A device for separating a shell from a launching device

Abstract

The application provides a bullet support-unplug cooperative separation device and a launching device, which comprises a bottom plate, a top plate and a stand column, the bottom plate and the top plate are connected through the stand columns, the top plate is provided with a first unplug used for connecting a UAV, the bottom plate is hung through a first rope and is provided with a second unplug used for connecting a rear cover of a launching cylinder, the first unplug and the second unplug are connected through a cable, the bottom plate and the rear cover of the launching cylinder are connected through a second rope, and the length of the first rope is smaller than that of the second rope. The bullet support structure is combined with the unplug, reliable separation of the bullet support and the UAV in the launching process is ensured, and the UAV can be powered and wired communicated through external equipment.

Description

Technical Field

[0001] This application relates to the field of unmanned aerial vehicle (UAV) launch technology, specifically to a sabot-disengagement coordinated separation device, and also to a launch device including the coordinated separation device. Background Technology

[0002] When a rotary-wing drone carries hazardous equipment and launches it from its launch tube, it is typically powered off during loading to ensure safety. Technicians must remotely control the drone's power supply and maintain internal communication to ensure the internal equipment is functioning correctly before launch. In reality, most sabots lack integrated detachable inserts. When a drone carries hazardous materials such as gunpowder, if this detachable insert is not integrated, it must be powered on externally before being inserted into the launch tube. This could lead to accidental power-on triggering, causing the gunpowder to explode and creating a safety hazard. Utility Model Content

[0003] In view of this, this application provides a sabot-disengagement coordinated separation device, which combines the sabot structure with disengagement to ensure reliable separation of the sabot from the UAV during launch, and also allows the UAV to be powered and wired communicated via external equipment.

[0004] The technical solution adopted in this application is as follows: A sabot-disengagement coordinated separation device includes a base plate, a top plate, and columns. The base plate and the top plate are connected by a plurality of columns. The top plate is provided with a first disengagement device for connecting a UAV. The base plate is connected by a first rope to a second disengagement device for connecting a launch tube rear cover. The first and second disengagement devices are connected by a cable. A second rope is connected between the base plate and the launch tube rear cover. The length of the first rope is less than the length of the second rope.

[0005] Furthermore, the base plate has a circular structure.

[0006] Furthermore, the outer diameter of the base plate is equal to the inner diameter of the launch tube of the launching device.

[0007] Furthermore, the top plate is a circular structure with symmetrical notches.

[0008] Furthermore, the outer diameter of the top plate is less than or equal to the inner diameter of the launch tube of the launching device.

[0009] Furthermore, the top plate is provided with a blocking block with a baffle groove.

[0010] Furthermore, hooks are provided on the base plate.

[0011] This application also includes a launching device, which includes the sabot-disengagement coordinated separation device.

[0012] The beneficial effects of this application are: This application enables the drone to be mounted in the launching device via a sabot. At the same time, the sabot's detachment structure allows the operator to remotely control the drone's power supply and conduct wired communication, while also ensuring the drone can be separated from the sabot in time during launch. This guarantees the safety of the drone and broadens the applicability of the drone and sabot. Attached Figure Description

[0013] Figure 1 This is a front view of the ejector-disengagement coordinated separation device in the embodiments of this application; Figure 2 This is a side view of the ejector-disengagement coordinated separation device in an embodiment of this application; Figure 3 This is a top view of the sabot-disengagement coordinated separation device in the embodiments of this application. In the diagram: 1 top plate, 2 bottom plate, 3 first disconnection, 4 second disconnection, 5 column, 6 cable, 7 first rope, 8 blocking block, 9 first hook, 10 second hook, 11 notch, 12 retaining groove. Detailed Implementation

[0014] To make the above-mentioned features and advantages of this application more apparent and understandable, the specific embodiments of this application are 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 this application. However, this application can be implemented 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 this application. Therefore, this application is not limited to the specific embodiments disclosed below.

[0015] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "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 application 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 application.

[0016] Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, "multiple" or "several" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0017] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; 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; they can refer to the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0018] To facilitate understanding of the design background of this application, the background technology is further described here. There are generally two ways to launch rotary-wing drones: one is to unfold the drone's rotor, place it on a flat surface, and then directly start the drone for launch; the other is to launch it through a gas launcher with a launch tube.

[0019] The second launch method requires folding the drone and inserting it into a launch tube equipped with a gas generator. The drone is then launched using the thrust generated by the gas generator. Due to the drone's complex structure, directly placing it into the launch tube could cause gas leakage, resulting in insufficient initial launch velocity. Therefore, a sabot is placed inside the launch tube first, followed by the drone. The sabot seals the gas generator, fully bearing the thrust and transferring it to the drone to achieve a higher initial launch velocity. When a rotary-wing drone carries hazardous equipment and launches from the tube using a launch device, it is usually powered off during loading to ensure safety. Technicians need to remotely control the drone's power supply and maintain internal communication to ensure the internal equipment is functioning correctly before launch. However, most sabots lack integrated detachable mechanisms. When carrying hazardous materials such as gunpowder, if these mechanisms are not integrated, the drone must be powered on externally before being inserted into the tube. This could lead to accidental power-on triggering, causing the gunpowder to explode and creating a safety hazard. To address this, a sabot-disengagement coordinated separation device is designed to allow operators to remotely control the power supply and wired communication of the drone, while also ensuring timely separation of the drone from the sabot during launch. This guarantees the safety of drone use and broadens the applicability of both the drone and the sabot.

[0020] Reference Figure 1-3A sabot-disengagement coordinated separation device includes a base plate 2, a top plate 1, and columns 5. The base plate 2 and the top plate 1 are connected by a plurality of columns 5. A first disengagement 3 for connecting a UAV is provided on the top plate 1. A second disengagement 4 for connecting a launch tube rear cover is hung on the base plate 2 by a rope. The first disengagement 3 and the second disengagement 4 are connected by a cable 6. A second rope is connected between the base plate 2 and the launch tube rear cover. The length of the first rope 7 is less than the length of the second rope.

[0021] Specifically, the sabot in this application includes a base plate 2 and a top plate 1, wherein several uprights 5 connect the base plate 2 and the top plate 1, forming a double-layer structure. A first disconnector 3 is provided on the top plate 1. The first disconnector 3 is fixedly installed and inseparable from the top plate 1. The first disconnector 3 is used to connect to an interface on a UAV. When the UAV is placed on the top plate 1, the first disconnector 3 can connect precisely to the UAV's interface. A second disconnector 4 is attached to the base plate 2. The second disconnector 4 is not fixedly connected to the base plate 2 by a first rope 7. The sabot and the second disconnector 4 can move relative to each other for a certain distance but cannot be separated. The second rope connects the sabot to the rear cover of the launch tube, wherein the movement distance of the sabot within the launch tube is limited by the length of the second rope.

[0022] In this application, the sabot is installed inside the launch tube of the launching device. The launch tube includes a front cover and a rear cover. The front cover needs to be removed when launching the UAV, and the rear cover is used to connect to an external control device. The rear cover has several interfaces for connecting to the external control device, and the second disconnector 4 is used to connect to at least one of these interfaces. A gas generator is installed inside the launch tube, and the gas generator connects to the interface on the rear cover, thereby connecting to the external control device. The sabot is installed inside the launch tube to seal the gas generator and simultaneously support the UAV. When the gas generator ignites, it generates a large amount of high-pressure gas, which propels the sabot to move rapidly within the launch tube and simultaneously propels the UAV to move rapidly. During the launch of the drone and the sabot, the sabot and drone will move first due to the connection between the second release 4 and the interface on the rear cover. Once the first rope 7, which connects to the second release 4, is fully extended, the sabot applies a pulling force to the second release 4, separating it from the launch tube's rear cover. The drone and sabot continue to move rapidly due to inertia. When the second rope is fully extended, the sabot stops moving. At this point, the drone separates from the sabot and continues to move rapidly due to inertia, separating from the first release 3. The drone launch is complete. The restriction imposed by the second rope prevents the sabot from exiting the launch tube, ensuring it won't fly out and hit nearby people or objects. It should be noted that the length of the cable 6 connecting the first release 3 and the second release 4 should be greater than the length of the first rope 7 to prevent the sabot from directly dragging the second release 4 through the cable 6, which could damage the cable 6.

[0023] Reference Figure 3 It is understood that the base plate 2 has a circular structure.

[0024] Specifically, the launch tube of a UAV launcher is usually circular in cross-section. Therefore, setting the base plate 2 to be circular can ensure the applicability of the sabot and the launch tube.

[0025] It is understood that the outer diameter of the base plate 2 is equal to the inner diameter of the launch tube of the launching device.

[0026] Specifically, the base plate 2 needs to seal the gas generator to ensure that the high-pressure gas generated after the gas generator is ignited will not leak and can be used to propel the sabot and the UAV. Therefore, the outer diameter of the base plate 2 is set to be equal to the inner diameter of the launch tube of the launching device. However, it should be noted that the side wall of the base plate 2 and the inner wall of the launch tube should be smoothed to ensure that the sabot can move smoothly and quickly inside the launch tube.

[0027] Reference Figure 3 It is understood that the top plate 1 is a circular structure with symmetrical notches 11.

[0028] Specifically, the launch tube of a typical UAV launcher has a circular cross-section. Therefore, setting the top plate 1 to a circular structure ensures the applicability of the sabot to the launch tube. It should be noted that the top plate 1 can also be set to other shapes that can be freely placed into the launch tube. This application does not limit this, as long as the movement of the sabot is unrestricted and it can support the UAV. In addition, in this application, the length of the UAV arm is greater than the length of the body. A support notch 11 is provided on the top plate 1, which allows the body with the arm folded to be inserted. In this way, the arm can sink down to fit against the top of the sabot through the notch 11, while ensuring that the interface on the UAV is connected to the first disengagement 3.

[0029] It is understood that the outer diameter of the top plate 1 is less than or equal to the inner diameter of the launch tube of the launching device.

[0030] Specifically, in this application, the gas generator is mainly sealed by the base plate 2, and the top plate 1 does not need to perform a sealing function. Therefore, its outer diameter can be small enough to support the drone.

[0031] Reference Figure 1-3 It is understood that the top plate 1 is provided with a blocking block 8 with a baffle groove 12.

[0032] Specifically, in this application, the drone is provided with a protrusion that matches the groove 12. When the drone is placed on the top plate 1, the protrusion can be inserted into the groove 12, thereby limiting the drone's swaying and preventing the drone from separating from the first disengagement 3. It should be noted that the groove 12 is only provided to prevent the drone from swaying and will not obstruct the drone's movement along the launch tube.

[0033] Referring to 1 and 2, hooks are provided on the base plate 2.

[0034] Specifically, the hooks on the base plate 2 are used to connect the second rope.

[0035] This application also includes a launching device, which includes the sabot-disengagement coordinated separation device.

[0036] The above embodiments are merely preferred technical solutions of this application and should not be considered as limitations on this application. The embodiments and features described therein can be arbitrarily combined without conflict. The scope of protection of this application should be limited to the technical solutions described in the claims, including equivalent substitutions of the technical features described in the claims. That is, equivalent substitutions and improvements within this scope are also within the scope of protection of this application.

Claims

1. A sabot-disengagement coordinated separation device, characterized in that, The device includes a base plate, a top plate, and columns. The base plate and the top plate are connected by a plurality of columns. The top plate is provided with a first detachable connector for connecting a drone. The base plate is connected by a first rope to a second detachable connector for connecting a launch tube rear cover. The first detachable connector and the second detachable connector are connected by a cable. A second rope connects the base plate and the launch tube rear cover. The length of the first rope is less than the length of the second rope.

2. The sabot-disengagement coordinated separation device according to claim 1, characterized in that, The base plate has a circular structure.

3. The sabot-disengagement coordinated separation device according to claim 2, characterized in that, The outer diameter of the base plate is equal to the inner diameter of the launch tube of the launching device.

4. The sabot-disengagement coordinated separation device according to claim 1, characterized in that, The top plate is a circular structure with symmetrical notches.

5. The sabot-disengagement coordinated separation device according to claim 4, characterized in that, The outer diameter of the top plate is less than or equal to the inner diameter of the launch tube of the launching device.

6. A sabot-disengagement coordinated separation device according to claim 2 or 4, characterized in that, The top plate is provided with a blocking block with a baffle groove.

7. The sabot-disengagement coordinated separation device according to claim 6, characterized in that, The base plate is equipped with hooks.

8. A launching device, characterized in that, The launching device includes the sabot-disengagement coordinated separation device as described in claim 7.

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