Integrated spacecraft payload telemetry data acquisition method, device, equipment and medium

Abstract

The present invention discloses an integrated spacecraft payload telemetry data acquisition method, device, equipment and medium, the method comprising: receiving status result information sent by each subsystem under different working states of the payload; parsing the status result information and injecting different identifiers according to the type of the status result information, converting it into payload telemetry data; sending the payload telemetry data to a receiving end. The present invention can simultaneously meet the requirements of high efficiency, real-time and integrity of integrated spacecraft payload telemetry.

Description

Technical Field

[0001] The present invention belongs to the field of aerospace telemetry technology, and in particular relates to an integrated spacecraft payload telemetry data acquisition method, device, equipment and medium. Background Art

[0002] Spacecraft payload refers to the instruments, equipment, test pieces, etc. loaded on the spacecraft to directly complete specific tasks.

[0003] Since aerospace equipment is difficult to maintain during operation and has high requirements for system stability, traditional satellite payloads are single-function payloads with fixed functions and single and fixed payload telemetry signal forms. Telemetry data is generally collected according to importance or refresh rate, with few payload collection states and low transmission rate and real-time requirements.

[0004] However, integrated payloads have become the development direction of spacecraft payloads. For integrated payloads running in large spacecraft, the equipment is complex, the working modes and functions are complex, the number and types of collected states are large, the state forms are not fixed, and the requirements for high-throughput and high-real-time information transmission are strong. Traditional telemetry data acquisition methods cannot meet the design requirements of integrated payloads. Summary of the invention

[0005] The purpose of the present invention is to overcome the defects of the prior art and provide a comprehensive spacecraft payload telemetry data acquisition method, device, equipment and medium, which collects different telemetry signals according to the mode of payload operation to improve resource telemetry resource utilization and transmission efficiency.

[0006] The object of the present invention is achieved through the following technical solutions:

[0007] A method for acquiring integrated spacecraft payload telemetry data, the method comprising:

[0008] Receive status result information sent by each subsystem under different working conditions of the load;

[0009] Parsing the status result information and injecting different identifiers according to the status result information type to convert it into payload telemetry data;

[0010] The payload telemetry data is sent to a receiving end.

[0011] Furthermore, the status result information types include remote control command execution result telemetry data, periodic self-test telemetry data, power-on self-test telemetry data and maintenance self-test telemetry data.

[0012] Further, when the status result information type is remote control instruction execution result telemetry data, parsing the status result information and injecting different identifiers according to the status result information type to convert it into payload telemetry data specifically includes:

[0013] Parsing the status result information to obtain the instruction execution result;

[0014] Injecting the subsystem identifier and the instruction type identifier of the remote control instruction into the instruction execution result;

[0015] Corresponding payload telemetry data is generated according to the subsystem identifier of the remote control instruction, the instruction type identifier and the instruction execution result.

[0016] Further, when the status result information type is periodic self-test telemetry data, parsing the status result information and injecting different identifiers according to the status result information type to convert it into load telemetry data specifically includes:

[0017] Analyze the status result information to obtain periodic self-test results of each subsystem;

[0018] Injecting a periodic self-test signal, an identifier of a subsystem performing self-test, and a periodic self-test identifier into the periodic self-test result;

[0019] Corresponding load telemetry data is generated according to the periodic self-test signals of each subsystem, the identification of the subsystem performing the self-test, the periodic self-test identification and the periodic self-test results.

[0020] Further, when the status result information type is power-on self-test telemetry data, parsing the status result information and injecting different identifiers according to the status result information type to convert it into load telemetry data specifically includes:

[0021] Parsing the status result information to obtain a power-on self-test result;

[0022] Injecting a power-on self-test subsystem identifier and a power-on self-test identifier into the power-on self-test result;

[0023] Generate corresponding load telemetry data according to the power-on self-test result, the power-on self-test subsystem identifier and the power-on self-test identifier.

[0024] Furthermore, the power-on self-test telemetry data includes the status of different functional software and hardware modules, including:

[0025] The power-on status, software loading status, and hardware and software initialization status of the hardware modules of the functional platform subsystem within the payload, as well as the software loading status and software initialization status of the functional software subsystem within the payload.

[0026] Further, when the status result information type is maintenance self-test telemetry data, parsing the status result information and injecting different identifiers according to the status result information type to convert it into load telemetry data specifically includes:

[0027] Analyze the status result information to obtain the maintenance self-check result,

[0028] Injecting a maintenance self-check subsystem identifier and a maintenance self-check identifier into the maintenance self-check result;

[0029] Corresponding load telemetry data is generated according to the maintenance self-check result, the maintenance self-check subsystem identifier and the maintenance self-check identifier.

[0030] On the other hand, the present invention provides an integrated spacecraft payload telemetry data acquisition device, the device comprising an instruction issuing module, the instruction issuing module is used to issue instructions to a subsystem in the payload, and the device further comprises:

[0031] Telemetry data receiving module, used to receive status result information returned by subsystems in the payload in different working states;

[0032] A data analysis module is used to analyze the status result information to obtain the corresponding instruction result;

[0033] The identification injection module is used to inject the corresponding identification into the instruction result and generate telemetry data;

[0034] The data transmission module is used to transmit the telemetry data to the receiving end.

[0035] On the other hand, the present invention also provides a computer device, comprising a processor and a memory, wherein the memory stores a computer program, and the computer program is loaded and executed by the processor to implement any one of the above-mentioned integrated spacecraft payload telemetry data acquisition methods.

[0036] On the other hand, the present invention also provides a computer-readable storage medium, in which a computer program is stored. The computer program is loaded and executed by a processor to implement any one of the above-mentioned integrated spacecraft payload telemetry data acquisition methods.

[0037] The beneficial effects of the present invention are:

[0038] (1) This method can solve the problem that the telemetry bandwidth resources of integrated spacecraft payloads cannot meet the high throughput and real-time performance of payload telemetry signals. Different from the traditional solution of collecting telemetry data according to data importance or refresh rate, the present invention collects telemetry data according to the different working states of the payload subsystem when the integrated payload executes the telemetry instruction, and can use fewer telemetry resources to transmit telemetry data. Compared with the traditional telemetry data collection method, this solution has small bandwidth occupancy and better real-time performance.

[0039] (2) The present invention collects different telemetry data during the integrated payload power-on self-test, daily operation or mission execution, and maintenance self-test, and can use fewer telemetry resources to transmit a larger scale of payload telemetry data. This solution is applied to integrated spacecraft payloads and can solve the bandwidth and delay problems of telemetry signals of hundreds of software and hardware functional modules using 200KB / s transmission bandwidth resources. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Figure 1 It is a schematic flow chart of a method for acquiring integrated spacecraft payload telemetry data provided by an embodiment of the present invention;

[0041] Figure 2 is a schematic diagram of a telemetry control system according to an embodiment of the present invention;

[0042] Figure 3 It is a schematic diagram of the structure of an integrated spacecraft payload telemetry data acquisition device provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0043] The following describes the embodiments of the present invention by specific examples, and those skilled in the art can easily understand other advantages and effects of the present invention from the contents disclosed in this specification. The present invention can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present invention. It should be noted that the following embodiments and features in the embodiments can be combined with each other without conflict.

[0044] Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in the field without making any creative work shall fall within the scope of protection of the present invention.

[0045] Since aerospace equipment is difficult to maintain during operation and has high requirements for system stability, traditional satellite payloads are single-function payloads with fixed functions and single and fixed payload telemetry signal forms. Telemetry data is generally collected according to importance or refresh rate, with few payload collection states and low transmission rate and real-time requirements.

[0046] However, integrated payloads have become the development direction of spacecraft payloads. For integrated payloads running in large spacecraft, the equipment is complex, the working modes and functions are complex, the number and types of collected states are large, the state forms are not fixed, and the requirements for high-throughput and high-real-time information transmission are strong. Traditional telemetry data acquisition methods cannot meet the design requirements of integrated payloads.

[0047] In order to solve the above technical problems, the following embodiments of the integrated spacecraft payload telemetry data acquisition method, device, equipment and medium of the present invention are proposed.

[0048] Example 1

[0049] Reference Figure 2 ,like Figure 2 The figure shows a schematic diagram of the telemetry control system of this embodiment. This embodiment realizes integrated load telemetry data control by designing the following system.

[0050] The integrated control subsystem is responsible for collecting telemetry data from the subsystem control; after collecting the telemetry data, the integrated control subsystem converts the telemetry data into payload telemetry data and sends it to the ground. The integrated control subsystem is deployed with a data storage module that can record the payload telemetry data and send the payload telemetry data to the ground through playback operations. In addition to collecting telemetry data from the functional platform subsystem, the integrated control subsystem also collects telemetry data from different functional subsystems according to different functional modes.

[0051] Different from the traditional scheme of collecting telemetry data according to importance or refresh rate, this embodiment innovatively proposes to collect telemetry data according to different working states of each load subsystem. In this embodiment, the comprehensive control subsystem first sends remote control instructions to each subsystem in the load, and receives status result information returned by each load subsystem.

[0052] Reference Figure 1 ,like Figure 1 FIG. 1 is a flow chart of a method for acquiring integrated spacecraft payload telemetry data provided by this embodiment, and the method specifically includes the following steps:

[0053] Step S100: receiving status result information sent by each subsystem under different working states of the load.

[0054] In this embodiment, the status result information includes the following categories:

[0055] Remote control command execution result telemetry signal, power-on self-test telemetry signal, periodic self-test telemetry signal and maintenance self-test signal.

[0056] Step S200: parse the status result information and inject different identifiers according to the status result information type, and convert it into payload telemetry data.

[0057] Specifically, when the load executes the remote control command, the integrated control subsystem sends the remote control command to each subsystem in the load. After each subsystem completes the remote control, it reports the status result information to the integrated control subsystem.

[0058] The status result information reported by the subsystem in the payload contains the command execution result and other unnecessary data. By parsing, only the command execution result is obtained, and the status result information type is determined.

[0059] After parsing the command execution result, the subsystem identifier and command type identifier of the remote control command are injected, and the payload telemetry data is generated based on these data feature identifiers.

[0060] When the status result information type is periodic self-test telemetry data, parsing the status result information and injecting different identifiers according to the status result information type to convert it into payload telemetry data specifically includes the following steps:

[0061] Analyze the status result information to obtain the periodic self-test results of each subsystem;

[0062] Injecting a periodic self-test signal, a subsystem identifier for executing the self-test, and a periodic self-test identifier into the periodic self-test result;

[0063] The corresponding load telemetry data is generated according to the periodic self-test signal of each subsystem, the identification of the subsystem performing the self-test, the periodic self-test identification and the periodic self-test result.

[0064] When the status result information type is power-on self-test telemetry data, the power-on self-test telemetry data includes the status of different functional software and hardware modules. Parsing the status result information and injecting different identifiers according to the status result information type to convert it into payload telemetry data specifically includes the following steps:

[0065] Analyze the status result information to obtain the status of different functional software and hardware modules in each subsystem and obtain the power-on self-test results;

[0066] Inject the power-on self-test subsystem identifier and the power-on self-test identifier into the power-on self-test result;

[0067] Generate corresponding payload telemetry data according to the power-on self-test result, the power-on self-test subsystem identifier and the power-on self-test identifier.

[0068] It should be noted that the above-mentioned different functional hardware and software modules include the hardware module power-on status, software loading status, and hardware and software initialization status of the functional platform subsystem within the payload, and the software loading status and software initialization status of the functional software subsystem within the payload. The functional platform subsystem within the payload is used to manage the hardware platform and the system running the platform, and the functional software subsystem within the payload is used to manage all application software in the system.

[0069] When the status result information type is maintenance self-test telemetry data, parsing the status result information and injecting different identifiers according to the status result information type, and converting it into payload telemetry data specifically includes the following steps:

[0070] Analyze the status result information to obtain the maintenance self-check result.

[0071] Inject the maintenance self-check subsystem identifier and maintenance self-check identifier into the maintenance self-check result;

[0072] Generate corresponding payload telemetry data based on the maintenance self-inspection results, maintenance self-inspection subsystem identification and maintenance self-inspection identification.

[0073] Step S300: Send the payload telemetry data to the receiving end.

[0074] Information that does not contain unnecessary information and only contains the required telemetry data results and corresponding identification is sent to the ground receiving end.

[0075] It should be noted that, in the present embodiment, the receiving end is arranged on the ground. According to actual needs, the receiving end may also be arranged at other locations, such as a space station.

[0076] The integrated spacecraft payload telemetry data acquisition method provided in this embodiment only collects the various execution results when the integrated payload executes the telemetry instruction, and can use fewer telemetry resources to transmit the telemetry data. Compared with the traditional telemetry data collection method, this solution has small bandwidth occupancy and better real-time performance. This solution collects different telemetry data during the integrated payload power-on self-test, daily operation or mission execution, and maintenance self-test, and can use fewer telemetry resources to transmit a larger scale of payload telemetry data.

[0077] Example 2

[0078] Reference Figure 3 ,like Figure 3 FIG. 1 is a block diagram of the structure of the integrated spacecraft payload telemetry data acquisition device provided in this embodiment, and the device specifically includes the following structures:

[0079] The instruction issuing module is used to issue instructions to the subsystems within the payload.

[0080] The telemetry data receiving module is used to receive status result information returned by the subsystems within the payload in different working states.

[0081] The data analysis module is used to analyze the status result information to obtain the corresponding instruction result.

[0082] The identification injection module is used to inject the corresponding identification into the instruction result and generate telemetry data.

[0083] The data transmission module is used to transmit the telemetry data to the receiving end.

[0084] The integrated spacecraft payload telemetry data acquisition device provided in this embodiment only collects the results of each execution when the integrated payload executes the telemetry instruction, and can use fewer telemetry resources to transmit the telemetry data. Compared with the traditional telemetry data collection method, this solution has small bandwidth occupancy and better real-time performance. This solution collects different telemetry data during the integrated payload power-on self-test, daily operation or mission execution, and maintenance self-test, and can use fewer telemetry resources to transmit a larger scale of payload telemetry data.

[0085] Example 3

[0086] This preferred embodiment provides a computer device, which can implement the steps in any embodiment of the integrated spacecraft payload telemetry data acquisition method provided in the embodiments of the present application. Therefore, the beneficial effects of the integrated spacecraft payload telemetry data acquisition method provided in the embodiments of the present application can be achieved. Please see the previous embodiments for details and will not be repeated here.

[0087] Example 4

[0088] Those skilled in the art will appreciate that all or part of the steps in the various methods of the above embodiments can be completed by instructions, or by controlling related hardware through instructions, and the instructions can be stored in a computer-readable storage medium and loaded and executed by a processor. To this end, an embodiment of the present invention provides a storage medium, which stores a plurality of instructions, and the instructions can be loaded by a processor to execute the steps of any embodiment of the integrated spacecraft payload telemetry data acquisition method provided by the embodiment of the present invention.

[0089] The storage medium may include: a read-only memory (ROM), a random access memory (RAM), a magnetic disk or an optical disk, etc.

[0090] Since the instructions stored in the storage medium can execute the steps in any integrated spacecraft payload telemetry data acquisition method embodiment provided in the embodiments of the present invention, the beneficial effects that can be achieved by any integrated spacecraft payload telemetry data acquisition method provided in the embodiments of the present invention can be achieved. Please refer to the previous embodiments for details and will not be repeated here.

[0091] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A method for acquiring integrated spacecraft payload telemetry data, characterized in that: The method comprises: Receive status result information sent by each subsystem under different working conditions of the load, the status result information types including remote control command execution result telemetry data, periodic self-test telemetry data, power-on self-test telemetry data and maintenance self-test telemetry data; Parsing the status result information and injecting different identifiers according to the status result information type to convert it into payload telemetry data; The payload telemetry data is sent to a receiving end.

2. The integrated spacecraft payload telemetry data acquisition method according to claim 1, characterized in that: When the status result information type is remote control instruction execution result telemetry data, parsing the status result information and injecting different identifiers according to the status result information type to convert it into payload telemetry data specifically includes: Parsing the status result information to obtain the instruction execution result; Injecting the subsystem identifier and the instruction type identifier of the remote control instruction into the instruction execution result; Corresponding payload telemetry data is generated according to the subsystem identifier of the remote control instruction, the instruction type identifier and the instruction execution result.

3. The integrated spacecraft payload telemetry data acquisition method according to claim 1, characterized in that: When the status result information type is periodic self-test telemetry data, parsing the status result information and injecting different identifiers according to the status result information type to convert it into load telemetry data specifically includes: Analyze the status result information to obtain the periodic self-test results of each subsystem; Injecting a periodic self-test signal, an identifier of a subsystem performing self-test, and a periodic self-test identifier into the periodic self-test result; Corresponding load telemetry data is generated according to the periodic self-test signals of each subsystem, the identification of the subsystem performing the self-test, the periodic self-test identification and the periodic self-test results.

4. The integrated spacecraft payload telemetry data acquisition method according to claim 1, characterized in that: When the status result information type is power-on self-test telemetry data, parsing the status result information and injecting different identifiers according to the status result information type to convert it into load telemetry data specifically includes: Parsing the status result information to obtain a power-on self-test result; Injecting a power-on self-test subsystem identifier and a power-on self-test identifier into the power-on self-test result; Generate corresponding load telemetry data according to the power-on self-test result, the power-on self-test subsystem identifier and the power-on self-test identifier.

5. The integrated spacecraft payload telemetry data acquisition method according to claim 4, characterized in that: The power-on self-test telemetry data includes the status of different functional software and hardware modules, including: The power-on status, software loading status, and hardware and software initialization status of the hardware modules of the functional platform subsystem within the payload, as well as the software loading status and software initialization status of the functional software subsystem within the payload.

6. The integrated spacecraft payload telemetry data acquisition method according to claim 1, characterized in that: When the status result information type is maintenance self-test telemetry data, parsing the status result information and injecting different identifiers according to the status result information type to convert it into load telemetry data specifically includes: Analyze the status result information to obtain the maintenance self-check result, Injecting a maintenance self-check subsystem identifier and a maintenance self-check identifier into the maintenance self-check result; Corresponding load telemetry data is generated according to the maintenance self-check result, the maintenance self-check subsystem identifier and the maintenance self-check identifier.

7. An integrated spacecraft payload telemetry data acquisition device, comprising an instruction issuing module, the instruction issuing module is used to issue instructions to a subsystem within the payload, characterized in that: The device also includes: A telemetry data receiving module is used to receive status result information returned by the subsystems in the load in different working states, wherein the status result information types include telemetry data of remote control command execution results, periodic self-test telemetry data, power-on self-test telemetry data and maintenance self-test telemetry data; A data analysis module is used to analyze the status result information to obtain the corresponding instruction result; The identification injection module is used to inject the corresponding identification into the instruction result and generate telemetry data; The data transmission module is used to transmit the telemetry data to the receiving end.

8. A computer device, characterized in that: The computer device includes a processor and a memory, wherein the memory stores a computer program, and the computer program is loaded and executed by the processor to implement the integrated spacecraft payload telemetry data acquisition method as described in any one of claims 1 to 6.

9. A computer-readable storage medium, characterized in that: The storage medium stores a computer program, which is loaded and executed by a processor to implement the integrated spacecraft payload telemetry data acquisition method as described in any one of claims 1 to 6.

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