Unmanned aerial vehicle parachute device and unmanned aerial vehicle

Abstract

This application relates to the field of unmanned aerial vehicle (UAV) accessory technology. It provides a UAV parachute device and a UAV, comprising a cabin with a receiving cavity and an opening at the top communicating with the receiving cavity; a parachute body disposed within the receiving cavity, with parachute lines connected to the parachute body; an airbag assembly disposed at the bottom of the receiving cavity for inflating to push the parachute body towards the opening; a guide plate movably disposed within the receiving cavity and located between the airbag assembly and the parachute body, the airbag assembly pushing against the guide plate when inflated; and a buffer assembly disposed within the receiving cavity, the guide plate surrounding the buffer assembly, one end of the buffer assembly connected to the parachute lines and the other end fixed to the cabin. By setting the movable guide plate between the airbag assembly and the parachute body, parachute body jamming is effectively reduced, and the buffer assembly effectively reduces the impact of parachute opening, protecting the aircraft's fuselage structure.

Description

Technical Field

[0001] This application relates to the field of drone accessories technology, and in particular to a parachute device for drones and a drone. Background Technology

[0002] As a widely used flying device in fields such as aerial photography, surveying, and inspection, the flight safety of drones has always been a key concern for those skilled in the art. To protect drones from damage in the event of a malfunction, parachute systems are typically installed for safe descent in emergencies. Existing parachute compartments are mostly cylindrical structures. As the parachute expands and moves towards the opening under the propulsion of the airbag, it can easily become stuck at the compartment opening. Furthermore, when the airbag directly propels the parachute, the flexible fabric of the parachute can cause uneven force distribution, leading to skew and further increasing the risk of sticking. This results in poor parachute deployment and exit, affecting the effectiveness of the descent. Summary of the Invention

[0003] This application aims to improve at least one technical problem in the background art.

[0004] This application provides a parachute device for unmanned aerial vehicles, which includes a cabin, the cabin having a receiving cavity, and an opening communicating with the receiving cavity at the top of the cabin; An umbrella body is disposed within the receiving cavity, and an umbrella cord is connected to the umbrella body; An airbag assembly, disposed at the bottom of the receiving cavity, is used to inflate and propel the umbrella toward the opening; A guide plate is movably disposed within the receiving cavity and located between the airbag assembly and the umbrella body; the airbag assembly pushes against the guide plate when it inflates. A buffer assembly is disposed within the receiving cavity, and a guide plate is disposed around the outside of the buffer assembly. One end of the buffer assembly is connected to the parachute rope, and the other end is fixed to the cabin body.

[0005] According to some technical solutions of this application, the buffer assembly includes a housing, a friction block, and an elastic element. The housing is fixed on the cabin body, the friction block is slidably disposed inside the housing, a connection hole is provided on the top of the housing, one end of the paracord passes through the connection hole and is connected to the friction block, and the elastic element is disposed between the friction block and the housing.

[0006] According to some technical solutions of this application, a guide protrusion is provided inside the housing along its length direction, and a guide groove is provided on the friction block for cooperating with the guide protrusion.

[0007] According to some technical solutions of this application, the shape of the guide plate is adapted to the cross-sectional shape of the receiving cavity, and there is a gap between the edge of the guide plate and the inner wall of the receiving cavity.

[0008] According to some technical solutions of this application, the airbag assembly includes an airbag, an air inlet valve, and an air supply device. The airbag is folded and stored at the bottom of the receiving cavity. The air inlet valve is connected to the airbag, and the air supply device is connected to the airbag through the air inlet valve.

[0009] According to some technical solutions of this application, the cabin includes a conical cover and a cylindrical section, the conical cover is snapped together with the cylindrical section, the receiving cavity is disposed inside the cylindrical section, and the opening is formed at the top of the cylindrical section.

[0010] According to some technical solutions of this application, the bottom of the cabin is also provided with a quick-release structure, which includes a pin and a protrusion. One end of the pin is fixed to the bottom of the cabin, and the other end of the pin is used to cooperate with the socket on the aircraft. The protrusion is provided on the side wall of the pin and is used to abut against the inner wall of the socket on the aircraft.

[0011] According to some technical solutions of this application, multiple protrusions are provided along the circumference of the pin, and the multiple protrusions are used to engage with the corresponding grooves provided on the inner wall of the insertion hole when the pin is inserted into the insertion hole on the aircraft.

[0012] According to some technical solutions of this application, the end of the pin is provided with a magnet layer for adsorbing each other with the metal layer inside the socket of the aircraft.

[0013] This application also provides a drone, which includes an aircraft and a drone parachute device as described in the above technical solution, wherein the cabin is disposed on the aircraft.

[0014] The parachute device for unmanned aerial vehicles provided in this application has at least the following beneficial effects: by setting a movable guide plate between the airbag assembly and the parachute body, when the airbag assembly inflates, it first pushes against the guide plate, and the guide plate transmits the thrust to the parachute body, ensuring that the parachute body moves in a predetermined direction, effectively reducing parachute body jamming; at the same time, the overall structure is compact, significantly reducing the overall volume of the parachute device, reducing assembly difficulty, and improving maintenance convenience. Attached Figure Description

[0015] Figure 1 A structural diagram of a drone provided in an embodiment of this application from one angle; Figure 2 This is a structural diagram of the drone provided in an embodiment of this application from another angle; Figure 3 This is a schematic diagram of the internal structure of the cabin provided in an embodiment of this application; Figure 4 This is a structural schematic diagram of the internal structure of the cabin provided in an embodiment of this application from another angle.

[0016] In the attached diagram: 100 - cabin; 120 - cylindrical section; 110 - conical cover; 121 - receiving cavity; 300 - buffer assembly; 310 - shell; 400 - parachute; 311 - connection hole; 200 - aircraft; 500 - airbag. Detailed Implementation

[0017] The embodiments of this application are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0018] In the description of this application, it should be understood that the orientation descriptions, such as up, down, front, back, left, right, etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation or be constructed or operated in a specific orientation. Therefore, they should not be construed as limiting the present invention.

[0019] In the description of this application, unless otherwise expressly defined, terms such as "setup," "installation," and "connection" should be interpreted broadly, and those skilled in the art can reasonably determine the specific meaning of the above terms in this application in conjunction with the specific content of the technical solution.

[0020] The following is combined with Figures 1 to 4 Embodiments of the present invention will be described.

[0021] During flight, especially when a drone malfunctions and requires an emergency landing, the parachute 400 deploys in mid-air, causing the parachute lines to suddenly taut from a freely bent state, generating a tremendous impact force. This impact force is directly transmitted to the cabin 100 and the drone fuselage, potentially causing deformation of the cabin 100, structural damage to the drone, or even breakage of the parachute lines, endangering the landing safety of the aircraft. Furthermore, existing parachute systems suffer from loose structural layouts, large size, and interference between functional components, making them unsuitable for integration and installation on drones with limited space.

[0022] Based on the above, this application provides a parachute device for unmanned aerial vehicles, which includes a cabin 100, the cabin 100 having a receiving cavity 121, and the top of the cabin 100 having an opening communicating with the receiving cavity 121; the receiving cavity 121 is used to accommodate components such as the parachute body 400, the airbag assembly, the guide plate, and the buffer assembly 300.

[0023] The umbrella body 400 is disposed in the receiving cavity 121, and the umbrella body 400 is connected to the umbrella rope; one end of the umbrella rope is fixedly connected to the umbrella body 400, and the other end extends downward for connection with the buffer assembly 300.

[0024] An airbag assembly, located at the bottom of the receiving cavity 121, is used to inflate to propel the umbrella 400 toward the opening; it is used to inflate in an emergency to propel the umbrella 400 toward the opening. The airbag assembly is folded and stored in its deflated state to save space.

[0025] A guide plate is movably disposed within the receiving cavity 121 and located between the airbag assembly and the umbrella body 400. When the airbag assembly inflates, it pushes against the guide plate. The guide plate has a plate-like structure, with its lower surface in contact with the airbag assembly and its upper surface in contact with the umbrella body 400. When the airbag assembly inflates, its top pushes against the guide plate, causing the guide plate to move upward, thereby transmitting the thrust to the umbrella body 400.

[0026] A buffer assembly 300 is disposed within the receiving cavity 121. A guide plate surrounds the buffer assembly 300. One end of the buffer assembly 300 is connected to the parachute lines, and the other end is fixed to the cabin body 100. Specifically, the buffer assembly 300 is located approximately at the center of the receiving cavity 121 and extends upward in a columnar shape. The guide plate has an annular plate structure with a through hole in its center for the buffer assembly 300 to pass through. The guide plate is fitted around the buffer assembly 300 through this through hole. One end of the buffer assembly 300 is connected to the parachute lines, and the other end is fixedly connected to the bottom of the cabin body 100.

[0027] When the drone malfunctions and requires an emergency landing, the control system triggers the airbag assembly to inflate. The inflated airbag assembly pushes upward against the guide plate, which then evenly transmits the thrust to the parachute 400 above, propelling it towards the opening. The parachute 400 releases from the receiving cavity 121 and unfolds in the air, with the parachute lines gradually straightening. When the parachute lines are fully tensioned, the impact force is transmitted to the buffer assembly 300. The buffer assembly 300, through its internal structure, reduces the impact energy, thus minimizing the direct transmission of impact force to the cabin 100 and the drone fuselage, preventing damage to the aircraft.

[0028] Therefore, the guide plate ensures that the thrust of the airbag assembly acts on the parachute 400, preventing the parachute 400 from tilting or jamming due to localized stress. Secondly, the buffer assembly 300 effectively reduces the impact energy of the parachute lines during tension, protecting the structure of the UAV. Thirdly, the layout of the guide plate surrounding the outside of the buffer assembly 300 allows the buffer assembly 300 and the guide plate to share the same axial space, forming a compact nested structure that reduces the additional volume required for separate installations and significantly improves space utilization. Fourthly, all functional components are integrated inside the cabin 100, resulting in a simple overall structure that is easy to install on UAVs with limited space.

[0029] In some embodiments, the buffer assembly 300 includes a housing 310, a friction block, and an elastic element. The housing 310 is fixed to the cabin 100, the friction block is slidably disposed within the housing 310, a connection hole 311 is provided at the top of the housing 310, one end of the paracord passes through the connection hole 311 and is connected to the friction block, and the elastic element is disposed between the friction block and the housing 310.

[0030] The shell 310 is a cylindrical structure, and its bottom is fixed to the bottom of the compartment 100, specifically by means of screws, clips, or integral molding. The top of the shell 310 can be opened, forming an internal storage space.

[0031] The friction block has a columnar structure and is slidably disposed within the housing 310, allowing it to move up and down along the axial direction of the housing 310. An appropriate gap exists between the friction block and the inner wall of the housing 310 to ensure smooth sliding.

[0032] The top of the housing 310 has a connecting hole 311 that penetrates the top wall of the housing 310. One end of the paracord passes through the connecting hole 311 into the interior of the housing 310 and is fixedly connected to the top of the friction block. The connection method can be knotting, crimping, or using a connecting ring, etc.

[0033] The elastic element is disposed between the friction block and the housing 310. In this embodiment, the elastic element is a compression spring, with one end abutting against the bottom of the friction block and the other end abutting against the bottom of the inner wall of the housing 310. The elastic element is always in a compressed state, providing resistance to prevent the friction block from sliding out of the housing 310. In order to further reduce impact and absorb impact energy, damping can also be provided in the housing 310 accordingly, which will not be elaborated here.

[0034] When the paracord is tensioned, the tension is transmitted to the friction block through the connecting hole 311, causing the friction block to tend to slide outward (i.e. upward) of the housing 310. When the tension is greater than the preset resistance of the elastic element, the friction block overcomes the elastic force of the elastic element and slides upward, while further compressing the elastic element, thereby buffering the impact energy. Upon landing, the elastic force of the elastic element can reset or partially reset the friction block.

[0035] In some embodiments, the housing 310 has a guide protrusion along its length, and the friction block has a guide groove for engaging with the guide protrusion.

[0036] The inner wall of the housing 310 is provided with a guide protrusion along its length, and the friction block is provided with a guide groove that mates with the guide protrusion. The extension directions of both the guide protrusion and the guide groove are parallel to the axial direction of the housing 310.

[0037] In this embodiment, the guide protrusion is a ridge extending longitudinally along the inner wall of the housing 310. Correspondingly, a guide groove is formed on the side wall of the friction block, and its shape is adapted to the guide protrusion. The guide protrusion is embedded in the guide groove, and the two form a sliding fit.

[0038] In other embodiments, the cross-sections of the guide protrusions and guide grooves can also be dovetail-shaped, rectangular, or other structural forms that can provide guiding and anti-detachment functions. The number of guide protrusions can be one or more; in this embodiment, two symmetrical guide protrusions are provided to ensure force balance on the friction block.

[0039] When the friction block is subjected to the tension of the paracord, its movement is restricted to linear sliding only along the extension direction of the guide protrusion (i.e., the axial direction of the housing 310) because the guide protrusion is embedded in the guide groove. The guide protrusion provides lateral constraint to the friction block, preventing it from deflecting, tilting, or rotating around its own axis during sliding, ensuring that the friction block always moves in the correct posture. In addition, the guide groove can be a T-shaped structure, which also serves as an anti-detachment mechanism, preventing the friction block from coming out of the housing 310.

[0040] In some embodiments, the shape of the guide plate is adapted to the cross-sectional shape of the receiving cavity 121, and there is a gap between the edge of the guide plate and the inner wall of the receiving cavity 121. The shape of the guide plate is adapted to the cross-sectional shape of the receiving cavity 121. In this embodiment, the cross-section of the receiving cavity 121 is circular, therefore the guide plate is circular. A gap is provided between the edge of the guide plate and the inner wall of the receiving cavity 121. This gap serves as an exhaust channel and also reduces frictional contact.

[0041] When the airbag assembly pushes the guide plate upward, the air above the guide plate needs to be expelled in time; otherwise, it will be compressed, creating air resistance and hindering the guide plate's movement. By setting a gap, the air above the guide plate can flow downward quickly through the gap and be expelled below the guide plate, thereby reducing air resistance. At the same time, due to the existence of the gap, the edge of the guide plate does not directly contact the inner wall of the cabin 100, reducing sliding friction and minimizing the guide plate's movement resistance. Even if the guide plate deviates slightly during movement, the gap provides a certain amount of tolerance to prevent the guide plate from jamming.

[0042] In some embodiments, the airbag assembly includes an airbag 500, an air inlet valve, and an air supply device. The airbag 500 is folded and stored at the bottom of the receiving cavity 121. The air inlet valve is connected to the airbag 500, and the air supply device is connected to the airbag 500 through the air inlet valve.

[0043] The airbag 500 is made of a flexible yet strong material, such as rubber, silicone, or fabric coated with an airtight layer. In its initial state, the airbag 500 is folded and stored at the bottom of the receiving cavity 121. The folding method can be a Z-shaped fold, a rolled fold, or other suitable folding method to minimize the space occupied.

[0044] The air intake valve is connected to the airbag 500 and is used to control the entry of gas into the airbag 500. The air intake valve can be in the form of a solenoid valve, a mechanical valve, or a disposable rupture disc. In this embodiment, a solenoid valve is used, which can be opened by an electrical signal controlled by the control system.

[0045] The gas supply device is connected to the airbag 500 via an air inlet valve. The gas supply device can be a high-pressure gas tank pre-filled with compressed gases such as nitrogen or carbon dioxide. Alternatively, it can be a chemical gas generator that produces a large amount of gas through the combustion of ignited propellant. This embodiment uses a miniature high-pressure gas tank, which is compact and suitable for use with drones.

[0046] When the parachute is deployed, the air intake valve is energized and opens, allowing high-pressure gas from the air supply device to rapidly inflate the airbag 500. The airbag 500 expands rapidly from its folded state in a very short time, increasing in volume several tens of times, thus generating sufficient thrust to push the guide plate and the parachute body 400. After the parachute body 400 deploys, the air intake valve can be closed to maintain the inflated state of the airbag 500.

[0047] Thus, through the coordination of the air intake valve and the air supply device, the airbag 500 is rapidly inflated, ensuring that the parachute 400 can deploy in a timely manner to meet the time requirements for emergency landing of the drone. The airbag 500 is folded and stored at the bottom of the receiving cavity 121, making full use of the bottom space of the cabin 100 without occupying additional volume. The air supply device uses a miniature high-pressure air tank, which has a simple and reliable structure, and a fast inflation speed, making it suitable for drone usage scenarios.

[0048] In some embodiments, the cabin 100 includes a conical cover 110 and a cylindrical section 120, the conical cover 110 being snap-fitted to the cylindrical section 120, the receiving cavity 121 being disposed within the cylindrical section 120, and the opening being formed at the top of the cylindrical section 120.

[0049] The cylindrical segment 120 is a cylindrical structure, and its interior forms the main part of the receiving cavity 121. The top of the cylindrical segment 120 is open, forming an opening. The bottom of the cylindrical segment 120 is closed, for mounting the airbag assembly and the cushioning assembly 300.

[0050] The conical cover 110 is conical in shape, with its lower edge matching the top edge of the cylindrical section 120. A snap-fit ​​structure is provided at the connection between the conical cover 110 and the cylindrical section 120. Specifically, the edge of the conical cover 110 has multiple hooks, and the top edge of the cylindrical section 120 has corresponding multiple slots. When the conical cover 110 is fastened onto the cylindrical section 120, the hooks engage with the slots, achieving a fixed connection between the two.

[0051] The inner wall of the conical cover 110 forms a conical transition surface, which smoothly connects with the inner wall of the cylindrical section 120 to form a complete receiving cavity 121. The conical transition surface gradually widens from the bottom to the opening, which helps guide the parachute 400 when it exits the cabin.

[0052] During assembly, first insert the parachute body 400, airbag assembly, guide plate, and buffer assembly 300 into the cylindrical section 120 in sequence. Then, align the conical cover 110 with the top of the cylindrical section 120 and press it down to engage the hooks in the slots, completing the closure of the cabin 100. When maintenance or replacement of internal components is required, simply pull the conical cover 110 upwards to disengage the hooks from the slots, then remove the conical cover 110 to expose the internal components for operation.

[0053] In some embodiments, the bottom of the cabin 100 is also provided with a quick-release structure, which includes a pin and a protrusion. One end of the pin is fixed to the bottom of the cabin 100, and the other end of the pin is used to engage with a socket on the aircraft 200. The protrusion is provided on the side wall of the pin and is used to abut against the inner wall of the socket on the aircraft 200.

[0054] The pin is a columnar structure, with its upper end fixed to the bottom of the cabin 100, and can be secured by threaded connection, welding, or integral molding. The other end of the pin is a free end, used to mate with a socket on the UAV. The diameter of the pin is slightly smaller than the diameter of the socket for easy insertion.

[0055] The protrusion is located on the side wall of the pin and is a partially raised structure. The protrusion can be an elastic arm integrally formed with the pin, or it can be an elastic body, such as a rubber pad or spring sheet, embedded in the side wall of the pin. The protrusion abuts against the inner wall of the insertion hole, generating a certain clamping force through elastic deformation to prevent the pin from easily dislodging.

[0056] During installation, align the pin at the bottom of the housing 100 with the socket on the drone body and push it in firmly. During insertion, the protrusion is compressed by the inner wall of the socket, causing elastic deformation and allowing the pin to enter smoothly. Once the pin is fully inserted, the elastic restoring force of the protrusion causes it to press tightly against the inner wall of the socket, generating sufficient friction to secure the housing 100 to the drone. For disassembly, pull the pin downwards forcefully; the protrusion will deform again, causing the pin to dislodge from the socket.

[0057] The simple pin-and-hole connection enables quick assembly and disassembly between the cabin 100 and the UAV without any tools, facilitating on-site maintenance and emergency replacement. The friction provided by the protrusions prevents accidental pin dislodgement due to flight vibrations, ensuring reliable connection. The overall structure is simple and inexpensive.

[0058] In some embodiments, a plurality of protrusions are provided along the circumference of the pin, and the plurality of protrusions are used to engage with grooves corresponding to the inner wall of the insertion hole when the pin is inserted into the insertion hole on the aircraft 200.

[0059] Multiple protrusions are provided along the circumference of the pin. In this embodiment, four protrusions are provided, evenly distributed along the circumference. The protrusions are hemispherical or wedge-shaped protrusions made of elastic material. Correspondingly, the inner wall of the socket on the drone is provided with multiple grooves, the position and number of which correspond to the protrusions. The grooves are partial depressions, and their shapes are adapted to the protrusions.

[0060] When the pin is inserted into the socket, the protrusion is first compressed by the inner wall of the socket, resulting in elastic deformation. As the pin continues to be inserted until the protrusion aligns with the groove, the protrusion springs up under the action of elastic restoring force and locks into the groove. For disassembly, sufficient pulling force needs to be applied to make the protrusion overcome the resistance of the groove edge and dislodge, or the protrusion can be pushed out of the groove by pressing it.

[0061] In some embodiments, the end of the pin is provided with a magnetic layer for attracting to a metal layer inside the socket of the aircraft 200. Correspondingly, the bottom of the socket on the drone is provided with a metal layer, which can be made of ferromagnetic materials such as iron, cobalt, or nickel, or it can be another magnetic layer with opposite polarity to the magnetic layer at the end of the pin. During installation, when the pin is brought close to the socket, the magnetic force between the magnetic layer and the metal layer guides the pin to automatically align with the center of the socket and generates a certain attraction, making it easier to insert the pin. Once the pin is inserted into place, the magnetic layer and the metal layer are tightly attracted to each other.

[0062] This application also provides a drone, which includes a drone parachute device as disclosed in any of the above embodiments, wherein the cabin 100 is disposed on the aircraft 200. The drone includes the aircraft 200 and the parachute device. The aircraft 200 may be a multi-rotor drone, a fixed-wing drone, or other types of unmanned aerial vehicles 200. In this application embodiment, a quadcopter drone is used as an example for description. Since the drone uses the drone parachute device disclosed in the embodiments of this application, in normal flight, the parachute body 400 is folded and stored inside the cabin 100, and the quick-release structure firmly fixes the cabin 100 to the top of the aircraft 200 without interfering with the normal flight of the aircraft 200. When the aircraft 200 experiences power failure, attitude loss, collision, or other malfunctions in the air and needs to make an emergency landing, the flight control system detects the abnormality and triggers the parachute device. The airbag assembly rapidly inflates and pushes the guide plate to eject the parachute body 400 from the opening of the cabin 100. After the parachute 400 fully deploys in the air, it suspends the aircraft 200 via parachute lines and a shock absorber 300. At the moment the parachute lines tighten, the shock absorber 300 absorbs the impact energy, protecting the aircraft 200's fuselage structure from damage. The aircraft 200 descends slowly under the parachute's pull and lands safely. After landing, the quick-release mechanism can be pressed or pulled out to detach the parachute system from the aircraft 200 for inspection and maintenance. After replacing the parachute 400, it can be used again.

[0063] Therefore, this UAV combines the technical advantages of the UAV parachute device disclosed in the embodiments of this application, integrating the aforementioned parachute device onto the UAV to achieve the UAV's emergency safe landing function, effectively protecting the expensive UAV equipment and the mission payload. The quick-release structure allows for rapid installation and replacement of the parachute compartment device, facilitating on-site maintenance and reuse, and reducing operating costs. The buffer component 300 effectively reduces the impact of parachute opening, protecting the aircraft 200's fuselage structure. The guide plate and conical compartment 100 design ensure smooth parachute exit from the compartment, improving the success rate of parachute opening. The overall structure is compact, highly reliable, and easy to maintain.

[0064] The preferred embodiments of the present invention have been described in detail above, but the present disclosure is not limited to the embodiments described. Those skilled in the art can make various equivalent modifications or substitutions without departing from the spirit of the present invention, and these equivalent modifications or substitutions are all included within the scope defined by the claims of the present disclosure.

Claims

1. A parachute device for unmanned aerial vehicles (UAVs), characterized in that: include: The cabin (100) has a receiving cavity (121) and the top of the cabin (100) has an opening communicating with the receiving cavity (121); The umbrella body (400) is disposed within the receiving cavity (121), and the umbrella body (400) is connected to the umbrella rope; An airbag assembly, disposed at the bottom of the receiving cavity (121), is used to inflate to push the umbrella body (400) toward the opening; A guide plate is movably disposed within the receiving cavity (121) and located between the airbag assembly and the umbrella body (400), and the airbag assembly pushes against the guide plate when it inflates; A buffer assembly (300) is disposed within the receiving cavity (121), and a guide plate is disposed around the buffer assembly (300). One end of the buffer assembly (300) is connected to the parachute rope, and the other end is fixed to the cabin body (100).

2. The parachute device for unmanned aerial vehicles according to claim 1, characterized in that: The buffer assembly (300) includes a housing (310), a friction block, and an elastic element. The housing (310) is fixed on the cabin (100). The friction block is slidably disposed inside the housing (310). A connection hole (311) is provided on the top of the housing (310). One end of the paracord passes through the connection hole (311) and is connected to the friction block. The elastic element is disposed between the friction block and the housing (310).

3. The parachute device for unmanned aerial vehicles according to claim 2, characterized in that: The housing (310) has a guide protrusion along its length, and the friction block has a guide groove for cooperating with the guide protrusion.

4. The parachute device for unmanned aerial vehicles according to claim 1, characterized in that: The shape of the guide plate is adapted to the cross-sectional shape of the receiving cavity (121), and there is a gap between the edge of the guide plate and the inner wall of the receiving cavity (121).

5. The parachute device for unmanned aerial vehicles according to claim 1, characterized in that: The airbag assembly includes an airbag (500), an air inlet valve, and an air supply device. The airbag (500) is folded and stored at the bottom of the receiving cavity (121). The air inlet valve is connected to the airbag (500), and the air supply device is connected to the airbag (500) through the air inlet valve.

6. The parachute device for unmanned aerial vehicles according to claim 1, characterized in that: The cabin (100) includes a conical cover (110) and a cylindrical section (120), the conical cover (110) being snapped together with the cylindrical section (120), the receiving cavity (121) being located inside the cylindrical section (120), and the opening being formed at the top of the cylindrical section (120).

7. The parachute device for unmanned aerial vehicles according to claim 1, characterized in that: The bottom of the cabin (100) is also provided with a quick-release structure, which includes a pin and a protrusion. One end of the pin is fixed to the bottom of the cabin (100), and the other end of the pin is used to cooperate with the socket on the aircraft (200). The protrusion is provided on the side wall of the pin and is used to abut against the inner wall of the socket on the aircraft (200).

8. The parachute device for unmanned aerial vehicles according to claim 7, characterized in that: The protrusions are provided in multiple ways along the circumference of the pin, and the multiple protrusions are used to engage with the corresponding grooves provided on the inner wall of the insertion hole when the pin is inserted into the insertion hole on the aircraft (200).

9. The parachute device for unmanned aerial vehicles according to claim 7, characterized in that: The end of the pin is provided with a magnetic layer for adsorbing with the metal layer inside the socket of the aircraft (200).

10. An unmanned aerial vehicle (UAV), characterized in that: It includes an aircraft (200) and a parachute device for a drone as described in any one of claims 1-9, wherein the cabin (100) is disposed on the aircraft (200).

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