Optimization methods for space resource utilization in low-Earth orbit communication satellite satellite service software

Abstract

This invention provides a method for optimizing the use of space resources in low-Earth orbit (LEO) communication satellite operation software. This method involves establishing a multi-factor model of the functional modules of the LEO communication satellite operation software. The multi-factor model includes the corresponding operating mode, space characteristic elements, key attribute elements, and control switch elements for each functional module. The method calculates the important parameter space resources used by the LEO communication satellite operation software. If the important parameter space resources are not less than the preset space resource usage alarm threshold of the LEO communication satellite operation software, adaptive scheduling measures are executed based on the multi-factor model. Thus, this invention can maximize the efficiency of space storage resource utilization, providing a solid guarantee for ensuring the stable and reliable operation of the software.

Description

Technical Field

[0001] This invention relates to the field of satellite technology, and in particular to an optimization method for the use of space resources in low-Earth orbit communication satellite mission software. Background Technology

[0002] Low-Earth orbit communication satellite satellite management software is complex, including multiple functional modules such as telemetry and remote control, autonomous energy management, autonomous thermal control management, autonomous fault management, time management, and autonomous payload management.

[0003] The software needs to have the function of saving and restoring important parameters so that when the satellite is switched or reset, the operating status of each functional module can be restored according to the previously saved important parameters, ensuring the continuity of the status data of the core software modules, thereby enabling the software to operate stably.

[0004] Due to the limited hardware storage resources of low-Earth orbit (LEO) communication satellites, efficiently storing critical parameters of the satellite's operational software within these limited resources to ensure the orderly and stable operation of all functions has become a key challenge in software design. Traditional software design methods are no longer adequate, necessitating a new improvement strategy that optimizes the use of spatial resources for functional modules and maximizes the utilization of hardware storage resources. Summary of the Invention

[0005] The purpose of this invention is to provide an optimization method for the use of space resources in low-Earth orbit communication satellite mission software, which can maximize the efficiency of space storage resource utilization and provide a solid guarantee for ensuring the stable and reliable operation of the software.

[0006] To achieve the above objectives, the present invention provides an optimization method for the use of space resources in low-Earth orbit communication satellite service software, comprising:

[0007] A multi-element model of the functional modules of the low-Earth orbit communication satellite satellite service software is established. The multi-element model includes the operating mode, spatial characteristic elements, key attribute elements, and control switch elements corresponding to each functional module. The spatial characteristic elements represent the space resources occupied by important parameters used by the functional module and its sub-functional modules during operation. The key attribute elements represent the preset critical level corresponding to the functional module. The control switch elements represent the enabled or disabled attribute state corresponding to the functional module.

[0008] Calculate the important parameters of space resources used by the low-Earth orbit communication satellite's satellite service software;

[0009] If the important parameter of space resources is not less than the space resource usage alarm threshold preset by the low-orbit communication satellite service software, then adaptive scheduling measures are executed based on the multi-factor model.

[0010] The adaptive scheduling measures include:

[0011] S1. Query the first functional module that is in operation and has the same operating mode as the current software through the multi-factor model;

[0012] S2. Based on the key attribute elements, select the second functional module with the lowest preset key level from a plurality of first functional modules.

[0013] S3. Traverse and select the target sub-functional modules of the second functional module, and adjust the control switch element corresponding to the target sub-functional module to the disabled state;

[0014] S4. Update the spatial characteristic elements of the second functional module and recalculate the important parameter spatial resources;

[0015] S5. If the updated important parameter space resource is not less than the space resource usage alarm threshold, then return to repeat steps S1 to S4 until the important parameter space resource is less than the space resource usage alarm threshold.

[0016] Furthermore, the adaptive scheduling measures also include:

[0017] If all the control switch elements of each of the second functional modules are adjusted to the disabled state, and the updated important parameter space resource is still not less than the space resource usage alarm threshold, then based on the key attribute elements, a third functional module one level above the preset key level is selected from several first functional modules; wherein, the one level above the preset key level refers to the priority level above the lowest preset key level.

[0018] Based on the selected third functional module, replace the second functional module in steps S3 to S5, and repeat steps S3 to S5 until the important parameter space resource is less than the space resource usage alarm threshold.

[0019] Furthermore, the multi-element model for establishing the functional modules of the low-Earth orbit communication satellite service software includes:

[0020] Based on the mission requirements of the low-Earth orbit communication satellite satellite service software, the various functional modules of the low-Earth orbit communication satellite satellite service software are defined.

[0021] Establish at least one of the aforementioned operating modes associated with each of the aforementioned functional modules;

[0022] Construct the spatial characteristic elements corresponding to each of the aforementioned functional modules;

[0023] Construct the key attribute elements corresponding to each of the aforementioned functional modules;

[0024] Construct the control switch element corresponding to each of the aforementioned functional modules.

[0025] Furthermore, establishing at least one operating mode associated with each of the aforementioned functional modules includes:

[0026] Based on the mission division of the low-Earth orbit communication satellite and the execution timing of each functional module, determine at least one of the operating modes associated with each functional module;

[0027] Construct a mapping matrix between each of the functional modules and the operating mode.

[0028] Furthermore, the spatial characteristic elements corresponding to each of the aforementioned functional modules include:

[0029] The spatial resources occupied by the important parameters used by the sub-functional modules corresponding to each functional module are analyzed and determined, and the spatial characteristic sub-elements associated with each sub-functional module are obtained.

[0030] The set of spatial characteristic elements, which is composed of the spatial characteristic sub-elements of each of the functional modules, is taken as the spatial characteristic element corresponding to the functional module.

[0031] Furthermore, the key attribute elements corresponding to each of the aforementioned functional modules include:

[0032] Based on the mission division and system risk analysis of low-Earth orbit communication satellites, the criticality level of each functional module in the low-Earth orbit communication satellite satellite management software is determined.

[0033] Obtain the quantitative representation of the key level as the key attribute element of the corresponding functional module.

[0034] Furthermore, the control switch elements of the functional module include the main control switch elements of the functional module itself and the control switch sub-elements corresponding to each sub-functional module of the functional module.

[0035] Furthermore, the important spatial resources used by the calculation of the low-Earth orbit communication satellite service software include:

[0036] Based on the spatial characteristic elements of each functional module in the multi-factor model, the important parameter spatial resources occupied by each running functional module are statistically analyzed.

[0037] Furthermore, the first functional module that is in operation and in the same operating mode as the current software, queried through the multi-factor model, includes:

[0038] Query the current operating mode of the software and the corresponding mapping element in the mapping relationship matrix;

[0039] Iterate through the queried mapping elements to identify the first functional module that is in operation.

[0040] Furthermore, the query of the current operating mode of the software and the corresponding mapping element in the mapping relationship matrix includes:

[0041] The current operating mode of the software is determined, and the mapping element corresponding to the current operating mode of the software is queried from the mapping relationship matrix; the mapping element includes a first value and a second value, the first value and the second value respectively representing whether the corresponding functional module is in an operating state or a non-operating state;

[0042] The step of traversing the first functional module in the running state from the queried mapping elements includes:

[0043] The target mapping element with the first value is traversed from the queried mapping elements, and the functional module corresponding to the target mapping element is determined as the first functional module.

[0044] The method for optimizing the use of space resources in low-Earth orbit communication satellite space service software described in this invention is based on attributes such as operating mode, space characteristic element model of each module, and control switch characteristics. It enables adaptive scheduling of the storage resources occupied by important parameters of each functional module of the software, thereby optimizing the utilization of space resources and ensuring stable and reliable operation of the software. Attached Figure Description

[0045] Figure 1 This is a flowchart illustrating the steps of an embodiment of the method for optimizing the use of space resources in low-Earth orbit communication satellite space service software.

[0046] Figure 2 A flowchart illustrating the adaptive scheduling measures of the optimization method for space resource utilization in low-Earth orbit communication satellite space service software according to an embodiment of the present invention;

[0047] Figure 3 This is a flowchart illustrating the steps of constructing a multi-factor model in the optimization method for space resource utilization of low-Earth orbit communication satellite space service software according to an embodiment of the present invention. Detailed Implementation

[0048] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention.

[0049] It should be noted that references to "an embodiment," "embodiment," "example embodiment," etc., in this specification refer to the described embodiment including specific features, structures, or characteristics, but not every embodiment must include these specific features, structures, or characteristics. Furthermore, such expressions do not refer to the same embodiment. Moreover, when describing specific features, structures, or characteristics in conjunction with embodiments, whether or not explicitly described, it is indicated that incorporating such features, structures, or characteristics into other embodiments is within the knowledge of those skilled in the art.

[0050] Furthermore, certain terms are used in the specification and subsequent claims to refer to specific components or parts. Those skilled in the art will understand that manufacturers may use different names or terms to refer to the same component or part. This specification and subsequent claims do not distinguish components or parts by differences in name, but rather by differences in function. The terms "comprising" and "including" used throughout the specification and subsequent claims are open-ended and should be interpreted as "including but not limited to." Additionally, the term "connection" here includes any direct and indirect electrical connection means. Indirect electrical connection means include connections made through other means.

[0051] Figure 1 This invention illustrates an embodiment of an optimization method for space resource utilization in low-Earth orbit communication satellite operational software. This optimization method, geared towards ground-based communication satellite operational software, constructs a multi-element model of a functional membrane and adaptively schedules the software's functional modules based on this model. This maximizes the efficiency of space storage resource utilization, providing a strong guarantee for ensuring stable and reliable software operation. The optimization method of this embodiment includes the following steps:

[0052] S101: Establish a multi-element model of the functional modules of the low-Earth orbit communication satellite operation software. This model includes the operating mode, spatial characteristic elements, key attribute elements, and control switch elements corresponding to each functional module. The spatial characteristic elements represent the space resources occupied by important parameters used by the functional module and its sub-modules during operation. The key attribute elements represent the preset critical level of the functional module, and the control switch elements represent the enabled or disabled attribute states of the functional module. Since the low-Earth orbit communication satellite operation software consists of multiple functional modules, it is necessary to first divide the functional modules and then construct the multi-element model based on these modules to provide a foundation for adaptive scheduling measures in the future.

[0053] like Figure 3 As shown, step S101 specifically includes:

[0054] S111: Based on the mission requirements of the low-Earth orbit (LEO) communication satellite maintenance software, the various functional modules of the LEO communication satellite maintenance software are defined. This step specifically involves identifying and organizing the functional modules of the LEO communication satellite maintenance software; that is, based on the mission requirements of the LEO communication satellite maintenance software, the functional characteristics of the LEO communication satellite maintenance software are organized to define and determine the various functional modules of the software; in this embodiment, let the i-th functional module be F. i Then F i = <M i S i C i K i >; where i = 1, 2, ..., n; n ≥ 1, and n is the total number of functional modules of the software.

[0055] M in the above formula i For functional module F i Corresponding operating mode; S i For functional module F i The spatial characteristics of the important parameters used in the process; C i For functional module F i Corresponding key attribute elements; K i For functional module F i The corresponding control switch elements.

[0056] The software functional modules in this embodiment include, but are not limited to: telemetry module, remote control module, energy autonomous management module, thermal control autonomous management module, fault autonomous management module, programmable control management module, load autonomous management module, bus management module, time management module, and on-orbit maintenance module.

[0057] Each of the above functional modules F i It may consist of several sub-functional modules, specifically represented as F i ={F is-1 F is-2 , ...F is-m}, where F is-j Indicates functional module F i One of the sub-functions (j = 1, ..., m. m ≥ 1 represents function F) i The number of sub-functional modules contained therein.

[0058] S112: Establish at least one operating mode associated with each functional module. That is, each functional module is associated with at least one operating mode, and the functional module can be executed in a single operating mode or in multiple operating modes.

[0059] In specific implementation, step S112 includes: determining the operating mode associated with each functional module based on the mission allocation of the low-Earth orbit communication satellite and the execution timing of each functional module; and constructing a mapping matrix between each functional module and its operating mode. That is, in this step, it is necessary to combine the mission allocation of the low-Earth orbit communication satellite and the execution timing of each functional module to determine the operating mode associated with each functional module in the low-Earth orbit communication satellite's satellite management software; referring to the above example, using M... i Indicates functional module F i Corresponding operating modes; each functional module F i It can belong to multiple operating modes and can be executed in multiple operating modes; therefore, functional module F i The corresponding operating mode M i Represented as: M i ={M i-1 M i-2 ,……M i-m}(j=1,…m。m≥1 represents function F) i (Number of corresponding operating modes).

[0060] The mapping matrix between all functional modules F and operating modes M in this embodiment can be represented as follows:

[0061]

[0062] In this matrix, each mapping element a ij (i = 1, 2, ..., n, n ≥ 1 represents the total number of functional modules in the software; j = 1, ..., m, m ≥ 1 represents the number of operating modes in the software) has a first value and a second value. Let the first value be 1 and the second value be 0; then 0 represents operating mode M. i The F module is not included. j Conversely, 1 indicates operating mode M. i Includes functional module F j The established mapping matrix can then be used to quickly query functional modules operating under specific operating modes in subsequent operations.

[0063] S113: Construct the spatial characteristic elements corresponding to each functional module. Spatial characteristic elements refer to the space resources occupied by the important parameters used by each functional module and sub-functional module in the low-Earth orbit communication satellite operation software during operation, which can be quantitatively described.

[0064] Considering each functional module F i It also consists of several sub-functional modules, so it is necessary to first determine the functional module F. iThe spatial characteristic sub-elements associated with each sub-functional module; in specific implementation, step S113 includes: analyzing and determining the spatial resources occupied by the important parameters used by the sub-functional modules corresponding to each functional module, and obtaining the spatial characteristic sub-elements associated with each sub-functional module; taking the set of spatial characteristic elements composed of the spatial characteristic sub-elements of each sub-functional module of the functional module as the spatial characteristic element corresponding to the functional module.

[0065] Each sub-functional module F is-j Only one spatial characteristic element S is associated. is-j (j = 1, ..., m. m ≥ 1 indicates function F) i (Number of sub-functional modules contained). Functional module F i Spatial characteristic elements S is-j Ultimately, this is reflected in the various sub-functions F it contains. is-j The associated spatial characteristic element S is-j , by S is-j Composition of functional module F i The set of all spatial characteristic elements can be represented as: S i ={S is-1 S is -2, ... S is-m}; For spatial characteristic element S i and S is-j It is necessary to statistically analyze and quantify the functional module or its sub-functional modules at the object code level, with the unit being bytes.

[0066] S114: Construct the key attribute elements corresponding to each functional module.

[0067] Specifically, step S114 includes: determining the critical level of each functional module in the low-Earth orbit communication satellite's satellite operation software based on the mission allocation and system risk analysis; and obtaining a quantitative representation of the critical level as the key attribute element of the corresponding functional module. That is, in this step S114, it is necessary to combine the mission allocation and system risk analysis of the low-Earth orbit communication satellite to determine the critical level of each functional module in the low-Earth orbit communication satellite's satellite operation software, and to quantitatively represent the critical level.

[0068] Considering each functional module F i It also consists of several sub-functions, and it is necessary to first derive each sub-function F. is-j The associated key attribute element C is-j Each sub-function F is-j Associate only one key attribute element C is-j (j = 1, ..., m. m ≥ 1 indicates function F) i (Number of sub-functional modules contained); Functional module F iKey attribute element C i Ultimately, this is reflected in the various sub-functions F it contains. is-j The associated key attribute element C is-j , by C is-j Composition of functional module F i The set of all key attribute elements can be represented as:

[0069] C i ={C is-1 C is -2, ... C is-m};

[0070] For key attribute element C i And C is-j The construction of this system requires quantitative modeling based on the impact of this functional module on the low-Earth orbit communication satellite's operational software.

[0071] This embodiment uses the numbers "1, 2, 3" to quantitatively represent key attribute elements. The specific definitions and descriptions are shown in the table below:

[0072]

[0073]

[0074] In this embodiment, it is stipulated that the key attribute elements corresponding to all sub-functional modules in a functional module have the same magnitude, that is, they have the same key attribute elements.

[0075] S115: Construct the control switch elements corresponding to each functional module. The control switch elements designed in this step are used to automatically enable and disable the various functional modules and sub-functional modules in the low-Earth orbit communication satellite service software; that is, the control switch elements of a functional module include the main control switch elements of the functional module itself and the control switch sub-elements corresponding to each sub-functional module of the functional module.

[0076] Functional module F i It has a unique control switch element K i This control switch element has two attribute states: representing functional module F respectively. i Enable, Functional Module F i Prohibited. Functional module F i The various sub-functions F included is-j (j = 1, ..., m, where m ≥ 1 represents the number of sub-functional modules contained), which also corresponds to a unique control switch element K. is-j The control switch element corresponding to this sub-functional module also has two states: representing the sub-functional module F respectively. is-j Enable, sub-functional module F is-jprohibit.

[0077] S102: Calculate the important parameter of space resources used by the low-Earth orbit communication satellite maintenance software. Before this step, an alarm threshold for space resource usage of the low-Earth orbit communication satellite maintenance software can be designed. For example, based on the operational requirements of the low-Earth orbit communication satellite maintenance software, an alarm threshold S for space resource usage during operation can be designed. threashold The unit is bytes.

[0078] During software operation, if the actual space resources used are close to or exceed S threashold Subsequently, this may cause system problems and affect the stable operation of the software. Therefore, it is necessary to calculate the important parameter of space resources used by the low-Earth orbit communication satellite service software, and then correlate it with the space resource usage alarm threshold S. threashold The comparison is used to determine whether the software's operation has been affected.

[0079] In specific implementation, step S102 includes: based on the spatial characteristic elements of each functional module in the multi-factor model, calculating the important parameter space resources occupied by each running functional module. This embodiment uses S... now The space resources, representing an important parameter used by the low-Earth orbit communication satellite's operational software, are determined based on the space characteristic elements of each functional module constructed in the aforementioned example. now It can be represented as: S now = (S1+S2+……+S n (i = 1, 2, ..., n. n represents the total number of functional modules).

[0080] S103: If the important parameter of space resources is not less than the space resource usage alarm threshold preset by the low-Earth orbit communication satellite service software, then adaptive scheduling measures are executed based on the multi-factor model; if S now threashold If the signal is positive, it indicates that the low-Earth orbit communication satellite's operational software is running stably and no further action is required; conversely, if the signal is negative... now ≥S threashold This indicates that the actual space resources used by the current low-Earth orbit communication satellite service software are approaching or exceeding the alarm threshold S. threashold This may affect the normal operation of the software, and scheduling strategies need to be implemented as soon as possible to prohibit or shut down some functional modules or sub-functional modules in order to reduce the space resources actually used by the low-orbit communication satellite service software.

[0081] like Figure 2 As shown, the adaptive scheduling measures in this embodiment include:

[0082] ​S1: Query the first functional module that is in operation and has the same operating mode as the current software through a multi-factor model. Specifically, step S1 includes: querying the current software's operating mode and the corresponding mapping element in the mapping relationship matrix; traversing the queried mapping elements to identify the first functional module in operation. Further, querying the current software's operating mode and the corresponding mapping element in the mapping relationship matrix includes: determining the current software's operating mode and querying the mapping element corresponding to the current software's operating mode from the mapping relationship matrix; the mapping element includes a first value and a second value, where the first value and the second value respectively represent whether the corresponding functional module is in operation or not; traversing the queried mapping elements to identify the first functional module in operation includes: traversing the queried mapping elements to identify the target mapping element with the first value, and determining the functional module corresponding to the target mapping element as the first functional module. That is, combining the aforementioned example of the mapping relationship matrix, in this step S1, specifically, the current software's operating mode M is queried... i and the corresponding mapping element a in mapping matrix A. ij Iterate through the values ​​of a that are 1. ij (i.e., current operating mode M) i (A certain function is currently running), and the corresponding first functional module is selected.

[0083] S2: Based on the aforementioned key attribute elements, a second functional module with the lowest preset key level is selected from a plurality of first functional modules. That is, this step further selects the second functional module with the lowest priority from a plurality of first functional modules; in conjunction with the foregoing, among the selected plurality of first functional modules, the functional module with the lowest key attribute element is selected according to the pre-established key attribute elements of each functional module; specifically, in this embodiment, key attribute element C is selected from the first functional modules. i =1 functional module F i (i = 1, 2, ..., n) serve as the second functional module to proceed to step S3 and perform subsequent operations.

[0084] S3: Iterate through and select the target sub-functional modules of the second functional module, and adjust the control switch elements corresponding to the target sub-functional modules to the disabled state; specifically, iterate through the second functional module F i Sub-functional module F is-1 Select F in sequence is-1 , select F is-1 The control switch element that was constructed was adjusted to "disable", that is, the corresponding sub-functional module F is-1 Disabled; the sub-functional module F is-1When the control switch element is set to the disabled state, the sub-function module F will be automatically shut down. is-1 The operation of this mechanism is intended to free up important parameter space resources.

[0085] S4: Update the spatial characteristic elements of the second functional module and recalculate the important parameter spatial resources; that is, recalculate the spatial resources in the prohibited sub-functional module F. is-1 Subsequently, the key parameters actually used in the latest low-Earth orbit communication satellite satellite management software are space resources: S now = (S1 + ... + S) n -S is-1 (i = 1, 2, ..., n. n represents the total number of functional modules); then, the recalculated important parameter resources are compared again with the space resource usage alarm threshold. If S now ' threashold This explains the sub-function F. is-1 After implementing a "prohibition" type scheduling operation, the space resources, a crucial parameter actually used by the current low-Earth orbit communication satellite's space management software, will be less than the alarm threshold. This ensures normal software space resource usage and allows for normal operation, ending the process. Otherwise, proceed to step S5 for further adjustments.

[0086] S5: If the updated critical parameter "space resources" is not less than the space resource usage alarm threshold, then return to repeat steps S1 to S4 until the critical parameter "space resources" is less than the space resource usage alarm threshold. If S5 remains unchanged... now '≥S threashold Then continue to select the second functional module F. i Sub-functional module F is-1 (j=2…m), and continue to execute steps S1~S4, if the previously selected second functional module F i It also has other sub-functional modules F is-1 If the enabled state is maintained, there is no need to enter step S1; simply proceed to step S3 to continue execution. That is, by returning to the loop, the aforementioned steps are executed to continue traversing the newly traversed sub-functional modules F. is-1 The control switch element is adjusted to the disabled state; if the execution reaches F i A certain sub-function F is-j After (j=2…m) is closed, it can satisfy S now ' threashold This means that you only need to enable the current function F. i After performing a "disable" scheduling operation on several sub-functions, the software can operate normally and the process will end when the actual space resource used is less than the space resource alarm threshold.

[0087] Correspondingly, if the currently selected second functional module F​​i Even after disabling all sub-functional modules, S still cannot be satisfied. now ' threashold Then continue at the lowest preset critical level (i.e., C). i =1) Iterate through the functional modules to select the next second functional module F. i (i = 2…n), and repeat the above operation. If the execution reaches a certain second functional module F, i (i = 2…n) and its corresponding sub-functional module F is-1 (j = 1, ..., m. m ≥ 1 indicates function F) i When the number of sub-functional modules contained is ( ), it can satisfy S now ' threashold This means that only the key attribute elements with the lowest values ​​(i.e., C) need to be minimized. i =1) Several second functional modules F1 to F1 in the layer i and the current F i Some sub-functions in F (traversing to F) is-j After implementing the "disable" scheduling operation, the actual usage of important parameter space resources will be less than the alarm threshold, software resource usage will return to normal, and the process execution will end.

[0088] Conversely, if each of the second functional modules F i All control switch elements are adjusted to the disabled state, and the updated important parameter, space resource, is still not less than the space resource usage alarm threshold, meaning it still cannot meet S. now ' threashold Then, based on key attribute elements, a third functional module that is one level above the preset key level is selected from several first functional modules; wherein, the preset key level above the preset key level refers to the priority level above the lowest preset key level; the second functional module in steps S3 to S5 is replaced based on the selected third functional module, and steps S3 to S5 are repeated until the important parameter space resource is less than the space resource usage alarm threshold.

[0089] Specifically, when all the second functional modules F i Even after all control switch elements are set to the disabled state, S still cannot be satisfied. now ' threashold This further increases the screening level of key attribute elements (i.e., C). i =2), traverse and select the third functional module F from this key attribute element. i And repeat the operations similar to those in steps S3 to S5 until a certain functional module F is executed. i (i = r, ..., n. r is C) i ​​​​= the number of the first function in the function module corresponding to 2, when r < n, where n represents the total number of function modules included), it can satisfy S now '<S threashold , it is necessary to include several third function modules in the key attribute (i.e., C i = 2) (up to F r ) and some sub-function modules in the current F i (traversing to F is-j ). After disabling some sub-functions, it can be ensured that the important parameter space resources actually used currently are less than the alarm threshold, the software resource usage returns to normal, and the process execution ends.

[0090] Since the quantization level of the key attribute elements of the third function module is 2, which belongs to the type that can be prohibited in special cases but should be restored to operation as soon as possible, the control switch elements of the foregoing third function module that are adjusted to the prohibited state need to ensure that S now '<S threashold and then, on the premise of ensuring S now '<S threashold , timely start the "enable" operation of the third function module F i = 2) corresponding to the foregoing prohibited key attribute (i.e., C r -F i (i = r,..., n; r is the number of the first function in the function module corresponding to C i = 2, r < n, n represents the total number of function modules included) and its sub-functions, to avoid the adverse effects caused by the long-term prohibition of these functions on the on-board software.

[0091] The method provided in this embodiment can, when there is insufficient or tight space resources and it is necessary to release space resources, based on the above-mentioned adaptive scheduling measures, traverse each function under the operation mode matrix A according to the current operation mode of the software. If the function is in the running state, then according to its key attribute, the function with the lowest priority is closed to release the space resources it occupies, and then continue to make judgments and corresponding processing. In this way, this embodiment can, on the premise of ensuring the stable operation of the on-board software functions of the low-earth orbit communication satellite,尽可能降低星务软件运行的空间资源负载,达到对系统设计优化的目的。

[0092] It should be noted that there is an error in the original Chinese text. The part "尽可能降低星务软件运行的空间资源负载,达到对系统设计优化的目的。" in the English translation should be "minimize the space resource load during the operation of the on-board software and achieve the purpose of optimizing the system design." for a more accurate translation. But according to the requirements, the above translation is presented as is.It should be noted that this application can be implemented in software and / or a combination of software and hardware, for example, using an application-specific integrated circuit (ASIC), a general-purpose computer, or any other similar hardware device. In one embodiment, the software program of this application can be executed by a processor to implement the steps or functions described above. Similarly, the software program of this application (including related data structures) can be stored in a computer-readable recording medium, such as RAM memory, magnetic or optical drives, floppy disks, and similar devices. Furthermore, some steps or functions of this application can be implemented in hardware, for example, as circuitry that works with a processor to perform the various steps or functions.

[0093] The method according to the invention can be implemented on a computer as a computer-implemented method, or in dedicated hardware, or a combination of both. Executable code or portions thereof for the method according to the invention can be stored on a computer program product. Examples of computer program products include memory devices, optical storage devices, integrated circuits, servers, online software, etc. Preferably, the computer program product includes non-transitory program code components stored on a computer-readable medium so as to execute the method according to the invention when the program product is executed on a computer.

[0094] In a preferred embodiment, the computer program includes computer program code components adapted to perform all the steps of the method according to the invention when the computer program is run on a computer. Preferably, the computer program is embodied on a computer-readable medium.

[0095] In summary, the optimization method for space resource utilization of low-Earth orbit (LEO) communication satellite satellite management software described in this invention establishes a multi-element model for the functional modules of LEO communication satellite management software, including elements such as operating mode, space characteristics, key attributes, and control switch attributes. It proposes a space resource optimization method for LEO communication satellite management software based on this multi-element model, which can adaptively schedule functional modules based on the software operating mode, combined with the key attributes of the functional modules, and according to the dynamic and important parameter of space resource utilization, thereby optimizing the hardware storage of the satellite management software.

[0096] Of course, the present invention may have other various embodiments. Without departing from the spirit and essence of the present invention, those skilled in the art can make various corresponding changes and modifications according to the present invention, but these corresponding changes and modifications should all fall within the protection scope of the appended claims.

Claims

1. A method for optimizing space resource usage of on-board software of a low earth orbiting communication satellite, characterized in that, The method comprises the following steps: establishing a multi-element model of a function module of a low-orbit communication satellite on-board software, wherein the multi-element model is configured with a running mode, a space characteristic element, a key attribute element and a control switch element corresponding to each function module; the space characteristic element is a space resource occupied by important parameters used by the function module and its sub-function module during running; the key attribute element represents a preset key level corresponding to the function module; and the control switch element represents an enabling attribute state or a prohibited attribute state corresponding to the function module; calculating a space resource of important parameters used by the low-orbit communication satellite on-board software; if the space resource of important parameters is not less than a preset space resource use alarm threshold of the low-orbit communication satellite on-board software, performing an adaptive scheduling measure based on the multi-element model; the adaptive scheduling measure comprises the following steps: S1, querying a first function module in an operating state and having the same operating mode as a current software through the multi-element model; S2, selecting a second function module having the lowest preset key level from the first function modules based on the key attribute element; S3, selecting a target sub-function module of the second function module, and adjusting a control switch element corresponding to the target sub-function module to a prohibited state; S4, updating the space characteristic element of the second function module, and recalculating the space resource of important parameters; S5, if the updated space resource of important parameters is not less than the space resource use alarm threshold, returning to repeat steps S1-S4 until the space resource of important parameters is less than the space resource use alarm threshold.

2. The method for optimizing the space resource usage of the on-board software of a low earth orbit communication satellite according to claim 1, characterized in that, The adaptive scheduling measure further comprises the following steps: if the control switch elements of each second function module are all adjusted to the prohibited state, and the updated space resource of important parameters is still not less than the space resource use alarm threshold, selecting a third function module having a next level of the preset key level from the first function modules based on the key attribute element; wherein the next level of the preset key level refers to a next priority level compared to the lowest level of the preset key level; repeating steps S3-S5 based on the selected third function module replacing the second function module in steps S3-S5 until the space resource of important parameters is less than the space resource use alarm threshold.

3. The method for optimizing the use of space resources in low-Earth orbit communication satellite space service software according to claim 1, characterized in that, The method of establishing the multi-element model of the function module of the low-orbit communication satellite on-board software comprises the following steps: determining each function module of the low-orbit communication satellite on-board software according to a task requirement of the low-orbit communication satellite on-board software; establishing at least one running mode associated with each function module; constructing the space characteristic element corresponding to each function module; constructing the key attribute element corresponding to each function module; constructing the control switch element corresponding to each function module.

4. The method for optimizing the space resource usage of the on-board software of a low earth orbiting communication satellite according to claim 3, characterized in that, The method of establishing at least one running mode associated with each function module comprises the following steps: According to the task division of the low-orbit communication satellite and the execution time of each function module, at least one operation mode associated with each function module is determined; A mapping relationship matrix between each function module and the operation mode is constructed.

5. The method for optimizing the use of space resources in low-Earth orbit communication satellite space service software according to claim 3, characterized in that, The construction of the spatial characteristic element corresponding to each function module includes: The spatial resource occupied by the important parameters used by each sub-function module corresponding to each function module is analyzed and determined to obtain the spatial characteristic sub-element associated with each sub-function module; The spatial characteristic sub-element of each sub-function module of the function module is used to form a spatial characteristic element set as the spatial characteristic element corresponding to the function module.

6. The method for optimization of space resources usage of LEO communication satellite on-board software according to claim 3, characterized in that, The construction of the key attribute element corresponding to each function module includes: Based on the task division of the low-orbit communication satellite and the system risk analysis, the key level of each function module in the low-orbit communication satellite software is determined; The quantitative representation of the key level is obtained as the key attribute element of the corresponding function module.

7. The method for optimization of space resources usage of LEO communication satellite on-board software according to claim 3, characterized in that, The control switch element of the function module includes the control switch main element of the function module itself and the control switch sub-element corresponding to each sub-function module of the function module.

8. The method for optimization of space resources usage of low earth orbit communication satellite on-board software according to claim 1, characterized in that, The calculation of the important parameter space resource used by the low-orbit communication satellite software includes: According to the spatial characteristic element of each function module in the multi-element model, the important parameter space resource occupied by each running function module is counted.

9. The method for optimization of space resources usage of LEO communication satellite on-board software according to claim 4, characterized in that, The first function module in the operation state and the same operation mode as the current software is queried through the multi-element model includes: The operation mode of the current software and the mapping element corresponding to it in the mapping relationship matrix are queried; The first function module in the running state is traversed from the queried mapping element.

10. The method for optimization of space resources usage of LEO communication satellite on-board software according to claim 9, characterized in that, The operation mode of the current software and the mapping element corresponding to it in the mapping relationship matrix are queried, including: The operation mode of the current software is determined, and the mapping element corresponding to the operation mode of the current software is queried from the mapping relationship matrix; the mapping element includes a first value and a second value, and the first value and the second value respectively represent that the corresponding function module is in an operation state or a non-operation state; The first function module in the running state is traversed from the queried mapping element, including: The target mapping element of the first value is traversed from the queried mapping element, and the function module corresponding to the target mapping element is determined as the first function module.

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