Ejection unmanned aerial vehicle structure

Abstract

The utility model relates to the field of unmanned aerial vehicles, in particular to a catapulting unmanned aerial vehicle structure which comprises a catapulting cavity and an unmanned aerial vehicle, and the catapulting cavity comprises a gun barrel, a guide rail and a catapulting plate. The unmanned aerial vehicle comprises a shell, a folding wing assembly and a holder assembly, the shell comprises an upper cavity and a lower cavity, and a plurality of concave positions and notches are correspondingly distributed in the side wall of the upper cavity and the side wall of the lower cavity; the problems that an unmanned aerial vehicle is prone to overturning and inclining in the take-off process, and ejection energy storage is insufficient due to the fact that the folding space of rotor blades of the unmanned aerial vehicle is too large, or an ejection device matched with the unmanned aerial vehicle is too large in specification and not easy to carry are solved. The energy consumption of the unmanned aerial vehicle in the takeoff stage is saved; the ejection direction of the unmanned aerial vehicle is limited; the overall layout of the unmanned aerial vehicle is compact and stable; and the size of the ejection cavity matched with the unmanned aerial vehicle shell is reduced, and the effect of improving the structural stability is achieved while the structural weight is reduced.

Description

Technical Field

[0001] The utility model relates to the field of unmanned aerial vehicles, and more specifically, to a ejection unmanned aerial vehicle structure. Background Art

[0002] Rotary-wing UAVs are being introduced into more and more fields because they can hover and perform various special tasks such as fixed-point shooting and fixed-point water spraying and firefighting. However, compared with fixed-wing UAVs, rotary-wing UAVs have short flight time and fast power consumption, which are defects that are difficult to get rid of. As a type of UAV that takes off and lands on land, gun-launched UAVs are mostly used in the military field. In military catapult UAVs, in order to perform reconnaissance, surveillance, communication, anti-submarine, electronic interference, damage assessment, precision strike, communication relay, target indication and other combat tasks above the target area, they can overcome the defects of the use of traditional rotary-wing UAVs, achieve efficient and accurate launch to the target area, adapt to various forms of delivery, and have the effect of long-term air patrol flights.

[0003] In order to combine the advantages of military artillery-launched drones, catapult-launched rotor drones came into being. Catapult-launched rotor drones do not need to consume electricity during the take-off phase. They rely on a carrying system to carry the rotor drone to a specific location and then separate it, or rely on the energy storage of the catapult device to unhook and launch the rotor drone into the air during the catapult process. The launch site of the catapult-launched rotor drone is not restricted by land conditions and it is easy to carry, making its application areas more extensive.

[0004] During the catapult takeoff phase, the thrust line of the rocket of current catapult drones is prone to misalignment with the center of gravity of the drone, which can cause the drone to flip or tilt after being ejected into the air. At the same time, in order to match the storage of the rotor blades of the catapult drone, the catapult device is usually longer than the overall length of the drone. Therefore, the folding method of the rotor blades will directly affect the matching length of the catapult device.

[0005] If the rotor blades are still too long after being stored, not only will the limited ejection space in the ejection device be over-squeezed, resulting in insufficient ejection energy storage for the drone, but the drone and ejection device will also be inconvenient to carry because they are too long, especially in mountain rescue, where rescue vehicles or aircraft cannot reach the disaster area quickly and directly. Rescuers can carry ejection drones near the entrance to the disaster area, and then launch the drones at any location to take fixed-point photos of the overall appearance of the disaster area to collect information, helping rescuers to make decisions and deployments quickly. Since the rescuers' personal equipment also includes a variety of medical emergency supplies, the weight and size of the ejection drone cannot exceed the rescuers' long-term load-bearing capacity, and its portability is crucial. How to overcome these defects is a technical problem that needs to be solved urgently in this field. Utility Model Content

[0006] The utility model aims to overcome at least one defect (shortcoming) of the above-mentioned prior art and provide a catapult UAV structure for solving the problem that the UAV is prone to flipping and tilting during take-off, and the problem that the folding space of the UAV's rotor blades is too large, resulting in insufficient catapult energy storage or the specifications of the catapult device adapted to the UAV are too large and difficult to carry.

[0007] The technical solution adopted by the utility model is a kind of ejection UAV structure, which includes an ejection chamber and a UAV placed therein, the ejection chamber includes a barrel, a guide rail arranged on the inner wall of the barrel, and a pop-up plate ejected along the guide rail, and the pop-up plate is connected to the UAV; the UAV includes a shell, a folding wing assembly and a gimbal assembly, the shell includes an upper cavity and a lower cavity communicated by a connecting ring, the lower surface of the upper cavity, the upper surface of the lower cavity and the connecting ring form an open accommodating space, the side wall of the upper cavity and the side wall of the lower cavity are correspondingly distributed with a plurality of recesses and notches, each group of corresponding recesses and notches is used to accommodate the folding wing assembly, and the gimbal assembly is arranged below the lower cavity.

[0008] It is beneficial to convert the stored energy in the ejection chamber into kinetic energy for launching the UAV to a specific height, saving the energy consumption of the UAV during the take-off phase and extending the flight time of the UAV to perform the mission; the ejection space of the UAV is limited by the barrel, and the ejection direction and path of the UAV are limited by the cooperation of the ejection plate and the guide rail; it is beneficial to reduce the volume of the UAV after the wings are stored by the folding wing assembly, thereby facilitating carrying and reducing the space occupied by the wings in the ejection chamber, thereby increasing the energy storage size of the ejection chamber; it is beneficial to improve the shooting quality of the ejection UAV when the airflow is unstable during mountain rescue through the gimbal assembly; it is beneficial to reduce the weight and volume of the overall structure through the open accommodation space; it is beneficial to realize the compactness and stability of the overall layout of the UAV through the upper and lower cavities that are longitudinally distributed but connected up and down; it is beneficial to store the folding wings in the side wall that does not exceed the UAV through the recesses and notches, thereby reducing the size of the ejection chamber adapted to the UAV shell, and facilitating carrying of the ejection chamber and the UAV.

[0009] Furthermore, the folding wing assembly includes a plurality of folding wing units, each folding wing unit includes a folding seat, an arm and a blade, the folding seat is arranged in the recess, the arm is horizontally unfolded or vertically folded around the folding seat, and the blade includes two blades, which are stored in the same direction under the arm or unfolded in opposite directions at the end of the arm.

[0010] It is beneficial to connect the machine arm to the shell through the folding seat, and the machine arm can be horizontally unfolded or vertically folded through the folding seat, which is convenient for the storage of the folding wing assembly. The blades are stored in the same direction to achieve the blades to be completely stored under the machine arm without occupying additional storage space, thereby reducing the volume of the UAV and the matching ejection cavity, making it convenient to carry around. The reverse unfolding of the blades enables the UAV to rotate quickly after being launched into the air, thereby shortening the control reaction time of the UAV.

[0011] Furthermore, the folding seat includes a fixing part, a folding part and a locking part, the side wall of the fixing part is flush with the side wall of the upper cavity, the folding part is used to connect the machine arm to the fixing part, and the locking part is located below the folding part and locks with the machine arm; when the locking part is unlocked, the folding part is retracted into the fixing part and the machine arm is horizontally unfolded; when the locking part is locked, the folding part protrudes out of the fixing part and the machine arm is vertically folded.

[0012] It is beneficial to realize the connection between the folding part and the shell through the fixing part, and provide a stable supporting force for the folding part; the folding structure for realizing the folding of the arm is hidden in the concave position of the upper cavity through the folding part, so as to avoid the folding structure being exposed outside the shell when the arm is horizontally extended, affecting the flight resistance and stability of the UAV; the stored arm is locked by the locking part, so as to avoid the arm being accidentally extended during the storage process. At the same time, the setting of the locking part makes the unlocking of the arm safely isolated, so as to avoid the arm extending after the UAV is hit in the ejection cavity, causing the arm to be scratched in the ejection cavity, affecting the ejection effect of the UAV and the service life of the UAV.

[0013] Furthermore, the top cover of the upper cavity includes a connecting portion and a protruding portion, the connecting portion matches the upper edge of the upper cavity, and the protruding portion is a protrusion formed below the connecting portion and is used to place the battery unit protruding above the connecting portion.

[0014] It is beneficial to form an upwardly protruding closed surface through the battery unit protruding above the connecting part and the upper edge of the upper cavity, thereby reducing the instantaneous wind resistance of the drone during the ejection process; the connecting part provides an installation position for the battery unit, so that the center of gravity of the battery unit is located in the upper cavity and is kept on the same center line with the center of gravity of the entire drone, thereby avoiding deflection, tilting and other problems caused by the deviation of the center of gravity during the ejection or flight of the drone.

[0015] Furthermore, the bottom cover of the lower cavity includes a groove portion and a hollow portion, the groove portion matches the lower edge of the lower cavity, and the center of the hollow portion overlaps with the center of the connecting ring.

[0016] It is beneficial to form a closed lower cavity by tilting the upper surface and the groove portion of the bottom cover, so that the lower cavity provides a larger accommodating space while reducing the volume of the lower cavity. The hollow portion of the bottom cover reduces the weight of the lower cavity, limits the installation center of gravity of the gimbal assembly to be on the same center line with the center of gravity of the drone, and provides wiring space for the components in the gimbal assembly.

[0017] Furthermore, the UAV also includes a main board, an electric adjustment board, a GPS module and an antenna arranged in the upper cavity, the main board includes a hollow position connected between the connecting part and the upper edge of the upper cavity, the GPS module is connected to the hollow position of the main board, the electric adjustment board is connected to the main board, and the antenna is connected between the main board and the connecting ring.

[0018] It is beneficial to shorten the reaction time of sending and receiving commands to control the folding wing assembly by connecting the main board between the top cover and the upper edge of the upper cavity; shorten the reaction time of the folding wing assembly by installing the electric adjustment board on the main board; improve the positioning accuracy by connecting the GPS module in the hollow position closest to the center of the drone, and at the same time, the distance from the upper cavity and the lower cavity is very close, which speeds up the reaction speed between the gimbal PCB board in the lower cavity and the main board in the upper cavity; and avoid the exposure of the antenna affecting the pop-up flight wind resistance of the drone by setting the antenna between the connecting ring and the main board.

[0019] Furthermore, the gimbal assembly includes a gimbal camera, a gimbal fixing, a gimbal PCB board, an optical flow module and a ranging module. The gimbal camera is connected to the gimbal fixing in the lower cavity through the hollow portion, and the gimbal PCB board, the optical flow module and the ranging module are arranged in the groove portion.

[0020] It is beneficial to ensure that the shooting angle of the gimbal camera arranged under the lower cavity is not blocked, and it is within the outer diameter of the drone shell and does not affect the wind resistance of the drone during the upward pop-up take-off stage; it is beneficial to avoid the stability of image processing being affected by the gimbal PCB board, optical flow module and ranging module arranged in the lower cavity.

[0021] Furthermore, it also includes a tripod, which is arranged below the lower cavity, and the length of the tripod is greater than the length of the arm extending out of the recess.

[0022] The tripod is conducive to realizing a support frame when the ejection of the drone fails, thereby expanding the application flexibility of the ejection drone; the length of the tripod is greater than the length of the lower cavity when the arm is stored in the recess, thereby preventing the end of the arm from being located at the bottom of the drone in the storage state of the folding wing assembly, causing wear of the arm and the blade, and affecting the service life of the drone.

[0023] Furthermore, the ejection chamber also includes a control switch, and the control switch is used to control the ejection or resetting of the ejection plate.

[0024] It is beneficial to simplify the internal structure of the ejection cavity, expand the ejection space in the ejection cavity, reduce the weight of the ejection cavity, and facilitate the carry-on of the ejection UAV through the manual control switch.

[0025] Furthermore, the inner diameter of the ejection cavity is greater than or equal to the outer diameter of the shell, the ejection cavity includes multiple drones, the guide rail includes an ejection track and a delivery track, the ejection track is used to eject the drone, and the delivery track is used to continuously deliver multiple drones to the ejection track.

[0026] It is beneficial to use the outer diameter of the shell as the upper limit of the outer diameter of the entire UAV to avoid obstruction of the UAV during the ejection of the ejection cavity; it is beneficial to achieve continuous launch of the ejection cavity through the separation of the ejection track and the delivery track, thereby accelerating the ejection efficiency of the ejection UAV.

[0027] Compared with the prior art, the utility model has the following beneficial effects: by converting the stored energy in the ejection chamber into kinetic energy for launching the UAV to a specific height, the energy consumption of the UAV during the take-off phase is saved, and the flight time of the UAV to perform the mission is extended; and the ejection direction and path of the UAV are limited; the volume of the UAV is reduced after the wings are stored by the folding wing assembly, which is convenient for carrying and reduces the space occupied by the wings in the ejection chamber, thereby increasing the energy storage size of the ejection chamber; the overall layout of the UAV is compact and stable through the upper and lower cavities that are longitudinally distributed but connected up and down; the folding wings are stored in the side wall of the UAV by the recesses and notches, thereby reducing the size of the ejection chamber that matches the UAV shell, which is conducive to carrying the ejection chamber and the UAV. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 It is an explosion diagram of the utility model.

[0029] Figure 2 The figure is a schematic diagram of the explosion of the UAV of the utility model.

[0030] Figure 3 It is a schematic diagram of the folding wing assembly of the utility model in a vertically folded state.

[0031] Figure 4 It is a schematic diagram of the folding wing assembly of the utility model in a horizontally unfolded state.

[0032] Description of the accompanying drawings: ejection chamber 10, barrel 110, guide rail 120, ejection plate 130, control switch 140, drone 20, shell 200, upper cavity 210, recess 211, top cover 212, lower cavity 220, notch 221, bottom cover 222, battery unit 230, main board 240, electric adjustment board 250, GPS module 260, antenna 270, folding wing assembly 300, folding seat 310, arm 320, blade 330, fixing part 311, folding part 312, locking part 313, gimbal assembly 400, gimbal camera 410, gimbal fixing part 420, gimbal PCB board 430, optical flow module 440, ranging module 450, tripod 600. DETAILED DESCRIPTION

[0033] The drawings of the present invention are only used for illustrative purposes and cannot be construed as limiting the present invention. In order to better illustrate the following embodiments, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product; for those skilled in the art, it is understandable that some well-known structures and their descriptions in the drawings may be omitted.

[0034] Example

[0035] like Figure 1-4 As shown, this embodiment provides a structure for ejecting a UAV 20, characterized in that it includes an ejection chamber 10 and a UAV 20 placed therein, wherein the ejection chamber 10 includes a barrel 110, a guide rail 120 provided on the inner wall of the barrel 110, and an ejection plate 130 ejected along the guide rail 120, wherein the ejection plate 130 is connected to the UAV 20; the UAV 20 includes a housing 200, a folding wing assembly 300, and a gimbal assembly 400, wherein the housing 200 includes a The upper cavity 210 and the lower cavity 220 are connected by a connecting ring, and the lower surface of the upper cavity 210, the upper surface of the lower cavity 220 and the connecting ring form an open accommodating space. The side walls of the upper cavity 210 and the side walls of the lower cavity 220 are correspondingly distributed with a plurality of recesses 211 and notches 221, and each group of corresponding recesses 211 and notches 221 is used to accommodate the folding wing assembly 300, and the gimbal assembly 400 is arranged below the lower cavity 220.

[0036] In this embodiment, the ejection chamber 10 is made of a high-temperature resistant lightweight material, and is used to provide ejection energy for the UAV 20 along a defined ejection path. The barrel 110 is a cavity with a single-side opening, and a spring and an ejection plate 130 are fixed to the base of the barrel 110. The UAV 20 is ejected from the opening of the barrel 110 under the push of the ejection plate 130.

[0037] In this embodiment, the side wall of the shell 200 is cylindrical as a whole, and the outer diameter of the cylinder is smaller than the inner diameter of the barrel 110, which is convenient for the UAV 20 to slide in and out of the ejection chamber 10; the shell 200 includes an upper cavity 210 and a lower cavity 220, and the upper surface of the upper cavity 210 is a battery unit 230 with a stepped protrusion and a round top cover 212; the side wall of the upper cavity 210 is a cylindrical wall with four recesses 211, and the four recesses 211 are used to install the folding wing assembly 300; the lower surface of the upper cavity 210 is an inclined surface, and the inclination angle is from the outside to the inside; the upper surface of the lower cavity 220 is an inclined surface, and the inclination angle is from the inside to the outside; the connecting ring is a cylindrical wall, Two inclined surfaces are used to connect the upper cavity 210 and the lower cavity 220; the open accommodating space can be embedded with a frustum-shaped reinforcement structure that fits the lower surface of the upper cavity 210 and the upper surface of the lower cavity 220; the side wall of the lower cavity 220 is a cylindrical wall with four notches 221, and the four notches 221 are used to accommodate the folding wing assembly 300 vertically folded from the recess 211, and the notches 221 correspond to the recess 211 on the vertical plane; the lower surface of the lower cavity 220 is a bottom cover 222; the upper cavity 210 is installed with equipment for controlling the folding wing assembly 300 and the take-off and landing flight control of the drone 20; the lower cavity 220 is installed with equipment for controlling the gimbal assembly 400.

[0038] The folding wing assembly 300 includes a plurality of folding wing units, each of which includes a folding seat 310, an arm 320 and a blade 330. The folding seat 310 is disposed in the recess 211, and the arm 320 is horizontally unfolded or vertically folded around the folding seat 310. The blade 330 includes two blades, which are stored in the same direction under the arm 320 or unfolded in opposite directions at the end of the arm 320.

[0039] In this embodiment, the folding wing assembly 300 includes four folding wing units, and the folding wing unit includes a storage state and an unfolded state. The folding seat 310 is fixed on the side wall of the upper cavity 210, and the arm 320 is movably connected to the folding seat 310, and the blade 330 is located below the end of the arm 320; when the folding wing unit is in the storage state, the folding seat 310 and the arm 320 are vertically retracted, and the two blade tips of the blade 330 are retracted upward in the same direction; when the folding wing unit is in the unfolded state, the folding seat 310 and the arm 320 are horizontally unfolded, and the two blade tips of the blade 330 are unfolded outward in opposite directions.

[0040] The folding seat 310 includes a fixing member 311, a folding member 312 and a locking member 313. The side wall of the fixing member 311 is flush with the side wall of the upper cavity 210. The folding member 312 is used to connect the arm 320 to the fixing member 311. The locking member 313 is located below the folding member 312 and is locked with the arm 320. When the locking member 313 is unlocked, the folding member 312 is retracted into the fixing member 311, and the arm 320 is horizontally unfolded. When the locking member 313 is locked, the folding member 312 protrudes from the fixing member 311, and the arm 320 is vertically folded.

[0041] In this embodiment, the fixing member 311 is fixed on the side wall of the upper cavity 210, and the side wall of the fixing member 311 is flush with the side wall of the upper cavity 210. The fixing member 311 also includes a storage recess 211. The folding member 312 is connected to the storage recess 211. The arm 320 is folded into the storage recess 211 through the folding member 312 to prevent the arm 320 from protruding from the side wall of the upper cavity 210, thereby causing an obstacle to the sliding of the drone 20 in the ejection cavity 10. The folding member 312 is a one-way folding arm, and the folding angle range is 0-90°; the locking member 313 is also provided in the storage recess 211, and it is located below the folding member 312. It is a protruding buckle, which cooperates with the card groove on the inner surface of the arm 320 to achieve the locking of the arm 320.

[0042] The top cover 212 of the upper cavity 210 includes a connecting portion and a protruding portion, wherein the connecting portion matches the upper edge of the upper cavity 210 , and the protruding portion is a protrusion formed below the connecting portion for placing the battery unit 230 protruding above the connecting portion.

[0043] In this embodiment, the connecting portion of the top cover 212 is a circular surface, and its outer edge matches the upper edge of the upper cavity 210. The protruding portion of the top cover 212 is a cylindrical surface protruding downward for placing the battery cell 230. The battery cell 230 is a special shape with an upper circle below, matching the circular surface of the connecting portion and the cylindrical surface of the protruding portion.

[0044] The bottom cover 222 of the lower cavity 220 includes a groove portion and a hollow portion, the groove portion matches the lower edge of the lower cavity 220, and the center of the hollow portion overlaps with the center of the connecting ring.

[0045] In this embodiment, the bottom cover 222 of the lower cavity 220 is a circular surface, and its outer edge matches the lower edge of the lower cavity 220. The groove portion of the bottom cover 222 is a groove formed upward along the wall surface of the circular surface of the bottom cover 222, which is used to place components for processing images taken by the gimbal. The hollow portion of the bottom cover 222 is used to install the gimbal camera 410 in the gimbal assembly 400 suspended below the lower cavity 220.

[0046] The drone 20 also includes a main board 240, an electric adjustment board 250, a GPS module 260 and an antenna 270 arranged in the upper cavity 210. The main board 240 includes a hollow position connected between the connecting portion and the upper edge of the upper cavity 210. The GPS module 260 is connected to the hollow position of the main board 240. The electric adjustment board 250 is connected to the main board 240. The antenna 270 is connected between the main board 240 and the connecting ring.

[0047] In this embodiment, after the UAV 20 leaves the ejection cavity 10, the main board 240 automatically controls the locking piece 313 in the folding wing assembly 300 to be in an unlocked state, so that the arm 320 can be unfolded; the main board 240 is a hollow board, and the electric adjustment board 250 is stacked and installed on the main board 240 to control the rotation speed of the blade 330; the GPS module 260 is installed in the hollow position of the main board 240, and the antenna 270 is installed in the lower and upper cavities 210 of the main board 240. The electric adjustment board 250, the GPS module 260 and the antenna 270 are used to locate the flight path of the UAV 20; the installation position of each component in the upper cavity 210 greatly reduces the installation space, reduces the weight while ensuring the function of the UAV 20 to perform rescue missions, and increases the portability of disaster relief personnel.

[0048] The gimbal assembly 400 includes a gimbal camera 410, a gimbal fixing part 420311, a gimbal PCB board 430, an optical flow module 440 and a ranging module 450. The gimbal camera 410 is connected to the gimbal fixing part 420311 in the lower cavity 220 through the hollow part, and the gimbal PCB board 430, the optical flow module 440 and the ranging module 450 are arranged in the groove part.

[0049] In this embodiment, the gimbal assembly 400 is used to improve the shooting quality when performing disaster relief tasks, wherein the ranging module 450, the optical flow module 440 and the gimbal PCB board 430 are installed in the lower cavity 220, and the gimbal camera 410 passes through the hollow part of the bottom cover 222 of the lower cavity 220 and is suspended below the lower cavity 220, which can not only avoid the shooting angle of the gimbal camera 410 from being blocked, but also shorten the communication distance between each component and the gimbal camera 410, thereby ensuring the stability of image processing.

[0050] The device further includes a tripod 600 , which is disposed below the lower cavity 220 . The length of the tripod 600 is greater than the length of the arm 320 extending out of the notch 221 .

[0051] In this embodiment, when the arm 320 is vertically folded, it extends from the recessed position 211 to the recess 221, and its length exceeds the bottom cover 222 of the lower cavity 220. The length of the tripod 600 is greater than the length of the arm 320 extending from the recess 221, and is used to protect the gimbal assembly 400 installed under the bottom cover 222, especially when the ejection fails and the drone 20 falls directly before it is turned on and started flying. The tripod 600 is a buffer part movably connected to the bottom cover 222 of the lower cavity 220, protecting the gimbal camera 410 suspended below the lower cavity 220 from being damaged.

[0052] The ejection chamber 10 further includes a control switch 140 , and the control switch 140 is used to control the ejection or resetting of the ejection plate 130 .

[0053] In this embodiment, the control switch 140 is a manual switch. When the rescue personnel carry the ejection drone 20 to the entrance of the disaster area, they place the ejection chamber 10 on the ground and manually press the control switch 140. The drone 20 is ejected to a maximum altitude of H1 in the air by the thrust of the ejection plate 130. The altitude for automatically starting the flight is preset as H2 in the main board 240 of the drone 20. When the drone 20 detects that H1>H2, the locking member 313 in the folding seat 310 is automatically unlocked, the arm 320 is horizontally unfolded, and the blades 330 are reversed. The drone 20 starts to perform a flight mission, and the gimbal assembly 400 starts to perform a shooting mission. When the drone 20 detects that H1 is less than H2, the locking member 313 in the folding seat 310 is still in a locked state, the machine arm 320 is still vertically retracted, the blades 330 are still retracted in the same direction, the drone 20 and the gimbal assembly 400 are both in a shutdown state, and the tripod 600 acts as a buffer to protect the drone 20 that fails to be ejected from landing smoothly and protect the gimbal assembly 400 of the drone 20 from damage.

[0054] The inner diameter of the ejection cavity 10 is greater than or equal to the outer diameter of the shell 200. The ejection cavity 10 includes multiple drones 20. The guide rail 120 includes an ejection track and a delivery track. The ejection track is used to eject the drone 20, and the delivery track is used to continuously deliver multiple drones 20 to the ejection track.

[0055] In this embodiment, the inner diameter of the ejection cavity 10 can be determined according to the outer diameter of the shell 200 of the drone 20. When one ejection cavity 10 is used for drones 20 of multiple leap-level specifications, ejection cavities 10 with different inner diameters can be customized to match. When one ejection cavity 10 is used for drones 20 of multiple similar specifications, the inner diameter can be fine-tuned by adjusting the distance between the guide rail 120 and the inner wall of the barrel 110. In this embodiment, the drone 20 enters the ejection cavity 10 through the delivery track and then ejects through the ejection track, so as to realize the continuous launch of the drone 20.

[0056] Obviously, the above embodiments of the utility model are only examples for clearly explaining the technical solution of the utility model, and are not intended to limit the specific implementation methods of the utility model. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the claims of the utility model shall be included in the protection scope of the claims of the utility model.

Claims

1. A catapult drone structure, characterized in that: The invention comprises an ejection chamber and a UAV placed therein, wherein the ejection chamber comprises a barrel, a guide rail arranged on the inner wall of the barrel, and a pop-up plate popped out along the guide rail, wherein the pop-up plate is connected to the UAV; the UAV comprises a shell, a folding wing assembly and a gimbal assembly, wherein the shell comprises an upper cavity and a lower cavity communicated with each other through a connecting ring, wherein the lower surface of the upper cavity, the upper surface of the lower cavity and the connecting ring form an open accommodation space, wherein a plurality of concave positions and notches are correspondingly distributed on the side walls of the upper cavity and the side walls of the lower cavity, and each group of corresponding concave positions and notches is used to accommodate the folding wing assembly, and the gimbal assembly is arranged below the lower cavity.

2. The ejection drone structure according to claim 1, characterized in that: The folding wing assembly includes a plurality of folding wing units, each of which includes a folding seat, an arm and a blade. The folding seat is arranged in the recess, the arm is horizontally unfolded or vertically folded around the folding seat, and the blade includes two blades, which are stored in the same direction under the arm or unfolded in opposite directions at the end of the arm.

3. The ejection drone structure according to claim 2, characterized in that: The folding seat includes a fixing part, a folding part and a locking part. The side wall of the fixing part is flush with the side wall of the upper cavity. The folding part is used to connect the machine arm to the fixing part. The locking part is located below the folding part and is locked with the machine arm. When the locking part is unlocked, the folding part is retracted into the fixing part and the machine arm is horizontally unfolded. When the locking part is locked, the folding part protrudes out of the fixing part and the machine arm is vertically folded.

4. The ejection drone structure according to claim 1, characterized in that: The top cover of the upper cavity includes a connecting portion and a protruding portion, wherein the connecting portion matches the upper edge of the upper cavity, and the protruding portion is a protrusion formed below the connecting portion and is used to place the battery unit protruding above the connecting portion.

5. The ejection drone structure according to claim 2, characterized in that: The bottom cover of the lower cavity comprises a groove portion and a hollow portion, the groove portion matches the lower edge of the lower cavity, and the center of the hollow portion overlaps with the center of the connecting ring.

6. The ejection drone structure according to claim 4, characterized in that: The drone also includes a main board, an electric adjustment board, a GPS module and an antenna arranged in the upper cavity. The main board includes a hollow position connected between the connecting portion and the upper edge of the upper cavity. The GPS module is connected to the hollow position of the main board. The electric adjustment board is connected to the main board. The antenna is connected between the main board and the connecting ring.

7. The ejection drone structure according to claim 5, characterized in that: The gimbal assembly includes a gimbal camera, a gimbal fixing part, a gimbal PCB board, an optical flow module and a ranging module. The gimbal camera is connected to the gimbal fixing part in the lower cavity through the hollow part, and the gimbal PCB board, the optical flow module and the ranging module are arranged in the groove part.

8. The ejection drone structure according to claim 5, characterized in that: It also includes a tripod, which is arranged below the lower cavity, and the length of the tripod is greater than the length of the machine arm extending out of the recess.

9. A catapult drone structure according to any one of claims 1 to 8, characterized in that: The ejection chamber further comprises a control switch, and the control switch is used for controlling the ejection or resetting of the ejection plate.

10. The ejection drone structure according to any one of claims 1 to 8, characterized in that: The inner diameter of the ejection cavity is greater than or equal to the outer diameter of the shell, and the ejection cavity includes multiple drones. The guide rail includes an ejection track and a delivery track. The ejection track is used to eject the drone, and the delivery track is used to continuously deliver multiple drones to the ejection track.

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