Pipeline control method, device and equipment for returning track and medium

Abstract

The invention provides a pipeline control method and device for a regression orbit, equipment and a medium, and the method comprises the steps: carrying out the calculation according to an initial orbit parameter of an initial orbit where a to-be-regulated spacecraft is located, and obtaining a regulation parameter; configuring the initial orbit according to the regulation and control parameters to obtain a configured target orbit; and in the process that the spacecraft to be regulated and controlled operates on the target orbit, the spacecraft to be regulated and controlled is regulated in real time according to the current orbit parameters of the target orbit, so that the spacecraft to be regulated and controlled is in a preset range. By introducing the regulation and control parameter and the regulation and control parameter-based regulation strategy, the regulation frequency is remarkably reduced, and the precision is improved.

Description

Technical Field

[0001] The present application relates to the field of spacecraft orbit control technology, and in particular to a pipeline control method, device, equipment and medium for a regression orbit. Background Art

[0002] In satellite missions, high-precision regression orbits enable satellites to revisit space target points with high precision after a strict regression cycle, and control the position regression accuracy in the Earth-fixed coordinate system to within meters. However, actual satellites are affected by atmospheric drag, solar and lunar gravity, solar light pressure and other perturbations during flight, and cannot fly completely according to the ideal strict regression orbit. Therefore, it is necessary to control the satellite through a pipeline so that it always runs in a pipeline with a certain radius centered on the reference trajectory.

[0003] At present, for out-of-orbital-plane pipeline control, the commonly used method is to compare the radial, normal and tangential directions of the satellite. This method will increase the frequency of out-of-orbital-plane control and cannot achieve optimal control. Summary of the invention

[0004] In view of this, the purpose of the present application is to provide a pipeline control method, device, equipment and medium for returning to the track to overcome the problems in the prior art.

[0005] In a first aspect, an embodiment of the present application provides a pipeline control method for a regression track, the method comprising: A control parameter is calculated according to the initial orbital parameters of the initial orbit of the spacecraft to be controlled; Configure the initial orbit according to the control parameters to obtain a configured target orbit; During the operation of the spacecraft to be controlled in the target orbit, the spacecraft to be controlled is adjusted in real time according to the current orbital parameters of the target orbit so that the spacecraft to be controlled is within a preset range.

[0006] In some technical solutions of the present application, the above-mentioned initial orbit parameters include an inclination difference extreme value, and the control parameter is an inclination bias; The step of calculating a control parameter according to the initial orbital parameters of the initial orbit of the spacecraft to be controlled includes: Obtaining the inclination difference extreme value of the initial orbit of the spacecraft to be controlled; Determining a first orbital radius deviation according to a first mission requirement of the spacecraft to be controlled; The inclination offset corresponding to the first task is calculated based on the inclination difference extreme value and the first orbital radius deviation.

[0007] In some technical solutions of the present application, the above-mentioned calculating the inclination bias corresponding to the first task according to the inclination difference extreme value and the first orbit radius deviation includes: A first reference quantity is calculated based on the radius of the earth and the real-time latitude argument of the spacecraft to be controlled; Calculating a second reference value according to the first track radius deviation and the first reference value; The inclination angle offset corresponding to the first task is calculated based on the inclination angle difference extreme value and the second reference amount.

[0008] In some technical solutions of the present application, the above-mentioned configuring the initial orbit according to the control parameter to obtain the configured target orbit includes: generating an orbital maneuvering instruction corresponding to the control parameter according to the inclination bias; The moving direction of the spacecraft to be controlled in the initial orbit is adjusted according to the orbital maneuvering instruction to obtain the adjusted target orbit.

[0009] In some technical solutions of the present application, the above method further includes: Obtaining verification orbit parameters of the target orbit; The configured target orbit is verified according to the verification orbit parameter to determine whether the target orbit reaches a preset offset value.

[0010] In some technical solutions of the present application, during the operation of the above-mentioned spacecraft to be controlled in the target orbit, the spacecraft to be controlled is adjusted in real time according to the current orbital parameters of the target orbit so that the spacecraft to be controlled is within a preset range, including: Calculating the current orbit radius deviation of the target orbit according to the inclination difference extreme value of the target orbit; The spacecraft to be controlled is adjusted in real time according to the current orbital radius deviation and the first orbital radius deviation.

[0011] In some technical solutions of the present application, when the spacecraft to be controlled performs the second task, the method further includes: Determining a second orbital radius deviation according to a second mission requirement of the spacecraft to be controlled; The inclination offset corresponding to the second task is calculated based on the inclination difference extreme value and the second orbit radius deviation.

[0012] In a second aspect, an embodiment of the present application provides a pipeline control device for a regression track, the device comprising: A calculation module, used for calculating a control parameter according to the initial orbital parameters of the initial orbit of the spacecraft to be controlled; A configuration module, configured to configure the initial orbit according to the control parameters to obtain a configured target orbit; The adjustment module is used to adjust the spacecraft to be controlled in real time according to the current orbital parameters of the target orbit during the operation of the spacecraft to be controlled in the target orbit, so that the spacecraft to be controlled is within a preset range.

[0013] In a third aspect, an embodiment of the present application provides an electronic device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the steps of the above-mentioned pipeline control method for the regression orbit when executing the computer program.

[0014] In a fourth aspect, an embodiment of the present application provides a computer-readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, the steps of the above-mentioned pipeline control method for the regression orbit are executed.

[0015] The technical solution provided by the embodiments of the present application may have the following beneficial effects: The method of the present application includes calculating a control parameter based on the initial orbital parameters of the initial orbit where the spacecraft to be controlled is located; configuring the initial orbit according to the control parameter to obtain a configured target orbit; and during the operation of the spacecraft to be controlled on the target orbit, adjusting the spacecraft to be controlled in real time according to the current orbital parameters of the target orbit so that the spacecraft to be controlled is within a preset range.

[0016] This application significantly reduces the number of adjustments and improves accuracy by introducing control parameters and adjustment strategies based on the control parameters.

[0017] In order to make the above-mentioned objects, features and advantages of the present application more obvious and easy to understand, preferred embodiments are specifically cited below and described in detail with reference to the attached drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present application and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without paying creative work.

[0019] Figure 1 A schematic flow chart of a pipeline control method for a regression track provided in an embodiment of the present application is shown; Figure 2A schematic diagram of a pipeline control device for a regression track provided in an embodiment of the present application is shown; Figure 3 A schematic diagram showing another pipeline control device of a regression track provided in an embodiment of the present application is shown; Figure 4 A schematic diagram of the structure of an electronic device provided in an embodiment of the present application. DETAILED DESCRIPTION

[0020] To make the purpose, technical scheme and advantages of the embodiments of the present application clearer, the technical scheme in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. It should be understood that the drawings in the present application only serve the purpose of explanation and description and are not used to limit the scope of protection of the present application. In addition, it should be understood that the schematic drawings are not drawn in real proportion. The flowchart used in this application shows the operations implemented according to some embodiments of the present application. It should be understood that the operations of the flowchart can be implemented out of sequence, and the steps without logical context can be reversed in order or implemented simultaneously. In addition, those skilled in the art can add one or more other operations to the flowchart under the guidance of the content of the present application, or remove one or more operations from the flowchart.

[0021] In addition, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The components of the embodiments of the present application described and shown in the drawings here can be arranged and designed in various configurations. Therefore, the following detailed description of the embodiments of the present application provided in the drawings is not intended to limit the scope of the application claimed for protection, but merely represents the selected embodiments of the present application. Based on the embodiments of the present application, all other embodiments obtained by those skilled in the art without making creative work belong to the scope of protection of the present application.

[0022] It should be noted that the term "comprising" will be used in the embodiments of the present application to indicate the existence of the features declared thereafter, but does not exclude the addition of other features.

[0023] In satellite missions, high-precision regression orbits enable satellites to revisit space target points with high precision after a strict regression cycle, and control the position regression accuracy in the Earth-fixed coordinate system to within meters. However, actual satellites are affected by atmospheric drag, solar and lunar gravity, solar light pressure and other perturbations during flight, and cannot fly completely according to the ideal strict regression orbit. Therefore, it is necessary to control the satellite through a pipeline so that it always runs in a pipeline with a certain radius centered on the reference trajectory.

[0024] At present, for out-of-orbital-plane pipeline control, the commonly used method is to compare the radial, normal and tangential directions of the satellite. This method will increase the frequency of out-of-orbital-plane control and cannot achieve optimal control.

[0025] Based on this, the embodiments of the present application provide a pipeline control method, device, equipment and medium for a regression track, which are described below through embodiments.

[0026] Figure 1 A schematic flow chart of a pipeline control method for a regression track provided in an embodiment of the present application is shown, wherein the method includes steps S101-S103; specifically: S101, calculating a control parameter according to the initial orbital parameters of the initial orbit of the spacecraft to be controlled; S102, configuring the initial orbit according to the control parameters to obtain a configured target orbit; S103. During the operation of the spacecraft to be controlled in the target orbit, the spacecraft to be controlled is adjusted in real time according to the current orbital parameters of the target orbit, so that the spacecraft to be controlled is within a preset range.

[0027] This application significantly reduces the number of adjustments and improves accuracy by introducing control parameters and adjustment strategies based on the control parameters.

[0028] Some embodiments of the present application are described in detail below. In the absence of conflict, the following embodiments and features in the embodiments can be combined with each other.

[0029] The embodiment of the present application provides a control method for a regression orbit, which acts on a spacecraft, also known as a spacecraft or a spacecraft. Various types of aircraft that operate in space according to the laws of celestial mechanics and perform specific tasks such as exploring, developing, and utilizing space and celestial bodies. Spacecraft basically operate within the solar system. For example, satellites, etc. For the convenience of describing the embodiment of the present application, the spacecraft that needs to be regulated is referred to as a spacecraft to be regulated.

[0030] The orbit of the spacecraft when it first enters orbit or when it first enters and operates is called the initial orbit. It can be determined by the Laplace method (initial value problem method), Gauss method (boundary value problem method) and Batrako method, and sometimes it is determined by the motion parameters at the end of the active phase of the launch vehicle. Based on the determined initial orbit, we can understand the general operation of the spacecraft after entering orbit.

[0031] After determining the initial orbit of the spacecraft to be controlled, the embodiment of the present application needs to obtain the initial orbit parameters of the initial orbit. The initial orbit parameters include the inclination difference extreme values, specifically the maximum and minimum values ​​of the inclination difference.

[0032] Inclination Deviation here refers to the deviation between the initial orbital inclination of the satellite and the preset reference orbital inclination, which is used to quantify the degree of deviation of the satellite's position outside the orbital plane. Inclination here refers to the angle between the orbital plane and the Earth's equatorial plane, which is the core parameter describing the orbital spatial position. Initial orbit: An ideal orbit designed according to mission requirements, with an inclination of the theoretical target value (i ref Actual orbit: The actual orbit of the satellite after being affected by the forces of perturbation (atmospheric drag, gravitational pull of the sun and the moon, etc.). Its inclination is the actual measured value (i actual ).

[0033] The calculation formula of the inclination difference Δi is:

[0034] Affected by the perturbation force, the inclination difference fluctuates within the interval to obtain the maximum and minimum values ​​of the inclination difference. Δi∈[Δimin,Δimax].

[0035] In an optional implementation, before acquiring data, it is necessary to start the orbit measurement equipment and control system of the satellite, perform equipment self-check and calibration, and ensure that each device is working properly. Only after it is confirmed that the equipment is working properly, data acquisition is performed.

[0036] After determining the inclination difference extreme value of the initial orbit of the spacecraft to be controlled, the embodiment of the present application needs to calculate a control parameter. The control parameter here is the inclination bias, which characterizes the size of the inclination error. When calculating the inclination bias, in addition to the inclination difference extreme value, the orbital radius deviation is also included. The orbital radius deviation here is set according to specific task requirements. For example, when executing the first task, it is set to the first orbital radius deviation according to the first task requirement of the first task. When executing the second task, it needs to be set to the second orbital radius deviation according to the second task requirement of the second task. By analogy, when executing the Nth task, it is set to the Nth orbital radius deviation according to the Nth task requirement of the Nth task. After the execution of the first task is completed, if the second task is to be executed later, it is set to the second orbital radius deviation, and then the spacecraft to be controlled is adjusted according to the second orbital radius deviation.

[0037] The specific calculation process is as follows: a first reference quantity is calculated based on the radius of the earth and the real-time latitude argument of the spacecraft to be controlled; a second reference quantity is calculated based on the first orbital radius deviation and the first reference quantity; and the inclination bias corresponding to the first task is calculated based on the inclination difference extreme value and the second reference quantity.

[0038] In the specific implementation, the radius of the earth is r, the real-time latitude argument is u, and the position deviation outside the orbital plane is δR, then:

[0039] The maximum allowable deviation of the pipeline radius (δRmax, the first track radius deviation) must satisfy: |δR|≤δRmax.

[0040] By introducing the tilt bias ( ), the original tilt angle difference range is shifted, so that the dynamic range of the adjusted tilt angle difference is reduced. The adjusted tilt angle difference is:

[0041] The adjusted inclination difference is required to satisfy:

[0042] Solve the inclination bias by using simultaneous equations, and substitute the original inclination difference extreme values ​​(Δimax and Δimin) into the constraints:

[0043] The reasonable interval of the inclination angle bias δi is obtained:

[0044] Optimal tilt angle bias: To minimize the control frequency, the median value of the interval is usually taken:

[0045] The "±" sign needs to be adjusted according to the direction of the perturbation force. Combined with the directionality of the perturbation force (such as the dominant direction of the sun and moon's gravity), the "±" sign is dynamically adjusted to improve control adaptability.

[0046] After obtaining the inclination bias, the embodiment of the present application needs to configure the initial orbit according to the inclination bias to obtain the configured target orbit. The target orbit here is the orbit for the spacecraft to be controlled to perform the mission. The specific configuration process includes generating orbital maneuvering instructions based on the calculated inclination bias, determining the required thrust direction (normal or lateral) and velocity increment (Δv). Using the chemical thrusters or electric thrusters (such as ion thrusters) of the spacecraft to be controlled, apply Δv along the normal direction of the orbit to adjust the orbital inclination to the target value. Control the working time and thrust of the thruster to ensure that the adjustment accuracy is better than 0.001°.

[0047] Track confirmation and calibration: After adjustment, obtain the verification track parameters of the target track; verify the configured target track according to the verification track parameters to determine whether the target track reaches the preset offset value. If there is a residual error, perform fine-tuning until the first pipeline radius requirement is met.

[0048] After the target orbit is verified, the spacecraft to be controlled is controlled to run on the target orbit. At the same time, during the operation, the embodiment of the present application also needs to adjust the real-time position of the spacecraft to be controlled. Specifically, the embodiment of the present application obtains the current orbital parameters of the target orbit, and calculates the current orbital radius deviation of the target orbit according to the extreme value of the inclination difference of the target orbit; and adjusts the spacecraft to be controlled in real time according to the current orbital radius deviation and the first orbital radius deviation.

[0049] During the specific implementation, deploy onboard high-precision orbit sensors (such as laser interferometers) to collect orbital inclination, real-time latitude angle, etc. at a frequency of once per second. Compare the current orbital radius deviation with the first orbital radius deviation. If the current orbital radius deviation is greater than the first orbital radius deviation, trigger the control instruction. Use the proportional-integral-differential (PID) control algorithm to calculate the required thrust direction and Δv in real time according to the deviation size. Give priority to using low-thrust electric thrusters for continuous fine-tuning to avoid fuel waste. Re-monitor the orbital parameters after each adjustment to ensure that they are within the regression pipeline. Optimize PID parameters based on historical control data to improve response speed and stability.

[0050] The embodiment of the present application significantly reduces the frequency of out-of-orbital plane control and improves the satellite orbit accuracy and stability by introducing an inclination bias optimization control strategy combined with a dynamic feedback mechanism.

[0051] Figure 2 A schematic diagram of the structure of a pipeline control device for a regression track provided in an embodiment of the present application is shown, and the device includes: A calculation module, used for calculating a control parameter according to the initial orbital parameters of the initial orbit of the spacecraft to be controlled; A configuration module, configured to configure the initial orbit according to the control parameters to obtain a configured target orbit; The adjustment module is used to adjust the spacecraft to be controlled in real time according to the current orbital parameters of the target orbit during the operation of the spacecraft to be controlled in the target orbit, so that the spacecraft to be controlled is within a preset range.

[0052] The initial orbit parameters include an inclination difference extreme value, and the control parameter is an inclination bias; The step of calculating a control parameter according to the initial orbital parameters of the initial orbit of the spacecraft to be controlled includes: Determining the inclination difference extreme value of the initial orbit of the spacecraft to be controlled; Determining a first orbital radius deviation according to a first mission requirement of the spacecraft to be controlled; The inclination offset corresponding to the first task is calculated based on the inclination difference extreme value and the first orbital radius deviation.

[0053] The calculating, according to the inclination difference extreme value and the first orbit radius deviation, the inclination bias corresponding to the first task comprises: A first reference quantity is calculated based on the radius of the earth and the real-time latitude argument of the spacecraft to be controlled; Calculating a second reference value according to the first track radius deviation and the first reference value; The inclination angle offset corresponding to the first task is calculated based on the inclination angle difference extreme value and the second reference amount.

[0054] The configuring the initial orbit according to the control parameter to obtain the configured target orbit includes: generating an orbital maneuvering instruction corresponding to the control parameter according to the inclination bias; The moving direction of the spacecraft to be controlled in the initial orbit is adjusted according to the orbital maneuvering instruction to obtain the adjusted target orbit.

[0055] like Figure 3 As shown, the device also includes: A verification module, used to obtain verification track parameters of the target track; The configured target orbit is verified according to the verification orbit parameter to determine whether the target orbit reaches a preset offset value.

[0056] During the operation of the spacecraft to be controlled on the target orbit, the spacecraft to be controlled is adjusted in real time according to the current orbital parameters of the target orbit so that the spacecraft to be controlled is within a preset range, including: Calculating the current orbit radius deviation of the target orbit according to the inclination difference extreme value of the target orbit; The spacecraft to be controlled is adjusted in real time according to the current orbital radius deviation and the first orbital radius deviation.

[0057] When the spacecraft to be controlled performs the second task, the method further includes: Determining a second orbital radius deviation according to a second mission requirement of the spacecraft to be controlled; The inclination offset corresponding to the second task is calculated based on the inclination difference extreme value and the second orbit radius deviation.

[0058] like Figure 4As shown, an embodiment of the present application provides an electronic device for executing the pipeline control method of the regression orbit in the present application, and the device includes a memory, a processor, a bus, and a computer program stored in the memory and executable on the processor, wherein the processor implements the steps of the pipeline control method of the regression orbit when executing the computer program.

[0059] Specifically, the above-mentioned memory and processor can be general-purpose memory and processor, which are not specifically limited here. When the processor runs the computer program stored in the memory, the above-mentioned pipeline control method of the regression orbit can be executed.

[0060] Corresponding to the pipeline control method of the regression orbit in the present application, an embodiment of the present application also provides a computer-readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, the steps of the pipeline control method of the regression orbit are executed.

[0061] Specifically, the storage medium can be a general storage medium, such as a mobile disk, a hard disk, etc. When the computer program on the storage medium is run, the above-mentioned pipeline control method of the regression track can be executed.

[0062] In the embodiments provided in the present application, it should be understood that the disclosed systems and methods can be implemented in other ways. The system embodiments described above are merely schematic. For example, the division of the units is only a logical function division. There may be other division methods in actual implementation. For example, multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the mutual coupling or direct coupling or communication connection shown or discussed can be through some communication interfaces, indirect coupling or communication connection of systems or units, which can be electrical, mechanical or other forms.

[0063] The units described as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, and may be located in one place or distributed on multiple network units. Some or all of the units may be selected according to actual needs to achieve the purpose of the solution of this embodiment.

[0064] In addition, each functional unit in the embodiments provided in the present application may be integrated into one processing unit, or each unit may exist physically separately, or two or more units may be integrated into one unit.

[0065] If the functions are implemented in the form of software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present application, or the part that contributes to the prior art or the part of the technical solution, can be embodied in the form of a software product. The computer software product is stored in a storage medium, including several instructions to enable a computer device (which can be a personal computer, server, or network device, etc.) to execute all or part of the steps of the method described in each embodiment of the present application. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM), random access memory (RAM), disk or optical disk, and other media that can store program codes.

[0066] It should be noted that similar numbers and letters represent similar items in the following figures. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures. In addition, the terms "first", "second", "third", etc. are only used to distinguish the description and are not to be understood as indicating or implying relative importance.

[0067] Finally, it should be noted that the above-described embodiments are only specific implementation methods of the present application, which are used to illustrate the technical solutions of the present application, rather than to limit them. The protection scope of the present application is not limited thereto. Although the present application is described in detail with reference to the above-mentioned embodiments, ordinary technicians in the field should understand that any technician familiar with the technical field can still modify the technical solutions recorded in the above-mentioned embodiments within the technical scope disclosed in the present application, or can easily think of changes, or make equivalent replacements for some of the technical features therein; and these modifications, changes or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present application. They should all be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. A pipeline control method for a regression track, characterized in that: The method comprises: A control parameter is calculated according to the initial orbital parameters of the initial orbit of the spacecraft to be controlled; Configure the initial orbit according to the control parameters to obtain a configured target orbit; During the operation of the spacecraft to be controlled in the target orbit, the spacecraft to be controlled is adjusted in real time according to the current orbital parameters of the target orbit so that the spacecraft to be controlled is within a preset range.

2. The method according to claim 1, characterized in that The initial orbit parameters include an inclination difference extreme value, and the control parameter is an inclination bias; The step of calculating a control parameter according to the initial orbital parameters of the initial orbit of the spacecraft to be controlled includes: Determining the inclination difference extreme value of the initial orbit of the spacecraft to be controlled; Determining a first orbital radius deviation according to a first mission requirement of the spacecraft to be controlled; The inclination offset corresponding to the first task is calculated based on the inclination difference extreme value and the first orbital radius deviation.

3. The method according to claim 2, characterized in that The calculating, according to the inclination difference extreme value and the first orbit radius deviation, the inclination bias corresponding to the first task comprises: A first reference quantity is calculated based on the radius of the earth and the real-time latitude argument of the spacecraft to be controlled; Calculating a second reference value according to the first track radius deviation and the first reference value; The inclination angle offset corresponding to the first task is calculated based on the inclination angle difference extreme value and the second reference amount.

4. The method according to claim 2, characterized in that: The configuring the initial orbit according to the control parameter to obtain the configured target orbit includes: generating an orbital maneuvering instruction corresponding to the control parameter according to the inclination bias; The moving direction of the spacecraft to be controlled in the initial orbit is adjusted according to the orbital maneuvering instruction to obtain the adjusted target orbit.

5. The method according to claim 4, characterized in that The method further comprises: Obtaining verification orbit parameters of the target orbit; The configured target orbit is verified according to the verification orbit parameter to determine whether the target orbit reaches a preset offset value.

6. The method according to claim 2, characterized in that During the operation of the spacecraft to be controlled on the target orbit, the spacecraft to be controlled is adjusted in real time according to the current orbital parameters of the target orbit so that the spacecraft to be controlled is within a preset range, including: Calculating the current orbit radius deviation of the target orbit according to the inclination difference extreme value of the target orbit; The spacecraft to be controlled is adjusted in real time according to the current orbital radius deviation and the first orbital radius deviation.

7. The method according to claim 2, characterized in that When the spacecraft to be controlled performs the second task, the method further includes: Determining a second orbital radius deviation according to a second mission requirement of the spacecraft to be controlled; The inclination offset corresponding to the second task is calculated based on the inclination difference extreme value and the second orbit radius deviation.

8. A pipeline control device for a return track, characterized in that: The device comprises: A calculation module, used for calculating a control parameter according to the initial orbital parameters of the initial orbit of the spacecraft to be controlled; A configuration module, configured to configure the initial orbit according to the control parameters to obtain a configured target orbit; The adjustment module is used to adjust the spacecraft to be controlled in real time according to the current orbital parameters of the target orbit during the operation of the spacecraft to be controlled in the target orbit, so that the spacecraft to be controlled is within a preset range.

9. An electronic device, characterized in that: include: A processor, a memory and a bus, wherein the memory stores machine-readable instructions executable by the processor, and when the electronic device is running, the processor and the memory communicate via the bus, and when the machine-readable instructions are executed by the processor, the steps of the pipeline control method for the regression orbit as described in any one of claims 1 to 7 are performed.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the steps of the pipeline control method of the regression orbit as described in any one of claims 1 to 7 are executed.

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