An air-dropped folding wing unmanned aerial vehicle system

Abstract

This invention belongs to the field of unmanned aerial vehicle (UAV) technology and discloses an airdrop-type folding-wing UAV system connected to an aircraft delivery canister. The airdrop-type folding-wing UAV system includes a load-bearing protective shell, a UAV body, and interstage connecting components. The load-bearing protective shell is slidably connected to the aircraft delivery canister. An accommodating cavity is provided inside the load-bearing protective shell, within which the UAV body is movably disposed. The UAV body includes a nose, a fuselage, a first folding component, and a second folding component. The nose is located at the end of the fuselage, which is connected to a front wing, a rear wing, a vertical tail, and a propeller. The rear wing, vertical tail, and propeller are located at the end of the fuselage opposite to the nose. The first folding component is connected to the front and rear wing, the second folding component is connected to the vertical tail, and the propeller is rotatably connected to the fuselage. The interstage connecting components include a parachute, which is connected to the UAV body. This allows the system to adapt to different application scenarios and quickly adjust the initial velocity and attitude of the UAV body.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and more particularly to an airdrop-type folding-wing UAV system. Background Technology

[0002] With the increasing diversification of modern aviation public service demands, large fixed-wing aircraft often use small drones to conduct large-scale activities such as monitoring forest fires, searching for people in distress, patrolling borders and large infrastructure, and assessing disaster situations. In order to overcome the limitations of the range and endurance of small drones, large aircraft are usually used as mobile air bases to carry drones to the target area for clustered release, so as to extend the operating radius of drones, improve response speed, and overcome the limitations of complex geographical environments such as mountains and oceans.

[0003] In related technologies, medium and large airdrop drones typically use external attachments under the wings, which not only affects aerodynamic shape, increases fuel consumption and operating costs, but also encroaches on the payload space of other supplies, making it difficult to quickly replenish and replace them during missions. In scenarios requiring continuous operation, such as responding to sudden natural disasters and large-scale search and rescue, they lack flexibility and cannot meet the requirements of low altitude, ultra-long endurance, and high payload. Traditional disposable delivery devices have fixed landing points and single functions, making it difficult to achieve dynamic tracking and continuous data transmission. Moreover, most existing drones are designed for ground launch and are incompatible with the standardized material delivery tubes inside large aircraft, resulting in idle resources. Traditional bulk delivery lacks initial velocity and attitude control, making the drone susceptible to instability and tumbling due to strong high-altitude airflow when detaching from the aircraft, posing a risk of parachute deployment failure and potentially causing property damage and mission failure. Summary of the Invention

[0004] The purpose of this invention is to provide an airdrop-type folding-wing drone system to solve the problems of poor deployment stability and compatibility of airdrop drones, and difficulty in controlling the initial velocity and attitude after deployment.

[0005] To achieve this objective, the present invention adopts the following technical solution: An airdrop-type folding-wing unmanned aerial vehicle (UAV) system is connected to an aircraft delivery canister. The system includes: a load-bearing protective shell slidably connected to the delivery canister; a UAV body, the load-bearing protective shell having an internal cavity in which the UAV body is movably disposed, the UAV body including a nose, a fuselage, a first folding assembly, and a second folding assembly; the nose being located at the end of the fuselage; the fuselage being connected to a front wing, a rear wing, a vertical tail, and a propeller; the front wing being located at the end of the fuselage facing the nose; the rear wing, the vertical tail, and the propeller being located at the end of the fuselage away from the nose; the first folding assembly being connected to the front wing and the rear wing; the second folding assembly being connected to the vertical tail; and the propeller being rotatably connected to the fuselage so that when the UAV body is located within the load-bearing protective shell, the front wing, the rear wing, the vertical tail, and the propeller are all in a folded state; and an interstage connection assembly including a parachute connected to the UAV body.

[0006] Preferably, the interstage connection assembly further includes a wind vane connected to the parachute for pulling the UAV body out of the accommodating cavity.

[0007] Preferably, the load-bearing protective housing has a bottom cover at one end near the machine head, and a shock-absorbing pad is provided between the bottom cover and the machine head on the side facing the accommodating cavity.

[0008] Preferably, the propeller is connected to a blade spring, which is connected to the fuselage. When the UAV body is located inside the accommodating cavity, the blade spring is compressed.

[0009] Preferably, the fuselage has a recess, the front wing and the rear wing are disposed in the recess, and the fuselage surface protrudes from the front wing and the rear wing.

[0010] Preferably, a recess is provided on each of the two sides of the fuselage in the vertical direction, and the front wing and the rear wing in the folded state are respectively provided in the two recesses.

[0011] Preferably, there are two first folding assemblies, which are respectively connected to the front wing and the rear wing. Each first folding assembly includes a first pivot, a first torsion spring, and a first rotary joint. The first pivot is disposed on the fuselage, the first torsion spring is sleeved on the first pivot, and each end of the first torsion spring is connected to a first rotary joint. The first rotary joints of the two first folding assemblies are respectively connected to the front wing and the rear wing.

[0012] Preferably, the first folding assembly further includes a locking pin, one end of which is connected to a compression spring. A locking groove is provided on the first rotary joint. After the UAV body is detached from the load-bearing protective shell, the compression spring pushes the locking pin into the locking groove so that the locking pin engages with the first rotary joint.

[0013] Preferably, the second folding assembly includes a second pivot, a second torsion spring, and a second rotary joint. The second pivot is disposed on the body, the second torsion spring is sleeved on the second pivot, the second torsion spring is connected to the second rotary joint, and the vertical tail is connected to the second rotary joint.

[0014] Preferably, the second folding assembly further includes a baffle disposed on the fuselage, and after the vertical tail is unfolded, the second rotary joint abuts against the baffle.

[0015] The beneficial effects of this invention are: An airdrop-type folding-wing unmanned aerial vehicle (UAV) system is connected to an aircraft delivery canister. The system includes a load-bearing protective shell, a UAV body, and interstage connecting components. The load-bearing protective shell is slidably connected to the aircraft delivery canister. An accommodating cavity is provided inside the load-bearing protective shell, within which the UAV body is movably positioned. The UAV body includes a nose, a fuselage, a first folding component, and a second folding component. The nose is located at the end of the fuselage, which is connected to a front wing, a rear wing, a vertical tail, and a propeller. The front wing is located at the end of the fuselage facing the nose, while the rear wing, vertical tail, and propeller are located at the end of the fuselage away from the nose. The first folding component is connected to the front and rear wings, the second folding component is connected to the vertical tail, and the propeller is rotatably connected to the fuselage so that when the UAV body is inside the load-bearing protective shell, the front wing, rear wing, vertical tail, and propeller are all in a folded state. The interstage connecting components include a parachute connected to the UAV body.

[0016] In this way, the load-bearing protection object can be adapted to the aircraft launch tube commonly used by large patrol aircraft, which facilitates the replenishment and replacement of the UAV body. The deployment of the UAV body can be achieved without modification, improving the compatibility of the aircraft launch tube, so as to facilitate the storage and deployment of multiple UAV bodies and avoid occupying the space under the aircraft. The UAV body is set inside the load-bearing protection object, which can reduce the friction force it experiences when the UAV body is deployed. The first folding component and the second folding component can quickly unfold the forewing, rear wing and vertical tail of the UAV body, realize the rapid adjustment of initial velocity and attitude, and prevent the UAV body from tumbling due to airflow. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the structure of an airdropped folding-wing unmanned aerial vehicle system according to one embodiment of the present invention; Figure 2This is a front view of the drone body in one embodiment of the present invention; Figure 3 This is a top view of the drone body in one embodiment of the present invention; Figure 4 This is a schematic diagram of the structure of the control component in one embodiment of the present invention; Figure 5 This is a partial cross-sectional view of the first folding component in one embodiment of the present invention; Figure 6 This is a partial structural schematic diagram of the first folding component in one embodiment of the present invention; Figure 7 This is a partial structural schematic diagram of the locking pin and locking groove in one embodiment of the present invention; Figure 8 This is a partial structural schematic diagram of the second folding component in one embodiment of the present invention.

[0018] In the picture: 1. Load-bearing protective shell; 11. Receiving cavity; 12. Bottom cover; 13. Shock-absorbing pad; 14. Filler pad; 2. UAV body; 21. Nose; 22. Fuselage; 221. Forward wing; 222. Rear wing; 2221. Servo; 223. Vertical tail; 224. Propeller; 2241. Propeller blade spring; 2242. Motor; 225. Recess; 23. First folding assembly; 231. First pivot; 2311. Pressure cover; 232. First torsion spring; 2321. Limiting channel; 233. First rotary joint; 2331 1. Locking slot; 234. Locking pin; 2341. Compression spring; 24. Second folding assembly; 241. Second pivot; 242. Second torsion spring; 243. Second rotary joint; 244. Baffle; 245. Elastic retaining ring; 25. Control assembly; 251. Electronics unit; 252. Satellite navigation antenna; 253. Power battery; 254. Payload battery; 255. Current monitoring unit; 256. Flight control computer; 257. Link segment unit; 258. Electronic speed controller; 259. PCB antenna; 3. Wing. Detailed Implementation

[0019] The present invention will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and not intended to limit it. Furthermore, it should be noted that, for ease of description, the accompanying drawings show only the parts relevant to the present invention, and not all of the structures.

[0020] In the description of this invention, unless otherwise explicitly specified and limited, the terms "connected," "linked," and "fixed" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0021] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0022] In the description of this embodiment, the terms "upper," "lower," "right," etc., refer to the orientation or positional relationship shown in the accompanying drawings. They are used only for ease of description and simplification of operation, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the present invention. In addition, the terms "first" and "second" are used only for distinction in description and have no special meaning.

[0023] See Figures 1 to 3This invention provides an airdrop-type folding-wing unmanned aerial vehicle (UAV) system, which is connected to an aircraft delivery canister. The airdrop-type folding-wing UAV system includes a load-bearing protective shell 1, a UAV body 2, and inter-stage connecting components. The load-bearing protective shell 1 is slidably connected to the aircraft delivery canister. The load-bearing protective shell 1 has an internal accommodating cavity 11, and the UAV body 2 is movably disposed within the accommodating cavity 11. The UAV body 2 includes a nose 21, a fuselage 22, a first folding component 23, and a second folding component 24. The nose 21 is located at the end of the fuselage 22. The fuselage 22 is connected to a forewing 221, a rear wing 222, a vertical tail 223, and a propeller 224. The forewing 221 is located at the end of the fuselage 22 facing the nose 21. The rear wing 222 and the vertical tail 223 are connected to the forewing 221. The propeller 224 is located at the end of the fuselage 22 away from the nose 21. The first folding assembly 23 is connected to the front wing 221 and the rear wing 222, and the second folding assembly 24 is connected to the vertical tail 223. The propeller 224 is rotatably connected to the fuselage 22 so that when the UAV body 2 is located inside the load-bearing protective shell 1, the front wing 221, the rear wing 222, the vertical tail 223, and the propeller 224 are all in a folded state. The interstage connection assembly includes a parachute (not shown in the figure). The parachute is connected to the UAV body 2. The parachute can stabilize the descent speed of the UAV body 2. When the descent speed reaches the preset stable range, the parachute detaches, and at the same time, the front wing 221, the rear wing 222, the vertical tail 223, and the propeller 224 unfold.

[0024] In this embodiment, the aircraft launch tube is a standard launch tube commonly used by large patrol aircraft. An ejection device (not shown in the figure) is installed inside the aircraft launch tube. The ejection device includes a high-pressure gas cylinder, a valve, and an ejection piston. The ejection device is connected to an ejection control unit (not shown in the figure) to remotely control and trigger the ejection. The load-bearing protective shell 1 is made of high-strength and corrosion-resistant stainless steel. The load-bearing protective shell 1 is a hollow cylindrical structure with an outer diameter that matches the inner diameter of the aircraft launch tube. Both the outer and inner circumferential surfaces of the load-bearing protective shell 1 are smooth surfaces to reduce friction during ejection and when the UAV body 2 is removed from the load-bearing protective shell 1. Before launch, the UAV body 2 is housed inside the accommodating cavity 11. The extension directions of the forewing wing 221, rear wing 222, vertical tail 223, and propeller 224 in the folded state are all parallel to the length direction of the fuselage 22. After the UAV body 2 is removed from the load-bearing protective shell 1, the forewing wing 221 and rear wing 222 are horizontally positioned, and the vertical tail 223 is vertically positioned.

[0025] In this way, the load-bearing protective shell 1 pops out from the aircraft delivery canister commonly used by large patrol aircraft, which facilitates the replenishment and replacement of the UAV body 2. The size of the airdropped folding-wing UAV system is controlled within the envelope of the aircraft delivery canister. The deployment of the UAV body 2 can be achieved without modification, improving the compatibility of the aircraft delivery canister and the flexibility of the airdropped folding-wing UAV system to adapt to different application scenarios. The UAV body 2 is set inside the load-bearing protective shell 1. When the UAV body 2 is released, the load-bearing protective shell 1 can withstand the overload and tube wall friction at the moment of launch, reducing damage to the UAV body 2. It also facilitates the deployment of the forewing wing 221, tail wing 222, and vertical tail 223 of the UAV body 2, enabling the UAV body 2 to quickly adjust its initial velocity and attitude and avoid tumbling due to airflow.

[0026] It is understandable that the ejection device uses compressed air to eject the load-bearing protective shell 1 out of the aircraft launch tube and adjusts the ejection force and ejection angle, which is existing technology and will not be elaborated here.

[0027] See Figure 4 In some embodiments, the UAV body 2 also includes a control component 25, which includes an electronics unit 251, a satellite navigation antenna 252, a power battery 253, a payload battery 254, a current monitoring unit 255, a flight control computer 256, a link segment unit 257, an electronic speed controller 258, and a PCB antenna 259 disposed on the fuselage 22.

[0028] In this embodiment, the power battery 253 has a built-in intelligent battery management system to realize charge and discharge protection and status monitoring. The payload battery 254 is isolated from the power battery 253 to avoid electromagnetic interference. Along the extension direction of the fuselage 22, the electronics unit 251, power battery 253, payload battery 254, current monitoring unit 255, flight control computer 256, and electronic speed controller 258 are sequentially arranged inside the fuselage 22. The satellite navigation antenna 252 is arranged above the power battery 253, the link segment unit 257 is arranged above the electronic speed controller 258, the PCB antenna 259 is arranged on the vertical tail 223, the motor 2242 is connected to the propeller 224 and is used to drive the propeller 224 to rotate, the rear wing 222 is connected to the servo motor 2221 and is used to drive the rear wing 222 to deflect. The servo motor 2221 is connected to the position feedback sensor (not shown in the figure) and is used to control the attitude of the UAV in real time.

[0029] Thus, the electronics unit 251 can coordinate the data interaction of various subsystems such as navigation, power, and payload; the satellite navigation antenna 252 can provide high-precision positioning data to the flight control computer 256 to accurately measure the attitude and motion state of the UAV; the power battery 253 can supply power to the motor 2242 and servo motor 2221; the payload battery 254 can provide power to the mission payload; the current monitoring unit 255 can monitor the current parameters of each circuit branch in real time to improve the operational safety of the UAV body 2; the flight control computer 256 can control the UAV body 2 to fly autonomously; the link segment unit 257 can ensure low-latency interaction of commands and data between the UAV and the ground control station, which is conducive to achieving dynamic tracking and continuous data transmission; and the electronic speed controller 258 can receive signals from the flight control computer 256 and dynamically adjust the speed of the propeller 224 to match the thrust requirements of different flight stages.

[0030] Under the action of motor 2242, propeller 224 can be driven to rotate, which is conducive to long-term reliable operation in marine environment. PCB antenna 259 can ensure two-way communication between UAV and ground control station, transmit flight data in real time and receive control commands, so that UAV body 2 can quickly adjust attitude and initial velocity after detaching from load-bearing protective shell 1, reduce loss and loss of control risk during deployment, improve low-altitude safe deployment capability, enable UAV to actively track high-speed moving targets when flying at low altitude, and transmit data back to the mother machine through the existing communication frequency band of buoy, improve the application scope of UAV body 2.

[0031] It is understandable that the materials of the load-bearing protective shell 1 and the UAV body 2 can be adjusted according to actual needs. In this embodiment, the fuselage 22, the front wing 221, and the rear wing 222 are all made of lightweight materials to reduce the weight of the UAV body 2. The nose 21 and the vertical tail 223 are made of fiberglass fabric with good wave transmission to avoid blocking signals and facilitate the installation of PCB antenna 259.

[0032] See Figure 1 In some embodiments, the interstage connection assembly also includes a wind vane 3, which is connected to a parachute for pulling the drone body 2 out of the accommodating cavity 11.

[0033] In this embodiment, the interstage connection component is located at the end of the load-bearing protective shell 1 away from the nose 21. The parachute is connected to the fuselage 22 via parachute lines. The wind vane 3 is connected to a spring (not shown in the figure). After the load-bearing protective shell 1 is launched from the aircraft launch tube, the wind vane 3 is lifted and detached under the influence of wind force and its own spring, and pulls out the parachute and parachute lines connected to it. The parachute lines pull the UAV body 2 out from inside the load-bearing protective shell 1. The front wing 221 and rear wing 222 of the UAV body 2 are deployed under the action of the first folding component 23, and the vertical tail 223 is deployed under the action of the second folding component 24 to adjust the attitude of the UAV body 2 in the air.

[0034] Thus, during the deployment of the UAV body 2, as the load-bearing protective shell 1 is ejected from the aircraft's delivery tube, the front wing 221, rear wing 222, and vertical tail 223 of the UAV body 2 can automatically unfold under the action of the wind wing 3, so that the UAV body 2 can quickly adjust its attitude and initial velocity when it leaves the aircraft, adapting it to low-altitude flight and improving the flexibility of the airdropped folding wing UAV system.

[0035] See Figure 1 In some embodiments, a bottom cover 12 is provided at one end of the load-bearing protective housing 1 near the machine head 21, and a shock-absorbing pad 13 is provided between the bottom cover 12 facing the receiving cavity 11 and the machine head 21.

[0036] In this embodiment, a filling pad 14 is provided inside the load-bearing protective shell 1. The filling pad 14 is filled between the fuselage 22 and the inner wall of the load-bearing protective shell 1 to limit the position of the drone body 2 in the accommodating cavity 11. After the drone body 2 is pulled out of the load-bearing protective shell 1, the filling pad 14 used for limiting the position automatically detaches backward under the action of aerodynamic resistance.

[0037] Thus, the shock-absorbing pad 13 and the filling pad 14 can respectively restrict the axial and radial movement of the UAV body 2 within the accommodating cavity 11, preventing the UAV body 2 from colliding and displacing with the load-bearing protective shell 1 within the accommodating cavity 11, thereby affecting the deployment effect of the UAV body 2. At the moment the load-bearing protective shell 1 is ejected from the aircraft launch tube, the shock-absorbing pad 13 can absorb the axial impact energy, preventing the nose 21 from colliding with the bottom cover 12, and reducing the shaking of the UAV body 2 during ejection, thereby improving the deployment stability of the airdrop folding wing UAV system.

[0038] It is understood that the materials of the filling pad 14 and the shock-absorbing pad 13 can be adjusted according to actual needs. In this embodiment, the filling pad 14 is made of foam material to improve the protection effect on the drone body 2 without adding too much weight.

[0039] See Figure 4In some embodiments, the propeller 224 is connected to a blade spring 2241, which is connected to the fuselage 22. When the UAV body 2 is located in the accommodating cavity 11, the blade spring 2241 is compressed.

[0040] In this embodiment, the propeller 224 includes a hub and blades. The blade spring 2241 is connected to the fuselage 22 and the blades at both ends. When the UAV body 2 is located in the accommodating cavity 11, the blades are in a folded state and the blade spring 2241 is compressed. When the UAV body 2 is pulled out from the load-bearing protective shell 1, the blades unfold under the elastic force of the blade spring 2241, so that the motor 2242 drives the propeller 224 to rotate, thereby enabling the UAV body 2 to operate in the marine environment.

[0041] In this way, the propeller 224 can automatically deploy after the UAV body 2 is deployed without the need for additional structures. This avoids the propeller 224 failing to deploy due to electrical or aerodynamic uncertainties, and enables the synchronous deployment of the forewing 221, rear wing 222, vertical tail 223 and propeller 224. The motor 2242 drives the hub and blades to rotate, further opening the blades. This facilitates rapid adjustment of the initial velocity and attitude during deployment, preventing the UAV body 2 from tumbling due to strong airflow at high altitudes when it detaches from the fuselage. This improves the deployment stability of the UAV body 2, allows it to adapt to low-altitude long-endurance cruise, increases the sweep area, and thus increases thrust.

[0042] It is understandable that the propeller 224 can also be connected to the fuselage 22 via a torsion spring. The deployment method of the propeller 224 can be adjusted according to actual needs, which will not be elaborated here.

[0043] See Figure 2 In some embodiments, the fuselage 22 has a recess 225, and the front wing 221 and rear wing 222 are disposed in the recess 225, with the surface of the fuselage 22 protruding beyond the front wing 221 and rear wing 222. Further, in some embodiments, a recess 225 is provided on each of the two sides of the fuselage 22 in the vertical direction, and the front wing 221 and rear wing 222 in the folded state are respectively disposed in the two recesses 225.

[0044] In this embodiment, the recess 225 extends along the length of the fuselage 22, the front wing 221 is rotatably disposed on the top surface of the fuselage 22, and the rear wing 222 is rotatably disposed on the bottom surface of the fuselage 22.

[0045] Thus, the recess 225 provides ample space for the forewing 221 and the rearwing 222, allowing the size of the UAV body 2 to be compatible with standard-sized aircraft delivery tubes, avoiding the occupation of space under the aircraft wings, improving space utilization, and reducing the friction between the forewing 221 and the rearwing 222 and the inner wall of the load-bearing protective shell 1 during assembly and disassembly. This prevents the forewing 221 and the rearwing 222 from colliding with the load-bearing protective shell 1 during the process of the UAV body 2 being pulled out by the parachute lines, making the deployment of the UAV body 2 smoother, and enabling the forewing 221 and the rearwing 222 to deploy immediately after deployment, achieving attitude control.

[0046] It is understood that the forewing 221 and the rearwing 222 can also be located in the recess 225 on the same side. In this embodiment, the forewing 221 and the rearwing 222 are respectively located in the recesses 225 on both sides of the fuselage 22, which can reduce the interference between the forewing 221 and the rearwing 222 during the deployment process. The number and location of the recesses 225 can be adjusted according to actual needs, and will not be listed in detail here.

[0047] See Figures 4 to 6 In some embodiments, two first folding components 23 are provided, and the two first folding components 23 are respectively connected to the front wing 221 and the rear wing 222. The first folding component 23 includes a first pivot 231, a first torsion spring 232 and a first rotary joint 233. The first pivot 231 is disposed on the fuselage 22, the first torsion spring 232 is sleeved on the first pivot 231, and a first rotary joint 233 is connected to each end of the first torsion spring 232. The first rotary joints 233 of the two first folding components 23 are respectively connected to the front wing 221 and the rear wing 222.

[0048] In this embodiment, two front wings 221 and two rear wings 222 are provided. The two front wings 221 and two rear wings 222 are folded in a staggered manner in the vertical direction and attached to the surface of the fuselage 22, so that the overall shape of the UAV body 2 is close to cylindrical, facilitating its internal installation within the load-bearing protective shell 1. The first rotating shaft 231 is fixedly mounted on the fuselage 22. When the front wings 221 and rear wings 222 are in the folded state, the first torsion spring 232 is also in the folded state. The first rotary joint 233 has an assembly groove (not shown in the figure) for engaging with the first torsion spring 232, so that the first... A torsion spring 232 is engaged with two first rotary joints 233 at both ends. Each front wing 221 and each rear wing 222 is connected to a first rotary joint 233 so that after the UAV body 2 is pulled out from the load-bearing protective shell 1, the first torsion spring 232 applies an elastic force to the first rotary joint 233, so that the two front wings 221 and the two rear wings 222 simultaneously unfold outward symmetrically, reducing the impact of strong airflow on the attitude of the UAV body 2. A pressure cap 2311 is connected to the side of the first rotating shaft 231 away from the fuselage 22 to restrict the axial movement of the first rotary joint 233.

[0049] Thus, by setting the scissor-shaped front wing 221 and rear wing 222, the length-to-diameter ratio of the load-bearing protective shell 1 can be used to ensure that the UAV body 2 has a large lift wing surface required for low-altitude cruise. When folded, the front wing 221 and rear wing 222 are retracted to the recess 225 along the axial direction of the first pivot 231, and the first torsion spring 232 stores elastic potential energy, which can reduce the volume of the UAV body 2, making it compatible with the size of the aircraft delivery tube, avoiding encroachment on the load space of other materials, and allowing the front wing 221 and rear wing 222 to unfold after the UAV body 2 is deployed.

[0050] Understandably, in order to fix the position of the front wing 221 and the rear wing 222 within the load-bearing protective shell 1, they can also be locked by a removable pin-type cable tie. After the UAV body 2 is pulled out of the load-bearing protective shell 1, the pin-type cable tie is released from locking the front wing 221 and the rear wing 222, allowing the front wing 221 and the rear wing 222 to quickly deploy under the action of the first torsion spring 232.

[0051] See Figures 3 to 7 In some embodiments, the first folding assembly 23 further includes a locking pin 234, one end of which is connected to a compression spring 2341. The first rotary joint 233 has a locking groove 2331. After the UAV body 2 is separated from the load-bearing protective shell 1, the compression spring 2341 pushes the locking pin 234 into the locking groove 2331 so that the locking pin 234 engages with the first rotary joint 233.

[0052] In this embodiment, a limiting channel 2321 (not shown in the figure) is provided inside the first torsion spring 232. The compression spring 2341 and the locking pin 234 are both provided in the limiting channel 2321. When the front wing 221 and the rear wing 222 are in the folded state, the locking pin 234 abuts against the first rotary joint 233 and is located in the limiting channel 2321, and the compression spring 2341 is in the compressed state. When the front wing 221 and the rear wing 222 are unfolded under the action of the first torsion spring 232, the locking groove 2331 on the first rotary joint 233 is aligned with the limiting channel 2321. The compression spring 2341 extends and pushes the locking pin 234 into the locking groove 2331, thereby realizing the locking pin 234 and the first rotary joint 233 engaging and restricting the rotation of the correspondingly connected front wing 221 and rear wing 222.

[0053] In this way, the UAV body 2 is folded and stored in the load-bearing protective shell 1. The locking pin 234 and the compression spring 2341 are both set inside the first torsion spring 232, avoiding occupying the space of the fuselage 22, improving space utilization and avoiding assembly interference between the front wing 221 and the rear wing 222. When the UAV body 2 is pulled out and the front wing 221 and the rear wing 222 unfold, the locking pin 234 is inserted into the locking groove 2331 under the action of the compression spring 2341, realizing the rigid locking of the front wing 221 and the rear wing 222. This can prevent the front wing 221 and the rear wing 222 from rotating in opposite directions due to airflow during the flight of the UAV body 2, so that the UAV body 2 can withstand the maneuver overload in subsequent flight, eliminate wing misalignment, and improve flight performance.

[0054] See Figure 3 and Figure 8 In some embodiments, the second folding assembly 24 includes a second pivot 241, a second torsion spring 242, and a second rotary joint 243. The second pivot 241 is disposed on the body 22, the second torsion spring 242 is sleeved on the second pivot 241, the second torsion spring 242 is connected to the second rotary joint 243, and the vertical tail 223 is connected to the second rotary joint 243.

[0055] In this embodiment, two vertical tails 223 are provided. When the vertical tails 223 are in the folded state, they are located in the recess 225 of the body 22. Correspondingly, two second rotating shafts 241 are provided. The two second rotating shafts 241 are fixedly arranged on both sides of the body 22 in the horizontal direction. A base is provided on the side of the second rotating shaft 241 away from the second rotary joint 243. Both the base and the second rotary joint 243 are provided with grooves for accommodating the second torsion spring 242, so that the two ends of the second torsion spring 242 are respectively connected to the second rotary joint 243. 43. The base is snapped in place, and the second rotary joint 243 is connected to the elastic retaining ring 245. When the UAV body 2 is stored in the load-bearing protective shell 1, the vertical tail 223 is in a folded state. The second torsion spring 242 stores elastic potential energy, the second rotating shaft 241 can achieve radial limitation, and the elastic retaining ring 245 can achieve axial limitation. After the UAV body 2 is pulled out from the load-bearing protective shell 1, the second torsion spring 242 drives the second rotary joint 243 and the vertical tail 223 to rotate, so that the vertical tail 223 gradually unfolds to be perpendicular to the fuselage 22.

[0056] In this way, the vertical tail 223 in the folded state can be accommodated in the recess 225, avoiding increasing the size of the UAV body 2, so that the UAV body 2 can be adapted to the aircraft delivery tube, enabling rapid replenishment and replacement during the mission. It also allows the UAV body 2 to be pulled out from the load-bearing protective shell 1, and the limiting filling pad 14 to detach from the fuselage 22. The forewing 221, rear wing 222 and vertical tail 223 unfold symmetrically at the same time, so that the vertical tail 223 can withstand the maneuvering overload in subsequent flight, eliminate the false position of the vertical tail 223, and help control the initial velocity and attitude of the UAV body 2 after delivery, thus improving the stability of UAV delivery.

[0057] See Figure 4 and Figure 6 In some embodiments, the second folding assembly 24 further includes a baffle 244 disposed on the body 22. After the tail 223 is unfolded, the second rotary joint 243 abuts against the baffle 244.

[0058] In this embodiment, the baffle 244 is fixedly installed on the body 22. When the vertical tail 223 is in the folded state, the vertical tail 223 and the baffle 244 are respectively installed on both sides of the second rotary joint 243. During the unfolding process, the vertical tail 223 gradually moves towards the baffle 244 until the baffle 244 abuts against the second rotary joint 243, preventing the vertical tail 223 from rotating further.

[0059] Thus, the baffle 244 can not only limit the second rotary joint 243, but also prevent the second rotary joint 243 from colliding with other structures and prevent the vertical tail 223 from rebounding after it is deployed. Together with the elastic retaining ring 245 and the second rotating shaft 241, it restricts the movement of the vertical tail 223, preventing the vertical tail 223 from oscillating or falling off due to airflow disturbance, thereby affecting the directional control accuracy and improving the deployment and operational stability of the UAV body 2.

[0060] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the implementation of the present invention. Those skilled in the art will be able to make various obvious changes, readjustments, and substitutions without departing from the scope of protection of the present invention. It is neither necessary nor possible to exhaustively describe all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the claims of the present invention.

Claims

1. An airdrop-type folding-wing unmanned aerial vehicle system, characterized in that, Connected to an aircraft delivery canister, the air-droppable folding-wing unmanned aerial vehicle system includes: A load-bearing protective shell (1) is slidably connected to the aircraft delivery canister; The unmanned aerial vehicle (UAV) body (2) has a cavity (11) inside the load-bearing protective shell (1). The UAV body (2) is movably disposed within the cavity (11). The UAV body (2) includes a nose (21), a fuselage (22), a first folding assembly (23), and a second folding assembly (24). The nose (21) is disposed at the end of the fuselage (22). The fuselage (22) is connected to a front wing (221), a rear wing (222), a vertical tail (223), and a propeller (224). The front wing (221) is disposed at the end of the fuselage (22) facing the nose (21). The rear wing... (222) The vertical tail (223) and the propeller (224) are disposed at one end of the fuselage (22) away from the nose (21). The first folding assembly (23) is connected to the fore wing (221) and the rear wing (222). The second folding assembly (24) is connected to the vertical tail (223). The propeller (224) is rotatably connected to the fuselage (22) so that when the UAV body (2) is located inside the load-bearing protective shell (1), the fore wing (221), the rear wing (222), the vertical tail (223), and the propeller (224) are all in a folded state. Interstage connection component, the interstage connection component including a parachute, the parachute being connected to the UAV body (2).

2. The airdrop-type folding-wing UAV system according to claim 1, characterized in that, The interstage connection assembly also includes a wind vane (3), which is connected to the parachute and is used to pull the UAV body (2) out of the accommodating cavity (11).

3. The airdrop-type folding-wing unmanned aerial vehicle system according to claim 1, characterized in that, The load-bearing protective housing (1) is provided with a bottom cover (12) at one end near the machine head (21), and a shock-absorbing pad (13) is provided between the bottom cover (12) facing the accommodating cavity (11) and the machine head (21).

4. The airdrop-type folding-wing unmanned aerial vehicle system according to claim 1, characterized in that, The propeller (224) is connected to a blade spring (2241), which is connected to the fuselage (22). When the UAV body (2) is located in the accommodating cavity (11), the blade spring (2241) is compressed.

5. The airdrop-type folding-wing unmanned aerial vehicle system according to claim 1, characterized in that, The fuselage (22) is provided with a recess (225), the front wing (221) and the rear wing (222) are provided in the recess (225), and the surface of the fuselage (22) protrudes from the front wing (221) and the rear wing (222).

6. The airdrop-type folding-wing unmanned aerial vehicle system according to claim 5, characterized in that, The fuselage (22) has a recess (225) on each side in the vertical direction, and the front wing (221) and the rear wing (222) in the folded state are respectively located in the two recesses (225).

7. The airdrop-type folding-wing unmanned aerial vehicle system according to any one of claims 1-6, characterized in that, Two first folding components (23) are provided. The two first folding components (23) are respectively connected to the front wing (221) and the rear wing (222). The first folding component (23) includes a first pivot (231), a first torsion spring (232) and a first rotary joint (233). The first pivot (231) is provided on the fuselage (22). The first torsion spring (232) is sleeved on the first pivot (231). The first torsion spring (232) is connected to a first rotary joint (233) at both ends. The first rotary joints (233) of the two first folding components (23) are respectively connected to the front wing (221) and the rear wing (222).

8. The airdrop-type folding-wing unmanned aerial vehicle system according to claim 7, characterized in that, The first folding assembly (23) also includes a locking pin (234), one end of which is connected to a compression spring (2341). The first rotary joint (233) has a locking groove (2331). After the UAV body (2) is separated from the load-bearing protective shell (1), the compression spring (2341) pushes the locking pin (234) into the locking groove (2331) so that the locking pin (234) engages with the first rotary joint (233).

9. The airdrop-type folding-wing unmanned aerial vehicle system according to any one of claims 1-6, characterized in that, The second folding assembly (24) includes a second pivot (241), a second torsion spring (242), and a second rotary joint (243). The second pivot (241) is disposed on the body (22), the second torsion spring (242) is sleeved on the second pivot (241), the second torsion spring (242) is connected to the second rotary joint (243), and the vertical tail (223) is connected to the second rotary joint (243).

10. The air-droppable folding-wing unmanned aerial vehicle system according to claim 9, characterized in that, The second folding assembly (24) also includes a baffle (244) disposed on the fuselage (22). After the vertical tail (223) is unfolded, the second rotary joint (243) abuts against the baffle (244).

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