Image terminal guided rocket projectile weapon system based on ground auxiliary identification

Abstract

The invention belongs to the technical field of guided weapons, and particularly relates to an image terminal guided rocket projectile weapon system based on ground auxiliary recognition. The system comprises an image terminal guided rocket projectile, a ground image control system, a box-type rocket gun, a command vehicle and an unmanned aerial vehicle reconnaissance relay system. The image terminal guidance rocket projectile adopts a satellite / inertial combination guidance + data link target image return ground target auxiliary identification + image terminal guidance mode, and is used for accurate striking and damage of a target. According to the system, under the condition that a satellite is disturbed, the precise striking capability on a fixed target and a land or sea surface moving target can be realized.

Description

Technical Field

[0001] The invention belongs to the technical field of guided weapons, and in particular relates to an image terminally guided rocket weapon system based on ground auxiliary recognition. Background Art

[0002] With the development of microelectronics technology, guidance and control technology, and the pursuit of precision strike and efficient destruction capabilities in combat operations, precision guidance of weapons has become the main direction and trend of the development of various types of weapons. In recent years, the guidance of field rocket weapons has been its most important and fastest-growing research direction. Field rockets have developed simple control and satellite inertial combined guidance. Although the simple control scheme has developed to a certain extent due to its low cost, it has gradually withdrawn from the development sequence due to its limited control capabilities and inability to achieve precision strikes. Satellite inertial composite guidance technology has been widely used in field long-range, long-range and ultra-long-range guided rocket weapon systems due to its advantages such as improved satellite positioning accuracy and all-weather use. Satellite inertial composite guidance has the problem that the accuracy of inertial guidance will be greatly reduced as the range increases after the satellite is interfered with. At the same time, the above guidance method cannot achieve strikes on moving targets. Summary of the invention

[0003] 1. Technical issues to be resolved

[0004] The technical problem to be solved by the present invention is: how to construct a field rocket weapon system for realizing the precision strike capability against fixed targets and mobile targets on land or sea when the satellite is interfered.

[0005] (II) Technical solution

[0006] In order to solve the above technical problems, the present invention provides an image terminal guided rocket weapon system based on ground auxiliary recognition, the system comprising: an image terminal guided rocket, a ground image control system, a box rocket launcher, a command vehicle, and an unmanned aerial vehicle reconnaissance relay system; wherein,

[0007] The image terminal guidance rocket adopts satellite / inertial combined mid-range guidance + data link target image return ground target auxiliary identification + image terminal guidance mode, which is used for precise attack and damage to the target;

[0008] The ground image control system is used to set the wireless communication frequency, the ground data link antenna tracking direction, receive and display the flight parameters of the guided rocket and the seeker image, identify the target in the seeker image, generate the corresponding target number, and use the human-computer interaction to realize the operator's confirmation of the target to be attacked, and send the target information confirmed by the operator to the missile-borne image data transmission device;

[0009] The box-type rocket launcher is used to receive combat mission information and instructions from the command vehicle and complete the launch preparation and launch of the guided rocket;

[0010] The command vehicle is used for planning weapon system combat missions, allocating targets, issuing combat orders and evaluating combat results;

[0011] The UAV reconnaissance relay system is mainly used for target area image acquisition and target coordinate measurement in the early stage of combat, as well as relay of communication between the guided rocket and the ground image control system in the final stage of flight.

[0012] The image terminal guided rocket includes a head cover, an image seeker, a flight control device, an inertial navigation device, a satellite positioning device, an onboard image data transmission device, an onboard power supply, a steering gear, a power unit, a warhead, a fuze and necessary structures and electrical components;

[0013] The nose cover is used to form the required low aerodynamic drag shape with the missile body structure, reduce the drag of the guided rocket during flight, and automatically detach from the guided rocket at the end of the flight by giving a command from the flight control device;

[0014] The image seeker is used to collect images of the target area, track the target based on the target information identified on the ground, and give the line-of-sight angular velocity of the tracked target;

[0015] The flight control device is used to integrate the inertial navigation device, satellite positioning device, seeker information and guidance control strategy to form control instructions, and send them to the steering gear to control the flight of the guided rocket;

[0016] The inertial navigation device is used to measure the overload, speed, position, attitude angular velocity and attitude angle parameters of the guided rocket during flight in the inertial coordinate system and the launch coordinate system;

[0017] Satellite positioning devices are used to measure the position and speed of guided rockets during flight;

[0018] The missile-borne image data transmission device is used to compress and encode the flight parameters of the guided rocket and the image of the seeker, and transmit them to the ground image control system by wireless communication, and receive the target identification information and target locking command uploaded by the ground image control system, and decode them, and transmit them to the missile-borne flight controller and seeker;

[0019] The missile-borne power supply is used to provide working power for the image seeker, flight control device, inertial navigation device, satellite positioning device, missile-borne image data transmission device, and steering gear components during the flight of the guided rocket;

[0020] The power unit is used to provide the power required for the guided rocket to fly;

[0021] The warhead is used to explode and damage the target after hitting the target;

[0022] The fuze is used to provide insurance protection for the detonation circuit in the early stages of flight, and to detonate the warhead when the guided rocket hits the target or reaches a certain range above the target.

[0023] The image seeker is a television image seeker or an infrared image seeker, which has the ability to store 500ms seeker images. The seeker has the ability to lock and track the target in the image according to the ground target recognition result, and has the ability to check and compare the image within 200ms before the current moment. The pitch and yaw angular velocity of the seeker tracking the target is not less than 10° / s.

[0024] Wherein, the resolution of the television image seeker imaging the target area is at least 1024×1024 pixels;

[0025] The television image seeker has the capability of clearly imaging the target area at a distance of 6km to 12km from the target.

[0026] Among them, the infrared image guidance head can clearly image when the target temperature difference is greater than 5K; the imaging resolution of the infrared image guidance head is not less than 640×512 pixels; and the imaging distance of the infrared image guidance head is not less than 6km.

[0027] Among them, the flight control device is an embedded computer device, which is used to realize the flight timing control of the guided rocket, receive the target information, flight control parameters and other parameters set by the rocket launcher, receive the guided rocket flight parameters given by the inertial navigation device and the satellite positioning device, receive the target line of sight angular velocity sent by the seeker, and receive the seeker operation instructions uploaded by the ground image control system received by the missile-borne image data transmission device; integrate the received information and generate the guided rocket flight control instructions through the pre-installed guidance and control model.

[0028] Wherein, the inertial navigation device is a strapdown inertial navigation device, which has the ability to process the three-direction attitude angular velocity, three-direction attitude angle, three-direction velocity and three-direction position coordinates of the guided rocket at the current moment in the inertial coordinate system;

[0029] The satellite positioning device and the inertial navigation device form a navigation device through information fusion, which further improves the accuracy of measuring flight parameters.

[0030] The satellite positioning device adopts a 4-element anti-interference antenna to achieve interference with active broadband jammers in no less than 3 directions;

[0031] The systems adopted by the satellite positioning device include: the GPS satellite positioning system of the United States and the Beidou navigation satellite system of China.

[0032] Among them, the missile-borne image data transmission device has a wireless image transmission bandwidth of 2.5Mbps; the missile-borne image data transmission device adopts a response working mode, and can only send a synchronization signal when it receives a synchronization signal from a ground image data transmission device; the missile-borne image data transmission device can only transmit images downward in one direction, and can realize upward and downward bidirectional transmission of data; the missile-borne image transmission device has the function of compressing the video image sent by the seeker without damaging the resolution.

[0033] Wherein, the power unit adopts a solid rocket engine; the solid rocket engine is a single-chamber dual-reasoning solid rocket engine.

[0034] The warhead is a prefabricated fragmentation-killing warhead, which causes damage to personnel and various combat equipment through the fragments after the explosion; the fuze adopts a proximity fuze or a trigger fuze.

[0035] Wherein, the ground image manipulation system comprises a ground image manipulation device, a ground image data transmission device and an auxiliary recognition unit;

[0036] The ground image manipulation device further includes an image information processor, an image processing display component, a chassis, an operating handle, and an operating keyboard;

[0037] The ground image data transmission device includes a data link antenna, an image data transmission processing device, and an antenna lodging tracking mechanism;

[0038] The data link antenna is a wide beam phased array antenna, which has the ability to communicate with two guided rocket-borne image data transmission devices at the same time, and also has the ability to communicate with a drone-borne data relay station;

[0039] The image data transmission and processing device has the ability to simultaneously process the image data transmitted by two guided rockets;

[0040] The antenna prostrate tracking mechanism ensures that the antenna is in a prostrate state when in a marching state, and is raised according to instructions when it is needed to work, and realizes the pointing of the antenna to the flight trajectory of the guided rocket according to the antenna position and the target coordinates provided by the command vehicle;

[0041] The auxiliary target recognition unit includes a high-speed image processor and an intelligent algorithm module based on offline training, and has the ability to select and recognize targets of 10 pixels in a 1024×1024 pixel image.

[0042] The auxiliary target recognition unit is used to determine in real time the position, size and accurate probability of recognition of the target recognized in the seeker image;

[0043] The auxiliary target recognition unit is integrated in the chassis of the ground image manipulation device; the auxiliary recognition unit should transmit the target position, size and recognition probability to the ground image manipulation device in real time;

[0044] The ground image control device superimposes the received information on the seeker image sent by the ground image transmission device in real time, and displays it on the display screen in real time.

[0045] The operating handle is used for the operator to interact with the ground image manipulation device. The operator locks and unlocks the target locking frame on the display screen and moves the cross frame on the display screen to lock the target.

[0046] The keyboard is used for the operator to interact with the ground image control device. The operator inputs the target coordinates, data link communication frequency, guided rocket number, and confirmed target number information through the keyboard;

[0047] The operating handle and the keyboard are both integrated and installed on the ground image control device box;

[0048] The ground image control device and the ground image data transmission device exchange data via Ethernet;

[0049] The ground image control device sends the target information confirmed by the operator through the handle and keyboard to the ground image data transmission device, and the ground image transmission device sends the information to the missile-borne image data transmission device, which in turn transmits it to the guidance head to realize target identification and locking.

[0050] (III) Beneficial effects

[0051] Compared with the prior art, the image terminal-guided rocket weapon system based on ground target auxiliary recognition proposed by the present invention can carry out long-range precision strikes and strike mobile targets on land and sea when satellites are interfered. BRIEF DESCRIPTION OF THE DRAWINGS

[0052] Figure 1 The weapon system composition relationship of the present invention;

[0053] Figure 2 The composition and layout of the image terminal guided rocket of the present invention;

[0054] Figure 3 The composition and information flow of the ground image control system of the present invention;

[0055] Figure 4 This is a schematic diagram of information flow of the present invention;

[0056] Figure 5 The figure is a flowchart of the system of the present invention. DETAILED DESCRIPTION

[0057] In order to make the purpose, content and advantages of the present invention more clear, the specific implementation methods of the present invention are further described in detail below in conjunction with the drawings and examples.

[0058] In order to solve the above technical problems, the present invention provides an image terminal guided rocket weapon system based on ground auxiliary recognition, the system comprising: an image terminal guided rocket, a ground image control system, a box rocket launcher, a command vehicle, and an unmanned aerial vehicle reconnaissance relay system; wherein,

[0059] The image terminal guidance rocket adopts satellite / inertial combined mid-range guidance + data link target image return ground target auxiliary identification + image terminal guidance mode, which is used for precise attack and damage to the target;

[0060] The ground image control system is used to set the wireless communication frequency, the ground data link antenna tracking direction, receive and display the flight parameters of the guided rocket and the seeker image, identify the target in the seeker image, generate the corresponding target number, and use the human-computer interaction to realize the operator's confirmation of the target to be attacked, and send the target information confirmed by the operator to the missile-borne image data transmission device;

[0061] The box-type rocket launcher is used to receive combat mission information and instructions from the command vehicle and complete the launch preparation and launch of the guided rocket;

[0062] The command vehicle is used for planning weapon system combat missions, allocating targets, issuing combat orders and evaluating combat results;

[0063] The UAV reconnaissance relay system is mainly used for target area image acquisition and target coordinate measurement in the early stage of combat, as well as relay of communication between the guided rocket and the ground image control system in the final stage of flight.

[0064] The image terminal guided rocket includes a head cover, an image seeker, a flight control device, an inertial navigation device, a satellite positioning device, an onboard image data transmission device, an onboard power supply, a steering gear, a power unit, a warhead, a fuze and necessary structures and electrical components;

[0065] The nose cover is used to form the required low aerodynamic drag shape with the missile body structure, reduce the drag of the guided rocket during flight, and automatically detach from the guided rocket at the end of the flight by giving a command from the flight control device;

[0066] The image seeker is used to collect images of the target area, track the target based on the target information identified on the ground, and give the line-of-sight angular velocity of the tracked target;

[0067] The flight control device is used to integrate the inertial navigation device, satellite positioning device, seeker information and guidance control strategy to form control instructions, and send them to the steering gear to control the flight of the guided rocket;

[0068] The inertial navigation device is used to measure the overload, speed, position, attitude angular velocity and attitude angle parameters of the guided rocket during flight in the inertial coordinate system and the launch coordinate system;

[0069] Satellite positioning devices are used to measure the position and speed of guided rockets during flight;

[0070] The missile-borne image data transmission device is used to compress and encode the flight parameters of the guided rocket and the image of the seeker, and transmit them to the ground image control system by wireless communication, and receive the target identification information and target locking command uploaded by the ground image control system, and decode them, and transmit them to the missile-borne flight controller and seeker;

[0071] The missile-borne power supply is used to provide working power for the image seeker, flight control device, inertial navigation device, satellite positioning device, missile-borne image data transmission device, and steering gear components during the flight of the guided rocket;

[0072] The power unit is used to provide the power required for the guided rocket to fly;

[0073] The warhead is used to explode and damage the target after hitting the target;

[0074] The fuze is used to provide insurance protection for the detonation circuit in the early stages of flight, and to detonate the warhead when the guided rocket hits the target or reaches a certain range above the target.

[0075] The image seeker is a television image seeker or an infrared image seeker, which has the ability to store 500ms seeker images. The seeker has the ability to lock and track the target in the image according to the ground target recognition result, and has the ability to check and compare the image within 200ms before the current moment. The pitch and yaw angular velocity of the seeker tracking the target is not less than 10° / s.

[0076] Wherein, the resolution of the television image seeker imaging the target area is at least 1024×1024 pixels;

[0077] The television image seeker has the capability of clearly imaging the target area at a distance of 6km to 12km from the target.

[0078] Among them, the infrared image guidance head can clearly image when the target temperature difference is greater than 5K; the imaging resolution of the infrared image guidance head is not less than 640×512 pixels; and the imaging distance of the infrared image guidance head is not less than 6km.

[0079] Among them, the flight control device is an embedded computer device, which is used to realize the flight timing control of the guided rocket, receive the target information, flight control parameters and other parameters set by the rocket launcher, receive the guided rocket flight parameters given by the inertial navigation device and the satellite positioning device, receive the target line of sight angular velocity sent by the seeker, and receive the seeker operation instructions uploaded by the ground image control system received by the missile-borne image data transmission device; integrate the received information and generate the guided rocket flight control instructions through the pre-installed guidance and control model.

[0080] Wherein, the inertial navigation device is a strapdown inertial navigation device, which has the ability to process the three-direction attitude angular velocity, three-direction attitude angle, three-direction velocity and three-direction position coordinates of the guided rocket at the current moment in the inertial coordinate system;

[0081] The satellite positioning device and the inertial navigation device form a navigation device through information fusion, which further improves the accuracy of measuring flight parameters.

[0082] The satellite positioning device adopts a 4-element anti-interference antenna to achieve interference with active broadband jammers in no less than 3 directions;

[0083] The systems adopted by the satellite positioning device include: the GPS satellite positioning system of the United States and the Beidou navigation satellite system of China.

[0084] Among them, the missile-borne image data transmission device has a wireless image transmission bandwidth of 2.5Mbps; the missile-borne image data transmission device adopts a response working mode, and can only send a synchronization signal when it receives a synchronization signal from a ground image data transmission device; the missile-borne image data transmission device can only transmit images downward in one direction, and can realize upward and downward bidirectional transmission of data; the missile-borne image transmission device has the function of compressing the video image sent by the seeker without damaging the resolution.

[0085] Wherein, the power unit adopts a solid rocket engine; the solid rocket engine is a single-chamber dual-reasoning solid rocket engine.

[0086] The warhead is a prefabricated fragmentation-killing warhead, which causes damage to personnel and various combat equipment through the fragments after the explosion; the fuze adopts a proximity fuze or a trigger fuze.

[0087] Wherein, the ground image manipulation system comprises a ground image manipulation device, a ground image data transmission device and an auxiliary recognition unit;

[0088] The ground image manipulation device further includes an image information processor, an image processing display component, a chassis, an operating handle, and an operating keyboard;

[0089] The ground image data transmission device includes a data link antenna, an image data transmission processing device, and an antenna lodging tracking mechanism;

[0090] The data link antenna is a wide beam phased array antenna, which has the ability to communicate with two guided rocket-borne image data transmission devices at the same time, and also has the ability to communicate with a drone-borne data relay station;

[0091] The image data transmission and processing device has the ability to simultaneously process the image data transmitted by two guided rockets;

[0092] The antenna prostrate tracking mechanism ensures that the antenna is in a prostrate state when in a marching state, and is raised according to instructions when it is needed to work, and realizes the pointing of the antenna to the flight trajectory of the guided rocket according to the antenna position and the target coordinates provided by the command vehicle;

[0093] The auxiliary target recognition unit includes a high-speed image processor and an intelligent algorithm module based on offline training, and has the ability to select and recognize targets of 10 pixels in a 1024×1024 pixel image.

[0094] The auxiliary target recognition unit is used to determine in real time the position, size and accurate probability of recognition of the target recognized in the seeker image;

[0095] The auxiliary target recognition unit is integrated in the chassis of the ground image manipulation device; the auxiliary recognition unit should transmit the target position, size and recognition probability to the ground image manipulation device in real time;

[0096] The ground image control device superimposes the received information on the seeker image sent by the ground image transmission device in real time, and displays it on the display screen in real time.

[0097] The operating handle is used for the operator to interact with the ground image manipulation device. The operator locks and unlocks the target locking frame on the display screen and moves the cross frame on the display screen to lock the target.

[0098] The keyboard is used for the operator to interact with the ground image control device. The operator inputs the target coordinates, data link communication frequency, guided rocket number, and confirmed target number information through the keyboard;

[0099] The operating handle and the keyboard are both integrated and installed on the ground image control device box;

[0100] The ground image control device and the ground image data transmission device exchange data via Ethernet;

[0101] The ground image control device sends the target information confirmed by the operator through the handle and keyboard to the ground image data transmission device, and the ground image transmission device sends the information to the missile-borne image data transmission device, which in turn transmits it to the guidance head to realize target identification and locking.

[0102] Example 1

[0103] The image terminal guided rocket weapon system based on ground-assisted target recognition constructed by the present invention is mainly composed of the following contents:

[0104] A command vehicle system, an unmanned aerial vehicle reconnaissance system, a rocket launcher, an image terminal-guided rocket, and a ground-assisted target recognition system, wherein the rocket launcher is a launching platform for rockets, and a rocket launcher can be loaded with 2 to 40 image terminal-guided rockets according to the size of the terminal-guided rockets; the image terminal-guided rocket is mainly composed of a seeker protection head cover, an image seeker, a flight control device, an inertial navigation device, a satellite positioning device, an on-board wireless image data transmission device, an on-board power supply, a steering gear, a solid rocket engine, a warhead, and a fuze; wherein the ground-assisted target recognition system is mainly composed of a ground image control device, a ground image data transmission device, a data link antenna, and an auxiliary target recognition unit. The system composition of the present invention is shown in FIG. Figure 1 , image terminal guidance rocket Figure 2 , ground image manipulation system see Figure 3 , system information transmission relationship see Figure 4 .

[0105] The workflow of the present invention is shown in Figure 5An example of a workflow is that the command vehicle system sends a command to command the drone reconnaissance system to conduct target reconnaissance, and transmits target images and target coordinates and other information back to the command vehicle system. The command vehicle determines the number of rockets to be used, whether the rockets are used in a man-in-the-loop attack mode or a template matching working mode, based on the reconnaissance situation and combat mission requirements. When the template matching working mode is adopted, the command vehicle completes the preparation of the target template, and transmits information such as the target template and target coordinates to each rocket launcher via a radio or wired method. The rocket launcher receives the target and combat mission, powers on the image terminal guidance rocket on the rocket launcher, completes the rocket self-check, completes the target template and coordinate setting and other preparatory work, and launches the image terminal guidance rocket. The rocket first performs a combined navigation guided flight based on the information provided by the satellite positioning device and the inertial navigation device. Before reaching the range of the seeker, the hood is jettisoned, and the seeker matches according to the set target template. When the match is successful, the seeker tracks the target and outputs the line-of-sight angular velocity of the tracked target to the flight control device. The flight control device integrates the inertial navigation device, satellite The information of the positioning device is used to generate a steering gear control command. The steering gear drives the rudder wing to deflect and control the image terminal guidance rocket to hit the target, and the fuse warhead is used to achieve accurate damage to the target. When the man-in-the-loop attack mode is adopted, the command vehicle transmits the target coordinates and other information to the rocket launcher and the ground image control system through the radio or wired communication. The rocket launcher completes a series of preparations such as the calculation of the firing angle and direction, the power-on of the image terminal guidance rocket, the information setting, and the transmission alignment. The ground image control system completes the startup of the ground image control device and the data link antenna according to the command of the command vehicle. The receiving direction is solved and adjusted, and the communication frequency is set. When the rocket launcher launches an image terminal guided rocket, the launch time is synchronized to the ground image control system. The ground image control system actively sends a synchronization signal. When the missile-borne image data transmission system receives the synchronization signal of the ground image data transmission device, it sends a response signal to establish communication with the ground image data transmission device, and sends the flight parameters of the image terminal guided rocket and the image of the seeker to the ground image data transmission device by wireless means. The ground image transmission device decodes the received information and sends it to the ground image control device and the auxiliary recognition device respectively. The ground image control device displays the received flight parameters of the image terminal guided rocket on the display screen, and superimposes the seeker image and the target coordinate information output by the auxiliary recognition unit on the seeker image and displays them on the image control device display screen at the same time. When the image terminal guided rocket flies to a certain distance from the target, the flight control device gives the seeker hood jettison instruction, the hood is jettisoned, and the seeker compresses the collected target area image through the missile-borne image data transmission device and transmits it to the ground image control system.The auxiliary recognition unit in the ground image control system processes the seeker image, identifies the target in the seeker image, and numbers the target according to the size of the real probability of target detection. The target with the highest probability is numbered as "1", and so on. A maximum of 5 targets can be distinguished, and the recognition result is sent to the ground image control device, which displays the recognition result on the display screen in real time; the operator confirms the target through the "function key" or numeric key on the keyboard according to the displayed target recognition result; the target ground image control system sends the target confirmation information to the missile-borne image data transmission device through the ground image data transmission device, and the missile-borne image transmission device further sends the target confirmation information to the seeker, and the seeker locks the target according to the target confirmation information and automatically tracks the locked target; while the seeker tracks the target, it sends the target tracking line of sight angular velocity to the flight control device, and the flight control device integrates the inertial navigation device information and the satellite positioning device information to form a flight control instruction, and sends it to the steering gear to control the image terminal guidance rocket to fly to the target, so as to achieve a precise strike on the target. ;

[0106] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the technical principles of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. An image terminal guided rocket weapon system based on ground-assisted recognition, characterized in that: The system includes: image terminal guidance rocket, ground image control system, box rocket launcher, command vehicle, and UAV reconnaissance relay system; among which, The image terminal guidance rocket adopts satellite / inertial combined mid-range guidance + data link target image return ground target auxiliary identification + image terminal guidance mode, which is used for precise attack and damage to the target; The ground image control system is used to set the wireless communication frequency, the ground data link antenna tracking direction, receive and display the flight parameters of the guided rocket and the seeker image, identify the target in the seeker image, generate the corresponding target number, and use the human-computer interaction to realize the operator's confirmation of the target to be attacked, and send the target information confirmed by the operator to the missile-borne image data transmission device; The box-type rocket launcher is used to receive combat mission information and instructions from the command vehicle and complete the launch preparation and launch of the guided rocket; The command vehicle is used for planning weapon system combat missions, allocating targets, issuing combat orders and evaluating combat results; The UAV reconnaissance relay system is mainly used for target area image acquisition and target coordinate measurement in the early stage of combat, as well as relay of communication between the guided rocket and the ground image control system in the final stage of flight.

2. The image terminal guided rocket weapon system based on ground-assisted recognition as claimed in claim 1, characterized in that: The image terminal guided rocket includes a head cover, an image seeker, a flight control device, an inertial navigation device, a satellite positioning device, an onboard image data transmission device, an onboard power supply, a steering gear, a power unit, a warhead, a fuze, and necessary structures and electrical components; wherein, The nose cover is used to form the required low aerodynamic drag shape with the missile body structure, reduce the drag of the guided rocket during flight, and automatically detach from the guided rocket at the end of the flight by giving a command from the flight control device; The image seeker is used to collect images of the target area, track the target based on the target information identified on the ground, and give the line-of-sight angular velocity of the tracked target; The flight control device is used to integrate the inertial navigation device, satellite positioning device, seeker information and guidance control strategy to form control instructions, and send them to the steering gear to control the flight of the guided rocket; The inertial navigation device is used to measure the overload, speed, position, attitude angular velocity and attitude angle parameters of the guided rocket during flight in the inertial coordinate system and the launch coordinate system; Satellite positioning devices are used to measure the position and speed of guided rockets during flight; The missile-borne image data transmission device is used to compress and encode the flight parameters of the guided rocket and the image of the seeker, and transmit them to the ground image control system by wireless communication, and receive the target identification information and target locking command uploaded by the ground image control system, and decode them, and transmit them to the missile-borne flight controller and seeker; The missile-borne power supply is used to provide working power for the image seeker, flight control device, inertial navigation device, satellite positioning device, missile-borne image data transmission device, and steering gear components during the flight of the guided rocket; The power unit is used to provide the power required for the guided rocket to fly; The warhead is used to explode and damage the target after hitting it; The fuze is used to provide insurance protection for the detonation circuit in the early stages of flight, and to detonate the warhead when the guided rocket hits the target or reaches a certain range above the target.

3. The image terminal guided rocket weapon system based on ground-assisted recognition as claimed in claim 2, characterized in that: The image seeker is a television image seeker or an infrared image seeker, and has the ability to store 500ms seeker images. The seeker has the ability to lock and track the target in the image based on the ground target recognition result, and has the ability to review and compare the image within 200ms before the current moment; the pitch and yaw angular speeds of the seeker tracking the target are not less than 10° / s.

4. The image terminal guided rocket weapon system based on ground-assisted recognition as claimed in claim 3, characterized in that: The resolution of the television image seeker imaging the target area is at least 1024×1024 pixels; The television image seeker has the ability to clearly image the target area at a distance of 6km to 12km from the target.

5. The image terminal guided rocket weapon system based on ground-assisted recognition as claimed in claim 3, characterized in that: The infrared image seeker can clearly image when the target temperature difference is greater than 5K; the imaging resolution of the infrared image seeker is not less than 640×512 pixels; and the imaging distance of the infrared image seeker is not less than 6km.

6. The image terminal guided rocket weapon system based on ground-assisted recognition as claimed in claim 2, characterized in that: The flight control device is an embedded computer device, which is used to realize the flight timing control of the guided rocket, receive the target information, flight control parameters and other parameters set by the rocket launcher, receive the flight parameters of the guided rocket given by the inertial navigation device and the satellite positioning device, receive the target line of sight angular velocity sent by the seeker, receive the seeker operation instructions uploaded by the ground image control system received by the missile-borne image data transmission device; integrate the received information, and generate the guided rocket flight control instructions through the pre-installed guidance control model.

7. The image terminal guided rocket weapon system based on ground-assisted recognition as claimed in claim 2, characterized in that: The inertial navigation device is a strapdown inertial navigation device, which has the ability to process the three-direction attitude angular velocity, three-direction attitude angle, three-direction velocity and three-direction position coordinates of the guided rocket at the current moment in the inertial coordinate system; The satellite positioning device and the inertial navigation device form a navigation device through information fusion, which further improves the accuracy of measuring flight parameters.

8. The image terminal guided rocket weapon system based on ground-assisted recognition as claimed in claim 2, characterized in that: The satellite positioning device adopts a 4-element anti-interference antenna to achieve interference with active broadband jammers in no less than 3 directions; The systems adopted by the satellite positioning device include: the GPS satellite positioning system of the United States and the Beidou navigation satellite system of China.

9. The image terminal guided rocket weapon system based on ground-assisted recognition as claimed in claim 2, characterized in that: The missile-borne image data transmission device has a wireless image transmission bandwidth of 2.5Mbps; the missile-borne image data transmission device adopts a response working mode, and can send a synchronization signal only when receiving a synchronization signal from a ground image data transmission device; the missile-borne image data transmission device can only transmit images one-way downward, and can realize up-down bidirectional transmission of data; The missile-borne image transmission device has the function of compressing the video image sent by the seeker without damaging the resolution.

10. The image terminal guided rocket weapon system based on ground-assisted recognition as claimed in claim 2, characterized in that: The power device adopts a solid rocket engine; the solid rocket engine is a single-chamber double-reason solid rocket engine. The warhead is a prefabricated fragmentation-killing warhead, which causes damage to personnel and various combat equipment through the fragments after the explosion; the fuze adopts a proximity fuze or a trigger fuze.

11. The image terminal guided rocket weapon system based on ground-assisted recognition as claimed in claim 2, characterized in that: The ground image manipulation system includes a ground image manipulation device, a ground image data transmission device and an auxiliary recognition unit; The ground image manipulation device further includes an image information processor, an image processing display component, a chassis, an operating handle, and an operating keyboard; The ground image data transmission device includes a data link antenna, an image data transmission processing device, and an antenna lodging tracking mechanism; The data link antenna is a wide beam phased array antenna, which has the ability to communicate with two guided rocket-borne image data transmission devices at the same time, and also has the ability to communicate with a drone-borne data relay station; The image data transmission and processing device has the ability to simultaneously process the image data transmitted by two guided rockets; The antenna prostrate tracking mechanism ensures that the antenna is in a prostrate state when in a marching state, and is raised according to instructions when it is needed to work, and realizes the pointing of the antenna to the flight trajectory of the guided rocket according to the antenna position and the target coordinates provided by the command vehicle; The auxiliary target recognition unit includes a high-speed image processor and an intelligent algorithm module based on offline training, and has the ability to select and recognize targets of 10 pixels in a 1024×1024 pixel image. The auxiliary target recognition unit is used to determine in real time the position, size and accurate probability of recognition of the target recognized in the seeker image; The auxiliary target recognition unit is integrated in the chassis of the ground image manipulation device; the auxiliary recognition unit should transmit the target position, size and recognition probability to the ground image manipulation device in real time; The ground image control device superimposes the received information on the seeker image sent by the ground image transmission device in real time, and displays it on the display screen in real time. The operating handle is used for the operator to interact with the ground image manipulation device. The operator locks and unlocks the target locking frame on the display screen and moves the cross frame on the display screen to lock the target. The keyboard is used for the operator to interact with the ground image control device. The operator inputs the target coordinates, data link communication frequency, guided rocket number, and confirmed target number information through the keyboard; The operating handle and the keyboard are both integrated and installed on the ground image control device box; The ground image control device and the ground image data transmission device exchange data via Ethernet; The ground image control device sends the target information confirmed by the operator through the handle and keyboard to the ground image data transmission device, and the ground image transmission device sends the information to the missile-borne image data transmission device, which in turn transmits it to the guidance head to realize target identification and locking.

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