A gun-launched coaxial rotor UAV airborne fireworks launching system

Abstract

The application discloses a kind of artillery launch coaxial rotor unmanned aerial vehicle airborne fireworks launching system, including artillery projectile platform, unmanned aerial vehicle and folding guided fireworks launching system;Folding guided fireworks launching system and unmanned aerial vehicle constitute integral system, folding is placed in shell cabin, and after being launched to a certain height in the air by air cannon, unmanned aerial vehicle and folding guided fireworks launching system are released by completing separation and dehulling, the launch timing and direction of fireworks are changed by remote control of remote control rudder, various different complex fireworks patterns are formed, and large-scale fireworks show performance is completed.Compared with traditional fireworks unmanned aerial vehicle, the application can better guarantee the flight stability of unmanned aerial vehicle during flight, and improve the safety of fireworks unmanned aerial vehicle performance.

Description

Technical Field

[0001] This invention relates to the field of airborne launch technology for fireworks drones, and in particular to an airborne fireworks launch system for a coaxial rotor drone launched by a cannon. Background Technology

[0002] With the continuous development of fireworks drone launch technology, the angle of fireworks launchers is not easy to adjust, and the fireworks patterns are not rich enough.

[0003] To address the issues of difficult angle adjustment and limited variety of firework patterns on fireworks launchers, patent application number 202123149607.0 discloses an angle-adjustable fireworks launcher. Through a fixed frame, motor, threaded rod, connecting block, support rod, and support assembly, the base can be stably adjusted in angle. Patent application number 201922292688.6 discloses an adjustable fireworks launcher and a bouquet-shaped launcher. It uses a telescopic adjustment rod to adjust the opening angle of the upper and lower fixed frames, thereby controlling the launch angle of the cannon disc containing the fireworks, meeting the needs of different launch positions and heights. Patent application number 202322702728.6 discloses a firework with adjustable launch direction. A limiting spring and partition are used to install the firework body, and an anti-slip pad limits the firework body. A motor drives a crank rod to achieve adjustable firework direction. Patent application number 202221037532.9 discloses a fireworks launcher with a precisely adjustable angle. Through the setting of slide rails, fixed side plates, launching components and fixing components, the fireworks launcher can be adjusted in an easy and precise manner.

[0004] The launch system and flight control system described above control the rotation of the drone together. However, since the launch system only has one motor, it can only control one pitch. The drone controls the launch angle and orientation. It is impossible to coordinate the two systems to achieve arbitrary changes in the position and orientation of the upward-facing drone in three-dimensional space. Furthermore, existing launch devices are designed based on fixed patterns and cannot be changed according to new patterns. It is impossible to achieve multiple different firework patterns with one launch device, and it is not possible to mass-produce them. It is also impossible to form highly controllable firework patterns. The firework patterns are monotonous and cannot make up for the shortcomings of traditional firework shows that cannot control firework patterns in real time. Summary of the Invention

[0005] This invention addresses the problems and shortcomings of existing airborne fireworks launch technology using drones, aiming to provide a cannon-launched coaxial rotor drone-borne fireworks launch system. The foldable, guideable fireworks launch system of this invention forms an integrated system with the drone, folded and housed in a magazine. After being launched to a certain altitude by an air cannon, it separates and releases the drone and the foldable, guideable fireworks launch system. By remotely controlling a servo motor, the launch timing and direction of the fireworks can be changed, creating various complex fireworks patterns to complete a large-scale fireworks show.

[0006] The technical solution to achieve the purpose of this invention is: a gun-launched coaxial rotor UAV airborne fireworks launching system, comprising a gun-launched missile platform, a UAV, and a foldable guideable fireworks launching system;

[0007] The gun-launched missile platform includes a missile compartment, a missile body, a spiral fin, and a valve mechanism. In the ready-to-launch state, four spiral fins are evenly spaced around the tail of the missile body. After the projectile is launched, the four spiral fins open simultaneously to ensure stability during flight.

[0008] The drone and the foldable guided fireworks launch system are fixed as a whole. The foldable guided fireworks launch system consists of an airborne fireworks launcher system and a launch control head system. The airborne fireworks launcher system can be folded clockwise and placed in the bomb bay. The launch control head system is installed on the airborne fireworks launcher system and includes a fixed base, control servo motor, hose, and swing control head. The deflection of the swing control head is controlled by remote control servo motor, thereby controlling the direction of the fireworks.

[0009] Compared with the prior art, the significant advantages of the present invention are:

[0010] (1) When the overall system is in flight, the wing in the cannon-launched missile platform of the present invention will be rotated off-axis by the force of the torsion spring. After reaching the predetermined rotation angle, it will be pushed backward by the ejection spring and locked into the limiting groove to achieve the limiting of the flight process. Compared with the traditional fireworks drone, this technology can better ensure the flight stability of the drone during the flight process and improve the safety of the fireworks drone performance.

[0011] (2) The airborne fireworks launcher system in the foldable guided fireworks launcher system of the present invention contains a fireworks launch tube that can be filled with a large amount of fireworks propellant and fireworks beads, ensuring that the amount of fireworks carried by a single fireworks drone reaches the amount of propellant required for fireworks performance; in addition, the structural design of the airborne fireworks launcher system can also protect the safety of the drone during flight and assist the drone in landing.

[0012] (3) The swing control head in the launch control head system of the foldable guideable fireworks launch system of the present invention can be remotely controlled by a remote control motor to control the deflection of the fireworks, thereby realizing the control of the fireworks launch direction. This allows a small number of drones to create a variety of fireworks patterns. Compared with traditional fireworks and other fireworks drones, the present invention can more accurately control the launch direction of the fireworks powder beads in real time, forming a richer variety of fireworks patterns. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the missile-borne structure ready for launch in the system of this invention.

[0014] Figure 2 This is a schematic diagram of the structure of the system of the present invention during missile flight.

[0015] Figure 3 This is a schematic diagram of a partial structure of the system of the present invention during missile-borne flight.

[0016] Figure 4 This is an explosion diagram of the projectile separation mechanism of the system of the present invention.

[0017] Figure 5 This is a schematic diagram of the projectile separation mechanism of the system of the present invention.

[0018] Figure 6 This is a three-dimensional structural diagram of the folded state of the UAV and airborne fireworks launching system of the present invention.

[0019] Figure 6-A This is a partial structural diagram of the folded state of the UAV and airborne fireworks launching system of the present invention.

[0020] Figure 7 This is a schematic diagram of the locking mechanism of the UAV and airborne fireworks launching system of the present invention.

[0021] Figure 8 This is a three-dimensional structural diagram of the UAV and airborne fireworks launching system of the present invention in the deployed state.

[0022] Figure 9 This is a three-dimensional structural diagram of the launch control head of the UAV and airborne fireworks launching system of the present invention.

[0023] The components are as follows: 1-Bomb bay, 2-Bomb body; 21-Separation part, 22-Bomb body main body, 3-Rolling wing, 4-Valve mechanism, 5-UAV, 6-Airborne fireworks launcher system; 61-Launch control head system; 61-1-Fixed base, 61-2-Control servo, 61-3-Hose, 61-4-Limit pin, 61-5-Swing control head, 62-Airbag, 63-Firework launch tube, 64-Folding moving rod, 65-Folding stationary rod, 66-Pin, 67-Locking mechanism, 67-1-Limit button, 67-2-Limit spring, 7-Air chamber, 8-Pin, 9-Remote ignition device, 10-Electric ignition wire, 11-Ejection spring, 12-Torsion spring. Detailed Implementation

[0024] Combination Figures 1-9 This invention discloses a gun-launched coaxial rotor unmanned aerial vehicle (UAV) airborne fireworks launching system. The system includes a gun-launched missile platform, a UAV, and a foldable, guideable fireworks launching system. The gun-launched missile platform consists of, in sequence from the warhead, a missile compartment, a missile body, a spiral wing, a gas chamber, and a valve mechanism.

[0025] Furthermore, a separation mechanism is provided at the connection between the projectile body and the missile bay. The external structure of the separation mechanism is part of the projectile body structure and connects to the exposed lower half of the projectile body. Its shape is a truncated cone with a narrower center. The truncated cone has a chamfer that fits flush with the chamfered plane of the projectile body's lower opening. In addition to the above structure, the separation mechanism also includes a remote ignition device, an electric ignition wire, and a pin. The remote ignition device is embedded in a hole along the projectile's axis within the separation mechanism, and the electric ignition wire is connected to the remote ignition device, with the other end positioned at the bottom of the hole.

[0026] Furthermore, the separation device has eight through holes perpendicular to the projectile's axis at its bottom. These holes are arranged in a radial pattern on the same plane, and their radius increases to the same size as the pins where they exit the separation device surface. Correspondingly, there are eight equidistant through holes on the same plane at the lower opening of the missile compartment. Eight pins pass through the corresponding through holes to restrain and lock the missile compartment and the projectile body.

[0027] Furthermore, the projectile's tail section is equipped with a coiled wing, a gas chamber, and a valve mechanism. The coiled wing is evenly spaced around the tail section. It is installed in the tail section via a pre-drilled annular groove and is movably connected to a pre-drilled hole at the rear of the projectile by a push-out spring and a torsion spring. When the coiled wing unfolds under the action of the torsion spring, the push-out spring will push the coiled wing into a limiting groove at a predetermined position, thus fixing its position. The gas chamber is a hollow section inside the projectile, used to store high-pressure gas for propulsion before launch. The valve mechanism connects to the high-pressure gas cylinder inside the launching device and plays a role in launch control.

[0028] Furthermore, the foldable guideable fireworks launching system comprises a launch control head system and an airborne fireworks launcher system. The airborne fireworks launcher system includes an airbag, four fireworks launch tubes, twelve folding moving rods, three folding stationary rods, pins, and a locking mechanism. The launch control head system includes a fixed base, control servos, hoses, limit pins, and a swing control head.

[0029] Furthermore, each fireworks launch tube features a one-way opening, with the opening at the top and no opening at the bottom, which is fitted with a frustum-shaped base. Inside the launch tube is a miniature electric ignition device. When the system reaches the predetermined performance conditions, the ignition device receives a ground signal and ignites the pre-embedded gunpowder and fireworks beads inside the launch tube, thus igniting and launching the fireworks. A launch control head system is connected to the launch tube opening.

[0030] Furthermore, each fireworks launch tube has a folding moving rod rigidly connected to it at three points: top, middle, and bottom. From top to bottom, the folding moving rods are connected to three folding stationary rods in a hinged manner. The folding moving rods can rotate the fireworks launch tube around the hinges, thereby realizing the folding and unfolding of the overall structure.

[0031] Furthermore, the aforementioned four fireworks launch tubes, twelve folding moving rods, and three folding stationary rods together form a cage-like structure that encloses the drone. The middle-layer folding stationary rods extend their four arms through pre-drilled, equidistant holes in the drone's fuselage, thus fixing the overall cage-like structure system relative to the drone.

[0032] Furthermore, the aforementioned folding moving rod is equipped with a locking mechanism. The locking mechanism consists of a limit button and a limit spring. Corresponding holes are provided on the folding stationary rod to cooperate with the limit button in fixing the relative position of the cage structure when it is unfolded. A protruding limit block is embedded within the limit button to ensure that the limit button does not exceed its normal travel.

[0033] The airborne fireworks launcher can carry and launch fireworks powder balls, and can also protect the drone and assist the drone in landing.

[0034] Furthermore, the drone and the foldable guided fireworks launching system form an integrated system, which is folded and placed inside the missile bay of the artillery-launched missile platform, keeping it in a ready-to-launch state.

[0035] Furthermore, the airbag is equipped with four annular fixing straps, which are embedded and fixed in the grooves in the middle of the four fireworks launch tubes. Before the shell ejection, the airbag is in a gas-free state, appearing as a deflated ring surrounding the foldable guided fireworks launch system. The airbag contains a small amount of gunpowder and a corresponding ignition device. After the shell ejection platform completes the ejection, the UAV and the foldable guided fireworks launch system assembly, influenced by gravity, detach downwards through the lower opening of the missile compartment. Once the assembly is completely detached, the airbag's internal ignition device ignites the gunpowder. The expanding gas generated by the combustion of the gunpowder rapidly inflates the airbag, causing it to expand and pull the four fireworks launch tubes outwards. During the rapid transition of the airbag from a deflated, folded state to a fully inflated state, the four fireworks launch tubes are pulled to the predetermined deployment position and secured by the locking structure on the aforementioned folding lever. Thus, the UAV and the foldable guided fireworks launch system are deployed in mid-air.

[0036] Furthermore, the launch control head system consists of a fixed base, a control servo motor, a flexible hose, and a swing control head. The system is fixed to the nozzle of the fireworks launch tube via a nested fixed base. The swing control head is hinged to the fixed base via a limiting pin and the control servo motor, and is controlled by the control servo motor to achieve a specified swing angle.

[0037] Furthermore, the aforementioned mounting base has a pre-drilled coaxial through hole, the lower half of which has a radius that matches the outer diameter of the fireworks launcher tube for nesting and fixation. The upper half of the through hole is slightly narrower, used to fix the relative position of the fireworks launcher tube and ensure that its radius matches that of the flexible hose.

[0038] Furthermore, the swing control head has a pre-drilled coaxial through hole with the same outer diameter as the flexible hose. Both ends of the flexible hose are fixed to the mounting base and the swing control head, respectively. When the swing control head swings, it bends the flexible hose, changing the firework launch path and enabling controllable firework launch. The flexible hose is made of a high-temperature resistant material to ensure that the high temperatures generated by multiple firework launches do not affect the normal operation of the hose and other components.

[0039] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0040] Example

[0041] The present invention will now be further described in conjunction with the accompanying drawings and specific embodiments in the context of missile-borne launch. (Refer to...) Figure 1-9As shown, this embodiment of the invention provides an airborne fireworks launching system for a cannon-launched coaxial rotor UAV. The system includes a cannon-launched missile platform, a UAV 5, and a foldable, guideable fireworks launching system. The overall system consisting of the UAV 5 and the foldable, guideable fireworks launching system is as follows: Figure 1 As shown, it is folded and placed inside the missile bay 1 of the gun-launched missile platform, keeping it in a ready-to-launch state.

[0042] In this embodiment, reference Figures 1-5 The artillery-launched missile platform mainly consists of a missile compartment 1, a missile body 2, a curved fin 3, an air chamber 7, and a mechanical core 4, starting from the missile head. The inner contour of the missile compartment 1 matches the outer contour of the separated portion 21 of the missile body 2. At corresponding locations on both portions, there are eight equally spaced circular holes of equal diameter, which are connected and fixed to the missile compartment 1 and the missile body 22 by eight pins 8. Figure 3 As shown, the gas chamber 7 is a hollow part inside the projectile body 2, used to store high-pressure gas as propulsion power before launch.

[0043] In this embodiment, reference Figure 3 The coiled wing 3 is movably connected to the pre-set mounting hole at the rear of the projectile body 2 in cooperation with the ejector spring 11 and the torsion spring 12. At the root of each coiled wing 3, a thin rod extends a certain distance along the projectile's axial direction. The ejector spring 11 and the torsion spring 12 are coaxially nested on this thin rod, and the coiled wing 3 is fixed to it using the pre-drilled equidistant mounting holes on the projectile body 2. The four coiled wings 3 of the projectile body 2 are equidistantly distributed around the pre-drilled annular groove of the projectile body 2. When the entire system is in a ready-to-launch state, the coiled wings 3 are slightly raised along the projectile's axial direction until their lower parts are completely away from the corresponding limiting grooves. Then, the coiled wings 3 are rotated in the opposite direction of the torsion spring force until they are tightly attached to the surface of the projectile body 2. The limiting grooves are aligned with the pre-set mounting holes along the projectile's axial direction, and there are four equidistantly distributed locations at the lower edge of the pre-drilled annular groove on the projectile body 2. After the four curved wings are fully fitted into the pre-reserved annular groove on the projectile body 2, the entire gun-launched missile platform is loaded into the launch tube with the valve mechanism 4 facing downwards, ready for launch. After the launch signal is given, the compressed air stored in the air chamber 7 is discharged through the valve mechanism 4, propelling the entire system out of the barrel. Then, the curved wings 3 are rotated off-axis and unfolded under the action of the torsion spring 12. After reaching the predetermined rotation angle, they are pushed backward into the limiting groove and fixed under the action of the ejection spring 11, completing the wing deployment and improving the flight stability of the gun-launched missile platform.

[0044] In this embodiment, reference Figure 4 , Figure 5 When the missile launcher platform reaches the predetermined separation height, the remote ignition device 9 receives a signal and ignites a small amount of gunpowder pre-loaded into the cavity inside the lower separation section 21 via the ignition wire 10. The airflow generated by the gunpowder directly pushes eight fixing pins 8 through eight radial air channels at the bottom of the cavity, causing them to fall off, thereby releasing the constraint between the missile compartment 1 and the missile body 2, achieving the purpose of separation and unpacking.

[0045] In this embodiment, the composition and function of the foldable guideable fireworks launching system are mainly realized by the relevant components of the airborne fireworks launching rack system 6, which is described separately as the launch control head system 61 and the remaining parts of the airborne fireworks launching rack system 6. Figure 6 and Figure 6-A As shown, the remaining parts of the airborne fireworks launcher system 6 include an airbag 62, a fireworks launch tube 63, a folding moving rod 64, a folding stationary rod 65, a pin 66, and a locking mechanism 67. A folding moving rod 64 is rigidly connected to each of the three points (top, middle, and bottom) of a single fireworks launch tube 63. The end of the folding moving rod 64 away from the fireworks launch tube 63 is hinged to the top, middle, and bottom folding stationary rods 65 via pins 66. The middle folding stationary rod 65 extends through four pre-drilled holes in the drone's fuselage, fixing the cage-like structure composed of the fireworks launch tube 63, folding moving rod 64, and folding stationary rod 65 onto the drone. Besides carrying and launching fireworks pellets, this cage-like structure also provides landing assistance and fuselage protection during drone descent. The fireworks launch tube 63 contains a miniature ignition device. When the system reaches the predetermined performance conditions, the ignition device ignites the pre-embedded gunpowder and fireworks pellets inside the launch tube, igniting and launching the fireworks.

[0046] In this embodiment, as Figure 9 As shown, the launch control head system 61 includes a fixed base 61-1, a control servo motor 61-2, a flexible hose 61-3, a limiting pin 61-4, and a swing control head 61-5. The fixed base 61-1 is nested and fixed at the opening of the fireworks launch tube 63. The swing control head 61-5 is hinged to the fixed base 61 via the limiting pin 61-4 and the control servo motor 61-2. Controlled by the control servo motor 61-2, the swing control head 61-5 can rotate left and right perpendicular to the hinge direction, forming a certain angle with the fixed base 61-1, thereby bending the flexible hose 61-3. The fireworks powder balls are ejected from the opening of the fireworks launch tube 63, and their trajectory is altered after passing through the bent flexible hose 61-3, thus achieving the effect and function of controlling the launch of the fireworks powder balls. The flexible hose 61-3 is made of a special high-temperature resistant material to prevent the high temperatures generated by repeated launches of fireworks powder balls from affecting the normal operation of key components of the launch control head system.

[0047] In this embodiment, the gasbag 62 has four annular fixing straps, which are embedded and fixed in the grooves in the middle of the four firework launch tubes 63. Before the ejection shell separation, the gasbag is in a gas-free state, appearing as a deflated ring surrounding the foldable guideable firework launch system. The gasbag 62 contains a small amount of gunpowder and a corresponding ignition device. After the ejection shell separation is completed by the artillery-launched projectile platform, the UAV and the entire foldable guideable firework launch system assembly, influenced by gravity, detach downwards through the lower opening of the bomb bay 1. Once the entire assembly is completely detached, the ignition device inside the gasbag 62 ignites the gunpowder. The expanding gas generated by the combustion of the gunpowder rapidly inflates the gasbag 62, causing it to expand and extend the four firework launch tubes 63 outwards. Figure 8 As shown, when the airbag is inflated to its maximum, the four firework launch tubes 63 will be pulled to the predetermined deployment position. This allows the drone and the foldable, guideable firework launch system to deploy in mid-air.

[0048] In this embodiment, after the drone and the foldable guided fireworks launching system are released into the air, the folding lever 64 will be propelled from its detached state by the inflating force of the airbag 62. Figure 6 The folded position shown rotates around pin 66 to... Figure 8 The unfolded position is shown. After reaching the unfolded position, the locking mechanism 67 installed on the folding moving rod 64 will engage with the reserved hole on the folding stationary rod 65 to ensure the stable and normal unfolding of the cage structure of the foldable guideable fireworks launching system.

[0049] In this embodiment, as Figure 6-A and Figure 7 As shown, the locking mechanism 67 consists of two parts: a limit button 67-1 and a limit spring 67-2. The limit button has a protruding limit block embedded in its inner part to ensure that the limit button does not exceed its normal travel.

[0050] The working principle of this embodiment is as follows: the overall system, consisting of a cannon-launched missile platform, a drone, and a foldable guided fireworks launching system, is ready to enter... Figure 1 The drone is loaded into the launch tube with its tail facing downwards in a ready-to-launch state. After the launch command is issued, the gas chamber 7, which is filled with high-pressure gas, releases compressed air through the valve mechanism 4 at the tail, thereby pushing the projectile out of the launch tube. After exiting the barrel, the coiled wings 3 unfold and are fixed by the ejection spring 11 and torsion spring 12, providing stability for the projectile's flight. When the preset altitude is reached, the remote ignition device 9 receives a signal remotely, activates the electric ignition wire 10, ignites a small amount of gunpowder in the cavity of the separation part 21, and pushes out the pin 8, releasing the connection constraint between the missile compartment 1 and the projectile body 2. Subsequently, the entire system consisting of the drone and the foldable guided fireworks launch system falls and detaches through the opening of the missile compartment 1. After detachment, the ignition device inside the gasbag 62 ignites the gunpowder and inflates it, forcing the four fireworks launch tubes 63 to unfold in all directions. After unfolding to the designated position, the locking mechanism 67 on the folding moving rod 64 will cooperate with the folding stationary rod 65 to lock and fix it, forming a shape like... Figure 8 The diagram shows the unfolded state of the foldable guided fireworks launch system. Once unfolded, the drone activates, providing power to ensure normal hovering of both the system and the launcher. The fireworks launch tube 63, pre-loaded with gunpowder and fireworks pellets, is ignited via the ignition circuit and then launched through the launch control head system 61 at the tube opening. Upon receiving preset commands, the control servo motor 61-2 drives the swing control head 61-5 and twists the hose 61-3 to a predetermined angle, controlling the launch trajectory of the fireworks pellets. Through the coordinated operation of multiple drones and the foldable guided fireworks launch system in multiple batches, complex aerial fireworks patterns can be formed, achieving the purpose of a fireworks show performance.

Claims

1. An airborne fireworks launching system for a gun-launched coaxial rotor unmanned aerial vehicle, characterized in that, The application relates to a gun-launched projectile platform, a UAV and a foldable guided firework launching system. The gun-launched projectile platform comprises a projectile cabin (1), a projectile body (2), four curved wings (3) and a valve core (4); in a state of being ready to be launched, the four curved wings (3) are distributed at equal intervals on the tail of the outer shell of the projectile body (2); after the projectile is launched, the four curved wings (3) are opened simultaneously, so that the stability of the flight process is ensured; the valve core (4) is used for connecting a high-pressure gas cylinder arranged in the projectile body; when the projectile is launched, high-pressure gas in the high-pressure gas cylinder is discharged through the valve core (4), so that a propelling force is provided. The UAV and the foldable guided firework launching system are fixed as a whole; the foldable guided firework launching system is composed of an airborne firework launching frame system (6) and a launching control head system (61); the airborne firework launching frame system (6) can be folded clockwise and is arranged in the projectile cabin (1); the launching control head system (61) is arranged on the airborne firework launching frame system (6) and comprises a fixing base (61-1), a control rudder (61-2), a hose (61-3) and a swing control head (61-5); the deflection of the swing control head (61-5) is controlled by the control rudder (61-2) through remote control, so that the direction of the firework is controlled; the airborne firework launching frame system (6) comprises firework launching tubes (63); the firework launching tubes (63) are internally provided with micro electric ignition devices; after receiving an ignition signal, the micro electric ignition devices ignite the pre-embedded gunpowder and firework beads in the firework launching tubes; the hose (61-3) is bent along with the deflection of the swing control head (61-5); the firework beads are shot out of the pipe mouths of the firework launching tubes (63) and change the trajectory after passing through the bent hose (61-3), so that the direction of the firework beads is controlled.

2. The cannon-launched coaxial-rotor unmanned aerial vehicle onboard fireworks launching system according to claim 1, characterized in that, The curved wings (3) are arranged at the tail of the projectile body (2) through a reserved annular groove of the projectile body (2) and are distributed at equal intervals around the tail of the projectile body (2); when the whole system is in a state of being ready to be launched, the curved wings (3) are arranged on the outer shell of the projectile body (2) and are folded in the barrel; when the whole system is in a state of flying, the curved wings (3) are rotated off the shaft and opened under the action of torsional springs (12); after a predetermined rotating angle is reached, the curved wings (3) are pushed backward into the limiting grooves under the action of the ejection springs (11), so that the limiting of the flight process is realized.

3. The cannon-launched coaxial-rotor unmanned aerial vehicle onboard fireworks launching system, according to claim 1, characterized in that, The airborne firework launching frame system (6) further comprises an air bag (62), a folding dynamic rod (64), a folding static rod (65), a pin (66) and a locking mechanism (67).

4. The cannon-launched coaxial-rotor unmanned aerial vehicle onboard fireworks launching system, according to claim 3, wherein, The swing control head (61-5) is hingedly connected with the fixing base (61-1) through a limiting pin (61-4) and the control rudder (61-2) and is controlled by the control rudder (61-2); the swing control head (61-5) and the fixing base (61-1) are nested with the hose (61-3).

5. The cannon-launched coaxial-rotor unmanned aerial vehicle onboard fireworks launching system, according to claim 4, wherein, The firework launching tubes (63) are provided in plurality; each firework launching tube (63) is designed as a one-way opening; the opening is arranged at the upper portion and the lower portion is not opened and is provided with a circular truncated cone base. Each of the fireworks launching tubes (63) is rigidly connected with a folding movable rod (64) at three positions; from top to bottom, the folding movable rods (64) are sequentially connected with three folding static rods (65) in a hinged form; the folding movable rods can rotate around the hinges to drive the fireworks launching tubes to rotate, thereby realizing the folding and unfolding of the overall structure.

6. The cannon-launched coaxial-rotor unmanned aerial system airborne fireworks launching system according to claim 5, wherein, The four fireworks launching tubes, the twelve folding movable rods and the three folding static rods form a cage structure together, which wraps the unmanned aerial vehicle; The middle layer folding static rod extends out of the four arms through the four-direction equidistant holes pre-arranged at the unmanned aerial vehicle body, so that the overall cage structure system is relatively fixed with the unmanned aerial vehicle.

7. The cannon-launched coaxial-rotor unmanned aerial vehicle onboard fireworks launching system, according to claim 6, characterized in that, The folding movable rod is provided with a locking mechanism composed of a limiting knob and a limiting spring; the folding static rod is correspondingly provided with a hole position, which cooperates with the limiting knob to realize the relative position fixation during the unfolding of the cage structure; the embedded part of the limiting knob is provided with a protruding limiting block to prevent the limiting knob from exceeding the normal stroke.

8. The cannon-launched coaxial-rotor unmanned aerial vehicle onboard fireworks launching system, according to claim 3, wherein, The air bag (62) is provided with four annular fixing bands embedded in the grooves at the middle parts of the four fireworks launching tubes; before the shell separation, the air bag is in a gas-free state, which is in a dry and shriveled annular shape around the folding guideable fireworks launching system; the air bag is internally provided with gunpowder and a corresponding ignition device.

9. The cannon-launched coaxial-rotor unmanned aerial vehicle onboard fireworks launching system, according to claim 1, wherein, The connecting part of the projectile body (2) and the projectile cabin (1) is provided with a separation mechanism; the outer structure of the separation mechanism is part of the projectile body structure, which is connected with the lower half exposed part of the projectile body, and has a circular truncated cone structure with a chamfer matched with the chamfer plane of the lower opening of the projectile body.

10. The cannon-launched coaxial-rotor unmanned aerial vehicle onboard fireworks launching system, according to claim 9, wherein, The separation mechanism further includes a remote control ignition device, an electric ignition wire and a pin; the remote control ignition device is embedded in the separation mechanism inside the projectile axis hole, the electric ignition wire is connected with the remote control ignition device, and the other end is placed at the bottom of the hole; the separation device hole bottom has eight vertical projectile axis through holes; they are distributed in the same plane in a wire-like manner and the hole radius is increased to the same size as the pin at the position penetrating out of the surface of the separation device; the lower opening of the projectile cabin shell is correspondingly provided with eight equidistantly distributed through holes in the same plane; the eight pins are respectively passed through the corresponding through holes to realize the constraint and locking of the projectile cabin and the projectile body.

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