Air defense interception device with automatic ejection net and method

Abstract

The invention discloses an intercepting device and method with an automatic catapulting net, the intercepting device comprises a missile head, a connector, the catapulting net and an engine, the automatic catapulting net is added on the basis of an existing intercepting missile, a plurality of guidance propelling devices are installed on the catapulting net, and after being launched, the intercepting device can be automatically catapulted when approaching an enemy target aircraft by a certain distance. The catapulting net of the intercepting device catapults at the same time under propelling of the multiple guidance propelling devices, and an intercepting net with a large intercepting area is automatically and cooperatively formed in the air to intercept a target. The interception success rate of the enemy aircraft is increased, the defects of an existing interception device are eliminated or made up, 'one net is used up 'is achieved, it is ensured that no'fish leakage' exists in the enemy target aircraft, and heavy property loss or heavy casualties of an interception party are avoided or reduced.

Description

Technical Field

[0001] The invention belongs to the technical field of military defense, and in particular relates to an air defense interception device and method with an automatic ejection net. Background Art

[0002] In modern military combat, the success rate of intercepting aircraft such as missiles and drones often determines the victory or defeat and the extent of losses of the intercepting party.

[0003] Although existing interception devices, such as interceptor missiles, have relatively precise guidance systems, the interception success rate is not high due to the fast flying speed, small size and small interception area of ​​the missiles of both sides, and there are often "fish slipping through the net". If the guidance system of the interceptor missile has deviations, the interception failure rate will be even higher, which will cause major property losses or casualties to the intercepting party. Summary of the invention

[0004] The purpose of the present invention is to provide an interception device and method with an automatic ejection net. On the basis of an existing interception missile, an automatic ejection net is added, and a plurality of guidance propulsion devices are installed on the ejection net. After the interception device is launched and approaches an enemy target aircraft at a certain distance, the ejection net of the interception device is ejected simultaneously under the propulsion of the plurality of guidance propulsion devices, and automatically and cooperatively forms an interception net with a larger interception area in the air. The interception net flies toward the enemy target aircraft in a "net-pulling" manner, and the interception net first catches and then destroys the enemy target aircraft, thereby improving the success rate of intercepting the enemy target aircraft.

[0005] If multiple interceptors are launched synchronously, each interceptor will automatically open the catapult net synchronously when it approaches the enemy target aircraft at a certain distance, and automatically coordinate in formation in the air to form a combined interception net with a larger interception area, and fly towards the enemy target aircraft in a "dragnet-like" manner. The combined interception net has a larger interception area, which greatly improves the success rate of intercepting enemy aircraft, eliminates or compensates for the defects of existing interception devices, achieves "one net catches all", ensures that no enemy target aircraft "slips through the net", and avoids or reduces major property losses or casualties on the intercepting party.

[0006] The technical solution of the present invention is an air defense interception device with an automatic ejection net, comprising a missile head, a connector, an ejection net and an engine.

[0007] The connector is a hollow cylinder used for embedded connection between the missile head and the engine, and is also used for installing and storing the ejection net. One end of the connector is connected to the missile head with embedded rivets or threads, and the other end of the connector is connected to the engine with embedded rivets or threads. The ejection net is installed on the connector. After launch, the ejection net can fly synchronously with the connector to the enemy target aircraft, or it can automatically separate from the connector and fly to the enemy target aircraft alone.

[0008] The connector includes an axial through hole and an axial cylindrical cavity inside, and a plurality of evenly distributed axial grooves around the outside for storing the guided propulsion device of the catapult net. The head of each axial groove is a through groove, which serves as a launching channel for the guided propulsion device of the catapult net, and the tail of each axial groove is a closed blind groove; each axial groove has a certain outward inclination along the axial direction, so that the guided propulsion device is in an upward-looking state after installation, which is convenient for the upward-looking launching of the guided propulsion device; each axial groove is provided with an axial opening of a certain length for passing the flexible net rope of the catapult net; the internal axial through hole is used for cable routing and weight reduction, and the internal axial cylindrical cavity is used for storing the flexible net rope of the catapult net.

[0009] The catapult net includes a plurality of flexible net ropes and a plurality of guided propulsion devices; the plurality of flexible net ropes pass through the axial openings of the corresponding axial grooves of the connector, one end of the flexible net ropes is fixed on the corresponding guided propulsion device, and the other end is fixed on the base of the axial cylindrical cavity inside the connector, or is orderly scattered in the axial cylindrical cavity inside the connector, so that the flexible net ropes can fly with the connector as needed, or can be automatically separated from the connector and fly alone; the guided propulsion device includes a guidance system, a propeller and a control module, which are used for the guidance and propulsion of the catapult net.

[0010] Under normal circumstances, each guided propulsion device is stored in an external axial groove of the connector and does not exceed the outer circle of the connector; under normal circumstances, multiple flexible net ropes are folded and contracted in an orderly manner in the axial cylindrical cavity inside the connector; the multiple refers to two or more.

[0011] The missile head includes an outer shell, a guidance system, an ammunition compartment, and a power module; the guidance system, the ammunition compartment, and the power module are installed inside the outer shell; the guidance system is connected to the control module of the catapult net through a wired cable, and the guidance system is connected to the control module of the engine through a wired cable, and the cable passes through an axial through hole inside the connector; the power module is used to provide power to the guidance system.

[0012] The engine includes an outer casing, a compressor, fuel, an oxidant, a control module, and a tail nozzle. The compressor, fuel, an oxidant, and a control module are installed inside the outer casing to propel the missile's flight.

[0013] Furthermore, the connector can be used alone as a launching seat for the catapult net to independently launch the catapult net.

[0014] Furthermore, multiple flexible net ropes are connected vertically and horizontally, and are made of light and tough material; electromagnetic jammers or micro bombs are provided on the flexible net ropes to interfere with or blow up enemy aircraft; the flexible net ropes can be twisted ropes or micro buckle chain ropes.

[0015] Furthermore, the guidance system includes a radar system, an AI visual recognition module, a navigation module, and a control module, which are used to detect the distance, flight direction, attitude, position, altitude, and speed of the enemy target aircraft in real time, and control the flight direction, attitude, altitude, and speed of the guidance propulsion device itself, so as to guide the guidance propulsion device to fly accurately to the target object along a suitable trajectory.

[0016] The radar system includes multiple radar distance sensors, which are used to detect the distance of enemy target aircraft. It is also used for auxiliary detection of the distance between teammates' guided propulsion devices, so as to maintain coordination and synchronization with teammates' guided propulsion devices during flight and maintain a certain flight distance between each other, thus forming a dragnet-style flight.

[0017] The AI ​​visual recognition module is an artificial intelligence visual recognition module, including a high-definition camera and a computer. It is used to quickly identify the target objects around the guided propulsion device in real time during flight, whether it is a teammate's guided propulsion device and its spatial position and horizontal distance from itself. If it is a teammate's guided propulsion device and the horizontal distance to the teammate's guided propulsion device is lower than the set value, a signal is sent to the control module of the guidance system, and the guidance system sends a signal to the engine, and the engine automatically adjusts the flight direction, speed and altitude to maintain the horizontal distance between itself and the teammate's guided propulsion device, and cooperate to form a dragnet flight.

[0018] The interception method of an air defense interception device with an automatic ejection net of the present invention comprises the following steps: Step 1: The air defense monitoring and early warning system sends the number, track, direction, attitude, altitude and speed information of incoming enemy target aircraft to the interception system.

[0019] Step 2: The interception system determines whether to launch a single interceptor or multiple interceptors based on the enemy target information.

[0020] Step 3: If a single interceptor is launched, the missile guidance system will automatically start after launch to monitor the flight direction, attitude, altitude, speed, and distance of the enemy target aircraft in real time, and adjust the interceptor's own flight direction, attitude, altitude, and speed in real time through the guidance system and engine to fly towards the enemy target aircraft along a suitable trajectory.

[0021] Step 4: When the interceptor device approaches a certain distance from the enemy target aircraft, the missile guidance system transmits the distance signal of the enemy target aircraft to the control modules of multiple guidance propulsion devices of the catapult network at the same time.

[0022] Step 5: The control module of the multiple guided propulsion devices of the catapult net controls the ignition action of the propulsion engine to automatically eject the guided propulsion devices in the axial groove outside the connector.

[0023] Step 6: Each guided propulsion device of the catapult net drives its own flexible net rope respectively. Driven by its own propulsion device and guided by the guidance system, it adjusts the flight direction, attitude, altitude and speed of each guided propulsion device in real time, and automatically cooperates to form an interception net with a larger interception area in the air. According to the flight direction, attitude, altitude and speed of the enemy target aircraft, the interception net flies towards the enemy target aircraft in a "net-like" manner, and destroys the enemy target aircraft using the "electromagnetic interference-netting-impacting-bombing" operation method.

[0024] Step 7: If multiple interceptors are launched synchronously, each interceptor will turn on its guidance system after launch, and each will monitor the flight direction, attitude, altitude, speed, and distance of the enemy target aircraft in real time. At the same time, it will monitor the flight direction, attitude, altitude, speed, and mutual distance of each teammate's interceptor device, and adjust the flight direction, attitude, altitude, and speed of each interceptor device in real time through the guidance system and engine, so that each interceptor device can always be coordinated and synchronized during flight. Each interceptor device also maintains a certain flight distance from each other, automatically flies in formation, and each flies toward the enemy target aircraft in coordination along a suitable trajectory.

[0025] Step 8: When each intercepting device approaches a certain distance from the enemy target aircraft, its respective guidance system simultaneously transmits the distance signal between itself and the enemy target aircraft to the control modules of multiple guidance propulsion devices of the catapult network of each intercepting device.

[0026] Step 9: The control modules of the guidance propulsion devices of the ejection nets of the interception devices respectively control the ignition actions of their respective thrusters to eject the guidance propulsion devices in the axial grooves outside their respective connectors.

[0027] Step 10: Each guided propulsion device of each catapult net drives its own flexible net rope respectively. Driven by its own propeller and guided by the guidance system, it adjusts the flight direction, attitude, altitude and speed of each guided propulsion device of each catapult net in real time, and automatically cooperates to form an interception net with a larger interception area in the air, and then cooperates to form a combined interception net with a larger interception area. The combined interception net flies towards the enemy target aircraft in a "net-pulling" manner according to the flight direction, attitude, altitude and speed of the enemy target aircraft. Each interception device jointly adopts the "electromagnetic interference-netting-impacting-blasting" operation mode to destroy the enemy target aircraft.

[0028] The beneficial technical effects of the present invention are: After the interception device of the present invention is launched, when it approaches the enemy target aircraft at a certain distance, the ejection net of the interception device is ejected simultaneously under the propulsion of multiple guidance propulsion devices, and automatically cooperates to form an interception net with a larger interception area in the air. The interception net flies toward the enemy target aircraft in a "dragnet-like" manner, thereby improving the success rate of intercepting the enemy target aircraft; if multiple interception devices are launched simultaneously, each missile will automatically and synchronously open the ejection net when it approaches the enemy target aircraft at a certain distance, and automatically cooperate in formation to form a combined interception net with a larger interception area in the air, and the combined "dragnet-like" fly toward the enemy target aircraft. The combined interception net has a larger interception area, which greatly improves the success rate of intercepting the enemy aircraft, achieving "one net catches everything", ensuring that the enemy target aircraft does not "slip through the net", and avoiding or reducing major property losses or major casualties on the intercepting party. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 It is a stereoscopic diagram of the interception device of the present invention in a normal state.

[0030] Figure 2 It is a separated stereogram of the interception device of the present invention in a normal state.

[0031] Figure 3 It is a three-dimensional diagram of the ejection net and the connector integrated into one when the interception device of the present invention is in the launching state.

[0032] Figure 4 It is a stereoscopic diagram of the interception device of the present invention in a state where the catapult net and the connector are separated when the interception device is in a launching state.

[0033] Figure 5 It is a front view of the interception device of the present invention in a normal state.

[0034] Figure 6 yes Figure 5 A-A view of.

[0035] Figure 7 yes Figure 5 B-B view.

[0036] Figure 8 yes Figure 5 Top view of the .

[0037] Fig. 9 It is a front view of the interception device of the present invention in a launching state where the catapult net and the connector are integrated.

[0038] Fig.10 yes Fig. 9 Top view of the .

[0039] Fig.11 yes Fig. 9 C-C view of the .

[0040] Fig.12 It is a front view of the interception device of the present invention in a state where the catapult net and the connector are separated when the interception device is in a launching state.

[0041] In the figure: 1. missile head, 2. connector, 3. catapult net, 4. engine, 5. axial through hole, 6. axial cylindrical cavity, 7. axial groove, 8. axial opening, 9. flexible net rope, 10. guided propulsion device. DETAILED DESCRIPTION

[0042] The present invention is further described in detail below with reference to the accompanying drawings and specific implementation methods.

[0043] An air defense interception device with an automatic ejection net according to the present invention is as follows Figure 1 As shown, it includes a missile head 1, a connector 2, a catapult net 3 and an engine 4.

[0044] The connector 2 is a hollow cylinder, which is used for embedded connection between the missile head 1 and the engine 4, and is also used for installing and storing the ejection net 3. One end of the connector 2 is connected to the missile head 1 by embedded rivets or threads, and the other end of the connector 2 is connected to the engine 4 by embedded rivets or threads; the ejection net 3 is installed on the connector 2. After launching, the ejection net 3 can fly synchronously with the connector 2 toward the enemy target aircraft, and can also automatically separate from the connector 2 and fly toward the enemy target aircraft alone.

[0045] Connector 2 Figure 2 and Figure 6 As shown, the axial through hole 5 and the axial cylindrical cavity 6 are provided inside. Figure 3 and Figure 5 As shown, a plurality of evenly distributed axial grooves 7 are provided around the outside of the connector 2 for storing the guidance and propulsion device 10 of the catapult net 3. Figure 5 As shown, the head of each axial slot 7 is a through slot, which serves as a launching channel for the guided propulsion device 10 of the catapult net 3, and the tail of each axial slot 7 is a closed blind slot. Each axial slot 7 has a certain outward inclination along the axial direction, so that the guided propulsion device 10 is in an upward-looking state after installation, which is convenient for the upward-looking launching of the guided propulsion device 10; each axial slot 7 is provided with an axial opening 8 of a certain length for passing the flexible net rope 9 of the catapult net 3; the internal axial through hole 5 is used for cable routing and weight reduction, and the internal axial cylindrical cavity 6 is used to store the flexible net rope 9 of the catapult net 3.

[0046] like Figure 3 , Figure 4 As shown, the catapult net 3 includes a plurality of flexible net ropes 9 and a plurality of guided propulsion devices 10. Figure 6 , Figure 7As shown, a plurality of flexible net ropes 9 pass through the axial openings 8 of the corresponding axial grooves 7 of the connector 2, with one end fixed to the corresponding guidance and propulsion device 10, and the other end fixed to the base of the axial cylindrical cavity 6 inside the connector 2, or scattered in an orderly manner in the axial cylindrical cavity 6 inside the connector 2, so that the flexible net ropes 9 can fly with the connector 2 as needed, or can automatically separate from the connector 2 and fly alone; the guidance and propulsion device 10 includes a guidance system, a propeller and a control module, which are used for guiding and propulsion of the catapult net 3.

[0047] Under normal circumstances, Figure 8 As shown, each guided propulsion device 10 is stored in the external axial groove 7 of the connector 2 and does not exceed the outer circle of the connector 2; under normal conditions, multiple flexible net ropes 9 are folded and contracted in an orderly manner in the axial cylindrical cavity 6 inside the connector 2; the multiple refers to two or more.

[0048] The missile head 1 includes a shell, a guidance system, an ammunition compartment, and a power module; the guidance system, the ammunition compartment, and the power module are installed inside the shell; the guidance system is connected to the control module of the catapult net 3 through a wired cable, and the guidance system is connected to the control module of the engine 4 through a wired cable, and the cable passes through the axial through hole 5 inside the connector 2; the power module is used to provide power to the guidance system.

[0049] The engine 4 includes a housing, a compressor, fuel, an oxidant, a control module, and a tail nozzle. The compressor, fuel, oxidant, and control module are installed inside the housing to propel the missile to fly. The engine belongs to the conventional method in this field, and can be a rocket engine and a jet engine. The rocket engine can be a solid rocket engine and a liquid rocket engine.

[0050] Furthermore, the connector 2 can be used alone as a launching seat for the catapult net 3 to launch the catapult net 3 independently.

[0051] Further, such as Fig. 9 , Fig.10 , Fig.11 As shown, multiple flexible net ropes 9 are connected vertically and horizontally, and are made of light and tough material; electromagnetic jammers or micro bombs are provided on the flexible net ropes 9 to interfere with or blow up enemy aircraft; the flexible net ropes 9 can be twisted ropes or micro buckle chain ropes.

[0052] Furthermore, the guidance system includes a radar system, an AI visual recognition module, a navigation module, and a control module, which are used to detect the distance, flight direction, attitude, position, altitude, and speed of the enemy target aircraft in real time, and control the flight direction, attitude, altitude, and speed of the guidance propulsion device 10 itself, and guide the guidance propulsion device 10 to accurately fly to the target object along a suitable track. The guidance method of the guidance system belongs to the conventional method in this field, including radio guidance, inertial guidance, homing guidance, terrain matching guidance, remote control guidance, wired guidance, etc.

[0053] The radar system includes multiple radar distance sensors, which are used to detect the distance of enemy target aircraft, and are also used for auxiliary detection of the distance between teammates' guided propulsion devices 10, so as to maintain coordination and synchronization with teammates' guided propulsion devices 10 during flight and maintain a certain flight distance between each other, thereby forming a dragnet-style flight.

[0054] The AI ​​visual recognition module is an artificial intelligence visual recognition module, including a high-definition camera and a computer, which is used to quickly and in real time identify the target objects around the guided propulsion device 10 during flight, whether it is a teammate guided propulsion device 10 and its spatial position and horizontal distance from itself. If it is a teammate guided propulsion device 10 and the horizontal distance from the teammate guided propulsion device 10 is lower than the set value, a signal is sent to the control module of the guidance system, and the guidance system sends a signal to the engine, and the engine automatically adjusts the flight direction, speed and altitude to maintain the horizontal distance from the teammate guided propulsion device 10, and cooperate to form a dragnet flight.

[0055] The working principle of AI visual recognition module is: (1) Collect training characteristic data of the target aircraft.

[0056] A certain number of target aircraft images or video data such as shape, size, pixels, brightness, and color are collected in advance as training sample images or videos, and representative feature information of the target aircraft is extracted from the images or videos. After processing, the information is stored in a computer to form a training feature image library or video library of the target aircraft.

[0057] (2) Collect characteristic data of the target aircraft in the application scenario.

[0058] The camera converts the captured scene target aircraft into an image signal, and processes the captured feature information such as the shape, size, direction, attitude, altitude, speed, pixels, brightness, color, etc. of the scene target aircraft through a computer image processing system, and then extracts the image or video features of the scene target aircraft.

[0059] (3) Identification and judgment of target aircraft in application scenarios.

[0060] The computer will match and compare the captured feature image or video of the target aircraft with the images or videos in the feature image library to determine whether the target aircraft in the scene is a teammate missile and its spatial position. It will determine the horizontal distance from the target aircraft based on its size and then send a signal to the engine, which will automatically adjust the flight direction, speed and altitude to maintain the horizontal distance from the teammate missile and fly in coordination.

[0061] The propulsion device includes an engine, which includes an outer shell, a compressor, fuel, an oxidant, a control module, and a tail nozzle. The compressor, fuel, oxidant, and control module are installed inside the outer shell to propel the flight of the missile. The engine belongs to the conventional method in this field and can be a rocket engine and a jet engine. The rocket engine can be a solid rocket engine and a liquid rocket engine.

[0062] The invention discloses an interception method of an air defense interception device with an automatic ejection net. Once the air defense monitoring and early warning system detects and finds that an enemy target aircraft is flying, the enemy aircraft is intercepted according to the following method steps: Step 1: The air defense monitoring and early warning system sends enemy target information such as the number, track, direction, attitude, altitude, and speed of incoming enemy target aircraft to the interception system.

[0063] Step 2: The interception system determines whether to launch a single interceptor or multiple interceptors based on the enemy target information.

[0064] Step 3: If a single interceptor is launched, the missile guidance system will automatically start after launch to monitor the flight direction, attitude, altitude, speed, and distance of the enemy target aircraft in real time, and adjust the interceptor's own flight direction, attitude, altitude, and speed in real time through the guidance system and engine to fly towards the enemy target aircraft along a suitable trajectory.

[0065] Step 4: When the interception device approaches a certain distance from the enemy target aircraft, the missile guidance system transmits the distance signal of the enemy target aircraft to the control modules of the multiple guidance propulsion devices 10 of the catapult network 3 at the same time.

[0066] Step 5: The control module of the multiple guided propulsion devices 10 of the ejection net 3 controls the ignition action of the propulsion engine to automatically eject the guided propulsion devices 10 in the external axial grooves 7 of the connector 2.

[0067] Step 6: The respective guided propulsion devices 10 of the catapult net 3 drive their respective flexible net ropes 9, and under the drive of their respective propulsion devices and the guidance of the guidance system, adjust the flight direction, attitude, altitude and speed of each guided propulsion device 10 in real time, and automatically cooperate to form an interception net with a larger interception area in the air. Fig.12As shown, according to the flight direction, attitude, altitude and speed of the enemy target aircraft, the interception net flies towards the enemy target aircraft in a "dragnet-like" manner, and destroys the enemy target aircraft using the "electromagnetic interference-netting-impact-bombing" operation method.

[0068] Step 7: If multiple interceptors are launched synchronously, each interceptor will turn on its guidance system after launch, and each will monitor the flight direction, attitude, altitude, speed, and distance of the enemy target aircraft in real time. At the same time, they will monitor each other's flight direction, attitude, altitude, speed, and mutual distance, and adjust each interceptor's own flight direction, attitude, altitude, and speed in real time through the guidance system and engine, so that each interceptor can always be coordinated and synchronized during flight. Each interceptor also maintains a certain flight distance (such as 50 meters) from each other, and automatically flies in formation, each flying toward the enemy target aircraft along a suitable trajectory.

[0069] Step 8: When each interception device approaches a certain distance (such as 500 meters) from the enemy target aircraft, its respective guidance system simultaneously transmits the distance signal between itself and the enemy target aircraft to the control modules of the multiple guidance propulsion devices 10 of the catapult network 3 of each interception device.

[0070] Step 9: The control modules of the guided propulsion devices 10 of the ejection nets 3 of the respective interception devices respectively control the ignition actions of their respective thrusters to eject the guided propulsion devices 10 in the external axial grooves 7 of their respective connectors 2.

[0071] Step 10: Each guided propulsion device 10 of each catapult net 3 drives its own flexible net rope 9 respectively. Under the drive of each propulsion device and the guidance of the guidance system, the guided propulsion device 10 of each catapult net 3 adjusts its own flight direction, attitude, height and speed in real time, automatically and cooperatively forms an interception net with a larger interception area in the air, and then cooperates to form a combined interception net with a larger interception area. The combined interception net is based on the flight direction, attitude, height and speed of the enemy target aircraft. The interception net combination "pull net style" flies to the enemy target aircraft, and each interception device jointly adopts the "electromagnetic interference-net-impact-bombing" operation mode to destroy the enemy target aircraft. Effective interception of enemy target aircraft is achieved, and the success rate of interception of enemy aircraft is further improved. Even if the guidance system of each interception device is slightly deviated, the enemy target aircraft can be effectively intercepted to ensure that the enemy target aircraft does not "slip through the net", avoiding or reducing major property losses or major casualties of the intercepting party.

[0072] Although the specific implementation of the invention is described in detail in conjunction with the drawings, it should not be understood as limiting the scope of protection of this patent. Within the scope described in the claims, various modifications and variations that can be made by those skilled in the art without creative work still fall within the scope of protection of this patent.

Claims

1. An air defense interception device with an automatic ejection net, characterized in that: It comprises a missile head (1), a connector (2), a catapult net (3) and an engine (4); The connector (2) is a hollow cylinder, used for embedded connection between the missile head (1) and the engine (4), and also used for installing and storing the ejection net (3); one end of the connector (2) is connected to the missile head (1) by an embedded rivet or thread, and the other end of the connector (2) is connected to the engine (4) by an embedded rivet or thread; the ejection net (3) is installed on the connector (2), and after launching, the ejection net (3) can fly towards the enemy target aircraft synchronously with the connector (2), or can automatically separate from the connector (2) and fly towards the enemy target aircraft alone; The connector (2) includes an axial through hole (5) and an axial cylindrical cavity (6) provided inside, and a plurality of evenly distributed axial grooves (7) provided around the outside for storing the guided propulsion device (10) of the catapult net (3). The head of each axial groove (7) is a through groove, which serves as a launching channel for the guided propulsion device (10) of the catapult net (3), and the tail of each axial groove (7) is a closed blind groove. Each axial groove (7) is inclined outwardly at a certain angle along the axial direction, so that the guided propulsion device (10) is in an upward-looking state after installation, which facilitates the upward-looking launching of the guided propulsion device (10). Each axial groove (7) is provided with an axial opening (8) of a certain length for passing the flexible net rope (9) of the catapult net (3). The internal axial through hole (5) is used for cable routing and weight reduction, and the internal axial cylindrical cavity (6) is used for storing the flexible net rope (9) of the catapult net (3). The catapult net (3) comprises a plurality of flexible net ropes (9) and a plurality of guided propulsion devices (10); the plurality of flexible net ropes (9) pass through the axial openings (8) of the corresponding axial grooves (7) of the connector (2), one end of which is fixed to the corresponding guided propulsion device (10), and the other end of which is fixed to the base of the axial cylindrical cavity (6) inside the connector (2), or is orderly scattered in the axial cylindrical cavity (6) inside the connector (2), so that the flexible net ropes (9) can fly together with the connector (2) or automatically separate from the connector (2) and fly alone as required; the guided propulsion device (10) comprises a guidance system, a propeller and a control module, and is used for guiding and propelling the catapult net (3); Under normal conditions, each guided propulsion device (10) is stored in an external axial groove (7) of the connecting body (2) and does not exceed the outer circle of the connecting body (2); under normal conditions, a plurality of flexible net ropes (9) are folded and contracted in an orderly manner in an internal axial cylindrical cavity (6) of the connecting body (2); the plurality refers to two or more; The missile head (1) comprises a shell, a guidance system, an ammunition compartment, and a power module; the guidance system, the ammunition compartment, and the power module are installed inside the shell; the guidance system is connected to a control module of a catapult net (3) via a wired cable, and the guidance system is connected to a control module of an engine via a wired cable, and the cable passes through an axial through hole (5) inside the connector (2); the power module is used to provide power to the guidance system; The engine (4) comprises a casing, a compressor, fuel, an oxidant, a control module, and a tail nozzle; the compressor, fuel, an oxidant, and a control module are installed inside the casing and are used to propel the missile into flight.

2. The air defense interception device with an automatic ejection net according to claim 1, characterized in that: The connector (2) can be used alone as a launching seat for the catapult net (3) to independently launch the catapult net (3).

3. The air defense interception device with an automatic ejection net according to claim 1, characterized in that: The multiple flexible net ropes (9) are connected in a longitudinal and transverse state and are made of a light and tough material; an electromagnetic jammer or a micro-bomb is provided on the flexible net rope (9) for interfering with or blowing up enemy aircraft; the flexible net rope (9) can be a twisted rope or a micro buckle chain rope.

4. The air defense interception device with an automatic ejection net according to claim 1, characterized in that: The guidance system comprises a radar system, an AI visual recognition module, a navigation module, and a control module, and is used to detect the distance, flight direction, attitude, position, altitude, and speed of the enemy target aircraft in real time, and to control the flight direction, attitude, altitude, and speed of the guidance propulsion device (10) itself, so as to guide the guidance propulsion device (10) to accurately fly to the target object along a suitable track; The radar system comprises a plurality of radar distance sensors for detecting the distance of an enemy target aircraft and for assisting in distance detection between teammate guided propulsion devices (10), so as to maintain coordination and synchronization with teammate guided propulsion devices (10) during flight and maintain a certain flight distance between them, thereby forming a dragnet flight; The AI ​​visual recognition module is an artificial intelligence visual recognition module, comprising a high-definition camera and a computer, and is used to quickly and in real time identify target objects around the guided propulsion device (10) during flight, whether it is a teammate guided propulsion device and its spatial position and horizontal distance from itself; if it is a teammate guided propulsion device (10) and the horizontal distance from the teammate guided propulsion device (10) is lower than a set value, a signal is sent to a control module of the guidance system, and the guidance system then sends a signal to the engine, so that the engine automatically adjusts the flight direction, speed and altitude to maintain the horizontal distance from the teammate guided propulsion device (10), thereby collaboratively forming a dragnet flight.

5. The interception method of an air defense interception device with an automatic ejection net according to any one of claims 1 to 4, characterized in that: The following steps are involved: Step 1: The air defense monitoring and early warning system sends the number, track, direction, attitude, altitude, and speed information of the incoming enemy target aircraft to the interception system; Step 2: The interception system determines whether to launch a single interceptor or multiple interceptors based on the enemy target information; Step 3: If a single interceptor is launched, the missile guidance system will be automatically turned on after launch to monitor the flight direction, attitude, altitude, speed and distance of the enemy target aircraft in real time, and adjust the flight direction, attitude, altitude and speed of the interceptor itself in real time through the guidance system and engine to fly towards the enemy target aircraft along a suitable trajectory; Step 4: When the interception device approaches a certain distance from the enemy target aircraft, the missile guidance system transmits the distance signal of the enemy target aircraft to the control modules of the multiple guidance propulsion devices (10) of the catapult net (3) at the same time; Step 5: The control module of the multiple guided propulsion devices (10) of the catapult net (3) controls the ignition action of the propulsion engine to automatically eject the guided propulsion devices (10) in the external axial groove (7) of the connector (2); Step 6: The respective guided propulsion devices (10) of the catapult net (3) drive their respective flexible net ropes (9) respectively. Under the drive of their respective propulsion devices and the guidance of the guidance system, the flight direction, attitude, altitude and speed of each guided propulsion device (10) are adjusted in real time, and an interception net with a large interception area is automatically formed in cooperation in the air. According to the flight direction, attitude, altitude and speed of the enemy target aircraft, the interception net "pull net style" flies towards the enemy target aircraft, and destroys the enemy target aircraft by adopting the operation mode of "electromagnetic interference - netting - impact - explosion"; Step 7: If multiple interceptors are launched synchronously, each interceptor will turn on its guidance system after launch, and each will monitor the flight direction, attitude, altitude, speed, and distance of the enemy target aircraft in real time. At the same time, each teammate's interceptor will monitor the flight direction, attitude, altitude, speed, and mutual distance of each other, and adjust the flight direction, attitude, altitude, and speed of each interceptor in real time through the guidance system and engine, so as to always keep the interceptors coordinated and synchronized during the flight. Each interceptor will also keep a certain flight distance from each other, automatically coordinate formation flight, and each will coordinately fly toward the enemy target aircraft along a suitable trajectory; Step 8: When each interception device approaches a certain distance from the enemy target aircraft, the respective guidance systems simultaneously transmit the distance signals between each interception device and the enemy target aircraft to the control modules of the plurality of guidance propulsion devices (10) of the catapult net (3) of each interception device; Step 9: The control modules of the guided propulsion devices (10) of the ejection nets (3) of the respective interception devices respectively control the ignition action of their respective thrusters to eject the guided propulsion devices (10) in the external axial grooves (7) of their respective connectors (2); Step 10: Each guided propulsion device (10) of each catapult net (3) drives its own flexible net rope (9) respectively. Under the drive of its own propulsion device and the guidance of the guidance system, the guided propulsion device (10) of each catapult net (3) adjusts its own flight direction, attitude, altitude and speed in real time, automatically and cooperatively forms an interception net with a larger interception area in the air, and then cooperates to form a combined interception net with a larger interception area. The combined interception net is based on the flight direction, attitude, altitude and speed of the enemy target aircraft. The interception net combination "pull net style" flies towards the enemy target aircraft, and each interception device jointly adopts the "electromagnetic interference-net-catching-impact-bombing" operation mode to destroy the enemy target aircraft.

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