CN219008166U

CN219008166U - Unmanned aerial vehicle wheeled undercarriage and unmanned aerial vehicle

Info

Publication number: CN219008166U
Application number: CN202320064633.3U
Authority: CN
Inventors: 付宇彤; 白越; 乔正; 裴信彪; 许嘉慧
Original assignee: Changchun Changguang Boxiang Uav Co ltd
Current assignee: Changchun Changguang Boxiang Uav Co ltd
Priority date: 2023-01-10
Filing date: 2023-01-10
Publication date: 2023-05-12
Anticipated expiration: 2033-01-10

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a wheel type landing gear of an unmanned aerial vehicle and the unmanned aerial vehicle. The wheeled undercarriage of unmanned aerial vehicle includes truckle, undercarriage mobile jib, undercarriage auxiliary rod and mount, and undercarriage mobile jib fluting forms and holds the chamber, and the undercarriage auxiliary rod sets up and is holding the intracavity, and the one end of undercarriage auxiliary rod is articulated with the one end of undercarriage mobile jib, and the other end of undercarriage auxiliary rod passes through mount and unmanned aerial vehicle fuselage fixed connection, and the other end and the truckle of undercarriage mobile jib are connected, utilize the articulated of undercarriage auxiliary rod and undercarriage mobile jib, realize the recovery and the extension of undercarriage mobile jib and truckle. The caster wheel can rotate at any angle to change the advancing direction at will, so that the unmanned aerial vehicle is convenient to transport, and meanwhile, the landing gear can be folded and retracted into the engine room after the unmanned aerial vehicle flies stably, so that the windward area of the landing gear in the air is reduced, and the aerodynamic resistance of the unmanned aerial vehicle during flying is reduced.

Description

Unmanned aerial vehicle wheeled undercarriage and unmanned aerial vehicle

Technical Field

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a wheel type landing gear of an unmanned aerial vehicle and the unmanned aerial vehicle.

Background

Unmanned aerial vehicle technology has developed rapidly and widely in various fields such as aviation measurement, electric power inspection, water condition monitoring, etc. The tailstock type vertical take-off and landing unmanned aerial vehicle has the advantages of a rotor unmanned aerial vehicle and a fixed wing unmanned aerial vehicle, has the capabilities of vertical take-off and landing, accurate hovering and high-speed plane flying, does not need an airport runway, and can execute operation tasks at any place. However, the tailstock type vertical take-off and landing unmanned aerial vehicle has two problems, namely weak wind resistance in the landing stage and difficult landing in strong wind weather. Secondly, when the robot is on the ground, the robot has difficulty in moving the operation field. Through set up a wheeled undercarriage that can freely rotate at lower wing lower surface, both can assist tailstock formula vertical take off and land unmanned aerial vehicle to descend under strong wind weather, also make things convenient for the manual work to carry on ground. When the tailstock type vertical take-off and landing unmanned aerial vehicle descends in strong wind weather, the pitching attitude of the airplane is low, the head is serious, the gravity center exceeds the stable range, the landing gear stretches out at the moment, the stable range is enlarged, and the unmanned aerial vehicle is assisted to safely descend. When the unmanned aerial vehicle takes off, the landing gear is retracted, so that the flight resistance is reduced. How to make the landing gear structure more reasonable, guarantee unmanned aerial vehicle safety landing as far as possible, accomplish the task smoothly still face a lot of technical difficulties.

As the patent application with the application number of 202210270395.1 gives a symmetrical multi-link electrically-driven aircraft landing gear structure, the safety coefficient of the landing gear is increased through the symmetrical structures of the first four-link mechanism and the second four-link mechanism; when the landing gear is put down, a triangular symmetrical structure is formed by the first four-bar mechanism, the second four-bar mechanism, the right pillar rocker and the left pillar rocker, the supporting strength and the stability are enhanced in a limited space of the cabin, and the landing gear has good practicability. However, the landing gear in the scheme is exposed to the air no matter in a retracted or an extended state, which can increase a certain aerodynamic resistance to the unmanned aerial vehicle performing the flight task and reduce the flight efficiency.

The utility model patent application with the application number of 202121069354.3 provides a landing gear, one end of the landing gear is connected with the unmanned aerial vehicle body through a fixed seat, and the lower end of the landing gear is in a bending and folding or straightening state through a mode of being hinged with the fixed seat. The undercarriage in this scheme has reduced unmanned aerial vehicle's size, has increased unmanned aerial vehicle's transportation mobility, but its earthing terminal is the ball device, can not roll, and unmanned aerial vehicle's ground transportation of being inconvenient for just can not change unmanned aerial vehicle's advancing direction on ground at will.

Disclosure of Invention

The utility model aims to overcome the defects of the prior art, and provides an unmanned aerial vehicle wheel type landing gear and an unmanned aerial vehicle, wherein the landing gear can realize arbitrary angle rotation of casters to randomly change the advancing direction, and can be folded and retracted into a cabin after stable flight to reduce resistance.

In order to achieve the above purpose, the present utility model adopts the following specific technical scheme:

the utility model provides a wheel type landing gear of an unmanned aerial vehicle, which comprises casters, a landing gear main rod, a landing gear auxiliary rod and a fixing frame, wherein a containing cavity is formed by grooving of the landing gear main rod, the landing gear auxiliary rod is arranged in the containing cavity, one end of the landing gear auxiliary rod is hinged with one end of the landing gear main rod, the other end of the landing gear auxiliary rod is fixedly connected with the body of the unmanned aerial vehicle through the fixing frame, the other end of the landing gear main rod is connected with the casters, and the recovery and the extension of the landing gear main rod and the casters are realized by utilizing the hinging of the landing gear auxiliary rod and the landing gear main rod.

Further, the truckle includes wheel, wheel carrier and truckle mount, and truckle mount and undercarriage mobile jib fixed connection are connected through axle and bearing cooperation between truckle mount and the wheel carrier for realize the level free rotation of wheel carrier, be connected through the cooperation of axle and bearing between wheel carrier and the wheel, be used for realizing the vertical axis rotation of wheel, and then realize the arbitrary direction rotation of truckle.

Further, the auxiliary landing gear rod is of a hollow structure, a miniature steering engine is arranged at the hinge joint of the auxiliary landing gear rod and the main landing gear rod, and the miniature steering engine is connected with a flight control unit of the unmanned aerial vehicle and used for controlling an included angle between the auxiliary landing gear rod and the main landing gear rod.

Further, the fixing frame is fixedly connected with the middle wing of the unmanned aerial vehicle through bolts.

The utility model provides an unmanned aerial vehicle, which comprises any one of the unmanned aerial vehicle wheel landing gear.

Further, the middle wing of the unmanned aerial vehicle is provided with a landing gear recovery cover for retracting the wheel landing gear of the unmanned aerial vehicle into the landing gear recovery cover.

Further, the fixed frame of the wheel landing gear of the unmanned aerial vehicle is fixedly arranged in the landing gear recovery cover.

Further, the left upper wing, the left lower wing, the right upper wing and the right lower wing of the unmanned aerial vehicle are all provided with oval support columns for assisting the wheel landing gear of the unmanned aerial vehicle to form multi-point support.

The utility model can obtain the following technical effects:

according to the wheel type landing gear of the unmanned aerial vehicle, the freely rotatable castor is arranged at the position where the bottom end of the landing gear contacts with the ground, so that the problem that a large unmanned aerial vehicle is difficult to carry is solved; the rolling of truckle replaces the transport, and the arbitrary angle rotation of truckle can change the direction of advance at will, has made things convenient for unmanned aerial vehicle's transportation to a great extent. When the unmanned aerial vehicle falls after operation in severe environments such as strong wind days, the unmanned aerial vehicle can be effectively prevented from falling and dumping due to overlarge wind power, the landing gear assists the unmanned aerial vehicle lower wing supporting rod to form a multi-point support, and safety of airborne equipment is guaranteed. After the unmanned aerial vehicle flies steadily, the landing gear can be folded and retracted into the engine room, so that the windward area of the landing gear in the air is reduced, and the additionally increased aerodynamic resistance of the unmanned aerial vehicle during flying is reduced.

Drawings

Fig. 1 is a schematic structural view of a wheel landing gear for an unmanned aerial vehicle according to an embodiment of the present utility model.

Fig. 2 is a schematic structural diagram of an unmanned aerial vehicle wheeled landing gear with a deployment angle θ according to an embodiment of the present utility model.

Fig. 3 is a schematic structural view of casters of a wheel landing gear of an unmanned aerial vehicle according to an embodiment of the present utility model.

Fig. 4 is a schematic view of a partially disassembled structure of a connection part between a wheel frame and a caster mount according to an embodiment of the present utility model.

Fig. 5 is a schematic view of a partially disassembled structure of a connection part of a main gear lever and a sub gear lever according to an embodiment of the present utility model.

Fig. 6 is a schematic structural diagram of an unmanned aerial vehicle in an un-take-off state according to an embodiment of the present utility model.

Fig. 7 is a schematic structural diagram of an unmanned aerial vehicle according to an embodiment of the present utility model during stable flight.

Wherein reference numerals include:

the landing gear main rod 2, the landing gear auxiliary rod 3, the fixing frame 4, the upper unmanned plane wing 5, the lower unmanned plane wing 6, the oval support column 7, the landing gear recovery cover 8, the wheels 101, the wheel frame 102, the castor fixing frame 103, the castor bearing 104, the rotating shaft 105, the shaft nail 106, the locknut 107, the micro steering engine 301, the upper left wing 501, the upper middle wing 502, the upper right wing 503, the lower left wing 601, the lower middle wing 602 and the lower right wing 603.

Detailed Description

Hereinafter, embodiments of the present utility model will be described with reference to the accompanying drawings. In the following description, like modules are denoted by like reference numerals. In the case of the same reference numerals, their names and functions are also the same. Therefore, a detailed description thereof will not be repeated.

In order to make the objects, technical solutions and advantages of the present utility model more apparent, the present utility model will be further described in detail with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not to be construed as limiting the utility model.

Fig. 1 shows a structure of a wheel type landing gear of an unmanned aerial vehicle provided by the embodiment of the utility model, and fig. 2 shows a structure of a wheel type landing gear of an unmanned aerial vehicle provided by the embodiment of the utility model with an unfolding angle θ.

As shown in fig. 1 and 2, the wheeled undercarriage of unmanned aerial vehicle includes truckle 1, undercarriage mobile jib 2, undercarriage auxiliary rod 3 and mount 4, and undercarriage mobile jib 2 fluting forms and holds the chamber, and undercarriage auxiliary rod 3 sets up in holding the intracavity, and the one end of undercarriage auxiliary rod 3 is articulated with the one end of undercarriage mobile jib 2, and the other end of undercarriage auxiliary rod 3 passes through mount and unmanned aerial vehicle fuselage fixed connection, and the other end of undercarriage mobile jib 2 is connected with truckle 1, utilizes undercarriage auxiliary rod 3 and undercarriage mobile jib 2's articulated, realizes the recovery and the extension of undercarriage mobile jib 2 and truckle 1.

Fig. 3 shows the structure of the caster of the wheel landing gear of the unmanned aerial vehicle, as shown in fig. 3, the caster 1 mainly comprises a wheel 101, a wheel frame 102 and a caster fixing frame 103, wherein the rotation center position of the wheel 101 is provided with an outer ring of a caster bearing 104 and an inner ring of the wheel 101 to form interference fit, and meanwhile, the inner ring of the caster bearing 104 and a rotating shaft 105 are in interference fit, so that the wheel 101 can freely rotate around the rotating shaft 105, and a shaft nail 106 is used for fixing the rotating shaft 105 and the wheel frame 102 in a bolt connection mode.

Fig. 4 shows a partially disassembled structure of a connection part between a wheel frame and a caster mount according to an embodiment of the present utility model. As shown in fig. 4, fixing holes are formed around the caster fixing frame 103, and corresponding fixing holes are formed on the side, connected with the caster fixing frame 103, of the main gear rod 2, and the main gear rod 2 are connected with the main gear rod through bolts. The part of the caster mount 103 connected with the caster mount 103 is provided with a vertical rod with threads at the lower end at the center of the connecting side, the rotation of the caster mount 102 is realized between the vertical rod and the caster mount 102 through a bearing, a locknut 107 is arranged at the lower end of the vertical rod to ensure the relative position of the caster mount 103 and the caster mount 102, so that the caster mount 102 can drive the wheels 101 to rotate freely in the horizontal direction, and the wheels 101 can rotate freely in all directions.

Fig. 5 shows a partially disassembled structure of the connection part of the main gear rod and the auxiliary gear rod according to the embodiment of the present utility model, as shown in fig. 5, one end of the main gear rod 2 is fixedly connected with the caster fixing frame 103, and the other end rotates around the auxiliary gear rod 3. The main body of the auxiliary rod 3 of the landing gear is of a hollow cylinder structure, a micro steering engine 301 is arranged in the main body of the landing gear, the rotating angle of the main rod 2 of the landing gear relative to the auxiliary rod 3 is controlled, and the unfolding and folding of the landing gear are completed. The miniature steering engine 301 completes the wiring in the auxiliary rod 3, is led out by the other end close to the middle wing of the unmanned aerial vehicle, and is convenient to be connected with the unmanned aerial vehicle flight control unit. The fixing frame 4 is used for fixing the landing gear auxiliary rod 3 and the unmanned aerial vehicle, and the fixing frame 4 is fixed on the wing in the unmanned aerial vehicle in a bolt connection mode.

Fig. 6 shows a structure of an unmanned aerial vehicle in a non-takeoff state provided by the embodiment of the present utility model, as shown in fig. 6, an unmanned aerial vehicle upper wing 5 is divided into a left upper wing 501, a middle upper wing 502, and a right upper wing 503, and an unmanned aerial vehicle lower wing 6 is divided into a left lower wing 601, a middle lower wing 602, and a right lower wing 603; the lower ends of the left upper wing 501, the right upper wing 503, the left lower wing 601 and the right lower wing 603 are respectively provided with an elliptical support column 7; the lower ends of the two middle wings of the unmanned aerial vehicle are respectively provided with a streamline bulge which is slightly higher than the wing surface of the wing, and the aeroplane is a landing gear recovery cover 8. It will be appreciated that the present fixed wing drone is a well established product of the prior art disclosure, and the functional configuration components that are less relevant to the practice of the present utility model will not be described in detail.

The elliptical support columns 7 are of an integral structure with the wing and are symmetrically distributed relative to the middle wing of the aircraft, and the structure assists the landing gear to form a multi-point support. The left wing and the right wing of the unmanned aerial vehicle are of detachable structures, if the problem of compact transportation space is solved, the left wing and the right wing can be respectively detached and stacked, and the middle wing part which is heavy and not easy to carry can be transported in a free sliding manner through the landing gear caster wheels.

Fig. 7 shows a structure of an unmanned aerial vehicle in stable flight, as shown in fig. 7, a fixing frame 4 of a wheel type landing gear of the unmanned aerial vehicle is fixedly installed in a landing gear recovery cover 8, an angle of a landing gear auxiliary rod 3 is controlled by a micro steering engine 301 positioned at the inner side of the landing gear during stable flight of the unmanned aerial vehicle in executing a task, the landing gear auxiliary rod is gradually folded and retracted to the outer side of a landing gear main rod 2, namely, the landing gear is completely retracted into the landing gear recovery cover 8, the landing gear recovery cover 8 and a middle wing are of an integrated structure, and the aerodynamic resistance additionally increased during flight is reduced as much as possible while retraction and retraction of the landing gear are not affected; when the unmanned aerial vehicle falls, the landing gear stretches, so that the unmanned aerial vehicle falling and dumping caused by overlarge wind force can be effectively avoided, the landing gear and the elliptical support column form a multi-point support, and the safety of airborne equipment is ensured.

In the description of the present specification, a description referring to terms "one embodiment," "some embodiments," "examples," "specific examples," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present utility model. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, the different embodiments or examples described in this specification and the features of the different embodiments or examples may be combined and combined by those skilled in the art without contradiction.

While embodiments of the present utility model have been shown and described above, it will be understood that the above embodiments are illustrative and not to be construed as limiting the utility model, and that variations, modifications, alternatives and variations may be made to the above embodiments by one of ordinary skill in the art within the scope of the utility model.

The above embodiments of the present utility model do not limit the scope of the present utility model. Any of various other corresponding changes and modifications made according to the technical idea of the present utility model should be included in the scope of the claims of the present utility model.

Claims

1. The utility model provides a wheeled undercarriage of unmanned aerial vehicle, its characterized in that, includes truckle, undercarriage mobile jib, undercarriage auxiliary rod and mount, undercarriage mobile jib fluting forms and holds the chamber, undercarriage auxiliary rod sets up hold the intracavity, the one end of undercarriage auxiliary rod with the one end of undercarriage mobile jib is articulated, the other end of undercarriage auxiliary rod passes through mount and unmanned aerial vehicle fuselage fixed connection, the other end of undercarriage mobile jib with the truckle is connected, utilizes the articulated of undercarriage auxiliary rod and undercarriage mobile jib, realizes the undercarriage mobile jib with the recovery and the extension of truckle.

2. The unmanned aerial vehicle wheel landing gear of claim 1, wherein the castor comprises a wheel, a wheel frame and a castor fixing frame, the castor fixing frame is fixedly connected with the landing gear main rod, the castor fixing frame is cooperatively connected with the wheel frame through a shaft and a bearing for realizing horizontal free rotation of the wheel frame, and the wheel frame is cooperatively connected with the wheel through the shaft and the bearing for realizing vertical axis rotation of the wheel so as to realize arbitrary direction rotation of the castor.

3. The unmanned aerial vehicle wheel landing gear according to claim 1, wherein the landing gear auxiliary rod is of a hollow structure, a miniature steering engine is arranged in the landing gear auxiliary rod at a position hinged with the landing gear main rod, and the miniature steering engine is connected with a flight control unit of the unmanned aerial vehicle and used for controlling an included angle between the landing gear auxiliary rod and the landing gear main rod.

4. The unmanned aerial vehicle wheel landing gear of claim 1, wherein the mount is fixedly connected to the unmanned aerial vehicle middle wing by bolts.

5. A unmanned aerial vehicle comprising an unmanned aerial vehicle wheeled landing gear according to any of claims 1 to 4.

6. The unmanned aerial vehicle of claim 5, wherein the unmanned aerial vehicle comprises an upper wing comprising an upper left wing, an upper middle wing and an upper right wing, and a lower wing comprising a lower left wing, a lower middle wing and a lower right wing, wherein the upper middle wing and the lower middle wing are provided with a landing gear recovery cover for recovering the unmanned aerial vehicle wheeled landing gear into the landing gear recovery cover.

7. The unmanned aerial vehicle of claim 6, wherein the mount for the unmanned aerial vehicle wheeled landing gear is fixedly mounted within the landing gear recovery housing.

8. The unmanned aerial vehicle of claim 6, wherein the upper left wing, the lower left wing, the upper right wing, and the lower right wing of the unmanned aerial vehicle are each provided with an elliptical support column for assisting the unmanned aerial vehicle wheel landing gear to form a multi-point support.