly (4-21), servo motor (4-22), motor fixing bracket screw assembly (4-23), two first upper bearings (4-24), upper bearing cover plate (4-25), upper steering gear transmission shaft (4-26) and second transmission gear (4-27); The connecting rod assembly (5) is rotatably connected to the second load-bearing bolt assembly (4-20); the steering device base (4-1) is installed on the rotating bearing disk (1-7); Using the angle sensor fixing screw assembly (4-17) to fix the angle sensor (4-16) to the steering device base (4-1); Inserting the output shaft notch of the angle sensor (4-16) into the corresponding notch of the steering driven gear (1-6); The second load-bearing bolt assembly (4-20) is fixed on the steering device base (4-1); The two first lower bearings (4-12) are sequentially placed in bearing grooves provided in the steering device base (4-1); one end of the lower steering gear transmission shaft (4-3) passes through the steering device base (4-1) from the bottom of the steering device base (4-1) and is then inserted into the two first lower bearings (4-12) placed in the steering device base (4-1) at the bearing grooves; The steering transmission shaft pin (4-6) is placed in a bearing groove corresponding to the lower steering gear transmission shaft (4-3); the steering transmission output gear (4-8) is rotatably connected to the end of the lower steering gear transmission shaft (4-3) that does not pass through the steering device base (4-1); and the steering transmission output gear (4-8) is connected using the second gear plate fixing screw assembly (4-10); Placing the lower bearing cover plate (4-4) on the top surface of the bearing groove in the steering device base (4-1), and fixing the lower bearing cover plate (4-4) on the steering device base (4-1) using the bearing cover plate fixing screw assembly (4-13); The bottom of the tooth-type electromagnetic clutch (4-11) is connected to one end of the lower steering gear transmission shaft (4-3) passing through the steering device base (4-1), and the top of the tooth-type electromagnetic clutch (4-11) is fixed to the lower part of the bearing fixing seat (4-2); The steering transmission shaft pin (4-6) is inserted into the tooth-type electromagnetic clutch (4-11); One end of the support rod (4-7) is fixedly connected to the steering device base (4-1), and the other end of the support rod (4-7) is fixedly connected to the bearing fixing seat (4-2); The bearing fixing seat (4-2) is provided with a bearing groove and a motor reducer notch; One end of the upper steering gear transmission shaft (4-26) passes through the bearing groove of the bearing fixing seat (4-2) and is connected to the top of the tooth-type electromagnetic clutch (4-11); the end of the upper steering gear transmission shaft (4-26) that does not pass through the bearing fixing seat (4-2) is rotationally connected to the first transmission gear (4-9); the first transmission gear (4-9) is connected to the end of the upper steering gear transmission shaft (4-26) that does not pass through the bearing fixing seat (4-2) via the second gear plate fixing screw assembly (4-10); The two first upper bearings (4-24) are sequentially sleeved on one end of the upper steering gear transmission shaft (4-26) passing through the bearing fixing seat (4-2) from the side of the bearing fixing seat (4-2) close to the tooth-type electromagnetic clutch (4-11), so that the two first upper bearings (4-24) are placed in the bearing groove of the bearing fixing seat (4-2), the upper bearing cover plate (4-25) is placed in the bearing groove of the bearing fixing seat (4-2), and the upper bearing cover plate (4-25) is fixed using the bearing cover plate fixing screw assembly (4-13); The motor reducer (4-15) and the servo motor (4-22) are connected together to form a servo motor assembly; the servo motor (4-22) is fixed to a side of the steering device base (4-1) close to the tooth-type electromagnetic clutch (4-11) through the motor fixing bracket (4-5), thereby fixing the servo motor assembly; wherein the motor fixing bracket (4-5) is fixed using the motor fixing bracket screw assembly (4-23); the steering transmission shaft pin (4-6) is placed at the notch of the motor reducer (4-15); The output end of the motor reducer (4-15) passes through the notch of the motor reducer, so that the motor reducer (4-15) abuts against the bottom surface of the bearing fixing seat (4-2), and the motor fixing screw assembly (4-14) is used to fix the motor reducer (4-15) on the bottom surface of the bearing fixing seat (4-2); The second transmission gear (4-27) is rotationally connected to the output end of the motor reducer (4-15), wherein the second transmission gear (4-27) is connected to the output end of the motor reducer (4-15) via the second gear plate fixing screw assembly (4-10).

5. The UAV front landing gear device according to claim 4, characterized in that: The steering structure assembly (4) further comprises: a support rod lower fixing screw assembly (4-18) and a support rod upper fixing screw assembly (4-19); The support rod (4-7) is fixedly connected to the steering device base (4-1) via a fixing screw assembly (4-18) under the support rod; The support rod (4-7) is fixedly connected to the bearing fixing seat (4-2) via a fixing screw assembly (4-19) on the support rod.

6. The UAV front landing gear device according to claim 4, characterized in that: The connecting rod assembly (5) comprises: a load-bearing connecting rod (5-1), an upper bearing outer cover (5-2), a lower bearing outer cover (5-3) and a bearing (5-4); The load-bearing connecting rod (5-1) is provided with a plurality of bearing notches; The bearings (5-4) are respectively placed in the bearing grooves of the plurality of bearing notches of the load-bearing connecting rod (5-1), and the bearing upper outer cover (5-2) and the bearing lower outer cover (5-3) are respectively used to fix the bearings (5-4) in the bearing grooves; The bearing lower outer cover (5-3) is rotatably connected to the second load-bearing bolt assembly (4-20) via an inner hole provided in the bearing lower outer cover (5-3); The bearing upper outer cover (5-2) is rotatably connected to the torque arm structural component (6) via an inner hole provided in the bearing upper outer cover (5-2) itself.

7. The UAV front landing gear device according to claim 6, characterized in that: The torque arm structure assembly (6) comprises: two force arm plates (6-1), a lower bearing outer gasket (6-2), a lower bearing inner gasket (6-3), a plurality of support connecting rods (6-4), a support connecting rod fixing screw assembly (6-5), a second lower bearing (6-6), a torque arm load-bearing bolt assembly (6-7), an upper bearing outer gasket (6-8), a second upper bearing (6-9), an upper bearing inner gasket (6-10), a bushing (6-11), and a shock absorber load-bearing bolt assembly (6-12); The two force arm sheets (6-1) are arranged opposite to each other, and a plurality of bearing notches are respectively arranged at two ends of each of the two force arm sheets (6-1); The two force arm sheets (6-1) are fixedly connected via a plurality of support connecting rods (6-4); two ends of each support connecting rod (6-4) in the plurality of support connecting rods (6-4) are respectively fixedly connected to the two force arm sheets (6-1) via the support connecting rod fixing screw assembly (6-5); The second lower bearing (6-6) is fixed in a bearing notch at one end of the force arm sheet (6-1) by means of the lower bearing outer gasket (6-2) and the lower bearing inner gasket (6-3); The second upper bearing (6-9) is fixed in the bearing notch at the other end of the force arm sheet (6-1) by means of the upper bearing outer gasket (6-8) and the upper bearing inner gasket (6-10); The shock absorber assembly (7) is fixed on the shock absorber load-bearing bolt assembly (6-12), and the two ends of the shock absorber load-bearing bolt assembly (6-12) are fixedly connected to the two force arm sheets (6-1) via the second upper bearings (6-9) on the two force arm sheets (6-1); The bushing (6-11) is fixed on the shock absorber bearing bolt assembly (6-12); The connecting rod assembly (5) is fixed to the torque arm bearing bolt assembly (6-7) via the bearing upper outer cover (5-2), and the two ends of the torque arm bearing bolt assembly (6-7) are fixedly connected to the two force arm plates (6-1) via the second lower bearings (6-6) on the two force arm plates (6-1).

8. A drone, characterized in that: include: The front landing gear device of the UAV as described in any one of claims 1 to 7 above.

Images