Launch device for unmanned aerial vehicle onboard missiles

Abstract

The application discloses a launching device for unmanned aerial vehicle airborne missile, which comprises an airborne missile, a plug-in part, a pulling-off fixing part and a guide part. At least two sliding blocks are arranged on the top of the airborne missile, and a locking release module is arranged on one of the sliding blocks. The plug-in part comprises a first plug-in part and a second plug-in part. The first plug-in part is fixedly arranged above the other sliding block of the airborne missile and electrically connected with the inside of the airborne missile. The second plug-in part is arranged on the same sliding block as the first plug-in part and is in plug-in connection with the first plug-in part. A shock-absorbing buffer is arranged on the other side of the second plug-in part and is electrically connected with the first plug-in part to control the on-off of the airborne missile. The pulling-off fixing part is arranged on one side of the plug-in part and is fixedly connected with the shock-absorbing buffer. A sliding groove matched with one or more sliding blocks is arranged on the guide part. The airborne missile is guided and launched through the cooperation of the sliding blocks and the sliding grooves. The small and light pulling-off plug is realized, and the launching safety and reliability are improved.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) airborne missile technology, and in particular to a launching device for UAV airborne missiles. Background Technology

[0002] The disconnect plug is a commonly used component in missile and rocket launchers. It is connected before launch and disconnected at the moment of ignition. Its on / off switching plays a vital role in important functions such as communication between the missile and the outside world, safety, and emergency activation.

[0003] Currently, release connectors mainly include release connectors with guide rods and ordinary docking connectors. Release connectors with guide rods typically can only be installed radially along the projectile body, and require a four-bar linkage or similar mechanism to assist release using the projectile's movement. This design, requiring a dedicated guide rod for release, has significant drawbacks: it is therefore larger in size. Furthermore, the need for a dedicated guide rod for release inevitably necessitates creating relatively large holes and slots in the projectile body, reducing its overall strength. Ordinary docking connectors are usually installed along the projectile's direction of movement, increasing the structural dimensions and potentially interfering with the projectile's movement. If installed radially, they require complex mechanisms to achieve the release action, which is cumbersome and complex for drones. Moreover, complexity implies reduced reliability and potentially increased weight, significantly reducing the drone's flight time. Summary of the Invention

[0004] To address some or all of the technical problems existing in the prior art, the present invention provides a launching device for airborne missiles of unmanned aerial vehicles (UAVs). In the application of micro-missiles launched by rotary-wing UAVs, the device achieves miniaturization and weight reduction of the disconnect plug, thereby reducing the openings in the missile body and improving the missile body strength while ensuring the safety and reliability of micro-missile launch.

[0005] The technical solution of the present invention is as follows:

[0006] This invention provides a launching device for an unmanned aerial vehicle (UAV) airborne missile, comprising:

[0007] An airborne missile is provided with at least two sliders on its top, and a locking and releasing module is provided on one or more of the two sliders for fixing the airborne missile during the flight of the UAV and releasing the constraint during launch.

[0008] The connector includes a first connector and a second connector. The first connector is fixedly disposed above one or more other sliders of the two sliders on the airborne missile and is electrically connected to the interior of the airborne missile via a wire. The second connector is located on the same slider as the first connector and is plugged into and detached from the first connector. A shock-absorbing buffer is provided on the other side of the second connector. The second connector is electrically connected to the first connector to control the on / off state of the airborne missile.

[0009] A detachable fixing component is disposed on one side of the connector and fixedly connected to the shock-absorbing buffer component. The detachable fixing component is fixedly disposed on the guide component and is used to detach and separate the first connector and the second connector simultaneously with the launch of the airborne missile. After the first connector and the second connector are detached and separated, the first connector flies with the airborne missile, and the second connector is constrained by the detachable fixing component to prevent the second connector from falling and interfering with the airborne missile and the slider on the airborne missile.

[0010] The guide component has a groove that matches one or more of the sliders. The guide component is used to fix the connection with an external UAV, and also to carry the airborne missile for guided launch through the cooperation of the sliders and the grooves and the locking and fixing of the locking and releasing module.

[0011] Furthermore, in the aforementioned launching device for UAV-borne missiles, the number of sliders includes two.

[0012] Furthermore, in the aforementioned launching device for UAV-borne missiles, the slider includes a first slider and a second slider. The first connector is attached to the first slider. The second slider can be locked and released by a locking and releasing module to fix and release the constraints of the airborne missile in the flight direction. The first slider and the second slider are spaced apart on the top of the airborne missile, and the first slider and the second slider are located on the same axis on the top of the airborne missile along the flight direction of the missile.

[0013] Furthermore, in the aforementioned launching device for UAV-borne missiles, the cross-section of the second slider is a T-shaped structure, the first slider has an integrally formed boss at the top of the T-shaped structure of the second slider, and a round hole for cooperating with the locking and releasing module is also provided at the top of the second slider.

[0014] Furthermore, in the aforementioned launching device for UAV-borne missiles, the guide component includes a detachment portion and a guide portion, which are integrally formed and have a linear structure. Both the detachment portion and the guide portion are provided with grooves that match one or more of the sliders. The shape of the groove in the guide portion matches the shape of the first slider and is provided with a boss hole for the boss and the first connector on the boss to pass through. The shape of the groove in the guide portion matches the shape of the second slider, and the cross-section of the groove in the guide portion is a T-shaped structure. After the airborne missile is launched and the first connector and the second connector separate, the second slider can pass through the groove through which the first slider passes.

[0015] Furthermore, in the aforementioned launching device for UAV-borne missiles, the first slider and the second slider have T-shaped cross-sections with the same height and shape, which are also consistent with the height and shape of the T-shaped structure of the release portion and the groove on the guide for the first slider and the second slider to pass through.

[0016] Furthermore, in the aforementioned launching device for UAV-borne missiles, the detachment fixing component includes a fixed base plate and a fixed top plate. The fixed base plate has a groove in the middle that mates with the first and second connectors. A rubber pad is provided between the fixed base plate and the fixed top plate. The shock-absorbing buffer connected to the second connector is pressed between the fixed top plate and the rubber pad.

[0017] Furthermore, in the aforementioned launching device for UAV-borne missiles, the shock-absorbing buffer includes one or more sets of connecting flexible wires.

[0018] Furthermore, in the aforementioned launching device for UAV-borne missiles, the length of the second connector connecting the second connector to the shock-absorbing buffer is less than the height of the boss provided on the first slider.

[0019] Furthermore, in the aforementioned launching device for UAV-borne missiles, the length of the shock-absorbing buffer connecting the second connector and the release fixing member includes 3mm-5mm.

[0020] The main advantages of the technical solution of this invention are as follows:

[0021] The present invention relates to a launch device for an unmanned aerial vehicle (UAV)-borne missile. This device achieves the separation and launch of the UAV-transported airborne missile through a structure consisting of a connector, a release fixing component, and a guide component. The structure is simple, reducing the need for excessive holes and slots in the missile body, thus mitigating the risk of weakening the missile's strength. Simultaneously, by reducing the weight of the launch device, the endurance of the UAV is extended. Specifically, in this invention, at least two sliders are provided on the airborne missile. A groove with a height difference is provided on the guide component for the sliders to pass through. During the launch of the airborne missile, the sliders slide along the groove with the height difference. The release fixing component releases the connector, enabling the connection and unlocking of the airborne missile's release plug. This achieves miniaturization and weight reduction of the release plug, reducing the need for openings in the missile body, increasing the missile body's strength, and ensuring the safety and reliability of the micro-missile launch. Attached Figure Description

[0022] The accompanying drawings, which are included to provide a further understanding of embodiments of the invention and constitute a part of this invention, illustrate exemplary embodiments of the invention and, together with their description, serve to explain the invention and do not constitute an undue limitation thereof. In the drawings:

[0023] Figure 1 This is a schematic diagram of a structure for mounting a launch device for an airborne missile on a drone according to an embodiment of the present invention.

[0024] Figure 2 This is a schematic diagram of the process of the airborne missile and the guide component cooperating in a launching device for an unmanned aerial vehicle (UAV) missile according to an embodiment of the present invention.

[0025] Figure 3 for Figure 2 A magnified view of area A;

[0026] Figure 4 for Figure 2 A magnified view of area B;

[0027] Figure 5 This is a cross-sectional structural schematic diagram of the pull-out portion in the guide member of a launch device for an unmanned aerial vehicle (UAV) missile, according to an embodiment of the present invention.

[0028] Figure 6 This is a cross-sectional structural schematic diagram of the guide portion in a guide member of a launch device for an unmanned aerial vehicle (UAV) airborne missile, according to an embodiment of the present invention.

[0029] Figure 7 This is a first-view structural diagram of a guide component in a launch device for an unmanned aerial vehicle (UAV) airborne missile, according to an embodiment of the present invention.

[0030] Figure 8 for Figure 7 Schematic diagram of the cross-sectional structure along the AA direction;

[0031] Figure 9 This is a second-view structural diagram of a guide component in a launch device for an unmanned aerial vehicle (UAV) airborne missile, according to an embodiment of the present invention.

[0032] Figure 10 This is a third-view structural diagram of a guide component in a launch device for an unmanned aerial vehicle (UAV) airborne missile, according to an embodiment of the present invention.

[0033] Figure 11 This is a schematic diagram of the structure of a launch device for UAV-borne missiles after the airborne missile is connected to the guide component, according to an embodiment of the present invention.

[0034] Figure 12 for Figure 11 A magnified view of area C;

[0035] Figure 13 This is a schematic diagram of a launching device for an unmanned aerial vehicle (UAV) airborne missile, according to an embodiment of the present invention, in which a release fixing member and a plug-in member are disposed on a first slider.

[0036] Figure 14 for Figure 13 A magnified view of area D;

[0037] Explanation of reference numerals in the attached figures:

[0038] 1. Airborne missile; 2. First connector; 3. Second connector; 4. Fixed base plate; 5. Fixed top plate; 6. First slider; 61. Boss; 7. Second slider; 71. Circular hole; 8. Slide groove; 9. Boss hole; 10. Shock-absorbing buffer; 11. Wire; 12. Guide; 121. Release part; 122. Guide part; 13. Locking and releasing module; 14. UAV; 15. Release fixing part. Detailed Implementation

[0039] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of this invention will be clearly and completely described below in conjunction with specific embodiments and corresponding drawings. Obviously, the described embodiments are only a part of the embodiments of this invention, and not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention.

[0040] The technical solutions provided by the embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0041] As attached Figures 1-14As shown, this embodiment of the invention provides a launching device for an airborne missile used by an unmanned aerial vehicle (UAV). The device includes an airborne missile 1, a connector, a release and fixing component 15, and a guide component 12, wherein:

[0042] At least two sliders are provided on the top of the airborne missile 1, and a locking and releasing module 13 is provided on one or more of the two sliders for fixing the airborne missile 1 during the flight of the UAV and releasing the constraint at the moment of launch. The connectors include a first connector 2 and a second connector 3. The first connector 2 is fixedly provided above one or more of the other two sliders of the airborne missile 1, and the slider of the first connector 2 is different from the slider of the locking and releasing module 13. It is electrically connected to the airborne missile 1 via a wire 11. The second connector 3 is located on the same slider as the first connector 2. The second connector 3 is plugged and pulled into the first connector 2. The second connector 3 is parallel and close to the first connector 2. A shock-absorbing buffer 10 is provided on the other side of the second connector 3. The connection and disconnection between the second connector 3 and the first connector 2 controls the communication status between the UAV and the airborne missile. A release fixing member 15 is provided on one side of the connector. The shock absorber 10 is fixedly connected to the guide member 12, and the detachment fixing member 15 is fixedly set on the guide member 12. It is used to detach and separate the first connector 2 and the second connector 3 at the same time as the airborne missile 1 is launched. After the first connector 2 and the second connector 3 are detached and separated, the first connector 2 flies with the airborne missile 1, and the second connector 3 is constrained by the detachment fixing member 15 to prevent the second connector 3 from falling and interfering with the airborne missile 1 and the slider set on the airborne missile 1. The shock absorber 10 on the second connector 3 is constrained on the detachment fixing member 15. Therefore, it can ensure that the two are separated at the time of launch, and prevent the second connector 3 from falling and interfering with the airborne missile 1 and one or more sliders on the airborne missile 1. The guide member 12 is provided with a groove 8 that matches one or more sliders. The guide member 12 is used to fix the connection with the external UAV 14. At the same time, the guide member 12 is also used to guide the launch of the airborne missile 1 through the cooperation of the slider and the groove 8 and the locking and fixing of the locking and releasing module 13.

[0043] Specifically, in practical applications, the connector can be placed above any one of the sliders. For example, the number of sliders includes two. That is, the sliders include a first slider 6 and a second slider 7. The first connector 2 is attached to the first slider 6. The second slider 7 can be locked and released by the locking and releasing module 13 to fix and release the constraint of the airborne missile 1 in the flight direction. The first slider 6 and the second slider 7 are spaced apart on the top of the airborne missile 1, and the first slider 6 and the second slider 7 are located on the same axis on the top of the airborne missile 1 along the flight direction of the missile.

[0044] It should be noted that for airborne missiles with a relatively long length, the slider can be set to three, and the specific number of sliders is determined according to the recorded length of missile 1.

[0045] It should also be noted that, in practical applications, the first connector 2 is attached and connected within the groove of the first slider 6 or the first slider 6. For example, as shown... Figures 2-3 , Figures 11-14 As shown in the figure, the first slider 6 is pasted on the surface. In the actual design, the thickness of the first slider 6 will be increased, and a groove will be designed at the corresponding pasting location to sink the first connector 2, so as to better play a restraining role.

[0046] Specifically, the above-mentioned constraint principle is as follows: the shock-absorbing buffer 10 on the second connector 3 is pressed into the pull-out fixing member 15, and the second connector 3 is constrained by the squeezing of the pull-out fixing member 15.

[0047] With this configuration, by placing the first slider 6 and the second slider 7 on the same axis at the top of the airborne missile 1, only one guide member 12 is needed for fixing and guiding to complete the transportation and guided launch of the airborne missile 1, thus making the structure simpler, more reliable, and less expensive. By reducing the number of sliders on the airborne missile 1 and the number of guide members 12 connected to the UAV 14, the weight transported by the UAV 14 is reduced, thereby increasing the endurance of the UAV 14 and ensuring the smooth launch of the airborne missile. This makes the transportation of the UAV 14 safer and more reliable. At the same time, it can avoid opening more holes or slots on the airborne missile 1, and can further improve the strength of the missile body by reducing the number of openings in the missile body, while ensuring the safety and reliability of the micro-missile launch.

[0048] To ensure that the first slider 6 and the second slider 7 in this invention can better serve their functions of fixing, connecting, and guiding, the first slider 6 is positioned closer to the warhead, and the second slider 7 is positioned closer to the tail. This ensures the stability of the airborne missile 1 during transport. In addition to the aforementioned front-to-back positioning, the first slider 6 and the second slider 7 are also positioned at the top center or bottom center of the airborne missile 1, that is, directly above or below the missile body structure. This prevents the UAV 14 from deviating or tilting during transport, facilitating transport and improving transport efficiency. Furthermore, to ensure a more secure connection between the first slider 6 and the second slider 7, guaranteeing the transport stability and launch reliability of the airborne missile 1, the first slider 6 and the second slider 7 are welded to the airborne missile 1.

[0049] In some optional implementations of this embodiment, the lead wire of the airborne missile 1 is passed through the first slider 6 and connected to the first connector 2, so that the airborne missile 1 can maintain its strength without being damaged, and can also play a sealing role, so as to avoid the hole or groove of the wire 11 causing the sealing performance of the airborne missile 1 to be reduced, thus affecting the launch of the airborne missile 1.

[0050] Specifically, in order to better connect the first connector 2 to the airborne missile 1, reduce the flight drag of the airborne missile, and prevent rainwater from entering, it is preferable to pass the wire 11 into the airborne missile 1 through a rectangular or circular slot. After the two are safely and reliably connected, in this invention, the front end of the first connector 2 connected to the airborne missile 1 is sealed and fixed into a 45° slope with insulating soft glue to reduce drag during flight. It can also be designed as a small part with a 45° slope, such as a 45° cover plate, and fixed to the wire 11 at the front end of the first connector 2.

[0051] Specifically, such as Figure 2 , Figures 7-10 As shown, the guide 12 includes a release part 121 and a guide part 122. The release part 121 and the guide part 122 are integrally formed and have a straight structure. Both the release part 121 and the guide part 122 are provided with a groove 8 that matches one or more sliders. The shape of the groove 8 of the guide part 122 matches the shape of the first slider 6. It is provided with a boss hole 9 for the boss 61 and the first connector 2 on the boss 61 to pass through. The shape of the groove 8 of the guide part matches the shape of the second slider 7. That is, the cross-section of the groove 8 of the guide part 122 is a T-shaped structure. After the airborne missile 1 is launched and the first connector 2 and the second connector 3 are separated, the second slider 7 can pass through the groove 8 through which the first slider 6 passes.

[0052] This configuration allows the guide component 12 to simultaneously serve as a guide and a release mechanism.

[0053] Preferably, the cross-section of the second slider 7 is a T-shaped structure, and the first slider 6 and the second slider 7 have the same structural form. The first slider 6 also has an integrally formed boss 61 at the top of the T-shaped structure of the second slider 7, and a circular hole 71 for cooperating with the locking and releasing module 13 is also provided at the top of the second slider 7. The length of the shock-absorbing buffer 10 connecting the second connector 3 and the release fixing member 15 is set to be less than the height of the boss 61 on the first slider 6. To ensure that the first slider 6, the second slider 7, the first connector 2, and the second connector 3 do not interfere with other components when sliding in the groove 8, the first slider 6 and the second slider 7 are set to the same height, or the height of the first slider 6 is set to be slightly higher than that of the second slider 7.

[0054] In some optional implementations of this embodiment, the locking and releasing module 13 is in a state of being able to lock and fix under normal conditions, and can release the force used for locking and fixing under stress or power-on conditions. Preferably, the locking and releasing module 13 is a quick-change structure, such as having a matching pin on the locking and releasing module 13 for locking the slider.

[0055] This configuration ensures that when the airborne missile 1 is launched from the UAV 14, after the first connector 2 and the second connector 3 separate, the first connector 2 can be fixed in the boss hole 9. This prevents the first connector 2 from falling into the sliding groove 8 of the second slider 7 after separation and interfering with the second slider 7. It also prevents the first connector 2 from colliding or interfering with the second slider 7 and / or the airborne missile 1, thus ensuring the safety of the airborne missile 1 and improving the safety and reliability of the launch.

[0056] For example, the first connector 2 is a female connector, and the second connector 3 is a male connector. The female connector is mounted on the first slider 6, and the two can be bonded together with strong adhesive. A rectangular slot is opened at the front end of the airborne missile 1, and the wire of the female connector enters the interior of the airborne missile 1 through this slot. The second slider 7 has a circular or rectangular hole for locking and releasing module 13 to engage. Before disengagement, there is a guide groove above the slide for the connector slider, but this is not needed afterward; a normal guide rail can be used. Since the width of the first slider 6 is larger than the width of the first connector 2 and the second connector 3, the female connector can be installed on the first slider or can be sunk into the first slider. The first slider 6 cannot enter the groove 8 of the first connector 2 and the second connector 3. The female connector is installed on the boss 61 of the first slider 6. Since the bottom of the groove 8 located in the guide 12 is higher than the upper surface of the second slider 7, this ensures that even after disengagement, the second slider 7 on the moving airborne missile 1 will not collide with the remaining disengaged male connector, thus ensuring the safety and reliability of the airborne missile 1.

[0057] Therefore, the launching device for UAV-borne missiles of the present invention achieves the separation and launch of the airborne missile 1 transported by the UAV 14 through the structure of the connector, the release fixing member 15, and the guide member 12. The structure is simple, reducing the problem of opening too many holes and slots in the airborne missile 1 body, which would reduce the strength of the airborne missile 1. At the same time, by reducing the weight of the launching device, the purpose of extending the endurance of the UAV 14 is achieved. Specifically, in the present invention, by setting at least two sliders on the airborne missile 1, and by opening a groove 8 on the guide member 12 for one or more sliders to pass through, and setting the groove 8 to have a height difference, multiple sliders can slide through the groove 8 with the height difference during the launch of the airborne missile 1. The launch control of the airborne missile 1 is achieved by releasing the connector through the release fixing member 15. The miniaturization and weight reduction of the release connector are achieved, thereby reducing the openings in the missile body and improving the strength of the missile body, while ensuring the safety and reliability of the micro-missile launch.

[0058] In some optional implementations of this embodiment, the first connector 2 and the first slider 6 are connected by strong adhesive.

[0059] Specifically, the first slider 6 and the second slider 7 have the same height and shape as the T-shaped structure in their cross-sections, which is the same as the groove 8 on the guide 12 on the pull-out part 121 and the guide part 122 for the passage of the first slider 6 and the second slider 7.

[0060] With this configuration, only one guide member 12 is needed. By setting a groove 8 on the guide member 12 that matches the first slider 6 and the second slider 7, the second slider 7 can complete the guided launch of the airborne missile 1 through the through groove of the first slider 6 after the first connector 2 and the second connector 3 are separated. This simplifies the overall structure and reduces the number of guide members 12, thereby reducing the weight carried by the UAV 14 and increasing the endurance.

[0061] Specifically, the detachment fixing component 15 includes a fixed base plate 4 and a fixed top plate 5. The fixed base plate 4 has a groove in the middle that mates with the first connector 2 and the second connector 3. There is a rubber pad between the fixed base plate 4 and the fixed top plate 5. The shock-absorbing buffer 10 connected to the second connector 3 is pressed between the fixed top plate 4 and the rubber pad. The fixed top plate 5 is detachably connected above the fixed base plate 4 to fix the shock-absorbing buffer 10.

[0062] Meanwhile, in order to better secure the second connector 3 and prevent the first connector 2 and the second connector 3 from falling off and / or loosening due to vibrations during the drone's flight, a rubber pad, plastic pad, or adhesive rubber pad is provided under the second connector 3. This allows the shock-absorbing buffer 10 to be pressed onto the fixed base plate 4, thereby securing the second connector 3. This design not only secures the second connector 3 well to the fixed base plate 4 but also prevents the shock-absorbing buffer 10 from being damaged by the pressure of the fixed top plate 5 and the fixed base plate 4, while also providing greater friction.

[0063] In some optional implementations of this embodiment, the fixed base plate 4 includes two parallel plate-like structures with a certain thickness and width, such as two parallel metal plates. The two parallel metal plates are disposed on the guide member 12, and after being disposed on the guide member 12, a gap is provided between the two metal plates for the passage of the first slider 6 and the second slider 7, so that the first slider 6 and the second slider 7 can slide guidedly along the gap of the fixed base plate 4. The fixed top plate 5 is disposed above the fixed base plate 4 by means of a threaded connection, and the area of ​​the fixed base plate 4 is larger than the area of ​​the fixed top plate 5. Preferably, the lateral width of the fixed base plate 4 and the fixed top plate 5 is consistent with the lateral width of the guide member 12. The fixed base plate 4 and the fixed top plate 5 are connected by a threaded connection to press the shock-absorbing buffer member 10, so that the first connector 2 and the second connector 3 on the airborne missile 1 can be smoothly separated.

[0064] Preferably, the detachment fixing member 15 of the present invention is disposed in the middle of the guide member 12, located between the mop portion and the guide portion 122 on the guide member 12. Preferably, the shock-absorbing buffer member 10 includes one or more sets of connecting flexible cords.

[0065] It should be noted that the selected flexible cable serves not only as a connector but also as a shock absorber and a fixator. The connector function is to link the second connector 3 to the release fixing member 15; this connection is mechanical, not an electrical connection for switching circuits on and off. The shock absorber function is to mitigate and absorb the unavoidable vibrations during the flight of the UAV 14, preventing vibration concentration on the second connector 3. The fixator function is to allow the flexible cable to transfer some of the support force to the second connector 3 under the action of the release fixing member 15, making the connection between the first connector 2 and the airborne missile 1 more secure, while preventing the first connector 2 from detaching and / or the connection between the first connector 2 and the second connector 3 from loosening due to vibrations during the flight of the UAV 14.

[0066] In order to better mitigate vibration and provide a fixing effect, and to ensure that the first connector 2 does not affect the launch of the airborne missile 1 and the smooth sliding out of the second slider 7 after the first connector 2 and the second connector 3 are separated, the length of the shock-absorbing buffer 10 connecting the second connector 3 and the release fixing member 15 is 3mm-5mm, so that the first connector 2 and the second connector 3 will not fall off or loosen due to vibration.

[0067] In summary, the launching device for an unmanned aerial vehicle (UAV)-borne missile of the present invention, through the integrated design of the first slider 6, the first connector, and the second connector 3, eliminates the need for opening holes in the side wall of the airborne missile 1 for the first connector 2, thereby improving the strength of the missile body. By setting the groove 8 through which the first slider 6 and the second slider 7 pass as a structure with a height difference, and using the height difference in conjunction with the release fixing member 15 to achieve the release and separation of the airborne missile 1, the design of the two with different heights ensures that the second slider 7 will not collide with the remaining second connector 3, thus ensuring the safety and reliability of the airborne missile 1. By connecting the second connector 3 to the first connector 2, the second connector 3 floats with the first connector 2. The shock-absorbing buffer 10 connected at a certain distance to the rear end of the second connector 3 prevents the first connector 2 and the second connector 3 from being loosened and detached during the flight of the UAV 14. By attaching a portion of the second connector 3 to the second slider 7 and a portion to the fixed base plate 4, the problem of the first connector 2, which droops and colliding with the subsequent slider, is prevented when the airborne missile 1 is launched. In this invention, the launching device can meet the launching requirements with any connector, which reduces the requirements for connectors, as well as the various requirements for their weight, size, and cost, improving practicality and applicability. Moreover, it eliminates the need for a dedicated release mechanism to assist in release, greatly simplifying the structure and reducing the weight of the release part. This is crucial for the micro-missile structure, especially for the airborne missile 1 and the UAV 14's endurance, ensuring safety while improving the UAV 14's endurance.

[0068] It should be noted that, in this document, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Additionally, the terms "front," "back," "left," "right," "upper," and "lower" in this document refer to the placement shown in the accompanying drawings.

[0069] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions carried out in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A launching device for an unmanned aerial vehicle (UAV) airborne missile, characterized in that, include: An airborne missile is provided with at least two sliders on its top, and a locking and releasing module is provided on one or more of the two sliders for fixing the airborne missile during the flight of the UAV and releasing the constraint during launch. The connector includes a first connector and a second connector. The first connector is fixedly disposed above one or more other sliders of the two sliders on the airborne missile and is electrically connected to the interior of the airborne missile via a wire. The second connector is located on the same slider as the first connector and is plugged into and detached from the first connector. A shock-absorbing buffer is provided on the other side of the second connector. The second connector is electrically connected to the first connector to control the on / off state of the airborne missile. A detachable fixing component is disposed on one side of the connector and fixedly connected to the shock-absorbing buffer component. The detachable fixing component is fixedly disposed on the guide component and is used to detach and separate the first connector and the second connector simultaneously with the launch of the airborne missile. After the first connector and the second connector are detached and separated, the first connector flies with the airborne missile, and the second connector is constrained by the detachable fixing component to prevent the second connector from falling and interfering with the airborne missile and the slider on the airborne missile. The guide component has a groove that matches one or more sliders. The guide component is used to fix the connection with an external UAV, and also carries the airborne missile for guided launch through the cooperation of the slider and the groove and the locking and fixing of the locking and releasing module. The slider includes a first slider and a second slider. The first connector is attached to the first slider. The cross-section of the second slider is a T-shaped structure. The first slider has an integrally formed boss at the top of the T-shaped structure of the second slider. The guide includes a release part and a guide part. Both the release part and the guide part are provided with a groove that matches one or more of the sliders. The shape of the groove of the guide part matches the shape of the first slider. It is provided with a boss hole for the boss and the first plug on the boss to pass through. The shape of the groove of the release part matches the shape of the second slider. The cross-section of the groove of the release part is a T-shaped structure.

2. The launching device for an unmanned aerial vehicle (UAV) airborne missile according to claim 1, characterized in that, The number of sliders includes two.

3. The launching device for an unmanned aerial vehicle (UAV) airborne missile according to any one of claims 1 or 2, characterized in that, The second slider can be locked and released by the locking and releasing module to fix and release the constraints of the airborne missile in the flight direction. The first slider and the second slider are spaced apart on the top of the airborne missile, and the first slider and the second slider are located on the same axis on the top of the airborne missile along the flight direction of the missile.

4. The launching device for an unmanned aerial vehicle (UAV) airborne missile according to claim 3, characterized in that, A circular hole is also provided at the top of the second slider for cooperating with the locking and releasing module.

5. The launching device for an unmanned aerial vehicle (UAV) airborne missile according to claim 4, characterized in that, The detachment part and the guide part are integrally formed and have a linear structure. When the airborne missile is launched, after the first connector and the second connector are separated, the second slider can pass through the groove through which the first slider passes.

6. The launching device for an unmanned aerial vehicle (UAV) airborne missile according to claim 5, characterized in that, The first slider and the second slider have the same height and shape as the T-shaped structure in their cross-sections, which is also the same as the height and shape of the T-shaped structure in the pull-out part and the groove on the guide part for the first slider and the second slider to pass through.

7. The launching device for an unmanned aerial vehicle (UAV) airborne missile according to claim 1, characterized in that, The release fixing component includes a fixed base plate and a fixed top plate. The fixed base plate has a groove in the middle that mates with the first plug and the second plug. There is a rubber pad between the fixed base plate and the fixed top plate. The shock-absorbing buffer connected to the second plug is pressed between the fixed top plate and the rubber pad.

8. The launching device for an unmanned aerial vehicle (UAV) airborne missile according to any one of claims 1 or 7, characterized in that, The shock-absorbing buffer includes one or more sets of connecting flexible wires.

9. The launching device for an unmanned aerial vehicle (UAV) airborne missile according to claim 3, characterized in that, The length of the shock-absorbing buffer component connected to the second connector and the pull-out fixing component is less than the height of the boss provided on the first slider.

10. The launching device for an unmanned aerial vehicle (UAV) airborne missile according to claim 1, characterized in that, The length of the shock-absorbing buffer connecting the second connector and the release fastener includes 3mm-5mm.

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