Folding empennage device of unmanned aerial vehicle

Abstract

The folding empennage device of the unmanned aerial vehicle relates to the technical field of unmanned aerial vehicles and comprises a shell, a center block is arranged in the middle of the shell, a plurality of extending rods are elastically and slidably arranged in the shell through first springs, and the ends, close to the center block, of the extending rods are rotationally connected with the center block through connecting rods; arc-shaped side plates are elastically and rotationally arranged on the two sides of the end, away from the center block, of the extension rod through torsional springs, and a plurality of sliding rod arc-shaped blocks are elastically and slidably arranged in the shell through second springs; after the unmanned aerial vehicle is launched, the extending rod extends outwards along the shell under the action of elastic force, meanwhile, the arc-shaped side plates on the two sides of the extending rod are unfolded under the action of the elastic force, the extending rod drives the center block to move when extending out, the arc-shaped side plates are pushed outwards along the shell, and a stable empennage structure is formed; the device has the advantages of being simple in structure, convenient to use and high in reliability.

Description

Technical Field

[0001] The invention relates to the technical field of unmanned aerial vehicles, and in particular to a foldable tail wing device of an unmanned aerial vehicle. Background Art

[0002] Among the many drone applications, applying drones to mortar platforms is an innovation and attempt, as well as a research and expansion of technical applications, which can improve the comprehensive combat capability of weapons; the engineering application of mortar-launched drones will bring considerable benefits to the application units, and can also improve the comprehensive combat effectiveness of my country's drone platforms; the high and low pressure launch technology of mortar-launched drones can give full play to the portability of mortars, improve the deployment efficiency of drones and extend the combat time of drones. Its portability enables it to be used on a large scale in urban combat; its deployment efficiency determines that it can build a dense drone reconnaissance network in a short time and provide real-time feedback on the battlefield environment; at the same time, longer combat time ensures that drones can carry out more complex battlefield penetrations and more accurate target damage. Mortar-launched drones help to improve the future ground unmanned equipment system structure, promote the leapfrog development and transformation of the army, and enhance the combat capability of the army system.

[0003] Existing tail wing devices for gun-launched UAVs, such as a folding tail wing device for gun-launched UAVs and a gun-launched UAV provided by publication number CN117208257A, include four sets of folding wings, locking tongues, supports, rotating shafts and torsion springs, the four supports are evenly distributed on the fuselage, the folding wings are outside the fuselage, the inner and outer surfaces are arc surfaces, and are connected to the supports through a rotating shaft; the torsion spring adopts a 45° multi-turn torsion spring structure, which is sleeved outside the rotating shaft, one end of which is against the fuselage, and the other end is against the inner plane of the folding wing; the locking tongue is fixed to the folding wing, and there is a notch at the connection between the support and the fuselage, the width of the locking tongue is consistent with the width of the notch of the fuselage, and the locking tongue is self-locking when it is embedded in the notch; the application unfolds and embeds multiple locking tongues at the tail into the notch outside the fuselage, and unfolds the locking tongue by self-locking to increase the flight distance of the UAV, however, in some cases, such as when the UAV is in a high-speed rotation state, the locking tongue may be separated from the fitting state with the notch of the fuselage due to the centripetal force or centrifugal force generated during the rotation, thereby causing the UAV flight stability to be weakened and the reliability to be poor. Summary of the invention

[0004] In response to the above-mentioned problems, the present invention aims to provide a foldable tail device for an unmanned aerial vehicle, which drives a plurality of extension rods to extend along the circumference of a shell body through a plurality of compression springs, and cooperates with the arc-shaped side panels on both sides of the extension rods to form a tail structure, and combines with a plurality of sliding rod arc blocks to provide the unmanned aerial vehicle with stable flight performance, and has the advantages of simple structure, easy use and high reliability.

[0005] The main idea of ​​the technical solution adopted by the present invention is: through the action of compression springs on both sides of the extension rod, multiple extension rods are extended along the circumference of the shell, and at the same time, the arc-shaped side panels on both sides of the extension rod connected by torsion springs are unfolded to form a tail structure. In addition, the sliding of the extension rod drives the central block to move, and the multiple sliding rod arc blocks are pushed out of the shell, providing stable flight performance for the UAV.

[0006] In order to achieve the above object, the technical solution adopted by the present invention is as follows: A foldable tail device for an unmanned aerial vehicle comprises a shell, a center block is arranged in the middle of the shell, a plurality of extension rods are arranged in the shell for elastic sliding through a first spring, an end of the extension rod close to the center block is rotatably connected to the center block through a connecting rod, arc-shaped side plates are arranged on both sides of the extension rod away from the center block for elastic rotation through a torsion spring, and a plurality of slide rod arc blocks are also arranged in the shell for elastic sliding through a second spring; the extension rod can be extended out of the shell by the elastic force of the first spring, and the arc-shaped side plates on both sides are pushed out by the torsion spring, and the slide rod arc blocks are pushed out along the shell by the sliding of the center block, so as to form a stable tail structure.

[0007] Based on the above technical solution, further, in the shell, each extension rod and each sliding rod arc block are arranged alternately.

[0008] Based on the above technical solution, further, the angle between each extending rod is 90°, and the angle between each sliding rod arc block is 90°; that is, the angle between each extending rod and the adjacent sliding rod arc block is 45°, so as to be evenly distributed along the circumference of the shell, providing stable flight performance for the UAV.

[0009] Based on the above technical solution, further, after the arcuate side panel is unfolded under the action of the torsion spring, the angle between the arcuate side panel and the extension rod is 90°; that is, under the elastic force of the torsion spring, the arcuate side panel can reach a mutually perpendicular state with the extension rod.

[0010] Based on the above technical solution, further, a back cover is provided on one side of the shell; the back cover can protect various structures inside the shell.

[0011] Based on the above technical solution, further, a through hole matching with the center block is opened at the center of the shell; when the center block slides and fits with the through hole, it can provide a certain friction force for the center block to make the tail wing structure more stable.

[0012] A drone comprises a body, a folding tail device of the drone is fixed at the tail of the body, a communication system is provided at the front of the body, and a power system, a steering gear system, a battery system, an optoelectronic system, a damage system and a launch system are arranged inside the body in order from the front to the tail.

[0013] Based on the above technical solution, further, the communication system is used to synchronize the position and heading of the UAV, the power system is used to drive the UAV to operate; the servo system is used for attitude and motion control of the UAV; the battery system is used to provide working energy for the UAV; the optoelectronic system is used to collect data such as pictures or positions of the detected objects; the damage system is used to perform damage missions; and the launch system is used to propel the UAV to a designated area.

[0014] Based on the above technical solution, further, when the UAV is not launched, the extension rod, the arc-shaped side panel and the slide rod arc block in the shell are all in a retracted state; after launching, the extension rod is extended along the shell, the arc-shaped side panel is unfolded, and the slide rod arc block is synchronously extended along the shell.

[0015] A foldable tail device of a drone or a method for using the drone comprises the following steps: S1. Place the UAV as a whole on the mortar launch platform, and launch the UAV to the designated mission area in conjunction with the launch system; S2. After the UAV is launched, the multiple extension rods extend out of the shell synchronously under the action of elastic force, and drive the central block to move, pushing the multiple sliding rod arc blocks outward along the shell, and at the same time, the arc-shaped side panels on both sides of the extension rods unfold under the action of elastic force to form the tail structure of the UAV; S3. During the flight of the UAV, the position and heading of the UAV are synchronized through the communication system, the UAV is driven by the power system, the attitude and movement of the UAV are controlled by the steering gear system, the UAV is provided with working energy by the battery system, the image or position of the detected object and other data are collected through the optoelectronic system, and the damage mission is performed by the damage system.

[0016] The beneficial effects of the present invention are: 1. By evenly distributing a plurality of extension rods along the circumference in the shell, and distributing a plurality of arc-shaped side panels on both sides of the extension rods, and pushing a plurality of sliding rod arc-shaped blocks to extend along the shell in combination with the central block, the main part of the tail wing of the UAV is formed by the extension rods and the arc-shaped side panels, and in combination with the plurality of extended sliding rod arc-shaped blocks, stable flight performance is provided for the tail of the UAV, which helps to improve the flight performance and combat effect of the UAV, and can better adapt to complex environmental conditions, such as strong winds, turbulence, etc. Compared with the existing self-locking structure formed by interlocking, the present invention can make the flight state of the UAV more stable and more reliable.

[0017] 2. By designing multiple first spring-driven extension rods, the extension rods can be automatically extended after the drone is launched, and the arc-shaped side panels can be automatically unfolded through the torsion springs to form a tail structure. At the same time, the sliding of the extension rods can drive the center block to slide close to the center of the shell, push out the multiple sliding rod arc blocks, and at the same time make the center block fit with the through hole in the middle of the shell, further increasing the overall stability of the tail structure through the action of friction, so that the present invention has the advantage of being easy to use.

[0018] 3. The foldable tail wing device of the present invention is designed based on a drone as a whole, has a simple structure, and is easy to produce. Moreover, the device as a whole does not require a power supply structure to unfold the tail wing, thereby improving the scope of application of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 is a schematic diagram of the three-dimensional structure of the foldable tail device in an unfolded state; Figure 2 is a schematic diagram of the three-dimensional structure inside the shell when the foldable tail device is in the unfolded state; Figure 3 It is a schematic diagram of the three-dimensional structure from the back perspective when the foldable tail device is in the unfolded state; Figure 4 is a schematic diagram of the three-dimensional structure of the foldable tail device in a retracted state; Figure 5 is a schematic diagram of the three-dimensional structure inside the shell when the foldable tail device is in a retracted state; Figure 6 for Figure 2 A local detail view at point A; Figure 7 for Figure 5 A local detail view at B; Figure 8 is a side view of the interior of the housing when the foldable tail device is in the unfolded state; Fig. 9 It is a cross-sectional view of the extended rod; Fig.10 It is a schematic diagram of the three-dimensional structure of the shell part in a cutaway state; Fig.11 Schematic diagram of the three-dimensional structure of the sliding rod arc block; Fig.12 This is a schematic diagram of the three-dimensional structure of the UAV; Fig.13 This is a schematic diagram of the internal three-dimensional structure of the drone; Fig.14 This is a model diagram of a foldable tail device; Fig.15 This is a model diagram of a drone.

[0020] Among them: 1. Shell; 101. Extension rod slide groove; 102. Slide rod arc block slide groove; 2. Center block; 3. Extension rod; 4. Arc-shaped side plate; 5. Slide rod arc block; 6. First spring; 7. Connecting rod; 8. Torsion spring; 9. Second spring; 10. Back cover; 11. Body; 12. Communication system; 13. Power system; 14. Servo system; 15. Battery system; 16. Optoelectronic system; 17. Destruction system; 18. Launch system. DETAILED DESCRIPTION

[0021] In order to make the purpose, technical solution and advantages of the embodiments of the present application clearer, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, rather than all the embodiments. The components of the embodiments of the present application described and shown in the drawings here can be arranged and designed in various different configurations.

[0022] The inventors have found that, among the numerous drone applications, applying drones to mortar platforms is an innovation and attempt, as well as a research and expansion of technical applications, which can improve the comprehensive combat capability of weapons; the engineering application of mortar-launched drones will bring considerable benefits to the application units, and can also improve the comprehensive combat effectiveness of my country's drone platforms; the high and low pressure launch technology of mortar-launched drones can give full play to the portability of mortars, improve the deployment efficiency of drones, and extend the combat time of drones, and its portability enables it to be used on a large scale in urban combat; however, in the existing gun-launched drone tail device, in some cases, such as when the drone is in a high-speed rotation state, the lock tongue may be out of the engagement state with the fuselage gap due to the centripetal force or centrifugal force generated during the rotation, thereby causing the drone's flight stability to be weakened and the reliability to be poor.

[0023] Based on the above findings, the present application proposes a folding tail device for an unmanned aerial vehicle. Through the action of compression springs on both sides of the extension rod, multiple extension rods are extended along the circumference of the shell. At the same time, the arc-shaped side panels on both sides of the extension rod connected by torsion springs unfold to form a tail structure. In addition, the sliding of the extension rod drives the center block to move and pushes the multiple sliding rod arc blocks out of the shell, providing the unmanned aerial vehicle with stable flight performance. It has the advantages of simple structure, easy use and high reliability.

[0024] See also Figure 1-Figure 5 ,as well as Fig.14 The present application discloses a foldable tail device for a drone, comprising a housing 1, referring to Fig.10The shell 1 is a flat cylindrical structure as a whole, and its overall material should be selected from an alloy material with high strength. A through hole is opened at the center, and the side wall of the through hole has a certain inclination and can match the side wall of the center block 2 located in the middle of the shell 1. In the embodiment of the present invention, the center block 2 is a truncated cone structure with a certain inclination of the side wall, see Figure 3 as well as Figure 8 , that is, the central block 2 can move along the middle of the shell 1 until the bottom of the central block 2 and the bottom of the shell 1 are located on the same plane; Located in the housing 1, four extension rod sliding grooves 101 are evenly distributed along the circumference, and the extension rod 3 is slidably arranged in the extension rod sliding groove 101. The extension rod 3 is a cylindrical structure as a whole. The extension rod 3 is located on both sides of one end of the extension rod 3 close to the center of the housing 1. The stop block structure that can prevent the extension rod 3 from rotating is fixed, and the middle part of the extension rod sliding groove 101 is provided with a stop slot structure that matches the stop block structure. At the same time, refer to Figure 6 as well as Figure 7 , a first spring 6 is fixedly arranged between the limit block structure on both sides of the extension rod 3 and the limit groove structure, that is, the extension rod 3 can be extended to the outside of the housing 1 along the extension rod slide groove 101 under the elastic force of the first spring 6; See also Fig. 9 , the two sides of the extension rod 3 away from the center of the housing 1 are also rotatably mounted with two arc-shaped side plates 4 by means of a rotating shaft, and a torsion spring 8 is also sleeved on the rotating shaft, that is, the arc-shaped side plates 4 can be rotated and unfolded along the two sides of the extension rod 3 by the elastic force of the torsion spring 8, thereby forming a preliminary tail wing structure in combination with the extension rod 3; The extension rod 3 is close to one end of the center of the shell 1, and a mounting seat structure is provided in the middle of the limit block structure on both sides. At the same time, a plurality of mounting seat structures are evenly distributed on the circumference of the center block 2. A connecting rod 7 with through holes at both ends is used to be respectively sleeved on the extension rod 3 and the mounting seat structure on the center block 2, so that when the four extension rods 3 slide along the extension rod slide groove 101, they can synchronously drive the center block 2 to move along the through hole at the center of the shell 1; In the housing 1, four sliding rod arc block slots 102 are evenly distributed along the circumference and arranged in an interlaced manner with the extension rod slots 101, and a sliding rod arc block 5 is slidably arranged in the sliding rod arc block slots 102, see Fig.11The sliding rod arc block 5 includes a vertical sliding rod structure and an arc structure that cooperates with the side wall of the shell 1. A limiting block structure is fixed on the sliding rod structure and away from the end of the arc structure. A second spring 9 is fixed between the limiting block structure and the arc block slide groove 102 and is sleeved on the sliding rod arc block 5. When the arc block slide groove 102 slides along the arc block slide groove 102 on the shell 1, it will cause a certain squeezing effect on the second spring 9. When the second spring 9 is in a normal relaxation state, the outer side of the arc structure of the sliding rod arc block 5 can be fit with the outer side wall of the shell 1; in some embodiments, a structure for guiding and limiting is also provided between the sliding rod arc block 5 and the arc block slide groove 102. For details, please refer to the limiting structure at the above-mentioned extension rod 3; In one embodiment of the present invention, when the extension rod 3 is retracted into the housing 1, the first springs 6 on both sides thereof are in a compressed state, and the arc-shaped side plates 4 on both sides of the other end of the extension rod 3 are also in a state of being retracted into the two sides of the extension rod 3, and the torsion spring 8 is in a tightened state. At this time, the second spring 9 is in a normal relaxation state, and the outermost side of the arc-shaped structure of the sliding rod arc block 5 forms a complete arc surface with the side wall of the housing 1, and its innermost end extends into the through hole at the center of the housing 1. At this time, the foldable tail device as a whole can be regarded as an unfolded state, that is, the UAV as a whole is in a state to be launched; When the UAV is launched, the first spring 6 quickly resets under the action of its own elastic force, pushing the four extension rods 3 out of the shell 1, and the arc-shaped side panels 4 unfold along both sides of the extension rods 3 under the torsion of the torsion spring 8. At the same time, the extension of the extension rod 3 can drive the center block 2 to move along the through hole in the middle of the shell 1, and the four sliding rod arc blocks 5 are synchronously pushed out along the shell 1 through the center block 2 until the center block 2 fits with the side wall of the through hole in the middle of the shell 1. At this time, one end of the center block 2 forms a complete plane with one side of the shell 1, indicating that the foldable displacement device is fully unfolded. Through the four extension rods 3 and the arc-shaped side panels 4 on both sides thereof, combined with the four sliding rod arc blocks 5, stable flight performance is provided for the UAV as a whole.

[0025] In some embodiments, the angle between the four extension rods 3 is 90°, and the angle between each sliding rod arc block 5 is 90°, then the angle between each extension rod 3 and its two adjacent sliding rod arc blocks 5 is 45°, that is, all the extension rods 3 and the sliding rod arc blocks 5 divide the entire shell 1 into eight uniform structures. At the same time, after the arc-shaped side panels 4 are unfolded under the torsion of the torsion spring 8, they can form a mutually perpendicular state with the extension rod 3, that is, the angle between them and the extension rod 3 is 90°. Then, when the extension rod 3 and the sliding rod arc block 5 are extended, and the arc-shaped side panels 4 are unfolded, the airflow passing through the drone body and tail can be made smoother, thereby making the flight state of the drone more stable.

[0026] In some embodiments, when the UAV is in a rotating state, due to the centrifugal force generated by the rotation, the extension rod 3 and the sliding rod arc block 5 tend to move toward the outside of the shell 1 under the action of the centrifugal force. At this time, the center block 2 is tightly attached to the through hole in the middle of the shell 1, and a certain pulling force can be provided to the center block 2 through the extension rod 3 and the sliding rod arc block 5, which is equivalent to strengthening the friction effect between the center block 2 and the center of the shell 1. At the same time, under the limiting action of the centrifugal force and the torsion spring 8, the arc side panels 4 are tightly attached to the two sides of the extension rod 3 in a state perpendicular to the extension rod 3, thereby making the device as a whole more stable, that is, the folding tail device of the present invention can provide a stronger stabilizing effect when the UAV is in a rotating state.

[0027] In some embodiments, a back cover 10 is fixed on one side of the shell 1, that is, the side of the shell 1 close to the center block 2, by snapping or the like. The cross-sectional area of ​​the back cover 10 is the same as that of the shell 1, that is, the back cover 10 can completely cover the side of the shell 1 where the center block 2 is provided, so as to provide good protection for the device as a whole.

[0028] See also Fig.12 , Fig.13 as well as Fig.15 A drone including the foldable tail device of the above-mentioned drone includes a body 11, and the tail of the body 11 fixes the shell 1 away from the center block 2 or the side of the back cover 10 by means of snap connection or the like. In an embodiment of the present invention, the body 11 as a whole is matched with the size of the shell 1 or the back cover 10. In actual application, the structural dimensions of each structure in the foldable tail device can be adjusted according to the actual size of the drone.

[0029] The front part of the body 11 is provided with a communication system 12, which can synchronize or adjust the position and route of the UAV in practical applications in combination with external equipment such as a ground control center; In some embodiments, the body 11 is provided with a power system 13, a steering gear system 14, a battery system 15, an optoelectronic system 16, a damage system 17 and a launch system 18 arranged in order from the front to the rear. The above-mentioned system structures can be regarded as being connected to each other along the cylindrical shaft through hole in the center of the body 11. In practical applications, the power system 13 can drive the UAV as a whole to operate in conjunction with equipment such as a ground control center. The steering gear system 14 can control and adjust the posture and movement of the UAV under the control of equipment such as a ground control center. The battery system 15 can provide sufficient working energy for the UAV. The optoelectronic system 16 can be used to collect data on the image and position of the reconnaissance object when the UAV is flying, and transmit it to the control center, etc. The damage system 17 is equipped with contents with a damage effect, which can enable the UAV to perform a damage mission under the control of the control center. The launch system 18 is used to cooperate with a launch platform, such as a mortar launch platform, to launch the UAV as a whole to a designated mission area. Regarding the specific structure inside the body 11, reference can be made to existing gun-fired UAV products.

[0030] A foldable tail device of a drone or a method for using the drone comprises the following steps: S1. The UAV is placed in a mortar launch platform as a whole, and is launched to a designated mission area through the mortar platform combined with a launch system 18; S2. After the UAV is launched, the multi-channel extension rod 3 is synchronously extended to the outside of the shell 1 under the elastic force of the first spring 6, and drives the central block 2 to move toward the shell 1, pushing the multi-channel sliding rod arc block 5 outward along the shell 1, and at the same time, the arc-shaped side plates 4 on both sides of the extension rod 3 are unfolded under the elastic force of the torsion spring 8 to form the tail structure of the UAV; S3. During the flight of the UAV, the position and heading of the UAV are synchronized through the communication system 12, the UAV is driven by the power system 13, the posture and movement of the UAV are controlled by the steering gear system 14, the working energy is provided for the UAV by the battery system 15, the image or position and other data of the detected object are collected by the optoelectronic system 16, and the damage mission is executed by the damage system 17.

[0031] Practical application cases The foldable tail device is installed on the tail of the UAV body 11, and the UAV is placed on the mortar launch platform. After the mission position is determined, the position information is input into the launch system 18, and the UAV is launched through the mortar launch platform; After the drone is launched, the multiple extension rods 3 in the shell 1 at the tail are extended under the elastic force of the first spring 6, and the arc-shaped side plates 4 on both sides of each extension rod 3 are unfolded under the elastic force of the torsion spring 8. When the extension rods 3 move, they can drive the central block 2 to move toward the through hole in the middle of the shell 1 and push out the multiple sliding rod arc blocks 5 to form a complete tail structure; When the UAV is flying, the power system 13 and the battery system 15 maintain the operation of the UAV, the communication system 12 synchronizes the position and heading of the UAV, and the flight attitude and motion state of the UAV are adjusted in combination with the steering gear system 14. When reaching or approaching the mission location, the optoelectronic system 16 collects data such as the image or location of the mission target, and when necessary, the communication system 17 is used to carry out a destructive attack on the target.

[0032] The above shows and describes the basic principles, main features and advantages of the present invention. It should be understood by those skilled in the art that the present invention is not limited to the above embodiments, and the above embodiments and descriptions are only for explaining the principles of the present invention. Without departing from the spirit and scope of the present invention, the present invention may have various changes and improvements, which fall within the scope of the present invention to be protected. The scope of protection of the present invention is defined by the attached claims and their equivalents.

Claims

1. A foldable tail device for an unmanned aerial vehicle, comprising a housing (1) and a center block (2), characterized in that: A plurality of extension rods (3) are slidably arranged in the shell (1), one end of the extension rod (3) is rotatably connected to the central block (2), and arc-shaped side plates (4) are elastically rotatably arranged on both sides of the other end of the extension rod (3). A plurality of sliding rod arc blocks (5) are also elastically slidably arranged in the shell (1).

2. The foldable tail device of a drone according to claim 1, characterized in that: In the housing (1), each extension rod (3) and each slide rod arc block (5) are arranged in an interlaced manner.

3. The foldable tail device of a drone according to claim 1, characterized in that: The included angle between each of the extending rods (3) is 90°, and the included angle between each of the sliding rod arc blocks (5) is 90°.

4. The foldable tail device of a drone according to claim 1, characterized in that: When the arc-shaped side plate (4) is unfolded, the angle between it and the extension rod (3) is 90°.

5. The foldable tail device of a drone according to claim 1, characterized in that: A rear cover (10) is also provided on one side of the housing (1).

6. The foldable tail device of a drone according to claim 1, characterized in that: A through hole matching the center block (2) is provided at the center of the shell (1).

7. An unmanned aerial vehicle, comprising a body (11), wherein a foldable tail wing device of an unmanned aerial vehicle according to any one of claims 1 to 6 is fixed to the tail of the body (11), characterized in that: The forward portion of the machine body (11) is provided with a communication system (12), and the interior of the machine body (11) is arranged in order from the forward portion to the rear portion with a power system (13), a steering gear system (14), a battery system (15), an optoelectronic system (16), a destruction system (17), and a launch system (18).

8. The drone according to claim 7, characterized in that: The communication system (12) is used to synchronize the position and heading of the UAV; the power system (13) is used to drive the UAV to operate; the steering gear system (14) is used to control the attitude and motion of the UAV; the battery system (15) is used to provide working energy for the UAV; the optoelectronic system (16) is used to collect data such as images or positions of the detected object; the damage system (17) is used to perform damage tasks; and the launch system (18) is used to propel the UAV to a designated area.

9. The drone according to claim 7, characterized in that: When the drone is not launched, the extension rod (3), the arc-shaped side plate (4) and the slide rod arc-shaped block (5) in the housing (1) are all in a retracted state.

10. A foldable tail device of a drone or a method for using a drone according to any one of claims 1 to 9, comprising the following steps: S1, placing the UAV as a whole in the mortar launch platform, and launching the UAV to a designated mission area in combination with a launch system (18); S2. After the UAV is launched, the multiple extension rods (3) are synchronously extended outward from the housing (1) under the action of elastic force, and drive the central block (2) to move, pushing the multiple sliding rod arc blocks (5) outward along the housing (1), and at the same time, the arc-shaped side panels (4) on both sides of the extension rods (3) are unfolded under the action of elastic force to form the tail wing structure of the UAV; S3. During the flight of the UAV, the position and heading of the UAV are synchronized through the communication system (12), the UAV is driven by the power system (13), the attitude and movement of the UAV are controlled by the steering gear system (14), the working energy is provided to the UAV by the battery system (15), the image or position data of the detected object is collected by the optoelectronic system (16), and the damage mission is executed by the damage system (17).

Images