Aerospace launch task evaluation method and system

Abstract

The invention provides a spaceflight launch mission evaluation method and system, and the method comprises the steps: dividing a spaceflight launch mission into a plurality of rocket flight segments, and carrying out the evaluation of a subsystem level, a rocket level and a key action in each rocket flight segment. Performing task level evaluation by combining the previous evaluation result, the parameter value of the injection parameter and the like after satellite-rocket separation to obtain a final task evaluation result of the spaceflight launch task; wherein the evaluation of the evaluation elements in the subsystems and the evaluation of the subsystems are realized by using a process evaluation criterion, and the evaluation of the subsystem level, the rocket level and the key action is realized by using a result evaluation criterion. According to the scheme disclosed by the invention, each level can take the most direct and most critical result index as an evaluation basis from the whole to the part, so that subsequent improvement and optimization are effectively guided.

Description

Technical Field

[0001] The present disclosure relates to the field of aerospace data processing, and in particular to the field of aerospace launch mission evaluation, and provides a method and system for aerospace launch mission evaluation. Background Art

[0002] In the field of space launch mission assessment, due to the lack of systematic research on missile and spacecraft launch assessment criteria in China, the assessment work mainly relies on the practical experience of rapid assessment work and the understanding of the principles of space launch. The assessment criteria used in rapid assessment work are the core standards for evaluating projects such as launch vehicle subsystems, flight status, satellite orbiting and test mission completion. Their formulation is based on the combination of practical experience and theory, and is gradually improved and supplemented in continuous practical applications. At present, rapid assessment work is mainly based on manual operation. During the assessment process, the key assessment parameters are displayed on the front end in the form of curves, tables, etc., and the technicians perform manual assessment based on the data display content.

[0003] It can be seen that the current space launch mission assessment technology is still highly dependent on manual judgment, which limits the level of automation and intelligence of the assessment. At the same time, since the formulation and improvement of the assessment criteria are mainly based on the combination of practical experience and theory, there is a lack of systematic research and scientific methodological support, which makes the assessment process susceptible to human factors and the objectivity and accuracy of the assessment results uncertain. In addition, the manual assessment method is inefficient and cannot meet the growing assessment speed requirements of space launch missions.

[0004] Therefore, existing technologies urgently need a more systematic, automated, and intelligent space launch mission assessment technology or solution to improve the accuracy and efficiency of the assessment. Summary of the invention

[0005] The present disclosure at least provides a method and system for evaluating a space launch mission to solve at least one of the above-mentioned technical problems.

[0006] According to one aspect of the present disclosure, a method for evaluating a space launch mission is provided, comprising:

[0007] Identify multiple rocket flight segments for space launch missions;

[0008] Perform the following operations for each rocket flight segment to determine the real-time mission assessment results, rocket stage flight condition assessment results, and key action assessment results of each rocket subsystem in the corresponding rocket flight segment:

[0009] The parameter values ​​of each preset evaluation factor of each rocket subsystem and matched with the current rocket flight stage are respectively obtained in real time; the element evaluation results of each preset evaluation factor are determined in real time by using the preset process evaluation criteria corresponding to each preset evaluation factor and matched with the current rocket flight stage; the real-time task evaluation results of each rocket subsystem in the current rocket flight stage are respectively determined by combining the result evaluation criteria of each rocket subsystem and matched with the current rocket flight stage and the element evaluation results of each preset evaluation factor;

[0010] Determine the key actions in the current rocket flight phase, and determine the key action evaluation results corresponding to each key action using the result evaluation criteria matched with each key action, based on the real-time task evaluation results of each rocket subsystem in the current rocket flight phase, the execution standards of each key action, and the expected target results of each key action;

[0011] Determine the flight trajectory of the rocket in the current rocket flight segment, whether the shutdown quantity requirements are met, and combine the key action evaluation results in the current rocket flight segment to determine the rocket stage flight condition evaluation results of the current rocket flight segment using the result evaluation criteria that match the current rocket flight segment;

[0012] After the separation of the satellite and the rocket, the mission evaluation results of the space launch mission are determined by using the real-time mission evaluation results of each rocket subsystem in each rocket flight segment, the rocket stage flight condition evaluation results, the key action evaluation results, and the parameter values ​​of the satellite's orbital parameters, and using the result evaluation criteria that match the space launch mission.

[0013] In a possible implementation, the rocket subsystem includes a plurality of subsystems; each subsystem includes at least one preset evaluation element; the preset process evaluation criteria include an element-level process evaluation criterion and a subsystem-level process evaluation criterion;

[0014] The method of using the preset process evaluation criteria corresponding to each preset evaluation factor and matching the current rocket flight stage to determine the factor evaluation results of each preset evaluation factor in real time includes:

[0015] For each subsystem, the element-level process evaluation criteria corresponding to each preset evaluation element of the subsystem and matching the current rocket flight segment are used to determine the element evaluation results of each preset evaluation element of the subsystem in real time; the subtask execution evaluation results of the subsystem in the current rocket flight segment are determined by using the element evaluation results of each preset evaluation element and the subsystem-level process evaluation criteria matching the current rocket flight segment; wherein different subsystems have different corresponding subsystem-level process evaluation criteria.

[0016] In a possible implementation, the rocket subsystem includes at least one key parameter; the preset process evaluation criteria include key parameter process evaluation criteria matching each key parameter;

[0017] The result evaluation criteria of each rocket subsystem that matches the current rocket flight stage and the factor evaluation results of each evaluation factor are combined to determine the real-time task evaluation results of each rocket subsystem in the current rocket flight stage, including:

[0018] For each rocket subsystem, the parameter evaluation results of each key parameter in the current rocket flight segment are determined respectively by using the key parameter process evaluation criteria and the parameter values ​​of each key parameter that match the current rocket flight segment;

[0019] The parameter evaluation results of each key parameter in the current rocket flight segment and the subtask execution evaluation results of each subsystem in the current rocket flight segment are used, combined with the result evaluation criteria of the rocket subsystem that matches the current rocket flight segment, to determine the real-time mission evaluation results of the rocket subsystem in the current rocket flight segment.

[0020] In a possible implementation, the space launch mission assessment method further includes:

[0021] Use the designated source UDP multicast mode and the master-slave duplex mode to receive the original data collected by the launch test mission data acquisition system; wherein the original data includes at least one of the following: engine temperature, fuel consumption rate, flight attitude data, structural stress state, parameter values ​​of satellite orbit parameters, rocket flight trajectory, and environmental monitoring data;

[0022] Filtering the original data or correcting data packets with incorrect formats to obtain data to be forwarded;

[0023] The data to be forwarded is forwarded to the corresponding processing module by using the designated source UDP multicast method to execute the space launch mission assessment method.

[0024] In a possible implementation, determining a plurality of rocket flight segments of a space launch mission includes:

[0025] The rocket flight segments of each level are defined by the rocket timing sequence parameters to obtain multiple rocket flight segments.

[0026] In a possible implementation, the following operations may also be performed during the rocket flight phase:

[0027] According to the real-time mission evaluation results of each rocket subsystem within the rocket flight segment, the rocket stage flight condition evaluation results, and the key action evaluation results, the mission evaluation results of the rocket flight segment are determined using the result evaluation criteria that match the flight mission of the rocket flight segment.

[0028] In a possible implementation, the mission evaluation result includes: a theoretical value, an actual value, and a deviation value of the orbital elements of the payload.

[0029] In a possible implementation, the space launch mission assessment method further includes:

[0030] A web-based evaluation report is generated using at least one of the real-time mission evaluation results of each rocket subsystem in each rocket flight segment, the rocket stage flight condition evaluation results, the key action evaluation results, the mission evaluation results of the space launch mission, and the mission evaluation results of each rocket flight segment; wherein the web-based evaluation report is displayed using animation.

[0031] According to another aspect of the present disclosure, there is provided a space launch mission assessment system, comprising:

[0032] A flight segment determination module is used to determine multiple rocket flight segments of a space launch mission;

[0033] The real-time assessment module is used to perform the following operations for each rocket flight segment to determine the real-time mission assessment results, rocket stage flight condition assessment results, and key action assessment results of each rocket subsystem in the corresponding rocket flight segment:

[0034] The parameter values ​​of each preset evaluation factor of each rocket subsystem and matched with the current rocket flight stage are respectively obtained in real time; the element evaluation results of each preset evaluation factor are determined in real time by using the preset process evaluation criteria corresponding to each preset evaluation factor and matched with the current rocket flight stage; the real-time task evaluation results of each rocket subsystem in the current rocket flight stage are respectively determined by combining the result evaluation criteria of each rocket subsystem and matched with the current rocket flight stage and the element evaluation results of each preset evaluation factor;

[0035] Determine the key actions in the current rocket flight phase, and determine the key action evaluation results corresponding to each key action using the result evaluation criteria matched with each key action, based on the real-time task evaluation results of each rocket subsystem in the current rocket flight phase, the execution standards of each key action, and the expected target results of each key action;

[0036] Determine the flight trajectory of the rocket in the current rocket flight segment, whether the shutdown quantity requirements are met, and combine the key action evaluation results in the current rocket flight segment to determine the rocket stage flight condition evaluation results of the current rocket flight segment using the result evaluation criteria that match the current rocket flight segment;

[0037] The result evaluation module is used after the separation of the satellite and the rocket. It uses the real-time mission evaluation results of each rocket subsystem in each rocket flight segment, the rocket stage flight condition evaluation results, the key action evaluation results, and the parameter values ​​of the satellite's orbital parameters to determine the mission evaluation results of the space launch mission using the result evaluation criteria that match the space launch mission.

[0038] The space launch mission evaluation method and system disclosed in the present invention evaluates the execution results at the subsystem level, subsystem level, rocket level, mission level and other dimensions of the subsystem, and uses the result evaluation criteria and result evaluation criteria corresponding to each level of evaluation in the evaluation process, and refines the evaluation work into multiple levels and dimensions, covering a comprehensive evaluation from the launch vehicle subsystem level to the mission level, reducing the interference of human factors, and improving the accuracy and objectivity of the evaluation; the evaluation of each level is based on the most direct and most critical achievement indicators, ensuring the reliability and scientificity of the evaluation results. At the same time, the scheme disclosed in the present invention can automatically parse and process the key evaluation factor parameter values ​​captured by sensors and monitoring equipment through real-time data acquisition and subsystem evaluation factor processing; the mathematical model or algorithm that realizes each evaluation criterion is used to calculate the real-time status of each evaluation factor, and the overall evaluation result of the subsystem is comprehensively obtained, which reduces the workload of manual judgment and improves the automation and intelligence level of the evaluation. In addition, compared with the traditional manual evaluation method, the method disclosed in this paper significantly improves the evaluation efficiency through systematic evaluation process and automated data processing; during the execution of the space launch mission, the system can capture the parameter values ​​of key evaluation factors in real time, and quickly analyze and process them, so as to obtain the evaluation results in time. This efficient evaluation method can meet the growing evaluation needs of space launch missions and provide timely data support for subsequent improvements and optimizations.

[0039] It should be understood that the content described in this section is not intended to identify the key or important features of the embodiments of the present disclosure, nor is it intended to limit the scope of the present disclosure. Other features of the present disclosure will become easily understood through the following description. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] The accompanying drawings are used to better understand the present solution and do not constitute a limitation of the present disclosure.

[0041] Figure 1 is a flow chart of a method for evaluating a space launch mission according to the present disclosure;

[0042] Figure 2A is an evaluation flow chart of the attitude control system in the subsystem according to an embodiment of the present disclosure;

[0043] Figure 2B is a schematic diagram of the structure of a subsystem according to an embodiment of the present disclosure;

[0044] Figure 2C is one of the schematic diagrams of a space launch mission assessment system according to an embodiment of the present disclosure;

[0045] Figure 3 is a second schematic diagram of a space launch mission assessment system according to an embodiment of the present disclosure;

[0046] Figure 4 is a schematic structural diagram of an electronic device according to the present disclosure. DETAILED DESCRIPTION

[0047] The following is a description of exemplary embodiments of the present disclosure in conjunction with the accompanying drawings, including various details of the embodiments of the present disclosure to facilitate understanding, which should be considered as merely exemplary. Therefore, it should be recognized by those of ordinary skill in the art that various changes and modifications may be made to the embodiments described herein without departing from the scope and spirit of the present disclosure. Similarly, for the sake of clarity and conciseness, descriptions of well-known functions and structures are omitted in the following description.

[0048] The present disclosure is in view of the defects of low systematization, automation and intelligence, poor evaluation accuracy and low efficiency in the current space launch mission evaluation scheme, and provides a space launch mission evaluation method and system. The present disclosure divides the space launch mission into multiple rocket flight segments, and evaluates the subsystem level, rocket level and key actions in each rocket flight segment, and after the separation of the satellite and the rocket, combines the previous evaluation results and the parameter values ​​of the orbital parameters to perform a mission level evaluation to obtain the final mission evaluation result of the space launch mission; wherein, the evaluation of the evaluation elements in the subsystem and the evaluation of the subsystem are realized using the process evaluation criteria, and the evaluation of the subsystem level, rocket level and key actions is realized using the result evaluation criteria. The scheme of the present disclosure ensures that from the whole to the part, each level can use the most direct and most critical achievement indicators as the evaluation basis, and on the basis of realizing the systematization, automation and intelligence of the evaluation, the accuracy and efficiency of the evaluation are effectively improved, and it can effectively guide the subsequent improvement and optimization.

[0049] The technical solution of the present disclosure is described below through specific embodiments.

[0050] like Figure 1 As shown, it is a flow chart of the space launch mission assessment method of this embodiment. The execution subject of this embodiment is a computing device, component or system with data processing capability. Specifically, the method of this embodiment may include the following steps:

[0051] S110. Determine multiple rocket flight segments for a space launch mission.

[0052] The rocket flight segment is usually defined by the rocket timing parameters. The flight segment settings of different models and series of rockets are different. The same model of rocket may have different rocket flight segments in different missions (such as whether the third stage has a glide segment or not).

[0053] S120, performing the following operations for each rocket flight segment to determine the real-time mission assessment results, rocket stage flight situation assessment results, and key action assessment results of each rocket subsystem in the corresponding rocket flight segment:

[0054] The first step is to obtain in real time the parameter values ​​of each preset evaluation element of each rocket subsystem that matches the current rocket flight segment; use the preset process evaluation criteria corresponding to each preset evaluation element and matching the current rocket flight segment to determine the element evaluation result of each preset evaluation element in real time; combine the result evaluation criteria of each rocket subsystem that matches the current rocket flight segment and the element evaluation results of each preset evaluation element to determine the real-time task evaluation result of each rocket subsystem in the current rocket flight segment.

[0055] When using process evaluation criteria to determine the evaluation results of each evaluation factor, mathematical models or algorithms are used to calculate the real-time status of each preset evaluation factor, such as whether it is within the normal range, whether there is an abnormal trend, etc., so as to obtain the evaluation results of each evaluation factor in real time. The basis for subsystem evaluation is the automatic interpretation of preset evaluation factor data and the rapid analysis of abnormal parameters. During the rocket flight, the evaluation results of the preset evaluation factors composed of key flight parameters are automatically interpreted by theoretical values, empirical values, data envelopment, data trend prediction and other methods. If there are no abnormal parameters, the evaluation result of the subsystem is normal; if abnormal parameters are found and confirmed, data association analysis, data comparison analysis and other methods are required to conduct preliminary analysis of abnormal parameters. After the analysis is completed, the evaluation results of the subsystem are obtained based on the corresponding result evaluation criteria of the subsystem and the analysis conclusions.

[0056] Based on the evaluation results of the preset evaluation factors corresponding to the subsystem, the subsystem further uses logical reasoning or comprehensive evaluation algorithms according to the set result evaluation criteria, comprehensively considers the mutual influence between various factors, and infers the real-time task evaluation results of the subsystem. Figure 2AThe following is the evaluation process of the attitude control system: first, determine whether the attitude angle deviation exceeds the theoretical value. If not, determine that the real-time task evaluation result of the attitude control system is normal. If the attitude angle deviation exceeds the theoretical value, then continue to determine whether the core stage engine thrust is normal. If normal, determine that the real-time task evaluation result of the attitude control system is normal. If not, then continue to determine whether the attitude angle deviation converges. If converged, determine that the real-time task evaluation result of the attitude control system is basically normal. If not converged, determine that the real-time task evaluation result of the attitude control system is abnormal. The above-mentioned attitude angle deviation and core stage engine thrust are both preset evaluation factors.

[0057] The second step is to determine the key actions in the current rocket flight segment, and based on the real-time mission evaluation results of each rocket subsystem in the current rocket flight segment, the execution standards of each key action and the expected target results of each key action, use the result evaluation criteria matching each key action to determine the key action evaluation results corresponding to each key action.

[0058] After the launch vehicle completes key actions such as ignition and launch, stage separation, and orbit insertion, the system uses a special evaluation model to infer the evaluation results of the key actions based on the real-time mission evaluation results of each subsystem, combined with the execution standards and expected goals of the key actions, thereby obtaining the real-time working status evaluation results of the launch vehicle, that is, the above-mentioned key action evaluation results.

[0059] The third step is to determine the flight trajectory of the rocket in the current rocket flight segment and whether the shutdown requirements are met. Combined with the key action evaluation results in the current rocket flight segment, the result evaluation criteria that match the current rocket flight segment are used to determine the rocket stage flight condition evaluation results of the current rocket flight segment.

[0060] Before executing step S120, it is necessary to collect data using the launch test mission data collection system, and only after processing the collected data can the processing operation of step S120 be performed. Specifically, during the execution of the space launch mission, the system uses various sensors and monitoring equipment to capture the key parameters of each subsystem of the launch vehicle (such as the power system, control system, structural system, etc.) and the parameter values ​​of the preset evaluation factors in real time. The evaluation factors here include but are not limited to engine temperature, fuel consumption rate, flight attitude data, structural stress state, etc., to ensure the timeliness and accuracy of the evaluation basis.

[0061] S130. After the separation of the satellite and the rocket, the mission evaluation result of the space launch mission is determined by utilizing the real-time mission evaluation results of each rocket subsystem in each rocket flight segment, the rocket stage flight condition evaluation results, the key action evaluation results, and the parameter values ​​of the satellite's orbital parameters, and utilizing the result evaluation criteria that match the space launch mission.

[0062] Step S130 corresponds to the overall mission assessment and conclusion generation stage. When the rocket and satellite separate, it indicates that the main stage of the space launch mission is completed. At this time, the system integrates the real-time mission assessment results of all subsystems, the key action assessment results of key actions, and other relevant information during the mission execution process. According to the overall mission assessment criteria, that is, the result assessment criteria that match the space launch mission, a comprehensive analysis and comprehensive assessment is conducted to generate the assessment conclusion of the space launch mission, that is, the mission assessment result of the above-mentioned space launch mission. The mission assessment results of the above-mentioned space launch mission can include mission success, potential risk points, performance evaluation, etc., providing valuable experience and data support for subsequent space activities.

[0063] Usually, the mission-level evaluation is performed after the separation of the rocket and the satellite, but sometimes it is necessary to evaluate multiple times in stages, with different triggering conditions and rules each time. For example, the mission-level evaluation is performed in a certain rocket flight segment. The specific method is as follows: Based on the real-time mission evaluation results of each rocket subsystem in the rocket flight segment, the rocket stage flight situation evaluation results, and the key action evaluation results, the mission evaluation results of the rocket flight segment are determined using the result evaluation criteria that match the flight mission of the rocket flight segment.

[0064] The above embodiment establishes a complete hierarchical evaluation criterion system, which includes process evaluation criteria and result evaluation criteria; wherein, the process evaluation criterion is to evaluate the evaluation elements in each subsystem of the launch vehicle during the flight of the satellite and rocket, and on this basis, to evaluate the working conditions of the subsystems in real time, and further use the result evaluation to accurately determine the evaluation conclusion of the working status of the subsystems of the rocket; the result evaluation criterion is to quickly evaluate the completion of the key actions of the rocket (such as take-off, shutdown, engine start, satellite-rocket separation, etc.), as well as the flight conditions of the rocket segments (such as the first stage, the second stage, the third stage, the glide stage, the third stage, the final speed correction) and the satellite orbiting conditions (i.e., the mission evaluation results of the following space launch missions). The evaluation criteria of the present disclosure can be divided into subsystem level, rocket level and mission level according to the level; the subsystem level, mission level and rocket level adopt the method of result evaluation; the subsystem evaluation of the subsystem adopts the method of process evaluation. Under the evaluation criteria of the space launch mission, the mission level evaluation is mainly based on the final orbit parameters of the satellite, and the evaluation results of the space launch mission are divided into three basic conclusions: complete success, basic success and failure. The rocket-level assessment focuses on the completion of key actions, the launch vehicle's flight trajectory, and whether the shutdown requirements have been met. Based on this, the rocket flight assessment results are divided into three categories: normal flight, basically normal, and abnormal. The subsystem-level assessment focuses more on the impact of each system on the launch vehicle's flight mission, and the assessment results are divided into three basic states: normal, basically normal, and abnormal.

[0065] In some embodiments, Figure 2B ,2C As shown, the above step S120 is completed by a real-time assessment module. A subsystem of a launch vehicle may include multiple subsystems; a subsystem may include one or more preset assessment elements, and the subsystem may also include one or more key parameters.

[0066] The above-mentioned preset process evaluation criteria include element-level process evaluation criteria, subsystem-level process evaluation criteria, and key parameter process evaluation criteria matching each key parameter.

[0067] The method of using the preset process evaluation criteria corresponding to each preset evaluation factor and matching the current rocket flight segment to determine the element evaluation results of each preset evaluation factor in real time can be specifically implemented using the following steps: for each subsystem, using the element-level process evaluation criteria corresponding to each preset evaluation factor of the subsystem and matching the current rocket flight segment to determine the element evaluation results of each preset evaluation factor of the subsystem in real time; using the element evaluation results of each preset evaluation factor and the subsystem-level process evaluation criteria matching the current rocket flight segment to determine the subtask execution evaluation results of the subsystem in the current rocket flight segment; wherein different subsystems correspond to different subsystem-level process evaluation criteria.

[0068] A certain subsystem of the rocket adopts a hierarchical evaluation method. The above-mentioned result evaluation criteria that match the current rocket flight phase and the factor evaluation results of each evaluation factor are combined to determine the real-time task evaluation results of each rocket subsystem in the current rocket flight phase. Specifically, it can be achieved by the following steps:

[0069] For each rocket subsystem, the parameter evaluation results of each key parameter in the current rocket flight segment are determined respectively using the key parameter process evaluation criteria and the parameter values ​​of each key parameter that match the current rocket flight segment; the parameter evaluation results of each key parameter in the current rocket flight segment and the subtask execution evaluation results of each subsystem in the current rocket flight segment are used, combined with the result evaluation criteria of the rocket subsystem that match the current rocket flight segment, to determine the real-time task evaluation results of the rocket subsystem in the current rocket flight segment.

[0070] The functions of the real-time assessment module include the flight process (assessment of the working conditions of the subsystems / subsystems in each rocket flight segment, assessment of the overall flight conditions of the rocket stage in each rocket flight segment, and key actions) and the result evaluation of the mission level in the rocket flight segment (for example, the evaluation corresponding to the number of satellites entering orbit). The evaluation of the working conditions of the rocket stage and each subsystem is usually evaluated within 5 seconds after the corresponding rocket flight segment ends; the evaluation of key actions is evaluated within 1 second after the completion of the action.

[0071] The above-mentioned process evaluation criteria refer to the method of calculating the evaluation results, and its implementation forms include reasoning matrix, reasoning flowchart, and reasoning script. At the same time, the real-time evaluation module supports the display and interaction of evaluation results, supports the display of the content of the evaluated object in a hierarchical structure, and supports users to display information at different levels; when the evaluation result is not normal, it will be prompted with a prominent color and an alarm will be issued.

[0072] like Figure 2C As shown, the above step S130 is completed by the result evaluation module, which supports evaluation methods such as result evaluation based on reasoning tables, flight result evaluation based on orbital element (deviation) areas, and flight result evaluation based on functions. The module supports displaying the theoretical value, actual value, and deviation of each orbital element of the payload; when there are multiple payloads at the same time, the orbital elements of multiple payloads are placed in the same table for comparison and display, or each payload can be displayed as a table.

[0073] In some embodiments, Figure 2C As shown, the raw data collected by the launch test mission data acquisition system can also be received through the assessment data connection module, and some data processing and forwarding work can be performed. Specifically, the assessment data connection module performs the following operations:

[0074] The original data collected by the launch test mission data acquisition system is received using a designated source UDP multicast method and a master-slave duplex mode; wherein the original data includes at least one of the following: engine temperature, fuel consumption rate, flight attitude data, structural stress state, parameter values ​​of satellite orbit parameters, rocket flight trajectory, and environmental monitoring data; the original data is filtered or incorrectly formatted data packets are corrected to obtain data to be forwarded; the data to be forwarded is forwarded to a corresponding processing module (such as a real-time evaluation module, a result evaluation module) using a designated source UDP multicast method to execute the space launch mission evaluation method.

[0075] The assessment data access module function can capture and integrate key data from various launch equipment, monitoring sensors and control systems in real time and accurately, including rocket launch status, flight trajectory parameters, environmental monitoring data, etc., to ensure that all key information flows seamlessly to the modules in the command and control center, providing solid data support for launch decisions, safety monitoring and launch mission evaluation.

[0076] The evaluation data access module can forward the real-time data forwarded by the space launch test mission data acquisition system, receive it using the specified source UDP multicast method, and forward it to the modules in need of the system using the specified source UDP multicast method; the module supports the selection of forwarding / not forwarding specific categories of data; the module can filter or correct incorrectly formatted data packets according to the relevant provisions of the internal application layer data communication protocol to ensure the maximum availability of data, such as processing incorrect data length, incorrect frame tail filling, etc. The module function supports the active-standby duplex mode. When the main interface sends data to the system, the backup interface does not forward it; when the backup interface detects that the main interface is offline, it automatically switches to the main interface. After the original faulty main interface automatically restarts, it is set to the backup state; the active-standby state of the interface can also be manually switched by the post personnel.

[0077] In some embodiments, Figure 2C As shown, a web version of the assessment report can also be generated through the assessment report generation module, specifically:

[0078] A web-based evaluation report is generated using at least one of the real-time mission evaluation results of each rocket subsystem in each rocket flight segment, the rocket stage flight condition evaluation results, the key action evaluation results, the mission evaluation results of the space launch mission, and the mission evaluation results of each rocket flight segment; wherein the web-based evaluation report is displayed using animation.

[0079] The evaluation report generation module realizes report generation based on the B / S mode, and its report content and form are customized by the template; the generated web version of the evaluation report has navigation and interactive capabilities, and simple animations are used to enhance the display effect of the report. The template of the evaluation report usually includes the following contents: cover and signature, launch overview, mission result evaluation, rocket trajectory evaluation, rocket timing and string evaluation, evaluation of each flight stage of each subsystem of the rocket, evaluation details of key parameters of each subsystem of the rocket, a list of other rocket parameter evaluations, abnormal parameter analysis, etc.

[0080] In addition, if Figure 2C As shown in the figure, the system corresponding to the space launch mission evaluation method can also include an evaluation management module, which is mainly responsible for building the evaluation system framework, managing the evaluation plan, integrating evaluation resources, and processing data. This module can create, edit, delete and view evaluation plans based on the evaluation requirements of the space launch mission. At the same time, it can integrate multi-source heterogeneous data such as system data and spacecraft performance data to provide comprehensive and accurate data support for the evaluation. In addition, the evaluation management module also has powerful data processing capabilities, including data analysis, legality checking and data cleaning functions to ensure the accuracy and reliability of the evaluation results.

[0081] Based on the same inventive concept, the present disclosure provides a space launch mission assessment system, the steps performed by the components of the system are the same or similar to the above method, so similar parts are not repeated. Figure 3 As shown, the space launch mission assessment system of this embodiment includes:

[0082] The flight segment determination module 310 is used to determine multiple rocket flight segments of a space launch mission.

[0083] The real-time assessment module 320 is used to perform the following operations for each rocket flight segment to determine the real-time mission assessment results, rocket stage flight condition assessment results, and key action assessment results of each rocket subsystem in the corresponding rocket flight segment:

[0084] The parameter values ​​of each preset evaluation factor of each rocket subsystem and matched with the current rocket flight stage are respectively obtained in real time; the element evaluation results of each preset evaluation factor are determined in real time by using the preset process evaluation criteria corresponding to each preset evaluation factor and matched with the current rocket flight stage; the real-time task evaluation results of each rocket subsystem in the current rocket flight stage are respectively determined by combining the result evaluation criteria of each rocket subsystem and matched with the current rocket flight stage and the element evaluation results of each preset evaluation factor;

[0085] Determine the key actions in the current rocket flight phase, and determine the key action evaluation results corresponding to each key action using the result evaluation criteria matched with each key action, based on the real-time task evaluation results of each rocket subsystem in the current rocket flight phase, the execution standards of each key action, and the expected target results of each key action;

[0086] Determine the flight trajectory of the rocket in the current rocket flight segment, whether the shutdown quantity requirements are met, and combine the key action evaluation results in the current rocket flight segment to determine the rocket stage flight condition evaluation results of the current rocket flight segment using the result evaluation criteria that match the current rocket flight segment;

[0087] The result evaluation module 330 is used to determine the mission evaluation result of the space launch mission after the separation of the satellite and the rocket, using the real-time mission evaluation results of each rocket subsystem in each rocket flight segment, the rocket stage flight condition evaluation results, the key action evaluation results, and the parameter values ​​of the satellite's orbital parameters, and using the result evaluation criteria that match the space launch mission.

[0088] According to an embodiment of the present disclosure, the present disclosure also provides an electronic device and a computer-readable storage medium.

[0089] Figure 4A schematic block diagram of an example electronic device 400 that can be used to implement an embodiment of the present disclosure is shown. The electronic device is intended to represent various forms of digital computers, such as laptop computers, desktop computers, workstations, personal digital assistants, servers, blade servers, mainframe computers, and other suitable computers. The electronic device can also represent various forms of mobile devices, such as personal digital processing, cellular phones, smart phones, wearable devices, and other similar computing devices. The components shown herein, their connections and relationships, and their functions are merely examples and are not intended to limit the implementation of the present disclosure described and / or required herein.

[0090] like Figure 4 As shown, the device 400 includes a computing unit 410, which can perform various appropriate actions and processes according to a computer program stored in a read-only memory (ROM) 420 or a computer program loaded from a storage unit 480 into a random access memory (RAM) 430. In the RAM 430, various programs and data required for the operation of the device 400 can also be stored. The computing unit 410, the ROM 420, and the RAM 430 are connected to each other via a bus 440. An input / output (I / O) interface 450 is also connected to the bus 440.

[0091] A number of components in the device 400 are connected to the I / O interface 450, including: an input unit 460, such as a keyboard, a mouse, etc.; an output unit 470, such as various types of displays, speakers, etc.; a storage unit 480, such as a disk, an optical disk, etc.; and a communication unit 490, such as a network card, a modem, a wireless communication transceiver, etc. The communication unit 490 allows the device 400 to exchange information / data with other devices through a computer network such as the Internet and / or various telecommunication networks.

[0092] The computing unit 410 may be a variety of general and / or special processing components with processing and computing capabilities. Some examples of the computing unit 410 include, but are not limited to, a central processing unit (CPU), a graphics processing unit (GPU), various dedicated artificial intelligence (AI) computing chips, various computing units running machine learning model algorithms, digital signal processors (DSPs), and any appropriate processors, controllers, microcontrollers, etc. The computing unit 410 performs the various methods and processes described above. For example, in some embodiments, any of the above methods may be implemented as a computer software program, which is tangibly contained in a machine-readable medium, such as a storage unit 480. In some embodiments, part or all of the computer program may be loaded and / or installed on the device 400 via ROM 420 and / or a communication unit 490. When the computer program is loaded into RAM 430 and executed by the computing unit 410, one or more steps of any of the methods described above may be performed. Alternatively, in other embodiments, the computing unit 410 may be configured to perform any of the methods described above in any other appropriate manner (e.g., by means of firmware).

[0093] Various implementations of the systems and techniques described above herein can be implemented in digital electronic circuit systems, integrated circuit systems, field programmable gate arrays (FPGAs), application specific integrated circuits (ASICs), application specific standard products (ASSPs), systems on chips (SOCs), load programmable logic devices (CPLDs), computer hardware, firmware, software, and / or combinations thereof. These various implementations can include: being implemented in one or more computer programs that can be executed and / or interpreted on a programmable system including at least one programmable processor, which can be a special purpose or general purpose programmable processor that can receive data and instructions from a storage system, at least one input device, and at least one output device, and transmit data and instructions to the storage system, the at least one input device, and the at least one output device.

[0094] The program code for implementing the method of the present disclosure may be written in any combination of one or more programming languages. These program codes may be provided to a processor or controller of a general-purpose computer, a special-purpose computer, or other programmable data processing device, so that the program code, when executed by the processor or controller, enables the functions / operations specified in the flow chart and / or block diagram to be implemented. The program code may be executed entirely on the machine, partially on the machine, partially on the machine and partially on a remote machine as a stand-alone software package, or entirely on a remote machine or server.

[0095] In the context of the present disclosure, a machine-readable medium may be a tangible medium that may contain or store a program for use by or in conjunction with an instruction execution system, device, or equipment. A machine-readable medium may be a machine-readable signal medium or a machine-readable storage medium. A machine-readable medium may include, but is not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, device, or equipment, or any suitable combination of the foregoing. A more specific example of a machine-readable storage medium may include an electrical connection based on one or more lines, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing.

[0096] To provide interaction with a user, the systems and techniques described herein can be implemented on a computer having: a display device (e.g., a CRT (cathode ray tube) or LCD (liquid crystal display) monitor) for displaying information to the user; and a keyboard and pointing device (e.g., a mouse or trackball) through which the user can provide input to the computer. Other types of devices can also be used to provide interaction with the user; for example, the feedback provided to the user can be any form of sensory feedback (e.g., visual feedback, auditory feedback, or tactile feedback); and input from the user can be received in any form (including acoustic input, voice input, or tactile input).

[0097] The systems and techniques described herein may be implemented in a computing system that includes back-end components (e.g., as a data server), or a computing system that includes middleware components (e.g., an application server), or a computing system that includes front-end components (e.g., a user computer with a graphical user interface or a web browser through which a user can interact with implementations of the systems and techniques described herein), or a computing system that includes any combination of such back-end components, middleware components, or front-end components. The components of the system may be interconnected by any form or medium of digital data communication (e.g., a communication network). Examples of communication networks include: a local area network (LAN), a wide area network (WAN), and the Internet.

[0098] A computer system may include a client and a server. The client and the server are generally remote from each other and usually interact through a communication network. The relationship of client and server is generated by computer programs running on respective computers and having a client-server relationship with each other. The server may be a cloud server, a server of a distributed system, or a server combined with a blockchain.

[0099] It should be understood that the various forms of processes shown above can be used to reorder, add or delete steps. For example, the steps recorded in this disclosure can be executed in parallel, sequentially or in different orders, as long as the desired results of the technical solutions disclosed in this disclosure can be achieved, and this document does not limit this.

[0100] The above specific implementations do not constitute a limitation on the protection scope of the present disclosure. It should be understood by those skilled in the art that various modifications, combinations, sub-combinations and substitutions can be made according to design requirements and other factors. Any modification, equivalent substitution and improvement made within the spirit and principle of the present disclosure shall be included in the protection scope of the present disclosure.

Claims

1. A space launch mission assessment method, characterized in that: include: Identify multiple rocket flight segments for space launch missions; Perform the following operations for each rocket flight segment to determine the real-time mission assessment results, rocket stage flight condition assessment results, and key action assessment results of each rocket subsystem in the corresponding rocket flight segment: The parameter values ​​of each preset evaluation factor of each rocket subsystem and matched with the current rocket flight stage are respectively obtained in real time; the element evaluation results of each preset evaluation factor are determined in real time by using the preset process evaluation criteria corresponding to each preset evaluation factor and matched with the current rocket flight stage; the real-time task evaluation results of each rocket subsystem in the current rocket flight stage are respectively determined by combining the result evaluation criteria of each rocket subsystem and matched with the current rocket flight stage and the element evaluation results of each preset evaluation factor; Determine the key actions in the current rocket flight phase, and determine the key action evaluation results corresponding to each key action using the result evaluation criteria matched with each key action, based on the real-time task evaluation results of each rocket subsystem in the current rocket flight phase, the execution standards of each key action, and the expected target results of each key action; Determine the flight trajectory of the rocket in the current rocket flight segment, whether the shutdown quantity requirements are met, and combine the key action evaluation results in the current rocket flight segment to determine the rocket stage flight condition evaluation results of the current rocket flight segment using the result evaluation criteria that match the current rocket flight segment; After the separation of the satellite and the rocket, the mission evaluation results of the space launch mission are determined by using the real-time mission evaluation results of each rocket subsystem in each rocket flight segment, the rocket stage flight condition evaluation results, the key action evaluation results, and the parameter values ​​of the satellite's orbital parameters, and using the result evaluation criteria that match the space launch mission.

2. The method according to claim 1, characterized in that The rocket subsystem includes a plurality of subsystems; each subsystem includes at least one preset evaluation element; the preset process evaluation criteria include element-level process evaluation criteria and subsystem-level process evaluation criteria; The method of using the preset process evaluation criteria corresponding to each preset evaluation factor and matching the current rocket flight stage to determine the factor evaluation results of each preset evaluation factor in real time includes: For each subsystem, the element-level process evaluation criteria corresponding to each preset evaluation element of the subsystem and matching the current rocket flight segment are used to determine the element evaluation results of each preset evaluation element of the subsystem in real time; the subtask execution evaluation results of the subsystem in the current rocket flight segment are determined by using the element evaluation results of each preset evaluation element and the subsystem-level process evaluation criteria matching the current rocket flight segment; wherein different subsystems have different corresponding subsystem-level process evaluation criteria.

3. The method according to claim 2, characterized in that The rocket subsystem includes at least one key parameter; the preset process evaluation criteria include key parameter process evaluation criteria matching each key parameter; The result evaluation criteria of each rocket subsystem that matches the current rocket flight stage and the factor evaluation results of each evaluation factor are combined to determine the real-time task evaluation results of each rocket subsystem in the current rocket flight stage, including: For each rocket subsystem, the parameter evaluation results of each key parameter in the current rocket flight segment are determined respectively by using the key parameter process evaluation criteria and the parameter values ​​of each key parameter that match the current rocket flight segment; The parameter evaluation results of each key parameter in the current rocket flight segment and the subtask execution evaluation results of each subsystem in the current rocket flight segment are used, combined with the result evaluation criteria of the rocket subsystem that matches the current rocket flight segment, to determine the real-time mission evaluation results of the rocket subsystem in the current rocket flight segment.

4. The method according to claim 1, characterized in that: Also includes: Use the designated source UDP multicast mode and the master-slave duplex mode to receive the original data collected by the launch test mission data acquisition system; wherein the original data includes at least one of the following: engine temperature, fuel consumption rate, flight attitude data, structural stress state, parameter values ​​of satellite orbit parameters, rocket flight trajectory, and environmental monitoring data; Filtering the original data or correcting data packets with incorrect formats to obtain data to be forwarded; The data to be forwarded is forwarded to the corresponding processing module by using the designated source UDP multicast method to execute the space launch mission assessment method.

5. The method according to claim 1, characterized in that The step of determining multiple rocket flight segments of a space launch mission includes: The rocket flight segments of each level are defined by the rocket timing sequence parameters to obtain multiple rocket flight segments.

6. The method according to claim 1, characterized in that The following operations can also be performed during the rocket flight phase: Based on the real-time mission evaluation results of each rocket subsystem within the rocket flight segment, the rocket stage flight condition evaluation results, and the key action evaluation results, the mission evaluation results of the rocket flight segment are determined using result evaluation criteria that match the flight mission of the rocket flight segment.

7. The method according to claim 1 or 6, characterized in that: The mission evaluation results include: theoretical value, actual value and deviation value of the orbital elements of the payload.

8. The method according to claim 6, characterized in that Also includes: A web-based evaluation report is generated using at least one of the real-time mission evaluation results of each rocket subsystem in each rocket flight segment, the rocket stage flight condition evaluation results, the key action evaluation results, the mission evaluation results of the space launch mission, and the mission evaluation results of each rocket flight segment; wherein the web-based evaluation report is displayed using animation.

9. A space launch mission assessment system, characterized in that: include: A flight segment determination module is used to determine multiple rocket flight segments of a space launch mission; The real-time assessment module is used to perform the following operations for each rocket flight segment to determine the real-time mission assessment results, rocket stage flight condition assessment results, and key action assessment results of each rocket subsystem in the corresponding rocket flight segment: The parameter values ​​of each preset evaluation factor of each rocket subsystem and matched with the current rocket flight stage are respectively obtained in real time; the element evaluation results of each preset evaluation factor are determined in real time by using the preset process evaluation criteria corresponding to each preset evaluation factor and matched with the current rocket flight stage; the real-time task evaluation results of each rocket subsystem in the current rocket flight stage are respectively determined by combining the result evaluation criteria of each rocket subsystem and matched with the current rocket flight stage and the element evaluation results of each preset evaluation factor; Determine the key actions in the current rocket flight phase, and determine the key action evaluation results corresponding to each key action using the result evaluation criteria matched with each key action, based on the real-time task evaluation results of each rocket subsystem in the current rocket flight phase, the execution standards of each key action, and the expected target results of each key action; Determine the flight trajectory of the rocket in the current rocket flight segment, whether the shutdown quantity requirements are met, and combine the key action evaluation results in the current rocket flight segment to determine the rocket stage flight condition evaluation results of the current rocket flight segment using the result evaluation criteria that match the current rocket flight segment; The result evaluation module is used after the separation of the satellite and the rocket. It uses the real-time mission evaluation results of each rocket subsystem in each rocket flight segment, the rocket stage flight condition evaluation results, the key action evaluation results, and the parameter values ​​of the satellite's orbital parameters to determine the mission evaluation results of the space launch mission using the result evaluation criteria that match the space launch mission.

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