A pipeline control method, device, equipment and medium for a return orbit

Abstract

The present application provides a pipeline control method, device, equipment and medium for a return orbit. The method includes: calculating a regulation parameter according to the initial orbit parameters of the spacecraft to be regulated in the initial orbit; configuring the initial orbit according to the regulation parameter to obtain a configured target orbit; during the operation of the spacecraft to be regulated on the target orbit, making real-time adjustment to the spacecraft to be regulated according to the current orbit parameters of the target orbit, so that the spacecraft to be regulated is within a preset range. By introducing the regulation parameter and the adjustment strategy based on the regulation parameter, the present application significantly reduces the number of adjustments and improves the accuracy.

Description

Technical Field

[0001] The present application relates to the technical field of spacecraft orbit control, and more particularly, to a pipeline control method, device, equipment and medium for a return orbit. Background Art

[0002] In satellite missions, a high-precision return orbit enables a satellite to revisit a space target point with high precision after experiencing a strict return period, and control the position return accuracy in the geocentric coordinate system within meters. However, in actual flight, a satellite is affected by disturbing forces such as atmospheric drag, solar and lunar gravity, and solar radiation pressure, and cannot fly completely along an ideal strict return orbit. Therefore, it is necessary to perform pipeline control on the satellite so that it always operates within a pipeline centered on a reference trajectory with a certain pipeline radius.

[0003] Currently, for out-of-plane pipeline control of an orbit, the commonly used method is to compare the radial, normal, and tangential directions of a comparison satellite. This method will increase the frequency of out-of-plane control and cannot achieve optimal control. Summary of the Invention

[0004] In view of this, an object of the present application is to provide a pipeline control method, device, equipment and medium for a return orbit 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 return orbit, the method comprising:

[0006] Calculating a regulation parameter according to initial orbit parameters of an initial orbit where a spacecraft to be regulated is located;

[0007] Configuring the initial orbit according to the regulation parameter to obtain a configured target orbit;

[0008] During the operation of the spacecraft to be regulated on the target orbit, performing real-time adjustment on the spacecraft to be regulated according to current orbit parameters of the target orbit so that the spacecraft to be regulated is within a preset range.

[0009] In some technical solutions of the present application, the above initial orbit parameters include an inclination difference extreme value, and the regulation parameter is an inclination offset;

[0010] The calculating a regulation parameter according to initial orbit parameters of an initial orbit where a spacecraft to be regulated is located includes:

[0011] Obtaining the inclination difference extreme value of the initial orbit where the spacecraft to be regulated is located;

[0012] Determining a first orbit radius deviation according to a first task requirement of a first task executed by the spacecraft to be regulated;

[0013] Based on the extreme value of the inclination difference and the deviation of the first orbital radius, the inclination offset corresponding to the first mission is calculated.

[0014] In some technical solutions of the present application, the above-mentioned calculating the inclination offset corresponding to the first mission based on the extreme value of the inclination difference and the deviation of the first orbital radius includes:

[0015] Based on the radius of the Earth and the real-time latitude argument of the spacecraft to be regulated, a first reference quantity is calculated;

[0016] Based on the deviation of the first orbital radius and the first reference quantity, a second reference quantity is calculated;

[0017] Based on the extreme value of the inclination difference and the second reference quantity, the inclination offset corresponding to the first mission is calculated.

[0018] In some technical solutions of the present application, the above-mentioned configuring the initial orbit according to the regulation parameter to obtain the configured target orbit includes:

[0019] Based on the inclination offset, an orbit maneuver command corresponding to the regulation parameter is generated;

[0020] Based on the orbit maneuver command, the running direction of the spacecraft to be regulated on the initial orbit is adjusted to obtain the adjusted target orbit.

[0021] In some technical solutions of the present application, the above-mentioned method further includes:

[0022] Obtain the verification orbit parameters of the target orbit;

[0023] Based on the verification orbit parameters, verify the configured target orbit to determine that the target orbit reaches a preset offset value.

[0024] In some technical solutions of the present application, during the process of the spacecraft to be regulated running on the target orbit, according to the current orbit parameters of the target orbit, the spacecraft to be regulated is adjusted in real time so that the spacecraft to be regulated is within a preset range, including:

[0025] Based on the extreme value of the inclination difference of the target orbit, the current orbit radius deviation of the target orbit is calculated;

[0026] Based on the current orbit radius deviation and the deviation of the first orbital radius, the spacecraft to be regulated is adjusted in real time.

[0027] In some technical solutions of the present application, when the spacecraft to be regulated executes the second mission, the above-mentioned method further includes:

[0028] Determine a second orbital radius deviation according to the second mission requirements of the second mission performed by the spacecraft to be regulated.

[0029] Calculate the inclination offset corresponding to the second mission based on the extreme value of the inclination difference and the second orbital radius deviation.

[0030] In a second aspect, an embodiment of the present application provides a pipeline control device for a return orbit, and the device includes:

[0031] A calculation module, configured to calculate a regulation parameter according to the initial orbital parameters of the initial orbit where the spacecraft to be regulated is located.

[0032] A configuration module, configured to configure the initial orbit according to the regulation parameter to obtain a configured target orbit.

[0033] An adjustment module, configured to perform real-time adjustment on the spacecraft to be regulated according to the current orbital parameters of the target orbit during the operation of the spacecraft to be regulated on the target orbit, so that the spacecraft to be regulated is within a preset range.

[0034] In a third aspect, an embodiment of the present application provides an electronic device, including a memory, a processor, and a computer program stored on the memory and executable on the processor. When the processor executes the computer program, the steps of the pipeline control method for the return orbit described above are implemented.

[0035] 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 run by a processor, the steps of the pipeline control method for the return orbit described above are executed.

[0036] The technical solutions provided by the embodiments of the present application may include the following beneficial effects:

[0037] The method of the present application includes calculating a regulation parameter according to the initial orbital parameters of the initial orbit where the spacecraft to be regulated is located; configuring the initial orbit according to the regulation parameter to obtain a configured target orbit; during the operation of the spacecraft to be regulated on the target orbit, performing real-time adjustment on the spacecraft to be regulated according to the current orbital parameters of the target orbit, so that the spacecraft to be regulated is within a preset range.

[0038] The present application significantly reduces the number of adjustments and improves the accuracy by introducing a regulation parameter and an adjustment strategy based on the regulation parameter.

[0039] To make the above objects, features, and advantages of the present application more obvious and understandable, the following specific preferred embodiments are given in conjunction with the accompanying drawings and described in detail as follows. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] 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 some embodiments of the present application, and therefore should not be regarded as limiting the scope. For those of ordinary skill in the art, without creative efforts, other relevant drawings can also be obtained based on these drawings.

[0041] Figure 1 FIG. shows a schematic flowchart of a pipeline control method for a return orbit provided by an embodiment of the present application;

[0042] Figure 2 FIG. shows a schematic diagram of a pipeline control device for a return orbit provided by an embodiment of the present application;

[0043] Figure 3 FIG. shows a schematic diagram of another pipeline control device for a return orbit provided by an embodiment of the present application;

[0044] Figure 4 FIG. is a schematic structural diagram of an electronic device provided by an embodiment of the present application. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0045] In order to make the objectives, technical solutions, and advantages of the embodiments of the present application clearer, the technical solutions 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 illustration and description, and are not used to limit the protection scope of the present application. In addition, it should be understood that the schematic drawings are not drawn to actual scale. The flowcharts used in the present application show the operations implemented according to some embodiments of the present application. It should be understood that the operations in the flowchart may not be implemented in sequence, and steps without logical context relationships may be reversed or implemented simultaneously. In addition, those skilled in the art can add one or more other operations to the flowchart or remove one or more operations from the flowchart under the guidance of the content of the present application.

[0046] In addition, the described embodiments are only a part of the embodiments of the present application, rather than all of the embodiments. The components of the embodiments of the present application described and shown in the drawings here can usually be arranged and designed in various different 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 present application to be protected, but only represents the selected embodiments of the present application. All other embodiments obtained by those skilled in the art based on the embodiments of the present application without creative efforts belong to the scope of protection of the present application.

[0047] It should be noted that in the embodiments of the present application, the term "including" will be used to indicate the existence of the features stated thereafter, but does not exclude the addition of other features.

[0048] In satellite missions, a high-precision recurrence orbit enables a satellite to revisit a spatial target point with high precision after experiencing a strict recurrence period, and control the position recurrence accuracy in the geocentric coordinate system within the meter level. However, in actual flight, a satellite is affected by disturbing forces such as atmospheric drag, solar and lunar gravity, and solar radiation pressure, and cannot fly completely along the ideal strict recurrence orbit. Therefore, it is necessary to perform pipeline control on the satellite so that it always operates within a pipeline centered on a reference trajectory with a certain pipeline radius.

[0049] Currently, for out-of-plane pipeline control of the orbit, the commonly used method is to compare the radial, normal, and tangential directions of a comparison satellite. This method will increase the frequency of out-of-plane control and cannot achieve optimal control.

[0050] Based on this, the embodiments of the present application provide a pipeline control method, device, equipment, and medium for a recurrence orbit, which will be described below through embodiments.

[0051] Figure 1 The flowchart of a pipeline control method for a recurrence orbit provided by the embodiments of the present application is shown, where the method includes steps S101 - S103; specifically:

[0052] S101. Calculate a regulation parameter according to the initial orbit parameters of the spacecraft to be regulated on the initial orbit;

[0053] S102. Configure the initial orbit according to the regulation parameter to obtain a configured target orbit;

[0054] S103. During the operation of the spacecraft to be regulated on the target orbit, perform real-time adjustment on the spacecraft to be regulated according to the current orbit parameters of the target orbit, so that the spacecraft to be regulated is within a preset range.

[0055] The present application significantly reduces the number of adjustments and improves the accuracy by introducing a regulation parameter and an adjustment strategy based on the regulation parameter.

[0056] Some embodiments of the present application will be described in detail below. Without conflict, the following embodiments and the features in the embodiments can be combined with each other.

[0057] An embodiment of the present application provides a control method for a return orbit, which is applied to a spacecraft. A spacecraft, also known as a space vehicle or a space flyer, operates in space according to the laws of celestial mechanics and is a type of flyer that performs specific tasks such as exploring, developing, and utilizing space and celestial bodies. Spacecraft basically operate within the solar system. For example, satellites. For the convenience of describing the embodiments of the present application, the spacecraft that needs to be regulated is referred to as the spacecraft to be regulated.

[0058] The initial orbit of the spacecraft to be regulated when it first enters the orbit or the orbit when it first enters and operates is called the initial orbit. It can be determined by the Laplace method (initial value problem method), the Gauss method (boundary value problem method), and the Batrakov method. Sometimes, the motion parameters at the end of the active section of the launch vehicle are also used to determine it. Based on the determined initial orbit, the general situation of the spacecraft's operation after entering the orbit can be understood.

[0059] After determining the initial orbit of the spacecraft to be regulated, the embodiment of the present application needs to obtain the initial orbit parameters of the initial orbit. The initial orbit parameters include the extreme values of the inclination difference, specifically the maximum and minimum values of the inclination difference.

[0060] The inclination difference (Inclination Deviation) here refers to the deviation value between the initial orbit inclination of the satellite and the preset reference orbit inclination, which is used to quantify the position deviation degree of the satellite outside the orbital plane. The inclination here refers to the angle between the orbital plane and the Earth's equatorial plane, which is the core parameter describing the spatial position of the orbit. Initial orbit: An ideal orbit designed according to mission requirements, and its inclination is the theoretical target value (i ref ). Actual orbit: The real orbit of the satellite affected by disturbing forces (such as atmospheric drag, solar and lunar gravity, etc.), and its inclination is the actual measured value (i actual ).

[0061] Calculation formula for the inclination difference Δi:

[0062]

[0063] Affected by disturbing forces, the inclination difference fluctuates within the interval to obtain the maximum and minimum values of the inclination difference. Δi ∈ [Δimin, Δimax].

[0064] In an alternative embodiment, before obtaining data, it is necessary to start the satellite's orbit measurement equipment and control system, perform equipment self-check and calibration to ensure that each device is working properly. Only after determining that the equipment is working properly can data acquisition be carried out.

[0065] After determining the extreme value of the inclination difference of the initial orbit where the spacecraft to be regulated is located, the embodiment of the present application needs to calculate a regulation parameter. Here, the regulation parameter is the inclination offset, which characterizes the magnitude of the inclination error. When calculating the inclination offset, in addition to the extreme value of the inclination difference, it also includes the orbital radius deviation. Here, the orbital radius deviation is set according to specific mission requirements. For example, when performing the first mission, it is set to the first orbital radius deviation according to the first mission requirement of the first mission. When performing the second mission, it needs to be set to the second orbital radius deviation according to the second mission requirement of the second mission. And so on. When performing the Nth mission, it is set to the Nth orbital radius deviation according to the Nth mission requirement of the Nth mission. After the first mission is completed, if the second mission is to be performed subsequently, it is set to the second orbital radius deviation according to the setting, and then the spacecraft to be regulated is adjusted according to the second orbital radius deviation.

[0066] The specific calculation process is as follows: According to the radius of the earth and the real-time latitude argument of the spacecraft to be regulated, a first reference quantity is calculated; according to the first orbital radius deviation and the first reference quantity, a second reference quantity is calculated; according to the extreme value of the inclination difference and the second reference quantity, the inclination offset corresponding to the first mission is calculated.

[0067] In specific implementation, when 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 there is:

[0068]

[0069] The maximum allowable deviation of the pipeline radius (δRmax, the first orbital radius deviation) needs to satisfy: ∣δR∣≤δRmax.

[0070] By introducing the inclination offset ( ), the original inclination difference range is translated, so that the adjusted inclination difference dynamic range is reduced. The adjusted inclination difference is:

[0071]

[0072] It is required that the adjusted inclination difference satisfies:

[0073]

[0074] Solve the simultaneous equations to find the inclination offset, and substitute the original extreme values of the inclination difference (Δimax and Δimin) into the constraint conditions:

[0075]

[0076] The reasonable range of the inclination offset δi is obtained:

[0077]

[0078] Optimal inclination offset: To minimize the control frequency, the median value of the interval is usually taken:

[0079]

[0080] Among them, the "±" sign needs to be adjusted according to the direction of the perturbing force. Combining the directionality of the influence of the perturbing force (such as the dominant direction of the sun and moon gravity), the "±" sign is dynamically adjusted to improve the control adaptability.

[0081] After obtaining the inclination offset, the embodiment of the present application needs to configure the initial orbit according to the inclination deviation to obtain the configured target orbit. Here, the target orbit is the orbit for the spacecraft to be regulated to perform tasks. The specific configuration process includes generating an orbit maneuver command according to the calculated inclination offset, determining the required thrust direction (normal or lateral) and velocity increment (Δv). Using the chemical thruster or electric thruster (such as ion thruster) of the spacecraft to be regulated, apply Δv along the normal direction of the orbit to adjust the orbit inclination to the target value. Control the working duration and thrust magnitude of the thruster to ensure that the adjustment accuracy is better than 0.001°.

[0082] Orbit confirmation and calibration: After adjustment, obtain the verification orbit parameters of the target orbit; according to the verification orbit parameters, verify the configured target orbit to determine that the target orbit reaches the preset offset value. If there is a residual error, perform fine-tuning until the first pipeline radius requirement is met.

[0083] After the target orbit passes the verification, control the spacecraft to be regulated to operate on the target orbit. At the same time, during the operation process, the embodiment of the present application also needs to adjust the real-time position of the spacecraft to be regulated. Specifically, the embodiment of the present application obtains the current orbit parameters of the target orbit, and calculates the current orbit radius deviation of the target orbit according to the extreme value of the inclination difference of the target orbit; according to the current orbit radius deviation and the first orbit radius deviation, perform real-time adjustment on the spacecraft to be regulated.

[0084] In the specific implementation, deploy an on-board high-precision orbit sensor (such as a laser interferometer) to collect the orbit inclination, real-time latitude argument, etc. at a frequency of once per second. Compare the current orbit radius deviation with the first orbit radius deviation. If the current orbit radius deviation is greater than the first orbit radius deviation, trigger a control command. Adopt a proportional-integral-differential (PID) control algorithm to calculate the required thrust direction and Δv in real time according to the deviation magnitude. Give priority to using a low-thrust electric thruster for continuous fine-tuning to avoid fuel waste. Monitor the orbit parameters again after each adjustment to ensure that it returns to the pipeline. Optimize the PID parameters according to the historical control data to improve the response speed and stability.

[0085] In the embodiments of the present application, by introducing an inclination bias optimization control strategy and combining it with a dynamic feedback mechanism, the out-of-plane control frequency of the orbit is significantly reduced, and the satellite orbit accuracy and stability are improved.

[0086] Figure 2 The structure diagram of a pipeline control device for a regression orbit provided by the embodiments of the present application is shown. The device includes:

[0087] A calculation module, configured to calculate a regulation parameter according to the initial orbit parameters of the spacecraft to be regulated in the initial orbit.

[0088] A configuration module, configured to configure the initial orbit according to the regulation parameter to obtain a configured target orbit.

[0089] An adjustment module, configured to perform real-time adjustment on the spacecraft to be regulated according to the current orbit parameters of the target orbit during the operation of the spacecraft to be regulated on the target orbit, so that the spacecraft to be regulated is within a preset range.

[0090] The initial orbit parameters include the extreme value of the inclination difference, and the regulation parameter is the inclination bias.

[0091] Calculating a regulation parameter according to the initial orbit parameters of the spacecraft to be regulated in the initial orbit includes:

[0092] Determining the extreme value of the inclination difference of the initial orbit where the spacecraft to be regulated is located.

[0093] Determining a first orbit radius deviation according to the first task requirements of the first task executed by the spacecraft to be regulated.

[0094] Calculating the inclination bias corresponding to the first task according to the extreme value of the inclination difference and the first orbit radius deviation.

[0095] Calculating the inclination bias corresponding to the first task according to the extreme value of the inclination difference and the first orbit radius deviation includes:

[0096] Calculating a first reference quantity according to the Earth radius and the real-time latitude argument of the spacecraft to be regulated.

[0097] Calculating a second reference quantity according to the first orbit radius deviation and the first reference quantity.

[0098] Calculating the inclination bias corresponding to the first task according to the extreme value of the inclination difference and the second reference quantity.

[0099] Configuring the initial orbit according to the regulation parameter to obtain a configured target orbit includes:

[0100] Generate an orbital maneuver command corresponding to the regulation parameter according to the inclination offset;

[0101] Adjust the running direction of the spacecraft to be regulated on the initial orbit according to the orbital maneuver command to obtain the adjusted target orbit.

[0102] As Figure 3 shown, the device further includes:

[0103] A verification module, configured to obtain verification orbit parameters of the target orbit;

[0104] Verify the configured target orbit according to the verification orbit parameters, and determine that the target orbit reaches a preset offset value.

[0105] During the process of the spacecraft to be regulated running on the target orbit, perform real-time adjustment on the spacecraft to be regulated according to the current orbit parameters of the target orbit, so that the spacecraft to be regulated is within a preset range, including:

[0106] Calculate the current orbit radius deviation of the target orbit according to the extreme value of the inclination difference of the target orbit;

[0107] Perform real-time adjustment on the spacecraft to be regulated according to the current orbit radius deviation and the first orbit radius deviation.

[0108] When the spacecraft to be regulated performs a second task, it further includes:

[0109] Determine a second orbit radius deviation according to the second task requirements of the second task performed by the spacecraft to be regulated;

[0110] Calculate the inclination offset corresponding to the second task according to the extreme value of the inclination difference and the second orbit radius deviation.

[0111] As Figure 4 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. The device includes a memory, a processor, a bus, and a computer program stored on the memory and executable on the processor. When the processor executes the computer program, the steps of the pipeline control method of the regression orbit described above are implemented.

[0112] Specifically, the above-mentioned memory and processor can be general memory and processor, which are not specifically limited here. When the processor runs the computer program stored in the memory, it can execute the pipeline control method of the regression orbit described above.

[0113] Corresponding to the pipeline control method of the return orbit in this application, an embodiment of this application also provides a computer-readable storage medium. A computer program is stored on this computer-readable storage medium, and when the computer program is run by a processor, it executes the steps of the pipeline control method of the above return orbit.

[0114] Specifically, this storage medium can be a general storage medium, such as a mobile disk, a hard disk, etc. When the computer program on this storage medium is run, it can execute the pipeline control method of the above return orbit.

[0115] In the embodiments provided in this application, it should be understood that the disclosed system and method can be implemented in other ways. The system embodiments described above are only illustrative. For example, the division of the units is only a logical function division. In actual implementation, there may be other division methods. For another example, multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point, the displayed or discussed coupling or direct coupling or communication connection between each other can be through some communication interfaces. The indirect coupling or communication connection of the system or unit can be in an electrical, mechanical or other form.

[0116] The units described as separate components may or may not be physically separated. The components displayed as units may or may not be physical units. They can be located in one place or distributed to multiple network units. Some or all of the units can be selected according to actual needs to achieve the purpose of the solution of this embodiment.

[0117] In addition, each functional unit in the embodiments provided in this application can be integrated in a processing unit, or each unit can exist physically alone, or two or more units can be integrated in one unit.

[0118] If the function is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on such an understanding, the technical solution of this application, in essence, or the part that contributes to the prior art, or a part of this technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to enable a computer device (which can be a personal computer, a server, or a network device, etc.) to execute all or part of the steps of the methods described in various embodiments of this application. The aforementioned storage medium includes: various media such as USB flash drives, mobile hard disks, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical discs that can store program codes.

[0119] It should be noted that like reference numerals and letters denote like 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 for descriptive distinction and should not be construed as indicating or implying relative importance.

[0120] Finally, it should be noted that the above-described embodiments are only specific embodiments 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 has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that any person skilled in the art within the technical scope disclosed by the present application can still modify the technical solutions recorded in the foregoing embodiments or can easily conceive of changes, or perform equivalent replacements on some of the technical features; and these modifications, changes or replacements do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present application. All of them should be covered by the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A pipeline control method for a return orbit, characterized in that, The method includes: Calculating a regulation parameter according to the initial orbit parameters of the spacecraft to be regulated in the initial orbit; Configuring the initial orbit according to the regulation parameter to obtain a configured target orbit; During the operation of the spacecraft to be regulated on the target orbit, according to the current orbit parameters of the target orbit, making real-time adjustments to the spacecraft to be regulated so that the spacecraft to be regulated is within a preset range; The initial orbit parameters include the extreme value of the inclination difference, and the regulation parameter is the inclination offset; The calculating a regulation parameter according to the initial orbit parameters of the spacecraft to be regulated in the initial orbit includes: Determining the extreme value of the inclination difference of the initial orbit where the spacecraft to be regulated is located; Determining a first orbit radius deviation according to the first mission requirements of the first mission executed by the spacecraft to be regulated; Calculating the inclination offset corresponding to the first mission according to the extreme value of the inclination difference and the first orbit radius deviation; The calculating the inclination offset corresponding to the first mission according to the extreme value of the inclination difference and the first orbit radius deviation includes: Calculating a first reference quantity according to the radius of the earth and the real-time latitude argument of the spacecraft to be regulated; Calculating a second reference quantity according to the first orbit radius deviation and the first reference quantity; Calculating the inclination offset corresponding to the first mission according to the extreme value of the inclination difference and the second reference quantity.

2. The method according to claim 1, wherein The configuring the initial orbit according to the regulation parameter to obtain a configured target orbit includes: Generating an orbit maneuver command corresponding to the regulation parameter according to the inclination offset; Adjusting the running direction of the spacecraft to be regulated in the initial orbit according to the orbit maneuver command to obtain the adjusted target orbit.

3. The method according to claim 2, wherein The method further includes: Obtaining the verification orbit parameters of the target orbit; Verifying the configured target orbit according to the verification orbit parameters to determine that the target orbit reaches a preset offset value.

4. The method according to claim 1, wherein During the operation of the spacecraft to be regulated on the target orbit, according to the current orbit parameters of the target orbit, making real-time adjustments to the spacecraft to be regulated so that the spacecraft to be regulated is within a preset range, includes: Calculating the current orbit radius deviation of the target orbit according to the extreme value of the inclination difference of the target orbit; Making real-time adjustments to the spacecraft to be regulated according to the current orbit radius deviation and the first orbit radius deviation.

5. The method according to claim 1, characterized in that, When the spacecraft to be regulated executes a second mission, the method further includes: Determining a second orbit radius deviation according to the second mission requirements of the second mission executed by the spacecraft to be regulated; Calculating the inclination offset corresponding to the second mission according to the extreme value of the inclination difference and the second orbit radius deviation.

6. A pipeline control device for a return orbit, characterized in that, The device includes: A calculation module, configured to calculate a regulation parameter according to the initial orbit parameters of the spacecraft to be regulated in the initial orbit; A configuration module, configured to configure the initial orbit according to the regulation parameter to obtain a configured target orbit; An adjustment module is used to perform real-time adjustment on the spacecraft to be regulated during the operation of the spacecraft to be regulated on the target orbit according to the current orbital parameters of the target orbit, so that the spacecraft to be regulated is within a preset range; The initial orbital parameters include the extreme value of the inclination difference, and the regulation parameter is the inclination offset; Calculating a regulation parameter according to the initial orbital parameters of the initial orbit where the spacecraft to be regulated is located includes: Determining the extreme value of the inclination difference of the initial orbit where the spacecraft to be regulated is located; Determining a first orbital radius deviation according to the first mission requirements of the first mission executed by the spacecraft to be regulated; Calculating the inclination offset corresponding to the first mission according to the extreme value of the inclination difference and the first orbital radius deviation; Calculating the inclination offset corresponding to the first mission according to the extreme value of the inclination difference and the first orbital radius deviation includes: Calculating a first reference quantity according to the Earth radius and the real-time latitude argument of the spacecraft to be regulated; Calculating a second reference quantity according to the first orbital radius deviation and the first reference quantity; Calculating the inclination offset corresponding to the first mission according to the extreme value of the inclination difference and the second reference quantity.

7. An electronic device, characterized in that, Including: A processor, a memory and a bus, the memory stores machine-readable instructions executable by the processor. When the electronic device runs, the processor communicates with the memory through the bus. When the machine-readable instructions are executed by the processor, the steps of the pipeline control method of the return orbit according to any one of claims 1 to 5 are executed.

8. A computer-readable storage medium, characterized in that, A computer program is stored on the computer-readable storage medium. When the computer program is run by the processor, the steps of the pipeline control method of the return orbit according to any one of claims 1 to 5 are executed.

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