Non-cooperative spacecraft maneuver parameter quantitative identification method and system

Abstract

The application provides a non-cooperative spacecraft maneuver parameter quantitative identification method and system, and belongs to the technical field of aerospace. The non-cooperative spacecraft maneuver parameter quantitative identification method comprises the following steps: based on spacecraft relative orbit dynamics, an unknown impulse maneuver time parameter optimization model of a non-cooperative spacecraft is established; the motion state before and after one impulse maneuver of the non-cooperative spacecraft is acquired, and an optimization algorithm is used to solve the unknown impulse maneuver time parameter of the non-cooperative spacecraft; the motion state before and after the impulse maneuver of the maneuver point is calculated according to the maneuver time parameter and the optimization model, and finally the maneuver position and velocity pulse increment of the maneuver point are calculated. The application realizes the identification of the unknown impulse maneuver parameter of the non-cooperative spacecraft, is an important link for researching space situation information, has important theoretical research value, and can quantitatively analyze the maneuver parameter of the non-cooperative target.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and in particular to a method and system for quantitative identification of maneuver parameters of non-cooperative spacecraft. Background Technology

[0002] The study of space situation information involves detecting and acquiring information about space targets, analyzing the situation of space targets and their impact on humans. Its main tasks are to accurately detect and track space targets, determine the important characteristics of space targets that may pose a threat to aerospace systems, such as size, shape, and orbital parameters, and classify and distribute the target characteristic data.

[0003] With the increasing activity of human spacefaring, a large number of man-made objects have been generated in the space surrounding Earth, including spacecraft, rocket final stages, and space debris. While these objects bring convenience to humanity, they also affect human space activities, thus necessitating the study of space situational information. Furthermore, with the increasing frequency of space activities and the growing number of spacecraft in orbit, a massive amount of maneuvering parameter information is generated. This requires more effective use of this information for orbital behavior analysis and prediction, determining the historical and real-time status of spacecraft. In addition, rapid and accurate detection of orbital maneuvers is also crucial for ensuring the safe operation of spacecraft.

[0004] Current orbital maneuver detection methods are mainly based on post-hoc maneuver detection using historical orbital information. This method can only determine whether a maneuver has occurred, but cannot quantitatively identify maneuver parameters. For maneuver parameter information identification methods, most existing technologies rely on continuous angle or range measurement tracking of the target using space-based or ground-based platforms, combined with dynamic models and filtering methods for maneuver trajectory determination and maneuver identification. Researching methods for identifying maneuver parameter information of non-cooperative spacecraft is a crucial step in studying space situational information and has significant theoretical research value. Summary of the Invention

[0005] To address the problems existing in the prior art, this invention provides a method and system for quantitatively identifying the maneuvering parameters of non-cooperative spacecraft. The identification method of this invention is designed for limited observation data, requiring only the motion state before and after the pulse maneuver to quantitatively analyze the maneuvering parameters of non-cooperative targets, including maneuvering time, pulse velocity increment, and maneuvering spatial position.

[0006] To achieve the above objectives, the present invention provides the following technical solution.

[0007] This invention provides a method for quantitative identification of maneuver parameters of non-cooperative spacecraft, comprising the following steps:

[0008] S1. Based on the relative orbital dynamics of spacecraft, establish an optimization model for the unknown pulse maneuver time parameters of non-cooperative spacecraft;

[0009] S2, obtain the motion state of the non-cooperative spacecraft before and after a pulse maneuver, and use an optimization algorithm to solve for the unknown pulse maneuver time parameters of the non-cooperative spacecraft;

[0010] S3, based on the unknown pulse maneuvering time parameters of the non-cooperative spacecraft and the optimization model of the unknown pulse maneuvering time parameters of the non-cooperative spacecraft, the motion state of the computer moving point before and after applying the pulse maneuvering;

[0011] S4 calculates the maneuver position and velocity pulse increment of the moving point based on the motion state before and after applying the pulse maneuver.

[0012] As a further improvement to the present invention, the specific steps of S1 are as follows:

[0013] 1) In a near-circular orbit, the state transition equations for a non-cooperative spacecraft under uncontrolled conditions:

[0014] (1)

[0015] in, The state transition matrix is:

[0016] (2)

[0017] In the above formula, the symbols have the following meanings:

[0018] —The radial position component of the orbit in the LVLH system;

[0019] —Position component of the flight direction in the LVLH system;

[0020] —Position component of orbital angular momentum in the LVLH system;

[0021] —The radial velocity component of the orbit in the LVLH system;

[0022] —The velocity component of the flight direction in the LVLH system;

[0023] —The velocity component in the direction of orbital angular momentum in the LVLH system;

[0024] —State time interval;

[0025] —Relative motion reference spacecraft angular rate;

[0026] When a non-cooperative spacecraft performs a pulse maneuver at the maneuver point, the spacecraft's motion status is detected at positions before and after the maneuver point. and , Reaching the maneuver point P It takes time Maneuvering point P arrive It takes time. ,based on and Establish an optimization model for the time parameters of unknown pulse maneuvers in a non-cooperative spacecraft:

[0027] (3)

[0028] In the formula, The pulse maneuver assignment matrix is:

[0029] (4)

[0030] In the formula, The optimized index weight matrix is ​​as follows:

[0031] (5)

[0032] In the formula, for The time required to reach the maneuver point Arrival at the maneuver point The time required for processing; The motion state before applying the pulse maneuver to the maneuver point. The motion state after applying a pulse maneuver to the maneuver point; To apply pulse maneuvering at the velocity pulse increment at the maneuvering point; for The optimal time required to reach the maneuver point. Arrival at the maneuver point The optimal time required.

[0033] As a further improvement of the present invention, S2 includes:

[0034] Obtain the motion state of a non-cooperative spacecraft before and after a pulse maneuver. and The particle swarm optimization algorithm is used to solve for the unknown pulse maneuver time parameters of non-cooperative spacecraft;

[0035] The solved unknown pulse maneuver time for the non-cooperative spacecraft is and ; for The time required to reach the maneuver point Arrival at the maneuver point The time required.

[0036] As a further improvement of the present invention, S3 includes:

[0037] Based on the unknown pulse maneuvering time of non-cooperative spacecraft and The obtained motion state of the non-cooperative spacecraft before and after a single pulse maneuver. and Then, based on the optimization model of unknown pulse maneuver time parameters of a non-cooperative spacecraft, the motion state of the computer moving point before and after applying the pulse maneuver was determined. and .

[0038] As a further improvement of the present invention, the motion state of the computer moving point before and after applying pulse maneuvering. and ,include:

[0039] (6)

[0040] In the formula, To obtain the motion state of a non-cooperative spacecraft prior to a single pulse maneuver; To obtain the motion state of a non-cooperative spacecraft after a single pulse maneuver; for The time required to reach the maneuver point; Arrival at the maneuver point The time required for processing; Here is the state transition matrix. Will Substitute into the state transition matrix ; Will Substitute into the state transition matrix ; The motion state before applying a pulse maneuver to the maneuver point; The motion state after applying a pulse maneuver to the maneuver point.

[0041] As a further improvement of the present invention, S4 calculates the maneuver position of the pulse maneuver at the maneuver point, including:

[0042] (7)

[0043] In the formula, The radial position component of the orbit in the LVLH system; The position component of the flight direction in the LVLH system; The position component of the orbital angular momentum in the LVLH system; The motion state before applying a pulse maneuver to the maneuver point; The motion state after applying a pulse maneuver to the maneuver point.

[0044] As a further improvement of the present invention, S4 calculates the velocity pulse increment at the maneuver point for the unknown pulse maneuver, including:

[0045] (8)

[0046] In the formula, The radial velocity component of the orbit in the LVLH system; —The velocity component in the direction of flight in the LVLH system; For the velocity component in the direction of orbital angular momentum in the LVLH system; The motion state before applying a pulse maneuver to the maneuver point; The motion state after applying a pulse maneuver to the maneuver point.

[0047] A quantitative identification system for non-cooperative spacecraft maneuver parameters includes:

[0048] The model building module is used to build an optimization model for unknown pulse maneuver time parameters of a non-cooperative spacecraft based on the relative orbital dynamics of the spacecraft.

[0049] The time parameter module acquires the motion state of the non-cooperative spacecraft before and after a single pulse maneuver, and uses an optimization algorithm to solve for the unknown pulse maneuver time parameters of the non-cooperative spacecraft.

[0050] The motion state module determines the motion state before and after applying pulse maneuvering based on the unknown pulse maneuvering time parameters of the non-cooperative spacecraft and the optimization model of the unknown pulse maneuvering time parameters of the non-cooperative spacecraft.

[0051] The position and velocity module calculates the maneuver position and velocity pulse increment of the moving point based on the motion state before and after applying a pulse to the maneuver point.

[0052] An electronic device includes a processor, a memory, and a computer program stored in the memory and operable on the processor, wherein the processor executes the computer program to implement the steps of the above-described method for quantitative identification of non-cooperative spacecraft maneuver parameters.

[0053] A computer-readable storage medium comprising a stored computer program that, when executed by a processor, implements the steps of the above-described method for quantitative identification of non-cooperative spacecraft maneuver parameters.

[0054] Compared with the prior art, the present invention has the following beneficial effects:

[0055] This invention, based on spacecraft relative orbital dynamics, establishes an optimization model for the unknown pulse maneuvering time parameters of a non-cooperative spacecraft. This model enables quantitative analysis of the maneuvering parameters of non-cooperative targets. By acquiring the motion state of the non-cooperative spacecraft before and after a single pulse maneuver, an optimization algorithm can be used to solve for the unknown pulse maneuvering time. Based on the maneuvering time parameters, the motion state of the maneuvering point before and after the applied pulse maneuver is calculated, and subsequently, the maneuvering position and velocity pulse increment of the maneuvering point are calculated. This invention is primarily designed for limited observation data; requiring only the motion state before and after the maneuver, it can quantitatively analyze the maneuvering time, pulse velocity increment, and maneuvering spatial position of a non-cooperative target. This method is simple to operate, easy to implement in engineering, and enables precise detection and tracking of space target maneuvering parameters. It is a crucial link in the study of space situational information and has significant theoretical research value. Attached Figure Description

[0056] The accompanying drawings described herein are for illustrative purposes only and are not intended to limit the scope of the invention in any way. Furthermore, the shapes and proportions of the components in the drawings are merely schematic to aid in understanding the invention and are not intended to specifically limit the shapes and proportions of the components. In the drawings:

[0057] Figure 1 This is a schematic diagram of the process for quantitative identification of non-cooperative spacecraft maneuvering parameters according to the present invention;

[0058] Figure 2 This is a schematic diagram of a time optimization scenario according to an embodiment of the present invention;

[0059] Figure 3 This is a pulse maneuver trajectory diagram of a non-cooperative spacecraft according to an embodiment of the present invention;

[0060] Figure 4 This is a graph of the fitness function of the particle swarm optimization algorithm according to an embodiment of the present invention;

[0061] Figure 5 This is a schematic diagram of the structure of a non-cooperative spacecraft maneuver parameter quantitative identification system according to the present invention;

[0062] Figure 6 This is a schematic diagram of the structure of a non-cooperative spacecraft maneuver parameter quantitative identification device according to the present invention;

[0063] The parameters in the attached diagram are noted as follows:

[0064] Figure 2 middle, - The motion state of the non-cooperative spacecraft prior to a single pulse maneuver; - The motion state of a non-cooperative spacecraft after a single pulse maneuver. - The time required to reach the maneuver point; -Arrival at the mobility point The time required for processing; - P The motion state when a pulse maneuver is applied at a point; - Apply pulse maneuvering at the speed pulse increment at the maneuvering point; Detailed Implementation

[0065] To enable those skilled in the art to better understand the technical solutions of this invention, the technical solutions of the embodiments of this invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this invention, and not all embodiments. Based on the embodiments of this invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the scope of protection of this invention.

[0066] It should be noted that when an element is referred to as being "set on" another element, it can be directly on the other element or there may be an intervening element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or there may be an intervening element. The terms "vertical," "horizontal," "left," "right," and similar expressions used herein are for illustrative purposes only and do not represent the only embodiments.

[0067] Unless otherwise specified, the technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this specification pertains. The terms “first,” “second,” etc., as used herein, do not indicate any order, quantity, or importance, but are used to distinguish one element from another. Furthermore, the terms “a” and “an” do not indicate a limitation of quantity, but rather the presence of at least one mentioned item. The use of “comprising,” “including,” or “having,” and their variations herein, is intended to encompass all items subsequently listed and their equivalents, as well as additional items. The terms “connection” and “linkage” are not limited to physical or mechanical connections or linkages, and can include direct or indirect electrical connections or linkages.

[0068] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. The terminology used herein in the specification of this invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0069] Obtaining the motion state of a non-cooperative spacecraft before and after a single pulse maneuver requires using optimization algorithms to solve for the unknown pulse maneuver time parameters of the non-cooperative spacecraft. Optimization algorithms include particle swarm optimization, genetic algorithms, and simulated annealing algorithms.

[0070] Existing track maneuver detection methods are mainly based on post-event maneuver detection using historical track information. This method can only determine whether a maneuver has occurred, but cannot quantitatively identify maneuver parameters. Moreover, most existing methods for identifying maneuver parameter information are based on continuous angle or distance measurement and tracking of the target using space-based or ground-based platforms, combined with dynamic models and filtering methods for track determination and maneuver identification, which is inconvenient.

[0071] Therefore, in order to solve the problems existing in the prior art, this invention proposes a method for identifying unknown pulse maneuvering parameters of non-cooperative spacecraft, which can quantitatively identify maneuvering parameters.

[0072] The first objective of this invention is to provide a method for quantitatively identifying the maneuvering parameters of a non-cooperative spacecraft, comprising the following steps:

[0073] S1. Based on the relative orbital dynamics of spacecraft, establish an optimization model for the unknown pulse maneuver time parameters of non-cooperative spacecraft;

[0074] S2, obtain the motion state of the non-cooperative spacecraft before and after a pulse maneuver, and use an optimization algorithm to solve for the unknown pulse maneuver time parameters of the non-cooperative spacecraft;

[0075] S3, based on the unknown pulse maneuvering time parameters of the non-cooperative spacecraft and the optimization model of the unknown pulse maneuvering time parameters of the non-cooperative spacecraft, the motion state of the computer moving point before and after applying the pulse maneuvering;

[0076] S4 calculates the maneuver position and velocity pulse increment of the moving point based on the motion state before and after applying the pulse maneuver.

[0077] Specifically, by solving for the optimal unknown pulse maneuvering time parameters of a non-cooperative spacecraft based on the model, the motion state of the maneuvering point before and after applying the pulse maneuver is calculated, and the maneuvering position and velocity pulse increment of the maneuvering point are calculated. This enables maneuvering detection and quantitative identification of maneuvering parameters.

[0078] The present invention will now be described in further detail with reference to the accompanying drawings:

[0079] like Figure 1As shown in the figure, this is a schematic flowchart of a method for quantitatively identifying the maneuver parameters of a non-cooperative spacecraft. This invention provides a method for quantitatively identifying the maneuver parameters of a non-cooperative spacecraft, including: establishing an optimization model for the unknown pulse maneuver time parameters of a non-cooperative spacecraft based on the spacecraft's relative orbital dynamics; obtaining the motion state of the non-cooperative spacecraft before and after a single pulse maneuver, and solving for the unknown pulse maneuver time parameters of the non-cooperative spacecraft using an optimization algorithm; calculating the motion state of a moving point before and after applying a pulse maneuver based on the established optimization model; calculating the maneuver position of the moving point based on the motion state before and after applying the pulse maneuver; and calculating the velocity pulse increment of the moving point based on the motion state before and after applying the pulse maneuver. By quantitatively calculating the maneuver parameters based on the optimization model, non-cooperative spacecraft can be detected and tracked quickly and accurately, and the status of space targets that pose a threat to space systems can be determined.

[0080] like Figure 2 As shown, this figure is a schematic diagram of a time optimization scenario according to an embodiment of the present invention. This schematic diagram can reflect the positional relationship between the non-cooperative spacecraft and the reference spacecraft. When the non-cooperative spacecraft is in P The point, or maneuver point, undergoes a pulse maneuver, and the motion states of the non-cooperative spacecraft before and after the pulse maneuver are detected respectively. and The particle swarm optimization algorithm is used to solve for the maneuvering time parameters of non-cooperative spacecraft. and ,calculate P Motion state before and after applying pulse control and ; Calculate velocity pulse increment based on non-cooperative spacecraft maneuver time parameters .

[0081] Example

[0082] The following typical examples illustrate the method for identifying unknown pulse maneuvering parameters of non-cooperative spacecraft, further demonstrating the application effect of this invention.

[0083] A method for quantitative identification of maneuver parameters of non-cooperative spacecraft, the specific steps of which are as follows:

[0084] (1) Based on the relative orbital dynamics of spacecraft, establish an optimization model for the unknown pulse maneuver time parameters of non-cooperative spacecraft;

[0085] In a near-circular orbit, the state transition equations for a non-cooperative spacecraft under uncontrolled conditions are as follows:

[0086] (1)

[0087] in, The state transition matrix is:

[0088] (2)

[0089] In the above formula, the symbols have the following meanings:

[0090] —The radial position component of the orbit in the LVLH system;

[0091] —Position component of the flight direction in the LVLH system;

[0092] —Position component of orbital angular momentum in the LVLH system;

[0093] —The radial velocity component of the orbit in the LVLH system;

[0094] —The velocity component of the flight direction in the LVLH system;

[0095] —The velocity component in the direction of orbital angular momentum in the LVLH system;

[0096] —State time interval;

[0097] —Relative motion reference spacecraft angular rate;

[0098] When a non-cooperative spacecraft performs a pulse maneuver at the maneuver point, the spacecraft's motion status is detected at positions before and after the maneuver point. and , Reaching the maneuver point P It takes time Maneuvering point P arrive It takes time. ,based on and Establish an optimization model for the time parameters of unknown pulse maneuvers in a non-cooperative spacecraft:

[0099] (3)

[0100] In the formula, The pulse maneuver assignment matrix is:

[0101] (4)

[0102] In the formula, The optimized index weight matrix is ​​as follows:

[0103] (5)

[0104] In the formula, for The time required to reach the maneuver point Arrival at the maneuver point The time required for processing; The motion state before applying the pulse maneuver to the maneuver point. The motion state after applying a pulse maneuver to the maneuver point; To apply pulse maneuvering at the velocity pulse increment at the maneuvering point; for The optimal time required to reach the maneuver point. Arrival at the maneuver point The optimal time required.

[0105] like Figure 3 As shown, this figure is a pulse maneuver trajectory diagram of a non-cooperative spacecraft according to an embodiment of the present invention. This figure can reflect the orbital game trajectory of a non-cooperative spacecraft.

[0106] (2) Obtain the motion state of the non-cooperative spacecraft before and after a single pulse maneuver, and use the particle swarm optimization algorithm to solve for the unknown pulse maneuver time parameters of the non-cooperative spacecraft;

[0107] The two motion states of the non-cooperative spacecraft before and after a single pulse maneuver were obtained. and as follows:

[0108] and

[0109] The particle swarm optimization algorithm is used to solve for the maneuver time parameters of non-cooperative spacecraft, and the fitness function is as follows: Figure 4 As shown, the estimated values ​​of the time parameters are calculated as follows:

[0110]

[0111]

[0112] like Figure 4 As shown in the figure, the fitness function curve of the particle swarm optimization algorithm in this embodiment of the invention is shown. The figure can reflect that as the number of calculations increases, the fitness curve function continuously decreases, indicating that the identification error of non-cooperative spacecraft maneuver parameters is continuously reduced, further confirming the feasibility of the algorithm.

[0113] (3) Based on the unknown pulse maneuvering time parameters of the non-cooperative spacecraft and the unknown pulse maneuvering time parameters of the non-cooperative spacecraft, optimize the motion state of the computer moving point before and after applying the pulse maneuvering;

[0114]

[0115] (4) Calculate the motion position, velocity, and pulse increment of the moving point based on the motion state before and after applying the pulse maneuver.

[0116] P The point's maneuvering position is:

[0117]

[0118] P The velocity pulse increment of the point is:

[0119]

[0120] like Figure 5 As shown, a non-cooperative spacecraft maneuver parameter quantitative identification system includes:

[0121] The model building module is used to build an optimization model for unknown pulse maneuver time parameters of a non-cooperative spacecraft based on the relative orbital dynamics of the spacecraft.

[0122] The time parameter module acquires the motion state of the non-cooperative spacecraft before and after a single pulse maneuver, and uses an optimization algorithm to solve for the unknown pulse maneuver time parameters of the non-cooperative spacecraft.

[0123] The motion state module determines the motion state before and after applying pulse maneuvering based on the unknown pulse maneuvering time parameters of the non-cooperative spacecraft and the optimization model of the unknown pulse maneuvering time parameters of the non-cooperative spacecraft.

[0124] The position and velocity module calculates the maneuver position and velocity pulse increment of the moving point based on the motion state before and after applying the pulse maneuver.

[0125] The module division in this embodiment of the invention is illustrative and represents only one logical functional division. In actual implementation, other division methods may be used. Furthermore, the functional modules in the various embodiments of the invention can be integrated into a single processor, exist as separate physical entities, or be integrated into a single module. The integrated modules described above can be implemented in hardware or as software functional modules.

[0126] like Figure 6As shown, in another embodiment of the present invention, an electronic device is provided, comprising a processor and a memory. The memory stores a computer program, which includes program instructions. The processor executes the program instructions stored in the computer storage medium. The processor may be a Central Processing Unit (CPU), or other general-purpose processors, digital signal processors (DSPs), application-specific integrated circuits (ASICs), field-programmable gate arrays (FPGAs), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. It is the computing and control core of the terminal, and is suitable for implementing one or more instructions, specifically suitable for loading and executing one or more instructions in the computer storage medium to realize the corresponding method flow or corresponding function. The processor described in this embodiment of the present invention can be used to implement the steps of the method for quantitative identification of non-cooperative spacecraft maneuver parameters.

[0127] In another embodiment of the present invention, a storage medium is provided, specifically a computer-readable storage medium (Memory), which is a memory device in a computer device used to store programs and data. It is understood that the computer-readable storage medium here can include both the built-in storage medium in the computer device and extended storage media supported by the computer device. The computer-readable storage medium provides storage space that stores the terminal's operating system. Furthermore, the storage space also stores one or more instructions suitable for loading and execution by a processor. These instructions can be one or more computer programs (including program code). It should be noted that the computer-readable storage medium here can be high-speed RAM or non-volatile memory, such as at least one disk storage device. The processor can load and execute one or more instructions stored in the computer-readable storage medium to implement the corresponding steps of the non-cooperative spacecraft maneuver parameter quantitative identification method in the above embodiments.

[0128] 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, CD-ROM, optical storage, etc.) containing computer-usable program code.

[0129] 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.

[0130] 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.

[0131] 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.

[0132] The above embodiments are merely illustrative of the technical solutions of this application and are not intended to limit it. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions 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 this application. Many embodiments and applications beyond the provided examples will be apparent to those skilled in the art upon reading the above description. Therefore, the scope of this teaching should not be determined by reference to the foregoing description, but rather by reference to the foregoing claims and the full scope of their equivalents. For the purpose of completeness, all articles and references, including patent applications and publications, are incorporated herein by reference. The omission of any aspect of the subject matter disclosed herein in the foregoing claims is not intended as a waiver of that subject matter, nor should it be considered that the applicant has not considered that subject matter as part of the disclosed inventive subject matter.

[0133] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit it. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that modifications or equivalent substitutions can still be made to the specific implementation of the present invention. Any modifications or equivalent substitutions that do not depart from the spirit and scope of the present invention should be covered within the scope of protection of the claims of the present invention.

[0134] The above content provides a further detailed description of the present invention. It should not be construed that the specific embodiments of the present invention are limited to this. For those skilled in the art, several simple deductions or substitutions can be made without departing from the concept of the present invention, and all such deductions or substitutions should be considered to fall within the scope of protection of the present invention as defined by the submitted claims.

Claims

1. A method for quantitatively identifying maneuver parameters of a non-cooperative spacecraft, characterized in that, Includes the following steps: S1. Based on the relative orbital dynamics of spacecraft, establish an optimization model for the unknown pulse maneuver time parameters of non-cooperative spacecraft; S2, obtain the motion state of the non-cooperative spacecraft before and after a pulse maneuver, and use the particle swarm optimization algorithm to solve the unknown pulse maneuver time parameters of the non-cooperative spacecraft; S3, based on the unknown pulse maneuvering time parameters of the non-cooperative spacecraft and the optimization model of the unknown pulse maneuvering time parameters of the non-cooperative spacecraft, the motion state of the computer moving point before and after applying the pulse maneuvering; S4, calculate the movement position and velocity pulse increment of the moving point based on the motion state before and after applying the pulse maneuver; The specific steps of S1 are as follows: In a near-circular orbit, the state transition equations for a non-cooperative spacecraft under uncontrolled conditions are as follows: （1） in, The state transition matrix is: （2） In the above formula, the symbols have the following meanings: —The radial position component of the orbit in the LVLH system; —Position component of the flight direction in the LVLH system; —Position component of orbital angular momentum in the LVLH system; —The radial velocity component of the orbit in the LVLH system; —The velocity component of the flight direction in the LVLH system; —The velocity component in the direction of orbital angular momentum in the LVLH system; —State time interval; —Relative motion reference spacecraft angular rate; When a non-cooperative spacecraft performs a pulse maneuver at the maneuver point, the spacecraft's motion status is detected at positions before and after the maneuver point. and , Arrive at the maneuver point P It takes time Maneuvering point P arrive It takes time. ,based on and Establish an optimization model for the time parameters of unknown pulse maneuvers in a non-cooperative spacecraft: （3） In the formula, The pulse maneuver assignment matrix is: （4） In the formula, The optimized index weight matrix is ​​as follows: （5） In the formula, The motion state before applying the pulse maneuver to the maneuver point. The motion state after applying a pulse maneuver to the maneuver point; To apply pulse maneuvering at the velocity pulse increment at the maneuvering point; for The optimal time required to reach the maneuver point. Arrival at the maneuver point The optimal time required; S2 includes: Obtain the motion state of a non-cooperative spacecraft before and after a pulse maneuver. and , To obtain the motion state of a non-cooperative spacecraft prior to a single pulse maneuver; To obtain the motion state of a non-cooperative spacecraft after a single pulse maneuver, a particle swarm optimization algorithm is used to solve for the unknown pulse maneuver time parameters of the non-cooperative spacecraft. The solved unknown pulse maneuver time for the non-cooperative spacecraft is and .

2. The method for quantitative identification of maneuver parameters of a non-cooperative spacecraft according to claim 1, characterized in that, S3 includes: Based on the unknown pulse maneuvering time of non-cooperative spacecraft and The obtained motion state of the non-cooperative spacecraft before and after a single pulse maneuver. and Then, based on the optimization model of unknown pulse maneuver time parameters of a non-cooperative spacecraft, the motion state of the computer moving point before and after applying the pulse maneuver was determined. and .

3. The method for quantitative identification of maneuver parameters of a non-cooperative spacecraft according to claim 2, characterized in that, The motion state of the computer motion point before and after applying pulse maneuvering and ,include: （6） In the formula, Here is the state transition matrix. Will Substitute into the state transition matrix ; Will Substitute into the state transition matrix .

4. The method for quantitative identification of maneuver parameters of a non-cooperative spacecraft according to claim 1, characterized in that, The calculation of the pulse maneuver's position at the maneuver point in S4 includes: （7） In the formula, The radial position component of the orbit in the LVLH system; The position component of the flight direction in the LVLH system; For the position component of the orbital angular momentum direction in the LVLH system.

5. The method for quantitative identification of maneuver parameters of a non-cooperative spacecraft according to claim 1, characterized in that, The calculation of the velocity pulse increment at the maneuver point in S4 for the unknown pulse maneuver includes: （8） In the formula, The radial velocity component of the orbit in the LVLH system; The velocity component in the flight direction under the LVLH system; For the velocity component in the direction of orbital angular momentum in the LVLH system.

6. A system for quantitatively identifying the maneuvering parameters of a non-cooperative spacecraft, implementing the method for quantitatively identifying the maneuvering parameters of a non-cooperative spacecraft as described in any one of claims 1-5, characterized in that, include: The model building module is used to build an optimization model for unknown pulse maneuver time parameters of a non-cooperative spacecraft based on the relative orbital dynamics of the spacecraft. The time parameter module obtains the motion state of the non-cooperative spacecraft before and after a single pulse maneuver, and uses a particle swarm optimization algorithm to solve for the unknown pulse maneuver time parameters of the non-cooperative spacecraft. The motion state module determines the motion state before and after applying pulse maneuvering based on the unknown pulse maneuvering time parameters of the non-cooperative spacecraft and the optimization model of the unknown pulse maneuvering time parameters of the non-cooperative spacecraft. The position and velocity module calculates the maneuver position and velocity pulse increment of the moving point based on the motion state before and after applying the pulse maneuver.

7. An electronic device comprising a processor, a memory, and a computer program stored in the memory and operable on the processor, wherein the processor executes the computer program to implement the steps of the non-cooperative spacecraft maneuver parameter quantitative identification method according to any one of claims 1-5.

8. A computer-readable storage medium comprising a stored computer program that, when executed by a processor, implements the steps of the method for quantitative identification of non-cooperative spacecraft maneuver parameters according to any one of claims 1-5.

Images