Delay cutter for unmanned aerial vehicle parachute

Abstract

The utility model provides a kind of unmanned aerial vehicle parachute is with delay cutter, comprising: upper sleeve, pull ring is embedded in upper sleeve upper end, compression spring, split pin, striker, impact primer, primer seat are embedded in upper sleeve inside, split pin is successively threaded through compression spring and striker and is placed in upper sleeve, impact primer is located in primer seat, one end of primer seat is fixedly connected with tube shell, ignition powder, delay body, gas generating agent and silk pad are sequentially arranged in the inside of tube shell, lower sleeve is connected to the one end of tube shell away from primer seat, ring cutter is arranged in the inside of lower sleeve close to silk pad side, sealing ring is arranged in the connecting place of lower sleeve and tube shell, plug is arranged in the one end of lower sleeve away from tube shell.This kind of unmanned aerial vehicle parachute is with delay cutter, by being provided with sealing whole structure, it is convenient to use, the high-speed gas generated after cutter gas generating agent burns is sealed, so that most gas works in ring cutter, ensure that cutter working reliability, improve the security in use process.

Description

Technical Field

[0001] This utility model relates to the technical field of drone parachute recovery devices, and more specifically, to a time-delay cutter for drone parachutes. Background Technology

[0002] The drone parachute delayed cutter (hereinafter referred to as the delayed cutter) is a power source pyrotechnic device. Its working principle is to use an impact pyrotechnic to ignite a chemical delayed pyrotechnic agent. After a preset time, the pyrotechnic agent burns, generating high-speed gas that triggers the blade, thereby cutting the parachute's closure line. The drone parachute delayed cutter can be widely used in aerospace, military airborne operations, drone recovery, and other scenarios that require precise delayed cutting.

[0003] The parachute retraction line is a key functional component of the parachute system. If the retraction line fails to cut safely and reliably during the parachute descent, the parachute canopy will not open properly, the parachute lines will become tangled, and it may even directly lead to the parachute falling to the ground.

[0004] This invention can reduce gas leakage and operating noise of the cutter, improve safety during use, and make the time-delay cutter have the characteristics of precise delay, reliable triggering, no power required, and lightweight and compact design. Summary of the Invention

[0005] The present invention aims to solve the technical problems mentioned in the background art and provide a time-delay cutter for drone parachutes.

[0006] To achieve the above objectives, this utility model provides the following technical solution: a delay cutter for a drone parachute, comprising: an upper sleeve, a pull ring embedded at the upper end of the upper sleeve, a compression spring, a cotter pin, a firing pin, an impact igniter, and an igniter seat embedded inside the upper sleeve, the cotter pin passing through the compression spring and the firing pin in sequence and placed inside the upper sleeve, the impact igniter being disposed inside the igniter seat, a tube shell being fixedly connected to one end of the igniter seat, an igniter, a delay body, a gas-generating agent, and a silk pad being sequentially disposed inside the tube shell, a lower sleeve being connected to the end of the tube shell away from the igniter seat, a ring cutter being disposed inside the lower sleeve near the silk pad, a sealing ring being disposed at the connection between the lower sleeve and the tube shell, and a plug being disposed at the end of the lower sleeve away from the tube shell.

[0007] A further preferred embodiment: the ignition powder is close to the impact cap, and the silk pad is positioned on the side of the gas-generating powder away from the delay body.

[0008] A further preferred embodiment: the pull ring is connected to the cotter pin, and the outer side of the firing pin has two inclined inner holes, through which the cotter pin can pass and be fixed inward.

[0009] A further preferred embodiment: the flame cap holder and the tube shell are connected by laser welding after the ends are closed.

[0010] A further preferred embodiment: The impact cap is installed inside the cap holder and fixed by a special tooling flange.

[0011] A further preferred embodiment: the ring cutter is fixedly connected to the lower sleeve by a spot riveting method.

[0012] A further preferred embodiment: two annular grooves are formed on the outer side of the ring cutter, and the sealing ring is embedded in the two annular grooves of the ring cutter.

[0013] A further preferred embodiment: the bottom of the lower sleeve is provided with a threaded hole, the plug is assembled and connected to the lower sleeve by threads, and the through hole on the side of the lower sleeve is used to pass through the parachute closure line. Beneficial effects

[0014] 1. The upper sleeve provides a stable mounting space for key components such as the compression spring, cotter pin, and firing pin. The precise dimensional design of its internal cavity ensures accurate firing pin movement trajectory and avoids jamming during triggering. The connection structure between the pull ring and the cotter pin is integrated into the upper end of the upper sleeve. Through the cooperation between the cotter pin and the inclined inner hole of the firing pin, reliable triggering can be achieved by the deformation of the cotter pin under a set tension. When the tension does not reach the threshold, the cotter pin is locked inward to fix the firing pin, effectively preventing accidental triggering during transportation or daily operation. When the tension reaches the threshold, the cotter pin accurately disengages and releases the firing pin, combining triggering sensitivity and stability. In addition, the upper sleeve's encasing design for the internal compression spring and firing pin can isolate external dust and moisture from corroding the moving parts. Combined with the overall sealed layout, it improves the reliability of operation in harsh environments. Its compact internal space design also reduces the overall volume, creating conditions for mounting on small drones.

[0015] 2. The lower sleeve provides a guide channel for the ring cutter within the internal cavity, ensuring that the ring cutter moves linearly along the axis under the push of high-pressure gas, avoiding blade deviation that could affect the cutting effect. The through hole on the side is specifically designed for threading the parachute tether, with precise positioning and a suitable hole diameter, ensuring that the tether is aligned with the ring cutter blade, thus improving cutting efficiency. The sealing ring at the connection with the tube shell and the double sealing ring design on the outside of the ring cutter create a highly airtight sealing cavity, which can completely lock in the high-pressure gas generated by the propellant, allowing the energy to be concentrated on the ring cutter, significantly improving the cutting speed. At the same time, the lower sleeve uses a modular design with spot riveting to fix the ring cutter and threaded connection to the plug, which simplifies the assembly process and facilitates later maintenance and replacement of parts. The threaded hole structure at the bottom also provides a basis for the sealing assembly of the plug, further enhancing the overall sealing performance and ensuring stable operation in humid and dusty environments.

[0016] 3. By incorporating a plug that engages with the threaded hole at the bottom of the lower sleeve, a reliable end-sealing structure is formed. This effectively prevents high-pressure gas from leaking from the end of the lower sleeve, ensuring that all the energy generated by the gas-generating agent is used to drive the ring cutter, thus improving energy utilization. The threaded connection design not only provides excellent sealing performance but also allows for disassembly, facilitating the later inspection or replacement of internal components in the lower sleeve and enhancing product maintenance convenience. Furthermore, the plug acts as an anvil, improving the cutting effect of the blade. In the event of high-pressure gas, the plug can also prevent internal components from flying out due to impact. Combined with the cushioning effect of the silk pad, this forms a double safety protection, avoiding safety hazards caused by component detachment. Its simple structure and compact size achieve sealing and protection functions without increasing the weight and volume of the overall device, meeting the lightweight requirements of small UAVs for their mounted components and further enhancing the product's safety and adaptability in practical applications.

[0017] 4. In summary, this type of delayed-action cutter for drone parachutes, with its sealed and uniform structure, is easy to use. The high-speed gas generated after the combustion of the propellant is sealed in both the front and rear directions by the two sealing rings on the outer circumference of the ring cutter and the sealing structure between the burner cap seat and the upper and lower sleeves. This ensures that most of the gas does work on the ring cutter, guaranteeing the reliability of the cutter, reducing gas leakage and operating noise, and improving safety during use. The product has a simple and compact structure, is highly environmentally friendly, easy to operate, highly efficient, and safe, and is suitable for scenarios such as drone parachute recovery and rope cutting. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the overall structure of this utility model.

[0019] Figure 1 In the middle: 1. Pull ring; 2. Compression spring; 3. Cotter pin; 4. Upper sleeve; 5. Strike pin; 6. Impact cap; 7. Cap holder; 8. Tube shell; 9. Ignition powder; 10. Delay body; 11. Gas-generating powder; 12. Silk pad; 13. Ring cutter; 14. Sealing ring; 15. Lower sleeve; 16. Plug. Detailed Implementation

[0020] The following will refer to the appendix in the embodiments of this utility model. Figure 1 The technical solutions in the embodiments of this utility model will be clearly and completely described.

[0021] Please see Figure 1In this embodiment of the present invention, a delay cutter for a drone parachute includes: an upper sleeve 4, with a pull ring 1 embedded at the upper end of the upper sleeve 4; a compression spring 2, a cotter pin 3, a firing pin 5, an impact cap 6, and a cap seat 7 embedded inside the upper sleeve 4; the cotter pin 3 passes through the compression spring 2 and the firing pin 5 in sequence and is placed inside the upper sleeve 4; the impact cap 6 is located inside the cap seat 7; a tube shell 8 is fixedly connected to one end of the cap seat 7; and an ignition powder 9, a delay body 10, a gas-generating powder 11, and a silk pad 1 are sequentially arranged inside the tube shell 8. 2. The end of the tube shell 8 away from the burner seat 7 is connected to a lower sleeve 15. A ring cutter 13 is provided inside the lower sleeve 15 near the side of the silk pad 12. A sealing ring 14 is provided at the connection between the lower sleeve 15 and the tube shell 8. A plug 16 is provided at the end of the lower sleeve 15 away from the tube shell 8. The igniter 9 is close to the impact burner 6. The silk pad 12 is located on the side of the gas-generating powder 11 away from the delay body 10. The pull ring 1 is connected to the cotter pin 3. Two inclined inner holes are opened on the outside of the firing pin 5. The cotter pin 3 can pass through the two inclined inner holes and be fixed inward.

[0022] When the pull ring 1 is subjected to external tension, the cotter pin 3 drives the firing pin 5 to overcome the resistance of the compression spring 2 and move upward, causing the compression spring 2 to store elastic potential energy. When the tension reaches the deformation limit of the cotter pin 3, the cotter pin 3 undergoes plastic deformation and disengages from the inclined inner hole of the firing pin 5. The compression spring 2 releases its elastic potential energy, pushing the firing pin 5 to strike the flash cap 6 at high speed. After the flash cap 6 is struck, the resulting flame ignites the igniter 9. The flame of the igniter 9 further ignites the delay body 10. After a preset time delay, the delay body 10 ignites the gas-generating agent 11. The gas-generating agent 11 burns rapidly, generating a large amount of high-pressure gas. The high-pressure gas acts on the end face of the ring cutter 13, pushing the ring cutter 13 to move at high speed within the sealed cavity. Under the push of the high-pressure gas, the ring cutter 13 moves rapidly along the axial direction of the lower sleeve 15, and its sharp edge cuts through the pre-drilled through-hole on the side of the lower sleeve 15. The parachute tether allows the parachute to deploy quickly, enabling a safe landing for the drone and meeting the needs of different drone landing scenarios. The cotter pin 3 and the firing pin 5 utilize an inclined inner hole mating structure to ensure reliable triggering under set tension, resulting in a low false trigger rate. Laser welding of the spark plug seat 7 and the casing 8, along with the double sealing ring 14 design of the ring cutter 13, ensures high airtightness of the high-pressure sealed space, allowing reliable operation in harsh environments such as humidity and dust. The special cutting edge design and high-speed gas drive of the ring cutter 13 provide a faster response speed than traditional mechanical cutting methods. Its compact structure and modular design reduce its size and weight compared to similar products, making it particularly suitable for small drones. The threaded sealing structure of the plug 16 and the cushioning design of the pad 12 effectively prevent high-pressure gas leakage and component ejection, ensuring safety during use.

[0023] In this embodiment of the utility model, the spark cap holder 7 and the tube shell 8 are connected by laser welding after being closed; the impact spark cap 6 is installed in the spark cap holder 7 and fixed by flange using a special tooling; the ring cutter 13 is fixedly connected to the lower sleeve 15 by spot riveting; two annular grooves are opened on the outer side of the ring cutter 13, and the sealing ring 14 is embedded in the two annular grooves of the ring cutter 13; the bottom of the lower sleeve 15 is provided with a threaded hole, and the plug 16 is assembled and connected to the lower sleeve 15 by threads; the through hole on the side of the lower sleeve 15 is used to pass through the parachute closing rope; pull ring. 1. When under tension, the cotter pin 3 drives the firing pin 5 to compress the spring 2. When the tension reaches the deformation limit of the cotter pin 3, the cotter pin 3 releases the firing pin 5. The elastic potential energy of the spring 2 drives the firing pin 5 to strike the flash cap 6, realizing energy conversion and triggering. After the flash cap 6 is struck and ignited, the flame sequentially ignites the ignition powder 9, the delay body 10 and the gas-generating powder 11. The delay body 10 realizes the delay control of the ignition time. The high-speed gas generated by the combustion of the gas-generating powder 11 drives the ring cutter 13 to move at high speed, completing the cutting action of the parachute closure line.

[0024] When the drone triggers the landing procedure, the pull ring 1 is subjected to external tension. This tension is transmitted to the striker 5 through the cotter pin 3. The striker 5 compresses the spring 2, converting mechanical energy into elastic potential energy. When the tension exceeds the shear strength of the cotter pin 3, the cotter pin 3 breaks or deforms at the inclined inner hole of the striker 5, releasing the striker 5. The spring 2 releases its elastic potential energy, pushing the striker 5 to strike the burner cap 6 at high speed, causing the burner cap to ignite. The flame generated by the burner cap ignites the igniter 9, which burns rapidly and expands the flame energy. After the delay body 10 is ignited, it undergoes controlled combustion according to the preset formula and structure, achieving a precise time delay. After the delay body 10 finishes burning, the gas-generating agent 11 is ignited. The gas-generating agent 11 burns violently, generating high-pressure gas. The high-pressure gas is contained in the sealed space formed by the burner cap seat 7, the ring cutter 13, and the lower sleeve 15. The internal expansion is rapid, propelling the ring cutter 13 to move at high speed along the axis. The cutting edge of the ring cutter 13 quickly cuts the parachute tether that passes through the side through-hole of the lower sleeve 15, causing the parachute to deploy immediately. The double sealing ring 14 of the ring cutter 13 ensures that the high-pressure gas does not leak, improving energy utilization and cutting reliability. The silk pad 12 absorbs the shock wave of the initial combustion of the propellant 11, protecting the structural integrity. The threaded connection between the plug 16 and the lower sleeve 15 provides maintainability and prevents external moisture or dust from entering. Laser welding, double sealing ring 14, and threaded seals ensure airtight performance throughout the entire life cycle, adapting to harsh environments such as humidity and dust. The sealing structure concentrates the gas energy onto the ring cutter 13. The shear strength design of the cotter pin 3 requires a specific tensile force to trigger, avoiding accidental activation during transportation or daily operation.

[0025] Working principle: When the UAV triggers the landing procedure, the pull ring 1 is subjected to external tension. This tension is transmitted to the striker 5 through the cotter pin 3. The striker 5 then overcomes the resistance of the compression spring 2 and moves upward, compressing the compression spring 2 and storing elastic potential energy. At this time, the cotter pin 3 passes through the inclined inner hole of the striker 5 to achieve internal locking. When the tension reaches the deformation limit of the cotter pin 3, the cotter pin 3 undergoes plastic deformation and disengages from the inclined inner hole. The compression spring 2 instantly releases its elastic potential energy, pushing the striker 5 to strike the impact cap 6 in the impeller 6 seat at high speed. After the impact cap 6 is ignited, it generates a flame, which sequentially ignites the ignition powder 9 and the delay body 10. The delay body 10 moves according to a preset time... After a delayed combustion, the propellant 11 is further ignited. The propellant 11 burns rapidly to produce a large amount of high-pressure gas, which expands rapidly in the sealed space formed by the burner cap 7, the shell 8, the lower sleeve 15, and the ring cutter 13. The high-pressure gas acts on the end face of the ring cutter 13 and pushes it to move at high speed along the axis of the lower sleeve 15. Driven by the gas, the ring cutter 13 cuts the parachute closure line that has been pre-passed through the through hole of the lower sleeve 15 with its sharp edge, causing the parachute to deploy. Throughout the process, the pad 12 buffers the impact of the high-pressure gas, and the plug 16 prevents gas leakage, thus achieving precise and rapid cutting of the parachute closure line and ensuring the safe landing of the UAV.

Claims

1. A delay cutter for a drone parachute, comprising: The upper sleeve (4) is characterized in that: a pull ring (1) is embedded in the upper end of the upper sleeve (4), and a compression spring (2), a cotter pin (3), a striking pin (5), an impact cap (6), and a cap seat (7) are embedded inside the upper sleeve (4). The cotter pin (3) passes through the compression spring (2) and the striking pin (5) in sequence and is placed inside the upper sleeve (4). The impact cap (6) is located inside the cap seat (7). One end of the cap seat (7) is fixedly connected to a tube shell (8). Inside the tube shell (8), an ignition powder (9), a delay body (10), a gas-generating powder (11), and a silk pad (12) are arranged in sequence. The end of the tube shell (8) away from the burner cap seat (7) is connected to a lower sleeve (15). Inside the lower sleeve (15) near the silk pad (12), a ring cutter (13) is arranged. A sealing ring (14) is arranged at the connection between the lower sleeve (15) and the tube shell (8). A plug (16) is arranged at the end of the lower sleeve (15) away from the tube shell (8).

2. The delay cutter for UAV parachute according to claim 1, characterized in that: The ignition powder (9) is close to the impact cap (6), and the silk pad (12) is placed on the side of the gas-generating powder (11) away from the delay body (10).

3. The delayed-action cutter for UAV parachutes according to claim 1, characterized in that: The pull ring (1) is connected to the cotter pin (3), and the outer side of the firing pin (5) has two inclined inner holes. The cotter pin (3) can pass through the two inclined inner holes and be fixed inside.

4. The delay cutter for UAV parachute according to claim 1, characterized in that: The fire cap holder (7) and the tube shell (8) are connected by laser welding after the ends are closed.

5. The delay cutter for UAV parachute according to claim 1, characterized in that: The impact cap (6) is installed inside the cap seat (7) and fixed by a special tooling flange.

6. The delay cutter for UAV parachute according to claim 1, characterized in that: The ring cutter (13) is fixedly connected to the lower sleeve (15) by spot riveting.

7. The delay cutter for UAV parachute according to claim 1, characterized in that: Two annular grooves are provided on the outer side of the ring cutter (13), and the sealing ring (14) is embedded in the two annular grooves of the ring cutter (13).

8. The delay cutter for UAV parachute according to claim 1, characterized in that: The bottom of the lower sleeve (15) is provided with a threaded hole, and the plug (16) is assembled and connected to the lower sleeve (15) by threads. The through hole on the side of the lower sleeve (15) is used to pass through the parachute closure rope.

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