Box-type launch unmanned aerial vehicle locking and releasing mechanism

Abstract

The utility model discloses a locking and releasing mechanism of a box-type launching unmanned aerial vehicle, and belongs to the field of launching of box-type launching unmanned aerial vehicles. Comprising a rotating shaft, a base, a locking hook and a connecting belt, the rotating shaft is horizontally fixed above the base; the locking hook is sleeved on the rotating shaft and can rotate around the rotating shaft; the front portion of the locking hook is used for being connected with an unmanned aerial vehicle to be launched, the rear portion of the locking hook is connected with the connecting belt, and the lower portion of the connecting belt is fixed. After a booster rocket on the to-be-launched unmanned aerial vehicle is ignited, the connecting belt can be fused. The unmanned aerial vehicle is locked through cooperation of the locking hook and the connecting belt during transportation and storage, the connecting belt is quickly fused through high temperature generated by ignition of the booster rocket during launching, and therefore automatic release of the unmanned aerial vehicle is achieved, and the unmanned aerial vehicle release device has the advantages of being low in cost, safe, reliable, small in release impact force, simple in structure and convenient to assemble.

Description

Technical Field

[0001] This utility model relates to a box-type launcher drone launch auxiliary mechanism, specifically a box-type launcher drone locking and releasing mechanism, belonging to the field of box-type launcher drone launch. Background Technology

[0002] Currently, with the continuous advancement of technology, the requirements for military confrontation training are becoming increasingly stringent. Large-scale collaborative operations, such as drone swarming and clustering, are increasingly becoming a development trend and will be an important form of combat on the future battlefield. To achieve this, drones need to possess dense, rapid, and efficient launch capabilities.

[0003] Currently, most drones utilize a distributed launch system, which suffers from low efficiency, poor safety, and significant launch difficulties. In contrast, containerized launch systems offer significant advantages: flexible site relocation, high launch efficiency, fewer operator requirements, enhanced safety, and ease of large-scale launches (group launches). Therefore, containerized launch is the future trend. The launch release mechanism is a crucial component of containerized launch systems. During transport and relocation of the launch container, it connects and locks the drone to the container, automatically releasing the drone upon launch. It directly impacts the production cost, transportation, and launch reliability of the launch container.

[0004] In existing launch containers, the locking and release mechanisms mostly employ explosive bolts, forced-force release, and electronic locks. Explosive bolts are expensive, and the explosives inside are highly hazardous materials, making storage, transportation, and management extremely complex. Forced-force release mechanisms utilize the immense thrust generated by the booster rocket during UAV launch to break the locking and release mechanism, achieving the release purpose. However, this mechanism requires the launch container to provide very high-strength support, increasing the launch container's weight and launch costs, and has poor safety, failing to meet the requirements for low-cost, high-efficiency launch of container-launched UAVs. Summary of the Invention

[0005] The technical problem to be solved by this utility model is to overcome the defects of the existing technology and provide a low-cost, efficient and reliable box-type launcher lock-up release mechanism.

[0006] To solve the above-mentioned technical problems, the box-type launcher lock-up and release mechanism provided by this utility model includes a rotating shaft, a base, a locking hook, and a connecting belt;

[0007] The rotating shaft is horizontally fixed above the base; the locking hook is fitted onto the rotating shaft and can rotate around the rotating shaft;

[0008] The front part of the locking hook is used to connect to the drone to be launched, the rear part of the locking hook is connected to the connecting belt, and the lower part of the connecting belt is fixed.

[0009] The connecting strip can be melted after the booster rocket on the drone to be launched is ignited.

[0010] In this invention, a limiting mechanism is provided between the rotating shaft and the locking hook to limit the rotation range of the locking hook.

[0011] In this utility model, the limiting mechanism includes a plurality of first arc-shaped protrusions spaced apart circumferentially along the axis of rotation and a plurality of second arc-shaped protrusions spaced apart circumferentially on the locking hook;

[0012] Any of the first arc-shaped protrusions / second arc-shaped protrusions can be inserted into the gap between any two adjacent second arc-shaped protrusions / first arc-shaped protrusions, and there is an movable interval between the first arc-shaped protrusions and the second arc-shaped protrusions.

[0013] In this invention, the connecting strip is an aluminum strip or a plastic strip.

[0014] The beneficial effects of this utility model are as follows: (1) During transportation and storage, the drone is locked by the cooperation of the locking hook and the connecting belt. During launch, the connecting belt is quickly melted by the high temperature generated by the ignition of the booster rocket, thereby realizing the automatic release of the drone. It has the advantages of low cost, safety and reliability, small release impact force, simple structure and convenient assembly; (2) A limiting mechanism is provided between the rotating shaft and the locking hook, which can effectively control the rotation amplitude of the locking hook and prevent the locking hook from hitting the drone due to excessive rotation angle, thus affecting the safety of the drone; (3) Through the cooperation of the first arc-shaped protrusion and the second arc-shaped protrusion, the rotation amplitude of the locking hook can be reliably controlled while ensuring the flexible rotation of the locking hook; (4) The connecting belt is made of aluminum or plastic, which can not only ensure the stable and reliable locking of the drone during transportation and storage, but also quickly melt and break during launch, improving the stability of the drone launch; (5) This utility model does not have high requirements for the strength of the base, which can effectively reduce the structural weight of the launch box and make it easier to maneuver during the launch process. Attached Figure Description

[0015] To more clearly illustrate the specific embodiments of this utility model or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0016] Figure 1 Schematic diagram of the locking and releasing mechanism for a box-type launcher drone;

[0017] Figure 2 A schematic diagram of the partial assembly of the locking and release mechanism for a box-type launcher drone;

[0018] Figure 3 Schematic diagram of the assembly of the interlocking release mechanism for the UAV and the box-type UAV launcher;

[0019] Figure 4 This is a schematic diagram of the drone's launch status;

[0020] In the diagram: 1-Box-type launcher UAV locking and release mechanism, 1.1-Locking hook, 1.2-Rotating shaft, 1.3-Left bracket, 1.4-Bracket fixing seat, 1.5-Right bracket, 1.6-Connecting belt, 1.7-Connecting belt fixing seat, 1.8-Base, 1.9-First arc-shaped protrusion, 1.10-Second arc-shaped protrusion, 1.11-Through hole, 1.12-Opening, 2-Booster rocket, 3-UAV to be launched, 4-UAV connector. Detailed Implementation

[0021] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, and not all embodiments. The components of the embodiments of this utility model described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0022] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0023] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0024] In the description of this utility model, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product of this utility model is in use. They are only for the convenience of describing this utility model 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 utility model. In addition, the terms "first," "second," and "third," etc., are only used to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0025] Furthermore, terms such as "horizontal," "vertical," and "sag" do not imply that components must be absolutely horizontal or suspended, but rather that they can be slightly tilted. For example, "horizontal" simply means that its direction is more horizontal relative to "vertical," and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0026] In the description of this utility model, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0027] The following detailed description, in conjunction with the accompanying drawings, outlines some embodiments of the present invention. Unless otherwise specified, the following embodiments and features can be combined with each other.

[0028] like Figure 1 and 2 As shown, the locking and releasing mechanism of the box-type launch UAV in this embodiment includes a locking hook 1.1, a rotating shaft 1.2, a left bracket 1.3, a bracket fixing seat 1.4, a right bracket 1.5, a connecting strap 1.6, a connecting strap fixing seat 1.7, and a base 1.8. The base 1.8 is installed inside the launch box of the UAV. The left bracket 1.3 and right bracket 1.5 are fixed to the base 1.8 via bracket fixing seats 1.41. The rotating shaft 1.2 is horizontally mounted above the base 1.8. Both ends of the rotating shaft 1.2 are square structures, placed in the top grooves of the left bracket 1.3 and right bracket 1.5 respectively, and connected and fixed to the left bracket 1.3 and right bracket 1.5 respectively. The locking and releasing mechanism of the box-type launch UAV in this embodiment does not require high strength from the base 1.8, thus effectively reducing the structural weight of the launch box and facilitating launch maneuvers.

[0029] The locking hook 1.1 has a through hole 1.11 in the middle, through which it is fitted onto the rotating shaft 1.2, allowing it to rotate around the shaft 1.2. The front end of the locking hook 1.1 has an opening 1.12, through which it connects to the drone via the drone connector 4. The rear end of the locking hook 1.1 is connected to the connecting strap 1.6.

[0030] The top end of the connecting strap 1.6 is connected to the rear end of the locking hook 1.1, and the bottom end of the connecting strap 1.6 is fixedly connected to the connecting strap fixing seat 1.7. The connecting strap fixing seat 1.7 is fixedly installed on the base 1.8.

[0031] Two first arc-shaped protrusions 1.9 are provided in the middle of the rotating shaft 1.2, and the two first arc-shaped protrusions 1.9 are evenly spaced along the circumference of the rotating shaft 1.2. Similarly, two second arc-shaped protrusions 1.10 are provided on the outer side of the through hole 1.11 on the locking hook 1.1, and the two second arc-shaped protrusions 1.10 are evenly spaced along the circumference of the through hole 1.11. The second arc-shaped protrusions 1.10 can be inserted into the gap between the two first arc-shaped protrusions 1.9, and a gap is maintained between them. The gap between the first arc-shaped protrusions 1.9 and the second arc-shaped protrusions 1.10 is the maximum range of rotation that the rotating shaft 1.2 can ultimately achieve. Through the cooperation between the first arc-shaped protrusions 1.9 and the second arc-shaped protrusions 1.10, the rotation angle of the locking hook 1.1 can be effectively limited, preventing the locking hook 1.1 from rotating too much and impacting the drone, thus preventing unnecessary damage to the drone.

[0032] As those skilled in the art should know, the number of the first arc-shaped protrusion 1.9 and the second arc-shaped protrusion 1.10 can be dynamically selected and adjusted according to actual needs.

[0033] In this embodiment, the connecting strip 1.6 is made of existing polyethylene, with a melting point of 120-136℃. Polyethylene is not only low in cost and high in strength, but it can also provide a stable lock for the drone 3 to be launched, and it can melt and break quickly, enabling stable and reliable launch of the drone.

[0034] In practical use, the connecting strip 1.6 can also be made of existing polyamide with a melting point of about 120°C.

[0035] like Figures 1 to 4 As shown, during assembly, the drone to be launched 3 is connected to the front end of the locking hook 1.1 of the box-type launch drone locking and release mechanism 1 via the drone connector 4. The booster rocket 2 is installed inside the launch box, and the flame nozzle of the booster rocket 2 is directly facing the connecting belt 1.6.

[0036] During the transportation and storage of the drone 3 to be launched, the drone connector 4 connects the locking hook 1.1 and the drone 3 to be launched. The connecting strap 1.6 connects the rear end of the locking hook 1.1 and the connecting strap fixing seat 1.7 respectively. The drone 3 to be launched is fixed in the launch box by the constraints of the guide rail, locking hook 1.1 and connecting strap 1.6 in the launch box. The overload impact generated during the transportation of the drone 3 to be launched is transmitted to the guide rail and connecting strap 1.6. The connecting strap 1.6 with a certain strength ensures that the drone 3 to be launched cannot move freely in the launch box, thereby achieving the purpose of locking and fixing.

[0037] When the drone 3 is launched, the booster rocket 2 ignites, generating extremely high temperatures (typically around 3000℃). The flames are directly sprayed onto the connecting belt 1.6, causing it to melt rapidly under the high temperature. After the connecting belt 1.6 melts, the rotational freedom of the locking hook 1.1 is instantly released, and the drone 3's freedom along the slide rail towards the nose is simultaneously released. Under the thrust of the booster rocket 2, the drone 3 moves along the slide rail towards the nose. The drone connector 4 drives the locking hook 1.1 to rotate, and the connector 4 slides out from the opening 1.12 at the front end of the locking hook 1.1, thus releasing the drone. After the shaft 1.2 rotates to a certain angle, the first arc-shaped protrusion 1.9 and the second arc-shaped protrusion 1.10 engage, restricting the continued rotation of the locking hook 1.1 and preventing it from colliding with the drone due to excessive rotation. This completes the launch of the box-type drone.

[0038] In another embodiment, the connecting strip 1.6 is made of existing aluminum, which has a melting point of about 660°C and has the advantages of being lightweight, strong, and quick to break.

[0039] This utility model provides a concept for a locking and releasing mechanism for a box-type launched unmanned aerial vehicle (UAV). Many methods and approaches exist for implementing this technical solution; the above description is merely a preferred embodiment. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principle of this utility model, and these improvements and modifications should also be considered within the scope of protection of this utility model. All components not explicitly stated in this embodiment can be implemented using existing technology.

Claims

1. A box-type launcher unmanned aerial vehicle (UAV) locking and release mechanism, characterized in that: Includes a pivot, base, locking hook, and connecting strap; The rotating shaft is horizontally fixed above the base, and the locking hook is fitted onto the rotating shaft and can rotate around the rotating shaft; The front part of the locking hook is used to connect to the drone to be launched, the rear part of the locking hook is connected to the connecting strap, and the lower part of the connecting strap is fixed. The connecting strip can be melted after the booster rocket on the drone to be launched is ignited.

2. The box-type launcher UAV locking and release mechanism according to claim 1, characterized in that: A limiting mechanism is provided between the rotating shaft and the locking hook to limit the rotation range of the locking hook.

3. The box-type launcher UAV locking and release mechanism according to claim 2, characterized in that: The limiting mechanism includes multiple first arc-shaped protrusions spaced circumferentially along the axis of rotation and multiple second arc-shaped protrusions spaced circumferentially on the locking hook; Any of the first arc-shaped protrusions / second arc-shaped protrusions can be inserted into the gap between any two adjacent second arc-shaped protrusions / first arc-shaped protrusions, and there is an movable interval between the first arc-shaped protrusions and the second arc-shaped protrusions.

4. The box-type launcher interlocking release mechanism according to any one of claims 1 to 3, characterized in that: The connecting strip is an aluminum strip or a plastic strip.

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