Tail end micro stroke actuation based rapid drop device mounted on a drone

Abstract

This invention belongs to the field of aviation equipment technology, specifically relating to a rapid deployment device based on tail-end micro-stroke actuation, mounted on a UAV and attached to the underside of the UAV's fuselage or wing. It includes a detachable warhead and warhead body. The warhead has a receiving cavity containing a pre-installed folded capture net with multiple counterweights distributed on the net. The warhead body integrates a high-pressure gas cylinder serving as the deployment power source, and a rapid unlocking and separation mechanism located at the cylinder's outlet. The rapid unlocking and separation mechanism includes a venting nut, a locking core, a limiting steel ball, a push rod, and an unlocking valve. This invention utilizes the tail-end micro-stroke actuation of the flight platform to achieve transient and precise venting, and the power source is recyclable.

Description

Technical Field

[0001] This invention belongs to the field of aviation equipment technology, specifically relating to a rapid throwing device based on tail-end micro-stroke actuation mounted on a UAV. It is an airborne flexible capture and throwing device that is compatible with airborne actuation platforms, has a rapid separation structure, and can be used repeatedly at high frequencies. Background Technology

[0002] In the fields of general aviation and low-altitude economy, unmanned aerial vehicles (UAVs) often need to perform tasks such as emergency material delivery or flexible recovery of runaway targets. The core of these tasks lies in ensuring that the payload can be released stably, transiently, and accurately from the flight platform during flight. Existing airborne delivery systems mainly suffer from the following bottlenecks: Poor platform compatibility: It mostly uses independent electronic control or side unlocking, which cannot utilize the axial actuation power provided by the aircraft's standard mission rack, increasing the system's dead weight; Response lag: Traditional pneumatic release mechanisms rely on valve core balance, and the opening time is uncertain in high-speed flight flow fields, resulting in large deviations in the load deployment landing point; Low recycling rate: High-voltage power sources are often discarded along with the load, resulting in high costs per operation, and non-recyclable power components pose a safety threat to the ground environment.

[0003] Therefore, there is an urgent need for an airborne throwing device that can utilize the micro-stroke at the tail end of the flight platform to achieve instantaneous and precise exhaust and has a recyclable power source. Summary of the Invention

[0004] To address the aforementioned technical problems, this invention provides a rapid throwing device mounted on a drone based on tail-end micro-stroke actuation.

[0005] The present invention is implemented by providing a rapid launching device based on tail-end micro-stroke actuation mounted on a drone, which is mounted under the belly or wing of the drone and includes a detachable warhead and warhead body. The warhead has an internal storage cavity, inside which a folded and pre-installed capture net is placed, and multiple counterweights are distributed on the capture net. The projectile body integrates a high-pressure gas cylinder as the power source for launching, and a quick-release mechanism configured at the outlet of the high-pressure gas cylinder. The quick-release mechanism includes a vent nut, a lock core, a limiting steel ball, a push rod, and an unlocking valve. The vent nut is fixed to the front end of the projectile body and has a release chamber inside for high-pressure gas to flow to the projectile head. The lock core is a tubular structure and is fixedly configured between the outlet of the high-pressure gas cylinder and the vent nut. The side wall of the lock core has several radially penetrating limiting holes, and a limiting steel ball is movably embedded in each limiting hole. The push rod coaxially passes through the high-pressure gas cylinder and the lock core. The surface of the push rod has an annular limiting groove, and the front end of the push rod abuts against a pressure spring. The other end of the pressure spring abuts against the inner wall of the vent nut near the projectile head. The unlocking valve is coaxially sleeved on the outside of the lock core and can slide along the outer wall of the lock core. The inner wall of the unlocking valve has a radial limiting groove. In the locked state, the outer wall of the push rod pushes the limiting steel ball radially outward and into the radial limiting groove of the unlocking valve, thus mechanically locking the unlocking valve and sealing the high-pressure gas cylinder together with the lock cylinder and the push rod. In the unlocked state, the push rod is triggered to generate axial displacement, aligning the annular limiting groove with the limiting hole, and the limiting steel ball slides into the annular limiting groove to release the radial constraint on the unlocking valve. Driven by the internal air pressure of the high-pressure gas cylinder, the unlocking valve slides axially instantaneously, opening the high-pressure gas release chamber of the vent nut. The high-pressure gas pushes the projectile out, achieving accelerated separation of the projectile from the projectile body. During the flight of the projectile, the capture net containing the counterweight separates from the projectile casing, and the capture net unfolds under the action of the counterweight.

[0006] Preferably, an O-ring I is fitted at the mating surface of the unlocking valve and the vent nut, an O-ring IV is fitted at the mating surface of the lock cylinder and the unlocking valve, at least one O-ring is fitted at the mating surface of the push rod and the lock cylinder, and at least one O-ring is fitted at the through mating surface of the push rod and the high-pressure gas cylinder.

[0007] Preferably, the projectile includes a spherical shell and a push plate that can be separably docked together. The spherical shell has an air passage in the center. The push plate has insertion holes with the same number as the counterweights. The counterweights can be separably inserted into the corresponding insertion holes. The capture net is folded and pre-placed in the cavity between the spherical shell and the counterweights. There are at least four counterweights, which are evenly connected around the perimeter of the capture net.

[0008] Preferably, a buffer rubber pad is provided circumferentially on the side of the unlocking valve near the warhead. In the unlocked state, the unlocking valve and the buffer rubber pad are pushed onto the vent nut by high-pressure gas to buffer the impact of the unlocking valve on the vent nut.

[0009] Preferably, the outer wall of the vent nut is threaded to the projectile body. At one end of the vent nut near the projectile, there is a groove for accommodating the projectile. The projectile is embedded and fixed in the groove. Several high-pressure gas release holes are distributed circumferentially at the mating surface between the groove and the projectile. The outer diameter of the buffer rubber pad is smaller than the inner diameter of the ring formed by the several high-pressure gas release holes.

[0010] Preferably, one end of the lock cylinder is fixedly connected to the inner wall of the vent nut near the end of the bullet, and the other end is located at the outlet of the high-pressure gas cylinder.

[0011] Preferably, the central angle of the radial limiting groove on the side of the high-pressure gas cylinder closer to the radial limiting groove on the unlocking valve is smaller than the central angle of the radial limiting groove on the side of the high-pressure gas cylinder farther away from the radial limiting groove on the push rod is smaller than the central angle of the radial limiting groove on the side of the push rod closer to the high-pressure gas cylinder.

[0012] Preferably, the overall projectile mass of the projectile, including the capture net and the counterweight, is 150-450 g, the area of ​​the capture net after deployment is not less than 20 m², and the initial inflation pressure of the high-pressure gas cylinder is 10-25 MPa.

[0013] Preferably, the axial micro-stroke displacement of the push rod is no more than 2 mm.

[0014] The present invention also provides a drone, which has the above-mentioned rapid launching device mounted on its belly or under its wings via a quick interface. The drone also includes an onboard actuator, the output end of which is located at the end of the push rod away from the projectile.

[0015] Compared with the prior art, the advantages of the present invention are as follows: 1) Meets airborne ejection standards: It adopts a micro-stroke triggering architecture of "push rod-limiting steel ball-unlocking valve", which is actuated by micro-stroke at the tail end, perfectly matching the mechanical thrust action of the UAV mission frame and reducing system complexity; 2) Transient energy response: The high-pressure gas release chamber can be opened by inputting a very small axial impact stroke, inducing the hysteresis-free, step-like release of high-pressure gas, eliminating the opening hysteresis and ensuring the trajectory consistency of the load under complex flight flow fields. Attached Figure Description

[0016] Figure 1 A schematic diagram of a rapid throwing device based on tail-end micro-stroke actuation mounted on a drone, provided by the present invention; Figure 2 This is a schematic diagram of the spherical shell structure of the warhead of the present invention; Figure 3 This is a schematic diagram of the internal structure of the warhead of the present invention; Figure 4 This is a schematic diagram of the rapid unlocking and separation mechanism in the projectile body of the present invention; Figure 5 This is a schematic diagram showing the distribution of the sealing rings in this invention; Figure 6 This is a schematic diagram of the locked state of the rapid throwing device of the present invention; Figure 7 This is a schematic diagram of the unlocked state of the rapid throwing device of the present invention; Figure 8 This is a diagram showing the unfolded state of the capture net of the present invention; Figure 9 This is a schematic diagram of the axial cross-sectional structure and high-pressure gas release in the unlocked state of the present invention; Figure 10 This is a schematic diagram of the rapid throwing device of the present invention mounted on a drone. Detailed Implementation

[0017] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are for illustrative purposes only and are not intended to limit the invention.

[0018] refer to Figures 1 to 10 The present invention provides a rapid throwing device based on tail-end micro-stroke actuation mounted on a drone, which is mounted under the belly or wing of the drone and includes a detachable warhead 5 and a warhead body. The projectile 5 has a storage cavity inside, and a folded and pre-installed capture net is placed inside the storage cavity. Multiple counterweights 6 are distributed on the capture net. Specifically, the projectile 5 includes a spherical shell 501 and a pusher plate 502 that can be detachably docked together. An air passage 503 is provided in the center of the spherical shell 501. The pusher plate 502 has insertion holes with the same number as the counterweights 6. The counterweights 6 can be detachably inserted into the corresponding insertion holes. The capture net is folded and pre-installed in the cavity between the spherical shell 501 and the counterweights 6.

[0019] The projectile body integrates a high-pressure gas cylinder 2, which serves as the power source for launching, and a quick-release mechanism located at the outlet of the high-pressure gas cylinder 2. The high-pressure gas cylinder 2 is integrally formed inside the projectile body. The quick-release mechanism includes a vent nut 3, a lock cylinder 10, a limiting steel ball 4, a push rod 1, and an unlocking valve 9. The vent nut 3 is fixed to the front end of the projectile body and has an internal release chamber for high-pressure gas to flow to the projectile head 5. The outer wall of the vent nut 3 is threadedly connected to the projectile body. At the end of the vent nut 3 near the projectile head 5, there is a groove for accommodating the projectile head 5. The projectile head 5 is embedded and fixed in the groove. Several high-pressure gas release holes are provided at the mating surface between the groove and the projectile head 5. The lock cylinder 10 has a tubular structure. Located inside the cavity of the vent nut 3, one end is fixedly connected to the inner wall of the vent nut 3 near the end of the bullet 5, and the other end is located at the outlet of the high-pressure gas cylinder 2. The side wall of the lock cylinder 10 has several radially penetrating limiting holes, and a limiting steel ball 4 is movably embedded in each limiting hole. The push rod 1 coaxially passes through the high-pressure gas cylinder 2 and the lock cylinder 10. The surface of the push rod 1 has an annular limiting groove, and the front end of the push rod 1 abuts against a pressure spring 8. The other end of the pressure spring 8 abuts against the inner wall of the vent nut 3 near the bullet 5. The unlocking valve 9 is coaxially sleeved on the outside of the lock cylinder 10 and can slide along the outer wall of the lock cylinder 10. The inner wall of the unlocking valve 9 has a radial limiting groove. In the locked state, the outer wall of the push rod 1 pushes the limiting steel ball 4 radially outward and into the radial limiting groove of the unlocking valve 9, thus mechanically locking the unlocking valve 9, thereby sealing the high-pressure gas cylinder 2 together with the lock cylinder 10 and the push rod 1. In the unlocked state, the push rod 1 is triggered to generate axial displacement, so that the annular limiting groove aligns with the limiting hole, and the limiting steel ball 4 slides into the annular limiting groove to release the radial constraint on the unlocking valve 9. The unlocking valve 9 slides axially instantaneously under the internal air pressure of the high-pressure gas cylinder 2, opening the high-pressure gas release chamber of the vent nut 3. The high-pressure gas pushes the projectile 5 out, realizing the accelerated separation of the projectile 5 from the projectile body. During the flight of the projectile 5 towards the target, the airflow enters the interior of the projectile 5 through the air passage 503, applying backward aerodynamic resistance to the push plate 502, causing the push plate 502 to separate from the spherical shell 501 due to relative velocity. Because the air resistance experienced by the push plate 502 is greater than that of the counterweight 6, a speed difference is generated between the two. When this speed difference reaches the preset condition, the connection between the counterweight 6 and the push plate 502 is released, and the capture net unfolds under the action of the counterweight 6 to capture the target. The central angle of the radial limiting groove on the side of the high-pressure gas cylinder 2 near the radial limiting groove on the unlocking valve 9 is smaller than the central angle of the radial limiting groove on the side away from the high-pressure gas cylinder 2. Similarly, the central angle of the annular limiting groove on the push rod 1 on the side away from the high-pressure gas cylinder 2 is smaller than the central angle of the annular limiting groove on the side near the high-pressure gas cylinder 2. Therefore, in the locked state, the gas pressure inside the high-pressure gas cylinder 2 applies an axial thrust to the unlocking valve 9. This axial thrust is converted into a radial compressive force on the limiting steel ball 4 through the radial limiting groove near the high-pressure gas cylinder 2. When the annular limiting groove of the push rod 1 moves to the aligned position, the limiting steel ball 4, under the pressure of the radial compressive force, instantly slides into the annular limiting groove, achieving mechanical unlocking without delay.

[0020] To ensure a tight seal, an O-ring I11 is fitted at the mating surface of the unlocking valve 9 and the vent nut 3, an O-ring IV14 is fitted at the mating surface of the lock cylinder 10 and the unlocking valve 9, an O-ring II12 and an O-ring III13 are fitted at the mating surface of the push rod 1 and the lock cylinder 10, and an O-ring V15 and an O-ring VI16 are fitted at the through mating surface of the push rod 1 and the high-pressure gas cylinder 2.

[0021] In order to absorb the transient impact kinetic energy generated by the high-pressure drive of the unlocking valve 9, and in order to prevent the unlocking valve 9 from blocking the high-pressure gas passage between the vent nut 3 and the bullet head 5, a buffer rubber pad 7 is provided circumferentially on the side of the unlocking valve 9 near the bullet head 5. In the unlocked state, the unlocking valve 9 and the buffer rubber pad 7 are pushed onto the vent nut 3 by the high-pressure gas, so as to buffer the impact of the unlocking valve 9 on the vent nut 3 and simultaneously open the high-pressure gas release chamber.

[0022] The aforementioned rapid deployment device is applied to a drone and mounted on the underside of the drone's fuselage or wing via a quick interface. An onboard actuator is also installed on the drone, with the output end of the onboard actuator located at the end of the push rod 1 furthest from the warhead 5. Example

[0023] The following is in conjunction with the appendix Figure 1-10 This embodiment will be described in detail below. Power source parameters: The initial inflation pressure of the high-pressure gas cylinder 2 is set to 10-25 MPa to ensure sufficient transient expansion impulse. Load parameters: To balance lightweight carrying capacity and kinetic energy retention rate to overcome air resistance in the external trajectory, the overall projectile mass of the warhead 5, including the capture net and counterweight, is preferably 150-450 g.

[0024] 1) Static assembly relationship and locking state The rapid throwing device in this embodiment has a streamlined rotating structure, such as... Figure 1As shown. The internal cavity of the warhead 5 is pre-loaded with a folded capture net and a counterweight 6. The warhead body contains a high-pressure gas cylinder 2, whose front end is coaxially fitted with a vent nut 3, a lock core 10, and an unlocking valve 9. A buffer rubber pad 7 is circumferentially arranged on the side of the unlocking valve 9 near the warhead 5. Figure 6 In the locked state shown, push rod 1 remains absolutely stationary, and its outer wall pushes the limiting steel ball 4 radially outward, which gets stuck in the limiting groove of unlocking valve 9, so that unlocking valve 9 is mechanically locked.

[0025] High-pressure static sealing mechanism: The mating surfaces of the push rod 1 and the high-pressure gas cylinder 2 are equipped with multi-stage seals. Since the push rod 1 is normally completely stationary, dynamic wear is eliminated. The multi-stage sealing arrangement is as follows: Figure 5 As shown. Preferably, the O-ring used for sealing is made of expanded polytetrafluoroethylene (ePTFE), which utilizes its high tensile strength and excellent creep resistance to ensure that the system does not relax or leak pressure under long-term high-pressure stress.

[0026] 2) Mounting layout and post-firing actuation mechanism In this embodiment, the rapid deployment device is suspended from the underside of the UAV's fuselage or wings via a standard quick-access interface (such as a dual-ear mount), and the rear-mounted power bay maintains close contact with the UAV's mission rack. Figure 10 As shown. The UAV flight control system sends pulse commands to the onboard actuator (such as a miniature linear motor or a high-torque servo), and the actuator outputs a thrust that acts on the tail end of push rod 1, triggering the release process. Figure 7 As shown, when push rod 1 is adjusted axially to the unlocked position, the limiting steel ball 4 slides into the annular limiting track machined on the surface of push rod 1, and the unlocking valve 9 loses its radial constraint. Under the action of the gas cylinder internal pressure, the unlocking valve 9 moves forward in the axial direction shown in the figure, carrying the buffer rubber pad 7 until it hits the vent nut 3. The buffer rubber pad 7 is used to absorb the impact and reduce vibration. At the same time, the high-pressure gas in the gas cylinder is released through the vent nut 3, which quickly pushes the projectile 5, which includes the capture net and the counterweight 6, out at high speed.

[0027] The quick unlocking and separation mechanism is as follows Figure 4 As shown, push rod 1 generates a small stroke displacement. (e.g., 2 mm), so that the annular limiting groove aligns with the limiting hole, and the limiting steel ball 4 falls off.

[0028] 3) Integration of transient decompression and avionics Traditional netting relies solely on centrifugal force to hold the net in place. However, in this embodiment, the rapid separation mechanism releases high-pressure gas via the vent nut 3 within microseconds, forming a high-speed jet. The unlocking valve 9 moves axially (…). Figure 9 (Solid arrow direction) generates extremely high acceleration forward sliding, high-pressure gas surges towards the warhead 5 along the dashed arrow, the optimal deployment state of the capture net is as follows: Figure 8As shown, the impact of the jet on the bottom of the projectile 5 not only provides extremely high initial translational kinetic energy, but also establishes an optimal radial aerodynamic deployment force model the instant the counterweight 6 detaches from the push plate 502. During this ejection process, the extremely high initial velocity of this invention activates the radial aerodynamic deployment force field of the capture net, ensuring that the net achieves optimal topological opening with a large area ≥20㎡ after leaving the barrel.

[0029] The drone accurately calculates the release timing based on the current ground speed, wind speed, and target distance using its built-in aerodynamic model, and utilizes the microsecond-level response characteristics of the unlocking valve 9 to achieve precise payload deployment.

[0030] 4) Reusable projectile structure After the warhead 5 is launched, the remaining projectile structure (which contains a high-pressure gas cylinder 2 serving as the propulsion power source and a quick-release separation mechanism located at the front outlet of the high-pressure gas cylinder 2) remains intact, enabling rapid recovery and reassembly. The high-pressure gas cylinder 2 in the power compartment is recovered with the UAV upon return and refilled through the vent nut 3 interface, achieving cyclical operation. The overall design demonstrates good recyclability and economy.

Claims

1. A rapid throwing device mounted on a drone based on tail-end micro-stroke actuation, characterized in that, Mounted under the belly or wing of the UAV, it includes a detachable warhead (5) and a warhead body; The warhead (5) has a storage cavity inside, and a capture net is folded and pre-placed inside the storage cavity. Multiple counterweights (6) are distributed on the capture net. The projectile body integrates a high-pressure gas cylinder (2) as the power source for launching, and a quick-release mechanism configured at the outlet of the high-pressure gas cylinder (2); the quick-release mechanism includes a vent nut (3), a lock core (10), a limiting steel ball (4), a push rod (1), and an unlocking valve (9). The vent nut (3) is fixed to the front end of the projectile body and has a release chamber inside for high-pressure gas to flow to the projectile head (5). The lock core (10) is a tubular structure and is fixedly configured between the outlet of the high-pressure gas cylinder (2) and the vent nut (3). The side wall of the lock core (10) has an opening There are several radially penetrating limiting holes, and a limiting steel ball (4) is movably embedded in each limiting hole. The push rod (1) coaxially passes through the high-pressure gas cylinder (2) and the lock core (10). The surface of the push rod (1) is provided with an annular limiting groove, and the front end of the push rod (1) abuts against a pressure spring (8). The other end of the pressure spring (8) abuts against the inner wall of the vent nut (3) near the bullet head (5). The unlocking valve (9) is coaxially sleeved on the outside of the lock core (10) and can slide along the outer wall of the lock core (10). The inner wall of the unlocking valve (9) is provided with a radial limiting groove. In the locked state, the outer wall of the push rod (1) pushes the limiting steel ball (4) radially outward and into the radial limiting groove of the unlocking valve (9), so that the unlocking valve (9) is mechanically locked, thereby sealing the high-pressure gas cylinder (2) together with the lock core (10) and the push rod (1); in the unlocked state, the push rod (1) is triggered to generate axial displacement, so that the annular limiting groove aligns with the limiting hole, and the limiting steel ball (4) slides into the annular limiting groove to release the radial constraint on the unlocking valve (9); the unlocking valve (9) slides axially instantaneously under the internal air pressure of the high-pressure gas cylinder (2), opening the high-pressure gas release chamber of the vent nut (3), and the high-pressure gas pushes the projectile (5) out, realizing the accelerated separation of the projectile (5) from the projectile body. During the flight of the projectile (5), the capture net containing the counterweight (6) separates from the shell of the projectile (5), and the capture net unfolds under the action of the counterweight (6).

2. The rapid throwing device based on tail-end micro-stroke actuation mounted on a UAV according to claim 1, characterized in that, O-ring I (11) is fitted on the mating surface of the unlocking valve (9) and the vent nut (3), O-ring IV (14) is fitted on the mating surface of the lock cylinder (10) and the unlocking valve (9), at least one O-ring is fitted on the mating surface of the push rod (1) and the lock cylinder (10), and at least one O-ring is fitted on the through mating surface of the push rod (1) and the high-pressure gas cylinder (2).

3. The rapid throwing device based on tail-end micro-stroke actuation mounted on a UAV according to claim 1, characterized in that, The warhead (5) includes a spherical shell (501) and a pusher plate (502) that can be separably docked together. The spherical shell (501) has an air passage (503) in the center. The pusher plate (502) has a number of insertion holes that are the same as the number of counterweights (6). The counterweights (6) can be separably inserted into the corresponding insertion holes. The capture net is folded and pre-placed in the cavity between the spherical shell (501) and the counterweights (6).

4. The rapid throwing device based on tail-end micro-stroke actuation mounted on a UAV according to claim 1, characterized in that, A buffer rubber pad (7) is provided circumferentially on the side of the unlocking valve (9) near the bullet (5).

5. The rapid throwing device based on tail-end micro-stroke actuation mounted on a UAV according to claim 1, characterized in that, The outer wall of the vent nut (3) is threaded to the projectile body. At one end of the vent nut (3) near the projectile (5), there is a groove for accommodating the projectile (5). The projectile (5) is embedded and fixed in the groove. Several high-pressure gas release holes are distributed circumferentially at the mating surface between the groove and the projectile (5).

6. The rapid throwing device based on tail-end micro-stroke actuation mounted on a UAV according to claim 1, characterized in that, One end of the lock core (10) is fixedly connected to the inner wall of the vent nut (3) near the end of the bullet (5), and the other end is located at the outlet of the high-pressure gas cylinder (2).

7. The rapid throwing device based on tail-end micro-stroke actuation mounted on a UAV according to claim 1, characterized in that, The central angle of the radial limiting groove on the side of the high-pressure gas cylinder (2) is smaller than the central angle of the arc surface on the side away from the high-pressure gas cylinder (2); the central angle of the annular limiting groove on the push rod (1) is smaller than the central angle of the arc surface on the side away from the high-pressure gas cylinder (2).

8. The rapid throwing device based on tail-end micro-stroke actuation mounted on a UAV according to claim 1, characterized in that, The overall projectile mass of the warhead (5), including the capture net and the counterweight (6), is 150-450 g. The area of ​​the capture net after being thrown is not less than 20 m². The initial inflation pressure of the high-pressure gas cylinder (2) is 10-25 MPa.

9. The rapid throwing device based on tail-end micro-stroke actuation mounted on a UAV according to claim 1, characterized in that, The axial micro-stroke displacement of the push rod (1) is no more than 2 mm.

10. A drone, characterized in that, The UAV is equipped with a rapid launching device as described in any one of claims 1-9 via a quick interface under the fuselage or wing. The UAV also includes an onboard actuator, the output end of which is located at the end of the push rod (1) away from the warhead (5).

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