Power assembly for launching unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicle launching, in particular to a power assembly for unmanned aerial vehicle launching, which comprises a launching cylinder and a power assembly, the launching cylinder is used for loading an unmanned aerial vehicle, the power assembly is used for providing power to launch the unmanned aerial vehicle from the launching cylinder, and the power assembly is arranged at the tail end of the launching cylinder; the power assembly comprises a shell, a generation chamber is arranged in the shell, a launcher is arranged in the generation chamber and emits the unmanned aerial vehicle through gas generated by explosion, an igniter is arranged on the shell, one end of the igniter is located in the generation chamber, the other end of the igniter penetrates through the bottom of the shell and is connected with a lead, and the lead is used for igniting the launcher; by the adoption of the power assembly, the mobility of the power assembly is improved, battle transfer of an own soldier is facilitated, the danger that the own soldier is locked by an enemy is reduced, and the safety of the own soldier during battle is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of UAV launch, in particular to a power component for UAV launch. Background Art

[0002] With the development of drone technology, the scope of application of drones is becoming more and more extensive. With the use of drones on the international battlefield, the strategic position of drones on the battlefield is becoming higher and higher. The use of drones on the battlefield can, on the one hand, reduce casualties of one's own personnel, and on the other hand, achieve precise strikes on the enemy.

[0003] Chinese patent CN220595241U discloses a spring-powered barrel-type launch device for a small unmanned aerial vehicle, including a launch tube, two baffles fixedly connected to the interior of the launch tube, a drone body movably connected to the top of the two baffles and located inside the launch tube, a launch assembly provided inside the launch tube, the launch assembly including a gas storage tank fixedly connected to the interior of the launch tube, a accommodating chamber provided inside the gas storage tank, an anti-tilt assembly provided outside the launch tube, an air pressure pump fixedly connected to the outside of the launch tube, and an output end of the air pressure pump extending into the interior of the gas storage tank.

[0004] However, although the spring-powered barrel-type launcher of the small UAV can realize the barrel launch of the UAV, the inventors found that the launch assembly of the spring-powered barrel-type launcher of the small UAV still has some deficiencies in actual use, specifically:

[0005] The launching assembly includes a gas storage tank, which is connected to an external air pressure pump to realize the barrel launch of the UAV through compressed air. First, in order to maintain the thrust of the compressed air, the gas storage tank usually requires a larger capacity, resulting in a larger volume of the gas storage tank. Secondly, the operation of the air pressure pump usually requires an external power supply, so that the launching assembly must be equipped with both an air pressure pump and an external power supply. This makes the launching assembly inconvenient to move, reducing the mobility of the small UAV's spring-powered barrel launching device. Especially on a battlefield with changing situations, combat equipment with low mobility can easily hinder the transfer of one's own soldiers, increase the risk of one's own soldiers being locked by the enemy, and further threaten the lives of one's own soldiers.

[0006] Therefore, based on the above-mentioned shortcomings, there is an urgent need to design a power component for launching UAVs. Utility Model Content

[0007] The purpose of the present utility model is to provide a power assembly for launching a UAV to address the above-mentioned shortcomings of the current UAV launching device, such as the inconvenience of movement during actual use.

[0008] In order to achieve the above-mentioned purpose of the utility model, the utility model provides the following technical solutions:

[0009] A power assembly for launching a UAV, comprising a launch tube and a power assembly, wherein the launch tube is used to load the UAV, and the power assembly is used to provide power to launch the UAV from the launch tube, wherein the power assembly is arranged at the rear end of the launch tube;

[0010] The power assembly includes a shell, a generating chamber is provided in the shell, a projectile is provided in the generating chamber, the projectile generates gas by explosion to launch the drone from the launch tube, an igniter is provided on the shell, one end of the igniter is located in the generating chamber and connected to the projectile, and the other end passes through the bottom of the shell and is connected to a lead, and the lead is used to ignite the projectile.

[0011] As a preferred technical solution of this application, a first sealing ring is provided between the igniter and the bottom of the generating chamber.

[0012] As a preferred technical solution of this application, an air outlet is provided on the top of the shell, and the gas generated by igniting the projectile enters the launch tube through the air outlet. The number of the air outlet is several.

[0013] As a preferred technical solution of the present application, a plurality of the air outlet holes are distributed in a cross shape along the center of the top of the shell.

[0014] As a preferred technical solution of the present application, a heat-insulating layer is provided between the generating chamber and the air outlet, and the heat-insulating layer has heat-insulating and breathable functions.

[0015] As a preferred technical solution of this application, a fixing plate is provided at the tail end of the launching tube, and the fixing plate is detachably connected to the outer shell.

[0016] As a preferred technical solution of the present application, the housing is connected to the fixing plate by bolts, and the housing and the fixing plate are sealed with sealant.

[0017] As a preferred technical solution of this application, a clamping component is provided below the fixing plate, and the clamping component is clamped with the fixing plate to keep the housing and the fixing plate in a fixed relative position;

[0018] A clamping groove is provided on the side wall of the fixing plate, a clamping strip is provided on the clamping component, the clamping strip is adapted to the clamping groove, and a second sealing ring is provided between the fixing plate and the clamping component.

[0019] As the preferred technical solution of this application, a push block is slidably provided on the card slot, one end of the push block is in contact with a spring, and the other end is in contact with the card strip. The push block and the card strip abut against each other so that the card strip and the card slot maintain a relative position.

[0020] As a preferred technical solution of the present application, a handle is further provided on the clamping component, and the handle is used for being held by hand.

[0021] Compared with the prior art, the present invention has the following beneficial effects:

[0022] 1. In the solution of the present application, a projectile is ignited and exploded to generate gas to propel the drone into flight. Thus, only a generator chamber is required for the projectile explosion to generate the gas used to propel the drone into flight. This eliminates the need for additional equipment to launch the drone, improving the mobility of the power assembly. Furthermore, by igniting and explosively generating gas, only a small amount of projectile and a smaller generator chamber are required to achieve the required thrust. This reduces the size and weight of the power assembly, further improving its mobility, facilitating the combat transfer of friendly soldiers, reducing the risk of friendly soldiers being targeted by the enemy, and improving their combat safety.

[0023] 2. The gas generated by the explosion of the projectile in the launch chamber has a certain pressure. The provision of the gas outlet further pressurizes the gas, increasing the thrust of the gas on the drone, which helps the drone fly farther. The gas outlet holes are distributed in a cross shape along the center of the top of the shell. This arrangement makes the thrust of the gas on the drone more uniform, and the drone's movement in the launch tube more stable, which is conducive to the drone's launch.

[0024] 3. The snap-on design improves the efficiency of power pack replacement compared to bolted connections. In a volatile battlefield, efficient power pack replacement facilitates the launch of more drones and enhances battlefield control for friendly soldiers. The second sealing ring ensures a tight seal between the outer shell and the launch tube.

[0025] 4. The above structure is easy to operate and has a reliable connection. During operation, you only need to press the clamping component toward the fixed plate. During the pressing process, the push block compresses the spring and moves backward. As the bottom of the clamping component contacts the fixed plate, the spring pushes the push block under the action of the spring, and the push block pushes the clamping component to rotate, so that the card strip is locked into the card slot. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 This is a schematic structural diagram of one embodiment of a UAV launch power assembly of the present application;

[0027] Figure 2 This is a schematic cross-sectional view of one embodiment of a power assembly for launching a UAV according to the present application;

[0028] Figure 3 This is a schematic structural diagram of one embodiment of a housing of a power assembly for launching a UAV according to the present application;

[0029] Figure 4 This is a schematic structural diagram of another embodiment of a UAV launch power assembly of the present application;

[0030] Figure 5 This is a partial cross-sectional structural schematic diagram of another embodiment of a power assembly for launching a UAV according to the present application;

[0031] Figure 6 This is a schematic cross-sectional view of another embodiment of a power assembly for launching a UAV according to the present application;

[0032] Markings in the figure: 1-launching tube, 2-power assembly, 3-UAV, 4-fixing plate, 5-clamping component, 6-push block, 7-second sealing ring, 21-housing, 211-generating chamber, 212-air outlet, 22-projectile, 23-igniter, 24-fuse, 25-first sealing ring, 26-thermal insulation layer, 41-slot, 51-card strip, 52-handle, 61-spring. DETAILED DESCRIPTION

[0033] To make the purpose, technical solutions and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be described clearly and completely in conjunction with the accompanying drawings. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of them.

[0034] Therefore, the following detailed description of the embodiments of the present invention is not intended to limit the scope of the claimed invention, but merely represents some embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0035] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features and technical solutions therein can be combined with each other.

[0036] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, it does not need to be further defined or explained in subsequent drawings.

[0037] In the description of this utility model, it should be noted that the terms "upper" and "lower" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, or the orientations or positional relationships in which the utility model product is typically placed when in use, or the orientations or positional relationships commonly understood by those skilled in the art. Such terms are intended solely to facilitate the description of this utility model and simplify the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limitations on this utility model. Furthermore, the terms "first" and "second" and the like are used solely for distinction and description and should not be construed as indicating or implying relative importance.

[0038] Example 1: See Figures 1 to 3 As shown,

[0039] This embodiment provides a power assembly for launching a drone, comprising a launch tube 1 and a power assembly 2. The launch tube 1 is used to load a drone 3, and the power assembly 2 is used to provide power to launch the drone 3 from the launch tube 1. The power assembly 2 is disposed at the rear end of the launch tube 1.

[0040] The power assembly 2 includes a shell 21, a generating chamber 211 is provided in the shell 21, and a projectile 22 is provided in the generating chamber 211. The projectile 22 generates gas by explosion to launch the drone 3 from the launch tube 1. An igniter 23 is provided on the shell 21. One end of the igniter 23 is located in the generating chamber 211 and is connected to the projectile 22, and the other end passes through the bottom of the shell 21 and is connected to a lead 24. The lead 24 is used to ignite the projectile 22.

[0041] In this embodiment, the projectile 22 is ignited and the explosion of the projectile 22 generates gas to propel the drone 3 to launch. In this way, only one generating chamber 211 required for the explosion of the projectile 22 is required to generate gas for propelling the drone 3 to launch. In this way, the launch of the drone 3 can be achieved without the need for additional equipment, thereby improving the mobility of the power assembly 2. Furthermore, by igniting and exploding to generate gas, only a small amount of projectiles 22 and a smaller generating chamber 211 are required to obtain the required thrust. In this way, the volume and weight of the power assembly 2 are reduced, and the mobility of the power assembly 2 is further improved, which is beneficial to the combat transfer of one's own soldiers, reduces the risk of one's own soldiers being locked by the enemy, and improves the safety of one's own soldiers during combat.

[0042] As a preferred embodiment, based on the above-mentioned method, further, the projectile 22 is made of nitrocellulose.

[0043] When nitrocellulose ignites and explodes, it does not produce smoke, which reduces the risk of exposing the positions of friendly soldiers and is beneficial to the safety of friendly soldiers during combat.

[0044] As a preferred embodiment, on the basis of the above embodiment, a first sealing ring 25 is further provided between the igniter 23 and the bottom of the generating chamber 211 .

[0045] The provision of the first sealing ring 25 prevents the gas generated by the explosion of the projectile 22 from escaping from the gap between the igniter 23 and the housing 21 , ensuring the diffusion of the gas toward the UAV 3 , which is beneficial to the launch of the UAV 3 .

[0046] As a preferred embodiment, on the basis of the above method, further, an air outlet 212 is provided on the top of the shell 21, and the gas generated by igniting the projectile 22 enters the launch tube 1 through the air outlet 212. The number of the air outlet holes 212 is several, and the several air outlet holes 212 are distributed in a cross shape along the center of the top of the shell 21.

[0047] The gas generated when the projectile 22 explodes in the generating chamber 211 has a certain pressure. The provision of the gas outlet 212 further pressurizes the gas, thereby increasing the thrust of the gas on the drone 3, which helps the drone 3 fly farther. The plurality of gas outlets 212 are distributed in a cross shape along the center of the top of the shell 21. Such a provision makes the thrust of the gas on the drone 3 more uniform, the movement of the drone 3 in the launching tube 1 more stable, and is conducive to the launch of the drone 3.

[0048] As a preferred embodiment, on the basis of the above-mentioned manner, further, a heat insulating layer 26 is provided between the generating chamber 211 and the air outlet 212, and the heat insulating layer 26 has heat insulating and breathable functions.

[0049] When the projectile 22 explodes in the generating chamber 211 , high temperature is generated. The heat insulating layer 26 filters the high temperature gas, lowering the temperature of the gas and preventing the high temperature gas from damaging the drone 3 , thereby facilitating protection of the drone 3 .

[0050] As a preferred embodiment, on the basis of the above-mentioned manner, further, a fixing plate 4 is provided at the tail end of the launch tube 1, and the fixing plate 4 is detachably connected to the outer shell 21.

[0051] The above structure makes it easy to remove and replace the power assembly 2 from the launch tube 1, thereby improving the sustainability of the launch of the UAV 3. At the same time, the disassembled power assembly 2 can be recycled and refilled with the projectile 22 for secondary use, thereby increasing the number of times the shell 21 is used and reducing the cost of using the power assembly 2.

[0052] As a preferred embodiment, on the basis of the above manner, further, the housing 21 is connected to the fixing plate 4 by bolts, and the housing 21 and the fixing plate 4 are sealed by using sealant.

[0053] The above structure is simple and the connection is reliable.

[0054] Example 2: See Figures 4 to 6 As shown,

[0055] The difference between this embodiment and the first embodiment is that a clamping member 5 is provided below the fixing plate 4, and the clamping member 5 is clamped with the fixing plate 4 so that the housing 21 and the fixing plate 4 maintain relative positions.

[0056] A clamping groove 41 is provided on the side wall of the fixing plate 4 , a clamping strip 51 is provided on the clamping component 5 , and the clamping strip 51 is adapted to the clamping groove 41 . A second sealing ring 7 is provided between the fixing plate 4 and the clamping component 5 .

[0057] The use of a snap-on connection method improves the efficiency of replacing the power assembly 2 compared to the bolt connection method. For battlefields with changing situations, efficient replacement of the power assembly 2 is conducive to launching more drones 3 and facilitating the control of the battlefield by one's own soldiers. The setting of the second sealing ring 7 ensures the sealing between the outer shell 21 and the launch tube 1.

[0058] As a preferred embodiment, on the basis of the above method, a push block 6 is further slidably provided on the card slot 41, one end of the push block 6 is in contact with a spring 61, and the other end is in contact with the card strip 51. The push block 6 is in contact with the card strip 51 so that the card strip 51 and the card slot 41 maintain a relative position.

[0059] The above structure is easy to operate and has reliable connection. During operation, it is only necessary to press the clamping component 5 toward the fixed plate 4. During the pressing process, the push block 6 compresses the spring 61 and moves backward. As the bottom of the clamping component 5 contacts the fixed plate 4, the spring 61 pushes the push block 6 under the action of the spring 61, and the push block 6 pushes the clamping component 5 to rotate, so that the clamping strip 51 is clamped into the clamping slot 41.

[0060] As a preferred embodiment, on the basis of the above embodiment, the clamping component 5 is further provided with a handle 52, and the handle 52 is used for being held by hand.

[0061] When replacing the power assembly 2, the setting of the handle 52 makes it convenient for soldiers to hold the clamping component 5, which is conducive to improving the replacement efficiency.

[0062] The above embodiments are only used to illustrate the present invention and are not intended to limit the technical solutions described in the present invention. Although this specification has described the present invention in detail with reference to the above embodiments, the present invention is not limited to the above specific implementation methods. Therefore, any modification or equivalent replacement of the present invention; and all technical solutions and improvements thereof that do not depart from the spirit and scope of the present invention are included in the scope of the claims of the present invention.

Claims

1. A power assembly for launching an unmanned aerial vehicle, characterized in that: It includes a launch tube and a power assembly, wherein the launch tube is used to load the UAV, and the power assembly is used to provide power to launch the UAV from the launch tube, and the power assembly is arranged at the tail end of the launch tube; The power assembly includes a shell, a generating chamber is provided in the shell, a projectile is provided in the generating chamber, the projectile generates gas by explosion to launch the drone from the launch tube, an igniter is provided on the shell, one end of the igniter is located in the generating chamber and connected to the projectile, and the other end passes through the bottom of the shell and is connected to a lead, and the lead is used to ignite the projectile.

2. The UAV launch power assembly according to claim 1, characterized in that: A first sealing ring is provided between the igniter and the bottom of the generating chamber.

3. The UAV launch power assembly according to claim 2, characterized in that: An air outlet is provided on the top of the shell, and the gas generated by igniting the projectile enters the launch tube through the air outlet. The number of the air outlet is several.

4. A UAV launch power assembly according to claim 3, characterized in that: A plurality of the air outlet holes are distributed in a cross shape along the center of the top of the shell.

5. The UAV launch power assembly according to claim 4, characterized in that: A heat-insulating layer is provided between the generating chamber and the air outlet, and the heat-insulating layer has heat-insulating and air-permeable functions.

6. The UAV launch power assembly according to claim 5, characterized in that: A fixing plate is provided at the tail end of the launching tube, and the fixing plate is detachably connected to the outer shell.

7. The UAV launch power assembly according to claim 6, characterized in that: The shell is connected to the fixing plate by bolts, and the shell and the fixing plate are sealed by using sealant.

8. The UAV launch power assembly according to claim 6, characterized in that: A clamping component is provided below the fixing plate, and the clamping component is clamped with the fixing plate to keep the housing and the fixing plate in a fixed relative position; A clamping groove is provided on the side wall of the fixing plate, a clamping strip is provided on the clamping component, the clamping strip is adapted to the clamping groove, and a second sealing ring is provided between the fixing plate and the clamping component.

9. The UAV launch power assembly according to claim 8, characterized in that: A push block is slidably provided on the card slot, one end of the push block abuts against a spring, and the other end abuts against the card strip. The push block abuts against the card strip so that the card strip and the card slot maintain relative positions.

10. The UAV launching power assembly according to claim 9, characterized in that: The clamping component is also provided with a handle, and the handle is used for being held by hand.

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