CN219339752U - Undercarriage and unmanned aerial vehicle - Google Patents

Abstract

The utility model relates to a landing gear and an unmanned aerial vehicle, wherein the landing gear comprises a connecting frame, two groups of movable frames and a locking assembly, the two groups of movable frames are respectively connected with the connecting frame in a rotating way on two sides of a machine body, and the movable frames can rotate relative to the connecting frame and can be switched between an unfolding state or a shrinking state, wherein: in the unfolded state, one ends of the two groups of movable frames, which are far away from the connecting frame, are mutually far away from each other so as to support the unmanned aerial vehicle, and in the contracted state, one ends of the two groups of movable frames, which are far away from the connecting frame, are mutually close to each other; the locking component is arranged on the connecting frame and/or the movable frame and is used for locking/unlocking the rotation of the movable frame relative to the connecting frame. When the landing gear is used, the movable frame is in a unfolding state, and the locking assembly locks the movable frame to rotate relative to the connecting frame, so that the stability and reliability of the landing gear are ensured. When the landing gear is not used, the locking component unlocks the movable frame to rotate relative to the connecting frame, and the movable frame is in a contracted state, so that the occupied space of the landing gear is reduced.

Description

Undercarriage and unmanned aerial vehicle

Technical Field

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

Background

The unmanned aerial vehicle is widely applied to the fields of military or civil monitoring, investigation, aerial photography, special operation and the like. Landing gear for an unmanned aerial vehicle is an accessory device for supporting the fuselage when the unmanned aerial vehicle is landing at take-off.

In the existing unmanned aerial vehicle, in order to ensure the stability of the landing gear when supporting the unmanned aerial vehicle, the landing gear is always in an unfolding state, the occupied space is large, the whole size of the unmanned aerial vehicle is large, the storage and transportation are inconvenient, and the portability is poor.

Disclosure of Invention

Accordingly, it is necessary to provide a landing gear and an unmanned aerial vehicle, which can reduce the space occupied by the landing gear when not in use while ensuring stability, thereby facilitating storage or transportation of the unmanned aerial vehicle.

The utility model first provides a landing gear for an unmanned aerial vehicle, comprising: the connecting frame is used for being connected with the body of the unmanned aerial vehicle; the two groups of movable frames are respectively connected with the connecting frames in a rotating mode on two sides of the machine body, and the movable frames can rotate relative to the connecting frames and are switched between an unfolding state or a shrinking state, wherein: in the unfolding state, one ends of the two groups of movable frames far away from the connecting frame are far away from each other so as to support the unmanned aerial vehicle, and in the shrinking state, one ends of the two groups of movable frames far away from the connecting frame are close to each other; and the locking component is arranged on the connecting frame and/or the movable frame and is used for locking/unlocking the movable frame to rotate relative to the connecting frame.

In the landing gear, when the landing gear is required to be used, the movable frame is controlled to rotate to be in a unfolding state relative to the connecting frame, so that the landing gear can support the unmanned aerial vehicle, and the locking component is controlled to lock the movable frame to rotate relative to the connecting frame, so that the stability and reliability of the landing gear are ensured; when the landing gear is not required to be used, the locking component is controlled to unlock the movable frame to rotate relative to the connecting frame, and the movable frame is controlled to rotate relative to the connecting frame to a contracted state, so that one ends of the two groups of movable frames, which are far away from the connecting frame, are close to each other, the occupied space of the landing gear is reduced, and the landing gear is convenient to store or transport.

In one embodiment, the locking component comprises a first clamping piece arranged on one of the movable frame and the connecting frame and a second clamping piece arranged on the other of the movable frame and the connecting frame, and in the unfolded state, the first clamping piece can be matched with the second clamping piece in a clamping manner so as to lock the movable frame in the unfolded state.

So set up, can guarantee the reliability of locking subassembly under the locking state through joint complex mode to the structure of joint is comparatively simple.

In one embodiment, the first clamping member is rotatably disposed on the movable frame around an axis, and the first clamping member can rotate around the axis along a first preset direction to be clamped with the second clamping member, and can rotate around the axis along a reverse direction of the first preset direction to be separated from the second clamping member.

The setting is so that the adjusting mode is simple and convenient, and the user operation is convenient.

In one embodiment, the first clamping piece comprises clamping parts and control parts distributed on two sides of the axis, and the clamping parts can be clamped with the second clamping piece; the locking assembly further comprises an elastic piece arranged between the control part and the movable frame, and the elastic piece can apply elastic force to the control part towards the first preset direction.

So arranged, the user can make the clamping part separate from the second clamping piece by toggling the control part; the elastic piece can avoid the unexpected disconnection of the first clamping piece and the second clamping piece, and further improve the stability of the landing gear.

In one embodiment, the landing gear further comprises a limiting assembly, wherein the limiting assembly comprises a first limiting piece arranged on one of the connecting frame and the movable frame and a second limiting piece arranged on the other one of the connecting frame and the movable frame; in the contracted state, the first limiting piece is abutted with the second limiting piece so as to limit the rotation of the movable frame relative to the connecting frame.

So set up, spacing subassembly can avoid the rotation scope of movable frame too big and lead to the movable frame of both sides to collide or movable frame and other external structure to collide each other and damage.

In one embodiment, the landing gear further comprises two supporting frames respectively arranged on two sides of the machine body, and one ends, far away from the connecting frames, of the two groups of movable frames are respectively connected with the two supporting frames.

So set up, the support frame can increase the area of contact between undercarriage and the external structure, guarantees the activity frame simultaneous movement of every group simultaneously, further improves stability and reliability when the undercarriage supports unmanned aerial vehicle.

The utility model also provides an unmanned aerial vehicle, comprising: a body; a plurality of horn assemblies arranged at intervals along the periphery of the body and connected with the body; the power supply assembly is arranged on the machine body and is electrically connected with the horn assembly; and the landing gear is characterized in that the connecting frame is arranged at the bottom of the machine body.

In one embodiment, the horn assembly comprises a connecting arm arranged on the machine body and a paddle rotatably arranged at one end of the connecting arm far away from the machine body; the connecting arm is detachably connected with the machine body, and/or the blade is detachably connected with the connecting arm.

By the arrangement, a user can conveniently and quickly assemble and disassemble the unmanned aerial vehicle, and usability of the unmanned aerial vehicle is improved; moreover, can dismantle paddle and linking arm in order to reduce unmanned aerial vehicle whole volume when accomodating unmanned aerial vehicle, unmanned aerial vehicle's accomodate or transportation of being convenient for promotes unmanned aerial vehicle's portability.

In one embodiment, the power supply assembly is disposed in the center of the bottom of the body.

So set up for unmanned aerial vehicle focus is close with the center, is favorable to unmanned aerial vehicle's flight control, promotes unmanned aerial vehicle's flight safety.

In one embodiment, the power supply assembly comprises an engine, a generator and a battery, wherein the engine can drive the generator to operate for generating electricity and transmitting the electric energy to the battery; the unmanned aerial vehicle also comprises an oil tank arranged in the machine body, and the oil tank supplies oil for the engine.

So set up, through the effect of engine and generator with fuel conversion for the electric energy, can provide the duration of longer time for unmanned aerial vehicle.

In one embodiment, the unmanned aerial vehicle further comprises a shock absorber disposed between the power supply assembly and the fuselage; and/or, the unmanned aerial vehicle further comprises a mounting piece which is arranged on the fuselage and used for mounting the mounting equipment.

The vibration absorber can isolate the vibration of the engine, so that the vibration is prevented from affecting the normal flight of the unmanned aerial vehicle; the mounting piece can realize quick assembly disassembly or change of mounting equipment.

Drawings

In order to more clearly illustrate the technical solutions of embodiments or conventional techniques of the present application, the drawings that are required to be used in the description of the embodiments or conventional techniques will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present application, and other drawings may be obtained according to these drawings without inventive effort for a person of ordinary skill in the art.

FIG. 1 is a schematic perspective view of a landing gear according to one embodiment of the present utility model in an extended state;

FIG. 2 is an enlarged schematic view of the structure shown in FIG. 1A according to the present utility model;

FIG. 3 is a schematic view of the structure of FIG. 2 at another angle according to the present utility model;

FIG. 4 is a schematic perspective view of the landing gear of FIG. 1 in a contracted state, according to the present utility model;

FIG. 5 is an enlarged schematic view of the structure shown in FIG. 4B;

FIG. 6 is a schematic view of the structure of FIG. 5 at another angle according to the present utility model;

fig. 7 is a schematic view of a three-dimensional structure of a unmanned aerial vehicle according to an embodiment of the present utility model;

fig. 8 is a schematic diagram of an explosion structure of the unmanned aerial vehicle of fig. 7 under another angle;

fig. 9 is a schematic partial perspective view of the unmanned aerial vehicle in fig. 7 in a contracted state according to the present utility model;

fig. 10 is a schematic structural diagram of the unmanned aerial vehicle of fig. 9 under another angle.

Reference numerals: 1. landing gear; 11. a connecting frame; 12. a movable frame; 13. a locking assembly; 131. a first clamping piece; 1311. a clamping part; 1312. a control unit; 132. a second clamping piece; 133. an elastic member; 134. a second rotating shaft; 14. a support frame; 15. a limit component; 151. a first limiting member; 152. a second limiting piece; 16. a connecting piece; 17. a first rotating shaft; 2. a body; 21. a housing; 22. a cover body; 3. a horn assembly; 31. a connecting arm; 32. a paddle; 33. a motor; 4. a power supply assembly; 41. an engine; 42. a generator; 43. a battery; 5. an oil tank; 6. and a mounting piece.

Detailed Description

In order to make the above objects, features and advantages of the present application more comprehensible, embodiments accompanied with figures are described in detail below. In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present application. This application is, however, susceptible of embodiment in many other forms than those described herein and similar modifications can be made by those skilled in the art without departing from the spirit of the application, and therefore the application is not to be limited to the specific embodiments disclosed below.

It will be understood that when an element is referred to as being "mounted" or "disposed" on another element, it can be directly on the other element or intervening elements may also be present. When a component is considered to be "connected" to another component, it can be directly connected to the other component or intervening components may also be present. The terms "vertical," "horizontal," "upper," "lower," "left," "right," and the like are used in the description of the present application for purposes of illustration only and do not represent the only embodiment.

Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present application, the meaning of "plurality" is at least two, such as two, three, etc., unless explicitly defined otherwise.

In this application, unless expressly stated or limited otherwise, a first feature "up" or "down" a second feature may be a direct contact of the first feature with the second feature, or an indirect contact of the first feature with the second feature via an intervening medium. Moreover, a first feature being "above," "over" and "on" a second feature may be a first feature being directly above or obliquely above the second feature, or simply indicating that the first feature is higher in level than the second feature. The first feature being "under", "below" and "beneath" the second feature may be the first feature being directly under or obliquely under the second feature, or simply indicating that the first feature is less level than the second feature.

Unless defined otherwise, all technical and scientific terms used in the specification of this application have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used in the description of the present application is for the purpose of describing particular embodiments only and is not intended to be limiting of the present application. The term "and/or" as used in the specification of this application includes any and all combinations of one or more of the associated listed items.

The landing gear of the unmanned aerial vehicle is an accessory device for supporting the fuselage when the unmanned aerial vehicle takes off and lands, and in order to ensure stability and reliability when the landing gear supports the unmanned aerial vehicle, the landing gear is generally arranged in a flared structure. In the existing unmanned aerial vehicle, in order to ensure the stability of the landing gear when supporting the unmanned aerial vehicle, the landing gear is always in an unfolding state, the occupied space is large, the whole size of the unmanned aerial vehicle is large, the storage and transportation are inconvenient, and the portability is poor.

In order to solve the above problems, as shown in fig. 1 to 6, the present utility model firstly provides a landing gear which can ensure stability during use, and at the same time, can also retract the landing gear when not in use to reduce the occupied space, thereby facilitating storage or transportation of the landing gear and the unmanned aerial vehicle.

As shown in fig. 1 and 4, specifically, the landing gear 1 is used for a unmanned aerial vehicle, and comprises a connecting frame 11, two sets of movable frames 12 and a locking assembly 13, wherein: the connecting frame 11 is used for being connected with the body 2 of the unmanned aerial vehicle; two sets of movable frames 12 are respectively rotatably connected with the connecting frame 11 at two sides of the machine body 2, and the movable frames 12 can rotate relative to the connecting frame 11 and switch between an expanded state or a contracted state, wherein: in the expanded state, the ends of the two movable frames 12 far from the connecting frame 11 are far away from each other to support the unmanned aerial vehicle, as shown in fig. 1, and in the contracted state, the ends of the two movable frames 12 far from the connecting frame 11 are close to each other; the locking component 13 is disposed on the connecting frame 11 and the movable frame 12, and is used for locking or unlocking the rotation of the movable frame 12 relative to the connecting frame 11.

As described above, in the existing unmanned aerial vehicle, in order to ensure stability when the landing gear supports the unmanned aerial vehicle, the landing gear is always in an unfolded state, and the occupied space is large, so that the overall size of the unmanned aerial vehicle is large, the storage and transportation are inconvenient, and the portability is poor. In the landing gear 1 provided by the utility model, when the landing gear 1 is required to be used, the movable frame 12 is controlled to rotate to the unfolded state relative to the connecting frame 11, so that the landing gear 1 can support the unmanned aerial vehicle, the locking component 13 is controlled to lock the movable frame 12 to rotate relative to the connecting frame 11, the stability and reliability of the landing gear 1 are ensured, and the landing gear 1 or the unmanned aerial vehicle is prevented from being toppled down due to the unexpected rotation of the movable frame 12 relative to the connecting frame 11. When the landing gear 1 is not required to be used, the locking component 13 is controlled to unlock the movable frame 12 to rotate relative to the connecting frame 11, and the movable frame 12 is controlled to rotate relative to the connecting frame 11 to a contracted state, so that one ends of the two groups of movable frames 12 far away from the connecting frame 11 are close to each other, the occupied space of the landing gear 1 can be reduced, and the landing gear 1 and the unmanned aerial vehicle can be conveniently stored or transported.

As shown in fig. 1 to 2, the number of movable frames 12 in each set of movable frames 12 may be one, two or more, and a plurality of movable frames 12 can promote stability when the landing gear 1 supports the unmanned aerial vehicle. In the illustrated embodiment, the number of movable frames 12 in each group of movable frames 12 is two, the connecting frames 11 are two parallel connecting rods, and two ends of each connecting rod are respectively rotatably connected with one movable frame 12 through a first rotating shaft 17. Of course, in other embodiments, the connecting frame 11 may be configured as a separate structure or a monolithic structure, for example, a plate structure, and the movable frame 12 and the connecting frame 11 may be rotatably connected by other structures such as a rotation pin, which is not particularly limited herein.

As shown in fig. 1 and 4, the landing gear 1 further includes two supporting frames 14 respectively on two sides of the fuselage 2, and one ends of the two sets of movable frames 12, which are far away from the connecting frame 11, are respectively connected with the two supporting frames 14. The supporting frame 14 can increase the contact area between the landing gear 1 and external structures such as the ground, the desktop and the like, and further improve the stability and the reliability when the landing gear 1 supports the unmanned aerial vehicle. In the illustrated embodiment, the support frames 14 are provided in a rod-like structure, and each set of two movable frames 12 is connected to one support frame 14 on the same side, so that the same set of movable frames 12 can move synchronously. In other embodiments, the support frame 14 may be configured as a plate structure or other structure capable of improving the stability of the landing gear 1, and the present utility model is not limited thereto.

As shown in fig. 1, the connecting frame 11 is connected with the bottom of the unmanned aerial vehicle body 2 through a connecting piece 16, the connecting piece 16 is sleeved on a connecting rod of the connecting frame 11 and is connected with the connecting frame 11 through gluing or screws and the like, so that the stability and reliability of the connection between the connecting frame 11 and the connecting piece 16 are ensured. The connection piece 16 is screwed with the fuselage 2 to achieve quick assembly and disassembly or replacement of the landing gear 1.

As shown in fig. 2 and 5, in one embodiment, the locking assembly 13 includes a first locking member 131 disposed on one of the movable frame 12 and the connecting frame 11 and a second locking member 132 disposed on the other, and in the unfolded state, the first locking member 131 can be engaged with the second locking member 132 to lock the movable frame 12 from rotating relative to the connecting frame 11. The reliability of the locking assembly 13 in the locking state can be ensured by the way of the clamping fit of the first clamping piece 131 and the second clamping piece 132, and the clamping structure is generally simpler.

In other embodiments, the locking assembly 13 may also include a fastener such as a screw that is threaded through one of the connecting frame 11 and the movable frame 12. Or, the locking component 13 may be configured as a plug-in structure or other structure capable of locking the rotation of the movable frame 12 relative to the connecting frame 11, for example, a protruding block is convexly disposed at one end of the movable frame 12 facing the connecting frame 11, and a slot is correspondingly disposed at one end of the connecting frame 11 facing the movable frame 12, when the movable frame 12 rotates relative to the connecting frame 11 to a deployed state, the protruding block is inserted into the slot, and the protruding block and the connecting frame are in interference fit with each other, so as to ensure the stability and reliability of the connection between the movable frame 12 and the connecting frame 11, and avoid the movable frame 12 from being accidentally separated from the connecting frame 11.

As shown in fig. 2 and 5, in the illustrated embodiment, the first locking member 131 is rotatably disposed on the movable frame 12 about the second rotating shaft 134, and the first locking member 131 can rotate about the second rotating shaft 134 along a first preset direction (i.e. the +a direction shown in fig. 2) to be locked with the second locking member 132, and can rotate about the second rotating shaft 134 along a reverse direction of the first preset direction (i.e. the-a direction shown in fig. 2) to be disengaged from the second locking member 132. Of course, the first fastening member 131 may be rotatably connected to the movable frame 12 by other structures such as a rotation pin. The first clamping piece 131 is controlled to rotate so that the first clamping piece 131 is clamped with or separated from the second clamping piece 132, and the adjusting mode is simple and convenient and is convenient for a user to operate. Of course, in other embodiments, the first locking member 131 may be slidably disposed on the movable frame 12 and capable of sliding close to or away from the second locking member 132 to be locked to or unlocked from the second locking member 132.

As shown in fig. 2 and 5, the first clamping member 131 includes clamping portions 1311 and a control portion 1312 distributed on two sides of the second rotating shaft 134, and the clamping portions 1311 can be clamped with the second clamping member 132; the locking assembly 13 further includes an elastic member 133 disposed between the control portion 1312 and the movable frame 12, and the elastic member 133 can apply an elastic force to the control portion 1312 in a first predetermined direction (i.e., the +a direction shown in fig. 2). The user can disengage the latch 1311 from the second latch 132 by toggling the control 1312 in the-a direction as shown in fig. 2. In the unfolded state, the elastic member 133 can always apply a force along the +a direction shown in fig. 2 to the control portion 1312, so as to avoid the first clamping member 131 and the second clamping member 132 from being accidentally separated, and further improve the stability of the landing gear 1.

As shown in fig. 3 and 6, the landing gear 1 further includes a limiting component 15, where the limiting component 15 includes a first limiting member 151 disposed on one of the connecting frame 11 and the movable frame 12 and a second limiting member 152 disposed on the other; in the contracted state, the first limiting member 151 abuts against the second limiting member 152 to limit the rotation of the movable frame 12 relative to the connecting frame 11. In the illustrated embodiment, the first limiting member 151 and the second limiting member 152 are both provided as step portions, and when the movable frame 12 rotates to a contracted state with respect to the connection frame 11, the two step portions are abutted against each other, and the movable frame 12 cannot further rotate with respect to the connection frame 11, so that the rotation range of the movable frame 12 can be limited, and damage caused by collision of the movable frames 12 on both sides with each other or collision of the movable frame 12 with other external structures due to an excessive rotation range of the movable frame 12 can be avoided.

Of course, in other embodiments, only one of the first limiting member 151 and the second limiting member 152 may be provided as a protrusion, and the other may be provided as an outer surface of the connecting frame 11 or the movable frame 12, and when the movable frame 12 rotates to a contracted state relative to the connecting frame 11, the protrusion may abut against the outer surface of the connecting frame 11 or the movable frame 12, so that the movable frame 12 cannot further rotate relative to the connecting frame 11.

The first rotating shaft 17 has a certain damping, and under the combined action of the limiting assembly 15 and the first rotating shaft 17, the movable frame 12 can be stabilized in a contracted state, so that the stability of the landing gear 1 in the contracted state can be improved, and the safety of the landing gear 1 and the unmanned aerial vehicle during storage or transportation is improved.

As shown in fig. 7 to 10, the present utility model further provides an unmanned aerial vehicle, which includes a fuselage 2, a plurality of horn assemblies 3, a power supply assembly 4, and the landing gear 1, wherein: a plurality of horn assemblies 3 are arranged at intervals along the outer circumference of the body 2 and are connected with the body 2; the power supply assembly 4 is arranged on the machine body 2 and is electrically connected with the horn assembly 3; the connection frame 11 is provided at the bottom of the body 2. The power supply assembly 4 supplies power to the horn assembly 3 so that the unmanned aerial vehicle can fly under the action of the horn assembly 3. The two groups of movable frames 12 are respectively arranged at two sides of the bottom of the machine body 2 so as to ensure the stability of the landing gear 1 when supporting the unmanned aerial vehicle.

As shown in fig. 7 and 9, the horn assembly 3 includes a connection arm 31 provided to the body 2 and a blade 32 rotatably provided at an end of the connection arm 31 remote from the body 2; the connection arm 31 is detachably connected to the body 2, and the paddle 32 is detachably connected to the connection arm 31. The end of the connecting arm 31 far away from the body 2 is also provided with a motor 33 for driving the paddle 32 to rotate, and the power supply assembly 4 is electrically connected with the motor 33 to drive the motor 33. The connecting arm 31 and the machine body 2 can be detachably connected through a quick connector, and the paddle 32 and the motor 33 can also be detachably connected through the quick connector, so that a user can quickly assemble and disassemble the unmanned aerial vehicle, and the usability of the unmanned aerial vehicle is improved; moreover, can dismantle paddle 32 and linking arm 31 in order to reduce unmanned aerial vehicle whole volume when accomodating unmanned aerial vehicle, unmanned aerial vehicle's accomodate or transportation of being convenient for promotes unmanned aerial vehicle's portability.

In the illustrated embodiment, the unmanned aerial vehicle includes six horn assemblies 3, and the six horn assemblies 3 are uniformly spaced along the outer circumference of the fuselage 2 to ensure balance of the unmanned aerial vehicle. Of course, in other embodiments, the unmanned aerial vehicle may also include two, three, four or more horn assemblies 3, and the plurality of horn assemblies 3 are arranged at intervals, so long as it can be ensured that the horn assemblies 3 do not interfere with each other, and the unmanned aerial vehicle can maintain balance, which is not particularly limited herein.

As shown in fig. 7 to 8, because the weight of the power supply assembly 4 is large, in order to avoid the influence of the power supply assembly 4 on the balance of the unmanned aerial vehicle, the power supply assembly 4 is arranged at the center of the bottom of the body 2, so that the gravity center of the unmanned aerial vehicle is close to the center, the flight control of the unmanned aerial vehicle is facilitated, and the flight safety of the unmanned aerial vehicle is improved. In the process of transporting the unmanned aerial vehicle, the movable frames 12 in the contracted state are positioned on two sides of the power supply assembly 4, so that the function of protecting the power supply assembly 4 can be achieved, and the safety of the power supply assembly 4 in the transportation process is improved. The power supply assembly 4 may be configured as a power source such as a lithium battery.

As shown in fig. 8 to 9, in the illustrated embodiment, the power supply assembly 4 includes an engine 41, a generator 42 and a battery 43, and the engine 41 can drive the generator 42 to generate electricity and transmit the electricity to the battery 43; the unmanned aerial vehicle further comprises an oil tank 5 arranged in the body 2, and the oil tank 5 supplies oil for the engine 41. Compared with the power supply by a lithium battery, the fuel with higher energy density is used as a power source, and the fuel is converted into electric energy through the functions of the engine 41 and the generator 42, so that the unmanned aerial vehicle can be provided with longer endurance. Because the volume of the oil tank 5 is large, setting the oil tank 5 in the fuselage 2 can also avoid increasing the volume of the unmanned aerial vehicle.

As shown in fig. 8, the body 2 includes a case 21 and a cover 22 enclosing a housing chamber, and the fuel tank 5 is housed in the housing chamber. The cover 22 is detachably connected with the housing 21, so that a user can conveniently detach the cover 22 and then refuel the oil tank 5, and simultaneously, the user can conveniently detach or replace the oil tank 5 and other elements in the accommodating cavity.

Since the engine 41 vibrates during operation, in order to avoid the vibration affecting the normal flight of the unmanned aerial vehicle, the unmanned aerial vehicle further includes a shock absorber (not shown) disposed between the power supply assembly 4 and the main body 2 to isolate the vibration of the engine 41.

As shown in fig. 7 and 9, the unmanned aerial vehicle further includes a mount 6 provided to the main body 2 and used for mounting the mounting device. The mounting member 6 may be a plate-like structure and provided with one or more mounting locations for mounting the mounting devices to enable mounting of a variety of mounting devices. The mounting equipment and the mounting position can be connected through screws, so that the mounting equipment can be quickly disassembled or replaced. The mount 6 can be used for installing and mount devices such as cloud deck, because the weight of the mount device is lighter, the influence on the gravity center of the unmanned aerial vehicle is less, so the mount 6 can be installed to the bottom of the body 2 and positioned on one side of the power supply assembly 4. The mounting piece 6 and the bottom of the machine body 2 can be connected through screws so as to realize quick disassembly and assembly or replacement of the mounting piece 6.

The technical features of the above-described embodiments may be arbitrarily combined, and all possible combinations of the technical features in the above-described embodiments are not described for brevity of description, however, as long as there is no contradiction between the combinations of the technical features, they should be considered as the scope of the description.

The above examples only represent a few embodiments of the present application, which are described in more detail and are not to be construed as limiting the scope of the claims. It should be noted that it would be apparent to those skilled in the art that various modifications and improvements could be made without departing from the spirit of the present application, which would be within the scope of the present application. Accordingly, the scope of the present application is to be determined by the following claims.

Claims (11)

1. Landing gear (1) for an unmanned aerial vehicle, characterized in that it comprises:

the connecting frame (11) is used for being connected with the unmanned aerial vehicle body (2);

two groups of movable frames (12), two groups of movable frames (12) are respectively connected with the connecting frames (11) in a rotating mode on two sides of the machine body (2), and the movable frames (12) can rotate relative to the connecting frames (11) and are switched between an unfolding state or a shrinking state, wherein: in the unfolded state, one ends of the two groups of movable frames (12) far away from the connecting frame (11) are far away from each other so as to support the unmanned aerial vehicle, and in the contracted state, one ends of the two groups of movable frames (12) far away from the connecting frame (11) are close to each other; the method comprises the steps of,

the locking component (13) is arranged on the connecting frame (11) and/or the movable frame (12) and is used for locking/unlocking the rotation of the movable frame (12) relative to the connecting frame (11).

2. Landing gear (1) according to claim 1, wherein the locking assembly (13) comprises a first clamping member (131) arranged on one of the mobile frame (12) and the connecting frame (11) and a second clamping member (132) arranged on the other, the first clamping member (131) being capable of being clamped and matched with the second clamping member (132) so as to lock the mobile frame (12) in the unfolded state.

3. Landing gear (1) according to claim 2, wherein the first clamping member (131) is rotatably arranged on the movable frame (12) about an axis, the first clamping member (131) being rotatable about the axis in a first predetermined direction into clamping engagement with the second clamping member (132) and being rotatable about the axis in a reverse direction of the first predetermined direction into disengagement with the second clamping member (132).

4. A landing gear (1) according to claim 3, wherein the first clamping member (131) comprises clamping portions (1311) and control portions (1312) distributed on both sides of the axis, the clamping portions (1311) being capable of clamping with the second clamping member (132);

the locking assembly (13) further comprises an elastic piece (133) arranged between the control part (1312) and the movable frame (12), and the elastic piece (133) can apply an elastic force to the control part (1312) towards the first preset direction.

5. Landing gear (1) according to claim 1, wherein the landing gear (1) further comprises a stop assembly (15), the stop assembly (15) comprising a first stop (151) provided to one of the connecting frame (11) and the mobile frame (12) and a second stop (152) provided to the other;

in the contracted state, the first limiting piece (151) is abutted with the second limiting piece (152) so as to limit the rotation of the movable frame (12) relative to the connecting frame (11).

6. Landing gear (1) according to claim 1, wherein the landing gear (1) further comprises two supporting frames (14) on both sides of the fuselage (2), respectively, and wherein two sets of movable frames (12) are connected to the two supporting frames (14) at their ends remote from the connecting frame (11), respectively.

7. An unmanned aerial vehicle, comprising:

a body (2);

a plurality of arm assemblies (3) arranged at intervals along the periphery of the body (2) and connected with the body (2);

the power supply assembly (4) is arranged on the machine body (2) and is electrically connected with the horn assembly (3); the method comprises the steps of,

landing gear (1) according to any of claims 1 to 6, the connection frame (11) being provided at the bottom of the fuselage (2).

8. The unmanned aerial vehicle according to claim 7, wherein the horn assembly (3) comprises a connecting arm (31) provided to the fuselage (2) and a blade (32) rotatably provided to an end of the connecting arm (31) remote from the fuselage (2);

the connecting arm (31) is detachably connected with the machine body (2), and/or the blade (32) is detachably connected with the connecting arm (31).

9. The unmanned aerial vehicle according to claim 7, wherein the power supply assembly (4) is arranged in the centre of the bottom of the fuselage (2).

10. The unmanned aerial vehicle according to claim 8, wherein the power supply assembly (4) comprises an engine (41), a generator (42) and a battery (43), and the engine (41) can drive the generator (42) to run for generating electricity and transmit the electric energy to the battery (43);

the unmanned aerial vehicle further comprises an oil tank (5) arranged in the machine body (2), and the oil tank (5) supplies oil for the engine (41).

11. The unmanned aerial vehicle according to claim 7, further comprising a shock absorber arranged between the power supply assembly (4) and the fuselage (2); and/or the number of the groups of groups,

the unmanned aerial vehicle further comprises a mounting piece (6) which is arranged on the body (2) and used for mounting equipment.

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