Large-scale symmetric star group internal collision assessment method
By constructing and expanding the collision box and calculating the error-free position boundary, the problems of inefficient satellite collision assessment and limited accuracy within large-scale symmetric star clusters are solved, and efficient and accurate collision risk assessment and time period prediction are achieved.
Patent Information
- Application Number
- CN202510304673.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-03-14
- Publication Date
- 2025-06-27
AI Technical Summary
The prior art is difficult to efficiently and accurately assess the risk of satellite collisions within large-scale clusters with high symmetry and complex geometric arrangements, resulting in inefficient assessments and limited accuracy.
By obtaining the orbital error area of the target satellite, building and expanding the collision box, and calculating the time period of the collision risk based on the error-free position boundary of both sides, we can judge whether there will be a collision.
It realizes efficient and accurate satellite collision evaluation of large-scale symmetric star clusters, improves evaluation efficiency and accuracy, accurately predicts the time period of collision, and supports satellite collision avoidance operations.
Smart Images
Figure CN120223154A_ABST
Abstract
Description
Technical Field
[0001] The present invention belongs to the field of aerospace technology, and particularly relates to a method, system, device, medium and program for evaluating internal collisions of a large-scale symmetric satellite constellation. Background Art
[0002] In the vast journey of exploring the universe, satellite collision assessment, as a crucial link in maintaining the safety and order of the space environment, has become increasingly important. With the rapid development of human aerospace technology, the number of satellites in low Earth orbit has shown an explosive growth. From scientific exploration, communication and navigation to Earth observation, various satellites are dotted in space like stars, greatly promoting humanity's understanding and utilization of the universe. However, behind this prosperous scene lies a security risk that cannot be ignored - the risk of satellite collisions. The accumulation of space debris and the rapid increase in the number of satellites are intertwined, forming an intricate and dynamically changing space environment, which significantly increases the likelihood of collision events. Once a collision occurs, it may not only lead to the loss of expensive satellite assets and mission interruptions, but also trigger a chain reaction, generating more space debris, further exacerbating the deterioration of the space environment, threatening the safe operation of all spacecraft, and even affecting the sustainable development of the entire human space activities.
[0003] Therefore, it is particularly urgent to carry out efficient and accurate satellite collision assessment work. Traditional collision assessment methods, such as those based on the collision box model, high and low point judgment method, and Monte Carlo simulation, although perform well when dealing with single or a small number of satellites with obvious orbital differences, their effectiveness becomes inadequate when facing a large-scale satellite constellation consisting of hundreds or even thousands of satellites. Especially when the satellite constellation exhibits a high degree of symmetry or specific geometric distribution characteristics, traditional methods often fail to fully utilize these inherent properties to optimize the calculation process, resulting in low evaluation efficiency and difficulty in meeting the requirements of rapid response and real-time decision-making. Taking the collision box model as an example, it simplifies the movement range of satellites into a static or dynamic three-dimensional box to judge potential collision risks. This method is relatively intuitive and efficient when dealing with isolated satellites or small-scale satellite constellations, but when facing a large-scale satellite constellation with complex geometric arrangements and a high degree of symmetry, the setting of the size and position of the collision box becomes extremely complex, not only increasing the computational burden, but also possibly ignoring the collision situations that are naturally avoided due to symmetry within the satellite constellation due to overly conservative settings, thus reducing the accuracy of the assessment.
[0004] The high and low point judgment rule focuses on judging the collision risk by comparing the highest and lowest point positions of two satellites in orbit. This method is more effective when the satellite orbits differ significantly. However, within a satellite constellation, due to the complex and dynamically changing relative positions among satellites, a direct comparison of high and low points becomes impractical, making it difficult to accurately capture potential collision threats. As for the Monte Carlo method, although it can simulate the uncertainty of satellite motion through a large number of random samples and provide a relatively comprehensive collision risk assessment, its computational cost is high. Especially when dealing with large-scale satellite constellations, the required computing resources and time increase exponentially, limiting its application in real-time assessment scenarios. Summary of the Invention
[0005] Aiming at the problem that in the prior art, when dealing with the collision assessment of large-scale satellite constellations with high symmetry and complex geometric arrangements, traditional methods fail to fully utilize these characteristics, resulting in low assessment efficiency and limited accuracy. The present invention provides a method for internal collision assessment of large-scale symmetric satellite constellations, which fully utilizes the symmetry and geometric characteristics of the satellite constellation to achieve efficient and accurate satellite collision assessment for large-scale satellite constellations composed of hundreds or even thousands of satellites.
[0006] To achieve the above object, the present invention provides the following technical solutions.
[0007] In a first aspect, the present invention provides a method for internal collision assessment of a large-scale symmetric satellite constellation, including: Obtain the orbital error region of the target satellite in the satellite constellation; Based on the orbital error region of the target satellite, construct a collision box for the target satellite; Expand the collision box of the target satellite to obtain the expanded collision box of the target satellite; According to the expanded collision box of the target satellite and the collision box of the slave satellite, construct the error-free position boundary between the two; Calculate the time period during which a collision risk occurs between the master satellite and the slave satellite through the error-free position boundary between the two; Detect the time period during which a collision risk occurs between the master satellite and the slave satellite, and judge whether a collision will occur.
[0008] As a further improvement of the present invention, the obtaining of the orbital error region of the target satellite in the satellite constellation includes: Confirm the position of the target satellite in the satellite constellation in the ECI coordinate system;
[0009] In the formula, is the position of the master satellite in the ECI coordinate system; is the semi-major axis of the master satellite; M is the phase of the master satellite; i is the inclination of the master satellite; Based on the position of the target satellite in the constellation in the ECI coordinate system and the error vertices, the orbital error region of the target satellite in the constellation is obtained;
[0010] In the formula, is the coordinate of the main star in the polar coordinate system; is the first error position of the main star in the ECI coordinate system; is the second error position of the main star in the ECI coordinate system; is the third error position of the main star in the ECI coordinate system.
[0011] As a further improvement of the present invention, constructing a collision box for the target satellite based on the orbital error region of the target satellite includes: Converting the shape of the orbital error region of the target satellite into a parallelogram and dragging the parallelogram to form a collision box for the target satellite;
[0012] In the formula, is the coordinate of the first error point in the polar coordinate system; is the coordinate of the second error point in the polar coordinate system; is the coordinate of the third error point in the polar coordinate system; is the coordinate of the fourth error point in the polar coordinate system; is the coordinate of the fifth error point in the polar coordinate system; is the coordinate of the sixth error point in the polar coordinate system; is the coordinate of the seventh error point in the polar coordinate system; is the coordinate of the eighth error point in the polar coordinate system; is the coordinate of the ninth error point in the polar coordinate system; is the coordinate of the tenth error point in the polar coordinate system; is the error of the right ascension of the ascending node.
[0013] As a further improvement of the present invention, expanding the collision box of the target satellite to obtain an expanded collision box of the target satellite includes: Expanding the collision box of the target satellite outward according to a set value and performing a de-stretching process to obtain an expanded collision box of the target satellite.
[0014] As a further improvement of the present invention, constructing an error-free position boundary for both sides based on the expanded collision box of the target satellite and the collision box of the slave satellite includes: Calculating the tangent between the expanded collision box of the target satellite and the collision box of the slave satellite according to the expanded collision box of the target satellite and the collision box of the slave satellite; Analyze the tangent between the collision boxes of the target satellite after expansion and the slave satellite to determine the trajectories of the target satellite and the slave satellite and the potential collision paths; Based on the determined trajectories of the target satellite and the slave satellite and the potential collision paths, construct the error-free position boundaries of both sides.
[0015] As a further improvement of the present invention, calculating the time period during which the master satellite and the slave satellite are at risk of collision through the error-free position boundaries of both sides includes: Calculate the phase of the master satellite at the intersection point through the error-free position boundaries of both sides; Based on the phase of the master satellite at the intersection point, use the phase at which the virtual slave satellite collides to obtain the phase of the slave satellite that will collide at the intersection moment; Through the phase of the real slave satellite and the phase of the slave satellite that will collide at the intersection moment, find the slave satellite that will collide with the master satellite to obtain the time period during which the master satellite and the slave satellite collide.
[0016] As a further improvement of the present invention, detecting the time period during which the master satellite and the slave satellite are at risk of collision and determining whether a collision will occur includes: At the time when the master satellite and the slave satellite are at risk of collision, compare whether the error-free position of the slave satellite is within the collision box calculated from the error-free position of the master satellite; If so, the master satellite and the slave satellite will collide; If not, the master satellite and the slave satellite will not collide.
[0017] In a second aspect, the present invention provides a large-scale symmetric satellite cluster internal collision assessment system, including: An orbital error acquisition module: used to acquire the orbital error region of the target satellite in the satellite cluster; A collision box construction module: used to construct the collision box of the target satellite based on the orbital error region of the target satellite; A collision box expansion module: used to expand the collision box of the target satellite to obtain the collision box of the target satellite after expansion; An error-free boundary construction module: used to construct the error-free position boundaries of both sides according to the collision box of the target satellite after expansion and the collision box of the slave satellite; A collision time period calculation module: calculate the time period during which the master satellite and the slave satellite are at risk of collision through the error-free position boundaries of both sides; A collision determination module: used to detect the time period during which the master satellite and the slave satellite are at risk of collision and determine whether a collision will occur.
[0018] In a third aspect, the present invention provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, the steps of the method for evaluating internal collisions in a large-scale symmetric star cluster are implemented.
[0019] In a fourth aspect, the present invention provides a computer-readable storage medium storing a computer program, and when the computer program is executed by a processor, the steps of the method for evaluating internal collisions in a large-scale symmetric star cluster are implemented.
[0020] In a fifth aspect, the present invention provides a computer program product including computer instructions, and when the computer instructions are executed by a processor, the steps of the method for evaluating internal collisions in a large-scale symmetric star cluster are implemented.
[0021] Compared with the prior art, the present invention has the following beneficial effects: By obtaining the orbital error region of the target satellite and constructing a collision box, the present invention effectively simplifies the complexity of collision evaluation. By performing an inflation process on the collision box, the influence of orbital errors on collision evaluation is further considered, while reducing the computational difficulty. In addition, the present invention further narrows the scope of collision risk analysis by constructing the error-free position boundaries of both sides, thereby greatly improving the efficiency of evaluation. Secondly, the present invention makes full use of the symmetry and geometric characteristics of the star cluster. By accurately constructing the collision box and the error-free position boundaries of both sides, accurate evaluation of the satellite collision risk is achieved. This accuracy is not only reflected in the judgment of collision risk, but also in the accurate prediction of the collision occurrence time period, thus providing strong support for the collision avoidance operation of the satellite. In addition, due to the universality of the symmetry and geometric characteristics of the star cluster, the method proposed by the present invention is not only applicable to specific types of large-scale star clusters, but can also be widely applied to various satellite systems with symmetry and complex geometric arrangements. At the same time, the method proposed by the present invention can also be flexibly adjusted according to specific application requirements, such as adjusting the inflation coefficient of the collision box, optimizing the construction algorithm of the error-free position boundary, etc., to meet the evaluation requirements in different scenarios. Description of the Drawings
[0022] The drawings described herein are for illustrative purposes only and are not intended to limit the scope of the disclosure of the present invention in any way. In the drawings: Figure 1 is a schematic flow chart of the method for evaluating internal collisions in a large-scale symmetric star cluster according to the present invention; Figure 2 is a schematic diagram showing the performance of inclination and phase errors of the method for evaluating internal collisions in a large-scale symmetric star cluster according to the present invention; Figure 3Schematic diagram of the right ascension of the ascending node error of a method for evaluating internal collisions in a large-scale symmetric star cluster according to the present invention; Figure 4 Schematic diagram of the error of a method for evaluating internal collisions in a large-scale symmetric star cluster according to the present invention in polar coordinates; Figure 5 Schematic diagram of the inflated collision box of a method for evaluating internal collisions in a large-scale symmetric star cluster according to the present invention; Figure 6 Schematic diagram of the chiral collision boxes of a method for evaluating internal collisions in a large-scale symmetric star cluster according to the present invention; Figure 7 Schematic diagram of the allowable boundary of the collision box of a method for evaluating internal collisions in a large-scale symmetric star cluster according to the present invention; Figure 8 Schematic diagram of collision warning in a typical case of a method for evaluating internal collisions in a large-scale symmetric star cluster according to the present invention; Figure 9 Schematic diagram of the structure of a system for evaluating internal collisions in a large-scale symmetric star cluster according to the present invention; Figure 10 Schematic diagram of an electronic device in an embodiment of the present invention. Detailed implementation manners
[0023] In order to enable those skilled in the art of the present technology to better understand the technical solutions in the present invention, the following will clearly and completely describe the technical solutions in the present invention in conjunction with the accompanying drawings in the present invention. The described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present invention without creative efforts shall fall within the protection scope of the present invention.
[0024] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by those skilled in the technical field of the present invention. The terms used herein in the specification of the present invention are only for the purpose of describing specific embodiments, and are not intended to limit the present invention. The term "and / or" used herein includes any and all combinations of one or more of the related listed items.
[0025] Aiming at the problem that in the prior art, when dealing with the collision evaluation of large-scale star clusters with high symmetry and complex geometric arrangements, traditional methods fail to fully utilize these characteristics, resulting in low evaluation efficiency and limited accuracy. The present invention provides a method for evaluating internal collisions in a large-scale symmetric star cluster, as Figure 1 shown, the method includes: S100: Obtain the orbital error region of the target satellite in the star cluster; S200: Construct a collision box for the target satellite based on the orbital error region of the target satellite; S300: Expand the collision box of the target satellite to obtain the expanded collision box of the target satellite; S400: Construct the error-free position boundaries of both sides based on the expanded collision box of the target satellite and the collision box of the slave satellite; S500: Calculate the time period during which the main satellite and the slave satellite are at risk of collision through the error-free position boundaries of both sides; S600: Detect the time period during which the main satellite and the slave satellite are at risk of collision and determine whether a collision will occur.
[0026] The present invention makes full use of the symmetry and geometric characteristics of the satellite constellation to achieve efficient and accurate satellite collision assessment for large-scale satellite constellations composed of hundreds or even thousands of satellites.
[0027] The following further explains the present invention with reference to specific drawings: A method for internal collision assessment of a large-scale symmetric satellite constellation according to the present invention includes the following steps: S1: Express satellite errors in the polar coordinate system Assume a standard Walker constellation with m×n satellites, which has m orbital planes, with n satellites evenly distributed in each orbital plane, a phase factor of k, an orbital inclination of i, and a semi-major axis of a; the control accuracy of the ascending node of these satellites is , the phase error is , the inclination error is ; the eccentricity of the constellation is zero, and analyze the collision possibility of the constellation, that is, the collision possibility that the distance between two satellites is less than D.
[0028] As Figure 2 shown, the influence of the orbital inclination error and the phase error on the satellite position. Under the influence of these two errors, the accurate position of the satellite becomes the area shown in red in Figure 2 . As Figure 3 shown, the influence of the right ascension of the ascending node error / RAAN, Figure 2 the red part in
[0029] "slides" along the longitude line / latitude plane, thus forming a complex shape. (1) In the formula, is the position of the main satellite in the ECI system; The semi-major axis of the primary star; M is the phase of the primary star; i is the inclination of the primary star.
[0030] When considering errors, the four vertices of the error, such as Figure 2 The vertices in are: (2) In the formula: Is the first error vertex; Is the second error vertex; Is the third error vertex; Is the fourth error vertex; Is the phase error; Is the inclination error.
[0031] Convert the above formula to polar coordinates: (3) In the formula, Is the coordinate of the primary star in the polar coordinate system; Is the first error position of the primary star in the ECI system; Is the second error position of the primary star in the ECI system; Is the third error position of the primary star in the ECI system.
[0032] After considering the right ascension of the ascending node error, such as Figure 2 As shown, Figure 2 The representation of the figure in in the polar coordinate system is as shown in formula (4) and Figure 4 As shown. Since the error of the satellite orbit is quite small, on the order of 0.01°; at such a small angle, the trigonometric functions can be regarded as constant values, Figure 2 The shape in can be regarded as a parallelogram and the dragging of the parallelogram; Figure 3 The collision box of the satellite in can be simplified to a hexagon.
[0033] (4) In the formula, Is the coordinate of the first error point in the polar coordinate system; Is the coordinate of the second error point in the polar coordinate system; Is the coordinate of the third error point in the polar coordinate system; Is the coordinate of the fourth error point in the polar coordinate system; Is the coordinate of the fifth error point in the polar coordinate system; Is the coordinate of the sixth error point in the polar coordinate system; Is the coordinate of the seventh error point in the polar coordinate system; Is the coordinate of the eighth error point in the polar coordinate system; Is the coordinate of the ninth error point in the polar coordinate system; is the coordinate of the tenth error point in the polar coordinate system; is the error of the right ascension of the ascending node; S2: Expand the possible area of the satellite: In S1, it is mentioned that the distance between two satellites shall not be less than D, where D = 1 km, and the distance of the possible area of the two satellites shall not be less than 1 km; this problem should be interpreted as "the collision boxes of the two satellites", and the closest area shall not be less than 1 km. "Expanding" the collision box of the main satellite by 1 km can obtain Figure 5 .
[0034] It should be specifically pointed out that since the horizontal axis will be stretched in the polar coordinate system, the length of 1 km horizontally is different from that of 1 km vertically in the polar coordinate system. When calculating, the graph needs to be scaled to 1:1 for expansion first, and then the expanded image is scaled back to the polar coordinate system. The relative vector of node n after de-stretching is: (5) In the formula, is the relative vector of node n after de-stretching; is the abscissa of node N in the polar coordinate system; is the ordinate of node n in the polar coordinate system; is the abscissa position where the satellite is located without error; is the ordinate position where the satellite is located without error; Figure 5 After de-stretching, the two sides worthy of attention are and , and through simple geometric analysis, it can be obtained that and The coordinates in the de-stretched coordinate system are: (6) In the formula, is the relative vector of node 5 after de-stretching; is the relative vector of node 9 after de-stretching; is the relative vector of node 10 after de-stretching; is the relative vector of node 21 after de-stretching; is the relative vector of node 22 after de-stretching; By re-stretching the coordinates in the above formula, the representations of these two points in the polar coordinate system can be obtained: (7) In the formula, is the coordinate of the Nth error point in the polar coordinate system. Due to the symmetry of the graph and the equivalence of coordinate changes, the coordinates of other points in Figure 4 can be expressed as: (8) Wherein, are the coordinates of the eleventh error point in the polar coordinate system; are the coordinates of the twelfth error point in the polar coordinate system; are the coordinates of the thirteenth error point in the polar coordinate system; are the coordinates of the fourteenth error point in the polar coordinate system; are the coordinates of the fifteenth error point in the polar coordinate system; are the coordinates of the sixteenth error point in the polar coordinate system; are the coordinates of the seventeenth error point in the polar coordinate system; are the coordinates of the eighteenth error point in the polar coordinate system; are the coordinates of the nineteenth error point in the polar coordinate system; are the coordinates of the tenth error point in the polar coordinate system; are the coordinates of the twenty-first error point in the polar coordinate system; are the coordinates of the twenty-second error point in the polar coordinate system.
[0035] S3: Introduce the collision box of the satellite (slave satellite) with collision risk, and construct the error-free position boundary of both sides: Since the dangerous distance between the two satellites is very close, at the order of 1 km, the corresponding angle is 0.0083°, so it can be considered that the longitudes and latitudes of the two satellites that will collide are very close; furthermore, due to the symmetry of the problem, the sizes and shapes of the collision boxes of the two satellites that will collide are the same but chiral to each other, as Figure 6 shown. Figure 6 The tangent line of the collision box of the slave satellite in Figure 5 corresponding to the inflated collision box of the master satellite is as Figure 7 shown.
[0036] It should be noted that due to the different shapes of the collision boxes under different parameters, the order of the tangent points in the allowable boundaries of the collision boxes with different inclinations and different phases is also different, as Figure 7 shown by the cyan-purple line in. The following formula shows the mathematical representation of the collision box boundary nodes in three typical cases: (9) Wherein, are the coordinates of the twenty-third error point in the polar coordinate system; are the coordinates of the twenty-fourth error point in the polar coordinate system; are the coordinates of the twenty-fifth error point in the polar coordinate system; are the coordinates of the twenty-sixth error point in the polar coordinate system; are the coordinates of the twenty-seventh error point in the polar coordinate system; are the coordinates of the twenty-eighth error point in the polar coordinate system; is the coordinate of the 29th error point in the polar coordinate system; is the coordinate of the 30th error point in the polar coordinate system; is the abscissa of the 5th error point in the polar coordinate system; is the ordinate of the 5th error point in the polar coordinate system; is the abscissa of the 9th error point in the polar coordinate system; is the ordinate of the 9th error point in the polar coordinate system; is the abscissa of the 10th error point in the polar coordinate system; is the ordinate of the 10th error point in the polar coordinate system.
[0037] Since Figure 7 is centrosymmetric, the coordinates of the left - hand side points can be obtained using the symmetry method: (10) wherein is the coordinate of the 27th error point in the polar coordinate system; is the coordinate of the 28th error point in the polar coordinate system; is the coordinate of the 29th error point in the polar coordinate system; is the coordinate of the 30th error point in the polar coordinate system; is the coordinate of the 31st error point in the polar coordinate system; is the coordinate of the 32nd error point in the polar coordinate system; is the coordinate of the 33rd error point in the polar coordinate system; is the coordinate of the 34th error point in the polar coordinate system; is the coordinate of the 35th error point in the polar coordinate system; is the coordinate of the 36th error point in the polar coordinate system; is the coordinate of the 37th error point in the polar coordinate system; is the coordinate of the 38th error point in the polar coordinate system.
[0038] S4: Add redundancy to the error - free position boundaries of both sides: Expand the overall collision box , that is: (11) wherein is the final allowable error boundary; is the overall expansion of the collision box.
[0039] The final allowable error boundary is the region enclosed by , which is a function of the primary star phase: (12) S5: Calculate the time period with collision risk: Due to the large orbital span and small collision interval, only the areas near the intersection of the two orbits need to be detected. For example, the maximum latitude of the primary satellite appears at 90° longitude, and the angle between two adjacent orbital planes , so the longitude where the intersection of the two orbits is located is , is the number of planes in difference. This relationship is expressed mathematically as: (13) The phase of the primary satellite at the moment of the orbital plane intersection can be analytically obtained as: (14) Assume that exactly one secondary satellite collides with the primary satellite at this intersection position at this moment. Then, through the symmetry of the figure, the phase of this virtual secondary satellite can be obtained as: (15) Due to the characteristics of the Walker constellation, the possible phases of the real secondary satellites are: (16) where, is the phase of the primary satellite, is the phase factor, is the satellite number on this orbit, and n is the number of co-orbital satellites. Since it is known that the secondary satellite with phase will definitely collide, so the secondary satellites with phases near also have the risk of colliding with the primary satellite. The numbers of these secondary satellites can be obtained by taking the remainder, that is: (17) where ceil() and floor() represent rounding up and rounding down respectively. In theory, only the two nearest satellites need to be detected for this method, but for redundancy, actually the four nearest satellites will be detected.
[0040] In this problem, it is not necessary to detect the entire orbital period, only a small part of the time when collision is most likely to occur needs to be detected. The duration of interest in this problem is the duration when the secondary satellite passes through the entire collision box of the primary satellite - if a collision will occur, it will definitely occur within the time period when the vertical coordinate / latitude distance between the two is less than the vertical coordinate span of the collision box. During this short time period (using phase to represent time), the longitudinal speed of the primary satellite can be expressed as: (18) Therefore, considering that the longitudinal speeds of the primary satellite and the secondary satellite that will collide are equal in magnitude and opposite in direction, the time period of interest can be expressed as follows, where and respectively represent the vertex and bottom latitude of the collision box.
[0041] (19) Under the above simplification, the actual time period that needs to be calculated is , is redundant.
[0042] S6: Compare whether the error-free position of the slave satellite is within the collision box calculated from the error-free position of the master satellite.
[0043] If it is, the master satellite and the slave satellite will collide; If not, the master satellite and the slave satellite will not collide.
[0044] The following further explains the present invention in conjunction with specific embodiments.
[0045] Substitute the constellation configuration , , , , orbital altitude of 1000 km, phase factor of 1 deg; the satellite distance shall not be less than 1 km, and redundancy is substituted , and perform simulation under typical errors.
[0046] When , two impact warnings occur, as Figure 8 shown, the figure also shows the positions of the four satellites of concern at the collision moment and the collision box of the master satellite.
[0047] In summary, a method for evaluating internal collisions of a large-scale symmetric satellite constellation disclosed by the present invention makes full use of the symmetry and geometric characteristics of the satellite constellation, and provides an effective solution for the collision evaluation and index design of a large-scale symmetric satellite constellation.
[0048] The second object of the present invention is to propose a system for evaluating internal collisions of a large-scale symmetric satellite constellation, as Figure 9 shown, including: Orbit error acquisition module 100: used to acquire the orbit error region of the target satellite in the satellite constellation; Collision box construction module 200: used to construct the collision box of the target satellite based on the orbit error region of the target satellite; Collision box expansion module 300: used to expand the collision box of the target satellite to obtain the expanded collision box of the target satellite; Error-free boundary construction module 400: used to construct the error-free position boundary of both sides according to the expanded collision box of the target satellite and the collision box of the slave satellite; Collision time period calculation module 500: calculate the time period of the collision risk between the master satellite and the slave satellite through the error-free position boundary of both sides; Collision determination module 600: used to detect the time period when there is a risk of collision between the master star and the slave star, and determine whether a collision will occur.
[0049] As Figure 10 As shown, the third object of the present invention is to provide an electronic device, which includes: a processor 701, a memory 702, and a display screen 703. Among them, the memory 702 and the display screen 703 are both connected to the processor 701, such as through a bus 704. Optionally, the electronic device may further include a transceiver 705. It should be noted that in practical applications, the transceiver 705 is not limited to one, and the structure of the electronic device does not constitute a limitation to the embodiments of the present application.
[0050] The processor 701 may be a CPU (Central Processing Unit, central processor), a general-purpose processor, a DSP (Digital Signal Processor, data signal processor), an ASIC (Application Specific Integrated Circuit, application-specific integrated circuit), an FPGA (Field Programmable Gate Array, field programmable gate array), or other programmable logic devices, transistor logic devices, hardware components, or any combination thereof. It can implement or execute various exemplary logic blocks, modules, and circuits described in combination with the disclosure of the present application. The processor 701 may also be a combination that implements a computing function, such as a combination of one or more microprocessors, a combination of a DSP and a microprocessor, etc.
[0051] The bus 704 may include a path for transmitting information between the above components. The bus 704 may be a PCI (Peripheral Component Interconnect, peripheral component interconnect standard) bus or an EISA (Extended Industry Standard Architecture, extended industry standard architecture) bus, etc. The bus 704 may be divided into an address bus, a data bus, a control bus, etc.
[0052] The memory 702 can be a ROM (Read Only Memory), or other types of static storage devices that can store static information and instructions, a RAM (Random Access Memory), or other types of dynamic storage devices that can store information and instructions. It can also be an EEPROM (Electrically Erasable Programmable Read Only Memory), a CD-ROM (Compact Disc Read Only Memory), or other optical disc storage, optical disc storage (including compact discs, laser discs, optical discs, digital versatile discs, Blu-ray discs, etc.), magnetic disk storage media, or other magnetic storage devices, or any other medium that can be used to carry or store the desired program code in the form of instructions or data structures and can be accessed by a computer, but is not limited thereto.
[0053] The memory 702 is used to store the application program code for executing the solution of this application and is controlled by the processor 701 for execution. The processor 701 is used to execute the application program code stored in the memory 702 to implement the content shown in the foregoing method embodiments.
[0054] Figure 10 The illustrated electronic device is only an example and should not impose any limitations on the functions and usage scope of the embodiments of this application.
[0055] The fourth object of the present invention is to provide a computer-readable storage medium, which stores a computer program. When the program is executed by a processor, it implements each process of the method embodiment as described above. Figure 1 For example, a memory including instructions, and the above instructions can be executed by the processor of the electronic device to complete the above method.
[0056] A computer-readable storage medium can be a tangible device that holds and stores instructions used by an instruction execution device. A computer-readable storage medium can be, but is not limited to, an electrical storage device, a magnetic storage device, an optical storage device, an electromagnetic storage device, a semiconductor storage device, or any combination of the above. Specifically, a computer-readable storage medium can be a portable computer disk, a hard disk, a USB flash drive, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), a static random access memory (SRAM), a portable compact disc read-only memory (CD-ROM), a digital versatile disc (DVD), a memory stick, a floppy disk, an optical disc, a magnetic disk, a mechanical encoding device, and any combination of the above.
[0057] The fifth object of the present invention is to provide a computer program product including computer instructions, which, when executed by a processor, implement each process of the method embodiment as described above and can achieve the same technical effects. To avoid repetition, it will not be elaborated here. Figure 1 The various processes of the method embodiment shown above, and can achieve the same technical effects. To avoid repetition, it will not be elaborated here.
[0058] Upon reading the above description, many embodiments and many applications beyond the provided examples will be obvious to those skilled in the art. Therefore, the scope of this teaching should not be determined with reference to the above description, but should be determined with reference to the full scope of the foregoing claims and the equivalents thereof. For the sake of completeness, all articles and references, including patent applications and publications, are incorporated herein by reference. Omission of any aspect of the subject matter disclosed herein in the foregoing claims is not intended to abandon such subject matter, nor should the applicant be regarded as not considering such subject matter as part of the disclosed inventive subject matter.
[0059] The above is a further detailed description of the present invention. It cannot be determined that the specific embodiments of the present invention are limited thereto. For those of ordinary skill in the technical field to which the present invention pertains, without departing from the concept of the present invention, several simple deductions or substitutions can be made, and all should be regarded as falling within the protection scope determined by the claims submitted for the present invention.
Claims
1. A large-scale symmetric star cluster internal collision assessment method, characterized in that: include: Get the orbit error area of the target satellite in the constellation; Based on the orbit error region of the target satellite, a collision box of the target satellite is constructed; Expanding the collision box of the target satellite to obtain an expanded collision box of the target satellite; According to the expanded collision box of the target satellite and the collision box of the slave satellite, the error-free position boundary of both parties is constructed; The time period of collision risk between the master and slave satellites is calculated through the error-free position boundary of both parties; The time period when there is a risk of collision between the master satellite and the slave satellite is detected to determine whether a collision will occur.
2. A large-scale symmetric star cluster internal collision assessment method according to claim 1, characterized in that: The step of obtaining the orbit error region of the target satellite in the constellation includes: Confirm the position of the target satellite in the constellation under the ECI system; In the formula, is the position of the main star in the ECI system; is the semi-major axis of the primary star; M is the phase of the primary star; i is the inclination of the primary star; Based on the position and error vertex of the target satellite in the star cluster in the ECI system, the orbit error region of the target satellite in the star cluster is obtained; In the formula, is the coordinate of the main star in the polar coordinate system; is the first error position of the main star in the ECI system; is the second error position of the main star in the ECI system; It is the third error position of the main star in the ECI system.
3. The method for evaluating internal collision of a large-scale symmetrical star cluster according to claim 1, characterized in that: The step of constructing a collision box of the target satellite based on the orbit error region of the target satellite includes: The shape of the orbit error region of the target satellite is converted into a parallelogram, and the parallelogram is dragged to form a collision box of the target satellite; In the formula, is the coordinate of the first error point in the polar coordinate system; is the coordinate of the second error point in the polar coordinate system; is the coordinate of the third error point in the polar coordinate system; is the coordinate of the fourth error point in the polar coordinate system; is the coordinate of the fifth error point in the polar coordinate system; is the coordinate of the sixth error point in the polar coordinate system; is the coordinate of the seventh error point in the polar coordinate system; is the coordinate of the eighth error point in the polar coordinate system; is the coordinate of the ninth error point in the polar coordinate system; is the coordinate of the tenth error point in the polar coordinate system; is the error of the right ascension of the ascending node.
4. The method for evaluating internal collision of a large-scale symmetrical star cluster according to claim 1, characterized in that: The step of expanding the collision box of the target satellite to obtain the expanded collision box of the target satellite includes: The collision box of the target satellite is expanded outward according to a set value and de-stretched to obtain the expanded collision box of the target satellite.
5. The method for evaluating internal collision of a large-scale symmetrical star cluster according to claim 1, characterized in that: The method of constructing the error-free position boundary of both parties according to the expanded collision box of the target satellite and the collision box of the slave satellite includes: According to the expanded collision box of the target satellite and the collision box of the slave satellite, the intersection between the expanded collision box of the target satellite and the collision box of the slave satellite is calculated; Analyze the intersection between the expanded collision box of the target satellite and the collision box of the slave satellite to determine the trajectory and potential collision path of the target satellite and the slave satellite; Based on the determined trajectories and potential collision paths of the target satellite and the slave satellite, an error-free position boundary is constructed for both parties.
6. A large-scale symmetric star cluster internal collision assessment method according to claim 1, characterized in that: The time period during which the collision risk between the master satellite and the slave satellite is calculated by using the error-free position boundary of both parties includes: Calculate the phase of the main star at the intersection through the error-free position boundary of both parties; According to the phase of the master star at the intersection, the phase of the virtual slave star when it collides is used to obtain the phase of the slave star that will collide at the intersection moment; Through the phase of the real slave star and the phase of the slave star that will collide at the intersection moment, find the slave star that will collide with the master star and obtain the time period when the master star and the slave star collide.
7. The method for evaluating internal collision of a large-scale symmetrical star cluster according to claim 1, characterized in that: The detecting of the time period during which the primary satellite and the secondary satellite have a risk of collision to determine whether a collision will occur includes: When there is a risk of collision between the master satellite and the slave satellite, compare whether the error-free position of the slave satellite is within the collision box calculated from the error-free position of the master satellite; If it is, the main star and the secondary star will collide; If it is not there, the main star and the slave star will not collide.
8. A large-scale symmetrical star cluster internal collision assessment system, characterized in that: include: Orbit error acquisition module: used to obtain the orbit error area of the target satellite in the constellation; Construct collision box module: used to construct the collision box of the target satellite based on the orbit error region of the target satellite; Collision box expansion module: used to expand the collision box of the target satellite to obtain the expanded collision box of the target satellite; Error-free boundary construction module: used to construct the error-free position boundary of both parties according to the expanded collision box of the target satellite and the collision box of the slave satellite; Calculation of collision time period module: Calculates the time period of collision risk between the master satellite and the slave satellite through the error-free position boundary of both parties; Collision determination module: used to detect the time period when there is a risk of collision between the master satellite and the slave satellite, and determine whether a collision will occur.
9. An electronic device, characterized in that: The invention comprises a memory, a processor and a computer program stored in the memory and executable on the processor, wherein the processor implements the steps of a large-scale symmetric star cluster internal collision assessment method as claimed in any one of claims 1 to 7 when executing the computer program.
10. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the steps of the large-scale symmetric star cluster internal collision assessment method according to any one of claims 1 to 7 are implemented.