Cylinder type launching folding wing unmanned aerial vehicle

Abstract

The utility model discloses a cylindrical launch folding wing unmanned aerial vehicle which comprises an unmanned aerial vehicle body, the unmanned aerial vehicle body comprises a square fuselage and a conical nose cover, a concave platform is arranged below the middle rear section of the fuselage, foldable wings are arranged in the concave platform, foldable empennages are arranged on the two side faces, close to the tail, of the fuselage, and the tail of the fuselage is connected with the tail of the fuselage. A foldable propeller is arranged at the tail of the fuselage, two blades of the propeller can be folded and retracted into an upper arc-shaped groove and a lower arc-shaped groove, close to the tail, of the fuselage respectively, a pod, a parachute cabin and a GPS antenna cabin are integrated in the nose cover, and a load cabin, a battery cabin and an equipment cabin are sequentially arranged at the front section, the middle section and the rear section of the fuselage. According to the cylindrical launching folding wing unmanned aerial vehicle, the design of the conical nose cover, the square fuselage, the lower single wing and the V-shaped empennage is adopted, launching is carried out through the square launching cylinder during launching, a plurality of cabin sections are designed in the square fuselage, each cabin section is fully utilized under the condition that the gravity center of the unmanned aerial vehicle is proper, and the assembly efficiency is greatly improved.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft, in particular to a barrel-launched folding-wing UAV. Background Art

[0002] With the development of drone technology, the demand for miniaturization and portability has led to the emergence of canister-launched drones. These systems utilize a canister-shaped launcher to safely store and quickly launch drones, significantly improving their concealment and survivability. This canister-launched system requires drones with folding wings. Folding-wing technology allows the drone's wingspan and tail to be folded before launch, allowing it to fit into a launch canister of the appropriate size, saving space. Once launched, it quickly unfolds, achieving optimal flight performance. Canister-launched folding-wing drones exhibit broad application potential in battlefield reconnaissance and strike missions, as well as relay missions.

[0003] At present, most drone fuselages in existing technologies are designed to be circular, which makes it impossible to fully utilize the internal structural space of the fuselage. Due to the limitation of the external dimensions, the fuselage space of the folding wing structure is limited, and it is very inconvenient to select onboard equipment and design the load. Therefore, there is still a lot of room for optimization in the design of the folding wing structure of drones, because the greater the degree to which the drone can be folded, the smaller the launch tube can be made, which is beneficial to the transportation of the launch tube and the drone.

[0004] Furthermore, a round folding cross-section can easily become unevenly positioned within the tube, causing it to roll after ejection. In severe cases, if the roll cannot be corrected, it can lead to a crash. Furthermore, adjusting the plane to a level position takes significantly longer. A square folding cross-section, however, does not present this problem.

[0005] Furthermore, many drone-like power plugs are located inside the fuselage, requiring removal of a cover each time a power plug is needed. Furthermore, the battery removal and installation process is cumbersome. Some parachute cords even pass through the top of the cover, requiring temporary maintenance before each takeoff. Removing the cover tangles the cords, necessitating a time-consuming and laborious reinstallation of the parachute.

[0006] Some folding-wing drone designs feature tails that unfold upon launch, without a locking mechanism for the entire tail's rotating mechanism. Wind tunnel testing of these drones with angle-of-attack control revealed that aerodynamic forces acting on the tail caused the entire tail to rotate axially around the rotating mechanism, shifting its original position and severely impacting the drone's flight performance. Utility Model Content

[0007] 1. Technical problem to be solved: Most existing drones use a circular fuselage, which cannot fully utilize the internal structural space of the fuselage, making it prone to rolling after launch. The functional area layout of the fuselage space is not reasonable, making maintenance difficult. In addition, the tail wing rotation mechanism is not designed with a locking mechanism. The tail is affected by aerodynamic forces, which will cause the entire tail wing to rotate axially around the rotation mechanism, causing the original position of the tail wing to change, seriously affecting the flight performance of the drone.

[0008] In order to solve the above technical problems, the utility model provides a cylinder-type launching folding-wing UAV.

[0009] 2. Technical solution:

[0010] A barrel-launched folding-wing UAV comprises a UAV body, which includes a square fuselage and a tapered nose cover. A concave platform is provided below the middle and rear sections of the fuselage, in which foldable wings are provided. Foldable tail wings are provided on both sides of the fuselage near its tail. A foldable propeller is provided at the tail of the fuselage, and two blades of the propeller can be folded and retracted into upper and lower arc-shaped grooves of the fuselage near its tail. A pod, a parachute compartment and a GPS antenna compartment are integrated in the nose cover. A payload compartment, a battery compartment and an equipment compartment are provided in the front, middle and rear sections of the fuselage in sequence.

[0011] Furthermore, the GPS antenna cabin is arranged above the front section of the nose cover, and an antenna cabin cover is provided on the top of the GPS antenna cabin, which is engaged with the top hatch of the GPS antenna cabin through locking protrusions. The pod is arranged below the GPS antenna cabin, and the parachute cabin is arranged at the rear section of the nose cover. The front end and bottom of the parachute cabin are provided with wire passages; the front end of the GPS antenna cabin is also provided with a hook groove and a pitot tube mounting hole, and the front end of the nose cover is provided with a guide head.

[0012] Furthermore, an electrical switch compartment close to the battery compartment is provided in the middle of the fuselage. The electrical switch compartment is arranged on the top of the fuselage. Multiple power control button switches and battery charging plugs are arranged in the electrical switch compartment. Removable center of gravity measurement rings are also provided on both sides of the middle section of the fuselage.

[0013] Furthermore, embedded air inlets are provided on both sides of the equipment compartment, a heat sink is provided at the bottom, a cooling fan is installed on the heat sink, a first servo plug is provided on one side of the heat sink, a mounting plate is provided on the side of the heat sink close to the tail of the fuselage, and an electronic speed regulator is provided on the mounting plate.

[0014] Furthermore, the wing is connected to a wing rotation mechanism, which includes an L-shaped mounting base fixed to the fuselage, a bearing seat fixed on the mounting base, a left wing mounting plate and a right wing mounting plate rotatably connected to the bearing seat, the left wing mounting plate and the right wing mounting plate are respectively fixedly connected to the metal embedded parts at the wing root positions of the left wing and the right wing, a wing torsion spring is provided between the left wing mounting plate and the right wing mounting plate, and two wing top blocks corresponding to the left wing and the right wing are also provided on the mounting base, the wing top blocks are rotatably connected to the mounting base through a plug screw, and the plug screw is provided with a top block torsion spring. After the left wing and the right wing are rotated open under the action of the wing torsion spring, the two wing top blocks are respectively engaged into the slots at the wing root positions of the left wing and the right wing.

[0015] Furthermore, the mounting base is provided with two buffer rubber pads corresponding to the left wing and the right wing respectively. The buffer rubber pads are provided with micro switches. The micro switches are triggered when the left wing and the right wing are opened. The mounting base is also provided with a second servo plug.

[0016] Furthermore, the wing includes an inner wing and an outer wing, a retractable structure is provided between the inner wing and the outer wing, and a fairing is provided below the wing.

[0017] Furthermore, the tail wing is provided with an embedded antenna, the tail wing is connected to the tail wing rotation mechanism, the tail wing rotation mechanism includes a rotating seat, the rotating seat is rotatably connected to the fixed seat, and two corresponding positioning protrusions are provided on the outer sides of the rotating seat and the fixed seat. The tail wing is connected to the tail wing locking mechanism, and the tail wing locking mechanism includes a spring plunger arranged on the fixed seat. When the tail wing is unfolded, the positioning column of the spring plunger is inserted into the positioning hole of the rotating seat. A button rod is also provided in the positioning hole. A button is provided at the end of the button rod, and a pressing spring is provided between the button and the rotating seat.

[0018] Furthermore, the blades of the propeller are hinged at both ends of the propeller clamp, a blade torsion spring is installed at the hinged position, and the propeller clamp is fixedly connected to the rotating part of the propeller.

[0019] Furthermore, the UAV is launched by a launching device, which includes a square launching tube, the end of which is fixed on a launching base, a bracket is provided in the middle of the launching tube, and a gas generating device is provided in the launching tube.

[0020] 3.Beneficial effects:

[0021] The utility model is a canister-launched folding-wing UAV with a tapered nose cover and a square fuselage, a lower monoplane, and a "V"-shaped tail. It is launched from a square launch tube. Multiple compartments are designed within the square fuselage, and each compartment is fully utilized when the center of gravity of the UAV is appropriate. A separate parachute compartment is designed to store the parachute, which is convenient for recovery during testing. Each compartment is fully arranged for the parachute, payload, power supply, onboard equipment, and electrical switches, greatly improving assembly efficiency. The overall structure of the nose cover is integrally formed using 3D printing materials, integrating the pod, parachute compartment, and GPS antenna compartment. It is designed with a wire guide and a pitot tube mounting hole, and a hook groove is designed at the front end for convenient hooking out when the launch is temporarily canceled after the UAV is inserted into the tube.

[0022] The electrical switch compartment is equipped with multiple power control button switches and battery charging plugs, which reduces the need for plugging and unplugging plugs, reduces the weight of the structure to a certain extent, and reduces the safety hazards caused by personnel plugging and unplugging plugs. The GPS antenna and data link antenna are installed by embedding them internally to reduce the exposure of the antenna and reduce the resistance effect on the UAV during flight. The parachute design facilitates the recycling of the UAV during test flights and can also serve as a mission payload sub-compartment to increase the payload capacity. The center of gravity measurement of the UAV is specially designed with a hanging point, which is convenient for use in the absence of ground measuring instruments. It can be directly removed before launch without affecting the launch of the UAV into the tube. The electronic equipment compartment has a large number of equipment arrangements, and there are embedded air intakes on both sides of the fuselage skin outside the cabin, and a cooling fan is designed underneath to blow out the hot air inside.

[0023] The wings are retractable and foldable. Before launch, the outer wings are retracted and the wing rotation mechanism is unlocked to retract the wings, significantly reducing the launch size while maintaining the drone's designed wingspan. The folding tail and foldable propellers reduce the drone's height. The tail locking mechanism prevents axial displacement of the tail from aerodynamic forces during flight, effectively safeguarding the drone's flight performance. The drone is launched from a square launch tube, offering high portability and a compact design, allowing for rapid launch in confined spaces and facilitating transport and deployment. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 This is a schematic diagram of the utility model's canister-launched folding-wing UAV in its unfolded state;

[0025] Figure 2 This is a schematic diagram of the folded state of the barrel-launched folding-wing UAV of the present invention;

[0026] Figure 3 A top view of the folded state of the canister-launched folding-wing UAV of the present invention and an enlarged view of a partial electrical switch compartment;

[0027] Figure 4This is a left side view of the barrel-launched folding-wing UAV of the present invention in a folded state;

[0028] Figure 5 This is a schematic diagram of the exploded wing rotation mechanism of the barrel-launched folding-wing UAV of the present invention and an enlarged cross-sectional view of a local wing top block;

[0029] Figure 6 This is a bottom view of the rear section of the fuselage of the barrel-launched folding-wing UAV of the present invention in the unfolded state;

[0030] Figure 7 This is a cross-sectional view of the nose cover of the barrel-launched folding-wing UAV of the present invention;

[0031] Figure 8 This is a cross-sectional view of the tail of the barrel-launched folding-wing UAV of the present invention and an enlarged view of a partial tail locking mechanism;

[0032] Figure 9 This is a solid diagram of the tail locking mechanism of the barrel-launched folding-wing UAV of the present invention;

[0033] Figure 10 This is a schematic diagram of the folding and stowing of the propeller of the barrel-launched folding-wing UAV of the present invention;

[0034] Figure 11 The utility model is a schematic diagram of a canister-launched folding-wing UAV in a launch canister.

[0035] Figure 1: 1-fuselage, 2-wing rotation mechanism, 3-wing, 4-tail, 5-tail rotation mechanism, 6-tail locking mechanism, 7-propeller, 8-launching device, 9-electrical switch compartment, 10-UAV body, 11-nose cover, 12-seeker, 13-first servo plug, 14-heat sink, 15-cooling fan, 16-electronic speed regulator, 17-mounting plate, 101-load compartment, 102-battery compartment, 103-equipment compartment, 104-fairing, 105-center of gravity measurement ring, 106-air inlet, 201-buffer pad, 202-mounting base, 203-wing top block, 204-left wing mounting plate, 205-right wing mounting plate, 206-wing torsion spring, 207-bearing seat, 208-top block torsion spring, 2 09-Punch screw, 210-Micro switch, 211-Second servo plug, 301-Outer wing, 302-Inner wing, 401-Data link antenna, 501-Fixer, 502-Swivel seat, 503-Positioning protrusion, 601-Button rod, 602-Pressure spring, 603-Button, 604-Spring plunger, 701-Propeller blade, 702-Propeller blade torsion spring, 703-Propeller clamp, 801-Launch tube, 802-Gas generator, 803-Launch base, 804-Bracket, 901-Push button switch, 902-Battery charging plug, 1101-Pitot tube mounting hole, 1102-Hook groove, 1103-Antenna hatch, 1104-GPS antenna cabin, 1105-Pod, 1106-Cableway, 1107-Parachute cabin. DETAILED DESCRIPTION

[0036] The present invention will be described in detail below with reference to the accompanying drawings.

[0037] As attached Figure 1 To the attached Figure 11 ,

[0038] Specific embodiment: A cylinder-type launching folding-wing UAV includes a UAV body 10, which includes a square fuselage 1 and a tapered streamlined nose cover 11. A concave platform is provided below the middle and rear section of the fuselage 1, and a foldable wing 3 is provided in the concave platform. Foldable "V"-shaped tail wings 4 are provided on both sides of the fuselage 1 near its tail. A foldable propeller 7 is provided at the tail of the fuselage 1, and the two blades 701 of the propeller 7 can be folded and retracted into the upper and lower arc-shaped grooves near the tail of the fuselage 1 respectively. A pod 1105, a parachute compartment 1107 and a GPS antenna compartment 1104 are integrated in the nose cover 11. The front, middle and rear sections of the fuselage 1 are respectively provided with a payload compartment 101, a battery compartment 102 and an equipment compartment 103.

[0039] The UAV is launched by a launching device 8, which includes a square launching tube 801. The end of the launching tube 801 is fixed on a launching base 803. A bracket 804 is provided in the middle of the launching tube 801. A gas generating device 802 is provided inside the launching tube.

[0040] When launching the drone, the wings 3, tail 4, and propeller 7 blades 701 are folded and inserted into the launch tube 801. The folded fuselage 1 is compact, and the launch tube 801 can also be designed as a small square structure, offering high portability and a compact design. This allows the drone to be quickly launched from a small space. The drone and launch device 8 take up little space for transportation, making them convenient to use and transport and deploy. This embodiment uses a square fuselage 1 paired with a square launch tube 801 for launch. A gas generator 802 generates high-pressure gas to propel the drone for launch. After launch, unlike a round fuselage, the drone does not roll after ejection and requires correction. Furthermore, the square fuselage has a regular structure, allowing for more efficient utilization of its internal space. This embodiment design takes into account the location of the drone's center of gravity, fully utilizing the internal space of the fuselage 1 while maintaining an appropriate center of gravity, significantly improving assembly efficiency.

[0041] The GPS antenna pod 1104 is located above the front section of the nose cover 11. Atop the GPS antenna pod 1104 is an antenna cover 1103, which snaps into place with a locking protrusion on the top hatch of the GPS antenna pod 1104. A gondola 1105 is located below the GPS antenna pod 1104. A parachute pod 1107 is located at the rear section of the nose cover 11. Cable runners 1106 are located at the front and bottom of the parachute pod 1107. The front of the GPS antenna pod 1104 also features a hook slot 1102 and a pitot tube mounting hole 1101. The front of the nose cover 11 is equipped with a seeker 12. The hook slot 1102 is used to easily remove the drone from the tube when it's not being launched. The cable for the pitot tube, installed in the pitot tube mounting hole 1101, can be passed through the cable runner 1106 to the fuselage and connected to the equipment, providing power and signal connections. The rubber hose of the pitot tube can also be connected to the flight control system on the fuselage through the cable runner 1106. The wire channel effectively connects the lines and pipes in the nose cover to the fuselage end, without affecting the function of the parachute compartment 1107 and without exposing the wire tubes, making the wiring of the body cover neat and beautiful. This embodiment optimizes the internal space and structure of the nose cover 11. The cabin component of the nose cover 11 is integrally formed with wave-transparent 3D printing materials, which will not affect the GPS antenna's ability to receive signals. The GPS antenna can also be connected to the fuselage through the wire channel 1106. The built-in antenna helps to maintain a smooth appearance and reduce resistance. The parachute compartment 1107 can be used as a payload compartment when there is no need to recover the drone and install the parachute, thereby increasing the drone's payload capacity and improving mission efficiency.

[0042] The central portion of the fuselage 1 also features an electrical switch compartment 9, located near the battery compartment 102. This compartment is located at the top of the fuselage 1 and contains multiple power control pushbutton switches 901 and a battery charging plug 902. The pushbutton switches 901 reduce the number of power cable connections, reducing the overall weight of the drone and minimizing safety hazards associated with plugging and unplugging. The battery charging plug 902 allows for direct connection to an external charger to charge the onboard batteries, reducing the need to open the hatch. Removable center of gravity measurement rings 105 are also located on both sides of the midsection of the fuselage 1. This allows for convenient use when ground-based center of gravity measurement equipment is unavailable. They can be removed before launch without interfering with the drone's insertion into the launch tube.

[0043] Embedded air inlets 106 are provided on both sides of the equipment compartment 103 to fully utilize airflow for heat dissipation. A heat sink 14 is provided at the bottom, and a cooling fan 15 is installed on the heat sink 14 to dissipate heat from the equipment inside the equipment compartment 103. A first servo plug 13 is provided on one side of the heat sink 14, and a mounting plate 17 is provided on the side of the heat sink 14 close to the tail of the fuselage 1, on which an electronic speed regulator 16 is provided. The heat sink of the electronic speed regulator 16 is installed exposed, and airflow can be used to effectively dissipate heat.

[0044] The wing 3 is connected to the wing rotation mechanism 2, which includes an L-shaped mounting base 202 fixed to the fuselage 1, a bearing seat 207 fixed to the mounting base 202, and a left wing mounting plate 204 and a right wing mounting plate 205 rotatably connected to the bearing seat 207. The left wing mounting plate 204 and the right wing mounting plate 205 are respectively fixedly connected to the metal embedded parts at the wing root position of the left wing 3 and the right wing 3. There is a Wing torsion spring 206, two wing top blocks 203 corresponding to the left wing 3 and the right wing 3 are respectively provided on the mounting base 202. The wing top blocks 203 are rotatably connected to the mounting base 202 through a plug screw 209. The plug screw 209 is provided with a top block torsion spring 208. After the left wing 3 and the right wing 3 are rotated open under the action of the wing torsion spring 206, the two wing top blocks 203 are respectively engaged into the slots at the wing root positions of the left wing 3 and the right wing 3.

[0045] Two buffer rubber pads 201 corresponding to the left wing 3 and the right wing 3 are also provided on the mounting base 202. A micro switch 210 is provided in the buffer rubber pad 201. When the left wing 3 and the right wing 3 are opened, the micro switch 210 is triggered. A second servo plug 211 is also provided on the mounting base 202.

[0046] The wing 3 includes an inner wing 302 and an outer wing 301 . A retractable structure is provided between the inner wing 302 and the outer wing 301 to further shorten the overall length. A fairing 104 is also provided below the wing 3 .

[0047] The wing 3 is designed as a two-section telescopic wing with inner and outer sections, which greatly reduces the launch size. The telescopic inner and outer wings also meet the design indicators of the drone. The telescopic wing increases the area to obtain more lift. When folding, the outer wing 301 must be pushed inward until it reaches the root of the inner wing 302, and then the wing top block 203 is picked open with a tool, and then the wing 3 is rotated and retracted to the concave platform below the fuselage 1. When unfolding, the wing 3 rotates around the wing rotation mechanism 2 axially and unfolds. When the wing 3 unfolds, it contacts the cushioning pad 201 on the mounting base 202. The wing top block 203 will snap into the slot to limit the wing 2, so that the wing 2 cannot rotate back and forth in the axial direction. When it contacts the cushioning pad 201, it will trigger the micro switch 210. When the wing 3 is locked in place, the signal is transmitted to the flight control, ensuring that the wing 3 is in the designed effective position. The second servo plug 211 facilitates the connection of the aileron servo plug and leads to the fuselage. The folded retractable wings 3 reduce the overall size of the drone, which is conducive to the design of the launch tube 801 into a small size. The folded wings 3 and the square fuselage 1 make the drone rectangular, so that the launch tube can be designed into a small square structure, which takes up little space for transportation and is easy to use.

[0048] The tail 4 is provided with an embedded data link antenna 401, which is arranged in the tail wire trough to reduce the exposure of the antenna and reduce the resistance effect on the drone during flight. The tail 4 is connected to the tail rotating mechanism 5, which includes a rotating seat 502, which is rotatably connected to the fixed seat 501. The outer sides of the rotating seat 502 and the fixed seat 501 are provided with two corresponding positioning protrusions 503. The tail 4 is connected to the tail locking mechanism 6, which includes a spring plunger 604 provided on the fixed seat 501. When the tail 4 is deployed, the positioning post of the spring plunger 604 is inserted into the positioning hole of the rotating seat 502. The positioning hole is also provided with a button rod 601, and the end of the button rod 601 is provided with a button 603. A pressure spring 602 is provided between the button 603 and the rotating seat 502.

[0049] When unlocking is required, the button 603 is pressed to a certain position. The button rod 601 pushes the positioning post of the spring plunger 604 out of the positioning hole. When the tail 4 is not rotating, the button rod 601 and the positioning post are both located in the gap between the rotating seat 502 and the fixed seat 501. At this time, the rotating seat 502 is unlocked and can rotate, that is, the entire tail 4 can rotate. The button rod 601 is acted upon by the spring to rebound to its original position, and the positioning post supports the lower surface of the rotating seat 502. The smooth positioning post on the lower surface of the rotating seat 502 does not affect the rotation state. The tail 4 is then pushed forward and retracted to the position on both sides of the fuselage 1. The personnel need to pinch the tail 4 to prevent it from rebounding. The positioning protrusions 503 limit the rotation angle, ensuring that the rotation angle of the rotating seat 502 meets the tail design. The folding tail reduces the height of the drone, making the drone smaller when folded, which also greatly facilitates the small size of the launch tube. The tail locking mechanism is designed to ensure that the tail does not shift axially due to aerodynamic forces during flight, effectively ensuring that the drone's aerodynamic performance is not affected.

[0050] The blades 701 of the propeller 7 are hinged at both ends of the blade clamp 703. The hinge position is equipped with a blade torsion spring 702. The blade clamp 703 is fixedly connected to the rotating part of the propeller 7. When inserting the launch tube 801, the blades 701 need to be pinched and inserted into the launch tube 801 after folding. After launch, they will automatically pop out. The folded blades reduce the height of the drone.

[0051] Although the present invention has been disclosed above in terms of preferred embodiments, they are not intended to limit the present invention. Anyone skilled in the art can make various changes or modifications without departing from the spirit and scope of the present invention. Therefore, the scope of protection of the present invention should be based on the scope of protection defined by the claims of this application.

Claims

1. A canister-launched folding-wing UAV, characterized in that: The drone comprises a square fuselage and a tapered nose cover, a concave platform is provided below the middle and rear section of the fuselage, foldable wings are provided in the concave platform, foldable tail wings are provided on both sides of the fuselage near its tail, a foldable propeller is provided at the tail of the fuselage, and the two blades of the propeller can be folded and retracted into the upper and lower arc-shaped grooves of the fuselage near the tail, a pod, a parachute compartment and a GPS antenna compartment are integrated in the nose cover, and a load compartment, a battery compartment and an equipment compartment are provided in the front, middle and rear sections of the fuselage respectively.

2. A barrel-launched folding-wing UAV according to claim 1, characterized in that: The GPS antenna cabin is arranged above the front section of the nose cover, and an antenna cabin cover is provided on the top of the GPS antenna cabin. The antenna cabin cover is engaged with the top hatch of the GPS antenna cabin through locking protrusions. The pod is arranged below the GPS antenna cabin, and the parachute cabin is arranged at the rear section of the nose cover. The front end and bottom of the parachute cabin are provided with wire passages; the front end of the GPS antenna cabin is also provided with a hook groove and a pitot tube mounting hole, and the front end of the nose cover is provided with a guide head.

3. A barrel-launched folding-wing UAV according to claim 2, characterized in that: An electrical switch compartment close to the battery compartment is also provided in the middle of the fuselage. The electrical switch compartment is arranged on the top of the fuselage. Multiple power control button switches and battery charging plugs are arranged in the electrical switch compartment. Removable center of gravity measurement rings are also provided on both sides of the middle section of the fuselage.

4. The barrel-launched folding-wing UAV according to claim 3, characterized in that: The equipment compartment is provided with embedded air inlets on both sides, a heat sink is provided at the bottom, a heat sink is installed with a cooling fan, a first servo plug is provided on one side of the heat sink, a mounting plate is provided on the side of the heat sink close to the tail of the fuselage, and an electronic speed regulator is provided on the mounting plate.

5. A barrel-launched folding-wing UAV according to any one of claims 1 to 4, characterized in that: The wing is connected to the wing rotation mechanism, and the wing rotation mechanism includes an L-shaped mounting base fixed to the fuselage, a bearing seat is fixed on the mounting base, and a left wing mounting plate and a right wing mounting plate are rotatably connected to the bearing seat. The left wing mounting plate and the right wing mounting plate are respectively fixedly connected to the metal embedded parts at the wing root positions of the left wing and the right wing. A wing torsion spring is provided between the left wing mounting plate and the right wing mounting plate. The mounting base is also provided with two wing top blocks corresponding to the left wing and the right wing respectively. The wing top blocks are rotatably connected to the mounting base through a plug screw, and the plug screw is provided with a top block torsion spring. After the left wing and the right wing are rotated and opened under the action of the wing torsion spring, the two wing top blocks are respectively engaged into the slots at the wing root positions of the left wing and the right wing.

6. The barrel-launched folding-wing UAV according to claim 5, characterized in that: The mounting base is also provided with two buffer rubber pads corresponding to the left wing and the right wing respectively. The buffer rubber pads are provided with micro switches. The micro switches are triggered when the left wing and the right wing are opened. The mounting base is also provided with a second servo plug.

7. The barrel-launched folding-wing UAV according to claim 6, characterized in that: The wing comprises an inner wing and an outer wing, a retractable structure is provided between the inner wing and the outer wing, and a fairing is provided below the wing.

8. The barrel-launched folding-wing UAV according to claim 7, characterized in that: The tail wing is provided with an embedded antenna, the tail wing is connected to the tail wing rotation mechanism, the tail wing rotation mechanism includes a rotating seat, the rotating seat is rotatably connected to the fixed seat, the outer sides of the rotating seat and the fixed seat are provided with two corresponding positioning protrusions, the tail wing is connected to the tail wing locking mechanism, and the tail wing locking mechanism includes a spring plunger arranged on the fixed seat. When the tail wing is unfolded, the positioning column of the spring plunger is inserted into the positioning hole of the rotating seat. A button rod is also provided in the positioning hole. A button is provided at the end of the button rod, and a pressing spring is provided between the button and the rotating seat.

9. The barrel-launched folding-wing UAV according to claim 8, characterized in that: The blades of the propeller are hinged at both ends of the propeller clamp, the hinged positions are provided with blade torsion springs, and the propeller clamp is fixedly connected to the rotating part of the propeller.

10. The barrel-launched folding-wing UAV according to claim 9, characterized in that: The UAV is launched by a launching device, which includes a square launching tube, the end of which is fixed on a launching base, a bracket is provided in the middle of the launching tube, and a gas generating device is provided in the launching tube.

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