Satellite on-orbit real-time state monitoring method and system based on sudden change telemetering and medium

Abstract

The invention provides a satellite in-orbit real-time state monitoring method and system based on abrupt change telemetry and a medium. The method comprises the following steps that S1, state monitoring telemetry information needing to be collected for satellite state monitoring is extracted; s2, inputting state monitoring telemetry information, and acquiring periodic telemetry information and abrupt change telemetry information through on-satellite state monitoring application software; s3, extracting satellite state features in the periodic telemetry information and the abrupt telemetry information; and S4, according to the satellite state characteristics, judging the in-orbit state of the satellite to obtain satellite state monitoring data, and storing and downloading the satellite state monitoring data. According to the method, a telemetering interpretation blind area in the satellite in-orbit process can be effectively filled up, the risk of misjudgment and missed judgment possibly caused by insufficient analysis of the satellite in-orbit condition during post interpretation by ground control personnel is effectively avoided, and meanwhile, the problems of limited on-satellite computing resources and on-satellite real-time state monitoring and maintenance can be effectively solved.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite status monitoring, and in particular to a method, system and medium for monitoring the on-orbit real-time status of a satellite based on mutation telemetry. Background Art

[0002] With the development of satellite development technology, the structure and function of the launched satellites are becoming more and more complex. Due to the harsh space environment in which satellites are located when they are in orbit, a large number of joint tests need to be completed before the satellites leave the factory, and the satellite system should have the means to monitor and evaluate the satellite's status in orbit, so as to strictly monitor and diagnose and repair the satellite system's faults, and ensure the reliability and safety of the satellite when it is in orbit. Due to the characteristics of its orbit, the visible arc of measurement and control and the visible arc of data transmission during the satellite's transit are very short. The satellite is invisible to the ground during most of its flight time in orbit. If the satellite has a problem in orbit and cannot make an independent judgment, it can only be discovered when it enters the country. Waiting for the ground to receive information, diagnose, determine treatment measures, implement them, observe the effects until the fault is eliminated, it often takes multiple orbits to completely solve the problem.

[0003] In recent years, the improvement of onboard computer computing power has greatly improved the data processing and management capabilities of satellites, which provides a good hardware foundation for on-orbit status monitoring. However, the space environment where satellites are located is dangerous and unknown, with harsh electromagnetic and radiation environments. Highly integrated circuits are more susceptible to interference. As the chip integration increases, the possibility of single-particle upset errors also increases. This is an issue that cannot be ignored in the realization of satellite software platforms.

[0004] In addition, the current satellite on-orbit status monitoring technology has the following shortcomings: First, the sampling frequency of the telemetry channel is limited, and there are telemetry blind spots for sudden telemetry fluctuations that need to be monitored, which cannot meet the needs of satellite fault troubleshooting; Second, the on-orbit status monitoring coverage is relatively small, focusing only on individual single machine or subsystem failures, and lacks monitoring of more satellite states such as state switching and whole-satellite failure modes.

[0005] In summary, there is an urgent need to develop a method and system for real-time on-orbit status monitoring of satellites based on mutation telemetry. Summary of the invention

[0006] In view of the defects in the prior art, the present invention provides a method, system and medium for real-time status monitoring of a satellite on-orbit based on mutation telemetry.

[0007] According to the present invention, a method for monitoring the satellite status in orbit in real time based on mutation telemetry comprises the following steps:

[0008] Step S1: extracting the status monitoring telemetry information required for satellite status monitoring;

[0009] Step S2: inputting the telemetry information for status monitoring, and obtaining the periodic telemetry information and the sudden change telemetry information through the onboard status monitoring application software;

[0010] Step S3: extract satellite status features from periodic telemetry information and mutation telemetry information;

[0011] Step S4: According to the satellite status characteristics, the satellite on-orbit status is judged to obtain satellite status monitoring data, and the satellite status monitoring data is stored and transmitted.

[0012] Preferably, in step S1, based on the basic information of each component on the satellite, the impact domain and measures of the component-level faults on the satellite are analyzed, the safety fault management items are sorted out, and the fault management control process is analyzed according to detectability, harmfulness, hazard impact range, and fault frequency. The fault mode of the satellite's autonomous on-orbit detection is screened out from the analysis results, and the status monitoring telemetry information that needs to be collected is obtained.

[0013] Preferably, in step S2, the on-board status monitoring application software relies on the satellite platform operating system module, and the satellite platform operating system module includes an operating system hardware module and an operating system software. The operating system hardware module serves as the control center of the platform and provides an interface and environment for the operation of the on-board status monitoring application software. The operating system software is responsible for developing drivers for all external devices of the integrated electrical stand-alone machine and providing a corresponding middleware layer. The satellite platform operating system module is responsible for unified scheduling and management of all devices and resources, coordinating the use of devices and resources by the on-board status monitoring application software, and realizing dynamic scheduling of telemetry collection by the on-board status monitoring application software.

[0014] Preferably, in step S2, a normal telemetry channel and a mutation telemetry channel are configured for the status monitoring telemetry information, and periodic telemetry information is collected through the normal telemetry channel, and mutation telemetry information is collected through the mutation telemetry channel. Different from the collection method of periodic telemetry information, targeted high-frequency sampling is performed on the mutation telemetry channel, and the collection frequency of the high-frequency sampling depends on the degree of frequency division of the time period by the integrated electronic application.

[0015] Preferably, in step S2, when the satellite conducts specific on-orbit activities that result in sudden fluctuations in satellite energy, attitude or bus voltage and current or abnormalities in some onboard telemetry, the onboard status monitoring application software selects one or more corresponding parameters, modifies the sampling address of the sudden telemetry package, and dynamically schedules telemetry collection through the sudden telemetry channel to obtain sudden telemetry information.

[0016] Preferably, in step S3, the periodic telemetry information and the mutation telemetry information are first preprocessed, the mutation telemetry information is first filtered using the low-order strategy, and the periodic telemetry information and the filtered mutation telemetry information are fused according to the needs of status monitoring, and the two are adjusted to corresponding lengths and then merged. Then, the processing formulas of voltage telemetry, temperature telemetry, integer telemetry, and floating-point telemetry are used to convert the telemetry true value, and the telemetry true value is compared with the designed normal value interval to obtain the satellite status characteristics.

[0017] Preferably, step S4 includes using the satellite failure mode to sort the state nodes of satellite components and subsystems of the entire satellite into a fault tree, and through the sorting process, obtaining various state characteristics corresponding to the failure mode, assigning corresponding values ​​to the instantaneous characteristic data during the on-orbit state detection of the satellite, and then performing fault judgment according to the cause-effect sequence of the state nodes of the fault tree, so that the state monitoring module can quickly locate the fault and store the fault signal.

[0018] Preferably, in step S4, a storage area is opened in the memory, and the onboard status monitoring application software transmits data to the memory through the processor's external interface. After receiving the data, the memory performs cyclic overwriting storage according to the data type, and the satellite status monitoring data is downloaded through the measurement and control channel and the data transmission channel.

[0019] The present invention also provides a satellite on-orbit real-time status monitoring system based on mutation telemetry, comprising:

[0020] Module M1: Extract the status monitoring telemetry information required for satellite status monitoring;

[0021] Module M2: Input status monitoring telemetry information, and obtain periodic telemetry information and mutation telemetry information through onboard status monitoring application software;

[0022] Module M3: Extract satellite status features from periodic telemetry information and mutation telemetry information;

[0023] Module M4: According to the satellite status characteristics, the satellite on-orbit status is judged, the satellite status monitoring data is obtained, and the satellite status monitoring data is stored and transmitted.

[0024] The present invention also provides a computer-readable storage medium storing a computer program, and when the computer program is executed by a processor, the steps of the above-mentioned method for real-time status monitoring of a satellite in orbit based on mutation telemetry are performed.

[0025] Compared with the prior art, the present invention has the following beneficial effects:

[0026] 1. The present invention can effectively fill the blind spots of telemetry interpretation during the satellite's on-orbit process by fusing mutation telemetry information with periodic telemetry information, effectively avoid the risk of misjudgment and missed judgment caused by insufficient analysis of the satellite's on-orbit situation during subsequent interpretation by ground control personnel, and effectively solve the problem of limited on-board computing resources and difficulty in maintaining on-board real-time status monitoring.

[0027] 2. The present invention dynamically schedules mutation telemetry acquisition based on customized telemetry information and monitoring strategies, reads the status signal of the satellite platform, makes on-orbit status judgments, and stores and downloads the results.

[0028] 3. The present invention completes the status monitoring function through the architecture of combining the integrated electrical stand-alone operating system with the on-board status monitoring application software, avoiding the problem of increasing the complexity of the satellite integrated electronic platform due to the addition of a status monitoring module alone. At the same time, the on-board status monitoring application software is started by controlling the management software to save on-board computing resources and power consumption, and the possible single particle flip anomaly problem is solved through the redundant design of the on-board status monitoring application software data processing process. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0030] Figure 1 A schematic diagram of the implementation process of the method in the embodiment of the present invention;

[0031] Figure 2 Schematic diagram of dynamically scheduling mutation telemetry collection operations in an embodiment of the present invention. DETAILED DESCRIPTION

[0032] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0033] The present invention dynamically schedules mutation telemetry acquisition according to customized strategies, reads the status signal of the satellite platform, makes an initial judgment on the on-orbit status and transmits customized satellite status monitoring data, effectively filling the blind spot of telemetry reading during the satellite's on-orbit process, reducing the lag of post-judgment by ground control personnel, and effectively avoiding the risk of misjudgment or missed judgment caused by insufficient analysis of the satellite's on-orbit status by ground control personnel during post-judgment. At the same time, it can effectively solve the problem of limited on-board computing resources and difficulty in maintaining real-time on-board status monitoring.

[0034] Embodiment 1:

[0035] This embodiment provides a method for monitoring the satellite status in orbit in real time based on mutation telemetry, comprising the following steps:

[0036] Step S1: extracting the status monitoring telemetry information required for satellite status monitoring.

[0037] Specifically, based on the basic information of each component on the satellite, the impact domain and measures of component-level failures on the satellite are analyzed, the safety fault management items are sorted out, and the fault management control process is analyzed according to detectability, harmfulness, hazard impact range, and failure frequency. The fault modes of autonomous detection of satellites in orbit are screened out from the analysis results, and the status monitoring telemetry information that needs to be collected is obtained.

[0038] Specifically, detectability is determined based on the satellite periodic telemetry and mutation telemetry collection frequency by analyzing the maximum necessary collection frequency of the status monitoring mutation telemetry information to be collected. Detectability is divided into "32s telemetry feature identifiable", "8s telemetry feature identifiable", "2s telemetry feature identifiable", "mutation telemetry feature identifiable" and "unidentifiable".

[0039] Collect information about launched satellites that are similar to the current payload and platform, pay attention to their failure mode analysis, as well as the telemetry design for directly identifying the failure and its associated telemetry. Consider the harmfulness of the failure, screen out the failure modes that require autonomous detection by the satellite on orbit; consider the scope of the harmful impact of the failure, screen the associated telemetry, and combine it with the telemetry for directly identifying the failure to obtain the state monitoring telemetry information required for satellite state monitoring; analyze whether there is any inconsistency between the frequency that can be identified by the screened telemetry fault characteristics and the frequency design for normal collection and transmission on the satellite, and include the telemetry with insufficient frequency into the mutation telemetry information required for state monitoring.

[0040] Step S2: Input the status monitoring telemetry information, and obtain the periodic telemetry information and the mutation telemetry information through the on-board status monitoring application software.

[0041] The on-board status monitoring application software relies on the satellite platform operating system module, which includes the operating system hardware module and the operating system software. The operating system hardware module, as the control center of the platform, provides an interface and environment for the operation of the on-board status monitoring application software, and realizes remote control information processing, telemetry information processing, thermal control management, whole satellite task management, and information interaction with each lower computer through the CAN bus. At the same time, it communicates with the measurement and control subsystem module to complete the satellite-ground information interaction and realize the real-time satellite status detection.

[0042] The operating system software is responsible for developing drivers for all external devices of the integrated electrical stand-alone machine and providing the corresponding middleware layer. The satellite platform operating system module is responsible for unified scheduling and management of all devices and resources, coordinating the use of devices and resources by the on-board status monitoring application software, and realizing dynamic scheduling of telemetry collection by the on-board status monitoring application software.

[0043] The satellite platform operating system module is the core product of the integrated electrical subsystem. The integrated electrical computer software consists of three types of software: management software, on-board status monitoring application software, and control software. A multi-process, multi-task, and strong real-time control software system is built based on an embedded operating system. The three types of software form a complete software product embedded in the integrated electrical computer. Among them, the management software completes the startup of the on-board status monitoring application software and control software, performs resource management, and controls the corresponding peripheral driver interface, while the satellite status monitoring is completed by the on-board status monitoring application software. Data is exchanged and transmitted between the various application software through shared memory and inter-process message queues. The functions implemented by the operating system software include but are not limited to remote control and on-orbit hot update operations, dynamic scheduling of telemetry acquisition, key status data acquisition and maintenance, creation and management of status monitoring data processing processes, and memory unloading.

[0044] Configure ordinary telemetry channels and mutation telemetry channels for the state monitoring telemetry information that needs to be collected. Collect periodic telemetry information through ordinary telemetry channels, and collect mutation telemetry information through mutation telemetry channels.

[0045] Specifically, when the satellite conducts specific on-orbit activities that cause sudden fluctuations in satellite energy, attitude, or bus voltage and current, or abnormalities in some onboard telemetry, the onboard status monitoring application software selects one or more corresponding parameters, modifies the sampling address of the sudden telemetry package, and dynamically schedules telemetry collection through the sudden telemetry channel to obtain sudden telemetry information.

[0046] Focus on monitoring the sudden change telemetry channel of state monitoring, such as the voltage that may surge, and conduct targeted high-frequency sampling. The sampling frequency depends on the degree of frequency division of the time period by the integrated electronic application, such as 0.5s. The specific method steps include:

[0047] Predefine idle telemetry source packets, assign them spatial application process identifiers (APIDs) and set their default transmission periods.

[0048] Design a one-channel / multi-channel parameter telemetry scheme that needs to be monitored when the satellite is in orbit or anomalies occur. Initialize the idle telemetry package sampling address according to the determined number of telemetry sampling channels. The specific sampling frequency of a telemetry parameter depends on the transmission period of the space telemetry package and the number of times it is collected in the space telemetry package.

[0049] Figure 2Schematic diagram of dynamically scheduling mutation telemetry collection operations in an embodiment of the present invention.

[0050] like Figure 2 As shown, before the satellite has any activity in orbit or when an abnormality occurs, the sampling address of the predefined idle telemetry package is modified according to the plan, and the periodic telemetry information is collected through the ordinary telemetry channel, and the mutation telemetry information is collected through the mutation telemetry channel. Different from the collection method of periodic telemetry information, targeted high-frequency sampling is performed on the mutation telemetry channel. The collection frequency of this high-frequency sampling depends on the degree of frequency division of the time period by the integrated electronic application.

[0051] Step S3: Extract satellite status features from periodic telemetry information and mutation telemetry information.

[0052] In this embodiment, the periodic telemetry information and the mutation telemetry information are first preprocessed, wherein the mutation telemetry information is first filtered using the low-order strategy, and the periodic telemetry information and the filtered mutation telemetry information are fused according to the needs of status monitoring. Specifically, the two are adjusted to corresponding lengths and then merged. Then, the processing formulas of voltage telemetry, temperature telemetry, integer telemetry, floating-point telemetry, etc. are used to convert the telemetry true value, and the telemetry true value is compared with the designed normal value interval to obtain the satellite status characteristics.

[0053] Step S4: According to the satellite status characteristics, the satellite on-orbit status is judged to obtain satellite status monitoring data, and the satellite status monitoring data is stored and transmitted.

[0054] In this embodiment, the satellite status characteristics are read, the characteristics are judged, and the satellite status monitoring data is confirmed.

[0055] Specifically, the satellite fault mode is used to sort the fault tree of the satellite components and the subsystem status nodes of the whole satellite. Through the sorting process, the various status characteristics corresponding to the fault mode are obtained. When the satellite is detected on-orbit, the real-time characteristic data is assigned corresponding values. Then, the fault judgment is performed according to the causal sequence of the state nodes of the fault tree, so that the status monitoring module can quickly locate the fault and store the fault signal.

[0056] Furthermore, two storage areas are opened in the memory, and the onboard status monitoring application software transmits data to the memory through the processor external interface. After receiving the data, the memory performs cyclic overwriting storage according to the data type, and the telemetry packets are stored in packet order according to the packet scheduling parameters. The satellite status monitoring data is transmitted through the measurement and control channel and the data transmission channel, or the data is extracted after being unloaded from the memory through the data transmission channel.

[0057] Embodiment 2:

[0058] The present invention also provides a satellite on-orbit real-time status monitoring system based on mutation telemetry. The satellite on-orbit real-time status monitoring system based on mutation telemetry can be realized by executing the process steps of the satellite on-orbit real-time status monitoring method based on mutation telemetry, that is, those skilled in the art can understand the satellite on-orbit real-time status monitoring method based on mutation telemetry as a preferred implementation of the satellite on-orbit real-time status monitoring system based on mutation telemetry.

[0059] In this embodiment, a satellite on-orbit real-time status monitoring system based on mutation telemetry includes:

[0060] Module M1: Extract the status monitoring telemetry information required for satellite status monitoring.

[0061] Module M2: Input status monitoring telemetry information, and obtain periodic telemetry information and mutation telemetry information through the on-board status monitoring application software.

[0062] Module M3: Extract satellite status features from periodic telemetry information and mutation telemetry information.

[0063] Module M4: According to the satellite status characteristics, the satellite on-orbit status is judged, the satellite status monitoring data is obtained, and the satellite status monitoring data is stored and transmitted.

[0064] Embodiment 3:

[0065] This embodiment provides a computer-readable storage medium storing a computer program. When the computer program is executed by a processor, the steps of the above-mentioned method for real-time on-orbit status monitoring of a satellite based on mutation telemetry are implemented.

[0066] Those skilled in the art know that, in addition to realizing the system and its various devices, modules, and units provided by the present invention in a purely computer-readable program code, it is entirely possible to realize the same functions in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers by logically programming the method steps. Therefore, the system and its various devices, modules, and units provided by the present invention can be considered as a hardware component, and the devices, modules, and units included therein for realizing various functions can also be regarded as structures within the hardware component; the devices, modules, and units for realizing various functions can also be regarded as both software modules for realizing the method and structures within the hardware component.

[0067] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A method for monitoring the satellite status in orbit in real time based on mutation telemetry, characterized in that: The steps include: Step S1: extracting the status monitoring telemetry information required for satellite status monitoring; Step S2: input the state monitoring telemetry information, and obtain periodic telemetry information and mutation telemetry information through the onboard state monitoring application software; Step S3: extracting satellite status features from the periodic telemetry information and the sudden change telemetry information; Step S4: judging the satellite's on-orbit status according to the satellite status characteristics, obtaining satellite status monitoring data, and storing and downloading the satellite status monitoring data.

2. The method for monitoring the satellite status in orbit in real time based on mutation telemetry according to claim 1, characterized in that: In step S1, based on the basic information of each component on the satellite, the impact domain and measures of the component-level faults on the satellite are analyzed, the safety fault management items are sorted out, and the fault management control process is analyzed according to detectability, harmfulness, hazard impact range, and fault frequency. The fault mode of the satellite's autonomous on-orbit detection is screened out from the analysis results, and the status monitoring telemetry information that needs to be collected is obtained.

3. The method for monitoring the satellite status in orbit in real time based on mutation telemetry according to claim 1, characterized in that: In step S2, the on-board status monitoring application software relies on the satellite platform operating system module, and the satellite platform operating system module includes an operating system hardware module and an operating system software. The operating system hardware module serves as the control center of the platform and provides an interface and environment for the operation of the on-board status monitoring application software. The operating system software is responsible for developing drivers for all external devices of the integrated electrical stand-alone machine and providing a corresponding middleware layer. The satellite platform operating system module is responsible for unified scheduling and management of all devices and resources, coordinating the use of devices and resources by the on-board status monitoring application software, and realizing dynamic scheduling of telemetry collection by the on-board status monitoring application software.

4. The method for monitoring the satellite status in orbit in real time based on mutation telemetry according to claim 1, characterized in that: In the step S2, a normal telemetry channel and a mutation telemetry channel are configured for the state monitoring telemetry information, and periodic telemetry information is collected through the normal telemetry channel, and mutation telemetry information is collected through the mutation telemetry channel. Different from the collection method of the periodic telemetry information, the mutation telemetry channel is subjected to targeted high-frequency sampling, and the collection frequency of the high-frequency sampling depends on the degree of frequency division of the time period by the integrated electronic application.

5. The method for monitoring the satellite status in orbit in real time based on mutation telemetry according to claim 4 is characterized in that: In step S2, when the satellite performs specific on-orbit activities that cause sudden fluctuations in satellite energy, attitude, or bus voltage and current, or abnormalities in some on-board telemetry, the on-board status monitoring application software selects one or more corresponding parameters, modifies the sampling address of the sudden telemetry package, and dynamically schedules telemetry collection through the sudden telemetry channel to obtain sudden telemetry information.

6. The method for monitoring the satellite status in orbit in real time based on mutation telemetry according to claim 1, characterized in that: In step S3, the periodic telemetry information and the mutation telemetry information are first preprocessed, and the mutation telemetry information is first filtered using the low-order strategy. According to the needs of status monitoring, the periodic telemetry information and the filtered mutation telemetry information are fused, and the two are adjusted to corresponding lengths and then merged. Then, the processing formulas of voltage telemetry, temperature telemetry, integer telemetry, and floating-point telemetry are used to convert the telemetry true value, and the telemetry true value is compared with the designed normal value interval to obtain the satellite status characteristics.

7. The method for monitoring the satellite status in orbit in real time based on mutation telemetry according to claim 1, characterized in that: The step S4 includes using the satellite fault mode to sort the state nodes of the satellite components and the subsystems of the whole satellite into a fault tree, and through the sorting process, various state characteristics corresponding to the fault mode are obtained, and the instant characteristic data is assigned corresponding values ​​when the satellite is detected on-orbit. Then, the fault is judged according to the cause-effect sequence of the state nodes of the fault tree, so that the state monitoring module can quickly locate the fault and store the fault signal.

8. The method for monitoring the satellite status in orbit in real time based on mutation telemetry according to claim 1, characterized in that: In step S4, a storage area is opened in the memory, and the on-board status monitoring application software transmits data to the memory through the processor's external interface. After receiving the data, the memory performs cyclic overwriting storage according to the data type, and the satellite status monitoring data is downloaded through the measurement and control channel and the data transmission channel.

9. A satellite on-orbit real-time status monitoring system based on mutation telemetry, characterized in that: include: Module M1: Extract the status monitoring telemetry information required for satellite status monitoring; Module M2: input the state monitoring telemetry information, and obtain periodic telemetry information and mutation telemetry information through the on-board state monitoring application software; Module M3: extracting satellite status features from the periodic telemetry information and the sudden change telemetry information; Module M4: According to the satellite status characteristics, the satellite on-orbit status is judged to obtain satellite status monitoring data, and the satellite status monitoring data is stored and transmitted.

10. A computer-readable storage medium storing a computer program, characterized in that: When the computer program is executed by a processor, the steps of a method for real-time on-orbit status monitoring of a satellite based on mutation telemetry according to any one of claims 1 to 8 are implemented.

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