Spacecraft injection data processing method and device

Abstract

The application provides a spacecraft injection data processing method and device, and relates to the technical field of spacecraft measurement and control. The method comprises the following steps: obtaining injection data content information, injection data input information and injection data framing and sending information; if it is determined that the preset injection data generation condition is met according to the injection data configuration, the injection data input information and the spacecraft real-time telemetry information, the injection data is generated; if the injection data that has passed the correctness check meets the preset injection data sending condition composed of the injection data input information and the spacecraft real-time telemetry information, the injection data is framed according to the injection data framing and sending information and the spacecraft real-time telemetry information; the injection data that has passed the framing is selected for a sending link, and the injection data is sent through the sending link. The device executes the above method. The method and device provided in the application embodiment can improve the timeliness of injection data generation and framing and sending.

Description

Technical Field

[0001] This invention relates to the field of spacecraft telemetry and control technology, specifically to a method and apparatus for processing injected data in spacecraft. Background Technology

[0002] After entering the space station phase, the launch frequency of spacecraft increases significantly, placing higher demands on mission preparation time and efficiency. As the complexity of spacecraft continues to rise, the safe operation of spacecraft places even greater demands on ground telemetry and control response time. In the field of aerospace telemetry and control, remotely injected data, as a crucial part of spacecraft control, plays a key role in aerospace telemetry and control missions. However, during the early stages of spacecraft operation in orbit, when ground control changed parameters required by spacecraft application software through injected data, it was necessary to create cfg files using injected data generation software and complete a step-by-step data approval process. This process was cumbersome and lengthy, unable to meet the needs of emergency response and rapid, efficient flight control modes. Summary of the Invention

[0003] To address the problems in the prior art, embodiments of the present invention provide a spacecraft injection data processing method and apparatus, which can at least partially solve the problems existing in the prior art.

[0004] On one hand, this invention proposes a spacecraft injected data processing method, comprising:

[0005] Read the injection data arrangement and split the injection data arrangement to obtain injection data content information, injection data input information and injection data frame sending information;

[0006] The injection data configuration is obtained based on the injection data content information. If the preset injection data generation conditions are met based on the injection data configuration, injection data input information, and spacecraft real-time telemetry information, then the injection data is generated.

[0007] The generated injection data and the injection data input information are checked for correctness. If the injection data that has completed the correctness check meets the preset injection data transmission conditions composed of the injection data input information and the spacecraft real-time telemetry information, then the injection data is framed according to the injection data frame transmission information and the spacecraft real-time telemetry information.

[0008] Based on the spacecraft's real-time telemetry information and the injected data framing and transmission information, the transmission link for the completed framed injected data is selected, and the injected data is transmitted based on the selected transmission link.

[0009] The preset injection data generation conditions include:

[0010] Any one of the following conditions: data generation time condition, input information threshold condition, data association condition, and real-time telemetry parameter condition, or a combination of at least two of these conditions.

[0011] The preset injection data sending conditions include at least the following:

[0012] Data transmission time conditions, and / or real-time telemetry parameter conditions.

[0013] The step of checking the correctness of the generated injection data and the injection data input information includes:

[0014] Verify the correctness of the injected data content and format, and the consistency between the output and the input content.

[0015] The spacecraft injection data processing method further includes:

[0016] If it is determined, based on the injection data configuration, injection data input information, and spacecraft real-time telemetry information, that the preset injection data generation conditions are not met, then the first target data that causes the preset injection data generation conditions to not be met is obtained, and a first prompt message is generated based on the first target data.

[0017] The spacecraft injection data processing method further includes:

[0018] If the injected data that has completed the correctness check does not meet the preset injection data transmission conditions composed of the injection data input information and the spacecraft real-time telemetry information, then the second target data that causes the failure to meet the preset injection data transmission conditions is obtained, and a second prompt message is generated based on the second target data.

[0019] On one hand, the present invention proposes a spacecraft injection data processing device, comprising:

[0020] The splitting unit is used to read the injection data arrangement and split the injection data arrangement to obtain injection data content information, injection data input information and injection data frame transmission information;

[0021] The generation unit is used to obtain the injection data configuration based on the injection data content information. If the preset injection data generation conditions are met based on the injection data configuration, injection data input information, and spacecraft real-time telemetry information, then the injection data is generated.

[0022] The framing unit is used to perform a correctness check on the generated injection data and the injection data input information. If the injection data that has completed the correctness check meets the preset injection data transmission conditions composed of the injection data input information and the spacecraft real-time telemetry information, then the injection data is framed according to the injection data framing transmission information and the spacecraft real-time telemetry information.

[0023] The transmitting unit is used to select a transmission link for the framed injected data based on the real-time telemetry information of the spacecraft and the injected data frame transmission information, and to transmit the injected data based on the selected transmission link.

[0024] In another aspect, embodiments of the present invention provide a computer device, including a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, it implements the following method:

[0025] Read the injection data arrangement and split the injection data arrangement to obtain injection data content information, injection data input information and injection data frame sending information;

[0026] The injection data configuration is obtained based on the injection data content information. If the preset injection data generation conditions are met based on the injection data configuration, injection data input information, and spacecraft real-time telemetry information, then the injection data is generated.

[0027] The generated injection data and the injection data input information are checked for correctness. If the injection data that has completed the correctness check meets the preset injection data transmission conditions composed of the injection data input information and the spacecraft real-time telemetry information, then the injection data is framed according to the injection data frame transmission information and the spacecraft real-time telemetry information.

[0028] Based on the spacecraft's real-time telemetry information and the injected data framing and transmission information, the transmission link for the completed injected data is selected, and the injected data is transmitted based on the selected transmission link.

[0029] This invention provides a computer-readable storage medium, comprising:

[0030] The computer-readable storage medium stores a computer program that, when executed by a processor, implements the following method:

[0031] Read the injection data arrangement and split the injection data arrangement to obtain injection data content information, injection data input information and injection data frame sending information;

[0032] The injection data configuration is obtained based on the injection data content information. If the preset injection data generation conditions are met based on the injection data configuration, injection data input information, and spacecraft real-time telemetry information, then the injection data is generated.

[0033] The generated injection data and the injection data input information are checked for correctness. If the injection data that has completed the correctness check meets the preset injection data transmission conditions composed of the injection data input information and the spacecraft real-time telemetry information, then the injection data is framed according to the injection data frame transmission information and the spacecraft real-time telemetry information.

[0034] Based on the spacecraft's real-time telemetry information and the injected data framing and transmission information, the transmission link for the completed framed injected data is selected, and the injected data is transmitted based on the selected transmission link.

[0035] This invention also provides a computer program product, which includes a computer program that, when executed by a processor, implements the following method:

[0036] Read the injection data arrangement and split the injection data arrangement to obtain injection data content information, injection data input information and injection data frame sending information;

[0037] The injection data configuration is obtained based on the injection data content information. If the preset injection data generation conditions are met based on the injection data configuration, injection data input information, and spacecraft real-time telemetry information, then the injection data is generated.

[0038] The generated injection data and the injection data input information are checked for correctness. If the injection data that has completed the correctness check meets the preset injection data transmission conditions composed of the injection data input information and the spacecraft real-time telemetry information, then the injection data is framed according to the injection data frame transmission information and the spacecraft real-time telemetry information.

[0039] Based on the spacecraft's real-time telemetry information and the injected data framing and transmission information, the transmission link for the completed framed injected data is selected, and the injected data is transmitted based on the selected transmission link.

[0040] The spacecraft injection data processing method and apparatus provided in this invention reads the injection data arrangement and splits it to obtain injection data content information, injection data input information, and injection data framing and transmission information. It obtains the injection data configuration based on the injection data content information. If the injection data configuration, injection data input information, and spacecraft real-time telemetry information determine that preset injection data generation conditions are met, then injection data is generated. The generated injection data and the injection data input information are checked for correctness. If the injection data that has passed the correctness check meets the preset injection data transmission conditions composed of the injection data input information and the spacecraft real-time telemetry information, then the injection data is framed according to the injection data framing and transmission information and the spacecraft real-time telemetry information. The framed injection data is then used to select a transmission link based on the spacecraft real-time telemetry information and the injection data framing and transmission information, and the injection data is transmitted based on the selected transmission link. This improves the timeliness of injection data generation and framing and transmission. Attached Figure Description

[0041] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort. In the drawings:

[0042] Figure 1 This is a schematic flowchart of a spacecraft injection data processing method provided in an embodiment of the present invention.

[0043] Figure 2 This is a schematic flowchart of a spacecraft injection data processing method provided in another embodiment of the present invention.

[0044] Figure 3 This is a schematic diagram of the structure of a spacecraft injection data processing device provided in an embodiment of the present invention.

[0045] Figure 4 This is a schematic diagram of the physical structure of a computer device provided in an embodiment of the present invention. Detailed Implementation

[0046] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the embodiments of the present invention will be further described in detail below with reference to the accompanying drawings. Here, the illustrative embodiments and descriptions of the present invention are used to explain the present invention, but are not intended to limit the present invention. It should be noted that, unless otherwise specified, the embodiments and features in the embodiments of this application can be arbitrarily combined with each other.

[0047] Figure 1This is a schematic flowchart of a spacecraft injection data processing method according to an embodiment of the present invention, as shown below. Figure 1 As shown, the spacecraft injection data processing method provided in this embodiment of the invention includes:

[0048] Step S1: Read the injection data arrangement and split the injection data arrangement to obtain injection data content information, injection data input information and injection data frame sending information.

[0049] Step S2: Obtain the injection data configuration based on the injection data content information. If the preset injection data generation conditions are met based on the injection data configuration, injection data input information, and spacecraft real-time telemetry information, then generate the injection data.

[0050] Step S3: Perform a correctness check on the generated injection data and the injection data input information. If the injection data that has completed the correctness check meets the preset injection data transmission conditions composed of the injection data input information and the spacecraft real-time telemetry information, then perform injection data framing according to the injection data framing transmission information and the spacecraft real-time telemetry information.

[0051] Step S4: Select a transmission link for the framed injection data based on the spacecraft's real-time telemetry information and the injection data frame transmission information, and send the injection data based on the selected transmission link.

[0052] In step S1 above, the device reads the injection data arrangement and splits the injection data arrangement to obtain injection data content information, injection data input information, and injection data frame transmission information. The device can be a computer device, such as a server, that executes this method. The acquisition, storage, use, and processing of data in this application's technical solution all comply with relevant regulations.

[0053] like Figure 2 As shown, the data injection scheme, which is used in spacecraft flight control, is usually written by the designer; the data injection scheme can include data injection content information, data injection input information, and data injection frame transmission information.

[0054] The injected data content information refers to the injection generation, data function, and injected data format.

[0055] The injected data input information typically includes input files and information. The input files include spacecraft orbital elements files, orbital control parameter files, relay satellite orbital elements files, and program control command plan files, etc. The information includes takeoff time, orbital information, orbital control information, flight procedure information, time difference between Earth and space, thermal control temperature, and solar panel angle, etc.

[0056] The injected data frame transmission information mainly includes transmission conditions, target spacecraft, route spacecraft, transmission method (including direct transmission, proxy transmission, serial and high-pass transmission, etc.) and telemetry and control link.

[0057] The examples are illustrated in Table 1:

[0058] Table 1

[0059]

[0060] The injected data arrangement includes the following information: at 9:00 AM on January 1st, time synchronization data will be transmitted from spacecraft B to spacecraft A via the L-satellite K-link. Data generation will begin at 8:00 AM. The data content is time synchronization for data management. The required input information is the time difference between Earth and space. The transmission station and link used are the L-satellite K-link. Specifically, the injected data content information is that the injected data will be generated at 8:00 AM on January 1st, and the generated data content is time synchronization for data management. The input information for the injected data is the time difference between Earth and space for time synchronization. The injected data framing and transmission information will be sent at 9:00 AM on January 1st, transmitted from spacecraft B to spacecraft A via the L-satellite K-link.

[0061] In step S2 above, the device obtains the injection data configuration based on the injection data content information. If the preset injection data generation conditions are met based on the injection data configuration, injection data input information, and spacecraft real-time telemetry information, then the injection data is generated. The injection data configuration is the injection data configuration file (CFG file). Referring to Table 1, the injection data configuration (CFG file) can be created according to the data format selected for data management and time synchronization based on the injection data arrangement, and provided to the injection generation software for injection data generation. Injection data generation refers to the process by which the injection generation software reads the injection data configuration, input file, and information to generate the injection data.

[0062] The preset injection data generation conditions include:

[0063] The conditions include any one of the following: data generation time condition, input information threshold condition, data association condition, and real-time telemetry parameter condition, or a combination of at least two of these conditions. Specific details are as follows:

[0064] Referring to the example above, 8:00 AM is the data generation time condition. In actual spacecraft flight control, in addition to fixed time conditions, there are also input information threshold conditions, data association conditions, real-time telemetry parameter conditions, and combined conditions. For example, in actual flight control, the generation of spacecraft time synchronization data is also determined by whether the time difference between Earth and space exceeds a specific threshold. Therefore, time conditions and input information threshold conditions can be used as combined conditions for injecting data generation.

[0065] If data b needs to wait for data a to be sent before its generation can begin, then data association conditions can be used, with the successful sending of data a serving as the starting condition for the generation of data b.

[0066] During the spacecraft temperature control process, when the real-time telemetry temperature is lower than a specific value, the thermal control injection data generation is initiated. The spacecraft telemetry parameters can be used as the conditions for generating the corresponding data.

[0067] When the spacecraft's real-time telemetry information and injection data input information determine that the preset injection data generation conditions are met, the injection generation software reads the injection data configuration, obtains the information required for injection generation, and generates the injection data.

[0068] The spacecraft injection data processing method also includes:

[0069] If, based on the injection data configuration, injection data input information, and real-time spacecraft telemetry information, it is determined that the preset injection data generation conditions are not met, then the first target data causing the failure to meet the preset injection data generation conditions is obtained, and a first prompt message is generated based on the first target data. The first target data can be understood as the data that causes the failure to meet the preset injection data generation conditions.

[0070] In step S3 above, the device performs a correctness check on the generated injection data and the injection data input information. If the injection data that has passed the correctness check meets the preset injection data transmission conditions composed of the injection data input information and the spacecraft real-time telemetry information, then injection data framing is performed according to the injection data framing transmission information and the spacecraft real-time telemetry information. The correctness check on the generated injection data and the injection data input information includes:

[0071] Verify the correctness of the injected data content and format, and the consistency between the output and the input content.

[0072] The preset injection data sending conditions include at least the following:

[0073] Data transmission time conditions, and / or real-time telemetry parameter conditions.

[0074] Before injecting and framing the data, it is necessary to determine whether the preset data injection and transmission conditions are met. In the example above, the Earth-Sky time difference file is the information required for injection generation. The generated data management time synchronization result is compared with the Earth-Sky time difference for accuracy. 9 o'clock is the data transmission time condition. After the conditions are met, the data injection framing and transmission begin. The real-time telemetry parameter conditions can be referred to the above description and will not be repeated here.

[0075] The spacecraft injection data processing method also includes:

[0076] If the injected data that has completed the correctness check does not meet the preset injection data transmission conditions comprised of the injected data input information and the spacecraft's real-time telemetry information, then a second target data that causes the failure to meet the preset injection data transmission conditions is acquired, and a second prompt message is generated based on the second target data. The second target data can be understood as the data that causes the failure to meet the preset injection data transmission conditions.

[0077] In step S4 above, the device selects a transmission link for the framed injection data based on the spacecraft's real-time telemetry information and the injected data framing and transmission information, and then transmits the injection data based on the selected transmission link. Referring to the example above, the spacecraft framing and transmission information is transmitted from spacecraft B to spacecraft A via the L-satellite K link, thus completing the process of automatically generating, framing, and transmitting injected data. In spacecraft telemetry and control, timeliness is one of the most important requirements. Therefore, using the spacecraft's real-time telemetry directly as the information required for injection data generation, framing, and transmission in the above process can effectively improve the timeliness of spacecraft telemetry and control. Real-time telemetry contains information such as spacecraft status, air-to-air communication status, and uplink and downlink status of the telemetry and control link. For example, when generating solar panel control data, it is necessary to confirm the real-time solar panel angle on the spacecraft. Processing the real-time solar panel angle information yields the injection information required for the spacecraft's solar panel control data. Through real-time telemetry information, the spacecraft's real-time telemetry status can also be obtained, thereby enabling data format framing, telemetry and control link selection, and transmission according to different mission states.

[0078] The spacecraft injection data processing method provided in this embodiment of the invention has the following beneficial technical effects:

[0079] 1. Improved the speed and accuracy of spacecraft injection data generation, solving the problems of lengthy and inefficient processes in existing injection data generation.

[0080] 2. When conditions are met, the injected data is automatically generated or sent, which solves the problem of on-duty monitoring in the long-term operation and control management of spacecraft, optimizes the judgment of the data start-up timing, and improves the level of intelligence and automation of aerospace telemetry and control.

[0081] 3. It improves the timeliness of spacecraft operation and control management and provides means for spacecraft emergency control and fault handling.

[0082] The spacecraft injection data processing method provided in this invention reads the injection data arrangement and splits it to obtain injection data content information, injection data input information, and injection data framing and transmission information. It obtains the injection data configuration based on the injection data content information. If the injection data configuration, injection data input information, and spacecraft real-time telemetry information determine that preset injection data generation conditions are met, then injection data is generated. The generated injection data and the injection data input information are checked for correctness. If the injection data that has passed the correctness check meets the preset injection data transmission conditions composed of the injection data input information and the spacecraft real-time telemetry information, then the injection data is framed according to the injection data framing and transmission information and the spacecraft real-time telemetry information. The framed injection data is then used to select a transmission link based on the spacecraft real-time telemetry information and the injection data framing and transmission information, and the injection data is transmitted based on the selected transmission link. This improves the timeliness of injection data generation and framing and transmission.

[0083] Furthermore, the preset injection data generation conditions include:

[0084] The conditions include any one of the following: data generation time condition, input information threshold condition, data association condition, and real-time telemetry parameter condition, or a combination of at least two of these conditions. Refer to the above embodiments for further explanation; details will not be repeated here.

[0085] Furthermore, the preset injected data sending conditions include at least:

[0086] Data transmission time conditions and / or real-time telemetry parameter conditions. These can be referred to the above embodiments for explanation and will not be repeated here.

[0087] Furthermore, the correctness check of the generated injection data and the injection data input information includes:

[0088] Verify the correctness of the injected data content and format, and the consistency between the output and input content. Refer to the above examples for further details.

[0089] Furthermore, the spacecraft injection data processing method also includes:

[0090] If, based on the injection data configuration, injection data input information, and real-time telemetry information of the spacecraft, it is determined that the preset injection data generation conditions are not met, then the first target data causing the failure to meet the preset injection data generation conditions is obtained, and a first prompt message is generated based on the first target data. This can be referred to the above embodiments for further explanation, and will not be repeated here.

[0091] Furthermore, the spacecraft injection data processing method also includes:

[0092] If the injected data that has completed the correctness check does not meet the preset injection data transmission conditions composed of the injection data input information and the spacecraft's real-time telemetry information, then a second target data that causes the failure to meet the preset injection data transmission conditions is acquired, and a second prompt message is generated based on the second target data. This can be referred to the above embodiments for further explanation, and will not be repeated here.

[0093] Figure 3 This is a schematic diagram of the structure of a spacecraft injection data processing device provided in an embodiment of the present invention, as shown below. Figure 3 As shown, the spacecraft injection data processing device provided in this embodiment of the invention includes a splitting unit 301, a generation unit 302, a framing unit 303, and a sending unit 304, wherein:

[0094] The splitting unit 301 is used to read the injection data arrangement and split the injection data arrangement to obtain injection data content information, injection data input information, and injection data frame transmission information; the generation unit 302 is used to obtain the injection data configuration according to the injection data content information. If the injection data configuration, injection data input information, and spacecraft real-time telemetry information determine that the preset injection data generation conditions are met, then the injection data is generated; the framing unit 303 is used to perform a correctness check on the generated injection data and the injection data input information. If the injection data that has completed the correctness check meets the preset injection data transmission conditions composed of the injection data input information and the spacecraft real-time telemetry information, then the injection data is framed according to the injection data frame transmission information and the spacecraft real-time telemetry information; the sending unit 304 is used to select a transmission link for the framed injection data according to the spacecraft real-time telemetry information and the injection data frame transmission information, and send the injection data based on the selected transmission link.

[0095] Specifically, the splitting unit 301 in the device is used to read the injection data arrangement and split the injection data arrangement to obtain injection data content information, injection data input information, and injection data frame transmission information; the generation unit 302 is used to obtain the injection data configuration according to the injection data content information. If the preset injection data generation conditions are met according to the injection data configuration, injection data input information, and spacecraft real-time telemetry information, then the injection data is generated; the framing unit 303 is used to perform a correctness check on the generated injection data and the injection data input information. If the injection data that has completed the correctness check meets the preset injection data transmission conditions composed of the injection data input information and the spacecraft real-time telemetry information, then the injection data is framed according to the injection data frame transmission information and the spacecraft real-time telemetry information; the transmission unit 304 is used to select a transmission link for the framed injection data according to the spacecraft real-time telemetry information and the injection data frame transmission information, and transmit the injection data based on the selected transmission link.

[0096] The spacecraft injection data processing device provided in this embodiment of the invention reads the injection data arrangement and splits the injection data arrangement to obtain injection data content information, injection data input information, and injection data frame transmission information. It obtains the injection data configuration based on the injection data content information. If the preset injection data generation conditions are met based on the injection data configuration, injection data input information, and spacecraft real-time telemetry information, then injection data is generated. The generated injection data and the injection data input information are checked for correctness. If the injection data that has passed the correctness check meets the preset injection data transmission conditions composed of the injection data input information and the spacecraft real-time telemetry information, then the injection data is framed based on the injection data frame transmission information and the spacecraft real-time telemetry information. The framed injection data is then selected for transmission links based on the spacecraft real-time telemetry information and the injection data frame transmission information, and the injection data is transmitted based on the selected transmission links. This improves the timeliness of injection data generation and frame transmission.

[0097] Furthermore, the preset injection data generation conditions in the spacecraft injection data processing device include:

[0098] Any one of the following conditions: data generation time condition, input information threshold condition, data association condition, and real-time telemetry parameter condition, or a combination of at least two of these conditions.

[0099] Furthermore, the preset injection data transmission conditions in the spacecraft injection data processing device include at least:

[0100] Data transmission time conditions, and / or real-time telemetry parameter conditions.

[0101] Furthermore, the correctness check of the generated injection data and the injection data input information includes:

[0102] Verify the correctness of the injected data content and format, and the consistency between the output and the input content.

[0103] Furthermore, the spacecraft injection data processing device is also used for:

[0104] If it is determined, based on the injection data configuration, injection data input information, and spacecraft real-time telemetry information, that the preset injection data generation conditions are not met, then the first target data that causes the preset injection data generation conditions to not be met is obtained, and a first prompt message is generated based on the first target data.

[0105] Furthermore, the spacecraft injection data processing device is also used for:

[0106] If the injected data that has completed the correctness check does not meet the preset injection data transmission conditions composed of the injection data input information and the spacecraft real-time telemetry information, then the second target data that causes the failure to meet the preset injection data transmission conditions is obtained, and a second prompt message is generated based on the second target data.

[0107] The embodiments of the present invention provide a spacecraft injection data processing device that can be used to execute the processing flow of the above-described method embodiments. Its functions will not be repeated here, but can be referred to the detailed description of the above-described method embodiments.

[0108] Figure 4 This is a schematic diagram of the physical structure of a computer device provided in an embodiment of the present invention, such as... Figure 4 As shown, the computer device includes: a memory 401, a processor 402, and a computer program stored in the memory 401 and executable on the processor 402. When the processor 402 executes the computer program, it implements the following method:

[0109] Read the injection data arrangement and split the injection data arrangement to obtain injection data content information, injection data input information and injection data frame sending information;

[0110] The injection data configuration is obtained based on the injection data content information. If the preset injection data generation conditions are met based on the injection data configuration, injection data input information, and spacecraft real-time telemetry information, then the injection data is generated.

[0111] The generated injection data and the injection data input information are checked for correctness. If the injection data that has completed the correctness check meets the preset injection data transmission conditions composed of the injection data input information and the spacecraft real-time telemetry information, then the injection data is framed according to the injection data frame transmission information and the spacecraft real-time telemetry information.

[0112] Based on the spacecraft's real-time telemetry information and the injected data framing and transmission information, the transmission link for the completed framed injected data is selected, and the injected data is transmitted based on the selected transmission link.

[0113] This embodiment discloses a computer program product, which includes a computer program that, when executed by a processor, implements the following method:

[0114] Read the injection data arrangement and split the injection data arrangement to obtain injection data content information, injection data input information and injection data frame sending information;

[0115] The injection data configuration is obtained based on the injection data content information. If the preset injection data generation conditions are met based on the injection data configuration, injection data input information, and spacecraft real-time telemetry information, then the injection data is generated.

[0116] The generated injection data and the injection data input information are checked for correctness. If the injection data that has completed the correctness check meets the preset injection data transmission conditions composed of the injection data input information and the spacecraft real-time telemetry information, then the injection data is framed according to the injection data frame transmission information and the spacecraft real-time telemetry information.

[0117] Based on the spacecraft's real-time telemetry information and the injected data framing and transmission information, the transmission link for the completed framed injected data is selected, and the injected data is transmitted based on the selected transmission link.

[0118] This embodiment provides a computer-readable storage medium storing a computer program that, when executed by a processor, implements the following method:

[0119] Read the injection data arrangement and split the injection data arrangement to obtain injection data content information, injection data input information and injection data frame sending information;

[0120] The injection data configuration is obtained based on the injection data content information. If the preset injection data generation conditions are met based on the injection data configuration, injection data input information, and spacecraft real-time telemetry information, then the injection data is generated.

[0121] The generated injection data and the injection data input information are checked for correctness. If the injection data that has completed the correctness check meets the preset injection data transmission conditions composed of the injection data input information and the spacecraft real-time telemetry information, then the injection data is framed according to the injection data frame transmission information and the spacecraft real-time telemetry information.

[0122] Based on the spacecraft's real-time telemetry information and the injected data framing and transmission information, the transmission link for the completed framed injected data is selected, and the injected data is transmitted based on the selected transmission link.

[0123] Compared with existing technologies, this invention reads the injection data arrangement and splits it to obtain injection data content information, injection data input information, and injection data framing and transmission information. It then obtains the injection data configuration based on the injection data content information. If the preset injection data generation conditions are met based on the injection data configuration, injection data input information, and spacecraft real-time telemetry information, injection data is generated. The generated injection data and the injection data input information are checked for correctness. If the injection data that has passed the correctness check meets the preset injection data transmission conditions composed of the injection data input information and the spacecraft real-time telemetry information, the injection data is framed based on the injection data framing and transmission information and the spacecraft real-time telemetry information. Finally, the framed injection data is selected for transmission links based on the spacecraft real-time telemetry information and the injection data framing and transmission information, and the injection data is transmitted based on the selected transmission links. This improves the timeliness of injection data generation and framing and transmission.

[0124] Those skilled in the art will understand that embodiments of the present invention can be provided as methods, systems, or computer program products. Therefore, the present invention can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, the present invention can take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code.

[0125] This invention is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the invention. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, generate instructions for implementing the flowchart illustrations and / or block diagrams. Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0126] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.

[0127] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0128] In the description of this specification, the references to terms such as "an embodiment," "a specific embodiment," "some embodiments," "for example," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0129] The specific embodiments described above further illustrate the purpose, technical solution, and beneficial effects of the present invention. It should be understood that the above descriptions are merely specific embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A method for processing injected data in a spacecraft, characterized in that, include: Read the injection data arrangement and split the injection data arrangement to obtain injection data content information, injection data input information and injection data frame sending information; The injection data configuration is obtained based on the injection data content information. If the preset injection data generation conditions are met based on the injection data configuration, injection data input information and spacecraft real-time telemetry information, the injection data is generated. The preset injection data generation conditions include any one of the following: data generation time conditions, input information threshold conditions, data association conditions, and real-time telemetry parameter conditions, or a combination of at least two of these conditions. The generated injection data and the injection data input information are checked for correctness. If the injection data that has completed the correctness check meets the preset injection data transmission conditions composed of the injection data input information and the spacecraft real-time telemetry information, then the injection data is framed according to the injection data frame transmission information and the spacecraft real-time telemetry information. Based on the spacecraft's real-time telemetry information and the injected data framing and transmission information, the transmission link for the completed framed injected data is selected, and the injected data is transmitted based on the selected transmission link.

2. The spacecraft injection data processing method according to claim 1, characterized in that, The preset injection data sending conditions include at least the following: Data transmission time conditions, and / or real-time telemetry parameter conditions.

3. The spacecraft injection data processing method according to claim 1, characterized in that, The correctness check of the generated injection data and the injection data input information includes: Verify the correctness of the injected data content and format, and the consistency between the output and the input content.

4. The spacecraft injection data processing method according to claim 1, characterized in that, The spacecraft injection data processing method also includes: If it is determined, based on the injection data configuration, injection data input information, and spacecraft real-time telemetry information, that the preset injection data generation conditions are not met, then the first target data that causes the preset injection data generation conditions to not be met is obtained, and a first prompt message is generated based on the first target data.

5. The spacecraft injection data processing method according to claim 1, characterized in that, The spacecraft injection data processing method also includes: If the injected data that has completed the correctness check does not meet the preset injection data transmission conditions composed of the injection data input information and the spacecraft real-time telemetry information, then the second target data that causes the failure to meet the preset injection data transmission conditions is obtained, and a second prompt message is generated based on the second target data.

6. A spacecraft injected data processing device, characterized in that, include: The splitting unit is used to read the injection data arrangement and split the injection data arrangement to obtain injection data content information, injection data input information and injection data frame transmission information; The generation unit is used to obtain the injection data configuration based on the injection data content information. If the preset injection data generation conditions are met based on the injection data configuration, injection data input information and spacecraft real-time telemetry information, the injection data is generated. The preset injection data generation conditions include any one of the following: data generation time conditions, input information threshold conditions, data association conditions, and real-time telemetry parameter conditions, or a combination of at least two of these conditions. The framing unit is used to perform a correctness check on the generated injection data and the injection data input information. If the injection data that has completed the correctness check meets the preset injection data transmission conditions composed of the injection data input information and the spacecraft real-time telemetry information, then the injection data is framed according to the injection data framing transmission information and the spacecraft real-time telemetry information. The transmitting unit is used to select a transmission link for the framed injected data based on the real-time telemetry information of the spacecraft and the injected data frame transmission information, and to transmit the injected data based on the selected transmission link.

7. A computer device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that, When the processor executes the computer program, it implements the method of any one of claims 1 to 5.

8. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores a computer program that, when executed by a processor, implements the method of any one of claims 1 to 5.

9. A computer program product, characterized in that, The computer program product includes a computer program that, when executed by a processor, implements the method of any one of claims 1 to 5.

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