CN207328811U - Unmanned vehicle - Google Patents

Abstract

A kind of unmanned vehicle, including：Fuselage and the wing components for being rotationally connected with the fuselage, the wing components include：First wing, the second wing and the bindiny mechanism for the first wing to be connected to fuselage, first wing includes first end and the second end opposite with first end, bindiny mechanism is assemblied in the first end, and second wing is removably assemblied in the second end；Wherein, the first wing is rotationally connected with fuselage by bindiny mechanism, so that the first wing is unfolded or folds with respect to fuselage.The utility model devises a kind of unmanned vehicle, wing components in unmanned vehicle are divided into the multi-segment structure wing detachably assembled, and the wing being connected with fuselage is rotatably connected, so that wing components are under non-working condition, multi element wing detachably assembles, and the wing being connected with fuselage fuselage can fold relatively, so that size of the wing components shared by under non-working condition is smaller, in order to store and carry.

Description

UAV

technical field

The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle with foldable wings.

Background technique

With the rapid development of science and technology, the development of unmanned aerial vehicle technology is becoming more and more mature, and its application fields are becoming more and more extensive, such as: military, scientific research, civil and other fields, which can be used for photography, exploration, communication, disaster prevention and mitigation , Border Patrol, and more.

For fixed-wing unmanned aerial vehicles, usually due to the long wings, the overall volume of the unmanned aerial vehicle is relatively large. During storage or transportation, a large carrier is required to package the unmanned aerial vehicle, which is not convenient for packaging and transportation. transportation.

Utility model content

The utility model proposes an unmanned aerial vehicle with foldable wings to solve the above technical problems.

According to an embodiment of the present invention, an unmanned aerial vehicle is provided, which is characterized in that it includes: a fuselage, and a wing assembly that is rotatably connected to the fuselage, and the wing assembly includes: a first wing, A second wing, and a connection mechanism for connecting the first wing to the fuselage, the first wing includes a first end and a second end opposite to the first end, so The connecting mechanism is assembled on the first end, and the second wing is detachably assembled on the second end;

Wherein, the first wing is rotatably connected to the fuselage through the connecting mechanism, so that the first wing is unfolded or folded relative to the fuselage.

Further, the connection mechanism includes a first connection part fixed to the fuselage, and a second connection part fixed to the first end; wherein, the second connection part is pivotally connected to the first connectors.

Further, the first wing also includes a matching part provided at the first end; wherein, when the first wing is deployed relative to the fuselage, the matching part and the fitting part on the fuselage The lock fitting fits the lock.

Further, the wing assembly further includes a first electrical connector disposed at the second end, and the second wing is provided with a second electrical connector mated with the first electrical connector;

Wherein, when the second wing is assembled on the first wing, the first electrical connector is mated with the second electrical connector, so that the second wing is connected to the first wing A wing communication link.

Further, the wing assembly further includes a locking mechanism arranged at the second end, and the second wing is provided with a locking part that cooperates with the locking mechanism;

Wherein, when the second wing is assembled on the first wing, the locking mechanism is locked to the locking part, so that the second wing is locked to the first wing.

Further, the locking mechanism includes a sliding part limited in the chute at the first end, a lock hook connected to the sliding part, an elastic part sleeved on the sliding part, and a sliding part connected to the sliding part. The adjustment piece on the top, the adjustment piece extends from the chute, when the elastic piece is in the initial state, the lock hook is in the state of being locked on the locking part;

Wherein, under the adjustment of the adjusting member along the width direction of the first wing, the sliding member regulates the locking hook to be assembled in the locking part or unlocked in the locking part; the sliding Under the restoring force of the elastic member, the locking hook is driven to be locked to the locking part.

Further, a guide rod is provided on a side of the second wing opposite to the second end, and a guide hole is correspondingly provided on the end surface of the second end, so that the second wing matches the Assembly position of the first wing.

Further, the wing assembly also includes a rotor assembly arranged on the first wing, which is used to provide flight power for the UAV.

Further, the rotor assembly includes a wing arm connected to the first wing, a power assembly connected to the free end of the wing arm, and a propeller connected to the power assembly.

Further, a circuit channel is provided in the wing arm for accommodating cables connected to the power assembly and the first wing.

Further, the unmanned aerial vehicle also includes an empennage connected to the fuselage, the empennage includes an empennage main body and a connecting arm connected to the empennage main body, the fuselage is provided with a connecting part.

Further, the connecting arm is provided with a lock pin, and the connecting part is provided with a lock matching hole for matching with the lock pin; wherein, through the cooperation of the lock pin and the lock matching hole, the The empennage is fixed to the fuselage.

Further, the connecting arm is also provided with a third electrical connector connected to the main body of the empennage, and the fuselage is provided with a fourth electrical connector adapted to the third electrical connector, so that The empennage is assembled to the fuselage while being communicatively connected to the fuselage.

The technical solution provided by the embodiments of the utility model may include the following beneficial effects: the utility model designs an unmanned aerial vehicle, which divides the wing assembly into detachable multi-section structural wings, and is connected with the fuselage The connected wings are rotatably connected so that the wing assembly is in a non-use state. The occupied size is small for easy storage and portability.

It should be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the present invention.

Description of drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings that need to be used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings in the following description are only some implementations of the present invention. For example, those skilled in the art can also obtain other drawings based on these drawings without paying creative labor.

Fig. 1 is a schematic diagram of the overall structure of an unmanned aerial vehicle shown in an exemplary embodiment of the present invention;

Fig. 2 is a detachable structural schematic diagram of a wing assembly of an unmanned aerial vehicle shown in an exemplary embodiment of the present invention;

Fig. 3 is a schematic diagram of the structure of a wing folded relative to the fuselage in an unmanned aerial vehicle shown in an exemplary embodiment of the present invention;

Fig. 4 is a structural schematic diagram of the folding of the first wing relative to the fuselage in an unmanned aerial vehicle shown in another exemplary embodiment of the present invention;

Fig. 5 is a structural schematic diagram of a connection mechanism in a wing assembly shown in an exemplary embodiment of the present invention;

Fig. 6 is a structural schematic diagram of the connection part between the first wing and the second wing of a wing assembly shown in an exemplary embodiment of the present invention;

Fig. 7 is an enlarged view of part B in Fig. 6;

Fig. 8 is an enlarged view of part A in Fig. 3;

Fig. 9 is a structural schematic diagram of an empennage of an unmanned aerial vehicle shown in an exemplary embodiment of the present invention.

Detailed ways

The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. example. Based on the embodiments of the present utility model, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the scope of protection of the present utility model.

The structure of the wing assembly of the present invention and the unmanned aerial vehicle with the wing assembly will be described in detail below in conjunction with the accompanying drawings. In the case of no conflict, the following embodiments and the features in the embodiments can be combined with each other.

As shown in FIGS. 1 to 5 , the unmanned aerial vehicle 100 of the embodiment of the present invention includes: a fuselage 101 and a wing assembly 10 rotatably connected to the fuselage 101 . The wing assembly 10 includes: a first wing 11 , a second wing 12 , and a connecting mechanism 13 for connecting the first wing 11 to the fuselage 101 of the UAV 100 . The first wing 11 can be folded relative to the fuselage 101 through the connecting mechanism 13 , so that the volume space occupied by the entire UAV 100 can be reduced for easy storage and carrying.

Specifically, the first wing 11 includes a first end 111 and a second end 112 opposite to the first end 111, the connecting mechanism 13 is assembled on the first end 111, and the second wing 12 is detachably assembled on the second end. end 112. In the present invention, the first wing 11 is rotatably connected to the fuselage 101 through the connection mechanism 13 , so that the first wing 11 is unfolded or folded relative to the fuselage 101 . When the first wing 11 is unfolded relative to the fuselage 101 , the wing assembly 10 is in the use state; when the first wing 11 is folded relative to the fuselage 101 , the wing assembly 10 is in the non-use state. In the present utility model, the wing assembly 10 is not limited to the first wing 11 and the second wing 12. According to the size design of the UAV 100, the wing assembly 10 can also include a third wing, a fourth wing, etc. , the connection between these wings is the same as that of the first wing 11 and the second wing 12 .

As shown in FIGS. 3 to 5 , the connecting mechanism 13 includes a first connecting member 131 fixed to the fuselage 101 and a second connecting member 132 fixed to the first end 111, and the second connecting member 132 is pivotally connected to The first connecting part 131 is such that the second connecting part 132 can rotate relative to the first connecting part 131 . In this embodiment, the first connecting member 131 can be fixed on the fuselage 101 by means of screws, rivets or snap-fitting. On the end surface of the first end 111 of the wing 11 , the first connecting member 131 and the second connecting member 132 are connected through a rotating shaft.

In this embodiment, the first wing 11 is rotated downward (bottom direction) through the connecting mechanism 13 to be folded relative to the fuselage 101. When the first wing 11 is converted into a non-use state, the first wing 11 can be used The self-gravity makes the wings fold relative to the fuselage 101. In this embodiment, when the first wing 11 is folded relative to the fuselage 101, the first wings 11 on both sides of the fuselage 101 are attached to the two sides of the fuselage 101, so that the wing assembly 10 is in a non-use state The volume space occupied is small. Wherein, the rotation angle of the first wing 11 relative to the fuselage 101 can be limited through the position limitation of the first wing 11 by the fuselage 101 .

Certainly, in other embodiments of the present utility model, according to the different models of the unmanned aerial vehicle 100, the first wing 11 can also be rotated upwards (roof direction) through the connecting mechanism 13 to rotate and fold relative to the fuselage 101, The first wing 11 can be deployed relative to the fuselage 101 by its own gravity to be in a use state. In addition, the first wing 11 can also be rotated and folded relative to the fuselage 101 forward (in the direction of the nose) or backward (in the direction of the empennage 20) through the connecting mechanism 13, specifically according to the shape of the fuselage 101. Certainly.

Further, the first wing 11 also includes a matching portion (not shown) disposed at the first end 111 , and correspondingly, a lock fitting (not shown) is provided on the fuselage 101 . Wherein, when the first wing 11 is deployed relative to the fuselage 101 for the second time, the matching part is locked with the lock fitting on the fuselage 101, and the lock fitting can also provide support for the first wing 11 to strengthen the first wing 11. The connection strength between the wing 11 and the fuselage 101. Of course, the matching part can also be arranged on the body 101 , and the locking part can be arranged on the first end 111 .

In an optional embodiment, the lock fitting may be a carbon tube, and the matching portion is a connection hole matched with the carbon tube. The matching mode of the lock fitting and the matching portion can be similar to that of the bolt and the pin hole. The carbon tube is arranged on the fuselage 101 and can be relatively adjusted to move into or out of the matching portion so that the first wing 11 is fixed. on the fuselage 101. Wherein, the carbon tube can also run through the fuselage 101 to be matched with the first wings 11 on both sides at the same time. During assembly, the first wings 11 on both sides can be fixedly assembled by moving the position of the carbon tube.

In yet another embodiment, the carbon tube is arranged on the first wing 11, and the connecting hole is arranged on the fuselage 101. When the first wing 11 is deployed relative to the fuselage 101, the carbon tube is inserted into the connecting hole to realize the first The fixing of wing 11 and fuselage 101. Wherein, the carbon tube can also pass through the first wing 11 , so that the second wing 12 can be fixed to the first wing 11 through the carbon tube, and then the first wing 11 can be fixed to the fuselage 102 . Of course, the structure of the lock fittings and matching parts of the present utility model is not limited thereto, and other lock fittings and fitting parts that can be used to keep the first wing 11 relatively unfolded relative to the fuselage 101 are applicable to the embodiments of the present utility model middle.

A communication cable (not shown) is also connected between the first wing 11 and the fuselage 101 , so that the wing assembly 10 can be communicatively connected to the fuselage 101 . Preferably, the communication cable can not only realize the communication between the wing assembly 10 and the fuselage 101 but also provide power for the wing assembly 10 . In order to prevent the communication cable from affecting the folding of the wing assembly 10 corresponding to the fuselage 101 , the communication cable has a certain redundancy between the first wing 11 and the fuselage 101 . Wherein, the communication cable may be an FPC (Flexible Printed Circuit, flexible circuit board) line or a coaxial line.

As shown in Figure 1, Figure 6 and Figure 7, the wing assembly 10 also includes a first electrical connector (not shown) located at the second end 112, and the second wing 12 is provided with the first electrical connector The second electrical connector 121 is matched and connected. Wherein, when the second wing 12 is assembled on the first wing 11 , the first electrical connector is matched with the second electrical connector 121 , so that the second wing 12 is communicatively connected with the first wing 11 . When the first connector and the second connector with stronger rigidity are used, the mating connection between the first connector and the second connector also has the effect of fixed connection, so that the second wing 12 can be connected to the first wing 11 on.

In the present utility model, steering gear 113 is respectively arranged in the first wing 11 and the second wing 12, in order to control the rudder surface on the first wing 11 and the second wing 12, thereby can control unmanned aerial vehicle 100's of flight. In this embodiment, the first connector and the second connector are mated and connected by a male aviation connector and a female aviation connector, so as to realize the communication between the first wing 11 and the second wing 12 . Certainly, the first connector and the second connector of the present invention are not limited to the selection of the aviation connection male and the aviation connection female, and other types of connectors are also applicable to the present invention.

The wing assembly 10 further includes a locking mechanism disposed at the second end 112 , and the second wing 12 is provided with an interlocking portion 122 cooperating with the locking mechanism. Wherein, when the second wing 12 is assembled on the first wing 11 , the second wing 12 is locked to the first wing 11 by locking the locking mechanism with the locking portion 122 . In this embodiment, the connection rigidity between the first wing 11 and the second wing 12 can be further ensured through the cooperation of the locking mechanism and the locking part 122 . Of course, in another embodiment, the locking mechanism can also be arranged on the second wing 12 , and the locking part 122 is arranged on the second end 112 .

In an embodiment, the locking mechanism includes a sliding part 141 limited in the sliding groove of the first end 111, a locking hook 142 connected to the sliding part 141, an elastic part 143 sleeved on the sliding part 141, and a sliding part connected to the sliding part 141. Adjustment piece 144 on 141. The adjusting member 144 extends out from the sliding groove. When the elastic member 143 is in an initial state, the locking hook 142 is in a state of being locked to the locking portion 122 . Wherein, under the adjustment of the adjusting member 144 along the width direction of the first wing 11 , the sliding member 141 can adjust and control the lock hook 142 to be assembled in the locking part 122 or unlocked in the locking part 122; Under the force, the locking hook 142 is driven to lock with the locking part 122 .

Further, a guide rod (not shown) is provided on the side of the second wing 12 opposite to the second end 112, and a guide hole (not shown) is correspondingly provided on the end surface of the second end 112, so that the first The second wing 12 matches the assembly position of the first wing 11 . In this embodiment, the connection between the guide rod and the guide hole can provide strength for the connection of the second wing 12 to the first wing 11 and enhance the rigidity of the connection between the second wing 12 and the first wing 11 .

As shown in FIG. 1 and FIG. 2 , the wing assembly 10 also includes a rotor assembly 15 arranged on the first wing 11 for providing flight power for the UAV 100 and enabling the UAV 100 to take off and land vertically. Specifically, the rotor assembly 15 includes a wing arm 151 connected to the first wing 11 , a power assembly 152 connected to the free end of the wing arm 151 , and a propeller 153 connected to the power assembly 152 . Wherein, the wing arm 151 is close to the second end 112 of the first wing 11, and the second end 112 is provided with a clamping portion for fixing the wing arm 151. The direction of the tail is the same.

Further, a circuit channel (not shown) is provided in the wing arm 151 to accommodate cables connected to the power assembly and the first wing 11, so as to provide power for the power assembly through the circuit in the first wing 11 . In addition, the cable also includes a communication cable, and the fuselage 101 can obtain information such as the rotational speed of the propeller through the connection of the communication cable.

As shown in Fig. 3, Fig. 8 and Fig. 9, unmanned aerial vehicle 100 also comprises the empennage 20 that is connected to fuselage 101, and empennage 20 comprises empennage main body 21 and is connected to the connecting arm 22 of empennage main body 21, and fuselage 101 is provided with There is a connecting portion 102 that is mated with the connecting arm 22 . In this embodiment, the empennage 20 is detachably assembled on the fuselage 101 through the cooperation of the connecting arm 22 and the connecting portion 102, so that the volume space occupied by the unmanned aerial vehicle 100 can be further reduced, which is convenient The user stores and carries, and the disassembly and assembly are relatively simple and convenient to use.

Further, the connecting arm 22 is provided with a locking pin 23 , and the connecting portion 102 is provided with a locking hole 1021 for matching with the locking pin 23 . Wherein, the empennage 20 is fixed to the fuselage 101 through the cooperation of the locking pin 23 and the locking hole 1021 . Specifically, the locking pin 23 is an elastic structure, and the locking pin 23 includes a pin shaft and a spring matched with the pin shaft. In an initial state, the spring can drive the pin shaft to protrude out of the connecting arm 22 under its own elastic force. When the user needs to install the empennage 20 on the fuselage 101 , the pin can be retracted into the connecting arm 22 by pressing the pin, and the spring is in a compressed state, so that the connecting arm 22 can be assembled in the connecting portion 102 . When the pin shaft corresponds to the locking hole 1021 , the pin shaft protrudes out of the connecting arm 22 under the elastic restoring force of the spring, and then is inserted into the locking hole 1021 , so that the empennage 20 is locked to the fuselage 101 . When the empennage 20 is disassembled, the user presses the pin shaft so that the pin shaft withdraws from the lock fitting hole 1021, so that the empennage 20 can be disassembled from the fuselage 101. This kind of matching method can be assembled simply and quickly without using tools. Disassemble.

Wherein, the connecting arm 22 is also provided with a third electrical connector (not shown) connected to the empennage main body 21, and the fuselage 101 is provided with a fourth electrical connector (not shown) adapted to the third electrical connector. ), so that the empennage 20 is mounted on the fuselage 101 and communicated with the fuselage 101 at the same time. The empennage 20 is provided with a steering gear 211 for controlling the flight of the UAV 100 . In this embodiment, the communication is realized through the third electrical connector and the fourth electrical connector, so that the control module in the fuselage 101 controls the empennage 20 to cooperate with the flight. Optionally, the third electrical connector and the fourth electrical connector are selected from aviation male connectors and aviation connector female connectors.

The unmanned aerial vehicle 100 also includes two hangers 104 arranged on two sides of the fuselage 101 , and the two hangers 104 cooperate to support the fuselage 101 . Preferably, after the first wing 11 is folded relative to the fuselage 101, the maximum occupied dimension between the first wings 11 on both sides is not greater than the maximum occupied dimension of the two hangars 104, so that the hangars 104 The effect of protecting the first wing 11 can be played.

When assembling the unmanned aerial vehicle 100 of the present invention, the assembly sequence of the wing assembly 10 and the empennage 20 is not limited, and the wing assembly 10 or the empennage 20 can be assembled first. When assembling the wing assembly 10, the first wing 11 can be rotated through the connecting mechanism 13 to unfold relative to the fuselage 101, and then the first wing 11 can be fixed by inserting the lock fitting into the mating part, and then the second wing can be fixed. The second wing 12 is assembled on the first wing 11, and the guide rod on the second wing 12 can be pre-assembled in the guide hole of the second end 112 for pre-positioning, and correspondingly connect the first connector to the second 121, and then the second wing 12 is further fixed on the first wing 11 through the cooperation of the locking mechanism 13 and the locking part 122; of course, the second wing 12 can also be assembled on the first wing 11 first. , and then deploy the first wing 11 relative to the fuselage 101. This assembly method is the same as that of the above-mentioned embodiment, except that the assembly sequence is different.

When the wing assembly 10 is disassembled, the locking hook 142 is unlocked with the locking part 122 by turning the adjusting part 144 of the locking mechanism 13, and then the second wing 12 is moved away from the first wing 11 in the direction of the second wing 12. Dismount from the first wing 11, now the first connector and the second connector 121 are loosened, the guide rod is also pulled out from the guide hole, the second wing 12 is disassembled from the first wing 11, Then adjust the locking fittings so that the locking fittings are disengaged from the first wing 11 , and now the first wing 11 is folded relative to the fuselage 101 under its own gravity, so that the first wing 11 is close to the fuselage 101 .

When assembling the empennage 20, press the lock pin 23 to retract the lock pin 23 into the connecting arm 22, then insert the connecting arm 22 into the connecting portion 102 of the fuselage 101, and connect the third connector and the fourth connector Corresponding connection, at the same time make the lock pin 23 correspond to the lock matching hole 1021 on the connecting part 102, at this time the lock pin 23 springs up and locks into the lock matching hole 1021, thereby realizing the fixed connection and communication connection between the empennage 20 and the fuselage 101 . When detaching the empennage 20, by pressing the lock pin 23 to unlock the lock pin 23 in the lock matching hole 1021, at this time, the connecting arm 22 is pulled out toward the direction away from the fuselage 101, so that the third connector and the fourth connector Disassemble, and then make the connecting arm 22 disengage from the connecting portion 102 , so as to complete the disassembly of the empennage 20 .

The utility model designs an unmanned aerial vehicle. The unmanned aerial vehicle has a foldable wing assembly. The wing assembly is divided into detachable and assembled multi-segment structural wings, and the wings connected to the fuselage are rotatably connected. In the non-use state of the wing assembly, the multi-section wing can be disassembled and assembled, and the wing connected to the fuselage can be folded relative to the fuselage, so that the size occupied by the wing assembly in the non-use state is small, so that Store and carry. In addition, the unmanned aerial vehicle also has a quickly detachable and connected empennage, and the empennage can be quickly disassembled, which can further reduce the occupied size of the unmanned aerial vehicle.

Other embodiments of the invention will be readily apparent to those skilled in the art from consideration of the specification and practice of the invention disclosed herein. This application is intended to cover any modification, use or adaptation of the utility model, which follows the general principles of the utility model and includes common knowledge or common knowledge in the technical field not disclosed by the utility model. conventional technical means. It is intended that the specification and examples be considered exemplary only, with a true scope and spirit of the invention indicated by the appended claims.

It should be understood that the present invention is not limited to the precise structure which has been described above and shown in the accompanying drawings, and various modifications and changes can be made without departing from the scope thereof. The scope of the invention is limited only by the appended claims.

Claims (13)

1. A kind of unmanned aerial vehicle, it is characterized in that, comprises: fuselage and the wing assembly that is rotatably connected to described fuselage, and described wing assembly comprises: first wing, second wing, and for A connecting mechanism for connecting the first wing to the fuselage, the first wing includes a first end and a second end opposite to the first end, the connecting mechanism is assembled on the first one end, the second wing is detachably assembled to the second end; Wherein, the first wing is rotatably connected to the fuselage through the connecting mechanism, so that the first wing is unfolded or folded relative to the fuselage. 2. The unmanned aerial vehicle according to claim 1, wherein the connecting mechanism includes a first connecting piece fixed to the fuselage and a second connecting piece fixed at the first end; wherein, The second connecting part is pivotally connected to the first connecting part. 3. The unmanned aerial vehicle according to claim 2, wherein the first wing also includes a matching portion located at the first end; wherein, the first wing is opposite to the fuselage When unfolded, the matching part cooperates and locks with the lock fitting on the fuselage. 4. The unmanned aerial vehicle according to claim 1, wherein the wing assembly further comprises a first electrical connector disposed at the second end, and the second wing is provided with the first electrical connector. a second electrical connector mated to the electrical connector; Wherein, when the second wing is assembled on the first wing, the first electrical connector is mated with the second electrical connector, so that the second wing is connected to the first wing A wing communication link. 5. The unmanned aerial vehicle according to claim 4, wherein the wing assembly also includes a locking mechanism located at the second end, and the second wing is provided with a lock that cooperates with the locking mechanism. distribution department; Wherein, when the second wing is assembled on the first wing, the locking mechanism is locked to the locking part, so that the second wing is locked to the first wing. 6. The unmanned aerial vehicle according to claim 5, wherein the locking mechanism comprises a sliding part limited in a chute at the first end, a locking hook connected to the sliding part, and a locking hook sleeved on the sliding part. The elastic piece on the sliding piece and the adjusting piece connected to the sliding piece, the adjusting piece extends from the chute, when the elastic piece is in the initial state, the locking hook is locked on the Describe the state of the locking part; Wherein, under the adjustment of the adjusting member along the width direction of the first wing, the sliding member regulates the locking hook to be assembled in the locking part or unlocked in the locking part; the sliding Under the restoring force of the elastic member, the locking hook is driven to be locked to the locking part. 7. The unmanned aerial vehicle according to claim 4, wherein a side surface of the second wing opposite to the second end is also provided with a guide rod, and the end surface of the second end is correspondingly provided with a guide rod. holes so that the second wing matches the assembly position of the first wing. 8 . The unmanned aerial vehicle according to claim 1 , wherein the wing assembly further comprises a rotor assembly arranged on the first wing for providing flight power for the unmanned aerial vehicle. 9. The unmanned aerial vehicle according to claim 8, wherein the rotor assembly comprises a wing arm connected to the first wing, a power assembly connected to the free end of the wing arm, and a power assembly connected to the The propeller on the power pack. 10 . The unmanned aerial vehicle according to claim 9 , wherein a line channel is provided in the wing arm for accommodating cables connected to the power assembly and the first wing. 11 . 11. The unmanned aerial vehicle according to claim 1, wherein the unmanned aerial vehicle also includes an empennage connected to the fuselage, the empennage comprises an empennage main body and a connecting arm connected to the empennage main body, the The fuselage is provided with a connecting part that is mated with the connecting arm. 12. The unmanned aerial vehicle according to claim 11, wherein the connecting arm is provided with a locking pin, and the connecting portion is provided with a lock fitting hole matched with the locking pin; wherein, through the The lock pin cooperates with the locking hole to fix the empennage to the fuselage. 13. The unmanned aerial vehicle according to claim 11, characterized in that, the connecting arm is also provided with a third electrical connector connected to the empennage body, and the fuselage is provided with the third electrical connector. The fourth electrical connector adapted to the electrical connector enables the empennage to be communicatively connected to the fuselage while being assembled to the fuselage.