A control method suitable for autonomous station-keeping acquisition of a high orbit satellite

Abstract

The application discloses a kind of suitable for high-orbit satellite autonomous spot acquisition control method, using three-pulse joint control strategy of drift rate and eccentricity, so that satellite completes spot acquisition in an orbit period, reaches near nominal spot position, and drift rate and eccentricity meet the requirements of acquisition index.The application can meet the demand of new generation high-orbit satellite, especially overseas spot autonomous working ability improvement, that is, it can be used for autonomous satellite spot acquisition task in flight control stage, and can be used for satellite spot drift and spot recapture control after spot, effectively improves satellite transfer segment autonomous working and fault self-recovery ability during synchronous segment autonomous operation, and has high economic value and practical value.

Description

Technical Field

[0001] This invention relates to a method for autonomous positioning and acquisition control of high-orbit satellites, belonging to the field of satellite autonomous orbit control technology. Background Technology

[0002] After undergoing multiple apogee maneuvers upon launch and insertion into orbit, a high-orbit satellite reaches a quasi-geosynchronous orbit. Next, it requires multi-pulse fixed-point acquisition control (either accelerating eastward or decelerating westward) to correct remaining deviations in longitude, eccentricity, and drift rate, ensuring the satellite reaches its predetermined longitude position and is ready to begin normal operation and routine position-keeping control. If necessary, when the satellite needs to change its fixed-point position or abnormally drifts out of the position-keeping loop, fixed-point acquisition control can be re-performed to bring the satellite to a new fixed-point position or back to its original fixed-point position, allowing routine position-keeping control to continue.

[0003] Currently, geostationary acquisition control for high-orbit satellites is performed during the flight control mission phase. Ground control stations formulate geostationary acquisition strategies based on the precise orbit determination results after satellite orbit changes, and personnel organize multiple geostationary acquisition maneuvers according to the plan, requiring significant human and material resources. With technological advancements, to meet the needs of next-generation high-orbit satellites, especially those with geostationary positions overseas and lacking ground control station support, it is necessary to research onboard autonomous geostationary acquisition control functions to satisfy the satellite's autonomous operation requirements. Summary of the Invention

[0004] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide a method for autonomous fixed-point acquisition control of high-orbit satellites. It adopts a three-pulse joint control strategy of longitude, drift rate and eccentricity to enable the satellite to complete fixed-point acquisition within one orbital period and reach near the nominal fixed-point position. The drift rate and eccentricity meet the acquisition index requirements, and the fault self-recovery capability during the autonomous operation of the satellite transfer segment and the autonomous operation of the synchronization segment is improved.

[0005] The technical solution of the present invention is: Firstly, a method for autonomous positioning and acquisition control of high-orbit satellites, comprising: Based on the satellite's current orbital parameters and the target value for fixed-point acquisition, calculate the control values ​​for longitude, eccentricity, and drift rate; Based on the control values ​​of longitude, eccentricity, and drift rate, calculate the three capture pulses for the fixed-point capture process; The ignition position of the first capture pulse is calculated based on the eccentricity control value; The fixed-point acquisition control process is as follows: when the satellite's right ascension reaches the ignition position of the first acquisition pulse, the first acquisition pulse is executed, and the second and third acquisition pulses are executed sequentially at half orbital intervals, thus completing the fixed-point acquisition control.

[0006] Furthermore, the calculation of the longitude, eccentricity, and drift rate control quantities based on the satellite's current orbital parameters and the target value for fixed-point acquisition includes: Calculate the longitude control amount Specifically: In the formula This is the satellite's current average longitude. To pinpoint and acquire the target's longitude; Calculate the eccentricity control value Specifically: In the formula and The eccentricity vector deviation is specifically: In the formula and The current eccentricity vector of the satellite is defined as: in e Ω represents the current eccentricity of the satellite, and Ω represents the right ascension of the current ascending node of the satellite. ω This is the current perigee argument of the satellite. and The target eccentricity vector; Calculate the drift rate control quantity Specifically: In the formula This represents the satellite's current drift rate, expressed in degrees per day. To capture the target drift rate.

[0007] Furthermore, the calculation of three acquisition pulses for fixed-point acquisition based on the control values ​​of longitude, eccentricity, and drift rate includes: Calculate drift rate to control speed increment Specifically: Calculate the eccentricity control speed increment Specifically: The formula for calculating the velocity increment of three pulses for fixed-point acquisition is as follows: .

[0008] Further, the calculation of the ignition position of the first capture pulse based on the eccentricity control amount includes: Based on eccentricity control amount and Calculate the right ascension of the first pulse ignition point L 1. Specifically: .

[0009] Secondly, a system for autonomous positioning and acquisition control of high-orbit satellites includes: The first module calculates the longitude, eccentricity, and drift rate control values ​​based on the satellite's current orbital parameters and the target value for fixed-point acquisition. The second module calculates the three capture pulses for the fixed-point capture process based on the control values ​​of longitude, eccentricity, and drift rate. The third module calculates the ignition position of the first captured pulse based on the eccentricity control value; The fourth module executes the fixed-point acquisition control process: when the satellite's right ascension reaches the ignition position of the first acquisition pulse, the first acquisition pulse is executed, and the second and third acquisition pulses are executed sequentially at half-orbit intervals, finally completing the fixed-point acquisition control.

[0010] Furthermore, the calculation of the longitude, eccentricity, and drift rate control quantities based on the satellite's current orbital parameters and the target value for fixed-point acquisition includes: Calculate the longitude control amount Specifically: In the formula This is the satellite's current average longitude. To pinpoint and acquire the target's longitude; Calculate the eccentricity control value Specifically: In the formula and The eccentricity vector deviation is specifically: In the formula and The current eccentricity vector of the satellite is defined as: in e Ω represents the current eccentricity of the satellite, and Ω represents the right ascension of the current ascending node of the satellite. ω This is the current perigee argument of the satellite. and The target eccentricity vector; Calculate drift rate control quantity Specifically: In the formula This represents the satellite's current drift rate, expressed in degrees per day. To capture the target drift rate.

[0011] Furthermore, the calculation of three acquisition pulses for fixed-point acquisition based on the control values ​​of longitude, eccentricity, and drift rate includes: Calculate drift rate to control speed increment Specifically: Calculate the eccentricity control speed increment Specifically: The formula for calculating the velocity increment of three pulses for fixed-point acquisition is as follows: .

[0012] Further, the calculation of the ignition position of the first capture pulse based on the eccentricity control amount includes: Based on eccentricity control amount and Calculate the right ascension of the first pulse ignition point L 1. Specifically: .

[0013] Thirdly, a computer-readable storage medium stores a computer program that, when executed by a processor, implements the steps of the method for autonomous positioning and acquisition control of high-orbit satellites.

[0014] Fourthly, a device for autonomous positioning and acquisition control of high-orbit satellites includes a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, it implements the steps of the method for autonomous positioning and acquisition control of high-orbit satellites.

[0015] The advantages of this invention compared to the prior art are: (1) This invention can meet the needs of the new generation of high-orbit satellites, especially the improvement of their overseas fixed-point autonomous working capabilities. It can be used to complete the satellite fixed-point acquisition task autonomously during the flight control phase, and can also be used for satellite drift and fixed-point reacquisition control after satellite fixed-point positioning. It effectively improves the satellite's fault self-recovery capability during autonomous operation in the transfer phase and autonomous operation in the synchronization phase, and has high economic and practical value.

[0016] (2) This invention employs a three-pulse joint control strategy based on longitude, drift rate, and eccentricity, enabling the satellite to achieve point-to-point acquisition within one orbital period, reaching the vicinity of the nominal point-to-point position, while the drift rate and eccentricity meet the acquisition requirements. The advantage of using three pulses is that any one of the elements—longitude, eccentricity, or drift rate—can be controlled independently without affecting other elements. The three pulses are executed sequentially within one orbital period, quickly achieving point-to-point acquisition control or point-to-point reacquisition after anomalies, saving control time and improving anomaly recovery capabilities. Attached Figure Description

[0017] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings: Figure 1 Simulation curve of geographical longitude change during fixed-point capture process; Figure 2 The simulation curve of eccentricity change during the fixed-point capture process; Figure 3 The simulation curve of the semi-major axis change during the fixed-point capture process; Figure 4 This is a schematic diagram of the fixed-point capture control process of the present invention. Detailed Implementation

[0018] To better understand the above technical solutions, the technical solutions of the present invention will be described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the embodiments of the present invention and the specific features in the embodiments are detailed descriptions of the technical solutions of the present invention, rather than limitations on the technical solutions of the present invention. In the absence of conflict, the embodiments of the present invention and the technical features in the embodiments can be combined with each other.

[0019] The following description, in conjunction with the accompanying drawings, provides a more detailed explanation of an autonomous positioning and acquisition control method for high-orbit satellites provided by an embodiment of the present invention. Figure 4 Specific implementation methods may include: (1) First, calculate the longitude, eccentricity and drift rate control values ​​based on the current orbital parameters of the satellite and the target value of the fixed-point acquisition; (2) Next, based on the longitude, eccentricity and drift rate control values, calculate the velocity increment of the three pulses for fixed-point capture; (3) Then calculate the ignition position of the first pulse based on the eccentricity vector control quantity; (4) When the satellite's right ascension reaches the first pulse ignition position, the first capture pulse is executed, and the second and third capture pulses are executed in sequence at half orbital intervals, and finally the fixed-point capture control is completed.

[0020] Step (1) involves calculating the longitude, eccentricity, and drift rate control values ​​based on the satellite's current orbital parameters and the target value for fixed-point acquisition. Specifically: 1) First, calculate the longitude control amount. Specifically: In the formula The satellite's current mean longitude is in degrees. The longitude of the target is used for fixed-point acquisition, which is usually the geographical longitude of the satellite's fixed-point location.

[0021] 2) Next, calculate the eccentricity control value. Specifically: In the formula and The eccentricity vector deviation is specifically: In the formula and The current eccentricity vector of the satellite is defined as: in e Ω represents the current eccentricity of the satellite, and Ω represents the right ascension of the current ascending node of the satellite. ω This is the current perigee argument of the satellite. and Given the target eccentricity vector, a sun-synchronous eccentricity control strategy is adopted, and the calculation formula is as follows: in To set the target eccentricity, it is usually set to 0.0001; The formula for calculating the right ascension of the sun is: in and These are the X-axis and Y-axis components of the solar vector in the J2000 inertial frame, respectively.

[0022] 3) Calculate the drift rate control value Specifically: In the formula This represents the satellite's current drift rate, expressed in degrees per day. To capture the target drift rate, the target value is typically set to 0.

[0023] Step (2) calculates the velocity increment of the three-pulse fixed-point capture based on the control values ​​of longitude, eccentricity, and drift rate, specifically as follows: 1) First, calculate the drift rate control speed increment. Specifically: 2) Next, calculate the eccentricity control speed increment. Specifically: 3) Fixed-point capture of the three-pulse velocity increment, the calculation formula is: Step (3) involves calculating the first pulse ignition position based on the eccentricity vector control quantity, specifically as follows: Based on the eccentricity vector control quantity and Calculate the right ascension of the first pulse ignition point L 1. Specifically: The fixed-point capture control process in step (4) is as follows: When the satellite's right ascension reaches the first pulse ignition position L The first capture pulse is executed at 1 o'clock. After a half-orbit cycle, the second capture pulse is executed. After another half orbital cycle, the third capture pulse is executed. Finally, fixed-point capture control is completed.

[0024] In the solution provided in this embodiment of the invention, the autonomous fixed-point acquisition control method proposed in this invention is verified by mathematical simulation. Taking a geostationary satellite as an example, it is assumed that the satellite has undergone multiple apogee maneuvers to reach a quasi-synchronous orbit, and its current longitude position is 119.5°E, located 0.5° west of the fixed-point position of 120°E, with an eccentricity of 0.0005. Three-pulse autonomous fixed-point acquisition control is activated, and the satellite is controlled to reach the fixed-point position within one orbital cycle, entering the position-keeping loop. The entire process satellite geographic longitude change curve is shown below. Figure 1 As shown, the eccentricity variation curve is as follows: Figure 2 As shown, the drift rate is reflected by the change in the semi-major axis, as shown in the curve. Figure 3 As shown in the figure. Simulation results show that the three-pulse fixed-point acquisition control successfully enabled the satellite to drift to a range of 120°E±0.05° within one day, while the eccentricity decreased from 0.0005 to less than 0.0002, and the drift rate approached zero, thus meeting the fixed-point requirements.

[0025] This invention provides a computer-readable storage medium storing computer instructions that, when executed on a computer, cause the computer to perform... Figure 4 The method described.

[0026] Those skilled in the art will understand that embodiments of the present invention can be provided as methods, systems, or computer program products. Therefore, the present invention can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, the present invention can take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage and optical storage) containing computer-usable program code.

[0027] This invention is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the invention. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations 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, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, generate instructions for implementing the flowchart illustrations and / or block diagrams. Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0028] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.

[0029] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0030] Obviously, those skilled in the art can make various modifications and variations to this invention without departing from its spirit and scope. Therefore, if these modifications and variations fall within the scope of the claims of this invention and their equivalents, this invention also intends to include these modifications and variations.

[0031] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A method for autonomous positioning and acquisition control of high-orbit satellites, characterized in that, include: Based on the satellite's current orbital parameters and the target value for fixed-point acquisition, calculate the control values ​​for longitude, eccentricity, and drift rate; Based on the control values ​​of longitude, eccentricity, and drift rate, calculate the three capture pulses for the fixed-point capture process; The ignition position of the first capture pulse is calculated based on the eccentricity control value; The fixed-point acquisition control process is as follows: when the satellite's right ascension reaches the ignition position of the first acquisition pulse, the first acquisition pulse is executed, and the second and third acquisition pulses are executed sequentially at half orbital intervals, thus completing the fixed-point acquisition control.

2. The method for autonomous positioning and acquisition control of high-orbit satellites according to claim 1, characterized in that, The calculation of longitude, eccentricity, and drift rate control parameters based on the satellite's current orbital parameters and the target value for fixed-point acquisition includes: Calculate the longitude control amount Specifically: In the formula This is the satellite's current average longitude. To pinpoint and acquire the target's longitude; Calculate the eccentricity control value Specifically: In the formula and The eccentricity vector deviation is specifically: In the formula and The current eccentricity vector of the satellite is defined as: in e Ω represents the current eccentricity of the satellite, and Ω represents the right ascension of the current ascending node of the satellite. ω This is the current perigee argument of the satellite. and The target eccentricity vector; Calculate drift rate control quantity Specifically: In the formula This represents the satellite's current drift rate, expressed in degrees per day. To capture the target drift rate.

3. The method for autonomous positioning and acquisition control of high-orbit satellites according to claim 1, characterized in that, The calculation of three acquisition pulses for fixed-point acquisition based on the control values ​​of longitude, eccentricity, and drift rate includes: Calculate drift rate to control speed increment Specifically: Calculate the eccentricity control speed increment Specifically: The formula for calculating the velocity increment of three pulses for fixed-point acquisition is as follows: 。 4. The method for autonomous positioning and acquisition control of high-orbit satellites according to claim 1, characterized in that, The calculation of the ignition position of the first capture pulse based on the eccentricity control value includes: Based on eccentricity control amount and Calculate the right ascension of the first pulse ignition point L 1. Specifically: 。 5. A control system for autonomous positioning and acquisition of high-orbit satellites, characterized in that, include: The first module calculates the longitude, eccentricity, and drift rate control values ​​based on the satellite's current orbital parameters and the target value for fixed-point acquisition. The second module calculates the three capture pulses for the fixed-point capture process based on the control values ​​of longitude, eccentricity, and drift rate. The third module calculates the ignition position of the first captured pulse based on the eccentricity control value; The fourth module executes the fixed-point acquisition control process: when the satellite's right ascension reaches the ignition position of the first acquisition pulse, the first acquisition pulse is executed, and the second and third acquisition pulses are executed sequentially at half-orbit intervals, finally completing the fixed-point acquisition control.

6. A high-orbit satellite autonomous positioning and acquisition control system according to claim 5, characterized in that, The calculation of longitude, eccentricity, and drift rate control parameters based on the satellite's current orbital parameters and the target value for fixed-point acquisition includes: Calculate the longitude control amount Specifically: In the formula This is the satellite's current average longitude. To pinpoint and acquire the target's longitude; Calculate the eccentricity control value Specifically: In the formula and The eccentricity vector deviation is specifically: In the formula and The current eccentricity vector of the satellite is defined as: in e Ω represents the current eccentricity of the satellite, and Ω represents the right ascension of the current ascending node of the satellite. ω This is the current perigee argument of the satellite. and The target eccentricity vector; Calculate drift rate control quantity Specifically: In the formula This represents the satellite's current drift rate, expressed in degrees per day. To capture the target drift rate.

7. A high-orbit satellite autonomous positioning and acquisition control system according to claim 5, characterized in that, The calculation of three acquisition pulses for fixed-point acquisition based on the control values ​​of longitude, eccentricity, and drift rate includes: Calculate drift rate to control speed increment Specifically: Calculate the eccentricity control speed increment Specifically: The formula for calculating the velocity increment of three pulses for fixed-point acquisition is as follows: 。 8. A high-orbit satellite autonomous positioning and acquisition control system according to claim 5, characterized in that, The calculation of the ignition position of the first capture pulse based on the eccentricity control value includes: Based on eccentricity control amount and Calculate the right ascension of the first pulse ignition point L 1. Specifically: 。 9. A computer-readable storage medium storing a computer program, characterized in that, When the computer program is executed by a processor, it implements the steps of the method as described in any one of claims 1 to 4.

10. A device for autonomous positioning and acquisition control of high-orbit satellites, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that: When the processor executes the computer program, it implements the steps of the method as described in any one of claims 1 to 4.

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