Unmanned aerial vehicle on-board fuze decoding method, fuze decoding device and unmanned aerial vehicle

Abstract

The application includes a method for arming a fuze on a UAV, a warhead is arranged on a UAV including at least one pair of foldable arms, a fuze arming pin connected by a compression spring is arranged on the warhead, an arming device is arranged between the warhead and the foldable arms, one end of the arming device is connected to the foldable arms, and the other end is capable of abutting against the fuze arming pin, the foldable arms are folded, the foldable arms drive the arming device to abut against the fuze and compress the compression spring, the fuze arming pin is retracted into the warhead, and the fuze is in an armed state, the foldable arms are unfolded, the foldable arms drive the arming device to separate from the fuze, the fuze arming pin is ejected from the warhead under the action of the compression spring, and the fuze is armed. The application also includes a fuze arming device and a UAV including the fuze arming device. The application can quickly and effectively arm a fuze on a UAV.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle airborne fuze arming device and an unmanned aerial vehicle. BACKGROUND

[0002] A common barrel type unmanned aerial vehicle, wherein the fuze of the warhead loaded on the unmanned aerial vehicle is armed once by pulling out the pin. The existing fuze arming solution relies on the recoil force generated when the unmanned aerial vehicle is launched out of the barrel to arm the fuze. However, in actual application, the acceleration of the unmanned aerial vehicle when it is launched out of the barrel cannot be too large due to the structural strength of the unmanned aerial vehicle body, thereby resulting in insufficient recoil force, which may cause the fuze to fail to be armed by the recoil force of the unmanned aerial vehicle when it is launched out of the barrel. In view of the above problem, the present application chooses to abandon the reliance on the recoil force and instead uses the unfolding action of the foldable arms of the unmanned aerial vehicle when it is launched out of the barrel to achieve successful arming of the fuze. SUMMARY

[0003] The present application aims to provide a fuze arming method and device that relies on the recoil force of the unmanned aerial vehicle after launch and uses the unfolding of the foldable arms of the unmanned aerial vehicle when it is launched to achieve arming of the fuze.

[0004] To achieve the above-mentioned purpose, the present application adopts the following technical solution:

[0005] The unmanned aerial vehicle airborne fuze arming method is arranged on a unmanned aerial vehicle comprising at least one pair of foldable arms.

[0006] A fuze arming pin connected by a compression spring is arranged in the warhead.

[0007] An arming device is arranged between the warhead and the foldable arms, one end of the arming device is connected to the foldable arms, and the other end can abut against the fuze arming pin.

[0008] The foldable arms are folded, the foldable arms drive the arming device to abut against the fuze and compress the compression spring, the fuze arming pin is retracted into the warhead, and at this time the fuze is in an armed state.

[0009] The foldable arms are unfolded, the foldable arms drive the arming device to separate from the fuze, the fuze arming pin is ejected from the warhead under the action of the compression spring, and at this time the fuze is armed.

[0010] The present application also includes a fuze arming device, which comprises two half-round hoops, a guide rail and a return spring.

[0011] The return spring is connected between the two half-round hoops, and the two half-round hoops are slidingly installed on the guide rail, and the guide rail is installed on the unmanned aerial vehicle.

[0012] The two semicircular hoops are respectively connected to the two foldable arms. When the foldable arms are retracted, they drive the two semicircular hoops to move towards each other. At the same time, the return spring is compressed, and at least one semicircular hoop abuts against the fuse safety pin and compresses the compression spring to put the fuse in a safe state. When the foldable arms are extended, the return spring drives the two semicircular hoops to move away from each other, and the semicircular hoops separate from the fuse safety pin. The compression spring extends and ejects the fuse safety pin from the warhead, thereby releasing the fuse from its safe state.

[0013] Furthermore, the fuse release device also includes two levers, which are rotatably mounted on the UAV, located on both sides of the semicircular hoop and in contact with it, and connected to the foldable arm.

[0014] Furthermore, a connecting rod connects the lever to the foldable arm.

[0015] Furthermore, a rotating hinge is provided at one end of the lever, which is used to mount the drone.

[0016] The present invention also includes an unmanned aerial vehicle (UAV) that includes the aforementioned fuse release device.

[0017] Beneficial effects of this invention:

[0018] In this invention, the foldable arm of the UAV retracts during storage, driving a semi-circular clamp to compress and secure the warhead fuse. After the UAV launches from the launch tube, a return spring drives the semi-circular clamp to separate from the fuse, causing the fuse to eject and release the fuse. This invention effectively avoids the inability to release the fuse due to insufficient recoil after UAV launch, increasing the reliability of normal fuse release. Attached Figure Description

[0019] Figure 1 Axonometric view of the connection relationship between the fuse release device and the foldable arm of this invention;

[0020] Figure 2 for Figure 1 Front view;

[0021] In the picture:

[0022] 1. Semicircular hoop, 2. L-shaped bracket, 3. Guide rail, 4. Return spring, 5. Lever, 6. Connecting rod, 7. Hinge, 8. Warhead, 9. Foldable arm, 10. Slider, 11. Fuze safety pin. Detailed Implementation

[0023] To make the above-mentioned objects, features, and advantages of the present invention more apparent and understandable, specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings. Many specific details are set forth in the following description to provide a thorough understanding of the present invention. However, the present invention can be practiced in many other ways different from those described herein, and those skilled in the art can make similar modifications without departing from the spirit of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0024] In the description of this invention, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0025] This invention includes a method for deactivating an airborne fuse on a drone, wherein a warhead 8 is mounted on a drone including at least a pair of foldable arms 9;

[0026] A fuse safety pin 11 connected by a compression spring is provided in the warhead 8;

[0027] A release device is provided between the warhead 8 and the foldable arm 9. One end of the release device is connected to the foldable arm 9, and the other end can abut against the fuse safety pin 11.

[0028] Fold the foldable arm 9, which in turn drives the release device to press against the fuse and compress the compression spring, causing the fuse safety pin 11 to retract into the warhead 8, at which point the fuse is in a safe state;

[0029] When the foldable arm 9 is unfolded, the foldable arm 9 causes the release device to separate from the fuse. The fuse safety pin 11 is ejected from the warhead 8 under the action of the compression spring, at which point the fuse is released.

[0030] Understandably, this invention is applicable to foldable, tube-fired drones. By linking the fuse release mechanism with the foldable arm 9 of the drone, the fuse can be locked or unlocked through the extension or folding of the foldable arm 9. Compared to unlocking the fuse through the recoil of the drone, this invention has higher reliability and will not fail to unlock due to insufficient recoil.

[0031] Reference Figure 1 , 2 The present invention also includes a fuse release device, which includes two semi-circular hoops 1, a guide rail 3 and a return spring 4;

[0032] The reset spring 4 is connected between the two semicircular hoops 1, and the two semicircular hoops 1 are slidably mounted on the guide rail 3, which is mounted on the drone;

[0033] The two semicircular hoops 1 are respectively connected to the two foldable arms 9. When the foldable arms 9 are retracted, they drive the two semicircular hoops 1 to move towards each other. At the same time, the return spring 4 is compressed, and at least one semicircular hoop 1 abuts against the fuse safety pin 11 and compresses the compression spring to put the fuse in a safe state. When the foldable arms 9 are extended, the return spring 4 drives the two semicircular hoops 1 to move away from each other, and the semicircular hoops 1 separate from the fuse safety pin 11. The compression spring extends and ejects the fuse safety pin 11 from the warhead 8, thereby releasing the fuse from its safe state.

[0034] It should be noted that the fuse release device of the present invention is used in conjunction with a drone equipped with at least a pair of foldable arms 9 that are launched through a launch tube. The fuse release device is mounted on the drone and located at the warhead 8 of the drone. The warhead 8 of the drone has a through hole, through which a fuse safety pin 11 is connected via a compression spring. When the fuse safety pin 11 is inserted into the warhead 8, the fuse is in a safe state; when the fuse safety pin 11 is ejected, the fuse is released.

[0035] Understandably, the present invention includes two semi-circular hoops 1 to enclose the UAV warhead 8, allowing one of the two semi-circular hoops 1 to abut against the fuse safety pin 11. Furthermore, a return spring 4 connects the two semi-circular hoops 1. When the foldable arm 9 on the UAV is folded, the foldable arm 9 can drive the two semi-circular hoops 1 to slide on the guide rail 3, thereby pressing the fuse safety pin 11 and the compression spring into the UAV warhead 8, ensuring the fuse is in a safe state. This is especially true when the UAV is retracted into the launch tube, where the foldable arm 9 is constrained by the launch tube, further constraining the fuse safety pin 11. When the foldable arm 9 of the UAV is extended, the two semi-circular hoops 1 separate from the warhead 8 under the action of the return spring 4, and the fuse safety pin 11 pops out under the action of the compression spring, thus releasing the fuse, especially when the UAV is launched from the launch tube.

[0036] Reference Figure 1 , 2 In some embodiments, the fuse release device further includes two levers 5, which are rotatably mounted on the UAV, located on both sides of the semicircular hoop 1 and in contact with it, and connected to the foldable arm 9. Understandably, when the foldable arm 9 is folded, it moves the two semicircular hoop 1 via the levers 5.

[0037] Reference Figure 1 , 2 In some embodiments, the bottoms of the two semicircular hoops 1 are connected to L-shaped brackets 2, and the bottoms of the L-shaped brackets 2 are connected to sliders 10, which are slidably mounted on guide rails 3. Furthermore, the L-shaped brackets 2 are also provided with positioning blocks, and positioning pins are mounted on the positioning blocks. The end of the return spring 4 is fitted onto the positioning pin.

[0038] Reference Figure 1 , 2 In some embodiments, a connecting rod 6 connects the lever 5 to the foldable arm 9. Since there is a certain distance between the UAV's warhead 8 and the foldable arm 9, adding the connecting rod 6 between the lever 5 and the foldable arm 9 allows the foldable arm 9 to better exert a pushing effect on the lever 5.

[0039] Reference Figure 1 , 2 In some embodiments, one end of the lever 7 is provided with a rotating hinge 7, which is used to mount the lever 5 onto the drone. It should be noted that those skilled in the art can also choose other rotating mounting methods to mount the lever 5 onto the drone, such as mounting the lever 5 on a rotating shaft, and rotatably mounting the lever 5 onto the drone via the rotating shaft.

[0040] In addition, the present invention also includes a drone that includes the above-mentioned fuse release device.

Claims

1. A method for disarming an airborne fuse on a UAV, characterized in that, The warhead is mounted on a drone including at least one pair of foldable arms; The warhead is equipped with a fuse safety pin connected by a compression spring; A release device is provided between the warhead and the foldable arm. One end of the release device is connected to the foldable arm, and the other end can abut against the fuse safety pin. The foldable arm is folded, and the foldable arm drives the release device to press against the fuse and compress the compression spring, so that the fuse safety pin is retracted into the warhead, at which point the fuse is in a safe state; The foldable arm unfolds, causing the release device to separate from the fuse. The fuse safety pin is ejected from the warhead under the action of the compression spring, at which point the fuse is released.

2. A fuse release and deactivation device, characterized in that, The unarmor protection is removed using the unmanned aerial vehicle airborne fuse removal method described in claim 1; The fuse release device includes two semi-circular hoops, a guide rail, and a return spring; The reset spring is connected between the two semicircular hoops, and the two semicircular hoops are slidably mounted on the guide rail, which is mounted on the drone; The two semicircular hoops are respectively connected to the two foldable arms. When the foldable arms are retracted, they drive the two semicircular hoops to move towards each other. At the same time, the return spring is compressed, and at least one semicircular hoop abuts against the fuse safety pin and compresses the compression spring to put the fuse in a safe state. When the foldable arms are extended, the return spring drives the two semicircular hoops to move away from each other, and the semicircular hoops separate from the fuse safety pin. The compression spring extends and ejects the fuse safety pin from the warhead, thereby releasing the fuse from its safe state.

3. The fuse release device according to claim 2, characterized in that, It also includes two levers, which are rotatably mounted on the drone, located on both sides of the semicircular hoop and in contact with it, and connected to the foldable arm.

4. The fuse release device according to claim 3, characterized in that, A connecting rod connects the lever to the foldable arm.

5. The fuse release and deactivation device according to any one of claims 2-4, characterized in that, A rotating hinge is provided at one end of the lever, and the drone is mounted on the drone via the rotating hinge.

6. A drone, characterized in that, The drone includes the fuse release device as described in claim 5.

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