Multifunctional launching device of unmanned aerial vehicle

Abstract

The invention relates to the technical field of unmanned aerial vehicle launching, and discloses an unmanned aerial vehicle multifunctional launching device which comprises a barrel, a fragile cover, a base, a piston, a fuel gas generator, an electric connector and a tail plug-off, an unmanned aerial vehicle is contained in the barrel and electrically connected with the electric connector through a plug-off cable, and the piston is slidably arranged in the barrel; a cable port is formed in the side part of the cylinder body, and a cable groove is formed outside the cylinder body; one end of the cylinder body is covered with the fragile cover, the base is installed in the other end of the cylinder body, an installation groove is formed in the base, the electric connector is fixed in the installation groove, an installation opening is formed in the groove bottom of the installation groove, the fuel gas generator is detachably connected to the installation opening in a sealed mode, a sealed containing cavity is formed between the fuel gas generator and the piston, and the fuel gas generator is electrically connected with the electric connector. The tail plug-off is detachably installed in a notch of the installation groove and used for being electrically connected with an external carrier or a carrier vehicle, and the electric connector is electrically connected with the tail plug-off. The storage, transportation and launching functions are integrated, and the lightweight design can be achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicle (UAV) launching, and in particular to a multifunctional UAV launching device. Background Art

[0002] With its advantages of low cost and low detectability, small patrol drones can be widely used to perform tasks in various complex environments such as electronic interference, fixed-point destruction, and long-term reconnaissance. They have the advantages of fast take-off, high efficiency and high reliability. Small patrol drones usually adopt ground take-off and electric power systems, which limits their endurance and has certain disadvantages in performing long-distance tasks. In order to overcome the above defects, the current tendency is to adopt an airborne hanging flight delivery method, that is, a large number of small patrol drones can be mounted on large drones, usually using a barrel launch type. With the increase in the demand for clustered and large-scale tasks of patrol drones, due to the limited maximum mounting capacity of carrier aircraft or vehicles, conventional launch devices cannot meet the increasing demand for the maximum number of patrol drones. And when mounting and launching, the drone needs to be taken out of the storage device and then installed in the launch device, which is complicated and cumbersome.

[0003] Therefore, there is an urgent need for a multifunctional launching device for unmanned aerial vehicles to solve the above problems. Summary of the invention

[0004] Based on the above, the purpose of the present invention is to provide a multifunctional launch device for unmanned aerial vehicles, which integrates storage, transportation and launch functions, and can achieve lightweight design, thereby increasing the maximum number of mounts on a single machine.

[0005] To achieve the above object, the present invention adopts the following technical solutions:

[0006] A multifunctional launch device for a drone, comprising a barrel, a fragile cover, a base, a piston, a gas generator, an electrical connector and a tail plug-out, wherein the drone is accommodated in the barrel, the drone is electrically connected to the electrical connector via a plug-out cable, and the piston is slidably disposed in the barrel;

[0007] The side of the cylinder is provided with a cable opening, and the outer wall of the cylinder is provided with a cable groove along the axial direction of the cylinder, and the cable groove is used for laying the plug-in / plug-out cable;

[0008] The fragile cover is arranged at one end of the cylinder, the base is detachably installed in the other end of the cylinder, a mounting groove is provided on the base, the electrical connector is fixed in the mounting groove, a mounting opening is provided at the bottom of the mounting groove, the gas generator is detachably and sealingly connected to the mounting opening, and a sealed cavity is formed between the gas generator and the piston, the gas generator is electrically connected to the electrical connector, the tail plug-in is detachably installed in the notch of the mounting groove, and is used to be electrically connected to an external carrier or vehicle, and the electrical connector is electrically connected to the tail plug-in.

[0009] As a preferred solution of the multifunctional launch device for unmanned aerial vehicles, the cylinder body is an integrated structure, and along the axial direction of the cylinder body, the cylinder body includes a first cylinder body and a second cylinder body, the wall thickness of the first cylinder body is greater than the wall thickness of the second cylinder body, the cable port is opened on the cylinder wall of one end of the second cylinder body close to the first cylinder body, and the cable groove is opened on the outer wall of the first cylinder body;

[0010] The fragile cover is arranged on the end of the second barrel body away from the first barrel body, and the base is detachably installed in the end of the first barrel body away from the second barrel body.

[0011] As a preferred solution for a multifunctional launching device for a drone, it also includes a cable protection cover, which is detachably connected to the first barrel, and a cable dimension-shaped cavity is formed between the cable protection cover and the cable groove, and the plug-in / unplug cable is limited in the cable dimension-shaped cavity.

[0012] As a preferred solution of the multifunctional launching device for unmanned aerial vehicles, it also includes a stopper, which is arranged on the outer wall of the piston, and includes a stopper rod elastically reset along the radial direction of the cylinder, and a stopper groove is provided on the inner wall of the cylinder;

[0013] In the initial state, the end of the stop rod abuts against the inner wall of the cylinder and has a tendency to reset outward along the radial direction of the first cylinder body. As the piston moves, the stop member resets and extends into the stop groove, and prevents the piston from continuing to move under the limiting action of the stop groove.

[0014] As a preferred solution for a multifunctional launching device of a drone, the stop member also includes a stop shell and an elastic member. The stop shell is limitedly connected to the outer wall of the piston. The stop shell has a guide hole. The stop rod is movably inserted into the guide hole along the radial direction of the cylinder. The elastic member is located in the stop shell and is sleeved on the stop rod. Under the elastic force of the elastic member, the stop rod has a tendency to move outward along the radial direction of the cylinder.

[0015] As a preferred solution for a multifunctional launching device for a drone, an outer wall of the piston is formed with an inwardly concave limiting groove, and the stop shell is located in the limiting groove.

[0016] As a preferred solution of the multifunctional launching device for unmanned aerial vehicles, a first annular sealing groove is provided on the outer circumference of the piston, a first sealing ring is arranged in the first annular sealing groove, and the first sealing ring is in movable sealing contact with the inner wall of the cylinder; and / or

[0017] A second annular sealing groove is formed on the outer periphery of the base, a second sealing ring is arranged in the second annular sealing groove, and the second sealing ring is in movable sealing contact with the inner wall of the cylinder.

[0018] As a preferred solution of the multifunctional launching device for unmanned aerial vehicles, it also includes a locking pin, which is penetrated through the wall of the cylinder, and one end of the locking pin extends into the cylinder and abuts against a limiting groove on the unmanned aerial vehicle.

[0019] As a preferred solution for a multifunctional launching device of a drone, a weakening groove is provided on the inner side of the fragile cover, and the shape of the weakening groove is adapted to the end shape of the drone.

[0020] As a preferred solution for the multifunctional launching device of a UAV, it also includes a mounting flange, which is arranged on the outer periphery of the first barrel and is used for fixing to an external carrier aircraft or vehicle.

[0021] The beneficial effects of the present invention are:

[0022] The present invention provides a multifunctional launch device for unmanned aerial vehicles. By laying the plug-in / plug-out cable in the cable groove outside the cylinder, the external routing of the plug-in / plug-out cable is realized, the space inside the cylinder is saved, and the diameter of the cylinder can be designed to be small in size, so as to realize the lightweight design of the cylinder, thereby increasing the maximum number of unmanned aerial vehicles mounted on a single carrier or a single vehicle, and realizing clustered and large-scale task execution; and the setting of the cable groove can provide a limiting effect for the plug-in / plug-out cable, and can also prevent the plug-in / plug-out cable from protruding relative to the outer wall of the first cylinder body, thereby ensuring the appearance and integrity. At the same time, the multifunctional launch device for unmanned aerial vehicles can be used as a storage device for unmanned aerial vehicles. During storage, the fragile cover, base, and tail plug-in structures provide good protection for the internal space of the cylinder; and when it is necessary to transport and launch, the cylinder can be directly loaded on the carrier or vehicle, and electrically connected to the carrier or vehicle through the tail plug-in, which is convenient and fast, and saves loading time. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments of the present invention. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the contents of the embodiments of the present invention and these drawings without paying any creative work.

[0024] Figure 1 It is a structural schematic diagram of a multifunctional launching device for a UAV provided by an embodiment of the present invention;

[0025] Figure 2 It is a schematic diagram of the internal structure of the multifunctional launching device for a UAV provided by an embodiment of the present invention;

[0026] Figure 3 It is a partial structural cross-sectional view of the multifunctional launching device for unmanned aerial vehicles provided by an embodiment of the present invention.

[0027] In the figure:

[0028] 1. Cylinder; 11. First cylinder body; 12. Second cylinder body; 2. Fragile cover; 3. Base; 4. Piston; 5. Gas generator; 6. Electrical connector; 7. Tail plug-in; 8. Cable protection cover; 9. Stopper; 91. Stopper rod; 92. Stopper housing; 93. Elastic member; 10. First sealing ring; 20. Second sealing ring; 30. Locking pin; 40. Mounting flange; 50. Limit pin; 60. Protection cover;

[0029] 100. Mounting groove; 200. Sealed cavity. DETAILED DESCRIPTION

[0030] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are only used to explain the present invention, rather than to limit the present invention. It should also be noted that, for ease of description, only parts related to the present invention, rather than all structures, are shown in the accompanying drawings.

[0031] In the description of the present invention, unless otherwise clearly specified and limited, the terms "connected", "connected", and "fixed" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0032] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0033] In the description of the present embodiment, the terms "upper", "lower", "left", "right" and other directions or positional relationships are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of description and simplification of operation, rather than indicating or implying that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be understood as a limitation of the present invention. In the description of the present invention, unless otherwise specified, the meaning of "plurality" is two or more. In addition, the terms "first" and "second" are only used to distinguish in the description and have no special meaning.

[0034] like Figures 1 to 3As shown, this embodiment provides a multifunctional launch device for unmanned aerial vehicles, which includes a cylinder 1, a fragile cover 2, a base 3, a piston 4, a gas generator 5, an electrical connector 6 and a tail plug-out 7. The unmanned aerial vehicle is accommodated in the cylinder 1, and the unmanned aerial vehicle is electrically connected to the electrical connector 6 through a plug-out cable. The piston 4 is slidably arranged in the cylinder 1; a cable opening is opened on the side of the cylinder 1, and a cable groove is opened on the outer wall of the cylinder 1 along the axial direction of the cylinder 1, and the cable groove is used to lay the plug-out cable; the fragile cover 2 is covered on the cylinder 1, the base 3 is detachably mounted in the other end of the cylinder 1, a mounting groove 100 is provided on the base 3, the electrical connector 6 is fixed in the mounting groove 100, a mounting port is provided at the bottom of the mounting groove 100, the gas generator 5 is detachably sealed and connected to the mounting port, and a sealed chamber 200 is formed between the gas generator 5 and the piston 4, the gas generator 5 is electrically connected to the electrical connector 6, the tail plug-out 7 is detachably mounted in the slot of the mounting groove 100, and is used to be electrically connected to an external carrier or vehicle, and the electrical connector 6 is electrically connected to the tail plug-out 7. By laying the plug-out cable in the cable groove outside the cylinder 1, the external routing of the plug-out cable is realized, the space inside the cylinder is saved, and the diameter of the cylinder 1 can be designed to be small in size, and the lightweight design of the cylinder 1 is realized, thereby increasing the maximum number of drones mounted on a single carrier or a single vehicle, and realizing clustered and large-scale task execution; and the setting of the cable groove can provide a limiting effect for the plug-out cable, and can also prevent the plug-out cable from protruding relative to the outer wall of the first cylinder body 11, ensuring the appearance and integrity. At the same time, the multifunctional launching device for unmanned aerial vehicles can be used as a storage device for unmanned aerial vehicles. During storage, structures such as the fragile cover 2, the base 3 and the tail plug 7 provide good protection for the internal space of the cylinder 1. When transportation and launching are required, the cylinder 1 can be directly loaded on a carrier aircraft or a vehicle, and electrically connected to the carrier aircraft or the vehicle through the tail plug 7, which is convenient and fast and saves loading time.

[0035] Specifically, the piston 4 is open at one end facing the gas generator 5, and one end of the gas generator 5 is sealed at the open end of the piston 4, forming a sealed cavity 200 with the piston 4. The gas generator 5 is used to generate gas in the sealed cavity 200 to push the piston 4 to move, thereby pushing the drone to break through the fragile cover 2 and exit the cylinder; and the above structure is conducive to saving the axial space in the cylinder 1, that is, reducing the invalid occupied space of the piston 4, which is conducive to further lightweight design of the cylinder 1. Among them, the fragile cover 2 not only plays a protective and dustproof role, but also prevents foreign objects from entering the cylinder 1 and causing influence or damage to the drone, and the drone can break through the fragile cover 2 under the action of thrust to achieve smooth exit. The multifunctional drone launch device provided in this embodiment can store the drone in the cylinder 1 for long-term storage when there is no mission, and has a long storage capacity of not less than 10 years; when the drone needs to be transferred, the drone can be stored in the cylinder 1 for integrated transportation; and it can also be loaded on the carrier through the cylinder 1 to launch the drone. That is, the multifunctional launch device for unmanned aerial vehicles integrates the functions of storage, transportation and launching unmanned aerial vehicles, and has good practicability. It should be noted that the gas generator 5 is a relatively mature prior art, and therefore, it will not be described in detail here.

[0036] Preferably, a weakening groove is provided on the inner side of the fragile cover 2, that is, on the side of the fragile cover 2 facing the inside of the barrel 1, and the shape of the weakening groove is adapted to the end shape of the drone. The structural strength at the weakening groove is relatively low, so that the drone can smoothly exit the barrel. Exemplarily, the fragile cover 2 is formed of polyurethane foam and bonded to the barrel 1. The thickness of the fragile cover 2 is 0.001m-0.004m, the diameter is 0.048m, and the area of ​​the shear surface at the weakening groove is less than 0.000192m2, which has reliable crushing performance during the launch process.

[0037] In this embodiment, the base 3 and the side wall of the cylinder 1 are fixedly connected by bolts or positioning pins to ensure that the position of the base 3 is fixed, to prevent the base 3 from slipping in the cylinder 1, and to improve the structural strength and stability of the multifunctional launch device of the UAV. For example, a plurality of bolts or positioning pins are arranged at intervals along the outer periphery of one end of the cylinder 1, and each bolt or positioning pin is connected to the side wall of the cylinder 1 and the peripheral wall of the base 3.

[0038] Preferably, the base 3 is sealingly sleeved in the cylinder body 1. For example, a second annular sealing groove is provided on the outer periphery of the base 3, and a second sealing ring 20 is provided in the second annular sealing groove. When the base 3 is sleeved into the cylinder body 1, the second sealing ring 20 is sealingly abutted against the inner wall of the cylinder body 1 to ensure the sealing of the sealing cavity 200 and the reliability of the position fixation of the base 3.

[0039] Preferably, a limit pin 50 is provided on the outer side of the base 3 to be limit-connected with a limit slot on the carrier aircraft or vehicle, so as to further improve the loading stability of the multifunctional launching device of the unmanned aerial vehicle.

[0040] Further, the cylinder 1 is an integrated structure, and along the axial direction of the cylinder 1, the cylinder 1 includes a first cylinder body 11 and a second cylinder body 12, the wall thickness of the first cylinder body 11 is greater than the wall thickness of the second cylinder body 12, the second cylinder body 12 is close to the first cylinder body 11 The end of the cylinder wall is provided with the above-mentioned cable port, and the outer wall of the first cylinder body 11 is provided with the above-mentioned cable groove; the fragile cover 2 is provided on the port of the second cylinder body 12 away from the first cylinder body 11, and the base 3 is provided at the end of the first cylinder body 11 away from the second cylinder body 12. Exemplarily, the inner diameter of the first cylinder body 11 is, the inner diameter of the second cylinder body 12 is, the overall envelope size is not greater than, and the total weight is not greater than 1.5kg. When launching the drone, the gas generator 5 is powered on to generate gas, and the gas pushes the piston 4 in the sealed cavity 200 to move toward the direction of the second cylinder body 12, thereby pushing the drone to break through the fragile cover 2 and exit the cylinder. The wall thickness of the first barrel 11 is greater than that of the second barrel 12, that is, the wall thickness of the first barrel 11 is thickened, so that the first barrel 11 with the cable groove has a higher structural strength, ensuring the overall structural strength while ensuring the total weight of the barrel 1 is light. That is, the structure of the barrel 1 fully utilizes the effective space of the barrel 1 and reduces the dead weight of the structure on the basis of ensuring the structural strength and the coordination and matching of the barrel and the machine.

[0041] Specifically, a mounting flange 40 is provided on the outer periphery of the first barrel 11, and the mounting flange 40 is used to be fixed to an external carrier or vehicle so as to fix the multifunctional launch device of the UAV on the carrier or vehicle. For example, the mounting flange 40 is connected to the carrier or vehicle by fastening bolts.

[0042] Preferably, a protective cover 60 is provided at the cable port, and the cable port is exposed or closed by opening and closing the protective cover 60, so as to facilitate the wiring of the cable, protect the cable, and prevent foreign objects from entering the barrel 1 through the cable port. Optionally, the protective cover 60 is detachably connected to the barrel 1 through a structure such as a bolt or a latch.

[0043] Preferably, the multifunctional launching device of the unmanned aerial vehicle further comprises a cable protection cover 8, which is detachably connected to the first barrel 11, and a cable dimension-shaped cavity is formed between the cable protection cover 8 and the cable groove, and the plug-in cable is limited in the cable dimension-shaped cavity. After laying the plug-in cable, the cable protection cover 8 is covered and fixed on the first barrel 11 to protect the plug-in cable and maintain the position and shape of the plug-in cable, so as to avoid the plug-in cable from being separated from the cable groove and interfering with foreign objects, resulting in de-line, etc. Optionally, the cable protection cover 8 is detachably connected to the barrel 1 by structures such as bolts or latches. For example, the cable groove extends along the axial direction of the first barrel 11, and along the axial direction of the first barrel 11, a plurality of screws are connected at intervals to fix the cable protection cover 8 on the first barrel 11.

[0044] More specifically, the multifunctional launch device for the unmanned aerial vehicle further comprises a locking pin 30, the locking pin 30 being arranged on the cylinder wall of the first cylinder body 11, and one end of the locking pin 30 extending into the first cylinder body 11 and abutting against the limiting groove on the unmanned aerial vehicle. Wherein, the locking pin 30 can be optionally but not limited to a top screw or a cylindrical pin. By limiting the unmanned aerial vehicle with the locking pin 30, the position of the unmanned aerial vehicle in the cylinder body 1 can be relatively fixed and not prone to sliding. It is understandable that the locking pin 30 can be one or more, for example, two, three, four or more are arranged at intervals along the circumference of the first cylinder body 11.

[0045] Preferably, the side wall of the first barrel body 11 at the connection between the base 3 and the first barrel body 11, the connection between the cable protection cover 8 and the first barrel body 11, and the location where the locking pin 30 is set are all thickened to improve the connection stability and the structural strength of the first barrel body 11. For example, along the axial direction of the first barrel body 11, a first thickened boss is respectively provided on both sides of the cable groove, and the bolts connecting the cable protection cover 8 are connected to the first thickened boss; a second thickened boss is also provided on the periphery of one end of the first barrel body 11 away from the second barrel body 12, and the bolts connecting the base 3 and the first barrel body 11 are connected to the second thickened boss; a third thickened boss is also provided along the periphery of the first barrel body 11 relative to the location of the locking pin 30, and the locking pin 30 is connected to the third thickened boss.

[0046] Furthermore, the multifunctional launch device of the unmanned aerial vehicle further comprises a stopper 9, which is arranged on the outer wall of the piston 4, and comprises a stopper rod 91 which is elastically reset along the radial direction of the first barrel 11, and a stopper groove is provided on the inner wall of the first barrel 11; in the initial state, the end of the stopper rod 91 abuts against the inner wall of the first barrel 11, and has a tendency to reset outward along the radial direction of the first barrel 11, and as the piston 4 moves, the stopper 9 resets and extends into the stopper groove, and prevents the piston 4 from continuing to move under the limiting action of the stopper groove. By limiting the stopper rod 91 in the stopper groove, the piston 4 is prevented from continuing to move in the barrel 1, and the piston 4 can be prevented from rushing out of the barrel 1 under a large impact force.

[0047] Specifically, the stopper 9 also includes a stopper housing 92 and an elastic member 93, the stopper housing 92 is limitedly connected to the outer wall of the piston 4, the stopper housing 92 is provided with a guide hole, the stopper rod 91 is movably arranged in the guide hole along the radial direction of the first barrel 11, the elastic member 93 is located in the stopper housing 92, and is sleeved on the stopper rod 91, under the elastic force of the elastic member 93, the stopper rod 91 has a tendency to move outward along the radial direction of the first barrel 11. The stopper rod 91 is guided by the guide hole, so that the moving direction of the stopper rod 91 is stable when resetting, so that it can be ensured that the stopper rod 91 can be smoothly inserted into the stopper groove under the action of the elastic member 93 when encountering the stopper groove, and the position stability of the stopper rod 91 is better, which can better prevent the piston 4 from continuing to move. Wherein, the elastic member 93 can be optionally but not limited to a compression spring or a tension spring, and the compression spring is sleeved on the stopper rod 91 and abuts against the two opposite inner walls of the stopper housing 92.

[0048] In this embodiment, the stopper rod 91 includes a first section and a second section, the first section is located in the stopper housing 92, the second section moves through the guide hole, the outer diameter of the first section is larger than the outer diameter of the second section, and is adapted to the internal space size of the stopper housing 92 to ensure the working stability of the stopper rod 91. Preferably, a groove is provided at one end of the first section away from the second section, a guide column is provided in the groove, and a spring is sleeved on the guide column, which provides sufficient elastic reset force for the stopper rod 91 while ensuring the movement stability of the stopper rod 91, so that the piston 4 can smoothly stop at the stopper groove.

[0049] Preferably, the outer wall of the piston 4 is formed with an inwardly concave limiting groove, and the stopper housing 92 is located in the limiting groove, which not only provides installation space for the stopper 9, but also plays a limiting role, so that the position of the stopper 9 on the piston 4 is reliably fixed. At the same time, the stopper 9 can be completely accommodated in the limiting groove, so that the gap between the outer periphery of the piston 4 and the inner wall of the first barrel 11 is small, ensuring the stability of the moving direction of the piston 4, thereby ensuring the firing effect.

[0050] Preferably, a first annular sealing groove is provided on the outer circumference of the piston 4, a first sealing ring 10 is provided in the first annular sealing groove, and the first sealing ring 10 is in movable sealing contact with the inner wall of the first barrel 11. The provision of the first sealing ring 10 can prevent the thrust gas generated by the gas generator 5 from overflowing from between the piston 4 and the first barrel 11, and ensure that the gas generated by the gas generator 5 has sufficient pressure within the effective stroke, so as to reliably complete the launch and achieve the required launch time and exit speed.

[0051] In the launch preparation stage, the required ignition current can be directly controlled by the control system on the carrier aircraft or vehicle to trigger, and the gas generator 5 ignites the main charge through the ignition powder to generate high-temperature and high-pressure gas in the closed cavity. When the gas pressure in the piston 4 reaches 1MPa, the locking pin 30 is cut off to push the piston 4 to move. The piston 4 further pushes the UAV to move out of the cylinder 1, and the head of the UAV hits the fragile cover 2, and the folding wings and tail rudder are unfolded in turn, completing the launch and autonomously starting to perform the mission.

[0052] Note that the above are only preferred embodiments of the present invention and the technical principles used. Those skilled in the art will understand that the present invention is not limited to the specific embodiments described herein, and that various obvious changes, readjustments and substitutions can be made by those skilled in the art without departing from the scope of protection of the present invention. Therefore, although the present invention has been described in more detail through the above embodiments, the present invention is not limited to the above embodiments, and may include more other equivalent embodiments without departing from the concept of the present invention, and the scope of the present invention is determined by the scope of the appended claims.

Claims

1. A multifunctional launching device for unmanned aerial vehicles, characterized in that: It includes a cylinder, a fragile cover, a base, a piston, a gas generator, an electrical connector and a tail plug-out, wherein a drone is contained in the cylinder, the drone is electrically connected to the electrical connector via a plug-out cable, and the piston is slidably disposed in the cylinder; The side of the cylinder is provided with a cable opening, and the outer wall of the cylinder is provided with a cable groove along the axial direction of the cylinder, and the cable groove is used for laying the plug-in / plug-out cable; The fragile cover is arranged at one end of the cylinder, the base is detachably installed in the other end of the cylinder, a mounting groove is provided on the base, the electrical connector is fixed in the mounting groove, a mounting opening is provided at the bottom of the mounting groove, the gas generator is detachably and sealingly connected to the mounting opening, and a sealed cavity is formed between the gas generator and the piston, the gas generator is electrically connected to the electrical connector, the tail plug-in is detachably installed in the notch of the mounting groove, and is used to be electrically connected to an external carrier or vehicle, and the electrical connector is electrically connected to the tail plug-in.

2. The multifunctional launch device for unmanned aerial vehicles according to claim 1, characterized in that: The cylinder body is an integrated structure. Along the axial direction of the cylinder body, the cylinder body includes a first cylinder body and a second cylinder body. The wall thickness of the first cylinder body is greater than the wall thickness of the second cylinder body. The cable port is provided on the cylinder wall of one end of the second cylinder body close to the first cylinder body, and the cable groove is provided on the outer wall of the first cylinder body. The fragile cover is arranged on the end of the second barrel body away from the first barrel body, and the base is detachably installed in the end of the first barrel body away from the second barrel body.

3. The multifunctional launch device for unmanned aerial vehicles according to claim 2, characterized in that: It also includes a cable protection cover, which is detachably connected to the first barrel, and a cable dimension-shaped cavity is formed between the cable protection cover and the cable groove, and the plug-in / unplug cable is limited in the cable dimension-shaped cavity.

4. The multifunctional launch device for unmanned aerial vehicles according to claim 1, characterized in that: It also includes a stopper, which is arranged on the outer wall of the piston, and includes a stopper rod which is elastically reset along the radial direction of the cylinder, and a stopper groove is provided on the inner wall of the cylinder; In the initial state, the end of the stop rod abuts against the inner wall of the cylinder and has a tendency to reset outward along the radial direction of the first cylinder body. As the piston moves, the stop member resets and extends into the stop groove, and prevents the piston from continuing to move under the limiting action of the stop groove.

5. The multifunctional launch device for unmanned aerial vehicles according to claim 4, characterized in that: The stop member also includes a stop shell and an elastic member. The stop shell is limitedly connected to the outer wall of the piston. The stop shell has a guide hole. The stop rod is movably inserted into the guide hole along the radial direction of the cylinder. The elastic member is located in the stop shell and is sleeved on the stop rod. Under the elastic force of the elastic member, the stop rod has a tendency to move outward along the radial direction of the cylinder.

6. The multifunctional launch device for unmanned aerial vehicles according to claim 5, characterized in that: The outer wall of the piston is formed with an inwardly concave limiting groove, and the stop shell is located in the limiting groove.

7. The multifunctional launch device for unmanned aerial vehicles according to claim 1, characterized in that: A first annular sealing groove is formed on the outer circumference of the piston, a first sealing ring is arranged in the first annular sealing groove, and the first sealing ring is in movable sealing contact with the inner wall of the cylinder; and / or A second annular sealing groove is formed on the outer periphery of the base, a second sealing ring is arranged in the second annular sealing groove, and the second sealing ring is in movable sealing contact with the inner wall of the cylinder.

8. The multifunctional launch device for unmanned aerial vehicles according to claim 1, characterized in that: It also includes a locking pin, which is penetrated through the cylinder wall of the cylinder, and one end of the locking pin extends into the cylinder to abut against a limiting groove on the drone.

9. The multifunctional launch device for unmanned aerial vehicles according to any one of claims 1 to 8, characterized in that: A weakening groove is arranged on the inner side of the fragile cover, and the shape of the weakening groove is adapted to the end shape of the drone.

10. The multifunctional launch device for unmanned aerial vehicles according to any one of claims 1 to 8, characterized in that: It also includes a mounting flange, which is arranged on the outer periphery of the first barrel and is used for fixing to an external carrier aircraft or vehicle.

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