Unmanned aerial vehicle launching channel

Abstract

The utility model relates to the technical field of unmanned aerial vehicle launching, in particular to an unmanned aerial vehicle launching channel which comprises a launching cylinder, a launching channel body is arranged in the launching cylinder and used for loading an unmanned aerial vehicle, and a booster is arranged at the tail end of the launching channel body and used for providing thrust to enable the unmanned aerial vehicle to be launched along the launching channel body. A bomb support is arranged between the booster and the tail of the unmanned aerial vehicle, the peripheral size of the bomb support is matched with the size of the launching channel, and thrust provided by the booster is transmitted to the tail of the unmanned aerial vehicle through the bomb support, so that the unmanned aerial vehicle is launched along the launching channel; through the arrangement of the missile support, thrust provided by the booster uniformly acts on the tail of the unmanned aerial vehicle, the unmanned aerial vehicle is stably launched along the launching channel, meanwhile, high-pressure gas provided by the booster is prevented from directly acting on the tail of the unmanned aerial vehicle, damage to driving parts at the tail of the unmanned aerial vehicle is avoided, and autonomous flight of the unmanned aerial vehicle after launching is facilitated.

Description

Technical Field

[0001] The utility model relates to the technical field of UAV launching, in particular to a UAV launching channel. Background Art

[0002] With the rapid development of UAV technology, the application scope of UAVs is becoming more and more extensive. UAVs are of great significance in military applications and are thus widely used in modern wars. The combination of UAV technology and ammunition technology has many advantages. UAVs can achieve long-distance and high-precision target strikes. UAVs can enhance the flexibility during combat and achieve strikes on fixed targets, moving targets, and in complex environments. UAVs can carry various types of ammunition and can select different ammunition to strike targets according to mission requirements. UAVs can quickly switch between reconnaissance and strikes, realizing integrated reconnaissance and strike, and improving the overall combat effectiveness.

[0003] Chinese Patent CN220595241U discloses a spring-powered barrel launching device for small UAVs, including a launching barrel. Two baffles are fixedly connected inside the launching barrel. The top of the two baffles and inside the launching barrel is movably connected with a UAV body. A launching component is arranged inside the launching barrel. The launching component includes a gas storage tank, which is fixedly connected inside the launching barrel. An accommodation cavity is arranged inside the gas storage tank. An anti-tilting component is arranged outside the launching barrel. An air pressure pump is fixedly connected to the outside of the launching barrel, and the output end of the air pressure pump extends into the gas storage tank.

[0004] However, although the spring-powered barrel launching device for small UAVs can achieve barrel launching of UAVs, during actual use, the inventor found that there are still deficiencies in the launching component of the spring-powered barrel launching device for small UAVs. Specifically:

[0005] After the gas in the gas storage tank of the launching component reaches the preset pressure, it flushes open the piston and directly acts on the tail of the UAV. In this way, on the one hand, it is easy to cause uneven force on the tail of the UAV, resulting in an unsatisfactory launching effect of the UAV. On the other hand, for UAVs with driving components at the tail, the high-pressure impact gas is likely to damage the components at the tail of the UAV, causing the UAV to lose the ability of autonomous flight.

[0006] Therefore, based on the above deficiencies, there is an urgent need to design a UAV launching channel at present. Summary of the Utility Model

[0007] The object of the present utility model is to provide a drone launch channel in view of the above-mentioned deficiencies that during the actual launch process of current drones, the high-pressure impact gas directly acts on the tail of the drone, which easily causes uneven stress on the tail of the drone and damage to the components at the tail of the drone.

[0008] In order to achieve the above object of the utility model, the present utility model provides the following technical solutions:

[0009] A drone launch channel includes a launch tube. A launch channel is provided inside the launch tube. The launch channel is used to load the drone. A booster is provided at the tail end of the launch channel. The booster is used to provide thrust to launch the drone along the launch channel.

[0010] A projectile support is provided between the booster and the tail of the drone. The outer peripheral dimension of the projectile support is adapted to the dimension of the launch channel. The thrust provided by the booster is transmitted to the tail of the drone through the projectile support to launch the drone along the launch channel. Low-temperature sealant is applied to the outer periphery of the projectile support. The low-temperature sealant plays a role in lubricating and sealing the launch tube.

[0011] As a preferred technical solution of the present application, one end of the projectile support in contact with the tail of the drone is annular, and a first counterbore is provided in the middle. The first counterbore is used to accommodate the driving component at the tail of the drone. One end of the projectile support in contact with the booster is annular, and a second counterbore is provided in the middle. The second counterbore is used to accommodate the booster.

[0012] As a preferred technical solution of the present application, a guiding cover is provided at one end of the launch channel away from the projectile support. The guiding cover plays a guiding role in the launch of the drone.

[0013] As a preferred technical solution of the present application, guiding grooves are provided on the guiding cover, guiding strips are provided on the drone, and the guiding strips are adapted to the guiding grooves. The guiding strips are slidably arranged in the guiding grooves.

[0014] As a preferred technical solution of the present application, a cover plate is provided on the guiding cover. The cover plate plays a role in sealing the launch channel.

[0015] As a preferred technical solution of the present application, a rubber pad is provided on the cover plate. When the drone is loaded in the launch channel, the rubber pad abuts against the head of the drone.

[0016] As a preferred technical solution of the present application, the material of the projectile support is bakelite.

[0017] As a preferred technical solution of the present application, a buffer mechanism is provided inside the launch tube, and the buffer mechanism is used to prevent the sabot from detaching from the launch channel.

[0018] As a preferred technical solution of the present application, the buffer mechanism includes a spring. A chute is provided on the inner wall of the launch tube, and a slide bar is provided on the sabot. The slide bar is adapted to the chute and is slidably disposed in the chute. The spring is provided at one end of the chute away from the sabot;

[0019] When the sabot pushes the UAV to be launched along the launch channel, the spring blocks the sabot from detaching from the launch channel.

[0020] As a preferred technical solution of the present application, the booster and the launch tube are detachably connected, and the chute penetrates to the tail of the launch tube.

[0021] Compared with the prior art, the beneficial effects of the present utility model are as follows:

[0022] 1. In the solution of the present application, by providing a sabot, the thrust provided by the booster acts uniformly on the tail of the UAV, enabling the UAV to be launched smoothly along the launch channel. At the same time, it avoids the direct action of the high-pressure gas provided by the booster on the tail of the UAV, preventing damage to the drive components at the tail of the UAV and facilitating the autonomous flight of the UAV after launch;

[0023] 2. The annular setting makes the contact surface between the tail of the UAV and the sabot more uniform, increasing the stability when the sabot pushes the UAV for launch. The setting of the first sinking platform avoids the contact between the drive components at the tail of the UAV and the sabot, preventing damage to the drive components at the tail of the UAV during the launch process and facilitating the autonomous flight of the UAV after launch. The setting of the second sinking hole makes the high-pressure gas provided by the booster act more uniformly on the sabot, facilitating the stable launch of the sabot and the stable launch of the UAV;

[0024] 3. The setting of the rubber pad keeps the relative position of the UAV in the launch channel unchanged, preventing the relative movement of the UAV or the sabot in the launch channel during transportation, which may cause damage to the UAV or the sabot and is beneficial to the transportation of the UAV. Further, the rubber pad can deform and can buffer the vibration of the UAV during transportation to a certain extent. Especially when transporting on an uneven road, excessive vibration may cause damage to the UAV or the sabot, which is not conducive to the transportation of the UAV. The setting of the rubber pad reduces the risk of damage to the UAV or the sabot and is beneficial to the transportation of the UAV;

[0025] 4. During the launch process of the drone, in the initial stage, the cartridge carrier pushes the drone forward. As the cartridge carrier and the drone move within the launch channel, when the cartridge carrier contacts the spring, under the action of the spring, the cartridge carrier begins to decelerate, and the drone maintains the launch speed. The drone detaches from the cartridge carrier, the drone exits the launch channel, the cartridge carrier decelerates until it stops, and under the action of the spring, the cartridge carrier moves towards the tail of the launch channel until it returns to the starting position. The spring serves two purposes: on the one hand, it prevents the cartridge carrier from detaching from the launch channel and buffers and decelerates the cartridge carrier; on the other hand, it pushes the cartridge carrier back to the initial position to facilitate the launch of the next drone. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 FIG. is a schematic structural diagram of one implementation manner of a drone launch channel of the present application;

[0027] Figure 2 FIG. is a sectional structural diagram of one implementation manner of a drone launch channel of the present application;

[0028] Figure 3 FIG. is an assembled sectional structural diagram of one implementation manner of a drone launch channel of the present application;

[0029] Figure 4 FIG. is an assembled sectional structural diagram of one implementation manner of a drone launch channel of the present application from another perspective;

[0030] Figure 5 FIG. is a schematic structural diagram of one implementation manner of a guiding cover of a drone launch channel of the present application;

[0031] Figure 6 FIG. is a schematic structural diagram of one implementation manner of a cartridge carrier of a drone launch channel of the present application;

[0032] Reference numerals in the figures: 1 - launch tube, 2 - launch channel, 3 - booster, 4 - cartridge carrier, 5 - guiding cover, 6 - cover plate, 7 - drone, 8 - buffer mechanism, 11 - sliding groove, 41 - sliding strip, 42 - first counterbore, 43 - second counterbore, 44 - low-temperature sealant, 51 - guiding groove, 61 - rubber pad, 71 - guiding strip, 81 - spring. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0033] To make the objectives, technical solutions, and advantages of the embodiments of the present utility model clearer, the technical solutions in the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings. Apparently, the described embodiments are some, but not all, of the embodiments of the present utility model.

[0034] Therefore, the following detailed description of the embodiments of the present utility model is not intended to limit the scope of the present utility model claimed, but merely represents some embodiments of the present utility model. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present utility model without creative efforts shall fall within the scope of protection of the present utility model.

[0035] It should be noted that, without conflict, the embodiments in the present utility model and the features and technical solutions in the embodiments may be combined with each other.

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

[0037] In the description of the present utility model, it should be noted that the orientation or positional relationship indicated by terms such as "upper", "lower", etc. is based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship in which the product of the present utility model is usually placed during use, or the orientation or positional relationship commonly understood by those skilled in the art. Such terms are only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation of the present utility model. In addition, terms such as "first", "second", etc. are only used for descriptive distinction and cannot be understood as indicating or implying relative importance.

[0038] Embodiment 1: Refer to Figure 1 as shown

[0039] A drone launch channel provided in this embodiment includes a launch tube 1. A launch channel 2 is arranged inside the launch tube 1. The launch channel 2 is used to load a drone 7. A booster 3 is arranged at the tail end of the launch channel 2. The booster 3 is used to provide thrust to launch the drone 7 along the launch channel 2.

[0040] A cartridge 4 is arranged between the booster 3 and the tail of the drone 7. The outer dimensions of the cartridge 4 are adapted to the dimensions of the launch channel 2. The thrust provided by the booster 3 is transmitted to the tail of the drone 7 through the cartridge 4, so that the drone 7 is launched along the launch channel 2. A low-temperature sealant 44 is applied to the outer periphery of the cartridge 4. The low-temperature sealant 44 plays a role in lubricating and sealing the launch tube 1.

[0041] In this embodiment, by providing the sabot 4, the thrust provided by the booster 3 acts uniformly on the tail of the UAV 7, enabling the UAV 7 to be smoothly launched along the launch channel 2. At the same time, it avoids the direct action of the high-pressure gas provided by the booster 3 on the tail of the UAV 7, preventing damage to the drive components at the tail of the UAV 7, which is beneficial to the autonomous flight of the UAV 7 after launch. The application of the cryogenic sealant 44 increases the lubrication and sealing effect of the launch tube 1, which is beneficial to the stability of the UAV 7 during launch; in this embodiment, the booster 3 provides thrust for the sabot 4 by generating gas through explosion.

[0042] As a preferred embodiment, on the basis of the above method, further, one end of the sabot 4 in contact with the tail of the UAV 7 is annular, and a first counterbore 42 is provided in the middle. The first counterbore 42 is used to accommodate the drive components at the tail of the UAV 7. One end of the sabot 4 in contact with the booster 3 is annular, and a second counterbore 43 is provided in the middle. The second counterbore 43 is used to accommodate the booster 3.

[0043] The annular setting makes the contact surface between the tail of the UAV 7 and the sabot 4 more uniform, increasing the stability of the sabot 4 when pushing the UAV 7 to launch. The setting of the first counterbore avoids the contact between the drive components at the tail of the UAV 7 and the sabot 4, preventing damage to the drive components at the tail of the UAV 7 during the launch process, which is beneficial to the autonomous flight of the UAV 7 after launch. The setting of the second counterbore 43 enables the high-pressure gas provided by the booster 3 to act more uniformly on the sabot 4, which is beneficial to the stable launch of the sabot 4 and the stable launch of the UAV 7.

[0044] As a preferred embodiment, on the basis of the above method, further, a guiding cover 5 is provided at one end of the launch channel 2 away from the sabot 4. The guiding cover 5 guides the launch of the UAV 7.

[0045] The setting of the guiding cover 5 ensures that the UAV 7 is launched in a predetermined direction at the moment of launch, which is beneficial to the stable launch of the UAV 7.

[0046] As a preferred embodiment, on the basis of the above method, further, a guiding groove 51 is provided on the guiding cover 5, and a guiding strip 71 is provided on the UAV 7. The guiding strip 71 is adapted to the guiding groove 51, and the guiding strip 71 is slidably arranged in the guiding groove 51.

[0047] At the moment of launch of the UAV 7, the setting of the guiding groove 51 restricts the guiding strip 71 on the UAV 7 to move within the guiding groove 51. In this way, on the one hand, it ensures the direction of the UAV 7 at the moment of launch, and on the other hand, it avoids the phenomenon of deflection or even tumbling of the UAV 7 during launch, which is beneficial to the stable launch of the UAV 7.

[0048] As a preferred embodiment, on the basis of the above - mentioned manner, further, a cover plate 6 is provided on the guiding cover 5, and the cover plate 6 functions to seal the emission channel 2.

[0049] The provision of the cover plate 6 prevents foreign objects from entering the emission channel 2 during transportation, further preventing foreign objects from getting stuck between the emission channel 2 and the unmanned aerial vehicle 7, which is beneficial to the smooth launch of the unmanned aerial vehicle 7.

[0050] As a preferred embodiment, on the basis of the above - mentioned manner, further, when the unmanned aerial vehicle 7 is loaded in the emission channel 2, the rubber pad 61 abuts against the head of the unmanned aerial vehicle 7.

[0051] The provision of the rubber pad 61 keeps the relative position of the unmanned aerial vehicle 7 in the emission channel 2 unchanged, preventing the relative movement of the unmanned aerial vehicle 7 or the cartridge case 4 in the emission channel 2 during transportation, which may cause damage to the unmanned aerial vehicle 7 or the cartridge case 4. This is beneficial to the transportation of the unmanned aerial vehicle 7. Further, the rubber pad 61 can deform and can buffer the jitter of the unmanned aerial vehicle 7 during transportation to a certain extent. Especially when transported on an uneven road, excessive jitter may cause damage to the unmanned aerial vehicle 7 or the cartridge case 4, which is not conducive to the transportation of the unmanned aerial vehicle 7. The provision of the rubber pad 61 reduces the risk of damage to the unmanned aerial vehicle 7 or the cartridge case 4 and is beneficial to the transportation of the unmanned aerial vehicle 7.

[0052] As a preferred embodiment, on the basis of the above - mentioned manner, further, the material of the cartridge case 4 is bakelite.

[0053] Bakelite has the advantages of high temperature resistance and high strength. When the booster 3 uses the method of generating gas by explosion, the bakelite - made cartridge case 4 can well withstand the gas impact and avoid damage to the unmanned aerial vehicle 7 caused by high temperature, which is beneficial to the protection of the unmanned aerial vehicle 7 and is beneficial to the stable launch of the unmanned aerial vehicle 7.

[0054] As a preferred embodiment, on the basis of the above - mentioned manner, further, a buffer mechanism 8 is provided in the launch tube 1, and the buffer mechanism 8 is used to prevent the cartridge case 4 from detaching from the emission channel 2.

[0055] The provision of the buffer mechanism 8 prevents the cartridge case 4 from detaching from the emission channel 2. In this way, the cartridge case 4 can be reused, reducing the launch cost of the unmanned aerial vehicle 7.

[0056] As a preferred embodiment, on the basis of the above - mentioned manner, further, the buffer mechanism 8 includes a spring 81. A sliding groove 11 is provided on the inner wall of the launch tube 1, and a sliding strip 41 is provided on the cartridge case 4. The sliding strip 41 is adapted to the sliding groove 11, and the sliding strip 41 is slidably arranged in the sliding groove 11. The spring 81 is provided at one end of the sliding groove 11 away from the cartridge case 4;

[0057] When the sabot 4 pushes the UAV 7 to be launched along the launch channel 2, the spring 81 blocks the sabot 4 from detaching from the launch channel 2.

[0058] During the launch process of the UAV 7, in the initial stage, the sabot 4 pushes the UAV 7 forward. As the sabot 4 and the UAV 7 move in the launch channel 2, when the sabot 4 contacts the spring 81, under the action of the spring 81, the sabot 4 starts to decelerate, the UAV 7 maintains the launch speed, the UAV 7 detaches from the sabot 4, the UAV 7 detaches from the launch channel 2, the sabot 4 decelerates until it stops, and under the action of the spring 81, the sabot 4 moves towards the tail of the launch channel 2 until it returns to the starting position; the setting of the spring 81, on the one hand, blocks the sabot 4 from detaching from the launch channel 2 and buffers and decelerates the sabot 4, and on the other hand, pushes the sabot 4 back to the initial position, facilitating the next launch of the UAV 7.

[0059] As a preferred embodiment, on the basis of the above method, further, the booster 3 and the launch tube 1 are detachably connected, and the chute 11 runs through to the tail of the launch tube 1.

[0060] With the above structure, on the one hand, after the sabot 4 is used multiple times, it may not meet the usage requirements, so it is convenient to take out the sabot 4 from the tail of the launch tube 1 and replace it in time. On the other hand, it is convenient to replace the booster 3, which is beneficial to improving the combat efficiency.

[0061] The above embodiments are only used to illustrate the present invention and do not limit the technical solutions described in the present invention. Although this specification has described the present invention in detail with reference to the above respective embodiments, the present invention is not limited to the above specific implementation manners. Therefore, any modification or equivalent replacement of the present invention; and all technical solutions and their improvements that do not depart from the spirit and scope of the present invention are covered by the scope of the claims of the present invention.

Claims

1. An unmanned aerial vehicle launch channel, characterized in that: It includes a launch tube, in which a launch channel is provided. The launch channel is used to load an unmanned aerial vehicle (UAV). A booster is arranged at the tail end of the launch channel, and the booster is used to provide thrust to launch the UAV along the launch channel. A sabot is arranged between the booster and the tail of the UAV. The outer peripheral dimension of the sabot is adapted to the dimension of the launch channel. The thrust provided by the booster is transmitted to the tail of the UAV through the sabot, so that the UAV is launched along the launch channel. A low-temperature sealant is smeared on the outer periphery of the sabot, and the low-temperature sealant plays a role in lubricating and sealing the launch tube.

2. The drone launch channel according to claim 1, characterized in that: One end of the sabot in contact with the tail of the UAV is annular, and a first counterbore is arranged in the middle. The first counterbore is used to accommodate the driving component at the tail of the UAV. One end of the sabot in contact with the booster is annular, and a second counterbore is arranged in the middle. The second counterbore is used to accommodate the booster.

3. The drone launch channel according to claim 2, wherein: A guiding cover is arranged at one end of the launch channel away from the sabot, and the guiding cover plays a guiding role in the launch of the UAV.

4. The drone launching channel according to claim 3, wherein: A guiding groove is arranged on the guiding cover, and a guiding strip is arranged on the UAV. The guiding strip is adapted to the guiding groove, and the guiding strip is slidably arranged in the guiding groove.

5. The drone launch channel according to claim 4, wherein: A cover plate is arranged on the guiding cover, and the cover plate plays a role in sealing the launch channel.

6. The drone launch channel according to claim 5, characterized in that: A rubber pad is arranged on the cover plate. When the UAV is loaded in the launch channel, the rubber pad abuts against the head of the UAV.

7. The drone launch channel according to claim 6, wherein: The material of the sabot is bakelite.

8. A drone launch channel as claimed in claim 7, wherein: A buffer mechanism is arranged in the launch tube, and the buffer mechanism is used to prevent the sabot from detaching from the launch channel.

9. The drone launch channel according to claim 8, wherein: The buffer mechanism includes a spring. A sliding groove is arranged on the inner wall of the launch tube, and a sliding strip is arranged on the sabot. The sliding strip is adapted to the sliding groove, and the sliding strip is slidably arranged in the sliding groove. The spring is arranged at one end of the sliding groove away from the sabot. When the sabot pushes the UAV to be launched along the launch channel, the spring prevents the sabot from detaching from the launch channel.

10. A drone launch channel as described in claim 9, characterized in that: The connection between the booster and the launch tube is detachable, and the sliding groove penetrates to the tail of the launch tube.

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