A loitering munition system for 40-mm rocket launchers

Abstract

The present invention provides a loitering munition system for 40-mm rocket launchers, comprising a loitering munition, an ejection mechanism and a 40-mm extended-range power system; the loitering munition is connected to the 40-mm extended-range power system through the ejection mechanism in a folded state, and is launched through a 40-mm rocket launcher. After the operation of the 40-mm extended-range power system ends, the loitering munition is separated from the 40-mm extended-range power system under the ejection action of the ejection mechanism, and the loitering munition unfolds and self-locks for loitering. After the shooter determines the target based on the target image transmitted back by the loitering munition, the shooter controls the loitering munition to attack the target. The loitering munition of the present invention has a long loitering distance and can accurately damage the target.

Description

Technical Field

[0001] The present invention relates to the technical field of weapons and ammunition, and particularly relates to a loitering munition system for launching by a 40-mm rocket launcher. Background Art

[0002] With the development of control and guidance technologies, unmanned aerial vehicle (UAV) products have been rapidly applied, among which loitering munitions are a key product under development. Previous loitering munitions were mainly fixed-wing. With the development of quadrotor UAVs, loitering munitions carried by rotor UAVs have also emerged. Due to the limited volume and energy of loitering munitions carried by rotor UAVs, the loitering distance or area they can cover is limited.

[0003] At the same time, the 40-mm individual rocket launcher is a conventional assault weapon and equipment for infantry to counter personnel, tanks, armor, and fortifications at close range. It is highly favored due to its low cost, light weight, simple operation, and convenient portability, and is still widely equipped and used by various countries. Therefore, a loitering munition system that can be launched by a 40-mm individual rocket launcher can be developed. Summary of the Invention

[0004] In view of this, the present invention provides a loitering munition system for launching by a 40-mm rocket launcher, which has a long loitering distance and can accurately damage targets.

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

[0006] A loitering munition system for launching by a 40-mm rocket launcher, the loitering munition system comprising a loitering munition, an ejection mechanism, and a 40-mm range extension power system;

[0007] The loitering munition is connected to the 40-mm range extension power system through the ejection mechanism in a folded state. After being launched by the 40-mm rocket launcher, when the operation of the 40-mm range extension power system ends, the loitering munition is separated from the 40-mm range extension power system under the ejection action of the ejection mechanism. The loitering munition unfolds and locks itself for loitering. After the shooter determines the target based on the target image transmitted back by the loitering munition, the shooter controls the loitering munition to attack the target.

[0008] Further, the loitering munition comprises a quadrotor UAV, a warhead, a video seeker, and a connecting tube;

[0009] The connecting tube is of a cylindrical structure, and grooves for the rotors of the quadrotor UAV to unfold and extend are provided on the connecting tube wall;

[0010] The quadrotor UAV is fixed at one end of the connecting tube. In the folded state, the rotors are located inside the connecting tube. The video seeker is fixed at the other end of the connecting tube; the warhead is fixedly connected to the quadrotor UAV and is located inside the connecting tube.

[0011] Further, the quadcopter drone includes a base, a rotor assembly, a spring plunger, a pin shaft, and a double torsion spring;

[0012] The rotor assembly is rotatably connected to the base through the pin shaft, and at the same time, the double torsion spring is sleeved on the pin shaft; a spring plunger is provided between the rotor assembly and the base. When the rotor assembly is in the folded state, the head of the spring plunger is in a compressed state under the pressure of the side wall of the rotor assembly. When the rotor assembly is in the unfolded state, the head of the spring plunger extends out and inserts into the locking hole on the rotor assembly to lock the rotor assembly.

[0013] Further, the base includes a bottom cover, a base housing, a firing plate, a receiver, a flight controller, a U-shaped block, a battery, and a sleeve;

[0014] Four U-shaped blocks are arranged at one end of the base housing and are evenly fixed along the circumferential direction of the base housing for installing the rotor assembly; the firing plate, the receiver, the flight controller, and the battery are fixed inside the base housing; the sleeve is radially installed on the outer circumference of the base housing, and the sleeve is used to place the pyrotechnic device, and the lead wire of the pyrotechnic device is connected to the firing plate; the other end of the base housing is closed by the bottom cover.

[0015] Further, the rotor assembly includes an upper blade clamp, a blade, a lower blade clamp, a motor, a motor flange, an electronic speed controller, and a cantilever;

[0016] The blade is fixed to form a rotor through the upper blade clamp and the lower blade clamp. The rotor is fixed on the motor, and the motor is fixed on the cantilever through the motor flange; the rotor is parallel to the cantilever, and the electronic speed controller is fixed at the bottom of the motor flange; the rotor unfolds to both sides under the drive of the motor.

[0017] Further, the ejection mechanism includes a projectile holder, a compression spring, a compression screw, and a pyrotechnic device;

[0018] The projectile holder is arranged inside the base housing for restricting the unfolding of the cantilever; at the same time, the projectile holder compresses the compression spring inside the base housing; the compression screw is radially installed and connected to the sleeve, and the pyrotechnic device is arranged inside the sleeve.

[0019] Further, the 40mm extended-range power system includes a soft launch engine, a double-channel firing tail rod, a flight engine, and an extended-range engine;

[0020] The soft launch engine, the double-channel firing tail rod, the flight engine, and the extended-range engine are connected in sequence from the tail; the soft launch engine, the double-channel firing tail rod, and the flight engine are located inside the 40mm rocket launcher, and the extended-range engine is located in the over-caliber part.

[0021] Further, the soft launch engine includes a front head, an electric contact piece seat, an electric contact piece, a medicine hanging plate, a propellant charge, a housing, a plug cover I, and a nozzle body;

[0022] The grain is fixed on the medicine hanging plate, and the medicine hanging plate is fixed inside the shell. The front end of the shell is fixedly connected to the front head, and the rear end is fixedly connected to the nozzle body. At the same time, the plug cover I is encapsulated at the rear end; the electrical connection piece is fixed inside the electrical connection piece seat, and the electrical connection piece seat is fixed inside the front head.

[0023] Further, the dual-channel firing tail rod includes a tail rod, fins, a torsion spring, a delay firing adapter plate, an overload switch, a firing circuit seat, a motor seat, and a magneto;

[0024] The motor seat is fixed at one end of the tail rod, the magneto is installed on the motor seat, the firing circuit seat is fixed at the other end of the tail rod, the overload switch is fixed on the firing circuit seat, and at the same time, the end is fixedly connected to the delay firing adapter plate; the fins are rotatably installed on the tail rod at the end of the firing circuit seat. At the same time, one leg of one end of the torsion spring is inserted into the tail rod hole, and the other end passes through the fin slot;

[0025] The magneto does work to generate a dual-channel electromotive force, which is transmitted by two wires. One wire is connected to the delay firing adapter plate to detonate the grain of the soft launch engine, and the other wire charges the capacitor in the delay firing adapter plate. When the cruise missile system breaks away from the launch tube, the fins open; when the delay reaches the set time, the delay firing adapter plate controls the capacitor to discharge and ignites the electric igniter of the flight engine.

[0026] Further, the range extension engine includes a shell, a charge, a rear end cover heat insulation, a throat liner, a bushing, a nozzle body, a rear end cover, an electric igniter, a plug cover II, and ignition powder;

[0027] One end of the shell is closed and the other end is open. The open end is fixedly connected to the rear end cover; the nozzle body is obliquely arranged on the outer surface of the rear end cover. The throat liner is fixed inside the nozzle body through the bushing, and the plug cover II closes the outlet of the nozzle body; the rear end cover heat insulation is arranged inside the rear end cover; the charge is arranged inside the shell, and the electric igniter is fixed on the rear end cover. The electric igniter is connected to the charge through the ignition powder.

[0028] Beneficial effects:

[0029] The cruise missile system of the present invention can be launched by a 40mm rocket launcher platform and is pushed to 2Km - 3Km by a 40mm range extension power system, and then the cruise missile is ejected. The cruise missile can be folded, has the functions of detection, reconnaissance, and attack, and can be remotely controlled. After determining the target, it can damage the target. Brief description of the drawings

[0030] Figure 1 It is a sectional view of the overall structure of the present invention;

[0031] Figure 2 It is an exploded view of the cruise missile and the ejection mechanism;

[0032] Figure 3(a) is a sectional view of the inner base of the quadrotor UAV, and Figure 3(b) is a front view of the inner base of the quadrotor UAV;

[0033] Figure 4 is an exploded view of the inner base of the quadrotor UAV;

[0034] Figure 5 is a sectional view of the inner rotor assembly of the quadrotor UAV;

[0035] Figure 6 is an exploded view of the inner rotor assembly of the quadrotor UAV;

[0036] Figure 7 is a half-sectional view of the installation structure of the rotor assembly and the base U-shaped block;

[0037] Figure 8 is an axonometric view of the U-shaped block;

[0038] Figure 9 is an axonometric view of the swing arm;

[0039] Figure 10 is a sectional view of the spring plunger;

[0040] Figure 11 is a sectional view of the warhead;

[0041] Figure 12 is a sectional view of the video seeker;

[0042] Figure 13 is an exploded view of the video seeker;

[0043] Figure 14 is a structural diagram of the cruise missile when the quadrotor is deployed;

[0044] Figure 15 is an installation sectional view of the ejection mechanism;

[0045] Figure 16 is an axonometric view of the base housing;

[0046] Figure 17 is an axonometric view of the projectile holder;

[0047] Figure 18 is a sectional view of the 40mm extended-range power system;

[0048] Figure 19 is a sectional view of the soft launch engine;

[0049] Figure 20 is a sectional view of the dual-channel percussion tail rod;

[0050] Figure 21 is a sectional view of the flight engine;

[0051] Figure 22 Cross-sectional view of the range extender engine;

[0052] Figure 23 Right view of the range extender engine. Detailed implementation manners

[0053] The present invention will be described in detail below with reference to the accompanying drawings and by way of examples.

[0054] This embodiment provides a loitering munition system for a 40-mm rocket launcher, as Figure 1 shown. The loitering munition system includes a loitering munition 1, an ejection mechanism 2, and a 40-mm range extender power system 3.

[0055] The loitering munition 1 is connected to the 40-mm range extender power system 3 through the ejection mechanism 2 in a folded state and is launched by a 40-mm rocket launcher. After the operation of the 40-mm range extender power system 3 ends, the loitering munition 1 is separated from the 40-mm range extender power system 3 under the ejection action of the ejection mechanism 2. The loitering munition 1 unfolds and locks itself for loitering. After the shooter determines the target based on the target image transmitted back by the loitering munition 1, the shooter controls the loitering munition 1 to attack the target.

[0056] The loitering munition 1 includes a quadrotor UAV 1-1, a warhead 1-2, a video seeker 1-3, and a connecting tube 1-4; the connecting tube 1-4 is of a cylindrical structure, and a groove for the rotor of the quadrotor UAV 1-1 to unfold and extend is provided on the wall of the connecting tube 1-4; the quadrotor UAV 1-1 is fixed at one end of the connecting tube 1-4, and the rotor is located inside the connecting tube 1-4 in the folded state, and the video seeker 1-3 is fixed at the other end of the connecting tube 1-4; the warhead 1-2 is fixedly connected to the quadrotor UAV 1-1 and is located inside the connecting tube 1-4.

[0057] The quadrotor UAV 1-1 includes a base 1-1-1, a rotor assembly 1-1-2, a spring plunger 1-1-3, a pin shaft 1-1-4, and a double torsion spring 1-1-5; the rotor assembly 1-1-2 is rotatably connected to the base 1-1-1 through the pin shaft 1-1-4, and at the same time, the double torsion spring 1-1-5 is sleeved on the pin shaft 1-1-4; a spring plunger 1-1-3 is provided between the rotor assembly 1-1-2 and the base 1-1-1. When the rotor assembly 1-1-2 is in the folded state, the head of the spring plunger 1-1-3 is in a compressed state under the pressure of the side wall of the rotor assembly 1-1-2. When the rotor assembly 1-1-2 is in the unfolded state, the head of the spring plunger 1-1-3 extends out and inserts into the locking hole on the rotor assembly 1-1-2 to lock the rotor assembly 1-1-2.

[0058] As shown in FIGS. 3(a), 3(b), Figure 4As shown in the figure, the base 1-1-1 includes a bottom cover 1-1-1-1, a base housing 1-1-1-2, a firing plate 1-1-1-3, a receiver 1-1-1-4, a flight controller 1-1-1-5, a U-shaped block 1-1-1-6, a battery 1-1-1-8 and a sleeve 1-1-1-9; four U-shaped blocks 1-1-1-6 are arranged at one end of the base housing 1-1-1-2 and are evenly fixed along the circumferential direction of the base housing 1-1-1-2 for installing the rotor assembly 1-1-2; the firing plate 1-1-1-3, the receiver 1-1-1-4, the flight controller 1-1-1-5, and the battery 1-1-1-8 are fixed inside the base housing 1-1-1-2. The receiver 1-1-1-4 receives signals and transmits them to the flight controller 1-1-1-5 to control the flight attitude of the cruise missile 1; the sleeve 1-1-1-9 is radially installed on the outer circumference of the base housing 1-1-1-2, and the sleeve 1-1-1-9 is used to place the initiator, and the lead wire of the initiator is connected to the firing plate 1-1-1-3; the other end of the base housing 1-1-1-2 is closed by the bottom cover 1-1-1-1.

[0059] During installation, first install the U-shaped block 1-1-1-6 on the base housing 1-1-1-2 through the fixing screw 1-1-1-7, then fix the firing plate 1-1-1-3, the receiver 1-1-1-4, the flight controller 1-1-1-5, and the battery 1-1-1-8 inside the base housing 1-1-1-2, and connect all parts with connecting wires at the same time. Pay attention to the positions of the connecting wires during installation. The connecting wire between the electronic speed controller 1-1-2-6 and the transmitter 1-3-4 should pass through the wire routing hole on the base housing 1-1-1-2. Install the sleeve 1-1-1-9 in the hole VI on the base housing 1-1-1-2, then place the initiator 2-4 in the sleeve 1-1-1-9, connect the lead wire of the initiator 2-4 to the firing plate 1-1-1-3, and finally connect the bottom cover 1-1-1-1 to the base housing 1-1-1-2.

[0060] As Figure 5 , Figure 6 shown in the figure, the rotor assembly 1-1-2 includes an upper blade clamp 1-1-2-1, a blade 1-1-2-2, a lower blade clamp 1-1-2-3, a motor 1-1-2-4, a motor flange 1-1-2-5, an electronic speed controller 1-1-2-6 and a cantilever 1-1-2-10; the blade 1-1-2-2 is fixed by the upper blade clamp 1-1-2-1 and the lower blade clamp 1-1-2-3 to form a rotor, and the rotor is fixed on the motor 1-1-2-4. The motor 1-1-2-4 is fixed on the cantilever 1-1-2-10 through the motor flange 1-1-2-5; the rotor is parallel to the cantilever 1-1-2-10, and the electronic speed controller 1-1-2-6 is arranged in the groove of the cantilever 1-1-2-10; the rotor expands to both sides under the drive of the motor.

[0061] During installation, first clamp the blade 1-1-2-2 with the upper blade clamp 1-1-2-1 and the lower blade clamp 1-1-2-3, and fix it with screws at the same time. Then fix the entire blade structure on the motor 1-1-2-4 with screws, and fix the motor 1-1-2-4 on the motor flange 1-1-2-5 with screws. Then the motor flange 1-1-2-5 is fixed on the cantilever 1-1-2-10 through the fixing screws 1-1-2-7, washers 1-1-2-8 and nuts 1-1-2-9. Fix the electronic speed controller 1-1-2-6 at the bottom of the motor flange 1-1-2-5. The assembly methods of the other three groups of rotor structures are the same.

[0062] After assembling the rotor assembly 1-1-2, install the rotor assembly 1-1-2 on the U-shaped block 1-1-1-6 on the base 1-1-1, as Figure 7 , Figure 8 , Figure 9 , Figure 10 shown. When installing, first insert the cantilever 1-1-2-10 into the U-shaped block 1-1-1-6, and at the same time ensure that the hole Ⅰ on the U-shaped block 1-1-1-6 is aligned with the hole Ⅲ on the cantilever 1-1-2-10. Then put the double torsion spring 1-1-5 into the inside of the cantilever 1-1-2-10, and at the same time ensure that the axis of the double torsion spring 1-1-5 is aligned with the hole Ⅲ on the cantilever 1-1-2-10. Then insert the pin shaft 1-1-4 so that it passes through the hole Ⅰ on the U-shaped block 1-1-1-6, the hole Ⅲ on the cantilever 1-1-2-10 and the inner hole of the double torsion spring 1-1-5 in sequence. Install the spring plunger 1-1-3 at the hole Ⅱ on the U-shaped block 1-1-1-6 through threaded connection. When the rotor assembly 1-1-2 is in the folded state, the head of the spring plunger 1-1-3 is in the compressed state under the pressure of the side wall of the cantilever 1-1-2-10. When the rotor assembly 1-1-2 is in the unfolded state, the head of the spring plunger 1-1-3 extends out and inserts into the hole Ⅳ on the cantilever 1-1-2-10 to lock the rotor assembly 1-1-2. The other three groups of rotor assemblies 1-1-2 are installed in the same way to complete the installation of the quadcopter drone.

[0063] As Figure 11 shown, the warhead 1-2 includes a rear head 1-2-1, a charge 1-2-2, a warhead shell 1-2-3, and a fuse 1-2-4. First, load the charge 1-2-2 onto the warhead shell 1-2-3, and install the rear head 1-2-1 on the warhead shell 1-2-3 at the same time. Then install the fuse 1-2-4 from the other end of the warhead shell 1-2-3, and the lead wire of the fuse 1-2-4 is connected to the firing plate 1-1-1-3 inside the base 1-1-1.

[0064] As Figure 12 , Figure 13As shown, the video guidance head 1-3 includes an optical lens 1-3-1, a camera 1-3-2, a hood 1-3-3, a transmitter 1-3-4, and a pressure cover 1-3-5. First, the optical lens 1-3-1 is bonded to the bottom groove of the hood 1-3-3, then the camera 1-3-2 and the transmitter 1-3-4 are fixed inside the hood 1-3-3, the antenna of the transmitter 1-3-4 is passed through the antenna hole on the hood 1-3-3, and the transmitter 1-3-4 is connected to the camera 1-3-2 with a data transmission line, and finally the battery power line led out from the base 1-1 is connected to the transmitter 1-3-4, and then the pressure cover 1-3-5 is connected to the hood 1-3-3 through a thread, and the assembly of the video guidance head 1-3 is completed.

[0065] After the assembly of the quad-rotor drone 1-1 is completed, the warhead 1-2 is first fixed to the base shell 1-1-1-2, and then the quad-rotor drone 1-1 is connected to the video guidance head 1-3 through the connecting tube 1-4 and fixed with screws to complete the assembly of the cruise missile 1.

[0066] like Figure 15 As shown, the ejection mechanism 2 includes a support 2-1, a compression spring 2-2, a compression screw 2-3 and an initiating device 2-4; the support 2-1 is arranged in the base shell 1-1-1-2, and is used to limit the deployment of the cantilever 1-1-2-10; at the same time, the support 2-1 compresses the compression spring 2-2 in the base shell 1-1-1-2; the compression screw 2-3 is radially installed and connected to the sleeve 1-1-1-9, and the initiating device 2-4 is arranged in the sleeve 1-1-1-9.

[0067] like Figure 2 , Figure 16 , Figure 17 As shown, when installing the cartridge case 2-1, the rotor structure 1-1-2 should be folded in advance, firstly, one end of the compression spring 2-2 is attached to the bottom cover 1-1-1-1, and then the cartridge case 2-1 is inserted into the base shell 1-1-1-2 to compress the compression spring 2-2. During the insertion process, when the hole Ⅶ on the cartridge case 2-1 is aligned with the hole Ⅵ on the base shell 1-1-1-2, the compression state at this time is maintained, the medicine bag is placed in the sleeve 1-1-1-9, and then the compression screw 2-3 is installed, and the compression screw 2-3 is connected to the sleeve 1-1-1-9 through a threaded connection, and the cartridge case 2-1 and the base shell 1-1-1-2 are positioned, and at the same time, the extension wall VIII of the cartridge case 2-1 presses against the plane V of the cantilever 1-1-2-10 to prevent it from being unfolded, and finally the cartridge case 2-1 is connected to the shell 3-4-1 in the 40mm extended-range power system 3 through a screw connection.

[0068] like Figure 18As shown in the figure, the 40mm extended-range power system 3 includes a soft launch engine 3-1, a dual-channel firing tail rod 3-2, a flight engine 3-3, and an extended-range engine 3-4; the soft launch engine 3-1, the dual-channel firing tail rod 3-2, the flight engine 3-3, and the extended-range engine 3-4 are connected in sequence from the tail; the soft launch engine 3-1, the dual-channel firing tail rod 3-2, and the flight engine 3-3 are located inside the 40mm rocket launcher, and the extended-range engine 3-4 is located in the over-caliber part.

[0069] As Figure 19 shown, the soft launch engine 3-1 is composed of a front head 3-1-1, a power connection piece seat 3-1-2, a power connection piece 3-1-3, a screw 3-1-4, a nut 3-1-5, a propellant hanging plate 3-1-6, a propellant charge 3-1-7, a housing 3-1-8, a plug cover I 3-1-9, and a nozzle body 3-1-10.

[0070] The propellant charge 3-1-7 is fixed on the propellant hanging plate 3-1-6, the propellant hanging plate 3-1-6 is fixed inside the housing 3-1-8, the front end of the housing 3-1-8 is fixedly connected to the front head 3-1-1, and the rear end is fixedly connected to the nozzle body 3-1-10. At the same time, the plug cover I 3-1-9 is encapsulated at the rear end; the power connection piece 3-1-3 is fixed inside the power connection piece seat 3-1-2, the power connection piece seat 3-1-2 is fixed inside the front head 3-1-1 through the screw 3-1-4, and the nut 3-1-5 is installed on the screw 3-1-4.

[0071] When assembling the soft launch engine 3-1, first place the power connection piece 3-1-3 into the square groove on the power connection piece seat 3-1-2 and fix it on the power connection piece seat 3-1-2 with a rivet. Then install the power connection piece seat 3-1-2 on the front head 3-1-1 through the screw 3-1-4. When installing, the screw 3-1-4 fits with the front head 3-1-1. Then install the nut 3-1-5 on the screw 3-1-4 through threaded connection and fix it with glue. Next, insert the propellant charge 3-1-7 into the hole on the propellant hanging plate 3-1-6 and fix it with glue. Then screw the propellant hanging plate 3-1-6 into the housing 3-1-8 through threaded connection and screw it in place. After that, screw the front head 3-1-1 and the housing 3-1-8 together through threaded connection and screw them in place. Finally, install the plug cover I 3-1-9 at the rear end of the housing 3-1-8, connect the nozzle body 3-1-10 to the housing 3-1-8 through threaded connection, and when the nozzle body 3-1-10 is screwed in place, the plug cover I 3-1-9 can be fixed.

[0072] As Figure 20As shown, the double - path firing tail rod 3 - 2 is composed of a tail rod 3 - 2 - 1, a fin 3 - 2 - 2, a torsion spring 3 - 2 - 3, a fin shaft 3 - 2 - 4, a delay - firing adapter plate 3 - 2 - 5, an overload switch 3 - 2 - 6, a firing circuit base 3 - 2 - 7, a retaining cover 3 - 2 - 8, a motor base 3 - 2 - 9, a motor baffle 3 - 2 - 10, and a magneto 3 - 2 - 11.

[0073] The motor base 3 - 2 - 9 is fixed at one end of the tail rod 3 - 2 - 1. The magneto 3 - 2 - 11 is installed on the motor base 3 - 2 - 9, and the motor baffle 3 - 2 - 10 is installed on the magneto 3 - 2 - 11. The firing circuit base 3 - 2 - 7 is fixed at the other end of the tail rod 3 - 2 - 1. The overload switch 3 - 2 - 6 is fixed on the firing circuit base 3 - 2 - 7, and at the same time, the end is fixedly connected to the delay - firing adapter plate 3 - 2 - 5. The wire led out from the delay - firing adapter plate 3 - 2 - 5 is led out through the wire groove and wire hole of the firing circuit base 3 - 2 - 7, and then led out from the wire groove of the motor base 3 - 2 - 9. The retaining cover 3 - 2 - 8 is installed at the bottom of the motor base 3 - 2 - 9 to protect the wire. The fin 3 - 2 - 2 is rotatably installed on the tail rod at the end of the firing circuit base 3 - 2 - 7 through the fin shaft 3 - 2 - 4. At the same time, one leg of one end of the torsion spring 3 - 2 - 3 is inserted into the hole of the tail rod 3 - 2 - 1, and the other end passes through the slot of the fin 3 - 2 - 2.

[0074] The gunpowder gas generated at the bottom 3 - 3 - 3 of the combustion chamber of the flight engine 3 - 3 is transmitted to the magneto 3 - 2 - 11. The magneto 3 - 2 - 11 does work to generate a double - path electromotive force, which is transmitted by two wires. One wire is connected to the delay - firing adapter plate 3 - 2 - 5 to detonate the propellant column 3 - 1 - 7 of the soft - launch engine 3 - 1, and the other wire charges the capacitor in the delay - firing adapter plate 3 - 2 - 5. When the cruise missile system breaks away from the launch tube, the fin 3 - 2 - 2 opens. When the delay reaches the set time, the delay - firing adapter plate 3 - 2 - 5 controls the capacitor to discharge, igniting the electric igniter 3 - 3 - 2 of the flight engine 3 - 3.

[0075] When assembling the double - path firing tail rod 3 - 2, first fix the overload switch 3 - 2 - 6 to the firing circuit base 3 - 2 - 7 with screws. At the same time, the wires led out from the delay - firing adapter plate 3 - 2 - 5 are led out through the wire groove and wire holes of the firing circuit base 3 - 2 - 7. Then, insert the firing circuit base 3 - 2 - 7 into the rear - end hole of the tail rod 3 - 2 - 1, and at the same time, lead the wires out from the tail - rod hole. Then, fix the delay - firing adapter plate 3 - 2 - 5 and the firing circuit base 3 - 2 - 7 to the tail rod 3 - 2 - 1 with screws. Next, lead the wires led out from the delay - firing adapter plate 3 - 2 - 5 out through the wire groove of the motor base 3 - 2 - 9. Then, bond the motor base 3 - 2 - 9 to the step of the front - end hole of the tail rod 3 - 2 - 1 with glue, and screw the retaining cover 3 - 2 - 8 to the bottom of the motor base 3 - 2 - 9 to protect the wires. After that, sequentially install the motor baffle 3 - 2 - 10 and the magneto 3 - 2 - 11 on the motor base 3 - 2 - 9. Insert the leg at one end of the torsion spring 3 - 2 - 3 into the hole of the tail rod 3 - 2 - 1, and the other end passes through the slot of the vane 3 - 2 - 2. Pass the vane shaft 3 - 2 - 4 through the hole of the torsion spring 3 - 2 - 3, the hole of the tail rod 3 - 2 - 1, and the hole of the vane 3 - 2 - 2 in sequence. When the tail rod 3 - 2 passes through the barrel, the vane 3 - 2 - 2 can automatically open under the action of the torsion spring 3 - 2 - 3.

[0076] As Figure 21 shown, the flight engine 3 - 3 is composed of a standard engine 3 - 3 - 1, an electric igniter 3 - 3 - 2, a combustion chamber bottom 3 - 3 - 3, a primer firing device 3 - 3 - 4, a wire retaining screw 3 - 3 - 5, and a combustion chamber compression screw 3 - 3 - 6.

[0077] The combustion chamber bottom 3 - 3 - 3 is fixed inside the standard engine 3 - 3 - 1. The electric igniter 3 - 3 - 2 is fixed at one end of the combustion chamber bottom 3 - 3 - 3. The lead wire of the electric igniter 3 - 3 - 2 passes through the middle hole on the combustion chamber bottom 3 - 3 - 3. There is a wire retaining screw 3 - 3 - 5 inside the combustion chamber bottom 3 - 3 - 3 to protect the lead wire of the electric igniter 3 - 3 - 2. The combustion chamber compression screw 3 - 3 - 6 is fixed at the other end of the combustion chamber bottom 3 - 3 - 3. The primer firing device 3 - 3 - 4 passes through the outer shell of the standard engine 3 - 3 - 1 and is fixed on the combustion chamber bottom 3 - 3 - 3.

[0078] During installation, first install the electric igniter 3 - 3 - 2 on the combustion chamber bottom 3 - 3 - 3 through threaded connection, and lead the lead wire of the electric igniter 3 - 3 - 2 out through the middle hole on the combustion chamber bottom 3 - 3 - 3. Then, screw the wire retaining screw 3 - 3 - 5 into the combustion chamber bottom 3 - 3 - 3 to protect the lead wire of the electric igniter 3 - 3 - 2. Next, screw the combustion chamber compression screw 3 - 3 - 6 into the combustion chamber bottom 3 - 3 - 3 through threaded connection and screw it in place. Finally, screw the combustion chamber bottom 3 - 3 - 3 into the standard engine 3 - 3 - 1. After screwing it in place, insert the primer firing device 3 - 3 - 4 into the outer shell of the standard engine 3 - 3 - 1 and the combustion chamber bottom 3 - 3 - 3 in sequence, and fix it with glue after installation.

[0079] As Figure 22 , Figure 23 shown, the range extender engine 3-4 is composed of a housing 3-4-1, a charge 3-4-2, a rear end cover heat insulation 3-4-3, a throat liner 3-4-4, a bushing 3-4-5, a nozzle body 3-4-6, a rear end cover 3-4-7, an electric igniter 3-4-8, a plug cover II 3-4-9, and an ignition cartridge 3-4-10.

[0080] One end of the housing 3-4-1 is closed and the other end is open, and the open end is fixedly connected to the rear end cover 3-4-7; the nozzle body 3-4-6 is obliquely arranged on the outer surface of the rear end cover 3-4-7, the throat liner 3-4-4 is fixed in the nozzle body 3-4-6 through the bushing 3-4-5, and the plug cover II 3-4-9 closes the outlet of the nozzle body 3-4-6; the rear end cover heat insulation 3-4-3 is arranged inside the rear end cover 3-4-7; the charge 3-4-2 is arranged inside the housing 3-4-1, the electric igniter 3-4-8 is fixed on the rear end cover 3-4-7, and the electric igniter 3-4-8 is connected to the charge 3-4-2 through an ignition charge. The ignition charge is arranged inside the ignition cartridge 3-4-10.

[0081] During installation, first, evenly apply silicone rubber on the outer surface of the bushing 3-4-5 and the inner surface of the nozzle body 3-4-6, and then insert the bushing 3-4-5 into the nozzle body 3-4-6; then evenly apply silicone rubber on the external threads of the nozzle body 3-4-6 with the bushing 3-4-5 installed, and apply a small amount of silicone rubber on the internal threads of the rear end cover 3-4-7 connected to the nozzle body 3-4-6, and then screw the nozzle body 3-4-6 onto the rear end cover 3-4-7 until it is screwed in place; then when installing the throat liner 3-4-4, first evenly apply a certain amount of silicone rubber on the outer surface of the throat liner 3-4-4 and the inner surface of the bushing 3-4-5, and then insert the throat liner 3-4-4 into the bushing 3-4-5. The other side of the nozzle body 3-4-6 is installed onto the rear end cover 3-4-7 in the same way; after the throat liner 3-4-4, the bushing 3-4-5 and the nozzle body 3-4-6 are installed, then install the rear end cover heat insulation 3-4-3. First, evenly apply silicone rubber on the conical surface of the rear end cover 3-4-7, and then insert the rear end cover heat insulation 3-4-3 into the rear end cover 3-4-7. The holes on the conical surface of the rear end cover heat insulation 3-4-3 should be coaxial with the center of the throat liner 3-4-4; bond the pre-made wool felt pad to the rear end cover heat insulation 3-4-3 with sealant; finally, bond the plug cover 3-4-9 inside the nozzle body 3-4-6. Then load the charge 3-4-2 into the housing 3-4-1, and then evenly apply silicone rubber on the threads of the electric igniter 3-4-8 and screw it onto the rear end cover 3-4-7. Pour the ignition charge into the ignition charge box 3-4-10, then seal the ignition charge box 3-4-10, bond the ignition charge box 3-4-10 to the inner surface in the middle of the rear end cover heat insulation 3-4-3, and finally thread-connect the rear end cover 3-4-7 and the housing 3-4-1 and then screw them together until they are in place.

[0082] When assembling the 40mm extended-range power system 3, first insert the combustion chamber bottom 3-3-11 in the flight engine 3-3 into the front end of the middle rod 3-2-1 of the dual-channel percussion tail rod 3-2, and at the same time ensure that the threaded holes on the combustion chamber bottom 3-3-11 are aligned with the counterbored holes at the front end of the rod 3-2-1, and then fix it with screws. Secondly, screw the internal threads of the front head 3-1-1 in the soft launch engine 3-1 onto the external threads at the rear end of the middle rod 3-2-1 of the dual-channel percussion tail rod 3-2 and screw it in place. Finally, screw the threaded part at the tail of the rear end cover 3-4-7 in the extended-range engine 3-4 into the nozzle 3-3-1 of the flight engine 3-3 and screw it in place to complete the assembly of the 40mm extended-range power system 3.

[0083] The working state of the entire loitering munition full system is as Figure 1As shown, when it is in the working state, first, the entire projectile flies to the target area under the gunpowder thrust of the soft launch engine 3-1, the flight engine 3-3, and the range extension engine 3-4. At the initial stage of the descent of the entire loitering munition system, the firing plate 1-1-1-3 is controlled by a ground remote controller to ignite the initiator 2-4 and the charge package in the sleeve 1-1-1-9. Under the action of the gunpowder, the compression screw 2-3 is ejected, and then the projectile holder 2-1 is separated from the base housing 1-1-1-2 under the action of the compression spring 2-2. At this time, the rotor assembly 1-1-2 is released from the restraint of the projectile holder 2-1 and is opened by the torsion provided by the double torsion spring 1-1-5, as Figure 14 shown. The spring plunger 1-1-3 locks it, and then the quadrotor UAV 1-1 is made to work through the ground remote controller. The loitering munition 1 loiters over the target area. The ground receiver receives the images transmitted back from the camera 1-3-2. When a target is found, the ground remote controller controls the loitering munition 1 to fly towards the target. When approaching the target, the fuse 1-2-4 is fired by remotely controlling the firing plate 1-1-1-3, causing the warhead 1-2 to explode, thereby damaging the target. In addition, the warhead 1-2 can also damage the target by detonating the warhead upon collision with the target.

[0084] In summary, the above is only a preferred embodiment of the present invention and is not intended to limit the protection scope of the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A loitering munition system for 40-mm rocket launcher, characterized in that, The loitering munition system includes a loitering munition, a catapult mechanism, and a 40mm extended-range power system; The loitering munition is connected to the 40mm extended-range power system through the catapult mechanism in a folded state and is launched through a 40mm rocket launcher. After the operation of the 40mm extended-range power system ends, the loitering munition is separated from the 40mm extended-range power system under the catapult action of the catapult mechanism. The loitering munition unfolds and locks itself for loitering. After the shooter determines the target based on the target image transmitted back by the loitering munition, the shooter controls the loitering munition to attack the target; The loitering munition includes a quadrotor UAV, and the quadrotor UAV includes a base, a rotor assembly, a spring plunger, a pin shaft, and a double torsion spring; the base includes a bottom cover, a base housing, a firing plate, a receiver, a flight controller, a U-shaped block, a battery, and a sleeve; four U-shaped blocks are arranged at one end of the base housing and are evenly fixed along the circumferential direction of the base housing for installing the rotor assembly; The firing plate, the receiver, the flight controller, and the battery are fixed inside the base housing; the sleeve is radially installed on the outer circumference of the base housing, and the sleeve is used to place the pyrotechnic device, and the lead wire of the pyrotechnic device is connected to the firing plate; the other end of the base housing is closed by the bottom cover.

2. The loitering munition system for 40-mm rocket launcher launch according to claim 1, characterized in that, The loitering munition further includes a warhead, a video seeker, and a connecting cylinder; The connecting cylinder is a cylindrical structure, and a groove for the rotor of the quadrotor UAV to unfold and extend is provided on the connecting cylinder wall; The quadrotor UAV is fixed at one end of the connecting cylinder, and the rotor is located inside the connecting cylinder in the folded state, and the video seeker is fixed at the other end of the connecting cylinder; the warhead is fixedly connected to the quadrotor UAV and is located inside the connecting cylinder.

3. The loitering munition system for 40-mm rocket launcher according to claim 2, wherein, The rotor assembly is rotatably connected to the base through the pin shaft, and at the same time, the double torsion spring is sleeved on the pin shaft; a spring plunger is provided between the rotor assembly and the base. When the rotor assembly is in the folded state, the head of the spring plunger is in a compressed state under the pressure of the side wall of the rotor assembly. When the rotor assembly is in the unfolded state, the head of the spring plunger extends and inserts into the locking hole on the rotor assembly to lock the rotor assembly.

4. The loitering munition system for 40-mm rocket launcher launch according to claim 3, wherein, The rotor assembly includes an upper blade clamp, a blade, a lower blade clamp, a motor, a motor flange, an electronic speed controller, and a cantilever; The blade is fixed to form a rotor through the upper blade clamp and the lower blade clamp. The rotor is fixed on the motor, and the motor is fixed on the cantilever through the motor flange; the rotor is parallel to the cantilever, and the electronic speed controller is fixed at the bottom of the motor flange; the rotor unfolds to both sides under the drive of the motor.

5. The loitering munition system for 40-mm rocket launcher according to claim 1, characterized in that, The catapult mechanism includes a projectile carrier, a compression spring, a compression screw, and a pyrotechnic device; The projectile carrier is arranged inside the base housing and is used to limit the unfolding of the cantilever; at the same time, the projectile carrier compresses the compression spring inside the base housing; the compression screw is radially installed and connected to the sleeve, and the pyrotechnic device is arranged inside the sleeve.

6. The loitering munition system for 40-mm rocket launcher as claimed in claim 1, wherein, The 40mm extended-range power system includes a soft launch engine, a dual-channel firing tail rod, a flight engine, and an extended-range engine; The soft launch engine, the dual-channel firing tail rod, the flight engine, and the extended-range engine are connected in sequence from the tail; the soft launch engine, the dual-channel firing tail rod, and the flight engine are located inside the 40mm rocket launcher, and the extended-range engine is located in the over-caliber part.

7. The loitering munition system for 40-mm rocket launcher as claimed in claim 6, wherein, The soft launch engine includes a front head, an electricity connection piece seat, an electricity connection piece, a medicine hanging plate, a propellant charge, a housing, a plug cover I, and a nozzle body; The grain is fixed on the hanging grain plate, and the hanging grain plate is fixed inside the housing. The front end of the housing is fixedly connected to the front head, and the rear end is fixedly connected to the nozzle body. At the same time, the plug cover I is encapsulated at the rear end; the electrical connection piece is fixed inside the electrical connection piece seat, and the electrical connection piece seat is fixed inside the front head.

8. The loitering munition system for 40-mm rocket launcher launch according to claim 6, characterized in that, The dual-channel firing tail rod includes a tail rod, fins, a torsion spring, a delay firing adapter plate, an overload switch, a firing circuit seat, a motor seat and a magneto; The motor seat is fixed at one end of the tail rod, the magneto is installed on the motor seat, the firing circuit seat is fixed at the other end of the tail rod, the overload switch is fixed on the firing circuit seat, and at the same time, the end is fixedly connected to the delay firing adapter plate; the fins are rotatably installed on the tail rod at the end of the firing circuit seat. At the same time, one leg of one end of the torsion spring is inserted into the tail rod hole, and the other end passes through the fin groove; The magneto does work to generate a dual-channel electromotive force, which is transmitted by two wires. One wire is connected to the delay firing adapter plate to detonate the grain of the soft launch engine, and the other wire charges the capacitor in the delay firing adapter plate. When the cruise missile system breaks away from the launch tube, the fins open; when the delay reaches the set time, the delay firing adapter plate controls the capacitor to discharge, igniting the electric igniter of the flight engine.

9. The loitering munition system for 40-mm rocket launcher according to claim 6, characterized in that, The range extension engine includes a housing, a charge, a rear end cover heat insulation, a throat liner, a bushing, a nozzle body, a rear end cover, an electric igniter, a plug cover II and ignition powder; One end of the housing is closed and the other end is open, and the open end is fixedly connected to the rear end cover; the nozzle body is obliquely arranged on the outer surface of the rear end cover, the throat liner is fixed in the nozzle body through the bushing, and the plug cover II closes the outlet of the nozzle body; the rear end cover heat insulation is arranged inside the rear end cover; the charge is arranged inside the housing, the electric igniter is fixed on the rear end cover, and the electric igniter is connected to the charge through the ignition powder.

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