CN117252327A - Method for evaluating elastic capability of space system - Google Patents
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Abstract
The invention relates to an evaluation method of elastic capability of a space system, which comprises the steps of evaluating the elastic capability of the space system from a preventive force dimension, a resistance dimension and a restoring force dimension to obtain an evaluation score corresponding to each dimension; carrying out weighted summation based on the evaluation scores corresponding to each dimension to obtain an elastic capability evaluation total score corresponding to the safety system; the elastic capability of the safety system is evaluated based on the elastic capability evaluation total score, and an elastic capability evaluation result of the space system is obtained, so that the elastic capability of the space system can be evaluated from the preventive force dimension, the resistance dimension and the restoring force latitude system, the evaluation of the elastic capability can be realized, and the evaluation accuracy can be improved.
Description
Technical Field
The invention relates to the technical field of space system elasticity evaluation, in particular to a method for evaluating elasticity of a space system.
Background
The elastic capability of a space system refers to the ability of the space system to continue to provide the desired capability in the face of system failure, environmental challenges, or hostile actions, and is a new concept that has emerged in the aerospace field in recent years. From the perspective of system design, the space system is required to be "flexible", i.e. capable of successfully resisting various types of destructive events and ensuring successful implementation of space domain tasks. And the elasticity of the space system is evaluated, so that the method has important significance for planning and designing the space system and improving the survivability of the space system.
However, for the evaluation of the elastic capacity of the space system, no evaluation method specific to the elastic capacity of the space system has been found.
Disclosure of Invention
First, the technical problem to be solved
In view of the foregoing drawbacks and deficiencies of the prior art, the present invention provides a method for evaluating the elastic capability of a space system, which can implement the evaluation of the elastic capability of the space system.
(II) technical scheme
In order to achieve the above purpose, the main technical scheme adopted by the invention comprises the following steps:
in a first aspect, an embodiment of the present invention provides a method for evaluating elastic capability of a spatial system, including: carrying out elastic capability evaluation on the space system from the preventive force dimension, the resistance dimension and the restoring force dimension to obtain an evaluation score corresponding to each dimension; carrying out weighted summation based on the evaluation scores corresponding to each dimension to obtain an elastic capability evaluation total score corresponding to the safety system; and (5) evaluating the elasticity of the safety system based on the elasticity evaluation total score to obtain an elasticity evaluation result of the space system.
In some possible embodiments, the obtaining the evaluation score corresponding to the preventive force dimension includes: acquiring an evaluation score corresponding to the air conditioner target detection capability, an evaluation score corresponding to the threat warning capability and an evaluation score corresponding to the space environment forecasting capability; and carrying out weighted summation on the evaluation score corresponding to the air conditioner target detection capability, the evaluation score corresponding to the threat warning capability and the evaluation score corresponding to the space environment forecasting capability to obtain the evaluation score corresponding to the preventive dimension.
In some possible embodiments, the process of obtaining the evaluation score corresponding to the air conditioner target detection capability includes: acquiring a space target catalogue, a ground radar scanning period and a detection precision value; and carrying out weighted summation on the space target catalogue, the ground radar scanning period and the detection precision value to obtain an evaluation score corresponding to the air conditioner target detection capability.
In some possible embodiments, the process of obtaining the evaluation score corresponding to the threat alert capability includes: acquiring collision early-warning time and collision early-warning distance; and carrying out weighted summation on the collision early-warning time and the collision early-warning distance to obtain an evaluation score corresponding to the threat warning capability.
In some possible embodiments, the process of obtaining the evaluation score corresponding to the spatial environment forecasting capability includes: acquiring solar flare forecasting time and solar wind forecasting time; and carrying out weighted summation on the solar flare forecasting time and the solar wind forecasting time to obtain an evaluation score corresponding to the space environment forecasting capability.
In some possible embodiments, the obtaining the evaluation score corresponding to the resistance dimension includes: acquiring a space protection capability evaluation score and a space system protection capability evaluation score; and carrying out weighted summation on the space protection capability evaluation score and the space system protection capability evaluation score to obtain an evaluation score corresponding to the resistance dimension.
In some possible embodiments, the obtaining of the spatial protection capability assessment score includes: acquiring a maneuvering performance evaluation score, a photoelectric countermeasure protection capability evaluation score, a satellite reinforcement performance evaluation score and a satellite hiding capability evaluation score; and carrying out weighted summation on the maneuvering performance evaluation score, the photoelectric countermeasure protection capability evaluation score, the satellite reinforcement performance evaluation score and the satellite hiding capability evaluation score to obtain a space protection capability evaluation score.
In some possible embodiments, the obtaining of the spatial system protection capability assessment score includes: acquiring the number of backup satellites and the number of information links; and carrying out weighted summation on the number of the backup satellites and the number of the information links to obtain a space system protection capability evaluation score.
In some possible embodiments, the obtaining the evaluation score corresponding to the restoring force dimension includes: acquiring an evaluation score of the quick response transmitting capability and an evaluation score corresponding to the space maintenance capability; and carrying out weighted summation on the evaluation score of the quick response transmitting capacity and the evaluation score corresponding to the space maintenance capacity to obtain the evaluation score corresponding to the restoring force dimension.
In some possible embodiments, the acquiring of the evaluation score of the quick response transmitting capability includes: acquiring a quick response transmitting period and a microsatellite production period; and carrying out weighted summation on the quick response emission period and the microsatellite production period to obtain an evaluation score of the quick response emission capability.
In some possible embodiments, the obtaining the evaluation score corresponding to the space maintenance capability includes: acquiring an evaluation score corresponding to an on-orbit repair period and a function recovery level; and carrying out weighted summation on the evaluation scores corresponding to the on-orbit repair period and the functional recovery level to obtain the evaluation score corresponding to the space maintenance capability.
In a second aspect, embodiments of the present application provide a storage medium having stored thereon a computer program which, when executed by a processor, performs the method of the first aspect or any alternative implementation of the first aspect.
In a third aspect, an embodiment of the present application provides an electronic device, including: a processor, a memory and a bus, the memory storing machine-readable instructions executable by the processor, the processor and the memory in communication via the bus when the electronic device is running, the machine-readable instructions when executed by the processor performing the method of the first aspect or any alternative implementation of the first aspect.
In a fourth aspect, the present application provides a computer program product which, when run on a computer, causes the computer to perform the method of the first aspect or any of the possible implementations of the first aspect.
(III) beneficial effects
The beneficial effects of the invention are as follows:
the invention provides a method for evaluating the elastic capability of a space system, which evaluates the elastic capability of the space system from a preventive force dimension, a resistance dimension and a restoring force latitude system, so that the evaluation of the elastic capability can be realized, and the accuracy of the evaluation can be improved.
In order to make the above objects, features and advantages of the embodiments of the present application more comprehensible, preferred embodiments accompanied with figures are described in detail below.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments of the present application will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present application and should not be considered as limiting the scope, and other related drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of an evaluation index system for elastic capability of a spatial system according to an embodiment of the present application;
fig. 2 shows a flowchart of a method for evaluating elastic capability of a spatial system according to an embodiment of the present application.
Detailed Description
The invention will be better explained by the following detailed description of the embodiments with reference to the drawings.
In order to realize the assessment of the elastic capability of the space system, the embodiment of the invention provides an assessment method of the elastic capability of the space system, which is characterized in that the elastic capability assessment of the space system is carried out from a preventive dimension, a resistance dimension and a restoring force dimension to obtain an assessment score corresponding to each dimension, the weighted summation is calculated and weighted summation is carried out based on the assessment score corresponding to each dimension to obtain an elastic capability assessment total score corresponding to the space system, and the elastic capability of the space system is assessed based on the elastic capability assessment total score to obtain an elastic capability assessment result of the space system, so that the assessment of the elastic capability of the space system can be effectively and accurately realized.
In order that the above-described aspects may be better understood, exemplary embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present invention are shown in the drawings, it should be understood that the present invention may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.
In order to facilitate understanding of the embodiments of the present application, some terms related to the embodiments of the present application are explained as follows:
preventive force ": it means that the system should be protected before destructive events occur, estimating the losses that may occur. Preventive forces are the ability of the system to perceive destructive events that have not yet occurred.
It should be understood that the evaluation index included in the preventive force may be set according to the actual requirement, and the embodiment of the present application is not limited thereto.
For example, the preventive measures include spatial target monitoring capability, threat alert capability, and spatial environment forecasting capability. The space target monitoring capability refers to the capability of monitoring, tracking and measuring a space target (such as space debris and the like); threat alarming capability refers to the capability of carrying out pre-judging analysis on potential threats and giving out alarms; spatial environment forecasting capability refers to the perceived forecasting capability of spatial environmental events (such as solar storms, electromagnetic storms, etc.).
It should also be understood that the evaluation index included in the space target monitoring capability may be set according to the actual requirement, and the embodiment of the present application is not limited thereto.
For example, the spatial target monitoring capability includes evaluation indexes including spatial target inventory, ground radar scan period, and detection accuracy. Wherein, the space target cataloging refers to the maximum cataloging number of the space targets through a ground or space-based sensor; the ground radar scanning period refers to the minimum "revisit" interval time for a space target; the detection accuracy refers to the resolution of the sensor.
Here, the detection accuracy may be obtained by weighted summation of resolutions of all sensors in the spatial system. Correspondingly, other similar indexes can be obtained by weighting and summing a plurality of corresponding data in the system, and the following description is omitted.
It should also be understood that the evaluation index included in the threat alert capability may also be set according to actual requirements, and embodiments of the present application are not limited thereto.
For example, the threat alert capability includes an evaluation index including a collision pre-warning time and a collision pre-warning distance. The collision early warning time is the longest collision time forecast provided for the in-orbit satellite in a space-based and foundation observation mode; the collision early warning distance refers to the distance from the farthest target of the specific in-orbit satellite, which can be sensed by the space-based sensor and the foundation sensor.
It should also be understood that the evaluation index included in the spatial environment prediction capability may also be set according to the actual requirement, and the embodiment of the present application is not limited thereto.
For example, the evaluation index included in the spatial environment prediction capability includes solar flare prediction and solar wind prediction. Wherein, the solar flare forecast refers to the shortest solar flare forecast time; the solar wind forecast refers to the shortest solar wind forecast time.
"resistance": it means that during the destructive event, the system should resist, absorb or transform the destructive action as much as possible, reducing the loss of the system. Resistance is the ability of the system to minimize the loss of the system to the damaging event that is occurring.
It should also be understood that the evaluation index included in the resistance may also be set according to the actual requirement, and the embodiment of the present application is not limited thereto.
For example, the evaluation index included in the resistance includes a space system protection capability and a space system task assurance capability. The protection capability of the space system refers to the self-protection capability of the space system in response to external destructive events; the task assurance capability of a space system refers to the capability of the space system to still complete mission tasks under the action of various destructive events that may occur.
It should also be understood that the evaluation index included in the protection capability of the space system may also be set according to the actual requirement, and the embodiment of the present application is not limited thereto.
For example, the evaluation index included in the protection capability of the space system includes maneuvering capability, photoelectric countermeasure protection capability, satellite reinforcement capability and satellite hiding capability. Wherein, the maneuvering performance refers to the speed of adjusting the gesture and orbit of the satellite so as to avoid the attack of an enemy anti-satellite weapon or the impact of space debris; the photoelectric countermeasure protection capability refers to the capability of operating photoelectric countermeasure protection to prevent the on-board photoelectric equipment from being damaged; the satellite reinforcement performance refers to the ability to prevent high-altitude nuclear explosions from damaging satellites and on-board equipment; satellite hiding capability refers to the ability to make it difficult for an adversary to discover, identify, track, and attack by camouflage or stealth.
It should also be understood that the evaluation index included in the task assurance capability of the spatial system may also be set according to the actual requirement, and the embodiment of the present application is not limited thereto.
For example, the evaluation index included in the task assurance capability of the space system includes the number of backup satellites and the number of information links. The number of the backup satellites is that in order to prevent unexpected failure of a certain satellite or a plurality of satellites in a satellite constellation, the supplementary redundant in-orbit satellites are in a standby state at ordinary times and are activated for use after the normal operation satellites fail; the number of information links refers to a number of information channels constructed in the terrestrial network formed between a plurality of satellites and the ground station in order to avoid failure of the primary terrestrial communication link.
Restoring force ": after the system suffers from destructive event, the system takes measures to recover from the lost state as soon as possible, so as to ensure the smooth realization of the system function. Restoring force is the ability of a system to quickly restore system functionality after experiencing a destructive event.
It should also be understood that the evaluation index included in the restoring force may also be set according to the actual requirement, and the embodiment of the present application is not limited thereto.
For example, the evaluation index included in the restoring force includes a quick response transmitting capability and a space maintenance capability. The quick response transmitting capability refers to the capability of organizing the power of each party to quickly transmit the satellite after receiving the satellite transmitting task instruction; space maintenance capability refers to the ability of a space system to perform on-orbit repair and routine maintenance.
It should also be understood that the evaluation index included in the fast response transmitting capability may also be set according to the actual requirement, and the embodiment of the present application is not limited thereto.
For example, the evaluation index included in the quick response transmitting capability includes a quick response transmitting period and a micro satellite production period. Wherein, the rapid response launch cycle refers to the minimum time required for a launch vehicle for rapid response launch from preparation to launch; the production cycle of a microsatellite refers to the minimum time required to produce a microsatellite for transmission using commercial off-the-shelf products according to satellite functionality requirements.
It should also be understood that the evaluation index included in the space maintenance capability may also be set according to the actual requirement, and the embodiment of the present application is not limited thereto.
For example, the evaluation index included in the space maintenance capability includes an on-orbit repair cycle and a functional recovery level. The on-orbit repair period refers to the time required by repairing the satellite functions or filling the on-orbit fuel and the like by adopting an on-orbit maintenance aircraft; the level of functional recovery refers to the percentage of damaged satellites that are recovered to be before damage by a space maintenance operation.
It should be noted that, considering that the space system construction and operation process must take into account the capabilities of preventing force, resistance force and restoring force, the elastic capability assessment of the space system can be performed from the preventing force dimension, the resistance force dimension and the restoring force dimension, and the specific description can be seen below.
Referring to fig. 1, fig. 1 is a schematic diagram illustrating an evaluation index system for elastic capability of a spatial system according to an embodiment of the present application. As shown in fig. 1, in the process of establishing the evaluation index system, evaluation can be performed from three dimensions, namely, a preventive dimension, a resistive dimension and a restoring dimension, and the secondary evaluation index and the tertiary evaluation index corresponding to each dimension can be referred to in fig. 1, which will not be described in detail herein.
Referring to fig. 2, fig. 2 is a flowchart illustrating a method for evaluating elastic capability of a space system according to an embodiment of the present application. The evaluation method shown in fig. 2 may be performed by an evaluation device of the elastic capability of the space system, and a specific device of the evaluation device may be set according to actual requirements, and the embodiment of the present application is not limited thereto. For example, the evaluation device may be a computer, a server, or the like, and the embodiment of the present application is not limited thereto. As shown in fig. 2, the evaluation method includes:
step S210, elastic capability evaluation is carried out on the space system from the preventive force dimension, the resistive force dimension and the restoring force dimension, and an evaluation score corresponding to each dimension is obtained.
It should be understood that the process of obtaining the evaluation score corresponding to the preventive force dimension may be set according to actual requirements, and the embodiment of the application is not limited thereto.
Optionally, acquiring an evaluation score corresponding to the air conditioner target detection capability, an evaluation score corresponding to the threat alert capability and an evaluation score corresponding to the space environment forecasting capability; and carrying out weighted summation on the evaluation score corresponding to the air conditioner target detection capability, the evaluation score corresponding to the threat warning capability and the evaluation score corresponding to the space environment forecasting capability to obtain the evaluation score corresponding to the preventive dimension.
Here, it should be noted that, the specific weight of the evaluation score corresponding to the air conditioner target detection capability, the specific weight of the evaluation score corresponding to the threat alert capability, and the specific weight of the evaluation score corresponding to the space environment forecasting capability may be set according to the actual requirement, so long as the sum of the weights of the three weights is guaranteed to be 1, and the embodiment of the present application is not limited thereto.
Correspondingly, the specific weights of other data in the present application are similar, and will not be described in detail later, see the relevant description above.
And the process for acquiring the evaluation score corresponding to the air conditioner target detection capability comprises the following steps: acquiring the inventory number of space targets, the ground radar scanning period and the detection precision value; and carrying out weighted summation on the space target catalogue, the ground radar scanning period and the detection precision value to obtain an evaluation score corresponding to the air conditioner target detection capability.
The method is characterized in that the space target cataloging number is the number of the space targets which can be monitored by the space monitoring system after detecting, tracking and monitoring all the space targets and acquiring target track parameters is processed; the ground radar scanning period refers to the time required by the ground radar and other equipment to scan the detectable airspace; the detection accuracy value is generally a measurable parameter for evaluating the accuracy of the detection accuracy value according to the acquired target detection data. The parameter value obtaining process can be set according to actual requirements, and the embodiment of the application is not limited thereto.
And the acquiring process of the evaluation score corresponding to the threat alert capability comprises the following steps: acquiring collision early-warning time and collision early-warning distance; and carrying out weighted summation on the collision early-warning time and the collision early-warning distance to obtain an evaluation score corresponding to the threat warning capability.
The time of collision early warning refers to the time when the analyzed collision event is possible to occur by using the existing monitoring data; the collision early warning distance is the minimum distance of the space target collision obtained by calculation and analysis based on the existing monitoring data. The parameter obtaining process can be set according to actual requirements, and the embodiment of the application is not limited thereto.
And the process for obtaining the evaluation score corresponding to the space environment forecasting capability comprises the following steps: acquiring solar flare forecasting time and solar wind forecasting time; and carrying out weighted summation on the solar flare forecasting time and the solar wind forecasting time to obtain an evaluation score corresponding to the space environment forecasting capability.
The solar flare forecasting time refers to the time and intensity of solar flare forecasting estimated by using monitoring information obtained by solar monitoring equipment; the solar wind forecast time refers to the time when solar wind forecast occurs estimated by using monitoring information acquired by solar monitoring equipment. The above-mentioned parameter obtaining process can be set according to actual requirements, and the embodiment of the application is not limited thereto.
It should also be understood that the process of obtaining the evaluation score corresponding to the resistance dimension may be set according to actual requirements, and the embodiment of the application is not limited thereto.
Optionally, the process of obtaining the evaluation score corresponding to the resistance dimension includes: acquiring a space protection capability evaluation score and a space system protection capability evaluation score; and carrying out weighted summation on the space protection capability evaluation score and the space system protection capability evaluation score to obtain an evaluation score corresponding to the resistance dimension.
And, the spatial protection capability assessment score includes: acquiring a maneuvering performance evaluation score, a photoelectric countermeasure protection capability evaluation score, a satellite reinforcement performance evaluation score and a satellite hiding capability evaluation score; and carrying out weighted summation on the maneuvering performance evaluation score, the photoelectric countermeasure protection capability evaluation score, the satellite reinforcement performance evaluation score and the satellite hiding capability evaluation score to obtain a space protection capability evaluation score.
The maneuvering performance refers to the capability of a space system for carrying a certain propellant for orbital maneuver in order to ensure self safety, and can be comprehensively determined by propellant quality and thruster performance indexes; the photoelectric countermeasure protection capability refers to a protection means which can attack or cope when the space system performs space countermeasure, and is generally determined according to the type of photoelectric protection carried by the space system, index parameters and residual available energy; the satellite reinforcement performance refers to the capability of a space system for strengthening the system performance and ensuring the task completion, and is generally comprehensively evaluated according to the material and structure conditions of the space system and the evaluation of a system user; satellite hiding capability refers to the capability of a space system to hide loads or states when encountering dangerous or mission requirements, and is generally determined according to space system load parameters and satellite orbit attitude adjustment capability.
The parameter obtaining process can be set according to actual requirements, and the embodiment of the application is not limited thereto.
For example, the maneuver performance assessment score may be obtained by an expert system or by weighted summation of related assessment parameters.
Correspondingly, the calculation process of other data is similar, and specific reference may be made to the related description of the above process, and the detailed description will not be repeated.
And the acquisition process of the spatial system protection capability assessment score comprises the following steps: acquiring the number of backup satellites and the number of information links; and carrying out weighted summation on the number of the backup satellites and the number of the information links to obtain a space system protection capability evaluation score.
The number of backup satellites refers to the number of backup satellites prepared by a space system for ensuring normal implementation of system functions and improving system reliability; the number of information links refers to the number of information channels that are used for measurement and control, data communication, etc. with the spatial system. The parameter obtaining process can be set according to actual requirements, and the embodiment of the application is not limited thereto
It should also be understood that the process of obtaining the evaluation score corresponding to the restoring force dimension may be set according to actual requirements, and the embodiment of the application is not limited thereto.
Optionally, the process of obtaining the evaluation score corresponding to the restoring force dimension includes: acquiring an evaluation score of the quick response transmitting capability and an evaluation score corresponding to the space maintenance capability; and carrying out weighted summation on the evaluation score of the quick response transmitting capacity and the evaluation score corresponding to the space maintenance capacity to obtain the evaluation score corresponding to the restoring force dimension.
And the acquisition process of acquiring the evaluation score of the quick response transmitting capability includes: acquiring a quick response transmitting period and a microsatellite production period; and carrying out weighted summation on the quick response emission period and the microsatellite production period to obtain an evaluation score of the quick response emission capability.
The fast response launching period generally refers to the sum of time for the rocket to launch a test and prepare for launching after receiving a launching task instruction; the production cycle of the microsatellite generally refers to the sum of time for system integration, assembly test, factory acceptance and the like after the satellite development party receives the satellite development and production task instruction.
The above-mentioned parameter obtaining process can be set according to actual requirements, and the embodiment of the application is not limited thereto.
And the process for obtaining the evaluation score corresponding to the space maintenance capability comprises the following steps: acquiring an evaluation score corresponding to an on-orbit repair period and a function recovery level; and carrying out weighted summation on the evaluation scores corresponding to the on-orbit repair period and the functional recovery level to obtain the evaluation score corresponding to the space maintenance capability.
And step S220, carrying out weighted summation based on the evaluation scores corresponding to each dimension to obtain the elastic capability evaluation total score corresponding to the safety system.
Specifically, weighted summation calculation is performed on the evaluation score corresponding to the preventive force dimension, the evaluation score corresponding to the resistance dimension and the evaluation score corresponding to the restoring force dimension, so as to obtain an elastic capacity evaluation total score corresponding to the safety system.
And step S230, the elastic capability of the safety system is evaluated based on the elastic capability evaluation total score, and an elastic capability evaluation result of the space system is obtained.
Specifically, in the case where each evaluation score range corresponds to one elasticity evaluation level, the evaluation score range to which the elasticity ability evaluation total score belongs may be determined, and further, the elasticity evaluation level corresponding thereto may be determined, and the determined elasticity evaluation level may be determined as the elasticity ability evaluation result.
Therefore, by means of the technical scheme, the embodiment of the application can evaluate the elastic capacity of the space system from the preventive force dimension, the resistance dimension and the restoring force latitude system, so that the elastic capacity can be evaluated, and the accuracy of the evaluation can be improved.
It should be understood that the above-described method for evaluating the elastic capability of a space system is only exemplary, and that a person skilled in the art may make various modifications, modifications or modifications according to the above-described method, and the content after the modifications is also within the scope of protection of the present application.
It will be appreciated by those skilled in the art that embodiments of the present invention may be provided as a method, system, or computer program product. Accordingly, the present invention may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present invention may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, and the like) having computer-usable program code embodied therein.
The present invention is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems) and computer program products according to embodiments of the invention. It will be understood that each flow and/or block of the flowchart illustrations and/or block diagrams, and combinations of flows and/or blocks in the flowchart illustrations and/or block diagrams, can be implemented by computer program instructions.
It should be noted that in the claims, any reference signs placed between parentheses shall not be construed as limiting the claim. The word "comprising" does not exclude the presence of elements or steps not listed in a claim. The word "a" or "an" preceding an element does not exclude the presence of a plurality of such elements. The invention may be implemented by means of hardware comprising several distinct elements, and by means of a suitably programmed computer. In the claims enumerating several means, several of these means may be embodied by one and the same item of hardware. The use of the terms first, second, third, etc. are for convenience of description only and do not denote any order. These terms may be understood as part of the component name.
Furthermore, it should be noted that in the description of the present specification, the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to a specific feature, structure, material, or characteristic described in connection with the embodiment or example being included in at least one embodiment or example of the present invention. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, the different embodiments or examples described in this specification and the features of the different embodiments or examples may be combined and combined by those skilled in the art without contradiction.
While preferred embodiments of the present invention have been described, additional variations and modifications in those embodiments may occur to those skilled in the art upon learning the basic inventive concepts. Therefore, the appended claims should be construed to include preferred embodiments and all such variations and modifications as fall within the scope of the invention.
It will be apparent to those skilled in the art that various modifications and variations can be made to the present invention without departing from the spirit or scope of the invention. Thus, the present invention should also include such modifications and variations provided that they come within the scope of the following claims and their equivalents.
Claims (10)
1. A method of evaluating the elastic capacity of a space system, comprising:
carrying out elastic capability evaluation on the space system from the preventive force dimension, the resistance dimension and the restoring force dimension to obtain an evaluation score corresponding to each dimension;
carrying out weighted summation based on the evaluation scores corresponding to each dimension to obtain an elastic capability evaluation total score corresponding to the safety system;
and evaluating the elastic capability of the safety system based on the elastic capability evaluation total score to obtain an elastic capability evaluation result of the space system.
2. The method of claim 1, wherein the obtaining the evaluation score corresponding to the preventive dimension comprises:
acquiring an evaluation score corresponding to the air conditioner target detection capability, an evaluation score corresponding to the threat warning capability and an evaluation score corresponding to the space environment forecasting capability;
and carrying out weighted summation on the evaluation score corresponding to the air conditioner target detection capability, the evaluation score corresponding to the threat warning capability and the evaluation score corresponding to the space environment forecasting capability to obtain the evaluation score corresponding to the preventive dimension.
3. The method according to claim 2, wherein the process of obtaining the evaluation score corresponding to the air conditioner target detection capability includes:
acquiring a space target catalogue, a ground radar scanning period and a detection precision value;
and carrying out weighted summation on the space target catalogue, the ground radar scanning period and the detection precision value to obtain an evaluation score corresponding to the air conditioner target detection capability.
4. The method of claim 2, wherein the process of obtaining the assessment score corresponding to the threat alert capability comprises:
acquiring collision early-warning time and collision early-warning distance;
and carrying out weighted summation on the collision early-warning time and the collision early-warning distance to obtain an evaluation score corresponding to the threat warning capability.
5. The method according to claim 2, wherein the process of obtaining the evaluation score corresponding to the spatial environment forecasting ability includes:
acquiring solar flare forecasting time and solar wind forecasting time;
and carrying out weighted summation on the solar flare forecasting time and the solar wind forecasting time to obtain an evaluation score corresponding to the space environment forecasting capacity.
6. The method of claim 1, wherein the obtaining the evaluation score corresponding to the resistance dimension comprises:
acquiring a space protection capability evaluation score and a space system protection capability evaluation score;
and carrying out weighted summation on the space protection capability evaluation score and the space system protection capability evaluation score to obtain an evaluation score corresponding to the resistance dimension.
7. The method of claim 6, wherein the step of obtaining the spatial protection capability assessment score comprises:
acquiring a maneuvering performance evaluation score, a photoelectric countermeasure protection capability evaluation score, a satellite reinforcement performance evaluation score and a satellite hiding capability evaluation score;
and carrying out weighted summation on the maneuvering performance evaluation score, the photoelectric countermeasure protection capability evaluation score, the satellite reinforcement performance evaluation score and the satellite hiding capability evaluation score to obtain the space protection capability evaluation score.
8. The method of claim 6, wherein the step of obtaining the spatial system protection capability assessment score comprises:
acquiring the number of backup satellites and the number of information links;
and carrying out weighted summation on the number of the backup satellites and the number of the information links to obtain the space system protection capability evaluation score.
9. The method of claim 1, wherein the process of obtaining the evaluation score corresponding to the restoring force dimension comprises:
acquiring an evaluation score of the quick response transmitting capability and an evaluation score corresponding to the space maintenance capability;
and carrying out weighted summation on the evaluation score of the quick response transmitting capacity and the evaluation score corresponding to the space maintenance capacity to obtain the evaluation score corresponding to the restoring force dimension.
10. The method of claim 9, wherein the obtaining of the evaluation score for the fast response transmitting capability comprises:
acquiring a quick response transmitting period and a microsatellite production period;
and carrying out weighted summation on the quick response transmitting period and the microsatellite production period to obtain an evaluation score of the quick response transmitting capability.
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