A high-speed impact midcourse guidance handover method and device for asteroid defense

Abstract

The application provides a high-speed impact terminal guidance shift method and device for asteroid defense, and belongs to the technical field of asteroid defense, and comprises the following steps: state confirmation before shift, target asteroid discovery and identification by a terminal guidance system guidance camera, target asteroid identification state setting and sending to the ground by the terminal guidance system, shift instruction sending to the high-speed impact spacecraft by the ground, on-duty spacecraft state setting, stop control and sending of stop control time, corresponding time attitude and orbit data to the terminal guidance system by the middle guidance system, and start control by the terminal guidance system. The application has comprehensive consideration factors and strong engineering practicability. The shift method of the application can realize smooth shift of the high-speed impact spacecraft from the middle guidance system to the terminal guidance system, ensure smooth transition of the high-speed impact spacecraft attitude and orbit before and after the shift, and ensure that the high-speed impact spacecraft can finally successfully complete accurate impact on the target asteroid.

Description

Technical Field

[0001] The present invention belongs to the technical field of asteroid defense, and in particular relates to a high-speed impact terminal guidance handover method and device for asteroid defense. Background Art

[0002] The impact of near-Earth asteroids on the Earth is related to human survival and security and is a common threat faced by mankind in the long term. Developing asteroid defense technology is an inevitable choice to protect our home Earth.

[0003] To achieve a precise impact with a target asteroid, a high-speed impactor must undergo both an intermediate-range guidance phase and a terminal-range guidance phase. The intermediate-range guidance phase involves the heliocentric approach to the asteroid, during which the impactor is guided and controlled by ground-based radio signals. However, due to the limited accuracy of asteroid orbit determination (on the order of hundreds of kilometers), achieving a precise impact with a 30-meter-class target requires the impactor to establish high-precision autonomous navigation and guidance control relative to the asteroid during the final phase of the mission. The handover process from the intermediate-range guidance system to the terminal-range guidance system involves a series of challenges, including target identification, joint ground-to-space verification, error chain transmission, flight procedures, and fault response plans. These challenges are not addressed in the current Tianwen and Chang'e deep space exploration missions. Therefore, it is of great practical significance to study a reasonable terminal guidance handover method for high-speed impact of asteroid defense. It can lay a technical foundation for the detailed design of the handover plan, strategy selection, precision chain analysis, etc. of the first near-Earth asteroid defense demonstration and verification mission, provide strong technical support for the smooth implementation of the engineering mission, reduce the demand for terminal guidance capabilities, and improve the success probability of the mission. Summary of the Invention

[0004] To solve the above technical problems, the present invention proposes a high-speed impact terminal guidance handover method for asteroid defense, comprising:

[0005] Step 1: Complete the status confirmation before handover on the ground;

[0006] Step 2: The guidance camera of the terminal guidance system of the high-speed impact vehicle is turned on to take pictures of the target sky area;

[0007] Step 3: The terminal guidance system extracts the target characteristic parameters of the target asteroid based on the image data captured by the guidance camera and determines whether the target asteroid has been found. If the target asteroid has been found, the system proceeds to Step 4; otherwise, Steps 2 to 3 are repeated.

[0008] Step 4: The terminal guidance system sets the target asteroid identification status;

[0009] Step 5: After the high-speed impactor obtains the target asteroid identification status, it sends the target asteroid identification status and target characteristic parameters to the ground;

[0010] Step 6: After receiving the target asteroid identification status and target characteristic parameters, the ground system determines whether the judgment in step 3 is correct. If the judgment in step 3 is incorrect, a command is sent to the terminal guidance system to clear the target asteroid identification status and repeat steps 2 to 6. If the judgment in step 3 is correct, the system proceeds to step 7.

[0011] Step 7: The ground sends a handover command to the high-speed impact aircraft;

[0012] Step 8: After receiving the shift handover instruction, the high-speed impact aircraft sets the on-duty status;

[0013] Step 9: The ground determines the current on-duty status of the high-speed impact aircraft based on the telemetry data of the high-speed impact aircraft. If the terminal guidance system is not on-duty, the ground sends a command to the high-speed impact aircraft to activate the intermediate guidance system. The ground checks, processes, and clears the fault status of the terminal guidance system of the high-speed impact aircraft. If the terminal guidance system is on-duty, proceed to step 10.

[0014] Step 10: After the terminal guidance system is on duty, the high-speed impact vehicle autonomously controls the guidance system to stop control;

[0015] Step 11: The mid-range guidance system sends the data of its stop control moment and the attitude and trajectory of the high-speed impact vehicle at the corresponding moment to the terminal guidance system;

[0016] Step 12: The terminal guidance system starts control, updates the target attitude, and performs attitude and trajectory stabilization and tracking control on the high-speed impact vehicle.

[0017] Step 13: The ground determines the attitude and orbit stability of the high-speed impact aircraft. If the attitude or orbit is abnormal, a handover instruction is sent to the high-speed impact aircraft; if the attitude and orbit of the high-speed impact aircraft are stable, the handover method ends.

[0018] A high-speed impact terminal guidance handover device for asteroid defense, comprising:

[0019] Status confirmation module before shift handover, ground completion status confirmation before shift handover;

[0020] The camera module starts the guidance camera of the terminal guidance system of the high-speed impact vehicle and takes pictures of the target sky area.

[0021] The target asteroid judgment module: The terminal guidance system extracts the target characteristic parameters of the target asteroid based on the image data captured by the guidance camera and determines whether the target asteroid has been found. If the target asteroid has been found, the function of the status setting module is executed. Otherwise, the functions of the photo taking module and the target asteroid judgment module are repeatedly executed in sequence.

[0022] Status setting module, the terminal guidance system sets the target asteroid identification status;

[0023] The state recognition module, after the high-speed impact spacecraft obtains the target asteroid identification state, sends the target asteroid identification state and target characteristic parameters to the ground;

[0024] The determination module, after receiving the target asteroid identification status and target characteristic parameters from the ground, determines whether the target asteroid identification module's judgment is correct. If the judgment is incorrect, it sends a command to the terminal guidance system to clear the target asteroid identification status and repeatedly executes the functions of the photographing module, the target asteroid identification module, the status setting module, the status identification module, and the determination module in sequence; if the judgment is correct, it executes the function of the shift command module;

[0025] The handover command module sends handover commands from the ground to the high-speed impact aircraft;

[0026] The status setting module sets the status of the aircraft on duty after the high-speed impact aircraft receives the shift handover instruction;

[0027] The on-duty aircraft status determination module determines the current on-duty aircraft status based on the telemetry data of the high-speed impact aircraft. If the terminal guidance system is not on-duty, the ground sends a command to the high-speed impact aircraft to start the intermediate guidance system and investigate, process, and clear the fault status of the terminal guidance system of the high-speed impact aircraft. If the terminal guidance system is on-duty, the function of the shutdown control module is executed;

[0028] The stop control module stops the guidance system of the terminal guidance system after the high-speed impact aircraft is autonomously controlled;

[0029] The data transmission module sends the middle guidance system the data of its stopping time and the attitude and trajectory of the high-speed impact vehicle at the corresponding time to the terminal guidance system;

[0030] Update module, start control of terminal guidance system, update target attitude, perform attitude and orbit stabilization and tracking control of high-speed impact vehicle;

[0031] The attitude and orbit stability judgment module judges the attitude and orbit stability of the high-speed impact aircraft on the ground. If the attitude or orbit is abnormal, a handover instruction is sent to the high-speed impact aircraft; if the attitude and orbit of the high-speed impact aircraft are stable, the handover method ends.

[0032] An electronic device includes a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the program, the steps of the high-speed impact terminal guidance handover method for asteroid defense are implemented.

[0033] A non-transitory computer-readable storage medium stores a computer program, which, when executed by a processor, implements the steps of the high-speed impact terminal guidance handover method for asteroid defense.

[0034] The present invention has the following beneficial effects:

[0035] The present invention relates to a shift handover method that fully considers status confirmation before the shift handover, abnormality handling during the shift handover, and smooth transition of attitude and orbit during the shift handover. It comprehensively considers various influencing factors of the shift handover, has a comprehensive fault prevention plan, and has strong engineering practicality. According to the shift handover method of the present invention, a smooth shift handover from the intermediate guidance system to the terminal guidance system of a high-speed impact vehicle can be achieved, ensuring a smooth transition of the attitude and orbit of the high-speed impact vehicle before and after the shift handover, thereby ensuring that the high-speed impact vehicle can ultimately successfully complete a precise impact with a target asteroid. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1 This is a flow chart of the terminal guidance handover method for high-speed impact asteroid defense according to the present invention;

[0037] Figure 2 This is the flow chart for status confirmation before shift handover. DETAILED DESCRIPTION

[0038] In order to make the objectives, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only intended to illustrate the present invention and are not intended to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.

[0039] like Figure 1 As shown, the terminal guidance handover method for high-speed impact asteroid defense of the present invention includes:

[0040] Step 1: Complete the status confirmation process before handover on the ground. The status confirmation process before handover includes six parallel sub-processes. The status confirmation process before handover is completed when the conditions of the six parallel sub-processes are met.

[0041] Step 2: After the conditions of the six parallel sub-processes in Step 1 are met, the two guidance cameras of the terminal guidance system of the high-speed impact spacecraft are turned on to take pictures of the target sky area.

[0042] Step 3: The terminal guidance system of the high-speed impact vehicle extracts the target characteristic parameters (shape, size, surface morphology, material, and surface reflectance characteristics) of the target asteroid based on the image data captured by the guidance camera, and determines whether the target asteroid has been found. That is, the extracted target characteristic parameters of the target asteroid are compared with the pre-set parameters. If the difference between each target characteristic parameter (shape, size, surface morphology, material, and surface reflectance characteristics) and the pre-set parameters is less than the set threshold, it is determined that the target asteroid has been found and the process proceeds to Step 4. Otherwise, Steps 2 to 3 are repeated.

[0043] Step 4: The terminal guidance system of the high-speed impact vehicle sets the target asteroid identification state.

[0044] Step 5: After the high-speed impactor obtains the identification status of the target asteroid, it sends the identification status and target characteristic parameters (shape, size, surface morphology, material, and surface reflectance characteristics) of the target asteroid to the ground.

[0045] Step 6: After receiving the target asteroid identification status and target characteristic parameters, the ground system determines whether the judgment in Step 3 is correct. Specifically, it determines whether the target asteroid discovered in Step 3 is the correct target asteroid. If the judgment in Step 3 is incorrect, a command is sent to the terminal guidance system to clear the target asteroid identification status and repeat Steps 2 to 6. If the judgment in Step 3 is correct, the system proceeds to Step 7. The specific judgment method is: the ground system compares the target characteristic parameters (shape, size, surface morphology, material, and surface reflectivity) extracted from the observation data with the target characteristic parameters (shape, size, surface morphology, material, and surface reflectivity) transmitted by the high-speed impactor. If the difference in each target characteristic parameter (shape, size, surface morphology, material, and surface reflectivity) is less than the set threshold, the judgment in Step 3 is determined to be correct.

[0046] Step 7: The ground sends a handover command to the high-speed impact aircraft.

[0047] Step 8: After receiving the shift handover instruction, the high-speed impact aircraft sets the on-duty status.

[0048] Step 9: The ground determines the current status of the aircraft on duty based on the telemetry data of the high-speed impact aircraft. If the terminal guidance system is not on duty (i.e., the shift handover is unsuccessful), the ground sends a command to the high-speed impact aircraft to start the intermediate guidance system. The ground checks, processes, and clears the fault status of the terminal guidance system of the high-speed impact aircraft. If the terminal guidance system is on duty (i.e., the shift handover is successful), execute step 10.

[0049] Step 10: After the terminal guidance system is on duty, the high-speed impact vehicle autonomously controls the intermediate guidance system to stop control. The terminal guidance system is on duty and autonomously takes over control. At this time, the intermediate guidance system does not participate in control.

[0050] Step 11: The mid-guidance system sends the control stop moment and the attitude and trajectory data of the high-speed impact vehicle at the corresponding moment to the terminal guidance system.

[0051] Step 12: The terminal guidance system starts control. The terminal guidance system extracts the target aiming point based on the guidance camera image and updates the target attitude. It also combines the stop control time sent by the mid-guidance system and the attitude and orbit data of the high-speed impact vehicle at the corresponding time to perform attitude and orbit stabilization and tracking control of the high-speed impact vehicle.

[0052] Step 13: The ground determines the attitude and orbit stability of the high-speed impact aircraft based on the telemetry data of the high-speed impact aircraft detected by it. If the attitude or orbit is abnormal, the ground sends a handover instruction to the high-speed impact aircraft, and the high-speed impact aircraft autonomously starts the intermediate guidance system to control the attitude and orbit. The ground checks, processes and clears the fault of the terminal guidance system on the high-speed impact aircraft based on the telemetry data of the high-speed impact aircraft detected by it, and then repeats steps 2 to 13; if the attitude and orbit of the high-speed impact aircraft are stable, the handover method ends.

[0053] Among them, such as Figure 2 As shown in the figure, the specific process of status confirmation before handover in step 1 is as follows:

[0054] (a) Confirmation of the shift handover window: The ground personnel confirm whether the current time of the high-speed impact vehicle meets the shift handover window for the intermediate guidance system to the terminal guidance system of the high-speed impact vehicle based on the onboard time telemetry data of the high-speed impact vehicle. If so, the shift handover window confirmation condition is met. If not, this step is repeated.

[0055] (b) Confirmation of on-duty status: The ground confirms whether the high-speed impact aircraft has the medium guidance system on duty based on the high-speed impact aircraft's on-duty status telemetry data. If so, the on-duty status confirmation conditions are met. If not, the ground sends a handover instruction to the high-speed impact aircraft and repeats this step.

[0056] (c) Time alignment status confirmation: The ground confirms whether the terminal guidance system of the high-speed impact aircraft is time-aligned with the mid-range guidance system based on the time synchronization status telemetry data of the high-speed impact aircraft. If they are aligned, the time alignment status confirmation condition is met. If they are not aligned, the ground sends a time synchronization command to the high-speed impact aircraft and repeats this step.

[0057] (d) Attitude pointing confirmation: The ground confirms based on the attitude telemetry data of the high-speed impactor spacecraft whether the guidance camera on the high-speed impactor spacecraft is pointing towards the target asteroid area under the current attitude of the high-speed impactor spacecraft and the stability meets the index requirements. If so, the attitude pointing confirmation condition is met. Otherwise, the ground sends a command to the high-speed impactor spacecraft to adjust the attitude of the high-speed impactor spacecraft and repeats this step.

[0058] (e) Target distance confirmation: The ground system verifies whether the distance between the high-speed impactor and the target asteroid is less than the maximum detection range of the guidance camera based on the orbit telemetry data of the high-speed impactor and the orbit determination data of the target asteroid. If so, the target distance confirmation condition is met. Otherwise, the ground system decides whether to perform orbit control or wait based on the current orbital status of the high-speed impactor and the target asteroid (if the deviation between the high-speed impactor's orbit and the nominal orbit is less than the threshold, wait; otherwise, perform orbit control on the high-speed impactor and adjust the orbit to be within the nominal orbit deviation range), and repeat this step.

[0059] (f) Confirmation of the target asteroid status data: The ground confirms whether the target asteroid status data is the latest version based on the telemetry data of the target asteroid characteristic parameters transmitted by the high-speed impact spacecraft. If so, the target asteroid status data confirmation conditions are met. Otherwise, the ground sends a command to the high-speed impact spacecraft to note the latest version of the target asteroid status parameters and repeat this step.

[0060] The shift handover method involved in the present invention has the advantages of comprehensive consideration of influencing factors and fault contingency plans and strong engineering practicality. According to the shift handover method of the present invention, smooth shift handover of the two major systems of a high-speed impact vehicle, from the intermediate guidance system to the terminal guidance system, can be achieved, ensuring a smooth transition of the attitude and orbit of the high-speed impact vehicle before and after the shift handover, thereby ensuring that the high-speed impact vehicle can ultimately successfully complete the precise impact with the target asteroid.

[0061] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art may make various variations or modifications within the scope of the claims, which do not affect the essence of the present invention.

[0062] Those skilled in the art will appreciate that embodiments of the present invention may be provided as methods, systems, or computer program products. Thus, the present invention may take the form of an entirely hardware embodiment, an entirely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, the present invention may take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk drives, CD-ROMs, optical storage devices, etc.) containing computer-usable program code. The solutions in the embodiments of the present invention may be implemented using various computer languages, such as the object-oriented programming language Java and the interpreted scripting language JavaScript.

[0063] The present invention is described with reference to flowcharts and / or block diagrams of methods, devices (systems), and computer program products according to embodiments of the present invention. It should be understood that each process and / or block in the flowcharts and / or block diagrams, as well as combinations of processes and / or blocks in the flowcharts and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing device to produce a machine, so that the instructions executed by the processor of the computer or other programmable data processing device generate instructions for implementing the processes in the flowcharts and / or block diagrams. Figure 1 a process or multiple processes and / or boxes Figure 1 A device that provides the functions specified in a block or multiple blocks.

[0064] These computer program instructions may also be stored in a computer readable memory that can direct a computer or other programmable data processing device to work in a specific manner, so that the instructions stored in the computer readable memory produce an article of manufacture comprising an instruction device, which implements the process Figure 1 a process or multiple processes and / or boxes Figure 1 The function specified in one or more boxes.

[0065] These computer program instructions can also be loaded onto a computer or other programmable data processing device so that a series of operational steps are executed on the computer or other programmable device to produce a computer-implemented process, thereby providing the instructions executed on the computer or other programmable device for implementing the process. Figure 1 a process or multiple processes and / or boxes Figure 1 The steps for the function specified in one or more boxes.

[0066] Although the preferred embodiments of the present invention have been described, those skilled in the art may make additional changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of the present invention.

[0067] It will be apparent to those skilled in the art that various modifications and variations can be made to the present application without departing from the spirit or scope of the application. Thus, it is intended that the present application cover modifications and variations of this application provided they come within the scope of the appended claims and their equivalents.

Claims

1. A high-speed impact terminal guidance handover method for asteroid defense, characterized by: include: Step 1: Complete the status confirmation before handover on the ground; Step 2: The guidance camera of the terminal guidance system of the high-speed impact vehicle is turned on to take pictures of the target sky area; Step 3: The terminal guidance system extracts the target characteristic parameters of the target asteroid based on the image data captured by the guidance camera and determines whether the target asteroid has been found. If the target asteroid has been found, the system proceeds to Step 4; otherwise, Steps 2 to 3 are repeated. Step 4: The terminal guidance system sets the target asteroid identification status; Step 5: After the high-speed impactor obtains the target asteroid identification status, it sends the target asteroid identification status and target characteristic parameters to the ground; Step 6: After receiving the target asteroid identification status and target characteristic parameters, the ground system determines whether the judgment in step 3 is correct. If the judgment in step 3 is incorrect, a command is sent to the terminal guidance system to clear the target asteroid identification status and repeat steps 2 to 6. If the judgment in step 3 is correct, the system proceeds to step 7. Step 7: The ground sends a handover command to the high-speed impact aircraft; Step 8: After receiving the shift handover instruction, the high-speed impact aircraft sets the on-duty status; Step 9: The ground determines the current on-duty status of the high-speed impact aircraft based on the telemetry data of the high-speed impact aircraft. If the terminal guidance system is not on-duty, the ground sends a command to the high-speed impact aircraft to activate the intermediate guidance system. The ground checks, processes, and clears the fault status of the terminal guidance system of the high-speed impact aircraft. If the terminal guidance system is on-duty, proceed to step 10. Step 10: After the terminal guidance system is on duty, the high-speed impact vehicle autonomously controls the guidance system to stop control; Step 11: The mid-range guidance system sends the data of its stop control moment and the attitude and trajectory of the high-speed impact vehicle at the corresponding moment to the terminal guidance system; Step 12: The terminal guidance system starts control, updates the target attitude, and performs attitude and trajectory stabilization and tracking control on the high-speed impact vehicle. Step 13: The ground determines the attitude and orbit stability of the high-speed impact aircraft. If the attitude or orbit is abnormal, a handover instruction is sent to the high-speed impact aircraft; if the attitude and orbit of the high-speed impact aircraft are stable, the handover method ends.

2. The high-speed impact terminal guidance handover method for asteroid defense according to claim 1, characterized in that: In step 1, the pre-shift status confirmation process includes six parallel sub-processes, namely, the shift handover window confirmation sub-process, the on-duty aircraft status confirmation sub-process, the time alignment status confirmation sub-process, the attitude pointing confirmation sub-process, the target distance confirmation sub-process, and the target asteroid status data confirmation sub-process; completing the pre-shift status confirmation includes confirming that the conditions of the six parallel sub-processes are all met.

3. The high-speed impact terminal guidance handover method for asteroid defense according to claim 2, characterized in that: The six parallel sub-processes are specifically as follows: Confirm the shift handover window. The ground confirms whether the current time of the high-speed impact aircraft meets the shift handover window for the intermediate guidance system to the terminal guidance system of the high-speed impact aircraft based on the onboard time telemetry data of the high-speed impact aircraft. If so, the shift handover window confirmation condition is met. If not, repeat this step. On-duty status confirmation: The ground confirms whether the high-speed impact aircraft has the mid-range guidance system on duty based on the high-speed impact aircraft's on-duty status telemetry data. If so, the on-duty status confirmation condition is met. If not, the ground sends a handover command to the high-speed impact aircraft and repeats this step; Time alignment status confirmation: The ground confirms whether the terminal guidance system of the high-speed impact aircraft is time-aligned with the mid-range guidance system based on the time synchronization status telemetry data of the high-speed impact aircraft. If they are aligned, the time alignment status confirmation condition is met. If not, the ground sends a time synchronization command to the high-speed impact aircraft and repeats this step; Attitude pointing confirmation: The ground confirms based on the attitude telemetry data of the high-speed impactor spacecraft whether the guidance camera on the high-speed impactor spacecraft is pointing towards the target asteroid area under the current attitude of the high-speed impactor spacecraft and the stability meets the index requirements. If so, the attitude pointing confirmation condition is met. Otherwise, the ground sends a command to the high-speed impactor spacecraft to adjust the attitude of the high-speed impactor spacecraft and repeats this step; Target distance confirmation: The ground determines whether the distance between the high-speed impactor and the target asteroid is less than the maximum detection range of the guidance camera based on the high-speed impactor orbit telemetry data and the target asteroid's orbit determination data. If so, the target distance confirmation condition is met. Otherwise, the ground decides whether to perform orbit control or wait based on the current orbital status of the high-speed impactor and the target asteroid. If the deviation between the high-speed impactor's orbit and the nominal orbit is less than the threshold, wait; otherwise, orbit control is performed on the high-speed impactor to adjust the orbit to within the nominal orbit deviation range, and this step is repeated; Target asteroid status data confirmation: The ground confirms whether the target asteroid status data is the latest version based on the telemetry data of the target asteroid characteristic parameters transmitted by the high-speed impact spacecraft. If so, the target asteroid status data confirmation conditions are met. Otherwise, the ground sends a command to the high-speed impact spacecraft to enter the latest version of the target asteroid status parameters and repeat this step.

4. The high-speed impact terminal guidance handover method for asteroid defense according to claim 1, characterized in that: In step 3, the target characteristic parameters of the target asteroid include shape, size, surface morphology, material, and surface reflectivity.

5. The high-speed impact terminal guidance handover method for asteroid defense according to claim 1, characterized in that: In step 3, determining whether the target asteroid has been found specifically includes comparing the extracted target characteristic parameters of the target asteroid with pre-set parameters. If the difference between each target characteristic parameter and the pre-set parameters is less than a set threshold, the target asteroid is determined to have been found, and the process proceeds to step 4. Otherwise, steps 2 to 3 are repeated.

6. The high-speed impact terminal guidance handover method for asteroid defense according to claim 1, characterized in that: In step 6, the determination of whether the judgment in step 3 is correct specifically includes: comparing the target characteristic parameters extracted from the observation data on the ground with the target characteristic parameters transmitted by the high-speed impact aircraft. If the differences in the target characteristic parameters are all less than the set threshold, it is determined that the judgment in step 3 is correct.

7. The high-speed impact terminal guidance handover method for asteroid defense according to claim 1, characterized in that: Step 12 is specifically as follows: the terminal guidance system starts control, extracts the target aiming point based on the guidance camera image, updates the target attitude, and combines the stop control time sent by the intermediate guidance system and the attitude and orbit data of the high-speed impact aircraft at the corresponding time to perform attitude and orbit stabilization and tracking control of the high-speed impact aircraft.

8. The high-speed impact terminal guidance handover method for asteroid defense according to claim 1, characterized in that: Step 13 is specifically as follows: the ground determines the attitude and orbit stability of the high-speed impact aircraft based on the telemetry data of the high-speed impact aircraft detected by it; if the attitude or orbit is abnormal, the ground sends a handover instruction to the high-speed impact aircraft, and the high-speed impact aircraft autonomously starts the intermediate guidance system to perform attitude and orbit control; the ground checks, processes and clears the fault of the terminal guidance system on the high-speed impact aircraft based on the telemetry data of the high-speed impact aircraft detected by it, and then repeats steps 2 to 13; if the attitude and orbit of the high-speed impact aircraft are stable, the handover method ends.

9. A high-speed impact terminal guidance handover device for asteroid defense, characterized by: include: Status confirmation module before shift handover, ground completion status confirmation before shift handover; The camera module starts the guidance camera of the terminal guidance system of the high-speed impact vehicle and takes pictures of the target sky area. The target asteroid judgment module: The terminal guidance system extracts the target characteristic parameters of the target asteroid based on the image data captured by the guidance camera and determines whether the target asteroid has been found. If the target asteroid has been found, the function of the status setting module is executed. Otherwise, the functions of the photo taking module and the target asteroid judgment module are repeatedly executed in sequence. Status setting module, the terminal guidance system sets the target asteroid identification status; The state recognition module, after the high-speed impact spacecraft obtains the target asteroid identification state, sends the target asteroid identification state and target characteristic parameters to the ground; The determination module, after receiving the target asteroid identification status and target characteristic parameters from the ground, determines whether the target asteroid identification module's judgment is correct. If the judgment is incorrect, it sends a command to the terminal guidance system to clear the target asteroid identification status and repeatedly executes the functions of the photographing module, the target asteroid identification module, the status setting module, the status identification module, and the determination module in sequence; if the judgment is correct, it executes the function of the shift command module; The handover command module sends handover commands from the ground to the high-speed impact aircraft; The status setting module sets the status of the aircraft on duty after the high-speed impact aircraft receives the shift handover instruction; The on-duty aircraft status determination module determines the current on-duty aircraft status based on the telemetry data of the high-speed impact aircraft. If the terminal guidance system is not on-duty, the ground sends a command to the high-speed impact aircraft to start the intermediate guidance system and investigate, process, and clear the fault status of the terminal guidance system of the high-speed impact aircraft. If the terminal guidance system is on-duty, the function of the shutdown control module is executed; The stop control module stops the guidance system of the terminal guidance system after the terminal guidance system is on duty and the high-speed impact aircraft autonomously controls the stop control; The data transmission module sends the middle guidance system the data of its stopping time and the attitude and trajectory of the high-speed impact vehicle at the corresponding time to the terminal guidance system; Update module, start control of terminal guidance system, update target attitude, perform attitude and orbit stabilization and tracking control of high-speed impact vehicle; The attitude and orbit stability judgment module judges the attitude and orbit stability of the high-speed impact aircraft on the ground. If the attitude or orbit is abnormal, a handover instruction is sent to the high-speed impact aircraft; if the attitude and orbit of the high-speed impact aircraft are stable, the handover method ends.

10. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein: When the processor executes the program, the steps of the terminal guidance handover method for high-speed impact for asteroid defense according to any one of claims 1 to 8 are implemented.

11. A non-transitory computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the steps of the high-speed impact terminal guidance handover method for asteroid defense according to any one of claims 1 to 8 are implemented.

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