Adaptive management method for health of heterogeneous spacecraft

Abstract

The present invention provides an adaptive management method for the health of heterogeneous spacecraft, comprising: heterogeneous spacecraft adopt information data standardization for adaptive management of the health of heterogeneous spacecraft; heterogeneous spacecraft adopt information data standardization including standardized design of information data structure, payloads with standardized interfaces adopt universally designed information data interfaces, each standardized designed payload sends an information data parameter table representing the health status of a single machine to an onboard computer through a bus, the parameter table comprising the number of parameters, parameter length, parameter code, parameter value, parameter type, statistical method and judgment threshold; wherein the parameter code adopts a uniform arrangement of sub-addresses and sequence numbers; the parameter type is used to distinguish between state quantities and statistical quantities; the statistical method provides the onboard computer with a basic mathematical processing method, comprising upper and lower boundary judgments, mean statistics, standard deviation statistics, and change rate calculation.

Description

Technical Field

[0001] The present invention relates to the technical field of autonomous health management of spacecraft, and in particular to an adaptive management method for the health of heterogeneous spacecraft. Background Art

[0002] With the development of spacecraft intelligent technology and artificial intelligence, as well as the improvement of spacecraft on-orbit empowerment technology, the on-board computer has greatly improved its information data processing and management capabilities for various subsystems of heterogeneous spacecraft, which provides a good technical foundation for the adaptive intelligent management of heterogeneous spacecraft information data. In addition, with the widespread application of payload digitalization technology on spacecraft and the introduction of spacecraft on-orbit service application technology, on-orbit empowerment of spacecraft software and hardware will become more and more common and frequent, and at the same time, it will bring about a faster update frequency of heterogeneous spacecraft information data.

[0003] The information data of spacecraft contains the important status of each subsystem of the spacecraft, reflects the performance characteristics or functional status of the spacecraft, and is an important basis for health diagnosis and fault prediction of the spacecraft. At present, the analysis and judgment of spacecraft information data depends on the data type, threshold range, and data processing method of telemetry parameters, and all of these contents come from the manual editing and updating of special format files by ground staff. When the number of telemetry parameters increases, the number of heterogeneous spacecraft is increasing, the functions of each spacecraft payload are different, and the functions of heterogeneous spacecraft are frequently updated, the re-editing of format files will bring huge manual load and potential reliability risks. Summary of the invention

[0004] The purpose of the present invention is to provide an adaptive management method for the health of heterogeneous spacecraft to solve the problem that the existing spacecraft telemetry parameter processing brings huge manual load and potential reliability risks.

[0005] In order to solve the above technical problems, the present invention provides an adaptive management method for the health of heterogeneous spacecraft, comprising:

[0006] Heterogeneous spacecraft adopts information data standardization for adaptive management of heterogeneous spacecraft health;

[0007] The information data standardization adopted by heterogeneous spacecraft includes the standardized design of information data structure. The payloads with standardized interfaces adopt the universally designed information data interface. Each standardized designed payload sends the information data parameter table representing the health status of the single machine to the onboard computer through the bus. The parameter table includes the number of parameters, parameter length, parameter code, parameter value, parameter type, statistical method and judgment threshold.

[0008] Among them, the parameter code is uniformly arranged in the form of sub-addresses and sequence numbers; the parameter type is used to distinguish state quantities and statistical quantities; the statistical method is used for the onboard computer to select basic mathematical processing methods, including upper and lower boundary judgments, mean statistics, standard deviation statistics, and rate of change calculations.

[0009] Optionally, in the adaptive management method for heterogeneous spacecraft health,

[0010] The parameter table includes 2 bits of parameter quantity, parameter length, parameter code, and 4 bits of parameter value, parameter type, statistical method, and judgment threshold, wherein the judgment threshold includes an upper boundary and a lower boundary;

[0011] The storage capacity of the onboard computer allows information data that needs to be judged based on long-term data to be stored in the memory using parameter codes as retrieval marks, and the rate of change is calculated regularly.

[0012] Optionally, in the adaptive management method for the health of heterogeneous spacecraft, the heterogeneous spacecraft adopting information data standardization further includes:

[0013] Standardized fault event package design is carried out. The onboard computer receives the telemetry parameters sent by the payload, makes health judgments based on the parameter types, and then writes the judgment results into a universal fault event package.

[0014] The fault event packet contains a 2-bit fault packet number, a parameter code, a 1-bit fault type, and a 4-bit time code.

[0015] Optionally, in the adaptive management method for the health of heterogeneous spacecraft, the method for writing a fault event package by an onboard computer includes:

[0016] For state quantity parameters: In order to save telemetry resources, the onboard computer only writes the parameter code and abnormal time code of the abnormal state in the fault event package. The fault type in this type of fault package is set to 1;

[0017] For statistical parameters: For telemetry of calculating the mean, when the amplitude of the mean jump exceeds the threshold value, this phenomenon is added to the fault event package, and the fault type is located 2;

[0018] For telemetry that calculates the rate of change, when the rate of change for a certain period of time exceeds the threshold value, this phenomenon is added to the fault event package and the fault type is set to 3;

[0019] Other types of statistics can be deduced based on the actual telemetry statistics of the standardized payload.

[0020] Optionally, in the adaptive management method of the health of heterogeneous spacecraft, in view of the complex structure of the source of telemetry data of heterogeneous spacecraft, the intricate and redundant categories, and the large difference in information standardization between similar design objects, a multi-task standard platform is used to standardize the mechanical, electronic and data interfaces of the payload. When the heterogeneous spacecraft has an on-orbit software function upgrade or the hardware has an on-orbit assembly and service requirement, after different functional modules or the same functional modules are replaced, the newly replaced modules can be quickly detected;

[0021] The platform and payload information data formats of heterogeneous spacecraft adopt standardized and universal compatible technologies, and the spacecraft onboard information transmission system adopts a universal model, thereby achieving standardized design and universal management of replaceable, multi-feature, and similar heterogeneous objects.

[0022] Optionally, in the adaptive management method for the health of heterogeneous spacecraft, the information data of the spacecraft payload is divided into analog quantities representing the health status of the hardware, digital quantities reflecting the functional completeness, and application data for functional synthesis. A standardized design scheme is adopted for the hardware of the heterogeneous spacecraft payload. When the function of the heterogeneous spacecraft changes or needs to be repaired and assembled on-orbit due to hardware failure, after quickly detecting the new module, the analog data collection of the new module is registered, the system-level function is dynamically configured, and the collected analog quantities are evaluated for health using a common data structure and processing method;

[0023] When the functions of heterogeneous spacecraft payloads change, a unified data source operation mechanism is adopted, and a standardized health assessment of the functional process is implemented in a unified information flow format. The method for judging the health of information data is automatically identified. The health assessment methods include trend analysis, boundary detection, mean check, expected value check, and deviation check. Through the adaptive standardized design of spacecraft software, highly adaptable normal operation can be achieved.

[0024] Optionally, in the adaptive management method for the health of heterogeneous spacecraft, the hardware interface of the heterogeneous spacecraft payload adopts a standardized design, the analog quantities of the heterogeneous spacecraft are all collected through an analog quantity acquisition terminal, the analog quantity acquisition terminal judges the hardware health status of the heterogeneous spacecraft according to a standardized analog quantity threshold range, and the judgment result is sent to the onboard computer through a bus; the software function of the payload is related to the mission of the heterogeneous spacecraft. When the heterogeneous spacecraft is enabled on orbit, the information data related to its function can be used through a standardized data interface to adaptively judge the health status.

[0025] Optionally, in the adaptive management method for heterogeneous spacecraft health, the data format standard platform is further configured as:

[0026] The information data of heterogeneous spacecraft is standardized and classified into: analog quantities used to characterize the basic health status of hardware, statistical quantities used to predict hardware aging trends, state quantities used for rapid diagnosis, and massive data used to generate application functions, in order to achieve the following effects:

[0027] When heterogeneous spacecraft are enabled in orbit, they can autonomously complete adaptive management of their health status through standardized information data formats and processing methods without ground intervention.

[0028] Optionally, in the adaptive management method for the health of heterogeneous spacecraft, the payload of the heterogeneous spacecraft is configured as:

[0029] Based on the standardized design of mechanical and electronic interfaces, it can realize plug-and-play on-orbit, automatically collect analog quantities, and perform adaptive health status judgment through standard threshold ranges; and

[0030] Based on the standardized design of data interface, the on-orbit adaptive operation of the onboard autonomous health management software is realized.

[0031] Optionally, in the adaptive management method for the health of heterogeneous spacecraft, the heterogeneous spacecraft only transmits fault event packages in telemetry parameters and massive application data generated for payload applications in real time, so as to significantly reduce the waste of measurement and control resources.

[0032] Optionally, in the adaptive management method for the health of heterogeneous spacecraft, the information data of the payload of the heterogeneous spacecraft is divided into analog quantities characterizing the health status of the hardware, digital quantities reflecting functional completeness, and application data for functional synthesis, so that the information data format of the satellite platform and payload of the heterogeneous spacecraft can adopt a standardized and universal data format, and the onboard information transmission system of the heterogeneous spacecraft can adopt a universal model.

[0033] Optionally, in the adaptive management method for the health of heterogeneous spacecraft, a standardized design is adopted for the hardware interface of the payload of the heterogeneous spacecraft to achieve the following functions:

[0034] When the functions of heterogeneous spacecraft change or require on-orbit repair and assembly due to hardware failure, it is possible to quickly detect the new module, register the analog data collection of the new module, dynamically configure system-level functions, and use common data structures and processing methods to perform health assessments on the collected analog quantities; and

[0035] When the payload functions of heterogeneous spacecraft change, a unified data source operation mechanism is used to achieve the following effects:

[0036] It does not rely on human assistance and ground support, and uses a unified information flow format to achieve standardized health assessment of functional processes. It automatically identifies methods for determining the health of information data. The health determination methods include trend analysis, boundary detection, mean check, expected value check, and deviation check. It can rely on the adaptive standardized design of spacecraft software to achieve highly adaptable normal operation.

[0037] Optionally, in the adaptive management method for the health of heterogeneous spacecraft, the hardware interface of the payload of the heterogeneous spacecraft adopts a standardized design including:

[0038] The analog quantities of heterogeneous spacecraft are all collected through analog quantity acquisition terminals. The analog quantity acquisition terminals judge the hardware health status of heterogeneous spacecraft according to the standardized analog quantity threshold range, and the judgment results are sent to the onboard computer through the bus.

[0039] Optionally, in the adaptive management method for the health of heterogeneous spacecraft, the software functions of the payload are related to the missions of the heterogeneous spacecraft. When the heterogeneous spacecraft is enabled on orbit, information data related to its functions are used through standardized data interfaces to perform adaptive judgment on its health status.

[0040] The inventor of the present invention has found through research that the traditional spacecraft data management strategy mostly collects information data of each subsystem through the onboard computer, transmits it to the ground through the measurement and control channel, and performs fault diagnosis on the ground through a special rule format file. This spacecraft data management method has the following defects:

[0041] Waste of measurement and control channel resources. During the life cycle of a spacecraft in orbit, some telemetry parameters show normal status for a long time, and some telemetry parameters are used to assist fault diagnosis, which leads to the waste of spacecraft measurement and control channel resources under normal operation.

[0042] Waste of human resources in updating and maintaining telemetry data. With the advancement of spacecraft hardware interface standardization technology, a large number of spacecraft are very likely to experience on-orbit hardware replacement and software re-enabling during their long-life operation. Currently, the processing and maintenance of telemetry data are completed through software and configuration files. The telemetry processing software relies on the telemetry configuration file to judge the correctness of the data, and the file uses the traditional manual input and maintenance mode, which wastes human resources and also poses the risk of data editing errors.

[0043] The health management is not real-time enough. The current status of spacecraft health management is to transmit most of the information data to the ground for processing. When the visible arc of some spacecraft is short, the spacecraft health management is only carried out through real-time telemetry of the visible arc and a large amount of delayed telemetry, which will cause the spacecraft health management to be not real-time enough.

[0044] Based on the above insights, the inventors of the present invention found that in order to overcome the shortcomings of the prior art, the key problem that needs to be solved currently is to propose that heterogeneous spacecraft must have the ability to standardize the design of information data formats and autonomously interpret and manage them, thereby realizing integrated management of heterogeneous spacecraft information from system design to autonomous fault diagnosis, so as to achieve the purpose of improving the efficiency of autonomous health management of heterogeneous spacecraft.

[0045] In the adaptive management method of the health of heterogeneous spacecraft provided by the present invention, in view of the problems of complex structure of the source of telemetry data of heterogeneous spacecraft, complicated and redundant categories, and large differences in information standardization between similar design objects, the design scheme of the present invention intends to adopt a multi-task standard platform to standardize the mechanical, electronic and data interfaces of the payload. When the heterogeneous spacecraft has an on-orbit software function upgrade or the hardware has on-orbit assembly and service requirements, after different functional modules or the same functional modules are replaced, the newly replaced modules can be quickly detected. At the same time, the platform and payload information data format of the heterogeneous spacecraft adopts standardized and universal compatible technology, and the spacecraft onboard information transmission system adopts a universal model, thereby realizing the design standardization and management universalization of replaceable, multi-feature, and similar heterogeneous objects. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] Figure 1 is a schematic diagram of a heterogeneous spacecraft bus architecture based on a standardized interface design in one embodiment of the present invention;

[0047] Figure 2 It is a schematic diagram of heterogeneous spacecraft information data flow based on standardized interface design in one embodiment of the present invention. DETAILED DESCRIPTION

[0048] The present invention will be further described below in conjunction with specific embodiments with reference to the accompanying drawings.

[0049] It should be noted that the components in the figures may be shown exaggeratedly for the sake of illustration and are not necessarily true to scale. In the figures, identical or functionally identical components are provided with the same reference numerals.

[0050] In the present invention, unless otherwise specified, "arranged on...", "arranged above..." and "arranged above..." do not exclude the existence of an intermediate between the two. In addition, "arranged on or above..." merely indicates the relative positional relationship between two components, and in certain cases, such as after reversing the product direction, it can also be converted into "arranged below or below...", and vice versa.

[0051] In the present invention, each embodiment is only intended to illustrate the aspects of the present invention and should not be construed as limiting.

[0052] In the present invention, unless otherwise specified, the quantifiers "a", "an" and "an" do not exclude the presence of a plurality of elements.

[0053] It should also be noted that in the embodiments of the present invention, for the sake of clarity and simplicity, only a portion of the parts or components may be shown, but those of ordinary skill in the art will understand that under the teachings of the present invention, the required parts or components may be added according to the needs of the specific scenario. In addition, unless otherwise specified, the features in different embodiments of the present invention may be combined with each other. For example, a feature in the second embodiment may be used to replace a corresponding or functionally identical or similar feature in the first embodiment, and the resulting embodiment also falls within the disclosure scope or recorded scope of the present application.

[0054] It should also be noted that within the scope of the present invention, the terms "same", "equal", "equal to" and the like do not mean that the values ​​of the two are absolutely equal, but allow a certain reasonable error, that is, the terms also cover "substantially the same", "substantially equal", "substantially equal to". By analogy, in the present invention, the terms "perpendicular to", "parallel to" and the like indicating directions also cover the meanings of "substantially perpendicular to" and "substantially parallel to".

[0055] In addition, the numbering of the steps of the methods of the present invention does not limit the execution order of the method steps. Unless otherwise specified, the method steps can be executed in different orders.

[0056] The following is a further detailed description of the adaptive management method for the health of heterogeneous spacecraft proposed in the present invention in conjunction with the accompanying drawings and specific embodiments. The advantages and features of the present invention will become more apparent from the following description and claims. It should be noted that the accompanying drawings are in a very simplified form and are not in precise proportions, and are only used to conveniently and clearly assist in explaining the purpose of the embodiments of the present invention.

[0057] The purpose of the present invention is to provide an adaptive management method for the health of heterogeneous spacecraft to solve the problem that the existing spacecraft telemetry parameter processing brings huge manual load and potential reliability risks.

[0058] To achieve the above-mentioned objectives, the present invention provides an adaptive management method for the health of heterogeneous spacecraft, comprising: a multi-task standard platform is configured to perform standardized design on the mechanical interface, electronic interface and data interface of the payload, so as to achieve the following effects: when the heterogeneous spacecraft undergoes on-orbit software function upgrades or on-orbit hardware assembly and service requirements, after different functional modules or the same functional modules are replaced, the multi-task standard platform can quickly detect the newly replaced modules; the data format standard platform is configured to make the information data format of the satellite platform and payload of the heterogeneous spacecraft adopt a standardized and universal data format, and to make the onboard information transmission system of the heterogeneous spacecraft adopt a universal model, so as to realize the standardization of the design and universal management of heterogeneous objects.

[0059] In view of the problems of complex structure of telemetry data sources of heterogeneous spacecraft, complicated and redundant categories, and large differences in information standardization between similar design objects, the design scheme of the present invention intends to adopt a multi-task standard platform to standardize the mechanical, electronic and data interfaces of the payload. When the heterogeneous spacecraft has on-orbit software function upgrades or the hardware has on-orbit assembly and service requirements, after different functional modules or the same functional modules are replaced, the newly replaced modules can be quickly detected. At the same time, the platform and payload information data format of heterogeneous spacecraft adopts standardized and universal compatible technology, and the spacecraft onboard information transmission system adopts a universal model, so as to realize the design standardization and management generalization of replaceable, multi-feature, and similar heterogeneous objects.

[0060] The information data of spacecraft payloads can be divided into analog quantities that characterize the health status of hardware, digital quantities that reflect functional completeness, and application data for functional synthesis. A standardized design scheme is adopted for the hardware of heterogeneous spacecraft payloads. When the functions of heterogeneous spacecraft change or in-orbit maintenance and assembly is required due to hardware failure, the analog data collection of the new module can be registered after the new module is quickly detected, the system-level functions can be dynamically configured, and the collected analog quantities can be evaluated for health using a common data structure and processing method. In addition, when the functions of heterogeneous spacecraft payloads change, the design scheme of this technology adopts a unified data source operation mechanism, which can achieve standardized health assessment of functional processes in a unified information flow format without relying on manual assistance and ground support, and automatically identify methods for judging the health of information data, including trend analysis, boundary detection, mean check, expected value check, deviation check and other health assessment methods, that is, it can rely on the adaptive standardized design of spacecraft software to achieve highly adaptable normal operation.

[0061] Heterogeneous spacecraft payload hardware interfaces adopt standardized designs, such as Figure 1As shown, the analog quantities of heterogeneous spacecraft are collected through analog quantity acquisition terminals. The analog quantity acquisition terminals judge the hardware health status of heterogeneous spacecraft according to the standardized analog quantity threshold range, and the judgment results are sent to the onboard computer through the bus. The software functions of the payload are related to the missions of the heterogeneous spacecraft. When the heterogeneous spacecraft is enabled on orbit, the information data related to its functions can be adaptively judged for its health status through standardized data interfaces. The adaptive management methods for the health of heterogeneous spacecraft using information data standardization design schemes are as follows:

[0062] First, it includes information data structure standardization design technology: such as Figure 2 As shown in Table 1, the payload with a standardized interface adopts a universally designed information data interface. Each standardized designed payload sends an information data parameter table representing the health status of a single machine to the onboard computer through the bus. The parameter table includes the number of parameters, parameter length, parameter code, parameter value, parameter type, statistical method, and judgment threshold. Among them, the parameter code is uniformly arranged in a sub-address and sequence number; the parameter type is used to distinguish between state quantities and statistical quantities; the statistical method is used for the onboard computer to select basic mathematical processing methods, including upper and lower boundary judgments, mean statistics, standard deviation statistics, and change rate calculations.

[0063] Table 1 Information data interface of universal design

[0064]

[0065] The onboard computer has a large storage capacity. For information data that needs to be judged based on long-term data, it is stored in the memory using the parameter code as the retrieval mark and the rate of change is calculated regularly.

[0066] Secondly, it includes the standardized design technology of fault event packages: such as Figure 2 As shown in Table 2, the onboard computer receives the telemetry parameters sent by the payload, makes a health judgment based on the parameter type, and then writes the judgment result into a generalized fault event package, as shown in Table 2:

[0067] Table 2 Fault event package of universal design

[0068]

[0069]

[0070] like Figure 2 As shown in the figure, the methods for writing fault event packages to the onboard computer are:

[0071] For state quantity parameters: In order to save telemetry resources, the onboard computer only writes the parameter code and abnormal time code of the abnormal state in the fault event package. The fault type in this type of fault package is set to 1.

[0072] Regarding statistical parameters: for telemetry that calculates the mean, when the amplitude of the mean jump exceeds the threshold value, this phenomenon is added to the fault event package, and the fault type is located as 2; for telemetry that calculates the rate of change, when the rate of change for a certain period of time exceeds the threshold value, this phenomenon is added to the fault event package, and the fault type is determined as 3; other types of statistics can be deduced accordingly based on the actual telemetry statistical method of the standardized load.

[0073] The present invention proposes a heterogeneous spacecraft adaptive management technology based on information data standardization design, and its innovations and advantages are:

[0074] The information data of heterogeneous spacecraft are standardized and classified, namely, analog quantities used to characterize the basic health status of hardware, statistical quantities used to predict the aging trend of hardware, state quantities used for rapid diagnosis, and massive data used for application function generation. When heterogeneous spacecraft are enabled in orbit, they can complete the adaptive management of their health status through standardized information data formats and processing methods without ground intervention.

[0075] Heterogeneous spacecraft payloads are plug-and-play on-orbit based on hardware standardization design, automatically collect analog quantities and perform adaptive health status judgment through standard threshold ranges;

[0076] Heterogeneous spacecraft payloads realize on-orbit adaptive operation of onboard autonomous health management software based on standardized design of data interfaces;

[0077] Among the telemetry parameters, only fault event packages and massive application data generated for payload applications are transmitted in real time, which greatly reduces the waste of measurement and control resources.

[0078] In summary, the above embodiments describe in detail different configurations of the adaptive management method for the health of heterogeneous spacecraft. Of course, the present invention includes but is not limited to the configurations listed in the above embodiments. Any content that is transformed based on the configurations provided in the above embodiments belongs to the scope of protection of the present invention. Those skilled in the art can draw inferences based on the contents of the above embodiments.

[0079] In this specification, each embodiment is described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the embodiments can be referred to each other. For the system disclosed in the embodiment, since it corresponds to the method disclosed in the embodiment, the description is relatively simple, and the relevant parts can be referred to the method part.

[0080] The above description is only a description of the preferred embodiments of the present invention, and is not intended to limit the scope of the present invention. Any changes or modifications made by a person skilled in the art in the field of the present invention based on the above disclosure shall fall within the scope of protection of the claims.

Claims

1. An adaptive management method for the health of heterogeneous spacecraft, characterized in that: include: Heterogeneous spacecraft adopts information data standardization for adaptive management of heterogeneous spacecraft health; The information data standardization adopted by heterogeneous spacecraft includes the standardized design of information data structure. The payloads with standardized interfaces adopt the universally designed information data interface. Each standardized designed payload sends the information data parameter table representing the health status of the single machine to the onboard computer through the bus. The parameter table includes the number of parameters, parameter length, parameter code, parameter value, parameter type, statistical method and judgment threshold. Among them, the parameter code is arranged in a unified manner using sub-addresses and sequence numbers; the parameter type is used to distinguish state quantities and statistical quantities; the statistical method is used for the onboard computer to select basic mathematical processing methods, including upper and lower boundary judgments, mean statistics, standard deviation statistics, and change rate calculations; The parameter table includes 2 bits of parameter quantity, parameter length, parameter code, and 4 bits of parameter value, parameter type, statistical method, and judgment threshold, wherein the judgment threshold includes an upper boundary and a lower boundary; The storage capacity of the onboard computer allows information data that needs to be judged based on long-term data to be stored in the memory with parameter codes as retrieval marks, and the rate of change is calculated regularly; The information data standardization adopted by heterogeneous spacecraft also includes: Standardized fault event package design is carried out. The onboard computer receives the telemetry parameters sent by the payload, makes health judgments based on the parameter types, and then writes the judgment results into a universal fault event package. The fault event packet contains 2 bits of fault packet number, parameter code, 1 bit of fault type, and 4 bits of time code; The method for writing the fault event package into the onboard computer includes: For state quantity parameters: In order to save telemetry resources, the onboard computer only writes the parameter code and abnormal time code of the abnormal state in the fault event package. The fault type in this type of fault package is set to 1; For statistical parameters: For telemetry of calculating the mean, when the amplitude of the mean jump exceeds the threshold value, this phenomenon is added to the fault event package, and the fault type is located 2; For telemetry that calculates the rate of change, when the rate of change for a certain period of time exceeds the threshold value, this phenomenon is added to the fault event package and the fault type is set to 3; Other types of statistics can be deduced based on the actual telemetry statistics of the standardized payload.

2. The adaptive management method for the health of heterogeneous spacecraft according to claim 1, characterized in that: In view of the complex structure of telemetry data sources of heterogeneous spacecraft, the intricate and redundant categories, and the large differences in information standardization between similar design objects, a multi-task standard platform is used to standardize the mechanical, electronic and data interfaces of the payload. When the heterogeneous spacecraft has on-orbit software function upgrades or the hardware has on-orbit assembly and service requirements, after different functional modules or the same functional modules are replaced, the newly replaced modules can be quickly detected; The platform and payload information data formats of heterogeneous spacecraft adopt standardized and universal compatible technologies, and the spacecraft onboard information transmission system adopts a universal model, thereby achieving standardized design and universal management of replaceable, multi-feature, and similar heterogeneous objects.

3. The adaptive management method for the health of heterogeneous spacecraft according to claim 2, characterized in that: The information data of spacecraft payloads are divided into analog quantities that represent the health status of hardware, digital quantities that reflect functional completeness, and application data for functional synthesis. A standardized design scheme is adopted for the hardware of heterogeneous spacecraft payloads. When the functions of heterogeneous spacecraft change or in-orbit maintenance and assembly are required due to hardware failure, after quickly detecting the new module, the analog data collection of the new module is registered, the system-level functions are dynamically configured, and the collected analog quantities are evaluated for health using a common data structure and processing method; When the functions of heterogeneous spacecraft payloads change, a unified data source operation mechanism is adopted, and a standardized health assessment of the functional process is implemented in a unified information flow format. The method for judging the health of information data is automatically identified. The health assessment methods include trend analysis, boundary detection, mean check, expected value check, and deviation check. Through the adaptive standardized design of spacecraft software, highly adaptable normal operation can be achieved.

4. The adaptive management method for the health of heterogeneous spacecraft according to claim 3, characterized in that: The hardware interface of heterogeneous spacecraft payloads adopts a standardized design. The analog quantities of heterogeneous spacecraft are all collected through analog quantity acquisition terminals. The analog quantity acquisition terminals judge the hardware health status of the heterogeneous spacecraft according to the standardized analog quantity threshold range, and the judgment results are sent to the onboard computer through the bus. The software functions of the payload are related to the missions of the heterogeneous spacecraft. When the heterogeneous spacecraft is enabled in orbit, the information data related to its functions can be used for adaptive judgment of its health status through standardized data interfaces.

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