Reusable emergency parachute device for drones

Abstract

This utility model discloses a reusable emergency parachute device for unmanned aerial vehicles (UAVs), including UAV components and a support shell located on one side. The device offers two implementation methods: First, the support shell houses the parachute, and a torsion spring and locking mechanism lock the shell's top cover; when the unlocking mechanism is triggered, the torsion spring drives the top cover to pop open and release the parachute. Second, the support shell houses an air tank and a valve assembly with a pressure balancing channel, connected to a launch tube housing the parachute; when triggered, the valve opens, high-pressure gas forces open the launch tube cover and ejects the parachute. Both methods enable rapid and reliable parachute deployment under emergency commands, and the core mechanisms can be manually reset and reused, significantly improving the safety and economy of the UAV.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a reusable emergency parachute device for UAVs. Background Technology

[0002] In the field of drone safety technology, emergency parachute systems are key crash mitigation devices that can automatically activate when an aircraft malfunctions or goes out of control. By deploying a parachute, they effectively buffer the descent speed, preventing the drone from falling rapidly and reducing the risk of collisions with people, property, and the environment.

[0003] However, existing emergency parachute technology still has significant drawbacks: the most prominent problem is that it is usually designed for single use. Once triggered, the parachute deploys and cannot be easily recovered or reset, and the device is often damaged or cannot be reloaded. This makes it not only costly to use—requiring the replacement of the entire parachute module or complex return-to-factory repairs for each trigger, which is a heavy economic burden for commercial drones, logistics drones, and industrial inspection agencies operating at high frequency and long endurance—but also results in poor mission continuity: the system fails after a single trigger and cannot provide continuous support for continuous multi-mission execution or within the same operational cycle, reducing the overall system reliability and operational efficiency.

[0004] Therefore, the industry urgently needs an emergency parachute device that can be quickly reset and reused, which can achieve low-cost maintenance and continuous support capabilities while ensuring reliable triggering and deployment, thereby truly promoting the development of UAV safety systems towards efficiency, economy and sustainability. Summary of the Invention

[0005] This invention addresses the aforementioned problems with the repeated use of self-rescue mechanisms in drones by proposing a reusable emergency parachute device for drones. This device enables rapid and reliable automatic deployment of the parachute upon receiving an emergency command, and allows for easy reset and reuse after deployment. This significantly improves the crash protection capability of drones and reduces operating costs.

[0006] The objective of this invention is achieved through the following technical solution: a reusable emergency parachute device for unmanned aerial vehicles (UAVs), comprising a UAV component, a first supporting shell on one side of the UAV component, a shell cover rotatably mounted on the first supporting shell, and a parachute placed inside the first supporting shell; the first supporting shell contains an elastic element and a locking mechanism that restricts the opening of the first supporting shell, the locking mechanism locking the first supporting shell so that the elastic element is in a compressed and stored state, and the first supporting shell also contains an unlocking mechanism for releasing the locking mechanism from the first supporting shell; the shell cover, when closed, can keep the parachute inside the first supporting shell in an undeployed state.

[0007] Preferably, the outer side wall of the first support housing is provided with a hinge slot, the upper cover of the housing is provided with a hinge pin coaxially installed inside the hinge slot, the upper cover of the housing is provided with a limiting plate facing the interior of the first support housing, the limiting plate is provided with a limiting hole, and the clamping mechanism can be clamped inside the limiting hole.

[0008] Preferably, the elastic element is a torsion spring; the first support housing has a bearing plate inside, the upper surface of the bearing plate has a torsion arm limiting shell and a shaft support plate, and the side wall of the shaft support plate has a torsion spring limiting shaft; the spring body of the torsion spring is installed on the torsion spring limiting shaft, one torsion arm of the torsion spring is locked inside the torsion arm limiting shell and the other torsion arm of the torsion spring abuts against the lower surface of the housing cover.

[0009] Preferably, the clamping mechanism includes a pin support block, a clamping pin shaft, a spring pressing shaft, a first spring, and a copper sleeve body. The lower surface of the bearing plate is provided with a plurality of pin support blocks, and a clamping pin shaft is slidably arranged inside the plurality of pin support blocks. A spring pressing shaft is provided radially outward from the clamping pin shaft. A first spring is provided between the spring pressing shaft and any one of the pin support blocks. The end of the clamping pin shaft is inserted into the interior of the limiting hole. A copper sleeve body is also rotatably provided on the spring pressing shaft. The outer surface of the copper sleeve body abuts against the unlocking mechanism.

[0010] Preferably, the unlocking mechanism includes an eccentric wheel, a gear connecting shaft, a driven large gear, a copper sleeve body, a motor support plate, a first drive motor, and a drive pinion. Each pin support block also has a pin sleeve at its bottom. The eccentric wheel has a gear connecting shaft rotatably connected to the pin sleeve. One end of the gear connecting shaft is fixedly connected to the driven large gear. The eccentric wheel extends radially upwards with a rectangular protrusion for pushing the copper sleeve body. The first support housing also has a motor support plate inside. The first drive motor is mounted on the motor support plate. The end of the first drive motor's shaft has a drive pinion, which meshes with the driven large gear.

[0011] Preferably, the drone component has a second support shell on one side, and an air tank is provided inside the second support shell. The air tank's nozzle is connected to one end of a valve assembly, and the other end of the valve assembly is connected to a launch tube. A parachute is provided inside the launch tube, and a cover plate is detachably provided at the end of the launch tube.

[0012] Preferably, the valve assembly includes a first valve body, a second valve body, a diaphragm body, a drive clamp, an iron drive rod, a valve body cover, an electromagnet, and a second spring. The first valve body has a first flow channel and a second flow channel inside, and the gas outlet of the gas storage tank is connected to the inside of the first flow channel. The second valve body has a diaphragm body and a drive clamp holding the diaphragm body inside, and an iron drive rod is located at the center of the drive clamp. The valve body cover is connected to the top of the second valve body. When the iron drive rod is not magnetically attracted, the diaphragm body is pressed against the top of the first flow channel. The valve body cover has an electromagnet inside, and the electromagnet has a clearance hole inside. The iron drive rod is slidably disposed inside the clearance hole. The clearance hole has a second spring inside, and the two ends of the second spring abut against the top of the iron drive rod and the inside of the valve body cover, respectively.

[0013] Preferably, the first valve body is further provided with a first air pressure balance channel inside, and the second valve body is further provided with a second air pressure balance channel connected to the first air pressure balance channel inside, with the other end of the second air pressure balance channel connected to the top of the diaphragm body.

[0014] Preferably, the outer surface of the launch tube is provided with an annular magnet, the cover plate is made of iron and the side wall of the cover plate is attached to the annular magnet; the air inlet of the gas storage tank is threaded with a sealing cap.

[0015] Preferably, the UAV component includes a UAV body, an arm body, a motor support sleeve, a second drive motor, and a rotor body. The outer side wall of the UAV body is provided with a plurality of arm bodies, each arm body has a motor support sleeve at its end, each motor support sleeve has a second drive motor inside, and each second drive motor has a rotor body at its shaft end.

[0016] Compared with the prior art, the present invention has the following beneficial effects: 1. Achieving reliable locking and rapid electromechanical triggering, ensuring reusability. A torsion spring is pre-placed on the support plate, providing a stable and direct power source for release by a torsion arm against the inside of the housing cover. The locking mechanism utilizes the spring force of the first spring to actively engage the locking pin in the limiting hole of the housing cover, achieving a purely mechanical passive locking with high reliability. The unlocking mechanism uses a motor-driven gear transmission to ultimately control an eccentric wheel to push the copper sleeve body on the locking mechanism. The continuous rotational motion of the motor is converted into a precise linear displacement sufficient to overcome the spring force of the first spring, thereby pulling out the locking pin. This scheme, which coordinates three motion forms—rotational energy storage, linear locking, and rotational unlocking (via an eccentric cam)—within a compact space, ensures secure locking under normal conditions, rapid triggering by an electrical signal in emergencies, and automatic re-engagement of the locking pin with the limiting hole by simple manual pressing after release. It perfectly achieves the comprehensive goals of rapid response, reliable operation, and convenient reusability.

[0017] 2. Compact structure and efficient power transmission, suitable for lightweight UAV platforms. The torsion spring's limiting shaft is fixed to the shaft support plate, one torsion arm is secured to the torsion arm limiting shell, and the other torsion arm acts directly on the shell cover. This layout makes the torsion spring's energy storage and release torque direct and efficient, with a short energy transmission path, ensuring that the shell cover can be instantly opened, creating an initial high speed for parachute deployment. The first spring of the locking mechanism continuously provides locking force, ensuring that it will not be accidentally unlocked during flight vibrations. During unlocking, the rectangular protrusion of the eccentric wheel pushes the copper sleeve body, utilizing the principles of leverage and sliding friction, allowing the first drive motor to complete the unlocking action with only a small torque for a short time, reducing the requirements for motor power and energy consumption.

[0018] 3. A first pressure balancing channel is provided on the first valve body, and a corresponding second pressure balancing channel is provided on the second valve body. These two channels guide the high-pressure gas in the gas storage tank to the upper chamber of the diaphragm body. In the standby state with the valve closed, the gas pressure on the upper and lower surfaces of the diaphragm body is basically balanced. Therefore, the force used to keep the valve closed only needs to overcome the elastic force of the second spring that deforms and seals the diaphragm body, without having to contend with enormous gas pressure; this allows for the use of a small, low-power electromagnet to control the opening and closing of the valve. After the electromagnet is energized, its magnetic attraction only needs to overcome the elastic force of the second spring to pull the iron drive rod, thereby quickly opening the valve. This structure achieves both long-term reliable sealing of high-pressure gas and triggering with a low-power, high-response electrical signal, which is of great value in applications where UAVs are extremely sensitive to weight and power consumption.

[0019] 4. A pre-filled gas tank serves as the power source, connected to the launch tube via a valve assembly. Once the valve opens, the high-pressure gas is released instantaneously, generating extremely high pressure within the launch tube. This provides the parachute with exceptionally strong and rapid ejection force, effectively buying precious time for parachute deployment during the drone's rapid descent. The launch tube opening is sealed using a ring magnet to attract an iron cover plate. This design creatively utilizes the normally closed yet easily open characteristic of magnetic attraction: under normal conditions, the magnetism reliably seals the outlet, preventing debris from entering; during ejection, the internal high-pressure gas instantly and easily overcomes the magnetism to open the iron cover plate, without any unlocking delay or interference from mechanical latches, ensuring instantaneous unobstructed ejection. After use, simply replace the parachute, replace the iron cover plate, and replenish the gas tank to reset the system; the maintenance process is clear.

[0020] 5. Two optional emergency ejection schemes are provided to adapt to different usage needs. Mechanical ejection (first embodiment): simple structure and convenient reset, suitable for small and medium-sized UAVs and routine operation scenarios; High-pressure gas ejection (second embodiment): high thrust and fast deployment speed, suitable for high-speed flight, heavy UAVs, or occasions with extremely strict requirements for parachute opening time. Both schemes are reusable, allowing users to flexibly configure them according to actual needs. This utility model fundamentally solves the pain point of traditional emergency parachutes being disposable, not only improving the safety redundancy of a single unit in continuous missions but also significantly reducing long-term maintenance costs and spare parts burden. It has positive significance for promoting the large-scale commercial application of industrial-grade UAVs in high-frequency application scenarios such as logistics, inspection, and surveying. Attached Figure Description

[0021] Figure 1 This is a perspective view of the first embodiment of the present utility model; Figure 2 This is a perspective view of the first embodiment of the present utility model; Figure 3This is a partial perspective view of the first embodiment of the present invention; Figure 4 This is a partial perspective view of the first support shell region in the first embodiment of this utility model; Figure 5 This is a partial cross-sectional view of the first support shell region in the first embodiment of this utility model; Figure 6 This is a partial cross-sectional view of the first support shell region in the first embodiment of this utility model; Figure 7 This is a partial cross-sectional view of the first support shell region of the present invention in the first embodiment; Figure 8 This is a perspective view of the second embodiment of the present utility model; Figure 9 This is a perspective view of the second embodiment of the present utility model; Figure 10 This is a schematic diagram of the image acquisition device of this utility model; Figure 11 This is a partial cross-sectional view of the second support shell region in the second embodiment of this utility model.

[0022] Markings in the diagram: 1. UAV component; 11. UAV body; 12. Arm body; 13. Motor support sleeve; 14. Second drive motor; 15. Rotor body; 2. First support housing; 20. Hinge slot; 21. First support housing; 211. Bearing plate; 221. Torsion arm limiting housing; 222. Shaft support plate; 223. Torsion spring limiting shaft; 22. Second support housing; 3. Housing top cover; 31. Hinge pin; 32. Limiting plate; 321. Limiting hole; 4. Elastic element; 5. Clamping mechanism; 51. Pin support block; 511. Pin sleeve; 52. Clamping pin; 521. Spring clamping shaft; 53. First spring; 54. Copper sleeve. 6. Body; 6. Unlocking mechanism; 61. Eccentric wheel; 611. Gear connecting shaft; 612. Rectangular protrusion; 62. Driven large gear; 63. Motor support plate; 64. First drive motor; 65. Drive pinion; 7. Gas tank; 8. Valve assembly; 81. First valve body; 811. First flow channel; 812. Second flow channel; 813. First air pressure balance flow channel; 82. Second valve body; 822. Second air pressure balance flow channel; 83. Membrane body; 84. Drive clamp plate; 85. Iron drive rod; 86. Valve body cover; 87. Electromagnet; 871. Clearance through hole; 88. Second spring; 9. Launch tube; 90. Cover plate; 91. Ring magnet; 10. Parachute. Detailed Implementation

[0023] The present invention will be further described below with reference to the embodiments shown in the accompanying drawings: like Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, a reusable emergency parachute device for unmanned aerial vehicles (UAVs) is disclosed in a first embodiment. The UAV component 1 has a first support housing 21 on one side. A rotatable upper cover 3 is mounted on the first support housing 21, and a parachute 10 is placed inside the first support housing 21. An elastic element 4 and a locking mechanism 5 that restricts the opening of the first support housing 21 are provided inside the first support housing 21. The locking mechanism 5 locks the first support housing 21, causing the elastic element 4 to be in a compressed, stored state.

[0024] Please continue to refer to the reference. Figure 4 and Figure 5 The outer wall of the first support housing 21 is provided with a hinge slot 20. The housing cover 3 is coaxially mounted in the hinge slot 20 through hinge pins 31 provided on both sides, so that the housing cover 3 can rotate relative to the first support housing 21 around the axis of the hinge pins 31 to realize opening and closing. The housing cover 3 is provided with a limiting plate 32 facing the inside of the first support housing 21. The limiting plate 32 is provided with a limiting hole 321, and the clamping mechanism 5 can be locked inside the limiting hole 321.

[0025] In the first embodiment, the elastic element 4 is a torsion spring; the first support housing 21 is provided with a bearing plate 211 inside, the upper surface of the bearing plate 211 is provided with a torsion arm limiting shell 221 and a shaft support plate 222, and a torsion spring limiting shaft 223 is horizontally fixed on the side wall of the shaft support plate 222; the spring body of the torsion spring is installed on the torsion spring limiting shaft 223, one torsion arm of the torsion spring is inserted into and fixed inside the torsion arm limiting shell 221, and the other torsion arm extends upward and abuts against the inner lower surface of the housing cover 3.

[0026] With this configuration, when the housing cover 3 is closed and pressed, the torsion arm of the torsion spring is compressed, causing the entire torsion spring to be in a torsional state of stored energy. Once the lock on the housing cover 3 is released, the energy stored in the torsion spring will be released rapidly, driving the housing cover 3 to spring upwards quickly around the hinge pin 31.

[0027] In the first embodiment, the interior of the first support housing 21 is further provided with an unlocking mechanism 6 for releasing the locking mechanism 5 from the limiting position between the first support housing 21 and the locking mechanism 5; the upper cover 3 of the housing is in the closed state and can press down the parachute 10 inside the first support housing 21 in an undeployed state. In the first embodiment, to ensure reliable locking of the housing cover 3 in non-emergency situations, the locking mechanism 5 includes a pin support block 51, a locking pin 52, a spring clamping shaft 521, a first spring 53, and a copper sleeve body 54. A plurality of pin support blocks 51 are integrally formed on the lower surface of the bearing plate 211, with their central holes coaxial and jointly supporting a locking pin 52. The locking pin 52 extends radially outward from the spring clamping shaft 521, and a first spring 53 is sleeved between the spring clamping shaft 521 and one of the pin support blocks 51. Under the elastic force of the first spring 53, the end of the locking pin 52 is continuously pushed against the limiting plate 32 of the housing cover 3 and inserted into the limiting hole 321. A copper sleeve body 54 is rotatably mounted on the spring clamping shaft 521, and the outer cylindrical surface of the copper sleeve body 54 contacts the side of the rectangular protrusion 612 of the eccentric wheel 61.

[0028] During implementation, when a reset device is needed, the parachute 10 is inserted back into the first support housing 21. With the unlocking mechanism 6 in the unlocked state, the housing cover 3 is manually pressed down. When the housing cover 3 is fully closed, the unlocking mechanism 6 returns to its initial position. Under the action of the first spring 53, the end of the locking pin 52 quickly springs into the limiting hole 321, completing the mechanical locking. At this time, the torsion spring 4 is compressed and stores energy, preventing the housing cover 3 from opening on its own.

[0029] In the first embodiment, please continue to refer to the reference. Figure 5 , Figure 6 and Figure 7 The unlocking mechanism 6 includes an eccentric wheel 61, a gear connecting shaft 611, a driven large gear 62, a copper sleeve body 54, a motor support plate 63, a first drive motor 64, and a drive pinion 65. Each pin support block 51 has a pin sleeve 511 at its bottom. The eccentric wheel 61 has a gear connecting shaft 611 rotatably connected to the pin sleeve 511. One end of the gear connecting shaft 611 is fixedly connected to the driven large gear 62. The eccentric wheel 61 extends radially and has a rectangular protrusion 612 for pushing the copper sleeve body 54. The first support housing 21 also has a motor support plate 63 inside. The first drive motor 64 is mounted on the motor support plate 63. The end of the shaft of the first drive motor 64 has a drive pinion 65, which meshes with the driven large gear 62.

[0030] During implementation, when the UAV's flight control system detects an emergency (such as motor failure or attitude loss), it sends a start signal to the first drive motor 64. The first drive motor 64 rotates forward, driving the gear connecting shaft 611 and the eccentric wheel 61 to rotate through the meshing of the drive pinion 65 and the driven gear 62. During rotation, the rectangular protrusion 612 on the eccentric wheel 61 pushes the copper sleeve body 54 in contact with it. Since the copper sleeve body 54 is restricted to the spring-loaded shaft 521, this thrust is converted into a thrust that slides the locking pin 52 as a whole. This thrust overcomes the elastic force of the first spring 53, completely pulling the end of the locking pin 52 out of the limiting hole 321 of the limiting plate 32.

[0031] Subsequently, once the locking pin 52 disengages from the limiting hole 321, the locking of the housing cover 3 is released. At this time, the torsion spring 4, which is in a compressed and stored state, instantly releases its stored elastic energy. The torsion arm against the lower surface of the housing cover 3 generates a strong torque, driving the housing cover 3 to rapidly spring upward around the hinge pin 31 in a very short time.

[0032] Because the parachute 10's parachute lines are securely connected to the drone's body or the first support shell 21, when the shell cover 3 is popped open, the internal constraints disappear, and the folded parachute 10 is thrown upwards under inertia and rapidly unfolds under air resistance, thus providing aerodynamic drag for the drone and achieving a slow descent.

[0033] In the first embodiment, the UAV component 1 includes a UAV body 11, an arm body 12, a motor support sleeve 13, a second drive motor 14, and a rotor body 15. The outer side wall of the UAV body 11 is provided with four arm bodies 12. Each arm body 12 is provided with a motor support sleeve 13 at its end. Each motor support sleeve 13 is provided with a second drive motor 14 inside. Each second drive motor 14 is provided with a rotor body 15 at its shaft end.

[0034] During implementation, the output shaft of the second drive motor 14 drives the rotor body 15 to rotate, and the rotor body 15 provides the lift and thrust required for the UAV to fly during the rotation.

[0035] Please continue to refer to this. Figure 8 , Figure 9 , Figure 10 and Figure 11In the second embodiment of this utility model, the only difference from the first embodiment is the drone component 1. Other components are as follows: a second support housing 22 is provided on one side of the drone component 1. An air tank 7 is located inside the second support housing 22. The air outlet of the air tank 7 is connected to one end of a valve assembly 8, and the other end of the valve assembly 8 is connected to a launch tube 9. The launch tube 9 is a cylinder closed at one end and open at the other, with its internal cavity used to accommodate a folded parachute 10. An iron cover plate 90 is magnetically attached to the open end of the launch tube 9. Specifically, a ring magnet 91 is embedded in the outer edge of the open end of the launch tube 9, and the iron cover plate 90 tightly seals the opening under magnetic force. A sealing cap is threaded onto the inflation port of the air tank 7.

[0036] Please continue to refer to this. Figure 11 The valve assembly 8 includes a first valve body 81, a second valve body 82, a diaphragm body 83, a drive clamping plate 84, an iron drive rod 85, a valve body cover 86, an electromagnet 87, and a second spring 88. The first valve body 81 has a first flow channel 811 and a second flow channel 812 inside. The gas outlet of the gas storage tank 7 is connected to the interior of the first flow channel 811. The second valve body 82 has a diaphragm body 83 inside and a drive clamping plate 84 holding the diaphragm body 83. An iron drive rod 85 is located at the center of the drive clamping plate 84. The valve body cover 86 is connected to the top of the second valve body 82. When the iron drive rod 85 is not magnetically attracted, the diaphragm body 83 is pressed against the top of the first flow channel 811. An electromagnet 87 is provided inside the valve body cover 86. An clearance through hole 871 is provided inside the electromagnet 87. The iron drive rod 85 is slidably disposed inside the clearance through hole 871. A second spring 88 is provided inside the clearance through hole 871. The two ends of the second spring 88 abut against the top of the iron drive rod 85 and the inside of the valve body cover 86, respectively. In the second embodiment, to ensure the sealing reliability and opening sensitivity of the valve under high pressure, a first pressure balancing flow channel 813 is also machined inside the first valve body 81. One end of the first pressure balancing flow channel 813 is connected to the high-pressure first flow channel 811, and the other end of the first pressure balancing flow channel 813 is connected to the cavity of the second valve body 82. Correspondingly, a second pressure balancing flow channel 822 is machined inside the second valve body 82, connecting the first pressure balancing flow channel 813 to the space above the diaphragm body 83.

[0037] With this configuration, the high-pressure gas in the gas tank 7 not only acts on the lower part of the diaphragm body 83 in an attempt to open it, but also acts on the upper part of the diaphragm body 83 through the pressure balance channels (813, 822). This makes the air pressure on the upper and lower sides of the diaphragm body 83 basically balanced, eliminating the direct pressure of the high-pressure gas on the valve core. Therefore, only a small force (the elastic force of the second spring 88 and the magnetic force of the electromagnet 87) is needed to control the opening and closing of the valve, improving the reliability and response speed of the valve action and reducing energy consumption.

[0038] In normal operation (off) state, electromagnet 87 is de-energized. Under the elastic force of second spring 88, iron drive rod 85 is pushed downward, which in turn causes drive clamp 84 and diaphragm body 83 to deform downward, so that they tightly cover the outlet end of the first flow channel 811 of the first valve body 81, forming a reliable air seal and blocking the passage between gas storage tank 7 and launch tube 9.

[0039] When an emergency command is triggered, the electromagnet 87 is energized, generating a strong downward suction force. This suction force acts on the iron drive rod 85, overcoming the elastic force of the second spring 88, and pulls the iron drive rod 85 upward. The iron drive rod 85 drives the drive clamp 84 and the film body 83 to move upward as a whole, causing the film body 83 to detach from the outlet of the first flow channel 811.

[0040] Once the seal is broken, the high-pressure gas inside the gas tank 7 instantly rushes into the closed end of the launch tube 9 through the first flow channel 811 and the second flow channel 812. The rapidly expanding high-pressure gas generates a huge thrust within the launch tube 9, which acts directly on the folded parachute 10 and instantly overcomes the attraction force of the annular magnet 91 on the iron cover plate 90, forcing the cover plate 90 open. Subsequently, the parachute 10 is ejected from the launch tube 9 by the high-speed gas and rapidly unfolds in the air.

[0041] The first embodiment employs a mechanical spring energy storage and electromechanical linkage unlocking principle, resulting in a compact structure and reliable operation. For reuse, simply manually press down the top cover and replace the parachute. The second embodiment utilizes high-pressure gas as a power source, achieving rapid ejection speed and high thrust. Furthermore, a balanced valve design ensures reliable sealing and low-power triggering during long-term operation. Both solutions achieve rapid response, reliable deployment, and reusability of core components in the UAV emergency parachute device, significantly improving UAV flight safety.

[0042] It should be noted that the detection and control logic used to determine whether the drone has malfunctioned and generate a trigger signal falls within the scope of existing technology and will not be elaborated upon in this solution. The purpose of this solution is to provide a physical device that can quickly, reliably, and repeatedly execute the parachute deployment action upon receiving the trigger signal.

[0043] Working principle and usage of this utility model: For the first embodiment: The housing cover 3 is manually closed and pressed, and the limiting hole 321 on the limiting plate 32 on its inner side is inserted and locked by the end of the locking pin 52 of the locking mechanism 5. During this process, the housing cover 3 presses the upper torsion arm of the torsion spring 4, causing the torsion spring 4 to twist around the torsion spring limiting shaft 223, and is in a compressed and stored state, storing elastic energy.

[0044] Under the elastic force of the first spring 53, the locking pin 52 remains extended, so that its end is stably locked in the limiting hole 321, thereby reliably locking the shell cover 3 in the closed position. At this time, the folded parachute 10 is constrained inside the first support shell 21.

[0045] The unlocking mechanism 6 is in the initial position, the rectangular protrusion 612 of the eccentric wheel 61 does not exert a thrust on the copper sleeve body 54, and the first drive motor 64 is stationary.

[0046] When the UAV's flight control system detects an emergency such as motor failure or attitude instability, it automatically sends a trigger signal. Upon receiving the signal, the first drive motor 64 rotates its output shaft. The first drive motor 64 drives the drive pinion 65 to rotate, which meshes with the driven large gear 62, transmitting power to the gear connecting shaft 611. The gear connecting shaft 611 then drives the eccentric wheel 61 to rotate. During rotation, the rectangular protrusion 612 on the eccentric wheel 61 pushes against the copper sleeve body 54 it contacts.

[0047] The copper sleeve body 54 drives the spring clamping shaft 521 to move, causing the locking pin 52 to slide backward (away from the limiting plate 32) against the elastic force of the first spring 53, until its end is completely removed from the limiting hole 321 of the limiting plate 32. At this point, the mechanical lock of the housing cover 3 is released.

[0048] The moment the lock is released, the torsion spring 4, which is in a stored state, rapidly releases its stored elastic energy. The upper torsion arm of the torsion spring 4 generates a powerful torque, driving the housing cover 3 to spring upward rapidly around the hinge pin 31 in a very short time.

[0049] Once the shell cover 3 is opened, the internal constraints disappear. The folded parachute 10 is thrown upwards by inertia and rapidly unfolds under the influence of air resistance. Since the parachute lines of the parachute 10 are pre-connected to the UAV body 11 or the first support shell 21, they can provide aerodynamic drag for the UAV, enabling a safe and slow descent.

[0050] For the second embodiment: The gas storage tank 7 is pre-filled with high-pressure gas (such as compressed air or carbon dioxide), and the filling port is sealed with a cap. The electromagnet 87 of the valve assembly 8 is de-energized. Under the elastic force of the second spring 88, the iron drive rod 85 is pushed downward, causing the drive clamp 84 and the diaphragm body 83 to deform downward, tightly pressing against the outlet end of the first flow channel 811 of the first valve body 81, forming an air seal. The passage between the gas storage tank 7 and the launching tube 9 is completely blocked.

[0051] At this time, the high-pressure gas in the gas storage tank 7 acts simultaneously on the upper and lower chambers of the diaphragm body 83 through the first pressure balancing channel 813 and the second pressure balancing channel 822. This makes the gas pressure on the upper and lower sides of the diaphragm body 83 basically balanced, and the valve core only needs to overcome the small elastic force of the second spring 88 to maintain the seal, ensuring the reliability and low power consumption of the valve under long-term high-pressure standby.

[0052] The folded parachute 10 is housed inside the launch tube 9, the opening of which is covered by an iron cover plate 90 and kept closed by the magnetic attraction of a ring magnet 91 embedded in the opening.

[0053] When an emergency trigger command is received: the electromagnet 87 of valve assembly 8 is energized, generating a strong downward magnetic force. The magnetic force acts on the iron drive rod 85, overcoming the elastic force of the second spring 88, and pulls the iron drive rod 85 upward. The iron drive rod 85 drives the drive clamp 84 and the diaphragm body 83 to move upward as a whole, causing the diaphragm body 83 to disengage from the outlet of the first flow channel 811.

[0054] The high-pressure gas in the gas storage tank 7 instantly flows into the closed end of the launch tube 9 through the opened first flow channel 811 and second flow channel 812.

[0055] The rapidly expanding high-pressure gas generates tremendous thrust within the launch tube 9, instantly overcoming the attraction of the annular magnet 91 to the iron cover 90 and blasting it open. The folded parachute 10, propelled by the high-pressure gas, is ejected at high speed from the launch tube 9. Once airborne, the parachute 10 rapidly unfolds under the influence of airflow, then opens, generating drag that allows the drone to descend slowly.

[0056] The specific embodiments described herein are merely illustrative examples illustrating the spirit of this utility model. Those skilled in the art to which this utility model pertains may make various modifications or additions to the described specific embodiments or use similar methods to replace them, without departing from the spirit of this utility model or exceeding the scope defined by the appended claims.

Claims

1. A reusable emergency parachute device for a drone, comprising a drone assembly (1), characterized in that, The drone component (1) has a first support shell (21) on one side. The first support shell (21) is rotatably equipped with a shell cover (3). A parachute (10) is placed inside the first support shell (21). The first support shell (21) is equipped with an elastic element (4) and a locking mechanism (5) that can restrict the opening of the first support shell (21). The locking mechanism (5) can lock the first support shell (21) so that the elastic element (4) is in a compressed and stored state. The first support shell (21) is also equipped with an unlocking mechanism (6) for releasing the locking mechanism (5) from the first support shell (21). When the shell cover (3) is closed, it can press the parachute (10) inside the first support shell (21) into an undeployed state.

2. The reusable emergency parachute device for a drone according to claim 1, wherein, The outer wall of the first support housing (21) is provided with a hinge slot (20), and the upper cover (3) of the housing is provided with a hinge pin (31) coaxially installed inside the hinge slot (20). The upper cover (3) of the housing is provided with a limiting plate (32) facing the interior of the first support housing (21), and the limiting plate (32) is provided with a limiting hole (321). The clamping mechanism (5) can be clamped inside the limiting hole (321).

3. The reusable emergency parachute device for drones according to claim 2, wherein, The elastic element (4) is a torsion spring; the first support housing (21) is provided with a bearing plate (211) inside, the upper surface of the bearing plate (211) is provided with a torsion arm limiting shell (221) and a shaft support plate (222), and the side wall of the shaft support plate (222) is provided with a torsion spring limiting shaft (223); the spring body of the torsion spring is installed on the torsion spring limiting shaft (223), one torsion arm of the torsion spring is stuck inside the torsion arm limiting shell (221) and the other torsion arm of the torsion spring abuts against the lower surface of the housing cover (3).

4. The reusable emergency parachute device for drones according to claim 3, wherein, The clamping mechanism (5) includes a pin support block (51), a clamping pin (52), a spring pressing shaft (521), a first spring (53), and a copper sleeve body (54). The lower surface of the bearing plate (211) is provided with a plurality of pin support blocks (51). The clamping pin (52) is slidably arranged inside the plurality of pin support blocks (51). The clamping pin (52) extends radially outward to provide a spring pressing shaft (521). A first spring (53) is provided between the spring pressing shaft (521) and any pin support block (51). The end of the clamping pin (52) is inserted into the interior of the limiting hole (321). The copper sleeve body (54) is also rotatably provided on the spring pressing shaft (521). The outer surface of the copper sleeve body (54) abuts against the unlocking mechanism (6).

5. The reusable emergency parachute device for drones according to claim 4, wherein, The unlocking mechanism (6) includes an eccentric wheel (61), a gear connecting shaft (611), a driven large gear (62), a copper sleeve body (54), a motor support plate (63), a first drive motor (64), and a drive pinion (65). The bottom of any pin support block (51) is also provided with a pin sleeve (511). The eccentric wheel (61) is provided with a gear connecting shaft (611) rotatably connected to the pin sleeve (511). One end of the gear connecting shaft (611) is fixedly connected to the driven large gear (62). The eccentric wheel (61) extends radially and is provided with a rectangular protrusion (612) for pushing the copper sleeve body (54). The first support housing (21) is also provided with a motor support plate (63). The first drive motor (64) is mounted on the motor support plate (63). The end of the shaft of the first drive motor (64) is provided with a drive pinion (65). The drive pinion (65) meshes with the driven large gear (62).

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