Satellite constellation simulation system and its reconstruction method

Abstract

This invention provides a satellite constellation simulation system and its reconfiguration method, solving the problem of excessively long constellation reconfiguration time. The method includes: periodically sending clock synchronization signals to each satellite model; for each satellite model in the satellite constellation simulation model: determining whether a clock synchronization signal has been received; if so, obtaining the operating status of all satellite models from the state pool; determining whether the current satellite model needs reconfiguration based on the operating status of all satellite models; if so, reconfiguring the current satellite model; calculating the difference rate between the reconfigured satellite model and the satellite constellation simulation model; forming a difference rate control pool based on the difference rate, the difference rate control pool including satellite ID, time / rate flag, acceleration time, and difference rate; and obtaining the difference rate corresponding to the current satellite model from the difference rate control pool after reconfiguration, configuring the difference rate as the simulation rate of the current satellite model.

Description

Technical Field

[0001] This invention relates to the field of satellite simulation technology, and in particular to a satellite constellation simulation system and its reconstruction method. Background Technology

[0002] The satellite constellation simulation model consists of multiple digital satellites. These satellites operate simultaneously; if one of them malfunctions or fails, it needs to be restarted. After restarting, this satellite node will begin operating from its initial state. At this point, the restarted satellite node will be significantly different from the other satellite nodes in the constellation. The other satellites in the constellation must pause and wait for the restarted satellite node, which leads to excessively long constellation reconstruction times. Summary of the Invention

[0003] The technical problem to be solved by the present invention is to provide a satellite constellation simulation system and its reconstruction method, thereby solving the problem of excessively long constellation reconstruction time.

[0004] To address the aforementioned technical problems, this invention provides a method for reconstructing a satellite constellation simulation system, comprising: periodically sending clock synchronization signals to each satellite model; for each satellite model in the satellite constellation simulation model: determining whether the clock synchronization signal has been received; if so, obtaining the operating status of all satellite models from a state pool, wherein the state pool is used to maintain the operating status of each satellite model for each satellite cycle; determining whether the current satellite model needs to be reconstructed based on the operating status of all satellite models; if so, reconstructing the current satellite model; calculating the difference rate between the reconstructed satellite model and the satellite constellation simulation model; forming a difference rate control pool based on the difference rate, wherein the difference rate control pool includes a satellite ID, a time / rate flag, an acceleration time, and a difference rate; obtaining the difference rate corresponding to the current satellite model from the difference rate control pool after reconstruction, and configuring the difference rate as the simulation rate of the current satellite model.

[0005] Optionally, the difference rate between the reconstructed satellite model and the satellite constellation simulation model is calculated, including:

[0006] Calculate the first time difference between the onboard time of the satellite constellation simulation model and the onboard time of the reconstructed satellite model; determine whether the first time difference is less than the maximum simulation rate; if so, add 1 to the first time difference to obtain the difference rate.

[0007] Optionally, it further includes: if the first time difference is greater than or equal to the maximum simulation rate, then setting the difference rate to the maximum simulation rate and calculating the acceleration time, wherein the acceleration time is the time required for the reconstructed satellite model to run at the maximum simulation rate.

[0008] Optionally, the acceleration time can be calculated according to the following formula:

[0009]

[0010] Optionally, it further includes: after acceleration time, calculating a second time difference between the on-board time of the satellite constellation simulation model and the on-board time of the reconstructed satellite model, determining whether the second time difference is less than the maximum simulation rate, and if so, adding 1 to the second time difference to obtain the difference rate.

[0011] Optionally, determining whether the current satellite model needs to be reconstructed based on the operating status of all satellite models includes: determining whether the satellite constellation simulation model is operating normally based on the operating status of all satellite models; if so, determining whether the current satellite model is operating normally; if not, then the current satellite model needs to be reconstructed.

[0012] Optionally, determining whether the satellite constellation simulation model is operating normally includes: determining whether the satellite constellation simulation model is operating normally according to preset conditions, wherein the preset conditions include that if more than or equal to N satellite models are operating normally, then the satellite constellation simulation model is operating normally, and N is a positive integer.

[0013] Optionally, reconstructing the current satellite model includes restarting the current satellite model or reconstructing the onboard software and then restarting the current satellite model.

[0014] Optionally, the clock synchronization signal may be broadcast periodically at the frequency of the satellite's operational cycle.

[0015] Optionally, the method further includes: when the reconstructed current satellite model has the same on-board time as the satellite constellation simulation model, configuring the simulation rate of the reconstructed current satellite model to be consistent with the simulation rate of the satellite constellation simulation model.

[0016] To address the aforementioned technical problems, this invention provides a satellite constellation simulation system, including a satellite constellation simulation model, and further comprising:

[0017] The clock source synchronization module is used to periodically send clock synchronization signals to each satellite model in the satellite constellation simulation model;

[0018] The simulation synchronization module includes a state pool, which is used to maintain the operating status of each satellite model for each satellite cycle;

[0019] The simulation reconstruction module is used to receive the judgment results of each satellite model. When the judgment result is that the current satellite model needs to be reconstructed, the current satellite model is restarted or the on-board software is reconstructed and then the current satellite model is restarted.

[0020] The simulation differential rate control module is used to calculate the differential rate between the reconstructed satellite model and the satellite constellation simulation model, and to form a differential rate control pool based on the differential rate. The differential rate control pool includes satellite ID, time / rate flag, acceleration time and differential rate.

[0021] In the satellite constellation simulation model, each satellite model is configured to, upon receiving the clock synchronization signal, obtain the operating status of all satellite models from the state pool, determine whether the current satellite model needs to be reconstructed based on the operating status of all satellite models, and after the current satellite model is reconstructed, obtain the differential rate corresponding to the current satellite model from the differential rate control pool and configure the differential rate as the simulation rate of the current satellite model.

[0022] Optionally, the simulation difference rate control module is used to: calculate the first time difference between the on-board time of the satellite constellation simulation model and the on-board time of the reconstructed satellite model; determine whether the first time difference is less than the maximum simulation rate; if so, add 1 to the first time difference to obtain the difference rate.

[0023] Optionally, the simulation difference rate control module is further configured to: if the first time difference is greater than or equal to the maximum simulation rate, set the difference rate to the maximum simulation rate and calculate the acceleration time, wherein the acceleration time is the time required for the reconstructed satellite model to run at the maximum simulation rate.

[0024] Optionally, the simulation difference rate control module is further configured to: after acceleration time, calculate the second time difference between the on-board time of the satellite constellation simulation model and the on-board time of the reconstructed satellite model, determine whether the second time difference is less than the maximum simulation rate, and if so, add 1 to the second time difference to obtain the difference rate.

[0025] Optionally, the system also includes a fault alarm module, which receives the judgment results of the operating status of each satellite model and issues a fault alarm signal when the judgment result indicates that the satellite constellation simulation model or the satellite model is faulty.

[0026] Compared with the prior art, the present invention has the following advantages:

[0027] The satellite constellation simulation system and its reconstruction method of the present invention calculate the difference rate between the reconstructed satellite model and the satellite constellation simulation model, form a difference rate control pool based on the difference rate, and automatically match the simulation rate of the satellite model that is re-added to the satellite constellation simulation model after reconstruction through the difference rate control pool. This achieves the automatic consistency between the reconstructed satellite model and the satellite constellation simulation model, thereby improving the efficiency of system reconstruction. Attached Figure Description

[0028] The accompanying drawings are included to provide a further understanding of this application; they are incorporated into and constitute a part of this application. The drawings illustrate embodiments of this application and, together with this specification, serve to explain the principles of the invention. In the drawings:

[0029] Figure 1 This is a system block diagram of a satellite constellation simulation system according to an embodiment of the present invention.

[0030] Figure 2A This is a schematic diagram of a state pool according to an embodiment of the present invention.

[0031] Figure 2B This is an operating status table according to an embodiment of the present invention.

[0032] Figure 3 This is a schematic diagram of a state machine in operation according to an embodiment of the present invention.

[0033] Figure 4 This is a simulation synchronization flowchart according to an embodiment of the present invention.

[0034] Figure 5 This is a schematic diagram of a differential rate control cell according to an embodiment of the present invention.

[0035] Figure 6 This is a flowchart illustrating the calculation of the differential rate by the simulation differential rate control module according to an embodiment of the present invention.

[0036] Figure 7 This is a flowchart of a reconstruction method for a satellite constellation simulation system according to an embodiment of the present invention. Detailed Implementation

[0037] To more clearly illustrate the technical solutions of the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are merely some examples or embodiments of this application. For those skilled in the art, these drawings can be applied to other similar scenarios without creative effort. Unless obvious from the context or otherwise specified, the same reference numerals in the drawings represent the same structures or operations.

[0038] Flowcharts are used in this application to illustrate the operations performed by the system according to embodiments of this application. It should be understood that the preceding or following operations are not necessarily performed in exact order. Instead, various steps can be processed in reverse order or simultaneously. Furthermore, other operations may be added to these processes, or one or more steps may be removed from these processes.

[0039] As described in the background section, in a satellite constellation simulation model, if one of the digital satellite nodes malfunctions or fails, it needs to be restarted. After restarting, this digital satellite node will resume operation from its initial state. At this time, the restarted satellite node will be significantly different from other satellite nodes in the constellation. This necessitates pausing other satellites in the constellation to wait for the restarted node, resulting in excessively long constellation reconfiguration times. This invention addresses this by maintaining the operational status of each satellite model for each satellite cycle through a state pool, and promptly reconfiguring satellite nodes that require reconfiguration based on the operational status. Furthermore, this invention improves the efficiency of system reconfiguration by automatically matching the simulation rate of satellite nodes rejoining the satellite constellation simulation model after reconfiguration through a differential rate control pool.

[0040] Figure 1 This is a system block diagram of a satellite constellation simulation system according to an embodiment of the present invention. Figure 1 As shown, the satellite constellation simulation system 100 includes a satellite constellation simulation model 10, a clock source synchronization module 11, a simulation synchronization module 12, a simulation reconstruction module 13, and a simulation differential rate control module 14. These modules can be executed entirely by software (including firmware, resident software, microcode, etc.) or by a combination of hardware and software. The satellite constellation simulation model 10 includes multiple satellite models. This application does not limit the number of satellite models. In this embodiment, the satellite constellation simulation model 10 includes satellite model 101, satellite model 102, and satellite model 103.

[0041] The clock source synchronization module 11 is used to periodically send clock synchronization signals to each satellite model in the satellite constellation simulation model 10. Optionally, the clock source synchronization module 11 uses a high-precision hardware clock source to provide a high-precision clock synchronization signal to the satellite constellation simulation model 10. The clock source synchronization module 11 sends the clock synchronization signal to each satellite model node via broadcast. Optionally, the clock source synchronization module 11 broadcasts the clock synchronization signal periodically at the frequency of the satellite's operational cycle.

[0042] The simulation synchronization module 12 includes a state pool. This state pool is used to maintain the operating status of each satellite model for each satellite cycle. Figure 2A This is a schematic diagram of a state pool according to an embodiment of the present invention. Figure 2A As shown, the state pool includes satellite IDs and the operational status of satellite models. The operational status of a satellite model includes fault, running, and normal operation. Different operational statuses can be represented by different values. Figure 2B This is an operational status table according to an embodiment of the present invention. For example... Figure 2BAs shown, -1 indicates an obstructed running status; 0 indicates the current cycle has not yet ended and the running status is "running"; 1 indicates the current cycle has ended and is running normally and the running status is "normal". The simulation synchronization module 12 achieves synchronized operation of the satellite constellation simulation model by maintaining the running status of each satellite model in the state pool. For example, when all satellite models in the satellite constellation simulation model are running normally in the current cycle, or when a specified number of satellite models are running normally in the current cycle, the satellite constellation simulation model enters the next running cycle; otherwise, the satellite constellation simulation model enters a fault state. Figure 3 This is a schematic diagram of a state machine in operation according to an embodiment of the present invention. Figure 4 This is a simulation synchronization flowchart according to an embodiment of the present invention. The following is in conjunction with... Figure 3 and Figure 4 Explain how the simulation synchronization module 12 achieves synchronized operation of the satellite constellation simulation model by maintaining the operational status of each satellite model in the state pool. For example... Figure 4 As shown, the simulation synchronization process includes the following steps:

[0043] Step S41: After the satellite model starts running, first determine whether a clock synchronization signal has been received. If not, continue to wait for the clock synchronization signal until it is received; if it is received, proceed to step S42.

[0044] Step S42: Retrieve the satellite IDs and operating statuses of all satellite models from the shared memory state pool.

[0045] Step S43: Determine whether the satellite constellation simulation model is operating normally based on preset conditions (hereinafter referred to as whether the constellation is operating normally). The preset conditions can be set to all satellite models operating normally, or a certain number of satellite models operating normally is considered sufficient for the entire satellite constellation simulation model to operate normally. If the satellite constellation simulation model is not operating normally, i.e., the preset conditions are not met, the entire satellite constellation simulation model will not enter the next operating cycle and will enter a fault state. If the constellation is operating normally, proceed to step S44.

[0046] Step S44: Continue to determine whether the current satellite model is operating normally. If yes, proceed to step S45; otherwise, proceed to step S49.

[0047] Step S45: Call the current satellite model to perform one satellite operation cycle, and set the current satellite model's running status to running.

[0048] Step S46: Determine whether the current satellite model has completed normal operation within one satellite service cycle. If yes, proceed to step S47; otherwise, proceed to step S48.

[0049] Step S47: Set the current satellite model's operating status to normal operation.

[0050] Step S48: Set the current satellite model's operating status to fault.

[0051] Step S49: Restart the current satellite model.

[0052] like Figure 3 As shown, when a satellite mission cycle ends normally, the current satellite model's operational status is set to "normal operation." If the cycle does not end normally or the end time exceeds one mission cycle, the current satellite model's operational status is automatically set to "fault" when the mission cycle ends. If the current satellite model's operational status is "fault," it needs to be reconstructed. Optionally, reconstructing the current satellite model includes restarting it or performing an onboard software reconstruction followed by a restart. After restarting, the satellite model's operational status is updated to "normal operation."

[0053] The simulation reconstruction module 13 receives the judgment results from each satellite model. When the judgment result indicates that the current satellite model needs reconstruction, it either restarts the current satellite model or updates the onboard software on the current satellite model and then restarts it. The restarted satellite model will start running again from its initial state. At this time, there will be a time difference between the restarted satellite model and other satellite models in the constellation. Therefore, the restarted satellite model needs to be configured with a faster simulation rate to catch up with other satellite models.

[0054] This invention uses a differential rate control pool to automatically match the simulation rate of the satellite model that has been reconstructed and then added back to the satellite constellation simulation model, thereby achieving automatic reconstruction of the satellite constellation simulation model.

[0055] The simulation differential rate control module 14 is used to calculate the differential rate between the reconstructed satellite model and the satellite constellation simulation model. The differential rate is the difference between the simulation rate of each satellite model and the simulation rate of the satellite constellation simulation model. A differential rate control pool is formed based on these differential rates, and the differential rate control pool can simultaneously maintain the differential rates of multiple satellite models. Figure 5 This is a schematic diagram of a differential rate control cell according to an embodiment of the present invention. Figure 5 As shown, the differential rate control pool 500 includes satellite ID, time / rate flags, acceleration time, and differential rate. The time / rate flags are as follows:

[0056] 0: Indicates that the satellite model is running normally and does not require acceleration.

[0057] 1: Indicates the reconstructed satellite model is running at the maximum simulation rate; in this case, the acceleration time needs to be calculated. 2: Indicates the reconstructed satellite model has an acceleration time of 1 second; in this case, the difference rate needs to be calculated.

[0058] Figure 6 This is a flowchart illustrating the calculation of the difference rate by a simulation difference rate control module according to an embodiment of the present invention. Figure 6 As shown, the simulation differential rate control module calculates the differential rate through the following steps:

[0059] Step S141: Calculate the first time difference between the on-board time of the satellite constellation simulation model and the on-board time of the reconstructed satellite model. Here, on-board time refers to the satellite operational time. If the satellite model is operating normally, the satellite operational time of the satellite model is consistent with the satellite operational time of the satellite constellation simulation model, and no acceleration is required. (Reference) Figure 5 As shown, the time / rate flag for satellite 101 is 0, indicating that the satellite model is operating normally and does not require acceleration. At this time, the acceleration time is 0; the difference rate is 1, representing the simulation rate of the satellite constellation simulation model. If the satellite model is reconstructed, it needs to restart from its initial state, and the satellite service time of the satellite model will inevitably differ from that of the satellite service time of the satellite constellation simulation model.

[0060] Step S142: Determine whether the first time difference is less than the maximum simulation rate. If yes, proceed to step S143; otherwise, proceed to step S144.

[0061] Step S143: Add 1 to the first time difference to obtain the difference rate.

[0062] When the time difference between the restarted satellite model and the satellite constellation simulation model onboard is less than the maximum simulation rate, the difference rate can be calculated using the following formula:

[0063] Difference rate = Satellite constellation simulation model on-board time - Reconstructed satellite model on-board time + 1

[0064] The acceleration time at this point is 1 second.

[0065] refer to Figure 5 As shown, the time / rate flag of satellite 103 is 2, indicating that the acceleration time of the reconstructed satellite model is 1 second, and the difference rate is x calculated by the above formula.

[0066] Step S144: Set the difference rate to the maximum simulation rate and calculate the acceleration time, which is the time required for the reconstructed current satellite model to run at the maximum simulation rate.

[0067] When the time difference between the restarted satellite model and the satellite constellation simulation model at launch is greater than or equal to the maximum simulation rate, the satellite model can only run at the maximum simulation rate. Therefore, the time difference is set to the maximum simulation rate. Furthermore, the acceleration time required for the current satellite model to run at the maximum simulation rate needs to be calculated. Optionally, the acceleration time can be calculated using the following formula:

[0068]

[0069] refer to Figure 5 As shown, the time / rate flag of satellite 102 is 1, the difference rate is the maximum simulated rate, and the acceleration time is X calculated by the above formula.

[0070] In some embodiments, the simulation difference rate control module further includes step S145 in calculating the difference rate: after the acceleration time, the time difference between the reconstructed satellite model's on-board time and the satellite constellation simulation model's on-board time decreases, and the first time difference between the satellite constellation simulation model's on-board time and the reconstructed satellite model's on-board time is recalculated (denoted as the second time difference). It is determined whether the second time difference is less than the maximum simulation rate. If so, the second time difference is incremented by 1 to obtain the difference rate. If not, the acceleration time is iteratively calculated, and the determination is repeated after the acceleration time, until the time difference between the restarted satellite model and the satellite constellation system's on-board time is less than the maximum simulation rate.

[0071] After the current satellite model is reconstructed, the difference rate corresponding to the current satellite model is obtained from the difference rate control pool, and the difference rate is configured as the simulation rate of the current satellite model. For example... Figure 5 As shown, after satellite 103 restarts, it obtains the differential rate x from the differential rate control pool 500 and configures the differential rate x as the simulation rate of the current satellite model. After satellite 102 restarts, it obtains the maximum simulation rate from the differential rate control pool 500 and configures the maximum simulation rate as the simulation rate of the current satellite model. The time that satellite 102 runs at the maximum simulation rate is the acceleration time X. After the acceleration time X, it re-obtains the differential rate corresponding to satellite 102 from the differential rate control pool 500 and configures the differential rate as the simulation rate of the current satellite model. This continues until the reconstructed current satellite model and the satellite constellation simulation model have the same on-board time, at which point the simulation rate of the reconstructed current satellite model is configured to be consistent with the simulation rate of the satellite constellation simulation model.

[0072] In some embodiments, the satellite constellation simulation system further includes a fault alarm module. The fault alarm module receives the operational status judgment results of each satellite model and issues a fault alarm signal when the judgment result indicates a fault in the satellite constellation simulation model or a fault in the satellite model. For example, the satellite model obtains the operational status of all satellite models from the state pool. Then, it judges whether the satellite constellation simulation model is operating normally according to preset conditions. If the preset conditions are not met, it is judged that the satellite constellation simulation model is faulty. If the preset conditions are met, it judges whether the current satellite model's operational status is normal; if not, it is judged that the satellite model is faulty. When the fault alarm module receives a satellite constellation simulation model fault or a satellite model fault, it issues a fault alarm signal to remind the user to intervene promptly.

[0073] Optionally, the fault alarm module includes a display unit. The fault alarm module is also used to receive key information such as the simulation rate of each satellite model. The display unit is used to display the simulation rate of each satellite model and the simulation rate of the satellite constellation simulation model. Optionally, the display unit is also used to display the judgment result of the operating status of each satellite model, for example, displaying whether the fault is in the satellite constellation simulation model or a single satellite model.

[0074] The satellite constellation simulation system of the present invention automatically matches the simulation rate of the satellite model that is re-added to the satellite constellation simulation model after reconstruction by using the differential rate control pool of the simulation differential rate control module. This enables the reconstructed satellite model to automatically maintain consistency with the satellite constellation simulation model, reduces manual operation, and improves the efficiency of system reconstruction.

[0075] Figure 7 This is a flowchart of a reconstruction method for a satellite constellation simulation system according to an embodiment of the present invention. The reconstruction method for the satellite constellation simulation system is applicable to the satellite constellation simulation system 100 described above. Therefore, detailed steps of the reconstruction method for the satellite constellation simulation system of this application can be found in the description of the satellite constellation simulation system 100, and will not be repeated here. Figure 7 As shown, the reconstructing method 700 for a satellite constellation simulation system includes the following steps:

[0076] Step S71: Periodically send clock synchronization signals to each satellite model.

[0077] Optionally, the clock synchronization signal can be broadcast to each satellite model. Preferably, the clock synchronization signal is broadcast periodically at the frequency of the satellite's operational cycle.

[0078] For each satellite model in the satellite constellation simulation model:

[0079] Step S72: Determine whether a clock synchronization signal has been received. If so, obtain the operating status of all satellite models from the state pool. The state pool is used to maintain the operating status of each satellite model for each satellite cycle.

[0080] Step S73: Determine whether the current satellite model needs to be reconstructed based on the operating status of all satellite models. If so, reconstruct the current satellite model.

[0081] Optionally, determining whether the current satellite model needs to be reconstructed based on the operating status of all satellite models includes determining whether the satellite constellation simulation model is operating normally based on the operating status of all satellite models. If it is, then determine whether the current satellite model is operating normally; if not, then the current satellite model needs to be reconstructed.

[0082] Optionally, determining whether the satellite constellation simulation model is operating normally includes determining whether the satellite constellation simulation model is operating normally based on preset conditions. These preset conditions include that if N or more satellite models are operating normally, then the satellite constellation simulation model is operating normally, where N is a positive integer. In other words, the preset conditions can be set to all satellite models operating normally, or they can be set to a certain number of satellite models operating normally for the entire satellite constellation simulation model to be operating normally.

[0083] When the satellite constellation simulation model is running normally but the current satellite model is in a faulty state, it is necessary to reconstruct the current satellite model. Reconstructing the current satellite model includes restarting the current satellite model or reconstructing the onboard software and then restarting the current satellite model.

[0084] Step S74: Calculate the difference rate between the reconstructed satellite model and the satellite constellation simulation model, and form a difference rate control pool based on the difference rate. The difference rate control pool includes satellite ID, time / rate flag, acceleration time and difference rate.

[0085] Optionally, the step of calculating the difference rate between the reconstructed satellite model and the satellite constellation simulation model includes:

[0086] Calculate the first time difference between the satellite constellation simulation model and the reconstructed satellite model on-board time;

[0087] When the first time difference is less than the maximum simulation rate, the acceleration time is 1 second, and the difference rate can be calculated using the following formula:

[0088] Difference rate = Satellite constellation simulation model on-board time - Reconstructed satellite model on-board time + 1

[0089] When the first time difference is greater than or equal to the maximum simulation rate, the difference rate is set to the maximum simulation rate, and the acceleration time is calculated. The acceleration time is the time required for the reconstructed current satellite model to run at the maximum simulation rate. The acceleration time can be calculated using the following formula:

[0090]

[0091] After acceleration, the first time difference (denoted as the second time difference) between the satellite constellation simulation model and the reconstructed satellite model is recalculated. It is then determined whether the second time difference is less than the maximum simulation rate. If so, the second time difference is incremented by 1 to obtain the difference rate.

[0092] For a detailed explanation of the difference rate between the reconstructed satellite model and the satellite constellation simulation model, please refer to [link / reference]. Figure 6 This will not be elaborated upon here.

[0093] Step S75: The reconstructed current satellite model obtains the difference rate corresponding to the current satellite model from the difference rate control pool, and configures the difference rate as the simulation rate of the current satellite model.

[0094] In some embodiments, the satellite constellation simulation system reconstruction method further includes the step of:

[0095] When the onboard time of the reconstructed current satellite model is consistent with that of the satellite constellation simulation model, the simulation rate of the reconstructed current satellite model should be configured to be consistent with that of the satellite constellation simulation model.

[0096] The basic concepts have been described above. Obviously, for those skilled in the art, the above disclosure is merely illustrative and does not constitute a limitation of this application. Although not explicitly stated herein, those skilled in the art may make various modifications, improvements, and corrections to this application. Such modifications, improvements, and corrections are suggested in this application, and therefore remain within the spirit and scope of the exemplary embodiments of this application.

[0097] Furthermore, this application uses specific terms to describe embodiments of the application. For example, "an embodiment," "one embodiment," and / or "some embodiments" refer to a particular feature, structure, or characteristic related to at least one embodiment of the application. Therefore, it should be emphasized and noted that "an embodiment," "one embodiment," or "an alternative embodiment" mentioned twice or more in different locations in this specification do not necessarily refer to the same embodiment. In addition, certain features, structures, or characteristics in one or more embodiments of the application can be appropriately combined.

[0098] Some aspects of this application can be executed entirely by hardware, entirely by software (including firmware, resident software, microcode, etc.), or by a combination of hardware and software. The aforementioned hardware or software may be referred to as a "data block," "module," "engine," "unit," "component," or "system." The processor may be one or more application-specific integrated circuits (ASICs), digital signal processors (DSPs), digital signal processing devices (DAPDs), programmable logic devices (PLDs), field-programmable gate arrays (FPGAs), processors, controllers, microcontrollers, microprocessors, or combinations thereof. Furthermore, aspects of this application may manifest as computer products residing in one or more computer-readable media, including computer-readable program code. For example, computer-readable media may include, but are not limited to, magnetic storage devices (e.g., hard disks, floppy disks, magnetic tapes, etc.), optical discs (e.g., compressed CDs, digital multifunction DVDs, etc.), smart cards, and flash memory devices (e.g., cards, sticks, key drives, etc.).

[0099] Similarly, it should be noted that, in order to simplify the description of the present application and thus aid in the understanding of one or more embodiments of the invention, the foregoing description of the embodiments of the present application sometimes combines multiple features into a single embodiment, drawing, or description thereof. However, this disclosure method does not imply that the subject matter of the application requires more features than those mentioned in the claims. In fact, the embodiments contain fewer features than all the features of the single embodiments disclosed above.

[0100] As indicated in this application and claims, unless the context clearly indicates otherwise, the words "a," "an," "an," and / or "the" are not specifically singular and may include plural forms. Generally speaking, the terms "comprising" and "including" only indicate the inclusion of explicitly identified steps and elements, which do not constitute an exclusive list, and the method or apparatus may also include other steps or elements.

[0101] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps described in these embodiments do not limit the scope of this application. It should also be understood that, for ease of description, the dimensions of the various parts shown in the drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters in the following drawings denote similar items; therefore, once an item is defined in one drawing, it need not be further discussed in subsequent drawings.

[0102] Furthermore, it should be noted that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, these terms have no special meaning and therefore should not be construed as limiting the scope of protection of this application. In addition, although the terminology used in this application is selected from commonly known and used terms, some terms mentioned in this application's specification may have been chosen by the applicant according to his or her judgment, and their detailed meanings are explained in the relevant sections of this description. Moreover, this application should be understood not only through the actual terms used, but also through the meaning implied by each term.

[0103] Although this application has been described with reference to specific embodiments, those skilled in the art should recognize that the above embodiments are only used to illustrate this application, and various equivalent changes or substitutions can be made without departing from the spirit of this application. Therefore, any changes or modifications to the above embodiments within the essential spirit of this application will fall within the scope of the claims of this application.

Claims

1. A method for reconstructing a satellite constellation simulation system, the satellite constellation simulation system comprising a satellite constellation simulation model, the satellite constellation simulation model comprising multiple satellite models, characterized in that, The method includes: Periodically send clock synchronization signals to each satellite model; For each satellite model in the aforementioned satellite constellation simulation model: Determine whether the clock synchronization signal has been received. If so, retrieve the operating status of all satellite models from the state pool, which is used to maintain the operating status of each satellite model for each satellite cycle. Determine whether the current satellite model needs to be reconstructed based on the operational status of all satellite models; if so, reconstruct the current satellite model. The difference rate between the reconstructed satellite model and the satellite constellation simulation model is calculated, and a difference rate control pool is formed based on the difference rate. The difference rate control pool includes satellite ID, time / rate flag, acceleration time and difference rate. The reconstructed current satellite model obtains the difference rate corresponding to the current satellite model from the difference rate control pool, and configures the difference rate as the simulation rate of the current satellite model; The calculation of the difference rate between the reconstructed satellite model and the satellite constellation simulation model includes: calculating the first time difference between the onboard time of the satellite constellation simulation model and the onboard time of the reconstructed satellite model; determining whether the first time difference is less than the maximum simulation rate; if so, adding 1 to the first time difference to obtain the difference rate.

2. The method as described in claim 1, characterized in that, Also includes: If the first time difference is greater than or equal to the maximum simulation rate, then the difference rate is set to the maximum simulation rate and the acceleration time is calculated, where the acceleration time is the time required for the reconstructed satellite model to run at the maximum simulation rate.

3. The method as described in claim 2, characterized in that, The acceleration time is calculated using the following formula: 。 4. The method as described in claim 2, characterized in that, Also includes: After acceleration, the second time difference between the satellite constellation simulation model's onboard time and the reconstructed satellite model's onboard time is calculated. It is then determined whether the second time difference is less than the maximum simulation rate. If so, the second time difference is incremented by 1 to obtain the difference rate.

5. The method as described in claim 1, characterized in that, Determining whether the current satellite model needs reconstruction based on the operational status of all satellite models includes: The satellite constellation simulation model is judged to be running normally based on the operating status of all satellite models. If it is, the current satellite model is judged to be running normally. If not, the current satellite model needs to be reconstructed.

6. The method of claim 5, characterized in that, Determining whether the satellite constellation simulation model is operating normally includes: The satellite constellation simulation model is judged to be operating normally according to preset conditions. The preset conditions include that if more than or equal to N satellite models are operating normally, then the satellite constellation simulation model is operating normally, where N is a positive integer.

7. The method as described in claim 1, characterized in that, Reconstructing the current satellite model includes restarting the current satellite model or reconstructing the onboard software and then restarting the current satellite model.

8. The method as described in claim 1, characterized in that, The clock synchronization signal is broadcast periodically at the frequency of the satellite's operational cycle.

9. The method as described in claim 1, characterized in that, Also includes: When the reconstructed current satellite model has the same on-board time as the satellite constellation simulation model, the simulation rate of the reconstructed current satellite model is configured to be the same as the simulation rate of the satellite constellation simulation model.

10. A satellite constellation simulation system, comprising a satellite constellation simulation model, characterized in that, Also includes: The clock source synchronization module is used to periodically send clock synchronization signals to each satellite model in the satellite constellation simulation model; The simulation synchronization module includes a state pool, which is used to maintain the operating status of each satellite model for each satellite cycle; The simulation reconstruction module is used to receive the judgment results of each satellite model. When the judgment result is that the current satellite model needs to be reconstructed, the current satellite model is restarted or the on-board software is reconstructed and then the current satellite model is restarted. The simulation differential rate control module is used to calculate the differential rate between the reconstructed satellite model and the satellite constellation simulation model, and to form a differential rate control pool based on the differential rate. The differential rate control pool includes satellite ID, time / rate flag, acceleration time and differential rate. In the satellite constellation simulation model, each satellite model is configured to, upon receiving the clock synchronization signal, obtain the operating status of all satellite models from the state pool, determine whether the current satellite model needs to be reconstructed based on the operating status of all satellite models, and after the current satellite model is reconstructed, obtain the differential rate corresponding to the current satellite model from the differential rate control pool and configure the differential rate as the simulation rate of the current satellite model. The simulation difference rate control module is used to: calculate the first time difference between the on-board time of the satellite constellation simulation model and the on-board time of the reconstructed satellite model; determine whether the first time difference is less than the maximum simulation rate; if so, add 1 to the first time difference to obtain the difference rate.

11. The system as claimed in claim 10, characterized in that, The simulation difference rate control module is further configured to: if the first time difference is greater than or equal to the maximum simulation rate, set the difference rate to the maximum simulation rate and calculate the acceleration time, wherein the acceleration time is the time required for the reconstructed satellite model to run at the maximum simulation rate.

12. The system as claimed in claim 11, characterized in that, The simulation difference rate control module is also used to: after acceleration time, calculate the second time difference between the satellite constellation simulation model on-board time and the reconstructed satellite model on-board time, determine whether the second time difference is less than the maximum simulation rate, and if so, add 1 to the second time difference to obtain the difference rate.

13. The system as described in claim 10, characterized in that, It also includes a fault alarm module, which is used to receive the judgment results of the operation status of each satellite model, and issue a fault alarm signal when the judgment result is that the satellite constellation simulation model or the satellite model is faulty.

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