An integrated system for generating and applying measurement and control information of a spacecraft subcontract

Abstract

The present invention discloses an integrated system for generating and applying spacecraft subcontracting measurement and control information. The remote control form generation module can receive the form supporting the spacecraft product to generate a remote control information form; the telemetry form generation module can receive the form supporting the spacecraft product to generate a telemetry information form; the remote control and telemetry mapping module can receive the remote control information form and the telemetry information form for mapping to obtain an instruction criterion form; the telemetry scheduling strategy generation module receives the telemetry information form for strategy design, evaluation, and packet arrangement optimization, and can compile and iterate the on-board software; the test sequence compilation module receives the remote control information form, the telemetry information form, and the instruction criterion form for semi-automatic compilation to generate a flight program / test sequence form, so as to realize automatic generation of remote control instructions, automatic operation of the test sequence, and automatic interpretation, and solve the problems of low iteration efficiency and high error rate in the design of information such as remote control, telemetry, and criterion of complex spacecraft, low upgrade efficiency of on-board software, and low spacecraft test efficiency.

Description

Technical Field

[0001] The present invention belongs to the technical field of spacecraft design and testing, and particularly relates to an integrated system for generating and applying sub-packet measurement and control information of a spacecraft. Background Art

[0002] In the traditional design and application of sub-packet measurement and control information of spacecraft, information is generally carried in the form of word documents. Usually, unstructured forms are used, and telemetry source packet information and remote control command information are manually compiled. On this basis, unstructured command criterion forms are formed through secondary design. The information carried by these forms can only be recognized manually, and the information homology is poor. Due to frequent iterations, the information consistency has also become worse and worse. When designing the on-board software of a spacecraft, it completely relies on manual digestion of documents and then secondary design and conversion into software, which is time-consuming and laborious, and errors are likely to occur during the iteration or conversion process. When testing a spacecraft, it also completely relies on manual digestion of documents, manually compiling and sending commands, and interpreting data, with low efficiency and prone to human errors.

[0003] With the development of China's space industry, the scale of spacecraft is getting larger and the functions are getting more complex. The amount of its remote control and telemetry information has increased significantly, while the requirements for design iteration and test cycle are getting shorter and shorter. Using structured forms to carry information such as remote control, telemetry, criterion, telemetry scheduling strategy, and test sequence, and using automated software tools for auxiliary design and mutual reference can improve the standardization of design, achieve machine-readable, speed up the design iteration process, avoid errors introduced by secondary design, and improve the information homology and consistency. And it is beneficial to quickly apply the information to the design of the on-board software of a spacecraft to achieve rapid software upgrade; quickly apply it to the test of a spacecraft to achieve automated test and machine interpretation. This helps to greatly improve the efficiency and effectiveness of spacecraft development.

[0004] The purpose of the present invention is to provide an integrated solution for generating and applying sub-packet measurement and control information with standardization, low error rate, high efficiency, and high effectiveness for complex spacecraft. Currently, no description or report of similar related technologies to the present invention has been found, and no domestic similar materials have been collected either. Summary of the Invention

[0005] The technical objective of the present invention is to provide an integrated system for generating and applying sub-packet measurement and control information of a spacecraft to solve the technical problems of low design iteration efficiency, high error rate, low on-board software upgrade efficiency, and low spacecraft test efficiency for remote control, telemetry, criterion, etc. information of complex spacecraft.

[0006] To solve the above problems, the technical solution of the present invention is as follows:

[0007] A spacecraft subcontracting TT&C information generation and application integration system, comprising: a telecommand form generation module, a telemetry form generation module, a telecommand-telemetry mapping module, a telemetry scheduling strategy generation module, and a test sequence compilation module;

[0008] The telecommand form generation module is signal-connected to the telecommand-telemetry mapping module, and is used for receiving the spacecraft product supporting form, generating a telecommand information form and transporting it to the telecommand-telemetry mapping module;

[0009] The telemetry form generation module is respectively signal-connected to the telecommand-telemetry mapping module and the telemetry scheduling strategy generation module, and is used for receiving the spacecraft product supporting form and generating a telemetry information form;

[0010] The telecommand-telemetry mapping module is signal-connected to the test sequence compilation module, and is used for receiving the telecommand information form and the telemetry information form for mapping to obtain an instruction criterion form;

[0011] The telemetry scheduling strategy generation module is used for receiving the telemetry information form for strategy design, evaluation and packet arrangement optimization, generating a downlink strategy form based on the strategy evaluation and then obtaining a multi-channel periodic scheduling matrix, and programming and iterating the on-board software based on the multi-channel periodic scheduling matrix;

[0012] The test sequence compilation module is used for receiving the telecommand information form, the telemetry information form and the instruction criterion form for semi-automatic compilation, thereby generating a flight program / test sequence form, and realizing automatic generation of telecommand instructions, automatic operation of the test sequence and automatic interpretation according to the flight program / test sequence form.

[0013] Specifically, the spacecraft product supporting form includes two fields of "subsystem name" and "space equipment name", and writes information of the subsystems related to telecommand and telemetry and the space equipment under their jurisdiction.

[0014] Among them, the telecommand form generation module is used to support the designer in compiling the telecommand information form. In the compilation process, the subsystem and space equipment names in the received spacecraft product supporting form can be provided for the designer to select, and the compiled equipment-level telecommand information forms are successively aggregated into subsystem telecommand information forms and spacecraft telecommand information forms, and iterative modification of the equipment-level, subsystem-level and spacecraft-level telecommand information is performed based on the statistical analysis of the spacecraft telecommand information form, and finally the telecommand information form is generated.

[0015] Specifically, the telecommand information form includes fields of "subsystem to which the sender belongs", "sender equipment name", "subsystem where the instruction goes", "equipment name where the instruction goes", "instruction code", "instruction name", "telecommand packet sequence flag", "telecommand packet name or sequence count", "telecommand packet APID", and "telecommand packet instruction unit data".

[0016] Among them, the telemetry form generation module is used to support designers in compiling telemetry information forms. During the compilation process, the names of subsystems and space equipment in the received spacecraft product supporting forms can be provided to the designers for selection, and the compiled device-level telemetry information forms are aggregated into subsystem-level telemetry information forms and spacecraft-level telemetry information forms in sequence. Based on the statistical analysis of the spacecraft-level telemetry information form, iterative modification of the device-level, subsystem-level, and spacecraft-level telemetry information is carried out, and finally the telemetry information form is generated.

[0017] Specifically, the telemetry information form includes fields such as "telemetry subsystem", "telemetry device", "APID", "source packet name", "parameter code", "parameter name", "parameter type", "channel number (Byte)", "bit number (bit)", "unit", "processing accuracy", "source code data type", "ground processing formula", "normal value range after parsing", "initial value", "formula coefficient", "bit width", "expected downlink period", "source packet subsystem", and "source packet device".

[0018] Among them, the telecommand-telemetry mapping module is used to support designers in compiling command criterion forms. During the compilation process, relevant information in the received telecommand information form and telemetry information form can be automatically extracted and provided to the designers for selection.

[0019] Specifically, the command criterion form includes "command destination subsystem", "command destination device name", "command code", "command name", the corresponding "telemetry subsystem", "telemetry device name", "telemetry APID", "telemetry source packet name", "telemetry source packet ID", "telemetry code", "telemetry name", "telemetry criterion", "interpretation logic", and "interpretation time limit".

[0020] Among them, the telemetry scheduling strategy generation module is used to process the received telemetry information form according to the preset telemetry mode, and then generate a downlink strategy form;

[0021] The telemetry scheduling strategy generation module generates a multi-channel cycle scheduling matrix according to the downlink strategy form and the preset space equipment ID, and inputs it into the on-board software;

[0022] The telemetry scheduling strategy generation module also calculates the downlink rate of the downlink strategy according to the downlink strategy form, and based on the channel transmission capacity, gives opinions on modifying the packet length and then modifies the telemetry information form.

[0023] Specifically, the downlink strategy form includes fields such as "telemetry mode", "subsystem", "device name", "source packet ID", "source packet name", "source packet APID", "downlink period", and "source packet length".

[0024] Among them, the test sequence compilation module is used to support the designer in compiling the flight program / test sequence form. During the compilation process, relevant information in the received remote control information form, telemetry information form, and instruction criterion form can be automatically extracted and provided for the designer to select.

[0025] Specifically, the flight program / test sequence form includes fields such as "operation type", "instruction code", "instruction name", "parameter code" corresponding to the instruction, "parameter name", "parameter criterion", "interpretation logic", "interpretation time limit", "corresponding telemetry APID", "corresponding telemetry source packet name", and "corresponding telemetry source packet ID"; it can be synchronously imported into the external spacecraft integrated test system to ensure information homology, so that the external spacecraft integrated test system can automatically run the test sequence and extract information from the flight program / test sequence form to achieve automatic generation of remote control instructions, automatic operation of the test sequence, and automatic interpretation.

[0026] Due to the adoption of the above technical solutions, the present invention has the following advantages and positive effects compared with the prior art:

[0027] The present invention provides an integrated system for generating and applying sub-packet measurement and control information of a spacecraft, which solves the problems of low design iteration efficiency and high error rate of complex spacecraft remote control, telemetry, criterion and other information, low star service software upgrade efficiency, and low spacecraft test efficiency. It provides technical support for improving the efficiency and benefit of spacecraft development and has a wide application prospect. Description of the Drawings

[0028] By reading the detailed description of the preferred embodiments below, various other advantages and benefits will become clear to those of ordinary skill in the art. The drawings are only for the purpose of showing the preferred embodiments and are not considered to be a limitation of the present invention.

[0029] Figure 1 It is a schematic flow structure diagram of an integrated system for generating and applying sub-packet measurement and control information of a spacecraft according to the present invention. Detailed Embodiments

[0030] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the specific embodiments of the present invention will be described below with reference to the drawings. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings and other embodiments can be obtained.

[0031] For the sake of simplicity of the drawings, only the parts related to the present invention are schematically shown in each figure, and they do not represent the actual structure of the product. In addition, for the sake of simplicity and easy understanding of the drawings, in some figures, only one of the components with the same structure or function is schematically shown, or only one of them is labeled. In this article, "one" not only means "only this one", but also can mean "more than one" situation.

[0032] The following further elaborates in detail on an integrated system for generating and applying subcontracting measurement and control information of a spacecraft proposed by the present invention in conjunction with the drawings and specific embodiments. According to the following description and the claims, the advantages and features of the present invention will be clearer.

[0033] Embodiment

[0034] Refer to Figure 1 , this embodiment provides an integrated system for generating and applying subcontracting measurement and control information of a spacecraft, including 5 modules, namely 5 software tools, which support iterative design, mutual association and information application of forms. The spacecraft is organized in an orderly manner according to the subsystem - equipment through the product matching table, and the subcontracting measurement and control information all belongs to specific subsystems and equipment. Specifically, this embodiment includes a remote control form generation module, a telemetry form generation module, a remote control and telemetry mapping module, a telemetry scheduling strategy generation module, and a test sequence compilation module. The remote control form generation module is signal - connected to the remote control and telemetry mapping module and is used to receive the spacecraft product matching form and generate a remote control information form. The telemetry form generation module is respectively signal - connected to the remote control and telemetry mapping module and the telemetry scheduling strategy generation module and is used to receive the spacecraft product matching form and generate a telemetry information form. The remote control and telemetry mapping module is signal - connected to the test sequence compilation module and is used to receive the remote control information form and the telemetry information form for mapping to obtain an instruction criterion form. The telemetry scheduling strategy generation module is used to receive the telemetry information form for strategy design, evaluation and packet arrangement optimization, generate a downlink strategy form based on strategy evaluation and then obtain a multi - path periodic scheduling matrix, and compile and iterate the on - board software based on the multi - path periodic scheduling matrix. The test sequence compilation module is used to receive the remote control information form, the telemetry information form and the instruction criterion form for semi - automatic compilation, so as to generate a flight program / test sequence form, and realize automatic generation of remote control instructions, automatic operation of the test sequence and automatic interpretation according to the flight program / test sequence form.

[0035] Refer to Figure 1 , both the remote control form generation module and the telemetry form generation module will receive the spacecraft product matching table, which includes two fields, namely "subsystem name" and "spacecraft equipment name", and other fields are not limited. All subsystems related to remote control and telemetry and their subordinate equipment must be filled in this form, and the same subsystem can have multiple subordinate equipment.

[0036] Refer to Figure 1, the remote control form generation module is used to support designers in preparing remote control information forms. During the preparation process, the names of subsystems and space equipment in the above-mentioned spacecraft product supporting forms received can be provided to the designers for selection, and the prepared equipment-level remote control information forms are aggregated into subsystem remote control information forms and spacecraft remote control information forms in sequence. Based on the statistical analysis of the spacecraft remote control information form, iterative modification of the equipment-level, subsystem-level, and spacecraft-level remote control information is carried out, and finally the remote control information form is finalized and generated.

[0037] Specifically, the remote control information form must contain fields such as "subsystem to which the sender belongs", "sender equipment name", "subsystem where the instruction goes", "equipment name where the instruction goes", "instruction code", "instruction name", "remote control packet sequence flag", "remote control packet name or sequence count", "remote control packet APID", "remote control packet instruction unit data", etc., and other fields are not limited. Information on the subsystems that require remote control instructions and their subordinate space equipment is written in the fields. Fields such as "instruction code", "instruction name", "remote control packet name or sequence count", "remote control packet APID", "remote control packet instruction unit data", etc. in the form are filled in manually by the designer, and the remaining fields are filled in with the support of the remote control form generation module.

[0038] When filling in fields such as "subsystem to which the sender belongs", "sender equipment name", "subsystem where the instruction goes", "equipment name where the instruction goes", etc., the designer can quickly select from the list to ensure the accuracy and uniqueness of the subsystem and equipment names. In addition, standard options are provided for the designer to fill in the "remote control packet sequence flag" field. In this implementation case, four options, namely "00", "01", "10", and "11", are set, which respectively represent the middle packet of the relevant packet sequence, the first packet of the relevant packet sequence, the last packet in the relevant packet sequence, and the independent packet.

[0039] The remote control form generation module will also check the filling norms such as data length and suffix according to established rules and give error prompts. It has the function of importing multiple instruction forms for content merging. It has the functions of marking, deleting duplicate instruction lines, and sorting by instruction code. It can count the number of instructions and the proportion of instructions in each subsystem, providing a reference for iterative modification of instruction design. In addition, a form can be split into multiple forms by subsystem or equipment to support iterative design between the overall spacecraft and subsystems and equipment parties.

[0040] See Figure 1, the telemetry form generation module is used to support designers in compiling telemetry information forms. During the compilation process, the names of subsystems and space equipment in the above-mentioned spacecraft product supporting forms received can be provided to the designers for selection, and the compiled equipment-level telemetry information forms are successively aggregated into subsystem telemetry information forms and spacecraft telemetry information forms. Based on the statistical analysis of the spacecraft telemetry information form, iterative modification of the equipment-level, subsystem-level, and spacecraft-level telemetry information is carried out, and finally, the telemetry information form is finalized and generated.

[0041] Specifically, an independent telemetry information form is designed for each telemetry source package, and the form name is named after the source package code (source package ID). The spacecraft can formulate a unified naming rule for the source package ID. In this implementation case, the naming rule of "PK + spacecraft identifier + subsystem identifier + decimal digital number" is adopted. The telemetry information form must include fields such as "subsystem to which the telemetry belongs", "equipment to which the telemetry belongs", "APID", "source package name", "parameter code", "parameter name", "parameter type", "channel number (Byte)", "bit number (bit)", "unit", "processing accuracy", "source code data type", "ground processing formula", "normal value range after parsing", "initial value", "formula coefficient", "bit width", "expected downlink period", "subsystem to which the source package belongs", "equipment to which the source package belongs", and other fields are not limited. All equipment involved in telemetry downlink in the product supporting form (i.e., the equipment to which the telemetry belongs) should fill in this form. Among them, the field "formula coefficient" can be divided into multiple fields according to the coefficients that may be included in the formula. In this implementation case, 10 coefficients, namely a, b, c, d, e, f, g, h, i, and j, are set, and specific data does not need to be filled in for the coefficients that do not exist in the formula. Fields such as "APID", "source package name", "parameter code", "parameter name", "channel number (Byte)", "bit number (bit)", "unit", "processing accuracy", "ground processing formula", "formula coefficient", and "expected downlink period" in the form can be filled in manually by the designer, and the remaining fields are filled in with the support of the telemetry form generation module.

[0042] In this embodiment, to support designers in accurately and quickly filling out the telemetry information form, after importing the product matching table, when designers fill in fields such as "Telemetry Subsystem", "Equipment", "Source Package Subsystem", and "Source Package Equipment", they select from a list to ensure that the subsystem and equipment names are accurate and unique, and are sourced from the same basic data as the remote control information form. Standard options are provided for designers to fill in the "Parameter Type" field. In this implementation case, four options, AN, BL, DS, and TH, are set, representing analog quantity, boolean quantity, digital quantity, and resistance quantity respectively. Standard options are provided for designers to fill in the "Source Code Data Type" field. In this implementation case, the following options are set: 1) None: None; 2) HexString: Hexadecimal string; 3) BinaryString: Binary string; 4) Uint: Unsigned integer (less than 4 bytes); 5) Int: Signed integer (less than 4 bytes); 6) Ulong: Unsigned long integer (4 - 8 bytes); 7) Long: Signed long integer (4 - 8 bytes); 8) Complement: Integer complement; 9) LongComplement: Long integer complement; 10) Float: Single-precision floating-point number; 11) Double: Double-precision floating-point number; 12) ASCII: ASCII code; 13) DateTimeDayMs: Days and milliseconds since the epoch; 14) DateTimeSMs: Seconds and milliseconds since the epoch; 15) DateTimeS: Seconds since the epoch; 16) DateTimeMS: Milliseconds since the epoch. Assistance is provided for designers to fill in the "Normal Value Range after Parsing", allowing designers to select the data base and data type. After the designers complete filling, it automatically generates a standard machine-readable expression using standard delimiters, connection symbols, etc. according to the established specifications and fills it into the form. In this implementation case, the base selection includes decimal, binary, and hexadecimal, and the data type selection includes basic type, boundary type, multi-value condition type, and cyclic counting type. The basic type format is: list the telemetry values one by one and their corresponding specific meanings. The boundary type format is: list the telemetry value ranges one by one and their corresponding specific meanings. The multi-value condition type format is: list the multi-value combinations of telemetry data one by one and their corresponding specific meanings. The cyclic counting type format is: list the minimum and maximum values of the telemetry data cycle. After the designers fill in the "Channel Number (Byte)" and "Bit Number (bit)", the "Bit Width" is automatically calculated and filled in.

[0043] After completion of filling, the telemetry form generation module will check the filling compliance according to established rules, such as the length of data, suffixes, symbols used in formulas, etc., and give error prompts. It can merge and summarize multiple imported telemetry information forms to obtain the subsystem telemetry information form and the spacecraft telemetry information form. In the spacecraft telemetry information form, the telemetry quantity and proportion of each subsystem are counted according to parameter types, providing a reference for iterative modification of telemetry information design. Naturally, the telemetry form generation module has the function of splitting a form into multiple forms according to subsystems or devices to support the iterative design between the spacecraft overall and subsystem and equipment parties.

[0044] See Figure 1 , in this embodiment, the main function of the remote control and telemetry mapping module is to support designers to establish a mapping relationship between remote control information and telemetry information and generate an instruction criterion form by importing the remote control information form and the telemetry information form. The instruction criterion form must contain fields such as "subsystem where the instruction goes", "device name where the instruction goes", "instruction code", "instruction name", the corresponding "telemetry subsystem", "telemetry device name", "telemetry APID", "telemetry source packet name", "telemetry source packet ID", "telemetry code", "telemetry name", "telemetry criterion", "interpretation logic", "interpretation time limit", etc., and other fields are not limited. All instructions in the instruction criterion form will be listed and filled with the corresponding telemetry criteria. Except for the "interpretation time limit" field, other fields are filled with the assistance of the remote control and telemetry mapping module. The filling format of the "interpretation time limit" is: [t,T];n. The letters in the expression represent the time (unit: "second") to start interpretation after the instruction is sent, the interpretation time limit (unit: "second"), and the number of interpretations in sequence.

[0045] Designers can extract all instructions from the remote control information form at one time and fill them into the "subsystem where the instruction goes", "device name where the instruction goes", "instruction code", and "instruction name" in this form. Organize and display the telemetry information in a tree structure of model - subsystem - device, so that designers can quickly select the "telemetry name" corresponding to a certain instruction, automatically fill it into the form, and bring in the corresponding "telemetry subsystem", "telemetry device name", "telemetry APID", "telemetry source packet name", "telemetry source packet ID", "telemetry code" and other information, supporting multiple telemetry information corresponding to one instruction. Automatically list each or each group of telemetry values included in the "normal value range after parsing" under a certain "telemetry name" for designers to select the specific value of this telemetry corresponding to a certain instruction, that is, to determine the instruction criterion. In addition, designers can set the logical relationship of "AND" or "OR" between multiple criteria of a certain instruction and automatically generate a machine - readable standard expression and fill it into the "interpretation logic" field of the form.

[0046] SeeFigure 1 The telemetry scheduling policy generation module is used to process the received telemetry information form according to a preset telemetry mode, and then generate a downlink policy form. The telemetry scheduling policy generation module generates a multi-channel periodic scheduling matrix based on the downlink policy form and a preset space equipment ID, and inputs it into the on-board software. The telemetry scheduling policy generation module also calculates the downlink rate of the downlink policy according to the downlink policy form, and gives opinions on modifying the packet arrangement length according to the channel transmission capacity, so as to modify the telemetry information form.

[0047] The main function of the telemetry scheduling policy generation module is to support designers in designing and evaluating the telemetry source packet scheduling period. Provide a spacecraft telemetry mode setting interface for designers to set multiple telemetry modes of the spacecraft. Multiple completed telemetry information forms can be imported. According to the set telemetry modes, a downlink policy form for a single-mode source packet is automatically generated for each telemetry mode.

[0048] Each downlink policy form for a single-mode source packet must include fields such as "telemetry mode", "subsystem", "equipment name", "source packet ID", "source packet name", "source packet APID", "downlink period", "source packet length", etc., and other fields are not limited. Among them, the "telemetry mode" field is automatically filled with the mode set by the designer, and the fields such as "subsystem", "equipment name", "source packet ID", "source packet name", "source packet APID" are respectively extracted from the corresponding fields such as "source packet belonging subsystem", "source packet belonging equipment", "form name", "source packet name", "APID" in the telemetry information form. The default value of the "downlink period" is extracted from the "expected downlink period" in the telemetry information form, and the source packet length is automatically calculated and filled with the number of bytes by the software according to the "channel number (Byte)" information in the telemetry information form.

[0049] Designers can modify the "downlink period" of each source packet. The software quickly calculates the downlink rate (baud rate) under the current downlink policy, and evaluates whether the design of the "downlink period" is reasonable and whether there will be channel congestion according to the known channel transmission capacity. In the case that the "downlink period" still exceeds the channel capacity after multiple adjustments, opinions on modifying the packet arrangement length of the source packet can be given, the telemetry information form can be modified, and iteration can be carried out. When the downlink policy forms for all single-mode source packets are completed, the software can summarize them into a downlink policy form with one key. After setting the IDs of each device, the software can generate a multi-channel periodic scheduling matrix (array) according to the spacecraft telemetry downlink scheduling policy form, which is directly used as the input of the on-board software.

[0050] The device ID is determined by the satellite operation software designer and filled into the device ID comparison form. The device ID comparison form must contain the fields of "subsystem name", "device name", "ID of the device in the satellite operation software", and "source packet transmission channel type code", and other fields are not limited. In the form, the fields of "subsystem name" and "device name" are automatically extracted from the imported telemetry information form by the telemetry scheduling strategy generation module as "subsystem to which the source packet belongs" and "device to which the source packet belongs", the "ID of the device in the satellite operation software" is filled in decimal, and the "source packet transmission channel type code" is filled in hexadecimal.

[0051] The multi-channel periodic scheduling matrix expresses the corresponding relationship between the device ID, the device source packet APID, and the source packet scheduling period in each telemetry mode in an array format for direct application to the satellite operation software. In this implementation case, two arrays are used for expression.

[0052] The format of the first array is as follows:

[0053] {

[0054] {source packet transmission channel type code of device 1, ID of device 1, APID of source packet 1 of device 1},

[0055] {source packet transmission channel type code of device 1, ID of device 1, APID of source packet 2 of device 1},

[0056] ……

[0057] {source packet transmission channel type code of device 1, ID of device 1, APID of source packet x of device 1},

[0058] ……

[0059] {source packet transmission channel type code of device n, ID of device n, APID of source packet 1 of device n},

[0060] {source packet transmission channel type code of device n, ID of device n, APID of source packet 2 of device n},

[0061] ……

[0062] {source packet transmission channel type code of device n, ID of device n, APID of source packet y of device n},

[0063] }

[0064] The format of the second array is as follows:

[0065] {

[0066] {APID value of source packet 1 of device 1, {downlink period of mode 1, downlink period of mode 2, downlink period of mode 3... downlink period of mode z}},

[0067] {APID value of the source packet 2 of device 1, {downlink period of mode 1, downlink period of mode 2, downlink period of mode 3... downlink period of mode z}},

[0068] ……

[0069] {APID value of the source packet x of device 1, {downlink period of mode 1, downlink period of mode 2, downlink period of mode 3... downlink period of mode z}},

[0070] ……

[0071] {APID value of the source packet 1 of device n, {downlink period of mode 1, downlink period of mode 2, downlink period of mode 3... downlink period of mode z}},

[0072] {APID value of the source packet 2 of device n, {downlink period of mode 1, downlink period of mode 2, downlink period of mode 3... downlink period of mode z}},

[0073] ……

[0074] {APID value of the source packet y of device n, {downlink period of mode 1, downlink period of mode 2, downlink period of mode 3... downlink period of mode z}},

[0075] }

[0076] See Figure 1 , in this embodiment, the flight program / test sequence form must include fields such as "operation type", "instruction code", "instruction name", "parameter code" corresponding to the instruction, "parameter name", "parameter criterion", "interpretation logic", "interpretation time limit", "corresponding telemetry APID", "corresponding telemetry source packet name", "corresponding telemetry source packet ID", etc., and other fields are not limited. Among them, "operation type" is used to indicate how the spacecraft integrated test system should operate currently, such as "send remote control instruction", "judge parameter", "wait", etc., and the definition of this field should be coordinated and matched with the integrated test system. For other fields in the form, the test sequence compilation module must extract them correspondingly from the remote control information form, telemetry information form, and instruction criterion form, and the above three types of forms should be synchronously imported into the spacecraft integrated test system to achieve information homology, so that the test system can automatically run the test sequence, automatically extract information from the form to generate remote control instructions, automatically perform telemetry parameter parsing, and automatically perform command result interpretation.

[0077] Therefore, the main function of the test sequence compilation module is to support designers to quickly design flight programs or test sequences, thereby generating flight program / test sequence forms. The standard option of "operation type" will be provided to designers to quickly specify the operation type of a row in the form, such as sending remote control instructions, sending program control instructions, judging parameters, etc. In this implementation case, the following options are set: sending remote control instructions, sending remote control instructions to judge parameters, judging parameters, sending program control instructions, sending program control instructions to judge parameters, judging instructions, and waiting. The completed remote control information form, telemetry information form and instruction judgment form can be imported, organized in a tree structure of model-subsystem-equipment, and remote control information, telemetry information and instruction judgment information are displayed for designers to quickly select and automatically fill in the form. It has an automatic association and import function. When the designer selects a certain instruction, the corresponding telemetry parameter-related fields in its mapping table will be automatically brought into the form. When the designer selects only a certain parameter (this row only judges the parameter but does not issue instructions), the relevant fields of the parameter will be automatically brought into the form, and the "normal value range after analysis" will also be brought in, so that the designer can further select one of them as the parameter judgment criterion for the current row.

[0078] The embodiments of the present invention are described in detail above in conjunction with the accompanying drawings, but the present invention is not limited to the above embodiments. Even if various changes are made to the present invention, if these changes fall within the scope of the claims of the present invention and their equivalents, they still fall within the protection scope of the present invention.

Claims

1. An integrated system for generating and applying measurement and control information of a spacecraft subcontract, characterized in that Including: A remote control form generation module, a telemetry form generation module, a remote control and telemetry mapping module, a telemetry scheduling strategy generation module, and a test sequence compilation module; The remote control form generation module is signal-connected to the remote control and telemetry mapping module and is used to receive the spacecraft product supporting form and generate a remote control information form; The telemetry form generation module is respectively signal-connected to the remote control and telemetry mapping module and the telemetry scheduling strategy generation module and is used to receive the spacecraft product supporting form and generate a telemetry information form; The remote control and telemetry mapping module is signal-connected to the test sequence compilation module and is used to receive the remote control information form and the telemetry information form for mapping to obtain an instruction criterion form; The telemetry scheduling strategy generation module is used to receive the telemetry information form for strategy design, evaluation, and packet arrangement optimization, generate a downlink strategy form based on strategy evaluation and then obtain a multi-channel periodic scheduling matrix, and compile and iterate the on-board software based on the multi-channel periodic scheduling matrix; The test sequence compilation module is used to receive the remote control information form, the telemetry information form, and the instruction criterion form for semi-automatic compilation, thereby generating a flight program / test sequence form, and realizing automatic generation of remote control instructions, automatic operation of the test sequence, and automatic interpretation according to the flight program / test sequence form.

2. The integrated application system for generating spacecraft subcontracting TT&C information according to claim 1, wherein The spacecraft product supporting form includes two fields of "subsystem name" and "space equipment name", and writes the information of the subsystems related to remote control and telemetry and the space equipment under their jurisdiction.

3. The integrated application system for generating spacecraft subcontracting TT&C information according to claim 1, wherein The remote control form generation module is used to support the designer in compiling the remote control information form. During the compilation process, the subsystem and space equipment names in the received spacecraft product supporting form can be provided to the designer for selection, and the compiled device-level remote control information forms are successively aggregated into subsystem remote control information forms and spacecraft remote control information forms. Statistical analysis is performed based on the spacecraft remote control information form to iteratively modify the device-level, subsystem-level, and spacecraft-level remote control information, and finally generate the remote control information form.

4. The integrated system for generating and applying spacecraft subcontracting TT&C information according to claim 3, wherein The remote control information form includes fields of "subsystem to which the sender belongs", "sender device name", "subsystem to which the instruction goes", "device name to which the instruction goes", "instruction code", "instruction name", "remote control packet sequence flag", "remote control packet name or sequence count", "remote control packet APID", and "remote control packet instruction unit data".

5. The integrated application system for generating spacecraft subcontract measurement and control information according to claim 1, characterized in that The telemetry form generation module is used to support the designer in compiling the telemetry information form. During the compilation process, the subsystem and space equipment names in the received spacecraft product supporting form can be provided to the designer for selection, and the compiled device-level telemetry information forms are successively aggregated into subsystem telemetry information forms and spacecraft telemetry information forms. Statistical analysis is performed based on the spacecraft telemetry information form to iteratively modify the device-level, subsystem-level, and spacecraft-level telemetry information, and finally generate the telemetry information form.

6. The integrated system for generating and applying spacecraft subcontracting measurement and control information according to claim 5, characterized in that, The telemetry information form includes fields of "Subsystem to which telemetry belongs", "Equipment to which telemetry belongs", "APID", "Source packet name", "Parameter code", "Parameter name", "Parameter type", "Channel number (Byte)", "Bit number (bit)", "Unit", "Processing precision", "Source code data type", "Ground processing formula", "Normal value range after parsing", "Initial value", "Formula coefficient", "Bit width", "Expected downlink period", "Subsystem to which the source packet belongs", and "Equipment to which the source packet belongs".

7. The integrated application system for generating spacecraft subcontracting TT&C information according to claim 1, wherein The remote control and telemetry mapping module is used to support designers in compiling the instruction criterion form. During the compilation process, relevant information in the received remote control information form and telemetry information form can be automatically extracted and provided for the designers to select.

8. The integrated system for generating and applying spacecraft subcontract measurement and control information according to claim 7, characterized in that The instruction criterion form includes "Subsystem to which the instruction goes", "Equipment name to which the instruction goes", "Instruction code", "Instruction name", "Subsystem to which the corresponding telemetry belongs", "Equipment name to which the corresponding telemetry belongs", "Telemetry APID", "Telemetry source packet name", "Telemetry source packet ID", "Telemetry code", "Telemetry name", "Telemetry criterion", "Interpretation logic", and "Interpretation time limit".

9. The integrated system for generating and applying spacecraft subcontract measurement and control information according to claim 1, wherein The telemetry scheduling strategy generation module is used to process the received telemetry information form according to a preset telemetry mode, and then generate the downlink strategy form; The telemetry scheduling strategy generation module generates the multi-channel cycle scheduling matrix according to the downlink strategy form and a preset space equipment ID, and inputs it into the on-board software; The telemetry scheduling strategy generation module also calculates the downlink rate of the downlink strategy according to the downlink strategy form, and based on the channel transmission capacity, gives opinions on modifying the packet arrangement length and then modifies the telemetry information form.

10. The integrated spacecraft subcontract measurement and control information generation and application system according to claim 9, characterized in that, The downlink strategy form includes fields of "Telemetry mode", "Subsystem", "Equipment name", "Source packet ID", "Source packet name", "Source packet APID", "Downlink period", and "Source packet length".

11. The integrated system for generating and applying spacecraft subcontracting measurement and control information according to claim 1, wherein The test sequence compilation module is used to support designers in compiling the flight program / test sequence form. During the compilation process, relevant information in the received remote control information form, telemetry information form, and instruction criterion form can be automatically extracted and provided for the designers to select.

12. The integrated system for generating and applying spacecraft subcontract measurement and control information according to claim 11, characterized in that, The flight program / test sequence form includes fields of "Operation type", "Instruction code", "Instruction name", "Parameter code" corresponding to the instruction, "Parameter name", "Parameter criterion", "Interpretation logic", "Interpretation time limit", "Corresponding telemetry APID", "Corresponding telemetry source packet name", and "Corresponding telemetry source packet ID"; and it is synchronously imported into an external spacecraft integrated test system to achieve information homology, so that the external spacecraft integrated test system can automatically run the test sequence, and is used to extract information from the flight program / test sequence form to realize automatic generation of remote control instructions, automatic operation of the test sequence, and automatic interpretation.

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