A ground-assisted recognition-based image-guided rocket weapon system

Abstract

This invention belongs to the field of guided weapon technology, specifically relating to an image-guided terminal-guided rocket weapon system based on ground-assisted identification. The system includes: an image-guided terminal-guided rocket, a ground image control system, a box-type rocket launcher, a command vehicle, and an unmanned aerial vehicle (UAV) reconnaissance relay system. The image-guided terminal-guided rocket employs a satellite / inertial combined mid-course guidance + data link target image transmission for ground target-assisted identification + image-guided terminal guidance method, used for precise strike and destruction of targets. Even when satellites are jammed, the system can achieve precise strike capability against fixed targets and moving targets on land or sea.

Description

Technical Field

[0001] This invention belongs to the field of guided weapon technology, specifically relating to an image-guided rocket weapon system based on ground-assisted identification. Background Technology

[0002] With the development of microelectronics and guidance and control technologies, and the pursuit of precision strikes and high-efficiency destruction capabilities in combat operations, precision guidance of weapons has become the main direction and trend of weapon development. In recent years, the guidance of field rocket weapons has been the most important and fastest-growing research direction. Field rockets have developed simplified control and satellite-inertial combined guidance systems. Although the simplified control scheme has seen some development due to its low cost, its limited control capabilities prevent precision strikes, and it has gradually been phased out of development. Satellite-inertial combined guidance technology, due to its advantages such as improved satellite positioning accuracy and all-weather operation, has been widely applied to long-range and ultra-long-range guided rocket weapon systems in field applications. However, satellite-inertial combined guidance suffers from drawbacks: after the satellite is jammed, the accuracy of inertial guidance decreases significantly with increasing range; furthermore, the aforementioned guidance methods cannot strike moving targets. Summary of the Invention

[0003] (a) Technical problems to be solved

[0004] The technical problem to be solved by this invention is: how to construct a field rocket weapon system to achieve the capability of precision strikes against fixed targets and moving targets on land or sea when satellites are jammed.

[0005] (II) Technical Solution

[0006] To address the aforementioned technical problems, this invention provides an image-guided terminal-guided rocket weapon system based on ground-assisted recognition. The system includes: an image-guided terminal-guided rocket, a ground image control system, a box-type rocket launcher, a command vehicle, and an unmanned aerial vehicle (UAV) reconnaissance relay system; wherein...

[0007] The image-guided rocket employs a satellite / inertial combined mid-course guidance + data link target image transmission to ground target auxiliary identification + image-guided terminal guidance method for precise strike and destruction of targets;

[0008] The ground image control system is used to set the wireless communication frequency and 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 enable the operator to confirm the target to be attacked through human-computer interaction, and send the target information confirmed by the operator to the onboard image data transmission device.

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

[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 image acquisition of target areas and target coordinate measurement in the early stage of combat, as well as relaying communication between guided rockets and the ground image control system during the terminal phase of flight.

[0012] The image-guided terminal guidance rocket includes a nose cone, image seeker, flight control device, inertial navigation device, satellite positioning device, onboard image data transmission device, onboard power supply, servo motors, propulsion system, warhead, fuze, and necessary structural and electrical components; wherein,

[0013] The visor is designed to form the low aerodynamic drag shape required by the projectile structure, reduce the drag of the guided rocket during flight, and automatically detach from the guided rocket at the end of flight by the command given by the flight control device.

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

[0015] The flight control unit integrates information from the inertial navigation system, satellite positioning system, and seeker head, as well as guidance and control strategies, to form control commands, which are then sent to the servo motors to control the flight of the guided rocket.

[0016] Inertial navigation devices are used to measure the overload, velocity, position, attitude angular velocity, and attitude angle parameters of guided rockets during flight in both the inertial and launch coordinate systems.

[0017] Satellite positioning devices are used to measure the position and velocity of guided rockets during their flight.

[0018] The onboard 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 via wireless communication. It also receives target identification information and target locking commands uploaded by the ground image control system, decodes them, and transmits them to the missile's flight controller and seeker.

[0019] The onboard power supply provides power to the image seeker, flight control device, inertial navigation device, satellite positioning device, onboard image data transmission device, and servo components during the flight of the guided rocket.

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

[0021] The warhead is designed to explode and destroy the target upon impact.

[0022] The fuse is used to protect the detonation circuit during the initial stage of flight, and detonates the warhead when the guided rocket hits the target or reaches a certain range above the target.

[0023] The image seeker is either a television image seeker or an infrared image seeker, capable of storing 500ms of seeker images. The seeker is capable of locking onto and tracking targets in the image based on ground target identification results, and capable of reviewing and comparing images within the previous 200ms. The pitch and yaw angular velocities of the seeker tracking the target are not less than 10° / s.

[0024] The resolution of the television image seeker imaging the target area is at least 1024×1024 pixels.

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

[0026] Specifically, the infrared image seeker can achieve clear imaging under target temperature differences 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.

[0027] The flight control device is an embedded computer device used to realize the flight timing control of the guided rocket, receive target information and flight control parameters set by the rocket launcher, receive flight parameters of the guided rocket from the inertial navigation device and satellite positioning device, receive the target line-of-sight angular velocity sent by the seeker, and receive seeker operation commands uploaded by the ground image control system from the onboard image data transmission device; and generate guided rocket flight control commands by integrating the received information through the pre-installed guidance control model.

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

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

[0030] The satellite positioning device uses a 4-element anti-jamming antenna to interfere with active broadband jammers in no less than 3 directions.

[0031] The satellite positioning device uses systems including the US GPS satellite positioning system and the Chinese BeiDou navigation satellite system.

[0032] The missile-borne image data transmission device has a wireless image transmission bandwidth of 2.5 Mbps; 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 the ground image data transmission device; the missile-borne image data transmission device can only transmit images downwards, but can achieve bidirectional transmission of data upwards and downwards; the missile-borne image transmission device has the function of compressing the video images transmitted by the seeker head without damaging the resolution.

[0033] The propulsion device is a solid rocket engine; the solid rocket engine is a single-chamber dual-propagation solid rocket engine.

[0034] The warhead is a pre-fragmented explosive warhead, which causes damage to personnel and various combat equipment through the fragments after the explosion; the fuse is a proximity fuse or a trigger fuse.

[0035] The ground image control system includes a ground image control device, a ground image data transmission device, and an auxiliary recognition unit.

[0036] The ground image control device further includes an image information processor, an image processing and 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 fall-down tracking mechanism;

[0038] The data link antenna is a wide-beam phased array antenna, which has the ability to communicate simultaneously with the image data transmission devices on two guided rockets, and also has the ability to communicate with a UAV-borne data relay station.

[0039] The image data transmission processing device has the ability to process image data transmitted from two guided rockets simultaneously.

[0040] The antenna-falling tracking mechanism ensures that the antenna is in a fallen state during marching. When it is needed to work, it rises according to the command and points the antenna to the flight trajectory of the guided rocket based on 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, which has the ability to detect 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 accuracy probability of the target identified in the seeker image.

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

[0044] The ground image control device overlays the received information onto 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 control device. The operator locks and unlocks the target locking frame on the display screen by operating the operating handle, and moves the target locking cross frame on the display screen.

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

[0047] Both the operating handle and the keyboard are integrated and installed on the ground image control device housing.

[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 via the handle and keyboard to the ground image data transmission device, which then sends the information to the missile-borne image data transmission device, which in turn transmits it to the seeker head to achieve target identification and locking.

[0050] (III) Beneficial Effects

[0051] Compared with existing technologies, the image-guided rocket weapon system based on ground target assisted identification proposed in this invention can carry out long-range precision strikes and strikes against moving targets on land and sea when satellites are jammed. Attached Figure Description

[0052] Figure 1 This describes the composition of the weapon system according to the present invention;

[0053] Figure 2 This invention relates to the composition and layout of a terminal-guided rocket.

[0054] Figure 3 This invention describes the composition and information flow of the ground image manipulation system.

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

[0056] Figure 5 This is a flowchart of the system operation of the present invention. Detailed Implementation

[0057] To make the objectives, contents, and advantages of the present invention clearer, the specific embodiments of the present invention will be described in further detail below with reference to the accompanying drawings and examples.

[0058] To address the aforementioned technical problems, this invention provides an image-guided terminal-guided rocket weapon system based on ground-assisted recognition. The system includes: an image-guided terminal-guided rocket, a ground image control system, a box-type rocket launcher, a command vehicle, and an unmanned aerial vehicle (UAV) reconnaissance relay system; wherein...

[0059] The image-guided rocket employs a satellite / inertial combined mid-course guidance + data link target image transmission to ground target auxiliary identification + image-guided terminal guidance method for precise strike and destruction of targets;

[0060] The ground image control system is used to set the wireless communication frequency and 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 enable the operator to confirm the target to be attacked through human-computer interaction, and send the target information confirmed by the operator to the onboard image data transmission device.

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

[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 image acquisition of target areas and target coordinate measurement in the early stage of combat, as well as relaying communication between guided rockets and the ground image control system during the terminal phase of flight.

[0064] The image-guided terminal guidance rocket includes a nose cone, image seeker, flight control device, inertial navigation device, satellite positioning device, onboard image data transmission device, onboard power supply, servo motors, propulsion system, warhead, fuze, and necessary structural and electrical components; wherein,

[0065] The visor is designed to form the low aerodynamic drag shape required by the projectile structure, reduce the drag of the guided rocket during flight, and automatically detach from the guided rocket at the end of flight by the command given by the flight control device.

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

[0067] The flight control unit integrates information from the inertial navigation system, satellite positioning system, and seeker head, as well as guidance and control strategies, to form control commands, which are then sent to the servo motors to control the flight of the guided rocket.

[0068] Inertial navigation devices are used to measure the overload, velocity, position, attitude angular velocity, and attitude angle parameters of guided rockets during flight in both the inertial and launch coordinate systems.

[0069] Satellite positioning devices are used to measure the position and velocity of guided rockets during their flight.

[0070] The onboard 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 via wireless communication. It also receives target identification information and target locking commands uploaded by the ground image control system, decodes them, and transmits them to the missile's flight controller and seeker.

[0071] The onboard power supply provides power to the image seeker, flight control device, inertial navigation device, satellite positioning device, onboard image data transmission device, and servo components during the flight of the guided rocket.

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

[0073] The warhead is designed to explode and destroy the target upon impact.

[0074] The fuse is used to protect the detonation circuit during the initial stage of flight, and detonates the warhead when the guided rocket hits the target or reaches a certain range above the target.

[0075] The image seeker is either a television image seeker or an infrared image seeker, capable of storing 500ms of seeker images. The seeker is capable of locking onto and tracking targets in the image based on ground target identification results, and capable of reviewing and comparing images within the previous 200ms. The pitch and yaw angular velocities of the seeker tracking the target are not less than 10° / s.

[0076] The resolution of the television image seeker imaging the target area is at least 1024×1024 pixels.

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

[0078] Specifically, the infrared image seeker can achieve clear imaging under target temperature differences 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.

[0079] The flight control device is an embedded computer device used to realize the flight timing control of the guided rocket, receive target information and flight control parameters set by the rocket launcher, receive flight parameters of the guided rocket from the inertial navigation device and satellite positioning device, receive the target line-of-sight angular velocity sent by the seeker, and receive seeker operation commands uploaded by the ground image control system from the onboard image data transmission device; and generate guided rocket flight control commands by integrating the received information through the pre-installed guidance control model.

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

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

[0082] The satellite positioning device uses a 4-element anti-jamming antenna to interfere with active broadband jammers in no less than 3 directions.

[0083] The satellite positioning device uses systems including the US GPS satellite positioning system and the Chinese BeiDou navigation satellite system.

[0084] The missile-borne image data transmission device has a wireless image transmission bandwidth of 2.5 Mbps; 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 the ground image data transmission device; the missile-borne image data transmission device can only transmit images downwards, but can achieve bidirectional transmission of data upwards and downwards; the missile-borne image transmission device has the function of compressing the video images transmitted by the seeker head without damaging the resolution.

[0085] The propulsion device is a solid rocket engine; the solid rocket engine is a single-chamber dual-propagation solid rocket engine.

[0086] The warhead is a pre-fragmented explosive warhead, which causes damage to personnel and various combat equipment through the fragments after the explosion; the fuse is a proximity fuse or a trigger fuse.

[0087] The ground image control system includes a ground image control device, a ground image data transmission device, and an auxiliary recognition unit.

[0088] The ground image control device further includes an image information processor, an image processing and 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 fall-down tracking mechanism;

[0090] The data link antenna is a wide-beam phased array antenna, which has the ability to communicate simultaneously with the image data transmission devices on two guided rockets, and also has the ability to communicate with a UAV-borne data relay station.

[0091] The image data transmission processing device has the ability to process image data transmitted from two guided rockets simultaneously.

[0092] The antenna-falling tracking mechanism ensures that the antenna is in a fallen state during marching. When it is needed to work, it rises according to the command and points the antenna to the flight trajectory of the guided rocket based on 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, which has the ability to detect 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 accuracy probability of the target identified in the seeker image.

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

[0096] The ground image control device overlays the received information onto 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 control device. The operator locks and unlocks the target locking frame on the display screen by operating the operating handle, and moves the target locking cross frame on the display screen.

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

[0099] Both the operating handle and the keyboard are integrated and installed on the ground image control device housing.

[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 via the handle and keyboard to the ground image data transmission device, which then sends the information to the missile-borne image data transmission device, which in turn transmits it to the seeker head to achieve target identification and locking.

[0102] Example 1

[0103] The image-guided rocket weapon system based on ground-assisted target recognition constructed in this invention mainly consists of the following:

[0104] The system comprises a command vehicle system, an unmanned aerial vehicle (UAV) reconnaissance system, a rocket launcher, image-guided terminal-guided rockets, and a ground-assisted target identification system. The rocket launcher serves as the launch platform for the rockets; one launcher can carry 2 to 40 image-guided terminal-guided rockets, depending on the size of the rockets. The image-guided terminal-guided rockets mainly consist of a seeker head protective shroud, an image seeker head, a flight control device, an inertial navigation device, a satellite positioning device, an onboard wireless image data transmission device, an onboard power supply, servo motors, a solid rocket motor, a warhead, and a fuze. The ground-assisted target identification system mainly consists of a ground image control device, a ground image data transmission device, a data link antenna, and an auxiliary target identification unit. The system composition of this invention is described in [details omitted]. Figure 1 Image of a terminal-guided rocket Figure 2 Ground image control system (see) Figure 3 See system information transmission relationship Figure 4 .

[0105] The workflow of this invention is as follows: Figure 5An example of the workflow is that the command vehicle system sends instructions to the UAV reconnaissance system to conduct target reconnaissance and transmits target images and coordinates back to the command vehicle system. Based on the reconnaissance situation and operational mission requirements, the command vehicle determines the number of rockets to use and whether to use human-in-the-loop attack mode or template matching mode. When using template matching mode, the command vehicle prepares the target template and transmits the target template and coordinates to each rocket launcher via radio or wired connection. Upon receiving the target and operational mission, the rocket launcher powers on its image-guided rockets, completes self-checks, and sets the target template and coordinates. The rockets are then launched. The rockets first undergo mid-course guidance flight using information from satellite positioning and inertial navigation systems. Before reaching the seeker's effective range, the seeker jettisons its nose cone. The seeker then matches the target template with the target. If a match is successful, the seeker tracks the target and outputs the line-of-sight angular velocity to the flight control unit. The flight control unit integrates the information from the inertial navigation system and satellite... The positioning device generates servo control commands, which in turn deflect the control wings to guide the image-guided rocket to the target. The fuze and warhead then engage, achieving precise damage to the target. In man-in-the-loop attack mode, the command vehicle transmits target coordinates and other information to the rocket artillery and ground image control system via radio or wired communication. The rocket artillery calculates the firing angle and trajectory, the image-guided rocket is powered on, information is set, and alignment is transmitted—a series of preparatory tasks. The ground image control system, based on commands from the command vehicle, activates the ground image control device and connects the data link antenna. The system performs tasks such as receiving direction calculation and adjustment, and setting communication frequencies. When the rocket artillery fires a terminally guided rocket, it synchronizes the launch time with the ground image control system. The ground image control system actively sends a synchronization signal. When the onboard image data transmission system receives the synchronization signal from the ground image data transmission system, it sends a response signal to establish communication with the ground image data transmission system. It then wirelessly transmits the flight parameters of the terminally guided rocket and the seeker image to the ground image data transmission system. The ground image transmission system decodes the received information and sends it to the ground image control system and the auxiliary identification device. The ground image control system displays the received flight parameters of the terminally guided rocket on its display screen and overlays the seeker image and the target coordinate information output by the auxiliary identification unit onto the seeker image, displaying them simultaneously on the image control system's display screen. When the terminally guided rocket reaches a certain distance from the target, the flight control system issues a seeker head jettison command. The seeker head jettisons the image, and the seeker compresses the target area image acquired by the rocket and transmits it to the ground image control system via the onboard image data transmission system.The auxiliary identification unit in the ground image control system processes the seeker image, identifies targets within it, and assigns them numbers based on their probability of detection. Targets with higher probabilities are numbered "1," and so on, distinguishing up to five targets. The identification results are then sent to the ground image control device, which displays them in real-time on a screen. The operator confirms the target using function keys or number keys on the keyboard. The ground image control system transmits the target confirmation information to the onboard image data transmission device, which in turn sends it to the seeker. The seeker locks onto the target and automatically tracks it. Simultaneously, the seeker transmits the target tracking line-of-sight angular velocity to the flight control device. The flight control device integrates information from the inertial navigation system and satellite positioning system to generate flight control commands, which are then sent to the servo motors to guide the terminal-guided rocket towards the target, achieving a precise strike.

[0106] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A ground-assisted recognition-based image-guided rocket weapon system, characterized in that, The system includes: image-guided terminal-guided rockets, a ground-based image control system, a box-type rocket launcher, a command vehicle, and an unmanned aerial vehicle (UAV) reconnaissance relay system; among which... The image-guided rocket employs a satellite / inertial combined mid-course guidance + data link target image transmission to ground target auxiliary identification + image-guided terminal guidance method, for precise strike and destruction of targets; The ground image control system is used to set the wireless communication frequency and 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 enable the operator to confirm the target to be attacked through human-computer interaction, and send the target information confirmed by the operator to the onboard image data transmission device. The box-type rocket launcher is used to receive combat mission information and instructions from the command vehicle and to complete the launch preparation and launch of guided rockets. 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 image acquisition of target areas and target coordinate measurement in the early stage of combat, as well as relaying communication between guided rockets and the ground image control system during the terminal phase of flight. The image-guided terminal guidance rocket includes a nose cone, image seeker, flight control device, inertial navigation device, satellite positioning device, onboard image data transmission device, onboard power supply, servo motors, propulsion system, warhead, fuze, and necessary structural and electrical components; wherein, The visor is designed to form the low aerodynamic drag shape required by the projectile structure, reduce the drag of the guided rocket during flight, and automatically detach from the guided rocket at the end of flight by the command given by the flight control device. The image seeker is used to acquire images of the target area and track the target based on the target information identified on the ground, providing the line-of-sight angular velocity of the tracked target; The flight control unit integrates information from the inertial navigation system, satellite positioning system, and seeker head, as well as guidance and control strategies, to form control commands, which are then sent to the servo motors to control the flight of the guided rocket. Inertial navigation devices are used to measure the overload, velocity, position, attitude angular velocity, and attitude angle parameters of guided rockets during flight in both the inertial and launch coordinate systems. Satellite positioning devices are used to measure the position and velocity of guided rockets during their flight. The onboard 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 via wireless communication. It also receives target identification information and target locking commands uploaded by the ground image control system, decodes them, and transmits them to the missile's flight controller and seeker. The onboard power supply provides power to the image seeker, flight control device, inertial navigation device, satellite positioning device, onboard image data transmission device, and servo components during the flight of the guided rocket. The power plant is used to provide the power required for the guided rocket to fly; The warhead is designed to explode and damage the target upon impact. The fuse is used to protect the detonation circuit during the initial stage of flight and detonates the warhead when the guided rocket hits the target or reaches a certain range above the target. The ground image control system includes a ground image control device, a ground image data transmission device, and an auxiliary target recognition unit. The ground image control device further includes an image information processor, an image processing and 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 fall-down tracking mechanism; The data link antenna is a wide-beam phased array antenna, which has the ability to communicate simultaneously with the image data transmission devices on two guided rockets, and also has the ability to communicate with a UAV-borne data relay station. The image data transmission processing device has the ability to process image data transmitted from two guided rockets simultaneously. The antenna-falling tracking mechanism ensures that the antenna is in a fallen state during marching. When it is needed to work, it rises according to the command and points the antenna to the flight trajectory of the guided rocket based on 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, which has the ability to detect and recognize 10-pixel targets in a 1024×1024 pixel image. The auxiliary target recognition unit is used to determine in real time the position, size, and accuracy probability of the target identified in the seeker image. The auxiliary target recognition unit is integrated into the chassis of the ground image control device; the auxiliary target recognition unit should transmit the target position, size and recognition probability to the ground image control device in real time; The ground image control device overlays the received information onto the seeker head 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 control device. The operator locks and unlocks the target locking frame on the display screen by operating the operating handle, and moves the target locking cross frame on the display screen. The keyboard is used for operators to interact with the ground image control device. Operators input target coordinates, data link communication frequency, guided rocket number, and confirmed target number information through the keyboard. Both the operating handle and the keyboard are integrated and installed on the ground image control device housing. 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 via the handle and keyboard to the ground image data transmission device, which then sends the information to the missile-borne image data transmission device, which in turn transmits it to the seeker head to achieve target identification and locking.

2. The image-guided rocket weapon system based on ground-assisted recognition as described in claim 1, characterized in that, The image seeker is a television image seeker or an infrared image seeker, capable of storing 500ms of seeker images. The seeker is capable of locking onto and tracking targets in the image based on ground target identification results, and capable of reviewing and comparing images within the previous 200ms. The pitch and yaw angular velocities of the seeker tracking the target are not less than 10° / s.

3. The image-guided rocket weapon system based on ground-assisted recognition as described in claim 2, 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.

4. The image-guided rocket weapon system based on ground-assisted recognition as described in claim 2, characterized in that, The infrared image seeker can clearly image targets under temperature differences 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.

5. The image-guided rocket weapon system based on ground-assisted recognition as described in claim 1, characterized in that, The flight control device is an embedded computer device used to realize the flight timing control of the guided rocket. It receives target information and flight control parameters set by the rocket launcher, flight parameters of the guided rocket given by the inertial navigation device and satellite positioning device, target line-of-sight angular velocity sent by the seeker, and seeker operation instructions uploaded by the ground image control system received by the onboard image data transmission device. It integrates the received information and generates flight control commands for the guided rocket through the pre-installed guidance control model.

6. The image-guided rocket weapon system based on ground-assisted recognition as described in claim 1, characterized in that, The inertial navigation device is a strapdown inertial navigation device, which has the ability to process the current attitude angular velocity, attitude angle, velocity and position coordinates of the guided rocket in the inertial coordinate system in three directions at the current moment. The satellite positioning device and the inertial navigation device are combined to form a navigation device through information fusion, which further improves the accuracy of measuring flight parameters.

7. The image-guided rocket weapon system based on ground-assisted recognition as described in claim 1, characterized in that, The satellite positioning device uses a 4-element anti-jamming antenna to achieve interference against active broadband jammers in no less than 3 directions; The satellite positioning device uses systems including the US GPS satellite positioning system and the Chinese BeiDou navigation satellite system.

8. The image-guided rocket weapon system based on ground-assisted recognition as described in claim 1, characterized in that, The missile-borne image data transmission device has a wireless image transmission bandwidth of 2.5 Mbps; 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 the ground image data transmission device; the missile-borne image data transmission device can only transmit images downwards, and can transmit data both upwards and downwards. The missile-borne image data transmission device has the function of compressing the video images sent by the seeker without compromising resolution.

9. The image-guided rocket weapon system based on ground-assisted recognition as described in claim 1, characterized in that, The propulsion system uses a solid rocket motor; the solid rocket motor is a single-chamber dual-propulsion solid rocket motor. The warhead is a pre-fragmented explosive warhead, which causes damage to personnel and various combat equipment through the fragments after the explosion; the fuse is a proximity fuse or a trigger fuse.

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