Airborne firework launching system of cannon-launched coaxial unmanned rotorcraft

Abstract

The invention discloses a cannon-launched coaxial unmanned rotorcraft airborne firework launching system which comprises a cannon-launched projectile-loaded platform, an unmanned aerial vehicle and a folding type guidable firework launching system. The folding type guidable firework launching system and the unmanned aerial vehicle form an integral system, the integral system is folded and arranged in a bullet cabin, after the unmanned aerial vehicle is launched to the air with a certain height through an air cannon, separation and shelling are completed, the unmanned aerial vehicle and the folding type guidable firework launching system are released, and the launching opportunity and launching direction of fireworks are changed by remotely regulating and controlling a remote control steering engine. Various different complex firework patterns are formed, and large firework show performance is completed. Compared with a traditional firework unmanned aerial vehicle, the flight stability of the unmanned aerial vehicle can be better guaranteed in the flight process of the unmanned aerial vehicle, and the performance safety of the firework unmanned aerial vehicle is improved.

Description

Technical Field

[0001] The invention relates to the technical field of airborne launch of fireworks unmanned aerial vehicles, and in particular to an airborne fireworks launch system for a gun-launched coaxial rotor unmanned aerial vehicle. Background Art

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

[0003] In order to solve the problem that the angle of the fireworks launcher is difficult to adjust and the fireworks patterns are not rich enough, the patent with application number 202123149607.0 discloses an angle-adjustable fireworks launcher. Through the fixed frame, motor, threaded rod, connecting block, support rod and support assembly, the chassis can be stably adjusted in angle. The patent with application number 201922292688.6 discloses an adjustable fireworks launcher and a bouquet-shaped launcher. The telescopic adjustment rod is used to adjust the opening angle of the upper and lower fixed frames, thereby controlling the launch angle of the barrel plate with the fireworks barrel inserted, meeting the needs of different positions and heights of fireworks launch. The patent with application number 202322702728.6 discloses a firework with adjustable launch direction. The firework body is installed by a limit spring and a partition, and the anti-slip pad limits the firework body. The motor drives the curved rod to work, and the direction of the fireworks can be adjusted. Patent application number 202221037532.9 discloses a firework launcher with precise angle adjustment. Through the provision of a slide, a fixed side panel, a launching assembly and a fixing assembly, the firework launcher can adjust the angle very easily and accurately.

[0004] The launch system and flight control system described in the above method control the rotation of the drone together. Since the launch system has only one motor, it can only control one pitch, and the drone controls the angle and direction of the launch. The two cannot work together to achieve the arbitrary change of the position and direction of the upward drone in three-dimensional space. In addition, the existing launch devices are designed according to inherent patterns and cannot be changed at any time according to new patterns. It is impossible to achieve multiple different firework patterns through one launch device, and it cannot be mass-produced. It is impossible to form a highly controllable firework pattern. The firework pattern is single, which cannot make up for the deficiency that traditional fireworks shows cannot control the firework pattern in real time. Summary of the invention

[0005] The present invention aims to solve the problems and shortcomings of the existing firework drone airborne launch technology, and aims to provide a cannon-launched coaxial rotor drone airborne firework launch system. The foldable and steerable firework launch system and the drone form an integral system, which is folded and placed in the bomb bay. After being lifted to a certain height in the air by air cannon firing, the drone and the foldable and steerable firework launch system are separated and released. The launch timing and direction of the fireworks are changed by remotely controlling the remote control servo, forming various complex firework patterns, and completing a large-scale firework show.

[0006] The technical solution to achieve the purpose of the present invention is: a cannon-launched coaxial rotor UAV airborne fireworks launching system, comprising a cannon-launched projectile-carrying platform, a UAV and a foldable steerable fireworks launching system;

[0007] The cannon projectile carrier platform includes a bomb bay, a projectile body, a curled wing and a valve mechanism; in a state ready to launch, four curled wings are distributed at equal intervals at the tail of the projectile body shell; after the projectile is launched, the four curled wings are opened at the same time to ensure the stability of the flight process;

[0008] The UAV and the foldable steerable fireworks launching system are fixed as a whole. The foldable steerable fireworks launching system consists of an airborne fireworks launching rack system and a launching control head system. The airborne fireworks launching rack system can be folded clockwise and placed in the bomb bay. The launching control head system is installed on the airborne fireworks launching rack system, including a fixing seat, a control servo, a hose, and a swinging control head. The servo is controlled by remote control to control the deflection of the swinging control head, thereby controlling the direction of the fireworks.

[0009] Compared with the prior art, the present invention has the following significant advantages:

[0010] (1) When the whole system of the cannon projectile carrier platform of the present invention is in flight, the curled wing will be rotated off-axis by the force of the torsion spring and open. After reaching a predetermined rotation angle, it will be pushed backward by the ejection spring to snap into the limit groove, thereby achieving the limit in the flight process. Compared with the traditional fireworks drone, the present 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 fireworks launch tubes included in the airborne fireworks launcher system of the foldable and steerable fireworks launcher system of the present invention can be loaded with a large amount of fireworks propellant and fireworks powder beads, ensuring that the amount of fireworks carried by a single fireworks drone reaches the amount of powder required for the 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 steerable fireworks launch system of the present invention can be remotely controlled by a remote control motor to control the direction of the fireworks, so that a small number of drones can 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 beads in real time, forming a richer fireworks pattern. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is a schematic diagram of the missile-loaded structure of the system of the present invention ready to be launched.

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

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

[0016] Figure 4 It is a schematic diagram of explosion of the projectile separation mechanism of the system of the present invention.

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

[0018] Figure 6 It is a schematic diagram of the three-dimensional structure of the unmanned aerial vehicle and the airborne fireworks launching system of the present invention in a folded state.

[0019] Figure 6-A It is a schematic diagram of the partial structure of the unmanned aerial vehicle and the airborne fireworks launching system of the present invention in the folded state.

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

[0021] Figure 8 It is a three-dimensional structural schematic diagram of the unmanned aerial vehicle and the airborne fireworks launching system of the present invention in the unfolded state.

[0022] Fig. 9 It is a schematic diagram of the three-dimensional structure of the launch control head of the UAV and the airborne fireworks launch system of the present invention.

[0023] Among them: 1-bomb bay, 2-projectile body: 21-separation part, 22-projectile body, 3-arc wing, 4-valve movement, 5-UAV, 6-airborne fireworks launcher system: 61-launch control head system: 61-1-fixed seat, 61-2-control servo, 61-3-hose, 61-4-limit pin, 61-5-swing control head, 62-airbag, 63-fireworks launch tube, 64-folding moving rod, 65-folding static rod, 66-pin, 67-locking mechanism, 67-1-limit button, 67-2-limit spring, 7-air chamber, 8-pin, 9-remote control ignition device, 10-electric ignition wire, 11-ejection spring, 12-torsion spring. DETAILED DESCRIPTION

[0024] Combination Figures 1 to 9 The invention discloses a cannon-launched coaxial rotor drone-mounted fireworks launching system, which comprises a cannon-launched projectile carrier platform, a drone and a foldable steerable fireworks launching system. The cannon-launched projectile carrier platform is composed of a bomb bay, a projectile body, a curled wing, an air chamber and a valve mechanism in order from the warhead.

[0025] Furthermore, a separation mechanism is provided at the connection between the projectile body and the bomb bay. The outer structure of the separation mechanism is a part of the projectile body structure, connected to the exposed lower half of the projectile body, and its appearance is a frustum structure with a thinner middle. The frustum is provided with a chamfer to fit the chamfered plane of the lower opening of the projectile body. In addition to the above structure, the separation mechanism also includes a remote control ignition device, an electric ignition wire and a pin. The remote control ignition device is buried in the separation mechanism in a hole on the axis of the projectile body, and the electric ignition wire is connected to the remote control ignition device, and the other end is placed at the bottom of the hole.

[0026] Furthermore, there are eight through holes perpendicular to the axis of the missile body at the bottom of the separation device. They are distributed in the same plane in a radial shape and the hole radius increases to the same size as the pin when passing through the surface of the separation device. In contrast, there are eight through holes distributed equidistantly and in the same plane at the lower opening of the bomb bay shell. The eight pins pass through the corresponding through holes to constrain and lock the bomb bay and the missile body.

[0027] Furthermore, the tail of the projectile is provided with a curling wing, an air chamber and a valve mechanism. The curling wings are distributed at equal intervals around the tail of the projectile. They are installed at the tail of the projectile through a reserved annular groove of the projectile, and are movably connected with the preset hole at the rear of the projectile in cooperation with the ejection spring and the torsion spring. When the curling wing is unfolded by the torsion spring, the ejection spring will reach the predetermined position and the curling wing will be pushed into the limiting groove, so that the position of the curling wing is fixed. The air chamber is a hollow part inside the projectile, which is used to store high-pressure gas as a propulsion power before launch. The valve mechanism is used to connect the built-in high-pressure gas cylinder of the launch device to play a role in launch control.

[0028] Furthermore, the foldable steerable fireworks launch system is composed of a launch control head system and an airborne fireworks launch rack system. The airborne fireworks launch rack system includes an air bag, four fireworks launch tubes, twelve foldable movable rods, three foldable static rods, a pin and a locking mechanism. The launch control head system includes a fixing seat, a control steering gear, a hose, a limit pin and a swing control head.

[0029] Furthermore, each firework launch tube is designed with a one-way opening, the opening is at the top, the bottom is not open and is designed with a truncated cone-shaped base. A micro-electric ignition device is installed inside the firework launch tube. When the system reaches the predetermined performance conditions, the ignition device receives the ground signal and ignites the pre-buried gunpowder and firework powder beads inside the launch tube to realize the ignition and launch of the fireworks. A launch control head system is connected to the launch tube mouth.

[0030] Furthermore, each firework launch tube has a folding movable rod rigidly connected to it at three locations, the top, the middle and the bottom. From top to bottom, the folding movable rod is sequentially connected to the three folding static rods in the form of hinges. The folding movable rod can drive the firework launch tube to rotate around the hinge, thereby realizing the folding and unfolding of the overall structure.

[0031] Furthermore, the four firework launch tubes, twelve folding movable rods and three folding static rods together form a cage structure, which wraps the drone. The middle folding static rod extends its four arms through four equidistant holes pre-set in the drone body, so that the overall cage structure system is relatively fixed to the drone.

[0032] Furthermore, a locking mechanism is provided on the folding movable rod. The locking mechanism consists of a limit button and a limit spring. Corresponding holes are reserved on the folding static rod, and the relative position of the cage structure is fixed when the cage structure is unfolded in cooperation with the limit button. A protruding limit block is provided in the embedded part of the limit button to ensure that the limit button does not exceed the normal travel.

[0033] The airborne fireworks launcher can realize the functions of carrying and launching fireworks powder beads, and can also protect the UAV and assist the UAV in landing.

[0034] Furthermore, the UAV and the foldable steerable fireworks launching system form an integral system, and are folded and placed inside the bomb bay of the artillery projectile carrier platform to maintain a ready-to-launch state.

[0035] Furthermore, the airbag is provided with four annular fixing belts, which are embedded in the grooves fixed in the middle of the four firework launch tubes. Before the shell ejection and separation are performed, the airbag is in a gas-free state and surrounds the foldable and steerable firework launch system in a deflated ring shape. A small amount of gunpowder and a corresponding ignition device are placed inside the airbag. When the shell ejection and separation are completed on the artillery shell carrier platform, the UAV and the foldable and steerable firework launch system as a whole are ejected downward from the lower opening of the bomb bay under the influence of gravity. When the above-mentioned whole is completely ejected, the built-in ignition device of the airbag will ignite the gunpowder, and the expanding gas generated by the combustion of the gunpowder will quickly inflate the airbag, causing it to swell and drive the four firework launch tubes to extend outward. In the process of the airbag rapidly changing from a deflated and folded state to an inflated and full state, the four firework launch tubes will be pulled to a predetermined deployment position and fixed by the locking structure on the folding movable rod. In this way, the UAV and the foldable and steerable firework launch system are deployed in the air.

[0036] Furthermore, the launch control head system is composed of a fixed seat, a control steering gear, a hose, and a swing control head. The system is fixed to the nozzle of the fireworks launch tube via the fixed seat. The swing control head is hingedly connected to the fixed seat via a limit pin and a control steering gear, and is controlled by the control steering gear to achieve a swing effect at a specified angle.

[0037] Furthermore, the fixing seat reserves a coaxial through hole, the radius of the lower through hole matches the outer diameter of the firework launch tube to achieve nesting and fixation. The upper through hole is slightly narrower, matching the relative position of the firework launch tube to ensure that it is consistent with the radius of the hose.

[0038] Furthermore, the swing control head reserves a coaxial through hole with the same outer diameter as the hose. The two ends of the hose are fixed to the fixing seat and the swing control head respectively. When the swing control head swings, the hose will bend, changing the fireworks launch path, so that the fireworks launch can be controlled. The hose is made of high temperature resistant material to ensure that the high temperature generated by multiple fireworks launches does not affect the normal operation of the hose and other components.

[0039] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0040] Example

[0041] The present invention is now further described in the missile launch use scenario in conjunction with the accompanying drawings and specific embodiments, with reference to Figure 1-9As shown in FIG. 1 , an embodiment of the present invention provides a cannon-launched coaxial rotor drone-mounted fireworks launching system. The system includes a cannon-launched missile-carrying platform, a drone 5, and a foldable and steerable fireworks launching system. The drone 5 and the foldable and steerable fireworks launching system form an integrated system as shown in FIG. Figure 1 As shown, it is folded and placed inside the ammunition bay 1 of the artillery projectile carrier platform to maintain a ready-to-fire state.

[0042] In this embodiment, reference Figure 1-Figure 5 The artillery projectile carrier platform is mainly composed of a bomb bay 1, a projectile body 2, a curled wing 3, an air chamber 7 and a movement 4 from the projectile head. The inner contour of the bomb bay 1 matches the outer contour of the separation part 21 of the projectile body 2. There are eight equal-diameter circular holes distributed evenly around the corresponding parts of the two parts, and eight pins 8 are used to connect and fix the bomb bay 1 and the projectile body 22. Figure 3 As shown, the air chamber 7 is a hollow portion inside the projectile body 2, which is used to store high-pressure gas as a propulsion force before launching.

[0043] In this embodiment, reference Figure 3 , the curling wing 3 is movably connected to the preset mounting hole at the rear of the projectile 2 in cooperation with the ejection spring 11 and the torsion spring 12. A thin rod is extended at a certain distance from the root of each curling wing 3 along the longitudinal direction of the projectile axis. The ejection spring 11 and the torsion spring 12 are coaxially nested on the thin rod, and the curling wing 3 is fixed on it in cooperation with the equidistant mounting holes reserved on the projectile 2. The four curling wings 3 of the projectile 2 are evenly distributed around the reserved annular groove of the projectile 2. When the overall system is in a state of waiting to be launched, the curling wing 3 is slightly lifted along the axial direction of the projectile until its lower part completely leaves the corresponding limiting groove, and then the curling wing 3 is rotated in the opposite direction of the torsion spring force until it is close to the surface of the projectile 2. The limiting groove is aligned with the above-mentioned preset mounting hole along the axis of the projectile, and a total of four are evenly distributed at the lower edge of the reserved annular groove of the projectile 2. After the four curved wings are completely fitted into the reserved annular groove of the projectile body 2, the cannon projectile carrier platform is loaded into the launch tube with the valve movement 4 facing downwards and waits for launch. After the launch signal is issued, the compressed air stored in the air chamber 7 is discharged through the valve movement 4 to push the entire system out of the chamber, and then the curved wings 3 rotate off-axis under the action of the torsion spring 12 to unfold, and after reaching the predetermined rotation angle, they are pushed backward into the limit groove under the action of the ejection spring 11 to be fixed, completing the unfolding of the projectile wings, thereby improving the flight stability of the cannon projectile carrier platform.

[0044] In this embodiment, reference Figure 4 , Figure 5 When the artillery projectile carrier reaches the predetermined separation height, the remote control ignition device 9 receives the signal and ignites the electric ignition wire 10 to ignite the small amount of gunpowder pre-filled in the cavity of the lower separation part 21. The airflow generated by the gunpowder directly pushes the eight pins 8 used for fixing to fall off through the eight linear air channels at the bottom of the cavity, thereby releasing the constraints of the bomb compartment 1 and the projectile body 2, and achieving the purpose of separation and shelling.

[0045] In this embodiment, the composition and functions of the foldable steerable fireworks launch system are mainly realized by the relevant components of the airborne fireworks launcher system 6, which are divided into the launch control head system 61 and the rest of the airborne fireworks launcher system 6 for separate description. Figure 6 As shown, the rest of the airborne fireworks launcher system 6 includes an airbag 62, a fireworks launch tube 63, a folding movable rod 64, a folding static rod 65, a pin 66, and a locking mechanism 67. A folding movable rod 64 is rigidly connected to the single fireworks launch tube 63 at three locations, the upper, middle, and lower. The folding movable rod 64 is hinged to the upper, middle, and lower three-layer folding static rods 65 through a pin 66 at one end away from the fireworks launch tube 63. The middle-layer folding static rod 65 extends its four walls through a pre-set four-way hole in the fuselage of the unmanned aerial vehicle, so that the cage structure composed of the fireworks launch tube 63, the folding movable rod 64, and the folding static rod 65 is fixed on the unmanned aerial vehicle. In addition to carrying and launching fireworks powder beads, the above-mentioned cage structure can also play the role of landing assistance and body protection when the unmanned aerial vehicle lands. A micro ignition device is installed inside the fireworks launch tube 63. When the system reaches the predetermined performance conditions, the ignition device ignites the pre-buried gunpowder and fireworks powder beads inside the launch tube to achieve the ignition and launch of fireworks.

[0046] In this embodiment, if Fig. 9 As shown, the launch control head system 61 includes a fixed seat 61-1, a control steering gear 61-2, a hose 61-3, a limit pin 61-4, and a swing control head 61-5. The fixed seat 61-1 is nested and fixed at the mouth of the fireworks launch tube 63, and its swing control head 61-5 is hingedly connected to the fixed seat 71 through the limit pin 61-4 and the control steering gear 61-2. Under the control of the control steering gear 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 seat 61-1, thereby bending the hose 61-3. The fireworks powder beads are ejected from the mouth of the fireworks launch tube 63, and the ballistic trajectory is changed after passing through the bent hose 61-3, thereby achieving the effect and function of the fireworks powder bead launch control. The hose 61-3 is made of special high-temperature resistant materials to prevent the high temperature generated by multiple fireworks powder bead launches from affecting the normal operation of key components of the launch control head system.

[0047] In the present embodiment, the airbag 62 is provided with four annular fixing belts, which are embedded and fixed in the grooves in the middle of the four fireworks launching tubes 63. Before the shell ejection and separation are performed, the airbag is in a gas-free state, and is in a deflated ring shape surrounding the foldable and steerable fireworks launching system. A small amount of gunpowder and a corresponding ignition device are placed inside the airbag 62. When the shell ejection and separation of the projectile carrier platform are completed, the drone and the foldable and steerable fireworks launching system as a whole are ejected downward from the lower opening of the bomb bay 1 under the influence of gravity. When the above-mentioned whole is completely ejected, the built-in ignition device of the airbag 62 will ignite the gunpowder, and the expanding gas generated by the combustion of the gunpowder will quickly inflate the airbag 62, causing it to swell and drive the four fireworks launching tubes 63 to extend outward. Figure 8 As shown, when the airbag is inflated to the maximum, the four firework launch tubes 63 will be pulled to the predetermined deployment position, thereby the drone and the foldable steerable firework launch system can be deployed in the air.

[0048] In this embodiment, after the drone and the foldable steerable fireworks launching system are released in the air, the foldable movable rod 64 will be moved from the air bag 62 due to the pressure of the inflation of the air bag 62. Figure 6 The folded position shown is rotated about pin 66 to Figure 8 After reaching the unfolded position, the locking mechanism 67 arranged on the folding movable rod 64 will be locked into the reserved hole of the folding static rod 65 to ensure that the cage structure of the foldable guideable fireworks launching system is stably and normally unfolded.

[0049] In this embodiment, if Figure 6-A and Figure 7 As shown, the locking mechanism 67 is composed of a limit button 67-1 and a limit spring 67-2. A protruding limit block is provided in the embedded part of the limit button to ensure that the limit button does not exceed the normal travel.

[0050] The working principle of this embodiment is as follows: the whole system consisting of the cannon projectile carrier platform, the drone and the foldable steerable fireworks launch system is ready to enter Figure 1 The drone is in a state ready to launch, and its tail is loaded downward into the launch tube. After the launch command is issued, the air chamber 7 prepared with high-pressure gas releases compressed air through the valve movement 4 at the tail, thereby pushing the projectile of the entire system out of the launch tube. After leaving the chamber, the arc wing 3 is unfolded and fixed by the ejection spring 11 and the torsion spring 12, providing stability for the flight of the projectile. When the preset height is reached, the remote control ignition device 9 receives the 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, thereby releasing the connection constraint between the bomb bay 1 and the projectile body 2. Subsequently, the entire system consisting of the drone and the foldable and steerable fireworks launching system falls out through the opening of the bomb bay 1. After escaping, the built-in ignition device of the airbag 62 ignites the gunpowder and inflates it, forcing the four fireworks launching tubes 63 to unfold to the surroundings. After unfolding to the specified position, the locking mechanism 67 provided on the folding movable rod 64 will cooperate with the folding static rod 65 to lock and fix, forming a Figure 8 The foldable steerable fireworks launch system is shown in the unfolded state. After unfolding, the drone starts to provide power to ensure that it and the launch system hover normally. The fireworks launch tube 63 is pre-loaded with gunpowder and fireworks powder beads, which are ignited through the ignition circuit and then ejected through the launch control head system 61 at the tube mouth. After receiving the preset command, the control servo 61-2 drives the swing control head 61-5 and twists the hose 61-3 to a predetermined angle to control the launch trajectory of the fireworks powder beads. Through the cooperation of multiple drones and multiple batches of foldable steerable fireworks launch systems, the formation of complex fireworks patterns in the air can be completed, and the purpose of fireworks show performance can be achieved.

Claims

1. A cannon-launched coaxial rotor drone airborne fireworks launching system, characterized in that: Includes artillery projectile carrier platforms, drones, and foldable steerable fireworks launch systems; The cannon projectile carrier platform comprises a bomb bay (1), a projectile body (2), curled wings (3) and a valve mechanism (4); in a state ready to launch, four curled wings (3) are distributed at equal intervals around the tail of the shell of the projectile body (2); after the projectile is launched, the four curled wings (3) are opened simultaneously to ensure the stability of the flight process; The unmanned aerial vehicle and the foldable steerable fireworks launching system are fixed as a whole, and the foldable steerable fireworks launching system is composed of an airborne fireworks launching frame system (6) and a launching control head system (61); the airborne fireworks launching frame system (6) can be folded clockwise and placed in a bomb bay (1); the launching control head system (61) is installed on the airborne fireworks launching frame system (6), and comprises a fixing seat (61-1), a control steering gear (61-2), a hose (61-3), and a swinging control head (61-5); the deflection of the swinging control head (61-5) is controlled by remotely controlling the steering gear (61-2), thereby controlling the firing direction of the fireworks.

2. The cannon-launched coaxial rotor drone airborne fireworks launching system according to claim 1 is characterized in that: The curling wings (3) are installed at the tail of the projectile (2) through the reserved annular groove of the projectile (2), and are evenly distributed around the tail of the projectile (2); when the whole system is in a state ready to launch, the curling wings (3) are distributed in contact with the outer shell of the projectile (2) and are folded and placed in the gun barrel; when the whole system is in a flying state, the curling wings (3) are rotated off-axis by the force of the torsion spring (12) and, after reaching a predetermined rotation angle, are pushed backward by the action of the ejection spring (11) to snap into the limit groove, thereby realizing the limit in the flight process.

3. The cannon-launched coaxial rotor drone airborne fireworks launching system according to claim 1 is characterized in that: The airborne fireworks launcher system (6) comprises an air bag (62), a fireworks launch tube (63), a folding movable rod (64), a folding stationary rod (65), a pin (66) and a locking mechanism (67); a micro-electric ignition device is installed inside the fireworks launch tube (63), and after receiving an ignition signal, the ignition device ignites the pre-buried gunpowder and fireworks powder beads inside the launch tube.

4. The cannon-launched coaxial rotor drone airborne fireworks launching system according to claim 3 is characterized in that: The launch control head system (61) is nested and fixed at the pipe mouth of the fireworks launch tube (63) via a fixed seat (61-1); the swing control head (61-5) is hingedly connected to the fixed seat (61-1) via a limit pin (61-4) and a control steering gear (61-2), and is controlled by the control steering gear (61-2); a hose (61-3) is nested between the swing control head (61-5) and the fixed seat (61-1); the hose (61-3) bends with the deflection of the swing control head (61-5); fireworks powder beads are ejected from the pipe mouth of the fireworks launch tube (63), and after passing through the bent hose (61-3), the ballistic trajectory is changed, thereby realizing the control of the launch direction of the fireworks powder beads.

5. The cannon-launched coaxial rotor drone airborne fireworks launching system according to claim 4 is characterized in that: Each firework launching tube (63) is designed to be opened in one direction, with the opening being at the top and the bottom being unopened and having a truncated cone-shaped base; Each firework launching tube (63) has a folding movable rod (64) rigidly connected to it at three locations, namely, the top, the middle and the bottom. From top to bottom, the folding movable rod (64) is sequentially connected to three folding static rods (65) in the form of hinges. The folding movable rod can drive the firework launching tube to rotate around the hinge, thereby realizing the folding and unfolding of the overall structure.

6. The cannon-launched coaxial rotor drone airborne fireworks launching system according to claim 5 is characterized in that: Four firework launch tubes, twelve folding moving rods and three folding static rods together form a cage structure that wraps the drone; The middle-layer folding static rod extends its four arms through four equidistant holes preset in the fuselage of the UAV, so that the overall cage structure system is relatively fixed to the UAV.

7. The cannon-launched coaxial rotor drone airborne fireworks launching system according to claim 5, characterized in that: A locking mechanism is provided on the folding moving rod, which consists of a limit button and a limit spring. Corresponding holes are reserved on the folding static rod to cooperate with the limit button to fix the relative position of the cage structure when it is unfolded. A protruding limit block is provided on the embedded part of the limit button to ensure that the limit button does not exceed the normal stroke.

8. The cannon-launched coaxial rotor drone airborne fireworks launching system according to claim 3 is characterized in that: The air bag (62) is provided with four annular fixing belts, which are embedded and fixed in the grooves at the middle of the four firework launching tubes; before the shell ejection and separation are performed, the air bag is in a gas-free state, and is in a deflated ring shape surrounding the foldable and steerable firework launching system; gunpowder and a corresponding ignition device are placed inside the air bag.

9. The cannon-launched coaxial rotor drone airborne fireworks launching system according to claim 1, characterized in that: A separation mechanism is provided at the connection between the projectile (2) and the bomb bay (1); the outer structure of the separation mechanism is a part of the projectile structure, connected to the exposed lower half of the projectile, and has a frustum structure, the frustum being provided with a chamfer that fits with the chamfered plane of the lower opening of the projectile.

10. The cannon-launched coaxial rotor drone airborne fireworks launching system according to claim 9, characterized in that: The separation mechanism also includes a remote control ignition device, an electric ignition wire and a pin; the remote control ignition device is buried in a hole on the axis of the projectile body in the separation mechanism, the electric ignition wire is connected to the remote control ignition device, and the other end is placed at the bottom of the hole; there are eight through holes perpendicular to the axis of the projectile body at the bottom of the separation device hole; they are distributed in a radial shape on the same plane and the hole radius is increased to the same size as the pin at the point where they pass through the surface of the separation device; there are eight through holes distributed equidistantly and on the same plane corresponding to the lower opening of the bomb bay shell; eight pins pass through the corresponding through holes respectively to realize the constraint and locking of the bomb bay and the projectile body.

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