CN109740942B - Spacecraft energy system safety autonomous management method and management system - Google Patents
Spacecraft energy system safety autonomous management method and management system Download PDFInfo
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Abstract
The invention relates to a safety autonomous management method for a spacecraft energy system, which comprises the following steps: a. collecting state values of an energy system of the spacecraft at regular time; b. detecting whether factors influencing the state of the spacecraft exist in the spacecraft energy system at regular time; c. processing the data generated in the step a and the step b; d. and c, analyzing the processing result in the step c, giving a processing method and handling the abnormal problem. According to the management method and the management system, the time for discovering the abnormity of the energy system is greatly reduced, and the speed of abnormity treatment is improved. The method greatly reduces the links of manual participation and saves the labor cost.
Description
Technical Field
The invention relates to the field of space flight and electricity, in particular to a safety autonomous management method and a safety autonomous management system for a spacecraft energy system.
Background
With the continuous increase of the on-orbit operation time of the spacecraft, the time of not being in a measurement and control area is gradually prolonged, which puts higher requirements on the autonomous management capability of the spacecraft. The energy system is one of the most critical systems of the spacecraft, and the autonomous management capability of the energy system determines the success or failure of the task execution of the whole spacecraft. The invention provides an autonomous management method for the safety of an energy system based on the purpose that the most basic requirement of autonomous management is to ensure the safety of a spacecraft.
The autonomous management of the spacecraft energy system is based on autonomous real-time monitoring of the current state of the spacecraft, and various factors affecting the state of the spacecraft exist. In order to efficiently and accurately judge whether the spacecraft energy system is in an abnormal state and quickly and effectively treat the abnormal state, influence factors need to be comprehensively sorted, reasonable autonomous investigation and treatment processes are set, and the spacecraft can be guaranteed to be restored to a normal state in the shortest time.
In order to recover the abnormal state of the energy system of the spacecraft, the conventional method is to determine the position of the abnormality by manually interpreting related parameters, analyze the reason of the abnormality, and then make a corresponding scheme according to the analysis result for recovery. The disadvantages of this approach are mainly twofold: the real-time performance of manual interpretation cannot be guaranteed, and since the spacecraft which runs in orbit for a long time runs outside the measurement and control area, data cannot descend timely, and after the spacecraft enters the measurement and control area, a long time is needed for searching abnormal data in massive information. This can result in the problem not being located for treatment even after the anomaly has occurred for a long time. Secondly, the comprehensiveness is not guaranteed, manual interpretation is carried out, when abnormal parameters are found, the interpretation is usually stopped, and the abnormal parameters are positioned and treated. If multiple abnormal parameters appear at the same time, the subsequent abnormal parameters are ignored, which may cause more serious abnormal parameters not to be found at the first time, and delay the handling of the abnormal parameters.
Disclosure of Invention
The invention aims to solve the problems and provides a safety autonomous management method and a safety autonomous management system for a spacecraft energy system, so that faults can be timely and accurately positioned and autonomously processed.
In order to achieve the aim, the invention provides an autonomous management method for safety of an energy system of a spacecraft, which comprises the following steps:
a. collecting state values of an energy system of the spacecraft at regular time;
b. detecting whether factors influencing the state of the spacecraft exist in the spacecraft energy system at regular time;
c. processing the data generated in the step a and the step b;
d. and c, analyzing the processing result in the step c, giving a processing method and handling the abnormal problem.
According to one aspect of the invention, in said a step, a state parameter list L is established, the parameters in this list being able to reflect all the states of the spacecraft energy system.
According to one aspect of the invention, in said step b, a list of influencing factors S is established, covering all influencing factors capable of changing the state parameters of the spacecraft energy system.
According to an aspect of the present invention, in the step c, a corresponding relationship between the state parameter and the influencing factor is established, and when the influencing factor corresponding to the state parameter can be found by all changes of the state parameter, f (V, Ω) is made to be 0;
when at least one state parameter changes and the corresponding influence factor cannot be found, the energy system is considered to generate at least one abnormality, and f (V, omega) is made to be the number of the abnormality, wherein
And V is the collection of all the influence factors generated in the period, and is the collection value of all the state parameters in the list L in the period.
According to one aspect of the invention, in said step d, a problem-handling library H is created, in which all the solutions to the abnormal problems are stored.
According to one aspect of the invention, setting a period of detecting the influencing factors and a period of collecting the state parameters, sending a group of V and omega values to the step c in each period, and then screening all the state parameter values X which can not find the corresponding relation, wherein
And generating a value n representing the number of abnormal problems, and then sending X and n to the step d for disposal.
According to one aspect of the invention, at least one solution is found in the problem-handling library H according to X and n, and the computer is driven to process.
In order to achieve the above object, the present invention further provides a management system for implementing a spacecraft energy system security autonomous management method, including:
the clock module is used for setting time;
the state acquisition module is used for acquiring the state value of the spacecraft energy system at regular time according to the time set by the clock module;
the influence factor module is used for detecting whether factors influencing the state of the spacecraft exist in the spacecraft energy system at regular time according to the time set by the clock module;
the state and influence factor comprehensive analysis module is used for receiving the real-time data sent by the state acquisition module and the influence factor module and processing the received data;
and the problem handling module is used for receiving the data processing result sent by the state and influence factor comprehensive analysis module, analyzing the result, giving a processing method and handling the abnormal problem.
According to one aspect of the invention, a state parameter list L is established, the parameters in the list L being capable of reflecting all states of the spacecraft energy system, the list L being stored in the state acquisition module.
According to one aspect of the invention, a list S of influencing factors is created, said list S covering all influencing factors capable of changing the state parameters of the spacecraft energy system, said list S being stored in said influencing factor module.
According to one aspect of the present invention, a corresponding relationship f between the state parameter and the influencing factor is established, and when the influencing factor corresponding to the change of all the state parameters can be found, f (V, Ω) is made to be 0;
when there is at least oneIf the state parameter is changed and the corresponding influence factor cannot be found, the energy system is considered to generate at least one abnormity, and f (V, omega) is made to be the number of the abnormity, wherein
The collection of all the influence factors generated in the period is shown, and V is the collection value of all the state parameters in the list L in the period;
and the corresponding relation f is stored in the state and influence factor comprehensive analysis module.
According to one aspect of the invention, a problem-handling library H is created, which holds all the resolution of abnormal problems, said problem-handling library H being held in said problem-handling module.
According to one aspect of the invention, the clock module gives a period of impact factor detection and a period of state parameter acquisition, each period, the impact factor module and the state acquisition module send a group of V and Ω values to the state and impact factor comprehensive analysis module, and the state and impact factor comprehensive analysis module screens out all state parameter values X for which a corresponding relationship cannot be found according to the received values, wherein the clock module gives the periods of impact factor detection and the periods of state parameter acquisition, and each period of the impact factor module and the state acquisition module send a group of V and Ω values to the state and impact factor comprehensive analysis module
And generates a value n representing the number of abnormal problems, and then sends X, n to the problem handling module.
According to one aspect of the invention, the problem handling module finds at least one solution in the problem handling library H according to the values of X and n and drives a computer to process.
According to the management method and the management system, the time for discovering the abnormity of the energy system is greatly reduced, and the speed of abnormity treatment is improved. The method greatly reduces the links of manual participation and saves the labor cost.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
Fig. 1 schematically shows a flow chart of a method for autonomous management of the security of a spacecraft energy system according to an embodiment of the invention.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments will be briefly described below. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
In describing embodiments of the present invention, the terms "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in an orientation or positional relationship that is based on the orientation or positional relationship shown in the associated drawings, which is for convenience and simplicity of description only, and does not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and thus, the above-described terms should not be construed as limiting the present invention.
The present invention is described in detail below with reference to the drawings and the specific embodiments, which are not repeated herein, but the embodiments of the present invention are not limited to the following embodiments.
Fig. 1 schematically shows a flow chart of a method for autonomous management of the security of a spacecraft energy system according to an embodiment of the invention. As shown in fig. 1, the autonomous management method for the safety of the spacecraft energy system according to the invention comprises the following steps:
a. collecting state values of an energy system of the spacecraft at regular time;
b. detecting whether factors influencing the state of the spacecraft exist in the spacecraft energy system at regular time;
c. processing the data generated in the step a and the step b;
d. and c, analyzing the processing result in the step c, giving a processing method and handling the abnormal problem.
According to an embodiment of the invention, in the step a, a state parameter list L is established, and the parameters in the list can reflect all states of the spacecraft energy system.
In the step b, establishing an influencing factor list S, wherein the list covers all influencing factors capable of changing the state parameters of the spacecraft energy system. The influence factors refer to positive influence factors, namely correctly sent program control commands, remote control commands and the like; negative influence factors such as single event upset caused by a spatial environment are not in the list.
In the step c, a corresponding relation between the state parameters and the influence factors is established, and when the influence factors corresponding to the state parameters can be found by changing all the state parameters, f (V, omega) is made to be 0;
when at least one state parameter changes and the corresponding influence factor cannot be found, the energy system is considered to generate at least one abnormality, and f (V, omega) is made to be the number of the abnormality, wherein
And V is the collection of all the influence factors generated in the period, and is the collection value of all the state parameters in the list L in the period.
In step d, a problem handling library H is created, in which all the solutions to the abnormal problems, usually instructions or instruction chains, are stored.
In this embodiment, a period for detecting the influencing factors and a period for collecting the state parameters are set, each period sends a group of V and Ω values to step c, and then all the state parameter values X for which the corresponding relationship cannot be found are screened out, wherein
And generating a value n representing the number of abnormal problems, and then sending X and n to the step d for disposal. And finding at least one solution in the problem disposal library H according to the X and the n, and driving a computer to process.
In order to achieve the object of the present invention, the present invention further provides a management system for implementing the above autonomous management method for spacecraft energy system security, the management system comprising:
the clock module is used for setting time;
the state acquisition module is used for acquiring the state value of the spacecraft energy system at regular time according to the time set by the clock module;
the influence factor module is used for detecting whether factors influencing the state of the spacecraft exist in the spacecraft energy system at regular time according to the time set by the clock module;
the state and influence factor comprehensive analysis module is used for receiving the real-time data sent by the state acquisition module and the influence factor module and processing the received data;
and the problem handling module is used for receiving the data processing result sent by the state and influence factor comprehensive analysis module, analyzing the result, giving a processing method and handling the abnormal problem.
According to an embodiment of the present invention, the list L is stored in the status collection module, the list S is stored in the influence factor module, the correspondence relationship f is stored in the status and influence factor comprehensive analysis module, and the problem handling library H is stored in the problem handling module.
In an embodiment of the present invention, the clock module gives a period of impact factor detection and a period of state parameter collection, and in each period, the impact factor module and the state collection module send a group of V and Ω values to the state and impact factor comprehensive analysis module, and the state and impact factor comprehensive analysis module screens out all state parameter values X for which a corresponding relationship cannot be found according to the received values, wherein the state and impact factor comprehensive analysis module screens out all state parameter values X for which a corresponding relationship cannot be found
And generates a value n representing the number of abnormal problems, and then sends X, n to the problem handling module. And the problem handling module finds at least one solution in the problem handling library H according to the values of X and n and drives a computer to process.
According to the method and the system, the problems in the prior art are solved, the time for discovering the abnormity of the energy system is greatly shortened, and the speed of abnormity treatment is increased. The method greatly reduces the links of manual participation and saves the labor cost.
The above description is only one embodiment of the present invention, and is not intended to limit the present invention, and it is apparent to those skilled in the art that various modifications and variations can be made in the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (2)
1. A safety autonomous management method for a spacecraft energy system comprises the following steps:
a. collecting state values of an energy system of the spacecraft at regular time;
b. detecting whether factors influencing the state of the spacecraft exist in the spacecraft energy system at regular time;
c. processing the data generated in the step a and the step b;
d. analyzing the processing result in the step c, giving a processing method, and handling the abnormal problem;
in the step a, establishing a state parameter list L, wherein parameters in the list can reflect all states of the spacecraft energy system;
in the step b, establishing an influence factor list S, wherein the list covers all influence factors capable of changing the state parameters of the spacecraft energy system;
in the step c, establishing a corresponding relation between the state parameters and the influence factors, and when the influence factors corresponding to the state parameters can be found out by changing all the state parameters, making f (V, omega) equal to 0;
when at least one state parameter changes and the corresponding influence factor cannot be found, the energy system is considered to generate at least one abnormality, and f (V, omega) is made to be the number of the abnormality, wherein
The collection of all the influence factors generated in the period is shown, and V is the collection value of all the state parameters in the list L in the period;
in the step d, a problem disposal library H is established, and all abnormal problem solving measures are stored in the library;
setting a period for detecting the influencing factors and a period for acquiring the state parameters, sending a group of V and omega values to the step c in each period, and screening all state parameter values X of which the corresponding relation cannot be found out, wherein
Generating a value n representing the number of abnormal problems, and then sending X and n to the step d for disposal;
and finding at least one solution in the problem disposal library H according to X and n, and driving a computer to process.
2. A management system implementing the spacecraft energy system security autonomous management method of claim 1, comprising:
the clock module is used for setting time;
the state acquisition module is used for acquiring the state value of the spacecraft energy system at regular time according to the time set by the clock module;
the influence factor module is used for detecting whether factors influencing the state of the spacecraft exist in the spacecraft energy system at regular time according to the time set by the clock module;
the state and influence factor comprehensive analysis module is used for receiving the real-time data sent by the state acquisition module and the influence factor module and processing the received data;
the problem handling module is used for receiving the data processing result sent by the state and influence factor comprehensive analysis module, analyzing the result, giving a processing method and handling the abnormal problem;
establishing a state parameter list L, wherein parameters in the list L can reflect all states of the spacecraft energy system, and the list L is stored in the state acquisition module;
establishing an influence factor list S, wherein the list S contains all influence factors capable of changing state parameters of the spacecraft energy system, and the list S is stored in the influence factor module;
establishing a corresponding relation f between the state parameters and the influence factors, and enabling f (V, omega) to be 0 when the influence factors corresponding to the state parameters can be found out through the change of all the state parameters;
when at least one state parameter changes and the corresponding influence factor cannot be found, the energy system is considered to generate at least one abnormality, and f (V, omega) is made to be the number of the abnormality, wherein
The collection of all the influence factors generated in the period is shown, and V is the collection value of all the state parameters in the list L in the period;
the corresponding relation f is stored in the state and influence factor comprehensive analysis module;
establishing a problem handling library H, wherein all abnormal problem solving measures are stored in the library, and the problem handling library H is stored in the problem handling module;
the clock module gives a period of detecting the influence factors and a period of acquiring the state parameters, wherein in each period, the influence factor module and the state acquisition module send a group of V and omega values to the state and influence factor comprehensive analysis module, and the state and influence factor comprehensive analysis module screens out all state parameter values X which cannot find the corresponding relation according to the received values, wherein in each period, the state and influence factor comprehensive analysis module screens out all state parameter values X which cannot find the corresponding relation
Generating a value n representing the number of abnormal problems, and then sending X, n to the problem handling module;
and the problem handling module finds at least one solution in the problem handling library H according to the values of X and n and drives a computer to process.
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