UAV launch tube and UAV launch method

Abstract

The present application provides a drone launch tube and a drone launch method. The drone launch tube provided by the present application includes a launch shell, a high-pressure gas tank, a piston adapter and a conversion assembly. One end of the launch shell is a closed bottom surface, and the other end of the launch shell is the outlet of the drone launch tube; the high-pressure gas tank and the drone are fixed inside the launch shell; one end of the conversion assembly is arranged inside the high-pressure gas tank through the tank opening of the high-pressure gas tank, and the tank opening faces the drone, and the other end of the conversion assembly extends through the tank opening of the high-pressure gas tank and is connected to the piston adapter. The part of the conversion assembly extending out of the high-pressure gas tank is fixed on the inner wall of the launch shell through a transfer seat around a circle; the piston adapter contacts the end of the drone away from the outlet of the launch shell; the conversion assembly releases the gas in the high-pressure gas tank through mechanical transmission, and pushes the piston adapter to move horizontally to launch the drone. The drone launch tube provided by the present application is used to launch drones simply and quickly.

Description

Technical Field

[0001] The present application relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to a UAV launch tube and a UAV launch method. Background Art

[0002] In the modern military field, the application of drones is becoming more and more widespread, becoming an indispensable part of the military equipment system of various countries. With the rapid development of science and technology, drones not only play an important role in traditional military tasks such as reconnaissance, surveillance, and target positioning, but also gradually expand to attack, communication relay, electronic warfare and other fields. The widespread use of drones has greatly improved the efficiency and safety of military operations and has become the mainstream on the modern battlefield.

[0003] As a key equipment for the rapid deployment and concealed launch of drones, the importance of drone launch tubes is self-evident. Although the traditional drone take-off methods, such as runway take-off, are mature in technology, they have many limitations in specific military scenarios. For example, in complex terrains such as mountains, jungles, and cities, as well as in special operations, reconnaissance missions, and local conflicts, the implementation of runway take-off is greatly increased in difficulty and even becomes infeasible due to factors such as terrain and time. Therefore, a launch device is needed that can enable drones to quickly enter a working state in a complex environment in order to achieve rapid reconnaissance, surveillance, or attack on the target area.

[0004] Then, the existing drone launch tubes are generally large in size and heavy in weight, which to a certain extent limits their portability and flexibility. In military scenarios that require rapid deployment and covert launch, the excessive size and weight not only increase the difficulty of transportation and carrying, but also in some rugged terrains, the stability and launch effect of the drone launch tube may be affected, which in turn affects the drone's take-off performance and combat effectiveness, and cannot meet the needs of actual use. Summary of the invention

[0005] In view of this, the present application provides a drone launch tube and a drone launch method for simply and quickly launching a drone.

[0006] Specifically, the present application is implemented through the following technical solutions:

[0007] The first aspect of the present application provides a drone launch tube, the drone launch tube comprising a launch shell, a high-pressure gas tank, a piston adapter and a conversion assembly, wherein:

[0008] One end of the launch shell is a closed bottom surface, and the other end of the launch shell is the outlet of the UAV launch tube;

[0009] The high-pressure gas tank and the UAV are fixed inside the launch shell, the high-pressure gas tank is located on the bottom surface of the launch shell, and the UAV is located at the exit of the launch shell;

[0010] One end of the conversion assembly and the tank opening through the high-pressure gas tank are arranged inside the high-pressure gas tank, the tank opening faces the UAV, the other end of the conversion assembly extends through the tank opening and is connected to the piston adapter, and the portion of the conversion assembly extending from the high-pressure gas tank is fixed to the inner wall of the launch shell through a transfer seat around a circle;

[0011] The piston adapter is located between the conversion assembly and the drone, and the piston adapter contacts an end of the drone away from the outlet of the launch housing;

[0012] A starting air chamber is provided in the conversion assembly, which is respectively connected to the high-pressure gas tank and the outside atmosphere. The release valve of the high-pressure gas tank is opened based on the pressure difference between the gas in the high-pressure gas tank and the gas in the starting air chamber, thereby releasing the gas in the high-pressure gas tank through mechanical transmission, pushing the piston adapter to move laterally to launch the UAV.

[0013] A second aspect of the present application provides a method for launching a drone, the method comprising:

[0014] The conduction state of the control valve is adjusted to be on, and the gas inside the conversion assembly is discharged through the exhaust pipe; wherein the pressure inside the conversion assembly is reduced, and a pressure difference is generated with the high-pressure gas tank;

[0015] Opening a first exhaust hole on the conversion assembly based on the air pressure difference, controlling the movement of a valve piston in the conversion assembly to expose a second exhaust hole, and releasing the gas in the high-pressure gas tank;

[0016] The released gas in the high-pressure gas tank pushes the piston adapter to move, and the piston adapter pushes the drone to be ejected.

[0017] The drone launch tube and the drone launch method provided by the present application release the gas in the high-pressure gas tank by the pressure difference between the inner cavity of the conversion component and the high-pressure gas tank, convert the gas pressure into the power of the drone through the piston adapter, and launch the drone from the launch shell. In this way, since the drone launch tube adopts a mechanical structure and does not involve energy such as electricity and fuel, the volume and weight of the drone launch tube can be greatly reduced, which is convenient for storage and transportation. Further, the entire launch process does not require auxiliary equipment such as power supply, and can be completed only by human triggering, making the entire launch process of the drone efficient and smooth. At the same time, the drone is launched by the gas in the drone launcher, which greatly shortens the preparation time and improves the response speed of the drone launch. Further, since the drone launch tube is small in size, light in weight and compact in structure, it can be used under complex terrain conditions. In this way, the drone launch tube realizes efficient launch of the drone under complex terrain. In the entire control process, it only needs to manually trigger the release of the gas in the air cavity into the atmosphere, and the release channel of the gas in the high-pressure gas tank can be opened due to the pressure difference, so that the high-pressure gas pressure is converted into thrust through mechanical tradition to drive the drone launch, and the whole process does not require the help of a gas power source. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 A schematic diagram of a drone launch tube provided for an exemplary embodiment of the present application;

[0019] Figure 2 A schematic diagram of a drone provided for an exemplary embodiment of the present application;

[0020] Figure 3 A schematic diagram of a conversion assembly provided for an exemplary embodiment of the present application;

[0021] Figure 4 A schematic diagram of a conversion assembly provided for another exemplary embodiment of the present application;

[0022] Figure 5 A schematic diagram of a drone launch tube provided for another exemplary embodiment of the present application;

[0023] Figure 6 A flowchart of a drone launching method provided for an exemplary embodiment of the present application.

[0024] Description of reference numerals:

[0025] 1: Launch shell;

[0026] 2: High-pressure gas tank;

[0027] 3: Piston adapter;

[0028] 4: Conversion component;

[0029] 5: Drone;

[0030] 6: Adapter;

[0031] 7: Support seat;

[0032] 8: Support rod;

[0033] 401: fixed base;

[0034] 402: valve piston;

[0035] 403: Start the air cavity;

[0036] 404: Exhaust pipe;

[0037] 405: control valve;

[0038] 406: Spring;

[0039] 407: first exhaust hole;

[0040] 408: second exhaust hole;

[0041] 409: air inlet;

[0042] 410: barometer;

[0043] 411: O-ring;

[0044] 412: rectangular sealing ring;

[0045] 413: Fixed end cap;

[0046] 414: guide sleeve;

[0047] 51: nose;

[0048] 52: Wing;

[0049] 53: fuselage. DETAILED DESCRIPTION

[0050] Here, exemplary embodiments are described in detail, and examples thereof are shown in the accompanying drawings. When the following description refers to the drawings, unless otherwise indicated, the same numbers in different drawings represent the same or similar elements. The implementations described in the following exemplary embodiments do not represent all implementations consistent with the present application.

[0051] The terms used in this application are only for the purpose of describing specific embodiments and are not intended to limit this application. The singular forms of "a", "said" and "the" used in this application are also intended to include plural forms, unless the context clearly indicates other meanings. It should also be understood that the term "and / or" used in this article refers to and includes any or all possible combinations of one or more associated listed items.

[0052] It should be understood that although the terms first, second, third, etc. may be used in the present application to describe various information, these information should not be limited to these terms. These terms are only used to distinguish the same type of information from each other. For example, without departing from the scope of the present application, the first information may also be referred to as the second information, and similarly, the second information may also be referred to as the first information. Depending on the context, the word "if" as used herein may be interpreted as "at the time of" or "when" or "in response to determining".

[0053] The present application provides a drone launch tube and a drone launch method for launching a drone simply and quickly.

[0054] The drone launch tube and drone launch method provided by the present application release the gas in the high-pressure gas tank through a conversion component, convert the gas pressure into the power of the drone through a piston adapter, and launch the drone from the launch shell. In this way, since the drone launch tube adopts a mechanical structure and does not involve energy such as electricity and fuel, the volume and weight of the drone launch tube can be greatly reduced, which is convenient for storage and transportation. Furthermore, the entire launch process does not require auxiliary equipment such as a power supply, and can be completed only by human triggering, making the entire launch process of the drone efficient and smooth. At the same time, the drone is launched by the gas in the drone launcher, which greatly shortens the preparation time and improves the response speed of the drone launch. Furthermore, since the drone launch tube is small in size, light in weight and compact in structure, it can be used under complex terrain conditions. In this way, the drone launch tube is used to achieve efficient launch of drones under complex terrain.

[0055] Specific embodiments are given below to introduce the technical solution of the present application in detail.

[0056] Figure 1 This is a schematic diagram of a drone launch tube provided by an exemplary embodiment of the present application. Figure 1 The drone launch tube provided in this embodiment includes a launch shell 1, a high-pressure gas tank 2, a piston adapter 3 and a conversion assembly 4, wherein:

[0057] One end of the launch shell 1 is a closed bottom surface, and the other end of the launch shell 1 is the outlet of the UAV launch tube;

[0058] The high-pressure gas tank 2 and the drone 5 are fixed inside the launch shell 1, the high-pressure gas tank 2 is located on the bottom surface of the launch shell 1, and the drone 5 is located at the exit of the launch shell 1;

[0059] One end of the conversion assembly 4 is disposed inside the high-pressure gas tank 2 through the tank opening of the high-pressure gas tank 2, the tank opening faces the drone 5, the other end of the conversion assembly 4 extends through the tank opening and is connected to the piston adapter 3, and the portion of the conversion assembly 4 extending from the high-pressure gas tank 2 is fixed to the inner wall of the launch housing 1 through a transfer seat 6 around a circle;

[0060] The piston adapter 3 is located between the conversion assembly 4 and the drone 5, and the piston adapter 3 is in contact with an end of the drone 5 away from the outlet of the launch housing 1;

[0061] The conversion assembly 4 releases the gas in the high-pressure gas tank 2 through mechanical transmission, pushing the piston adapter 3 to move laterally to launch the drone 5.

[0062] For details, please refer to Figure 1 The launch shell 1 is a tubular structure with one end open and the other end closed. The launch shell 1 is used to load and launch the UAV.

[0063] It should be noted that the specific material of the launch shell 1 is determined according to actual needs, and is not limited in this embodiment. In specific implementation, the launch shell 1 can be made of a material with sufficient strength and rigidity to ensure that the launch shell 1 can withstand various forces generated during the launch process. For example, in one embodiment, the launch shell 1 can be made of a fiberglass material.

[0064] Furthermore, the launch housing 1 is used to provide a loading and launching platform for the UAV. In specific implementation, when the wings of the UAV 5 are folded, they can be loaded into the launch housing 1. During the launch process, the launch housing 1 provides an initial guiding function for the UAV 5, ensuring that the UAV 5 can smoothly accelerate and take off along the predetermined track.

[0065] Furthermore, the drone 5 is an unmanned aircraft that can be flown and controlled by remote control or a preset program. In specific implementation, a drone 5 with foldable wings can be selected as the drone 5 of the drone launch tube. It should be noted that the drone 5 with foldable wings can be reduced in size by folding the wings when it does not need to fly, so as to facilitate carrying and storage.

[0066] Figure 2 A schematic diagram of a drone provided for an exemplary embodiment of the present application. Figure 2 The drone 5 may include a nose 51 , wings 52 and a fuselage 53 .

[0067] Specifically, the nose 51 is the frontmost part of the drone 5, and a variety of key devices can be integrated into the nose 51. It should be noted that the nose 51 needs to take into account both aerodynamic performance and the compact layout of internal devices.

[0068] In specific implementation, a navigation and control system, a sensor kit and a communication module may be installed in the nose 51. For example, in one embodiment, the nose 51 is integrated with a GPS navigation module, an inertial navigation system, etc., for realizing accurate positioning and autonomous flight control of the drone 5, and is also integrated with a camera, an infrared sensor, a radar, etc., for environmental perception, target tracking and obstacle avoidance, and is also integrated with a communication kit for data transmission and command reception.

[0069] Furthermore, the wing 52 is the main component for providing lift for the drone 5. It should be noted that the wing 52 is folded and unfolded through a precise mechanical structure. In specific implementation, the folding and unfolding functions of the wing 52 can be ensured by a slide rail, a hinge, a locking mechanism, etc.

[0070] Furthermore, the specific material of the wing 52 can be determined according to actual needs, and is not limited in this embodiment. For example, in one embodiment, the wing 52 can be made of a lightweight and high-strength material such as a carbon fiber composite material or a glass fiber composite material.

[0071] Furthermore, the fuselage 53 is the main part of the UAV 5 , connecting the nose 51 , the wings 52 and the tail of the UAV 5 , and carrying various equipment and loads of the UAV 5 .

[0072] In specific implementation, the fuselage 53 may include a power system for providing the UAV 5 with the power required for flight, as well as an equipment compartment for installing various sensors, communication equipment, control panels and other equipment.

[0073] It should be noted that grooves or folding plates may be designed on both sides of the fuselage 53 so as to reduce the volume when the wings 52 are in the folded state.

[0074] The drone provided in this embodiment has a foldable wing design, which achieves a more compact and portable structure while maintaining necessary functions and performance. In this way, the drone can be more conveniently deployed quickly and carried by a single soldier, and is suitable for a variety of complex scenarios.

[0075] It can be understood that when the UAV 5 needs to be launched, the exit of the launch shell 1 is directed toward the direction in which the launch is required, and the bottom surface of the launch shell 1 is directed toward the direction opposite to the launch direction.

[0076] Furthermore, the high-pressure gas tank 2 is a container capable of storing high-pressure air. It should be noted that the high-pressure gas tank 2 can withstand a relatively high internal pressure to ensure that a stable and sufficient power source can be provided during the launch process.

[0077] It should be noted that the specific pressure of the gas in the high-pressure gas tank 2 is determined according to actual needs, and is not limited in this embodiment. In specific implementation, the gas pressure in the high-pressure gas tank 2 can be set to a pressure value that can provide sufficient power for the drone.

[0078] Furthermore, the high-pressure gas tank 2 usually needs to withstand high internal pressure and external environmental factors. It should be noted that the specific material of the high-pressure gas tank 2 is determined according to actual needs, and is not limited in this embodiment. In specific implementation, a material with high strength, corrosion resistance, and good pressure resistance can be selected as the material of the high-pressure gas tank 2. For example, in one embodiment, high-strength steel, aluminum alloy, and composite materials can be selected to make the high-pressure gas tank.

[0079] It can be understood that the UAV 5 is located on the exit side of the launch shell 1, with the nose of the UAV 5 facing the exit and the tail of the UAV 5 facing the bottom; the high-pressure gas tank 2 is located on the bottom side of the launch shell 1, with the mouth of the high-pressure gas tank facing the UAV 5, and the bottom of the high-pressure gas tank 2 facing the bottom of the launch shell 1.

[0080] Please continue to refer to Figure 1 The launch shell 1 is placed on the outermost side of the UAV launch tube, the left end of the launch shell 1 is a closed bottom surface, and the right end of the launch shell 1 is an opening. Inside the launch shell 1, from left to right are a high-pressure gas tank 2, a conversion assembly 4, a piston adapter 3 and a UAV 5.

[0081] It should be noted that the high-pressure gas tank 2 can be in contact with and fixed to the launch shell 1 to ensure the firmness of the high-pressure gas tank 2; the high-pressure gas tank 2 may not be in contact with the launch shell 1 to prevent the high-pressure gas tank 2 and the launch shell 1 from interacting with each other due to environmental factors and causing wear.

[0082] For further information, please refer to Figure 1 The conversion component 4 is located at the tank mouth of the high-pressure gas tank 2, and the storage and release of the gas in the high-pressure gas tank are controlled by the conversion component 4.

[0083] Furthermore, one end of the conversion assembly 4 is connected to the tank opening of the high-pressure gas tank 2, and the sealing of the tank opening of the high-pressure gas tank 2 is completed through the conversion assembly 4. The other end of the conversion assembly 4 is connected to the docking connector. It should be noted that the docking connector is used to connect the conversion assembly 4 and the space in front of the piston adapter 3.

[0084] It should be noted that the docking connector, the adapter and the conversion assembly 4 can be connected by threads, so that the fixation can be stable and secure.

[0085] In a specific implementation, when the conversion assembly 4 is in the conducting state, the gas in the high-pressure gas tank 2 can sequentially pass through the conversion assembly 4 and the connecting converter to reach the piston adapter 3 .

[0086] Furthermore, the conversion assembly 4 is fixed on the inner wall of the launch shell 1 by the adapter seat 6. In specific implementation, the adapter seat 6 is a fixing device for the conversion assembly 4, and the adapter seat 6 is a disc-shaped structure with an opening in the middle. The conversion assembly 4 is fixed in the middle of the adapter seat 6 by the adapter seat 6 and the inner wall of the launch shell 1, thereby completing the fixing of the adapter seat.

[0087] In specific implementation, the adapter 6 and the launch housing 1 can be connected by threads to ensure that the adapter is fixed reliably.

[0088] It can be understood that the mouth of the high-pressure gas tank 2 is connected to one end of the conversion assembly 4. When the conversion assembly 4 is fixed to the launch shell 1, the high-pressure gas tank 2 is also fixed.

[0089] A specific embodiment is given below to introduce the structure of the conversion component 4 in detail:

[0090] Figure 3 This is a schematic diagram of a conversion assembly provided by an exemplary embodiment of the present application. Figure 3 The conversion assembly 4 includes a fixed base 401, a spring 406, a valve piston 402, a starting air chamber 403, an exhaust pipe 404 and a control valve 405, wherein:

[0091] The fixed base 401 is arranged inside the high-pressure gas tank 2, one end of the spring 406 is connected to the fixed base 401, and the other end is connected to the valve piston 402, a starting air cavity 403 is formed between the valve piston 402 and the shell of the conversion assembly 4, and the valve piston 402 repeatedly moves in the starting air cavity 403 along a first direction according to the difference between the air pressure in the spring 406 and the air pressure in the high-pressure gas tank 2;

[0092] The control valve 405 is located on the side outer wall of the starting air cavity 403, the first port of the control valve 405 is connected to the starting air cavity 403, and the second port of the control valve 405 is connected to the exhaust pipe 404; the control valve 405 is unidirectionally conductive to the exhaust pipe 404; preferably, the control valve is connected to a control switch, which can be controlled around the launch tube or remotely to control the conduction of the control valve, so that the launch can take into account both the near end and the far end at the same time, meeting the launch control in complex environments.

[0093] The exhaust pipe 404 is connected to the spring 406 through a pipeline to discharge the gas in the spring 406 to form a pressure difference between the conversion component 4 and the high-pressure gas tank 2.

[0094] Specifically, the conversion assembly 4 can quickly release the gas in the high-pressure gas tank 2. In specific implementation, when the valve piston 402 controls the one-way valve at the tank opening of the high-pressure gas tank 2 to open, the high-pressure gas tank 2 and the conversion assembly 4 are connected, and the gas in the high-pressure gas tank 2 is quickly released through the conversion assembly 4.

[0095] For further information, please refer to Figure 3 The valve piston 402 is used to control the opening and closing of the conversion assembly 4. In the specific implementation, when the valve piston 402 moves toward the high-pressure gas tank 2 ( Figure 3 , the gas in the high-pressure gas tank 2 can be released to the piston adapter 3. In other words, the gas in the high-pressure gas tank 2 can be released through the conversion assembly 4.

[0096] Furthermore, when the valve piston 402 is in the initial position due to the pressure of the spring 406, the second exhaust hole 408 on the conversion assembly 4 is blocked by the valve piston 402, and the gas in the high-pressure gas tank 2 cannot pass through the conversion assembly 4. In other words, the valve of the high-pressure gas tank 2 is closed, and the gas in the high-pressure gas tank 2 cannot circulate.

[0097] Please refer to Figure 3 , the valve piston 402 can only move in one direction from the bottom side of the high-pressure gas tank 2 blocking the second exhaust hole 408. In other words, the valve piston 402 can move from the left side back to the initial position to block the second exhaust hole 408, or move from the initial position to the left side to open the second exhaust hole 408. In specific implementation, the air pressure value in the conversion component 4 can be set to be higher than the external atmospheric pressure, so that when the valve piston does not need to be opened, the valve piston blocks the conversion component 4 based on the air pressure difference.

[0098] For further information, please refer to Figure 3 A guide sleeve 414 is also provided in the conversion assembly 4. It should be noted that the guide sleeve 414 is a sleeve-shaped structure for guiding and positioning, and the guide sleeve 414 can reduce friction and wear during the movement of the valve piston 402, extend the service life of the valve piston 402, and also help improve the launch efficiency.

[0099] In specific implementation, the valve piston and the guide sleeve 414 are clearance-matched to ensure the opening and closing of the conversion assembly 4.

[0100] It should be noted that the specific direction of the first direction is determined according to actual needs, and is not limited in this embodiment. In specific implementation, the first direction can be set to be parallel to the direction of the drone launch tube.

[0101] Furthermore, the guide sleeve 414 can ensure that the valve piston 402 moves smoothly along the first direction under the push of the high-pressure gas, and prevent the valve piston 402 from deviating from the predetermined route, thereby ensuring the stability and reliability of the launch process.

[0102] Furthermore, the guide sleeve 414 can also play a certain sealing role, preventing high-pressure gas from leaking out from the gap during the UAV launch process, thereby ensuring the stability of the air pressure in the UAV launch tube.

[0103] Furthermore, the starting air cavity 403 is an air cavity formed between the valve piston 402 and the fixed base 401. It should be noted that when the drone launch tube is not started, the air pressure value of the starting air cavity 403 on the left side of the valve piston 402 is the same as that on the right side of the valve piston 402. At this time, there is only pressure applied by the spring 406 on both sides of the valve piston 402.

[0104] Furthermore, the start-up air cavity 403 is used to control the opening and closing of the high-pressure gas tank 2 , and the high-pressure gas tank 2 can be controlled to open quickly by starting the air cavity 403 .

[0105] Furthermore, the control function of the starting air cavity 403 can be realized based on the air pressure difference. When the high-pressure gas tank 2 needs to be closed, since the gas in the high-pressure gas tank 2 is released, the pressure in the starting air cavity 403 and the pressure in the high-pressure gas tank 2 are both the current atmospheric pressure, and the pressure difference disappears. At this time, the valve piston 402 is closed under the thrust of the spring 406, blocking the second exhaust hole 408, so that the high-pressure gas tank 2 remains closed.

[0106] For further information, please refer to Figure 3 The spring 406 provides a repulsive force for the valve piston 402 by fixing the base 401, thereby preventing the valve piston 402 from accidentally opening when the valve piston 402 vibrates.

[0107] In a specific implementation, the spring 406 is pressed between the valve piston 402 and the fixed base 401 to fix the valve piston 402 at an initial position blocking the second exhaust hole 408 .

[0108] The drone launch tube provided in this embodiment pushes the valve piston to reset after the gas in the high-pressure gas tank is released, ensuring that the valve can be closed after the launch to prevent further gas leakage. Furthermore, the valve piston is compressed by the spring to prevent the gas in the high-pressure gas tank from leaking in advance, thereby maintaining the sealing of the drone launch tube and providing a guarantee for the next launch.

[0109] For further information, please refer to Figure 3 The control valve 405 is used to control the pressure change of the start-up air cavity 403. In specific implementation, when the control valve 405 is not started, the pressure in the start-up air cavity 403 remains unchanged.

[0110] Furthermore, when the drone 5 needs to be launched, the control valve 405 needs to be turned on. At this time, the gas in the starting air chamber 403 flows out through the control valve 405 and the exhaust pipe 404 in sequence, so that the pressure in the starting air chamber 403 is reduced. At this time, since the pressure in the high-pressure gas tank 2 is greater than the pressure in the starting air chamber 403, the air pressure on the right side of the valve piston 402 is greater than the air pressure on the left side of the valve piston 402, pushing the valve piston 402 to move in the direction close to the spring 406, and the gas in the high-pressure gas tank 2 is released through the conversion assembly 4.

[0111] In specific implementation, when the control valve 405 controls the starting air cavity 403 to exhaust, the control valve 405 opens, and the starting air cavity 403 is connected to the exhaust pipe 404. Since the exhaust pipe 404 is connected to the outside air, the pressure in the starting air cavity 403 is greater than the pressure in the exhaust pipe 404. At this time, the air in the starting air cavity 403 flows to the outside along the exhaust pipe 404.

[0112] It should be noted that the control valve 405 is unidirectionally conducted toward the exhaust pipe 404. In specific implementation, the control valve 405 can be set to be conducted only toward the exhaust pipe 404, and limited toward the conversion assembly 4, so that the gas cannot flow in one direction.

[0113] Furthermore, the exhaust pipe 404 can be fixed on the starting air cavity 403 through the fixed end cover 413 to complete the exhaust of the starting air cavity 403.

[0114] The drone launch tube provided in this embodiment controls the pressure of the start-up air cavity through a control valve, thereby completing the opening and closing of the high-pressure gas tank, and can quickly and efficiently complete the launch of the drone, which is more efficient than the launch of an electrically assisted drone. Furthermore, the high-pressure gas tank is started by a conversion component, and the entire process of drone launch is mechanical transmission, directly using the air pressure difference between the cavities to drive the movement of the mechanical structure, converting the air pressure difference into kinetic energy, without using any additional energy, which can reduce the supporting equipment required for drone launch, reduce the weight of the carry-on, and achieve the convenience and concealment of drone launch.

[0115] A specific embodiment is given below to introduce in detail the release process of the gas in the high-pressure gas cylinder:

[0116] The conversion assembly 4 further includes a first exhaust hole 407 and a second exhaust hole 408, wherein:

[0117] The first exhaust hole 407 is provided on a side wall of the conversion assembly 4 inside the high-pressure gas tank 2, one end of the first exhaust hole 407 is connected to the high-pressure gas tank 2, and the other end of the first exhaust hole 407 is connected to the starting gas chamber 403. The first exhaust hole 407 is subjected to the pressure of the gas in the high-pressure gas tank 2 and is unidirectionally connected to the starting gas chamber 403, thereby squeezing the valve piston 402 to move in a direction close to the spring 406.

[0118] The second exhaust hole 408 is provided on an inner wall where the valve piston 402 contacts the starting air chamber 403. The valve piston 402 moves to a preset position in a direction close to the spring 406, and the second exhaust hole 408 is exposed. One end of the second exhaust hole 408 is connected to the starting air chamber 403, and the other end releases the gas in the high-pressure gas tank 2 to push the piston adapter 3.

[0119] Figure 4 A schematic diagram of a conversion assembly provided for another exemplary embodiment of the present application. Figure 4 When it is necessary to launch the drone, the gas in the space where the spring 406 is located is discharged through the exhaust pipe 404. At this time, the high-pressure gas tank 2 and the starting gas chamber 403 are connected through the first exhaust hole 407, resulting in the air pressure in the starting gas chamber 403 being higher than the air pressure value of the space where the spring 406 is located. The first exhaust hole 407 releases the gas in the high-pressure gas tank 2, pushing the valve piston 402 to move to the left (i.e., in the direction close to the spring 406).

[0120] Furthermore, after the valve piston 402 moves to the left to a preset position, the second exhaust hole 408 blocked by the valve piston 402 is exposed. At this time, the second exhaust hole 408 is connected to the starting air chamber 403, and the gas in the high-pressure gas tank 2 is released quickly and in large quantities through the second exhaust hole 408, pushing the piston adapter 3 to complete the launch.

[0121] It should be noted that the specific position of the preset position is set according to actual needs, and is not limited in this embodiment. For example, in one embodiment, the preset position can be set at a position where the second exhaust hole 408 is fully exposed.

[0122] For further information, please refer to Figure 1 , the piston adapter 3 is located between the docking connector and the drone 5. It should be noted that the docking connector is used to tightly connect the conversion assembly 4 and other components, and the air tightness and structural integrity of the entire drone launch tube are ensured through the docking connector. In specific implementation, for example, in one embodiment, the docking connector can be tightly connected to the conversion assembly 4 through a threaded interface.

[0123] Furthermore, the piston adapter 3 is tightly connected to the launch shell 1. When the high-pressure gas tank 2 releases the internal gas, a large amount of gas released by the high-pressure gas tank 2 will be filled between the docking connector and the piston adapter 3. At this time, due to the close vector between the piston adapter 3 and the launch shell 1, the gas will push the piston adapter 3 to move quickly toward the outlet of the launch shell 1. In this way, the piston adapter 3 will drive the drone 5 to complete the launch.

[0124] In a specific implementation, the piston adapter 3 is clearance-matched with the launch shell 1 , so that the piston adapter 3 can quickly slide in the launch shell 1 , and the launch of the UAV 5 is completed under the thrust of the gas released by the high-pressure gas tank 2 .

[0125] It should be noted that the piston adapter 3 and the drone 5 only maintain contact and are not connected to each other. In this way, when the piston adapter 3 pushes the drone 5 to launch out of the launch shell 1, the piston adapter 3 will naturally fall due to insufficient power, and the drone 5 will complete the launch.

[0126] The drone launch tube provided in this embodiment uses a conversion component to quickly open the deflation of the high-pressure gas tank, which can quickly form a strong thrust between the piston adapter and the docking connector, so that the drone can obtain the speed required for take-off in a short time, thereby improving the launch efficiency and response speed. Furthermore, the conversion component is simple to operate, and the operator can complete the release of the gas in the high-pressure gas tank by simply pressing or toggling, without complex preparation steps or professional skills, which reduces the difficulty of operation. Furthermore, since no external power supply or other auxiliary equipment is required, the entire launch system is lighter and convenient for a single soldier to carry and perform tasks. In addition, the design of the launch tube can also adapt to different terrains and combat environments, improving the flexibility of use. Furthermore, compared with the launch method using fuel or other energy sources, high-pressure gas as a power source is more environmentally friendly and does not produce harmful emissions during use. At the same time, since the gas can be recycled, energy consumption is also reduced. In this way, through the drone launch tube, the launch of the drone can be completed efficiently and reliably under complex terrain. On the one hand, in the non-launched state, the high-pressure gas provided by the present invention is blocked in the high-pressure gas tank through the exhaust hole and the conversion component. Once the internal gas release of the conversion component is triggered, the pressure of the high-pressure gas is used to directly open the exhaust hole of the conversion component, thereby guiding the high-pressure gas to be ejected. At the same time, the fixing of the conversion component and the setting of the exhaust hole enable the high-pressure gas to be concentrated in a small range, which greatly improves the thrust and improves the success rate of the UAV launch.

[0127] Optionally, the conversion assembly further includes an air inlet 409, wherein:

[0128] One end of the air inlet 409 is connected to the tank opening of the high-pressure gas tank, and the other end of the air inlet 409 is connected to a high-pressure air pump;

[0129] The high-pressure air pump fills the gas in the high-pressure gas tank into the high-pressure gas tank through the air inlet 409 .

[0130] Specifically, after the drone launch tube is used, the high-pressure gas tank 2 needs to be inflated. For specific implementation, please continue to refer to Figure 3 , connect the high-pressure air pump to the air inlet 409, and the high-pressure gas can be directly filled into the high-pressure gas tank 2.

[0131] It should be noted that the specific model of the high-pressure air pump is determined according to actual needs and is not limited to this in this embodiment.

[0132] The drone launch tube provided in this embodiment inflates the high-pressure gas tank through the air inlet 409, which can ensure that there is enough compressed air in the high-pressure gas tank for use during launch, thereby improving the adaptability and flexibility of the system.

[0133] Optionally, the drone launch tube further includes a barometer 410, wherein:

[0134] The barometer 410 is fixed to the tank opening of the high-pressure gas tank, and the barometer 410 is used to display the air pressure value in the high-pressure gas tank.

[0135] For details, please continue to refer to Figure 3 The barometer 410 is an instrument for observing and monitoring the internal air pressure of the high-pressure gas tank 2. In specific implementation, the barometer 410 is used to understand the air pressure in the gas tank in real time to ensure that the air pressure in the gas tank reaches a predetermined safe and effective range before launching the drone. Through the reading of the barometer 410, the operator can determine whether it is necessary to continue to inflate the gas tank or make other necessary adjustments to ensure the smooth progress of the launch process and the successful take-off of the drone.

[0136] It should be noted that the specific model of the barometer 410 is determined according to actual needs and is not limited in this embodiment.

[0137] Optionally, the drone launch tube further includes a rectangular sealing ring 412 and an O-ring 411, wherein:

[0138] The rectangular sealing ring 412 is fixed inside the conversion assembly;

[0139] The O-ring 411 is fixed inside the air inlet 409 .

[0140] For details, please continue to refer to Figure 3 The rectangular sealing ring 412 is fixed inside the conversion assembly 4. The rectangular sealing ring 412 fills the gap through its elastic deformation to form a seal to prevent the high-pressure gas from leaking out of the gap of the conversion assembly 4.

[0141] For further information, please refer to Figure 3 The O-ring 411 is fixed inside the air inlet 409 . The O-ring 411 generates elastic force through pre-compression to fill and seal the tiny gap inside the air inlet 409 .

[0142] It should be noted that the specific material of the rectangular sealing ring 412 and the O-shaped sealing ring 411 is determined according to actual needs and is not limited in this embodiment. In specific implementation, the rectangular sealing ring 412 and the O-shaped sealing ring 411 can be made of rubber or other elastic materials.

[0143] The drone launch tube provided in this embodiment ensures that high-pressure gas during the launch process will not leak out from the various connections of the drone launch tube through rectangular sealing rings and O-rings, thereby ensuring the smooth launch and successful take-off of the drone.

[0144] Optionally, the drone launch tube further includes a fixing assembly, wherein:

[0145] The fixing assembly includes a support rod 8 and a support seat 7; one end of the support rod 8 is connected to the side surface of the launch housing, and the other end of the support rod 8 is in contact with the bottom surface;

[0146] One end of the support base 7 is connected to the bottom surface of the launching shell; the support base 7 provides a buffer when launching the UAV.

[0147] Figure 5 This is a schematic diagram of a drone launch tube provided by another exemplary embodiment of the present application. Figure 5 , support rod 8 is used to provide stable support and fixation. In the drone launch tube, support rod 8 is responsible for fixing the drone launch tube on the ground or adjusting it to a specific launch angle.

[0148] In specific implementation, the position of the support rod 8 can be adjusted to change the tilt angle of the drone launch tube. In this way, the drone launch tube can be adjusted to the optimal launch angle according to different launch requirements and terrain conditions to ensure that the take-off trajectory and flight direction of the drone meet expectations.

[0149] It should be noted that the specific number and specific material of the support rod 8 are set according to actual needs, and are not limited in this embodiment. In specific implementation, the support rod 8 can be made of a lightweight but high-strength material. For example, in one embodiment, the support rod 8 can be made of aluminum alloy or carbon fiber, and the number of the support rod 8 can be one.

[0150] Furthermore, the support seat 7 is a structural component used to absorb and disperse the recoil of the drone launch tube and maintain the stability of the drone launch tube.

[0151] In specific implementation, the support seat 7 absorbs and transmits the recoil force generated during the launching process, thereby ensuring that the launching tube remains stable and does not shake when launching the UAV.

[0152] It should be noted that the specific material of the support base 7 is set according to actual needs, and is not limited in this embodiment. In specific implementation, the support base 7 can be made of a strong and durable material, such as a metal alloy or an engineering plastic with high strength characteristics.

[0153] Furthermore, the structural design of the support seat 7 also focuses on stability and weight distribution to ensure a stable support effect while absorbing recoil.

[0154] The drone launch tube provided in this embodiment ensures the stability and reliability of the drone launch process through the support seat and the support rod. Furthermore, the support seat is mainly responsible for absorbing the recoil and maintaining the stability of the launch tube, while the support rod provides the necessary support and fixation and adjustment of the launch angle. The two complement each other and together provide a strong guarantee for the successful launch of the drone.

[0155] Optionally, the weight of the drone launch tube is less than a first preset threshold, and the length of the drone launch tube is less than a second preset threshold.

[0156] Specifically, the specific numbers of the first preset threshold and the second preset threshold are determined according to actual needs, and are not limited in this embodiment. In specific implementation, the first preset threshold and the second preset threshold can be determined according to the average handheld weight and height of the personnel. For example, in one embodiment, the first preset threshold can be set to 20 kilograms, and the second preset threshold can be set to 2 meters.

[0157] Furthermore, the weight of the drone launch tube can be reduced by optimizing the material of the drone launch tube.

[0158] The drone launch tube provided in this embodiment can achieve single-person carrying of the drone launch tube by setting the weight of the drone launch tube to be less than a first preset threshold value and the length to be less than a second preset threshold value. In this way, single-soldier carrying can be completed in complex terrain, thereby improving the reliability and convenience of the drone launch tube.

[0159] Corresponding to the aforementioned embodiment of a drone launch tube, the present application also provides an embodiment of a drone launch method.

[0160] Figure 6 This is a flowchart of a drone launch method provided by an exemplary embodiment of the present application. Figure 6 , the method comprising:

[0161] S601, adjusting the conduction state of the control valve to conduction, and exhausting the gas inside the conversion component through the exhaust pipe; wherein the pressure inside the conversion component is reduced, and a pressure difference is generated with the high-pressure gas tank.

[0162] In specific implementation, when all components have been assembled as required and the high-pressure gas tank has been filled with a sufficient amount of high-pressure gas, the operator adjusts the control valve to adjust its conduction state to conduction.

[0163] Furthermore, the air in the conversion assembly is exhausted through the exhaust pipe. It should be noted that when the air in the conversion assembly is exhausted, the pressure in the high-pressure gas tank will be greater than the pressure in the conversion assembly.

[0164] A specific embodiment is given below to introduce the implementation process of this step in detail:

[0165] (1) Trigger the start switch installed on the UAV launch tube to open the control valve.

[0166] In specific implementation, the operator presses or pulls the start switch installed on the UAV launch tube to send a mechanical signal to the control valve to open the control valve.

[0167] (2) The control valve is connected to the starting air chamber and the exhaust pipe, and the gas in the starting air chamber is discharged through the exhaust pipe.

[0168] Specifically, after the control valve is opened, the conversion assembly and the exhaust pipe are connected. At this time, the gas in the conversion assembly will be quickly discharged through the exhaust pipe due to the high pressure.

[0169] The method provided in this embodiment ensures that the gas in the conversion assembly is released when the drone needs to be launched through precise control of the control valve, thereby ensuring the safety and reliability of the drone launch operation.

[0170] Furthermore, the air in the conversion assembly is exhausted through the exhaust pipe. It should be noted that when the air in the conversion assembly is exhausted, the pressure in the high-pressure gas tank will be greater than the pressure in the conversion assembly, and a pressure difference will be generated between the conversion assembly and the high-pressure gas tank.

[0171] S602: opening the first exhaust hole on the conversion assembly based on the air pressure difference, controlling the movement of the valve piston in the conversion assembly to expose the second exhaust hole, and releasing the gas in the high-pressure gas tank.

[0172] In a specific implementation, after a pressure difference occurs between the inside of the high-pressure gas tank and the starting gas chamber, the first exhaust hole inflates the conversion assembly to overcome the resistance provided by the spring on the valve piston, so that the valve piston opens.

[0173] Furthermore, after the valve piston is opened, the second exhaust hole is exposed. At this time, the gas channel between the high-pressure gas tank and the conversion assembly is opened, and the gas in the high-pressure gas tank is released through the conversion assembly.

[0174] S603, the released gas in the high-pressure gas tank drives the piston adapter to move, and the piston adapter drives the drone to be ejected.

[0175] Specifically, the released gas acts on the piston adapter, pushing the piston adapter and the launch shell to fit together, so that the piston adapter is quickly launched in the launch shell.

[0176] Furthermore, since the piston adapter is in direct contact with the drone, the movement of the piston adapter will drive the drone to slide in a straight line at an accelerated speed in the launch shell, and eventually the drone will be ejected.

[0177] The method for launching a drone provided in this embodiment first adjusts the conduction state of the control valve to conduction, and discharges the gas inside the conversion assembly through the exhaust pipe; wherein, the pressure inside the conversion assembly is reduced, and a pressure difference is generated with the high-pressure gas tank, and then the first exhaust hole on the conversion assembly is opened based on the pressure difference, and the valve piston in the conversion assembly is controlled to move, exposing the second exhaust hole, and the gas in the high-pressure gas tank is released, and then the released gas in the high-pressure gas tank pushes the piston adapter to move, and the drone is pushed out based on the piston adapter. In this way, by adjusting the conduction state of the control valve and discharging the gas in the conversion assembly, the opening of the conversion assembly can be quickly triggered, ensuring that the gas in the high-pressure gas tank can be quickly and effectively released, thereby pushing the piston adapter and the drone loaded therein, and this launch mechanism can shorten the launch preparation time of the drone and improve the launch efficiency. Furthermore, since the gas in the high-pressure gas tank is released through a precisely controlled conversion assembly, the thrust generated by the gas in the launch tube is stable and controllable, so that the drone can be ensured to remain stable during the launch process. Furthermore, the launch of the drone is controlled by a mechanical control valve, which reduces the size and weight of the drone launch tube, making the drone launch tube easier to carry and operate. It is particularly suitable for individual carrying and rapid deployment missions, and can stably and reliably complete the launch of the drone in complex terrain.

[0178] The above description is only a preferred embodiment of the present application and is not intended to limit the present application. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present application shall be included in the scope of protection of the present application.

Claims

1. A UAV launch tube, characterized in that: The UAV launch tube comprises a launch shell, a high-pressure gas tank, a piston adapter and a conversion assembly, wherein: One end of the launch shell is a closed bottom surface, and the other end of the launch shell is the outlet of the UAV launch tube; The high-pressure gas tank and the UAV are fixed inside the launch shell, the high-pressure gas tank is located on the bottom surface of the launch shell, and the UAV is located at the exit of the launch shell; One end of the conversion assembly and the tank opening through the high-pressure gas tank are arranged inside the high-pressure gas tank, the tank opening faces the UAV, the other end of the conversion assembly extends through the tank opening and is connected to the piston adapter, and the portion of the conversion assembly extending from the high-pressure gas tank is fixed to the inner wall of the launch shell through a transfer seat around a circle; The piston adapter is located between the conversion assembly and the drone, and the piston adapter contacts an end of the drone away from the outlet of the launch housing; A starting air chamber is provided in the conversion assembly, and the starting air chamber is connected to the high-pressure gas tank and the outside atmosphere respectively. The release valve of the high-pressure gas tank is opened based on the pressure difference between the gas in the high-pressure gas tank and the gas in the starting air chamber, so that the gas in the high-pressure gas tank is released through mechanical transmission, and the piston adapter is pushed to move laterally to launch the UAV; The conversion assembly at least includes: a fixed base, a spring, a valve piston, a starting air chamber, an exhaust pipe and a control valve, wherein: The fixed base is arranged inside the high-pressure gas tank, one end of the spring is connected to the fixed base, and the other end is connected to the valve piston, a starting air cavity is formed between the valve piston and the housing of the conversion assembly, and the valve piston repeatedly moves in the starting air cavity along a first direction according to the difference between the air pressure in the spring and the air pressure in the high-pressure gas tank; The control valve is located on the outer wall of the side of the starting air cavity, the first port of the control valve is connected to the starting air cavity, and the second port of the control valve is connected to the exhaust pipe; the control valve is unidirectionally connected to the exhaust pipe; The exhaust pipe is connected to the spring through a pipeline to discharge the gas in the spring, thereby forming a pressure difference between the conversion component and the high-pressure gas tank.

2. The UAV launch tube according to claim 1, characterized in that: The conversion assembly further includes a first exhaust hole and a second exhaust hole, wherein: The first exhaust hole is provided on a side wall of the conversion assembly inside the high-pressure gas tank, one end of the first exhaust hole is connected to the high-pressure gas tank, and the other end of the first exhaust hole is connected to the starting gas cavity. The first exhaust hole is subjected to the pressure of the gas in the high-pressure gas tank and is unidirectionally connected to the starting gas cavity, thereby squeezing the valve piston to move in a direction close to the spring; The second exhaust hole is arranged on an inner wall where the valve piston contacts the starting air cavity. When the valve piston moves to a preset position in a direction close to the spring, the second exhaust hole is exposed. One end of the second exhaust hole is connected to the starting air cavity, and the other end releases the gas in the high-pressure gas tank to push the piston adapter.

3. The UAV launch tube according to claim 2, characterized in that: The control valve is controlled to be unidirectional, and the gas in the spring is discharged through the exhaust pipe, the exhaust pipe has a first pressure, and the high-pressure gas tank is filled with gas and has a second pressure, which is greater than the first pressure; The difference between the second pressure and the first pressure controls the opening of the first exhaust hole, and the gas in the high-pressure gas tank squeezes the valve piston to move close to the spring to expose the second exhaust hole, and the gas output from the high-pressure gas tank pushes the piston.

4. The UAV launch tube according to claim 1, characterized in that: The conversion assembly also includes an air inlet, wherein: One end of the air inlet is connected to the tank opening of the high-pressure gas tank, and the other end of the air inlet is connected to the high-pressure air pump; The high-pressure air pump fills the gas in the high-pressure gas tank into the high-pressure gas tank through the air inlet.

5. The UAV launch tube according to claim 1, characterized in that: The drone launch tube also includes a barometer, wherein: The barometer is fixed on the tank opening of the high-pressure gas tank, and is used to display the air pressure value in the high-pressure gas tank.

6. The UAV launch tube according to claim 4, characterized in that: The UAV launch tube also includes a rectangular sealing ring and an O-ring, wherein: The rectangular sealing ring is fixed inside the conversion assembly; The O-type sealing ring is fixed inside the air inlet.

7. The UAV launch tube according to claim 1, characterized in that: The drone launch tube also includes a fixing assembly, wherein: The fixing assembly comprises a support rod and a support seat; one end of the support rod is connected to the side surface of the launch shell, and the other end of the support rod is in contact with the bottom surface; One end of the support base is connected to the bottom surface of the launching shell; the support base provides a buffer when launching the UAV.

8. The UAV launch tube according to claim 1, characterized in that: The weight of the drone launch tube is less than a first preset threshold, and the length of the drone launch tube is less than a second preset threshold.

9. A method for launching a drone, characterized in that: The UAV launching method is applied to the UAV launching tube according to any one of claims 1 to 8, and the method comprises: The conduction state of the control valve is adjusted to be on, and the gas inside the conversion assembly is discharged through the exhaust pipe; wherein the pressure inside the conversion assembly is reduced, and a pressure difference is generated with the high-pressure gas tank; Opening a first exhaust hole on the conversion assembly based on the air pressure difference, controlling the movement of a valve piston in the conversion assembly to expose a second exhaust hole, and releasing the gas in the high-pressure gas tank; The released gas in the high-pressure gas tank pushes the piston adapter to move, and the piston adapter pushes the drone to be ejected.

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