CN113627018A - Heterogeneous spacecraft information data self-adaptive management method based on standardized design - Google Patents
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Abstract
The invention provides a heterogeneous spacecraft information data self-adaptive management method based on standardized design, which comprises the following steps: a multitasking standard platform configured to standardize design of mechanical, electrical and data interfaces for the payload to: when the heterogeneous spacecraft is subjected to in-orbit software function upgrading or hardware in-orbit assembly and service requirements, after different functional modules or the same functional module are replaced, the multi-task standard platform can quickly detect a newly replaced module; and the data format standard platform is configured to enable the information data formats of the satellite platform and the payload of the heterogeneous spacecraft to adopt a standard and universal data format, and enable the satellite-borne information transmission system of the heterogeneous spacecraft to adopt a universal model so as to realize design standardization and management generalization of the heterogeneous object.
Description
Technical Field
The invention relates to the technical field of autonomous health management of spacecrafts, in particular to a heterogeneous spacecraft information data self-adaptive management method based on standardized design.
Background
With the development of spacecraft intelligent technology and artificial intelligence and the improvement of spacecraft in-orbit energizing technology, the on-board computer greatly improves the information data processing and management capability of each subsystem of the heterogeneous spacecraft, and a good technical basis is provided for the information data adaptive intelligent management of the heterogeneous spacecraft. In addition, with the common application of the load digitization technology to the spacecraft and the proposal of the application technology of the on-orbit service of the spacecraft, the on-orbit energization of software and hardware of the spacecraft is more and more common and frequent, and the information data updating frequency of the heterogeneous spacecraft is accelerated.
The information data of the spacecraft comprises important states of all subsystems of the spacecraft, reflects the performance characteristics or the functional states of the spacecraft, and is an important basis for health diagnosis and fault prediction of the spacecraft. At present, information data analysis and judgment of a spacecraft depend on data types, threshold ranges and data processing methods of telemetering parameters, all of the contents are manually edited and updated by ground workers on special format files, when the number of the telemetering parameters is increased, the number of heterogeneous spacecrafts is increasingly huge, the functions of loads of each spacecraft are different, and the functions of the heterogeneous spacecrafts are frequently updated, the re-editing of the format files can bring huge artificial loads and potential reliability risks.
Disclosure of Invention
The invention aims to provide a heterogeneous spacecraft information data self-adaptive management method based on standardized design, so as to solve the problems of huge artificial load and potential reliability risk caused by the conventional spacecraft telemetering parameter processing.
In order to solve the technical problem, the invention provides a heterogeneous spacecraft information data self-adaptive management method based on standardized design, which comprises the following steps:
the multitasking standard platform is configured to standardize the mechanical, electronic and data interfaces of the payload to achieve the following:
when the heterogeneous spacecraft is subjected to in-orbit software function upgrading or hardware in-orbit assembly and service requirements, after different functional modules or the same functional module are replaced, the multi-task standard platform can quickly detect a newly replaced module;
the data format standard platform is configured to enable the information data formats of the satellite platform and the payload of the heterogeneous spacecraft to adopt a standard and universal data format, and enable the satellite-borne information transmission system of the heterogeneous spacecraft to adopt a universal model so as to realize design standardization and management generalization of the heterogeneous object.
Optionally, in the method for adaptively managing information data of a heterogeneous spacecraft based on a standardized design, the data format standard platform is further configured to:
information data of the heterogeneous spacecraft are standardized and classified, and the information data are divided into: analog quantity used for characterizing hardware basic health status, statistic quantity used for predicting hardware aging trend, state quantity used for rapid diagnosis and massive data used for application function generation, so as to realize the following effects:
when the heterogeneous spacecraft is energized in orbit, the self-adaptive management of the health state is automatically completed through an information data format and a processing method which are designed in a standardized way without the help of ground intervention.
Optionally, in the method for adaptively managing information data of a heterogeneous spacecraft based on a standardized design, a payload of the heterogeneous spacecraft is configured to:
on the basis of the standardized design of a mechanical interface and an electronic interface, on-track plug and play, automatic analog quantity acquisition and self-adaptive health state judgment through a standard threshold range are realized; and
the on-orbit self-adaptive operation of the satellite-borne autonomous health management software is realized based on the data interface standardized design.
Optionally, in the heterogeneous spacecraft information data adaptive management method based on the standardized design, the heterogeneous spacecraft only downloads the fault event package in the telemetry parameters and massive application data for load application generation in real time, so as to greatly reduce the waste of measurement and control resources.
Optionally, in the information data adaptive management method for the heterogeneous spacecraft based on the standardized design, the information data of the payload of the heterogeneous spacecraft is divided into an analog quantity representing a hardware health state, a digital quantity representing functional completeness, and application data for function synthesis, so that a standard and universal data format can be adopted for the information data format of the satellite platform and the payload of the heterogeneous spacecraft, and a universal model is adopted for a satellite-borne information transmission system of the heterogeneous spacecraft.
Optionally, in the method for adaptively managing information data of a heterogeneous spacecraft based on a standardized design, a standardized design is adopted for a hardware interface of a payload of the heterogeneous spacecraft, so that the following functions can be realized:
when the functions of the heterogeneous spacecraft are changed or the in-orbit maintenance and assembly is needed due to hardware faults, after a new module is quickly detected, the analog quantity data acquisition of the new module can be registered, the system level functions can be dynamically configured, and the health evaluation is carried out on the acquired analog quantity by adopting a universal data structure and a processing method; and
when the payload functions of the heterogeneous spacecraft are changed, a unified data source operation mechanism is adopted, so that the following effects can be realized:
the method for judging the health degree of the information data automatically identifies the judgment method of the health degree of the information data by realizing the standardized health evaluation of the functional flow through a unified information flow format without depending on manual assistance and ground support, wherein the judgment method of the health degree comprises trend analysis, boundary detection, mean value inspection, expected value inspection and deviation inspection, and can realize the normal operation with strong adaptability by depending on the adaptive standardized design of spacecraft software.
Optionally, in the method for adaptively managing information data of a heterogeneous spacecraft based on a standardized design, the standardized design of a hardware interface of a payload of the heterogeneous spacecraft includes:
the analog quantity of the heterogeneous spacecraft is collected through the analog quantity collecting terminal, the analog quantity collecting terminal judges the hardware health state of the heterogeneous spacecraft according to the standard analog quantity threshold range, and the judgment result is sent to the satellite-borne computer through the bus in a unified mode.
Optionally, in the heterogeneous spacecraft information data adaptive management method based on the standardized design, software functions of the payload are related to tasks of the heterogeneous spacecraft, and after the heterogeneous spacecraft is powered on orbit, information data related to the functions are subjected to adaptive judgment of the health state through a standardized data interface.
Optionally, in the method for adaptively managing information data of a heterogeneous spacecraft based on a standardized design, the standardization of information data by the heterogeneous spacecraft for adaptively managing health of the heterogeneous spacecraft includes:
carrying out standardized design on an information data structure, wherein loads with standardized interfaces adopt information data interfaces with generalized design, each load with standardized design sends an information data parameter table representing the health state of a single machine to a satellite borne computer through a bus, and the parameter table comprises 2-bit parameter number, parameter length, parameter code number, 4-bit parameter value, parameter type, statistical mode and judgment threshold, wherein the judgment threshold comprises an upper boundary and a lower boundary; wherein, the parameter code adopts a mode of uniformly arranging sub-addresses and sequence numbers; the parameter type is used for distinguishing the state quantity and the statistic quantity; the statistical mode is used for the spaceborne computer to select a basic mathematical processing method, and comprises upper and lower boundary judgment, mean value statistics, standard deviation statistics and change rate calculation; the satellite-borne computer stores information data which needs to be subjected to trend judgment according to long-term data in a memory by taking a parameter code as a retrieval mark, and calculates the change rate at regular time;
and (3) carrying out standardized design on the fault event packet, receiving the telemetering parameters sent by the load by the spaceborne computer, carrying out health judgment according to the parameter types, and writing the judgment result into a universal fault event packet, wherein the fault event packet comprises the number of 2-bit fault packets, the parameter code, the 1-bit fault type and a 4-bit time code.
Optionally, in the method for adaptively managing information data of a heterogeneous spacecraft based on a standardized design, the method for writing the fault event package into the on-board computer includes:
for the state quantity parameters: in order to save telemetry resources, the on-board computer only writes a parameter code and an abnormal time code with abnormal states into a fault event packet, and the fault type in the fault packet of the type is 1;
for the statistical quantity parameters: for the telemetering quantity of the calculated mean value, when the amplitude of the mean value jumping exceeds a threshold value, the phenomenon is added into a fault event packet, and the fault type is positioned 2;
for the telemetering amount for calculating the change rate, when the change rate of a certain time length exceeds a threshold value, the phenomenon is added into a fault event packet, and the fault type is determined to be 3;
other types of statistics may be based on actual telemetry statistics of the normalized load and so on.
The inventor of the invention discovers through research that most of the traditional spacecraft data management strategies collect information data of all subsystems through an on-board computer, the information data are downloaded to the ground through a measurement and control channel, and fault diagnosis is carried out on the ground through a special rule format file. The aerospace data management method has the following defects:
and (4) measuring and controlling the waste of channel resources. In the life cycle of the on-orbit operation of the spacecraft, a part of telemetering parameters are in a normal state for long-term display, and a part of telemetering parameters are used for assisting fault diagnosis, so that the resource of a spacecraft measurement and control channel is wasted in a normal operation state.
The human resources consumed by the updating and maintenance of the telemetry data are wasted. With the advance of spacecraft hardware interface standardization technology, a large number of spacecraft have a high possibility of rail hardware replacement and software re-energization during long-life operation. At present, the processing and maintenance of telemetering data are completed together through software and a configuration file, the telemetering processing software relies on the telemetering configuration file to judge the correctness of the data, and the file adopts a traditional manual input and maintenance mode, so that the risk of data editing errors exists while human resources are wasted.
Health management is not real-time enough. At present, most information data of spacecraft health management is downloaded to the ground for processing, and when some spacecraft visual arc sections are short, the spacecraft health management is carried out only through real-time telemetering and mass time-delay telemetering of the visual arc sections, so that the real-time performance of the spacecraft health management is insufficient.
Based on the above insights, the inventor of the present invention finds that, in order to overcome the defects of the prior art, the problem to be solved at present is mainly to provide that the heterogeneous spacecraft needs to have the capabilities of performing standardized design and autonomous interpretation management on an information data format, so as to realize integrated management of information of the heterogeneous spacecraft from system design to autonomous fault diagnosis, and achieve the purpose of improving the autonomous health management efficiency of the heterogeneous spacecraft.
In the heterogeneous spacecraft information data self-adaptive management method based on standardized design, aiming at the problems of complex source structure, complicated category, large information standardization difference among similar design objects and the like of the telemetry data of the heterogeneous spacecraft, a multi-task standard platform is adopted in the design scheme of the invention to carry out standardized design on mechanical, electronic and data interfaces of a payload, and when the heterogeneous spacecraft has on-orbit software function upgrading or hardware has on-orbit assembly and service requirements, newly replaced modules can be quickly detected after different functional modules or the same functional modules are replaced. Meanwhile, the platform and the load information data format of the heterogeneous spacecraft adopt standard and universal compatible technologies, and the spacecraft satellite-borne information transmission system adopts a universal model, so that design standardization and management generalization of replaceable, multi-feature and homogeneous heterogeneous objects are realized.
Drawings
Fig. 1 is a schematic diagram of a heterogeneous spacecraft bus architecture based on a standardized interface design in an embodiment of the present invention;
fig. 2 is a schematic diagram of data flow of information of a heterogeneous spacecraft based on a standardized interface design in an embodiment of the present invention.
Detailed Description
The invention is further elucidated with reference to the drawings in conjunction with the detailed description.
It should be noted that the components in the figures may be exaggerated and not necessarily to scale for illustrative purposes. In the figures, identical or functionally identical components are provided with the same reference symbols.
In the present invention, "disposed on …", "disposed over …" and "disposed over …" do not exclude the presence of an intermediate therebetween, unless otherwise specified. Further, "disposed on or above …" merely indicates the relative positional relationship between two components, and may also be converted to "disposed below or below …" and vice versa in certain cases, such as after reversing the product direction.
In the present invention, the embodiments are only intended to illustrate the aspects of the present invention, and should not be construed as limiting.
In the present invention, the terms "a" and "an" do not exclude the presence of a plurality of elements, unless otherwise specified.
It is further noted herein that in embodiments of the present invention, only a portion of the components or assemblies may be shown for clarity and simplicity, but those of ordinary skill in the art will appreciate that, given the teachings of the present invention, required components or assemblies may be added as needed in a particular scenario. Furthermore, features from different embodiments of the invention may be combined with each other, unless otherwise indicated. For example, a feature of the second embodiment may be substituted for a corresponding or functionally equivalent or similar feature of the first embodiment, and the resulting embodiments are likewise within the scope of the disclosure or recitation of the present application.
It is also noted herein that, within the scope of the present invention, the terms "same", "equal", and the like do not mean that the two values are absolutely equal, but allow some reasonable error, that is, the terms also encompass "substantially the same", "substantially equal". By analogy, in the present invention, the terms "perpendicular", "parallel" and the like in the directions of the tables also cover the meanings of "substantially perpendicular", "substantially parallel".
The numbering of the steps of the methods of the present invention does not limit the order of execution of the steps of the methods. Unless specifically stated, the method steps may be performed in a different order.
The following describes in detail a heterogeneous spacecraft information data adaptive management method based on standardized design according to the present invention with reference to the accompanying drawings and specific embodiments. Advantages and features of the present invention will become apparent from the following description and from the claims. It is to be noted that the drawings are in a very simplified form and are not to precise scale, which is merely for the purpose of facilitating and distinctly claiming the embodiments of the present invention.
The invention aims to provide a heterogeneous spacecraft information data self-adaptive management method based on standardized design, so as to solve the problems of huge artificial load and potential reliability risk caused by the conventional spacecraft telemetering parameter processing.
In order to achieve the purpose, the invention provides a heterogeneous spacecraft information data self-adaptive management method based on standardized design, which comprises the following steps: the multitasking standard platform is configured to standardize the mechanical, electronic and data interfaces of the payload to achieve the following: when the heterogeneous spacecraft is subjected to in-orbit software function upgrading or hardware in-orbit assembly and service requirements, after different functional modules or the same functional module are replaced, the multi-task standard platform can quickly detect a newly replaced module; the data format standard platform is configured to enable the information data formats of the satellite platform and the payload of the heterogeneous spacecraft to adopt a standard and universal data format, and enable the satellite-borne information transmission system of the heterogeneous spacecraft to adopt a universal model so as to realize design standardization and management generalization of the heterogeneous object.
Aiming at the problems of complex structure of telemetry data sources of heterogeneous spacecrafts, complicated and complicated categories, large difference of information standardization among similar design objects and the like, the design scheme of the invention adopts a multi-task standard platform to carry out standardized design on mechanical, electronic and data interfaces of a payload, and when the heterogeneous spacecrafts have on-orbit software function upgrading or hardware has on-orbit assembly and service requirements, different functional modules or the same functional modules can be quickly detected after being replaced. Meanwhile, the platform and the load information data format of the heterogeneous spacecraft adopt standard and universal compatible technologies, and the spacecraft satellite-borne information transmission system adopts a universal model, so that design standardization and management generalization of replaceable, multi-feature and homogeneous heterogeneous objects are realized.
The information data of the spacecraft load can be divided into analog quantity representing the health state of hardware, digital quantity reflecting functional completeness and application data used for function synthesis, a standardized design scheme is adopted for hardware of the heterogeneous spacecraft load, when the function of the heterogeneous spacecraft is changed or on-orbit maintenance and assembly is needed due to hardware faults, after a new module is rapidly detected, analog quantity data acquisition of the new module can be registered, system level functions can be dynamically configured, and health evaluation is carried out on the acquired analog quantity by adopting a universal data structure and a processing method; in addition, when the load function of the heterogeneous spacecraft is changed, the design scheme of the technology adopts a unified data source operation mechanism, can realize standardized health assessment on a functional process by a unified information flow format without depending on manual assistance and ground support, automatically identifies a judgment method of information data health degree, comprises health assessment methods such as trend analysis, boundary detection, mean value inspection, expected value inspection, deviation inspection and the like, and can realize normal operation with strong adaptability by means of spacecraft software self-adaptive standardized design.
The heterogeneous spacecraft load hardware interface adopts a standardized design, as shown in fig. 1, analog quantities of heterogeneous spacecraft are collected through an analog quantity collecting terminal, the analog quantity collecting terminal judges the hardware health state of the heterogeneous spacecraft according to a standardized analog quantity threshold range, and a judgment result is uniformly sent to a satellite-borne computer through a bus. The software function of the load is related to the task of the heterogeneous spacecraft, and after the heterogeneous spacecraft is powered on orbit, the information data related to the function can be used for self-adaptive judgment of the health state through a standardized data interface. The self-adaptive management method for the health degree of the heterogeneous spacecraft by adopting the information data standardization design scheme comprises the following steps:
firstly, the information data structure standardization design technology is included: as shown in fig. 2, the loads with standardized interfaces adopt information data interfaces with generalized design, and as shown in table 1, each load with standardized design sends an information data parameter table representing the health status of a single machine to the satellite-borne computer through a bus, where the parameter table includes the number of parameters, the length of the parameters, the code number of the parameters, the parameter values, the types of the parameters, the statistical manner, and the judgment threshold. Wherein, the parameter code adopts a mode of uniformly arranging sub-addresses and sequence numbers; the parameter type is used for distinguishing the state quantity and the statistic quantity; the statistical method is used for selecting a basic mathematical processing method for the spaceborne computer, and comprises upper and lower boundary judgment, mean value statistics, standard deviation statistics, change rate calculation and the like.
Table 1 information data interface of universal design
The spaceborne computer has a large-capacity storage capacity, information data needing to be subjected to trend judgment according to long-term data are stored in a memory by taking a parameter code as a retrieval mark, and the change rate is calculated at regular time.
Secondly, the method comprises the following standardized design technology of the fault event package: as shown in fig. 2, the on-board computer receives the telemetry parameters sent by the load, performs health judgment according to the parameter type, and writes the judgment result into a generalized fault event packet, as shown in table 2:
TABLE 2 generalized design of failure event packages
As shown in fig. 2, the method for writing the fault event packet by the on-board computer includes:
for the state quantity parameters: in order to save telemetry resources, the on-board computer only writes the parameter code and the abnormal time code with abnormal states in the fault event package. The failure type in this type of failure packet is set to 1.
For the statistical quantity parameters: for the telemetering quantity of the calculated mean value, when the amplitude of the mean value jumping exceeds a threshold value, the phenomenon is added into a fault event packet, and the fault type is positioned 2; for the telemetering amount for calculating the change rate, when the change rate of a certain time length exceeds a threshold value, the phenomenon is added into a fault event packet, and the fault type is determined to be 3; other types of statistics may be based on actual telemetry statistics of the normalized load and so on.
The invention provides a heterogeneous spacecraft self-adaptive management technology based on information data standardized design, which has the innovation points and advantages that:
the method comprises the steps that information data of the heterogeneous spacecraft are subjected to standardized classification, namely analog quantity used for representing basic health state of hardware, statistic quantity used for predicting aging trend of the hardware, state quantity used for rapid diagnosis and mass data used for application function generation, and when the heterogeneous spacecraft is in orbit energized, self-adaptive management of the health state is automatically completed through an information data format and a processing method which are designed in a standardized mode without ground intervention;
heterogeneous spacecraft loads are subjected to on-orbit plug and play based on hardware standardized design, analog quantity is automatically collected, and self-adaptive health state judgment is carried out through a standard threshold range;
the heterogeneous spacecraft load realizes the on-orbit self-adaptive operation of satellite-borne autonomous health management software based on the data interface standardized design;
and in the telemetering parameters, only the fault event packet and massive application data generated by load application are downloaded in real time, so that the waste of measurement and control resources is greatly reduced.
In summary, the foregoing embodiments have described in detail different configurations of the heterogeneous spacecraft information data adaptive management method based on standardized design, and it is understood that the present invention includes, but is not limited to, the configurations listed in the foregoing embodiments, and any content that is transformed based on the configurations provided by the foregoing embodiments falls within the scope of the present invention. One skilled in the art can take the contents of the above embodiments to take a counter-measure.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. For the system disclosed by the embodiment, the description is relatively simple because the system corresponds to the method disclosed by the embodiment, and the relevant points can be referred to the method part for description.
The above description is only for the purpose of describing the preferred embodiments of the present invention, and is not intended to limit the scope of the present invention, and any variations and modifications made by those skilled in the art based on the above disclosure are within the scope of the appended claims.
Claims (10)
1. A heterogeneous spacecraft information data self-adaptive management method based on standardized design is characterized by comprising the following steps:
the multitasking standard platform is configured to standardize the mechanical, electronic and data interfaces of the payload to achieve the following:
when the heterogeneous spacecraft is subjected to in-orbit software function upgrading or hardware in-orbit assembly and service requirements, after different functional modules or the same functional module are replaced, the multi-task standard platform can quickly detect a newly replaced module;
the data format standard platform is configured to enable the information data formats of the satellite platform and the payload of the heterogeneous spacecraft to adopt a standard and universal data format, and enable the satellite-borne information transmission system of the heterogeneous spacecraft to adopt a universal model so as to realize design standardization and management generalization of the heterogeneous object.
2. The standardized design-based heterogeneous spacecraft information data adaptive management method of claim 1, wherein the data format standard platform is further configured to:
information data of the heterogeneous spacecraft are standardized and classified, and the information data are divided into: analog quantity used for characterizing hardware basic health status, statistic quantity used for predicting hardware aging trend, state quantity used for rapid diagnosis and massive data used for application function generation, so as to realize the following effects:
when the heterogeneous spacecraft is energized in orbit, the self-adaptive management of the health state is automatically completed through an information data format and a processing method which are designed in a standardized way without the help of ground intervention.
3. The standardized design-based heterogeneous spacecraft information data adaptive management method of claim 2, wherein a payload of a heterogeneous spacecraft is configured to:
on the basis of the standardized design of a mechanical interface and an electronic interface, on-track plug and play, automatic analog quantity acquisition and self-adaptive health state judgment through a standard threshold range are realized; and
the on-orbit self-adaptive operation of the satellite-borne autonomous health management software is realized based on the data interface standardized design.
4. The adaptive management method for the information data of the heterogeneous spacecraft based on the standardized design as claimed in claim 3, wherein the heterogeneous spacecraft only downloads the fault event package in the telemetry parameters and massive application data generated by the load application in real time so as to greatly reduce the waste of measurement and control resources.
5. The adaptive management method for information data of the heterogeneous spacecraft based on the standardized design as claimed in claim 3, wherein the information data of the payload of the heterogeneous spacecraft is divided into analog quantity for representing the health state of hardware, digital quantity for embodying the completeness of functions and application data for function synthesis, so that the information data formats of the satellite platform and the payload of the heterogeneous spacecraft can adopt a normative and general data format, and the information transmission system on board the satellite of the heterogeneous spacecraft adopts a general model.
6. The heterogeneous spacecraft information data adaptive management method based on standardized design according to claim 5, is characterized in that standardized design is adopted for hardware interfaces of payloads of heterogeneous spacecraft so as to realize the following functions:
when the functions of the heterogeneous spacecraft are changed or the in-orbit maintenance and assembly is needed due to hardware faults, after a new module is quickly detected, the analog quantity data acquisition of the new module can be registered, the system level functions can be dynamically configured, and the health evaluation is carried out on the acquired analog quantity by adopting a universal data structure and a processing method; and
when the payload functions of the heterogeneous spacecraft are changed, a unified data source operation mechanism is adopted, so that the following effects can be realized:
the method for judging the health degree of the information data automatically identifies the judgment method of the health degree of the information data by realizing the standardized health evaluation of the functional flow through a unified information flow format without depending on manual assistance and ground support, wherein the judgment method of the health degree comprises trend analysis, boundary detection, mean value inspection, expected value inspection and deviation inspection, and can realize the normal operation with strong adaptability by depending on the adaptive standardized design of spacecraft software.
7. The heterogeneous spacecraft information data adaptive management method based on standardized design according to claim 6, wherein the hardware interface of the payload of the heterogeneous spacecraft adopts standardized design, and comprises the following steps:
the analog quantity of the heterogeneous spacecraft is collected through the analog quantity collecting terminal, the analog quantity collecting terminal judges the hardware health state of the heterogeneous spacecraft according to the standard analog quantity threshold range, and the judgment result is sent to the satellite-borne computer through the bus in a unified mode.
8. The heterogeneous spacecraft information data adaptive management method based on standardized design according to claim 2,
the software function of the payload is related to the task of the heterogeneous spacecraft, and after the heterogeneous spacecraft is energized in orbit, the information data related to the function is subjected to self-adaptive judgment of the health state through a standardized data interface.
9. The heterogeneous spacecraft information data adaptive management method based on standardized design according to claim 2, wherein the heterogeneous spacecraft adopts information data standardization for adaptive management of health of the heterogeneous spacecraft comprises:
carrying out standardized design on an information data structure, wherein loads with standardized interfaces adopt information data interfaces with generalized design, each load with standardized design sends an information data parameter table representing the health state of a single machine to a satellite borne computer through a bus, and the parameter table comprises 2-bit parameter number, parameter length, parameter code number, 4-bit parameter value, parameter type, statistical mode and judgment threshold, wherein the judgment threshold comprises an upper boundary and a lower boundary; wherein, the parameter code adopts a mode of uniformly arranging sub-addresses and sequence numbers; the parameter type is used for distinguishing the state quantity and the statistic quantity; the statistical mode is used for the spaceborne computer to select a basic mathematical processing method, and comprises upper and lower boundary judgment, mean value statistics, standard deviation statistics and change rate calculation; the satellite-borne computer stores information data which needs to be subjected to trend judgment according to long-term data in a memory by taking a parameter code as a retrieval mark, and calculates the change rate at regular time;
and (3) carrying out standardized design on the fault event packet, receiving the telemetering parameters sent by the load by the spaceborne computer, carrying out health judgment according to the parameter types, and writing the judgment result into a universal fault event packet, wherein the fault event packet comprises the number of 2-bit fault packets, the parameter code, the 1-bit fault type and a 4-bit time code.
10. The heterogeneous spacecraft information data adaptive management method based on standardized design according to claim 9, wherein the method for writing the fault event package by the on-board computer comprises the following steps:
for the state quantity parameters: in order to save telemetry resources, the on-board computer only writes a parameter code and an abnormal time code with abnormal states into a fault event packet, and the fault type in the fault packet of the type is 1;
for the statistical quantity parameters: for the telemetering quantity of the calculated mean value, when the amplitude of the mean value jumping exceeds a threshold value, the phenomenon is added into a fault event packet, and the fault type is positioned 2;
for the telemetering amount for calculating the change rate, when the change rate of a certain time length exceeds a threshold value, the phenomenon is added into a fault event packet, and the fault type is determined to be 3;
other types of statistics may be based on actual telemetry statistics of the normalized load and so on.
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