Space Launch Mission Evaluation Method and System

Abstract

The present disclosure provides a method and system for evaluating space launch missions. The present disclosure divides space launch missions into multiple rocket flight segments, evaluates at the subsystem level, rocket level, and key actions in each rocket flight segment, and combines the previous evaluation results and the parameter values of the orbit insertion parameters, etc. after satellite-rocket separation to conduct mission-level evaluation, so as to obtain the final mission evaluation result of the space launch mission; among them, the evaluation of evaluation elements in the subsystem and the evaluation of the subsystem are implemented using process evaluation criteria, and the evaluation at the subsystem level, rocket level, and key actions is implemented using result evaluation criteria. The solution of the present disclosure ensures that from the whole to the part, each level can use the most direct and critical achievement indicators as the evaluation basis, thereby effectively guiding subsequent improvement and optimization.

Description

Technical Field

[0001] The present disclosure relates to the field of space data processing, and particularly to the field of space launch mission assessment, and provides a method and system for space launch mission assessment. 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 previously, the assessment work mainly relied on the practical experience of rapid assessment work and the understanding of space launch principles. The assessment criteria used in the rapid assessment work, as the core standards for evaluating items such as the subsystems of launch vehicles, flight states, satellite orbit insertion, and completion of test tasks, were formulated based on the combination of practical experience and theory, and were gradually improved and supplemented in continuous practical applications. The current rapid assessment work mainly relies on manual operations. During the assessment process, key assessment parameters are displayed at the front end in the form of curves, tables, etc., and technicians conduct manual assessments based on the data display content.

[0003] It can be seen that the current space launch mission assessment technology still highly relies on manual judgment, which restricts the automation and intelligence level of the assessment. At the same time, since the formulation and improvement of the assessment criteria mainly rely on the combination of practical experience and theory, lacking systematic research and scientific methodology support, it is easy to be affected by human factors during the assessment process, and the objectivity and accuracy of the assessment results are uncertain. In addition, the manual assessment method is inefficient and difficult to meet the increasing assessment speed requirements of space launch missions.

[0004] Therefore, there is an urgent need for a more systematic, automated, and intelligent space launch mission assessment technology or solution in the prior art to improve the accuracy and efficiency of the assessment. Summary of the Invention

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

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

[0007] Determine multiple rocket flight segments of a space launch mission;

[0008] For each rocket flight segment, perform the following operations to determine the real-time task assessment results of each rocket subsystem, the assessment results of rocket stage flight conditions, and the assessment results of key actions within the corresponding rocket flight segment:

[0009] Obtain in real time the parameter values of each preset evaluation element of each rocket subsystem that match 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 in real time the element evaluation results of each preset evaluation element; combine the result evaluation criteria of each rocket subsystem that match the current rocket flight segment and the element evaluation results of each preset evaluation element to determine respectively the real-time task evaluation results of each rocket subsystem within the current rocket flight segment;

[0010] Determine the key actions within the current rocket flight segment, and according to the real-time task evaluation results of each rocket subsystem, the execution standards of each key action, and the expected target results of each key action within the current rocket flight segment, use the result evaluation criteria matching each key action to determine respectively the key action evaluation results corresponding to each key action;

[0011] Determine the flight trajectory of the rocket within the current rocket flight segment and the information on whether the shutdown quantity requirement is met, and combine the key action evaluation results within the current rocket flight segment to use the result evaluation criteria matching the current rocket flight segment to determine the rocket stage flight situation evaluation result of the current rocket flight segment;

[0012] After the separation of the satellite and the rocket, use the real-time task evaluation results of each rocket subsystem, the rocket stage flight situation evaluation results, the key action evaluation results, and the parameter values of the satellite's orbit injection parameters within each rocket flight segment, and use the result evaluation criteria matching the space launch mission to determine the mission evaluation result of the space launch mission.

[0013] In a possible implementation manner, the rocket subsystem includes multiple 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;

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

[0015] For each subsystem, use the element-level process evaluation criteria corresponding to each preset evaluation element of the subsystem and matching the current rocket flight segment to determine in real time the element evaluation results of each preset evaluation element of the subsystem; use the element evaluation results of each preset evaluation element and the subsystem-level process evaluation criteria matching the current rocket flight segment to determine the sub-task execution evaluation result of the subsystem within the current rocket flight segment; wherein, the subsystem-level process evaluation criteria corresponding to different subsystems are different.

[0016] In a possible implementation, the rocket subsystem includes at least one key parameter; the preset process evaluation criterion includes a key parameter process evaluation criterion that matches each key parameter;

[0017] Combining the result evaluation criterion that matches the current rocket flight segment for each rocket subsystem and the element evaluation results of each evaluation element, respectively determining the real-time task evaluation results of each rocket subsystem within the current rocket flight segment, including:

[0018] For each rocket subsystem, using the key parameter process evaluation criteria that match the current rocket flight segment and the parameter values of each key parameter, respectively determining the parameter evaluation results of each key parameter within the current rocket flight segment;

[0019] Using the parameter evaluation results of each key parameter within the current rocket flight segment and the sub-task execution evaluation results of each subsystem within the current rocket flight segment, and combining the result evaluation criterion that matches the current rocket flight segment for this rocket subsystem, determining the real-time task evaluation results of this rocket subsystem within the current rocket flight segment.

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

[0021] Using the specified source UDP multicast method and the primary and backup 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 the satellite's orbit insertion parameters, the flight trajectory of the rocket, environmental monitoring data;

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

[0023] Using the specified source UDP multicast method to forward the data to be forwarded to the corresponding processing module to execute the space launch mission evaluation method.

[0024] In a possible implementation, the determination of multiple rocket flight segments of the space launch mission includes:

[0025] Defining the flight segments of each stage of the rocket based on the rocket timing string parameters to obtain multiple rocket flight segments.

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

[0027] Based on the real-time task evaluation results of each rocket subsystem, the rocket stage flight situation evaluation results, and the key action evaluation results within the rocket flight segment, the task evaluation result of the rocket flight segment is determined using the result evaluation criteria that match the flight mission of the rocket flight segment.

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

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

[0030] Using at least one of the real-time task evaluation results of each rocket subsystem, the rocket stage flight situation evaluation results, the key action evaluation results, the task evaluation results of the space launch mission, and the task evaluation results of each rocket flight segment within each rocket flight segment, a web version evaluation report is generated; wherein, the web version evaluation report is presented in an animated manner.

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

[0032] A flight segment determination module for determining multiple rocket flight segments of a space launch mission;

[0033] A real-time evaluation module for performing the following operations for each rocket flight segment to determine the real-time task evaluation results of each rocket subsystem, the rocket stage flight situation evaluation results, and the key action evaluation results within the corresponding rocket flight segment:

[0034] Respectively and in real time obtain the parameter values of each preset evaluation element of each rocket subsystem that match 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 results of each preset evaluation element in real time; combine the result evaluation criteria of each rocket subsystem that match the current rocket flight segment and the element evaluation results of each preset evaluation element to respectively determine the real-time task evaluation results of each rocket subsystem within the current rocket flight segment;

[0035] Determine the key actions within the current rocket flight segment, and based on the real-time task evaluation results of each rocket subsystem within 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 that match each key action to respectively determine the key action evaluation results corresponding to each key action;

[0036] Determine the flight trajectory of the rocket within the current rocket flight segment and the information on whether the shutdown quantity requirement is met, and combine the key action evaluation results within the current rocket flight segment to determine the rocket stage flight situation evaluation results of the current rocket flight segment using the result evaluation criteria that match the current rocket flight segment;

[0037] A result evaluation module, which is used to determine the task evaluation result of a space launch mission by using the real-time task evaluation results of each rocket subsystem, the evaluation results of the rocket stage flight conditions, the evaluation results of key actions, and the parameter values of the satellite's orbit insertion parameters within each rocket flight segment after the separation of the rocket and satellite, and by using the result evaluation criteria matching the space launch mission.

[0038] The space launch mission evaluation method and system of the present disclosure evaluate the execution results at dimensions such as the subsystem level, the subsystem level of the subsystem, the rocket stage, and the mission level of the subsystem. Moreover, during the evaluation process, the result evaluation criteria corresponding to each level of evaluation and the result evaluation criteria are utilized, refining the evaluation work into multiple levels and dimensions, covering a comprehensive evaluation from the subsystem level of the launch vehicle 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 critical achievement indicators, ensuring the reliability and scientific nature of the evaluation results. At the same time, the solution of the present disclosure can automatically analyze and process the parameter values of the key evaluation elements captured by sensors and monitoring devices through real-time data acquisition and processing of the evaluation elements of the subsystem; calculate the real-time status of each evaluation element by using the mathematical models or algorithms implementing each evaluation criterion, and comprehensively obtain the overall evaluation result of the subsystem, reducing the workload of manual judgment and improving the automation and intelligence level of the evaluation. In addition, compared with the traditional manual evaluation method, the method of the present disclosure significantly improves the evaluation efficiency through a systematic evaluation process and automated data processing; during the execution process of the space launch mission, the system can capture the parameter values of the key evaluation elements in real time and quickly analyze and process them, thereby obtaining the evaluation result in a timely manner. This efficient evaluation method can meet the growing evaluation needs of space launch missions and provide timely data support for subsequent improvement and optimization.

[0039] It should be understood that the content described in this part is not intended to identify the key or important features of the embodiments of the present disclosure, nor is it used to limit the scope of the present disclosure. Other features of the present disclosure will become easily understood through the following description. Description of the Drawings

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

[0041] Figure 1 is a flowchart of the space launch mission evaluation method according to the present disclosure;

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

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

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

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

[0046] Figure 4 is the structural schematic diagram of the electronic device according to the present disclosure. Detailed implementation manners

[0047] The following describes exemplary embodiments of the present disclosure with reference to the accompanying drawings. Various details of the embodiments of the present disclosure are included to facilitate understanding, and they should be considered merely exemplary. Therefore, those of ordinary skill in the art should recognize that various changes and modifications can be made to the embodiments described herein without departing from the scope and spirit of the present disclosure. Similarly, descriptions of well-known functions and structures are omitted below for clarity and conciseness.

[0048] In view of the deficiencies of the current space launch mission evaluation scheme, such as low systematization, automation, and intelligence levels, poor evaluation accuracy, and low efficiency, the present disclosure provides a space launch mission evaluation method and system. The present disclosure divides the space launch mission into multiple rocket flight segments, conducts evaluations at the subsystem level, rocket level, and key actions in each rocket flight segment, and combines the previous evaluation results and parameter values of the orbital injection parameters, etc. after the satellite-rocket separation to conduct mission-level evaluations, obtaining the final mission evaluation result of the space launch mission; among them, the evaluation of evaluation elements in the subsystem and the evaluation of the subsystem are implemented using the process evaluation criterion, and the evaluations at the subsystem level, rocket level, and key actions are implemented using the result evaluation criterion. The solution of the present disclosure ensures that from the whole to the part, each level can use the most direct and critical result indicators as the evaluation basis, effectively improving the evaluation accuracy and efficiency on the basis of realizing evaluation systematization, automation, and intelligence, and being able to effectively guide subsequent improvements and optimizations.

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

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

[0051] S110. Determine multiple rocket flight segments of the space launch mission.

[0052] The rocket flight segments are usually defined for each stage of the rocket by the rocket sequence time series parameters. The flight segment settings of different rocket models and series are different, and even for the same rocket model, the flight segments may vary in different missions (such as the presence or absence of a coasting segment in the third stage).

[0053] S120. For each rocket flight segment, perform the following operations to determine the real-time task evaluation results, rocket stage flight condition evaluation results, and key action evaluation results of each rocket subsystem within the corresponding rocket flight segment:

[0054] The first step: Obtain in real time the parameter values of each preset evaluation element of each rocket subsystem that match 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 in real time the element evaluation results of each preset evaluation element; combine the result evaluation criteria of each rocket subsystem that match the current rocket flight segment and the element evaluation results of each preset evaluation element to determine respectively the real-time task evaluation results of each rocket subsystem within the current rocket flight segment.

[0055] When using the process evaluation criteria to determine the element evaluation results of each preset evaluation element, use a mathematical model or algorithm to calculate the real-time state of each preset evaluation element, such as whether it is within the normal range, whether there is an abnormal trend, etc., so as to obtain in real time the element evaluation results of each evaluation element. The basis for subsystem evaluation is the automatic interpretation of preset evaluation element data and the rapid analysis of abnormal parameters. During the rocket flight, methods such as theoretical values, empirical values, data envelopment, and data trend prediction are used to automatically interpret the evaluation results of preset evaluation elements composed of key flight parameters. If there are no abnormal parameters, the evaluation result of the subsystem is normal operation; if abnormal parameters are found and confirmed, methods such as data correlation analysis and data comparison analysis need to be used to conduct a preliminary analysis of the abnormal parameters. After the analysis is completed, based on the result evaluation criteria corresponding to the subsystem and combined with the analysis conclusion, the evaluation result of the subsystem is obtained.

[0056] Based on the evaluation results of the preset evaluation elements corresponding to the subsystem, the subsystem further uses logical reasoning or a comprehensive evaluation algorithm according to the set result evaluation criteria, comprehensively considers the mutual influence among the elements, and reasons out the real-time task evaluation result of the subsystem. For example, Figure 2AThe following is the evaluation process of the attitude control system: First, determine whether the attitude angle deviation exceeds the theoretical value. If it does not exceed, it is determined that the real-time task evaluation result of the attitude control system is normal; if the attitude angle deviation exceeds the theoretical value, continue to determine whether the core-stage engine thrust is normal. If it is normal, it is determined that the real-time task evaluation result of the attitude control system is normal. If it is not normal, continue to determine whether the attitude angle deviation converges. If it converges, it is determined that the real-time task evaluation result of the attitude control system is basically normal. If it does not converge, it is determined that the real-time task evaluation result of the attitude control system is abnormal. The above attitude angle deviation and core-stage engine thrust are both preset evaluation elements.

[0057] Second step: Determine the key actions within the current rocket flight segment, and based on the real-time task evaluation results of each rocket subsystem within the current rocket flight segment, the execution criteria of each key action, and the expected target results of each key action, use the result evaluation criteria matching each key action to respectively determine the key action evaluation results corresponding to each key action.

[0058] After the launch vehicle completes key actions such as ignition and liftoff, stage separation, and orbit insertion, the system, based on the real-time task evaluation results of each subsystem, combines the execution criteria and expected goals of the key actions, and uses a special evaluation model to infer the evaluation results of the key actions, thereby obtaining the evaluation result of the real-time working state of the launch vehicle, that is, the above key action evaluation results.

[0059] Third step: Determine the flight trajectory of the rocket within the current rocket flight segment and the information on whether the shutdown quantity requirement is met, and combine the key action evaluation results within the current rocket flight segment, and use the result evaluation criteria matching the current rocket flight segment to determine the rocket stage flight situation evaluation result of the current rocket flight segment.

[0060] Before performing step S120, it is necessary to collect data using the launch test mission data acquisition system and process the collected data before being able to perform the processing operation of step S120. Specifically, during the execution of the space launch mission, the system captures in real time the key parameters of each rocket subsystem (such as the power system, control system, structure system, etc.) and the parameter values of the preset evaluation elements through various sensors and monitoring devices. The evaluation elements 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, use the real-time task evaluation results of each rocket subsystem within each rocket flight segment, the rocket stage flight situation evaluation results, the key action evaluation results, and the parameter values of the satellite's orbit insertion parameters, and use the result evaluation criteria matching the space launch mission to determine the mission evaluation result of the space launch mission.

[0062] Step S130 corresponds to the overall mission assessment and conclusion generation stage. After the separation of the rocket and the satellite, it marks the completion of the main stage of the space launch mission. At this time, the system synthesizes 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. According to the overall mission assessment criteria, that is, the result assessment criteria matching the space launch mission, a comprehensive analysis and overall assessment are carried out 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 result of the above-mentioned space launch mission may include mission success degree, potential risk points, performance evaluation, etc., providing valuable experience and data support for subsequent space activities.

[0063] Generally, mission-level assessment is carried out after the separation of the rocket and the satellite, but sometimes it is also necessary to conduct phased assessments multiple times, and the triggering conditions and rules are different each time. For example, mission-level assessment is carried out in a certain rocket flight segment, and the specific method is as follows: According to the real-time mission assessment results of each rocket subsystem, the rocket stage flight situation assessment results, and the key action assessment results within this rocket flight segment, the mission assessment result of this rocket flight segment is determined by using the result assessment criteria matching the flight mission of this rocket flight segment.

[0064] The above embodiments establish a complete hierarchical assessment criterion system, which includes process assessment criteria and result assessment criteria; among them, the process assessment criteria are to evaluate the assessment elements in each subsystem of the launch vehicle during the flight of the rocket and the satellite, and on this basis, the working conditions of the subsystems are evaluated in real time, and further use the result assessment to accurately determine the assessment conclusion of the working state of the rocket's subsystems; the result assessment criteria are for the completion of key actions of the rocket (such as takeoff, shutdown, engine start, separation of the rocket and the satellite, etc.), as well as the flight conditions of the rocket flight segments (such as the first stage, the second stage, the first time of the third stage, the glide segment, the second time of the third stage, the terminal velocity correction) and the satellite's orbit insertion situation (that is, the mission assessment result of the following space launch mission) for rapid assessment. According to the hierarchical division, the assessment criteria of the present disclosure can be divided into subsystem level, rocket level, and mission level; the subsystem level, mission level, and rocket level adopt the result assessment method; the sub-subsystem assessment of the subsystem adopts the process assessment method. Under the assessment criteria of the space launch mission, the mission-level assessment is mainly based on the final orbit insertion parameters of the satellite, and the assessment results of the space launch mission are divided into three basic conclusions: a complete success, a basic success, and a failure. For the assessment of the rocket level, it focuses on the completion of key actions, the flight trajectory of the launch vehicle, and whether the shutdown quantity requirements are met. Accordingly, the assessment results of the rocket flight situation are divided into three types: normal flight, basically normal, and abnormal. The assessment at the subsystem level pays more attention to the influence degree of each system on the flight mission of the launch vehicle, and divides the assessment results into three basic states: normal, basically normal, and abnormal.

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

[0066] The above 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] Using the preset process evaluation criteria corresponding to each preset evaluation element and matching the current rocket flight segment, the element evaluation results of each preset evaluation element are determined in real time. Specifically, it can be achieved through the following steps: For each subsystem, using the element-level process evaluation criteria corresponding to each preset evaluation element of the subsystem and matching the current rocket flight segment, the element evaluation results of each preset evaluation element of the subsystem are determined in real time; using the element evaluation results of each preset evaluation element and the subsystem-level process evaluation criteria matching the current rocket flight segment, the sub-task execution evaluation result of the subsystem within the current rocket flight segment is determined; among them, the subsystem-level process evaluation criteria corresponding to different subsystems are different.

[0068] A certain subsystem of the rocket adopts a hierarchical evaluation method. Combining the result evaluation criteria of each rocket subsystem and matching the current rocket flight segment, and the element evaluation results of each preset evaluation element, the real-time task evaluation results of each rocket subsystem within the current rocket flight segment are determined respectively. Specifically, it can be achieved through the following steps:

[0069] For each rocket subsystem, using the key parameter process evaluation criteria matching the current rocket flight segment and the parameter values of each key parameter, the parameter evaluation results of each key parameter within the current rocket flight segment are determined respectively; using the parameter evaluation results of each key parameter within the current rocket flight segment and the sub-task execution evaluation results of each subsystem within the current rocket flight segment, and combining the result evaluation criteria of the rocket subsystem and matching the current rocket flight segment, the real-time task evaluation result of the rocket subsystem within the current rocket flight segment is determined.

[0070] The functions of the real-time evaluation module include flight process (evaluation of the working conditions of subsystems / sub-systems in each rocket flight segment, evaluation of the overall rocket stage flight situation in each rocket flight segment, key actions) and result evaluation at the task level within the rocket flight segment (for example, evaluation corresponding to the satellite orbit elements). The evaluation of the working conditions of the rocket stage and each subsystem is usually carried out within 5 seconds after the end of the corresponding rocket flight segment; the key action evaluation is carried out within 1 second after the completion of the action.

[0071] The above process evaluation criteria refer to the methods for calculating the evaluation results, and their implementation forms include inference matrices, inference flowcharts, and inference scripts. At the same time, this real-time evaluation module supports the display and interaction of evaluation results, supports the display of the content of the object under evaluation in a hierarchical structure, and supports the user to display information at different levels; when the evaluation result is not normal, prominent colors are used for prompting and an alarm is given.

[0072] As Figure 2C shown, the above step S130 is completed by the result evaluation module, which supports evaluation methods such as result evaluation based on an inference table, flight result evaluation based on the orbital element (deviation) region, and flight result evaluation based on a function. This module supports the display of the theoretical values, actual values, and deviations of the orbital elements of the payload; when there are multiple payloads at the same time, the orbital elements of multiple payloads are compared and displayed in the same table, or each payload can be displayed as a separate table.

[0073] In some embodiments, as Figure 2C shown, it is also possible to receive the original data collected by the launch test mission data acquisition system through the evaluation data access module and perform some data processing and forwarding tasks. Specifically, the evaluation data access module performs the following operations:

[0074] Receive the original data collected by the launch test mission data acquisition system using the specified source UDP multicast method and the primary / backup 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 the satellite's orbit insertion parameters, the flight trajectory of the rocket, and environmental monitoring data; filter the original data or correct the data packets with incorrect formats to obtain the data to be forwarded; use the specified source UDP multicast method to forward the data to be forwarded to the corresponding processing modules (such as the real-time evaluation module, result evaluation module) to execute the space launch mission evaluation method.

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

[0076] The evaluation data connection 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 that need it in the system using the specified source UDP multicast method; this module supports selecting to forward / not forward specific category data; this module can filter or correct data packets with incorrect formats according to the relevant regulations of the internal application layer data communication protocol to ensure the maximum availability of the data, such as handling situations where the data length is incorrect or the frame tail is filled in incorrectly. The function of this module supports the primary and backup duplex mode. When the primary interface sends data into the system, the backup interface does not forward; when the backup interface detects that the primary interface is offline, it automatically switches to the primary interface. After the original faulty primary interface restarts automatically, it is set to the backup state; the primary and backup states of the interface can also be manually switched by the on-site personnel.

[0077] In some embodiments, such as Figure 2C shown, a web version of the evaluation report can also be generated by the evaluation report generation module. Specifically:

[0078] Using at least one of the real-time mission evaluation results of each rocket subsystem in each rocket flight segment, the rocket stage flight situation 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, a web version of the evaluation report is generated; among them, the web version of the evaluation report is presented in an animated manner.

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

[0080] In addition, as Figure 2C shown, the system corresponding to the space launch mission evaluation method can also include an evaluation management module. The evaluation management module is mainly responsible for constructing 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 strong data processing capabilities, including functions such as data parsing, legality checking, and data cleaning 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 evaluation system. The steps performed by the components of this system are the same as or similar to those of the above method. Therefore, similar parts will not be elaborated. As Figure 3 shown, the space launch mission evaluation system of this embodiment includes:

[0082] A flight segment determination module 310, configured to determine multiple rocket flight segments of a space launch mission.

[0083] A real-time evaluation module 320, configured to perform the following operations for each rocket flight segment to determine the real-time task evaluation results of each rocket subsystem, the rocket stage flight situation evaluation results, and the key action evaluation results within the corresponding rocket flight segment:

[0084] Respectively and in real time obtain the parameter values of each preset evaluation element of each rocket subsystem that match the current rocket flight segment; use the preset process evaluation criteria corresponding to each preset evaluation element and that match the current rocket flight segment to determine the element evaluation results of each preset evaluation element in real time; combine the result evaluation criteria of each rocket subsystem that match the current rocket flight segment and the element evaluation results of each preset evaluation element to determine the real-time task evaluation results of each rocket subsystem within the current rocket flight segment respectively;

[0085] Determine the key actions within the current rocket flight segment, and based on the real-time task evaluation results of each rocket subsystem, the execution standards of each key action, and the expected target results of each key action within the current rocket flight segment, use the result evaluation criteria matching each key action to determine the key action evaluation results corresponding to each key action respectively;

[0086] Determine the flight trajectory of the rocket within the current rocket flight segment and the information on whether the shutdown quantity requirement is met, and combine the key action evaluation results within the current rocket flight segment, and use the result evaluation criteria matching the current rocket flight segment to determine the rocket stage flight situation evaluation results of the current rocket flight segment;

[0087] A result evaluation module 330, configured to, after the separation of the satellite and the rocket, use the real-time task evaluation results of each rocket subsystem, the rocket stage flight situation evaluation results, the key action evaluation results, and the parameter values of the satellite's orbit insertion parameters within each rocket flight segment, and use the result evaluation criteria matching the space launch mission to determine the task evaluation results of the space launch mission.

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

[0089] Figure 4FIG. 0 shows a schematic block diagram of an exemplary electronic device 400 that may be used to implement embodiments of the present disclosure. The electronic device is intended to represent various forms of digital computers, such as, for example, a laptop computer, a desktop computer, a workbench, a personal digital assistant, a server, a blade server, a mainframe computer, and other suitable computers. The electronic device may also represent various forms of mobile devices, such as, for example, a personal digital processor, a cellular phone, a smart phone, a wearable device, and other similar computing devices. The components shown herein, their connections and relationships, and their functions are merely exemplary and are not intended to limit the implementations of the present disclosure described and / or claimed herein.

[0090] As Figure 4 shown, the device 400 includes a computing unit 410 that may perform various appropriate actions and processes in accordance with 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 may 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 plurality 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 magnetic 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 via a computer network such as the Internet and / or various telecommunication networks.

[0092] The computing unit 410 may be various general-purpose and / or special-purpose 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, a digital signal processor (DSP), and any suitable processor, controller, microcontroller, etc. The computing unit 410 executes 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 tangibly embodied in a machine-readable medium, such as the storage unit 480. In some embodiments, part or all of the computer program may be loaded and / or installed onto the device 400 via the ROM 420 and / or the communication unit 490. When the computer program is loaded into the RAM 430 and executed by the computing unit 410, one or more steps of any of the methods described above may be executed. Alternatively, in other embodiments, the computing unit 410 may be configured to execute any of the methods described above in any other suitable manner (e.g., by means of firmware).

[0093] Various embodiments of the systems and techniques described above herein can be implemented in digital electronic circuitry, integrated circuit systems, field-programmable gate arrays (FPGA), application-specific integrated circuits (ASIC), application-specific standard products (ASSP), systems-on-chip (SOC), complex programmable logic devices (CPLD), computer hardware, firmware, software, and / or combinations thereof. These various embodiments 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 receives data and instructions from a storage system, at least one input device, and at least one output device, and transmits the 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 methods of the present disclosure can be written in any combination of one or more programming languages. These program codes can be provided to a processor or controller of a general-purpose computer, a special-purpose computer, or other programmable data processing device, such that when the program codes are executed by the processor or controller, the functions / operations specified in the flowcharts and / or block diagrams are implemented. The program codes can be executed entirely on the machine, partially on the machine, as a stand-alone software package partially on the machine and partially on a remote machine, or entirely on a remote machine or server.

[0095] In the context of this disclosure, a machine-readable medium can be a tangible medium that can contain or store a program for use by or in connection with an instruction execution system, apparatus, or device. A machine-readable medium can be a machine-readable signal medium or a machine-readable storage medium. A machine-readable medium can include, but is not limited to, electronic, magnetic, optical, electromagnetic, infrared, or semiconductor systems, apparatus, or devices, or any suitable combination of the foregoing. More specific examples of a machine-readable storage medium would include an electrical connection based on one or more wires, a portable computer diskette, 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 disc read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing.

[0096] To provide for 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 a pointing device (e.g., a mouse or a trackball) by which the user can provide input to the computer. Other kinds of devices can also be used to provide for interaction with the user; for example, 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, speech, or tactile input).

[0097] The systems and techniques described herein can 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 having a graphical user interface or a web browser through which the user can interact with an implementation 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 can be interconnected by any form or medium of digital data communication (e.g., a communication network). Examples of a communication network include: a local area network (LAN), a wide area network (WAN), and the Internet.

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

[0099] It should be understood that the various forms of processes shown above can be used, with steps reordered, added or deleted. For example, the steps described in the present disclosure can be executed in parallel, sequentially, or in different orders, as long as the desired results of the technical solutions disclosed in the present disclosure can be achieved, and no limitations are imposed herein.

[0100] The above specific embodiments do not constitute a limitation on the protection scope of the present disclosure. Those skilled in the art should understand that various modifications, combinations, sub - combinations, and substitutions can be made according to design requirements and other factors. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present disclosure shall be included within the protection scope of the present disclosure.

Claims

1. A method for evaluating space launch missions, characterized in that, Including: Determine multiple rocket flight segments of a space launch mission; For each rocket flight segment, perform the following operations to determine the real-time task evaluation results of each rocket subsystem, the rocket stage flight situation evaluation results, and the critical action evaluation results within the corresponding rocket flight segment: Obtain in real time the parameter values of each preset evaluation element of each rocket subsystem that match 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 in real time the element evaluation results of each evaluation element; combine the result evaluation criteria of each rocket subsystem that match the current rocket flight segment and the element evaluation results of each evaluation element to determine respectively the real-time task evaluation results of each rocket subsystem within the current rocket flight segment; Determine the critical actions within the current rocket flight segment, and based on the real-time task evaluation results of each rocket subsystem, the execution standards of each critical action, and the expected target results of each critical action within the current rocket flight segment, use the result evaluation criteria matching each critical action to determine respectively the critical action evaluation results corresponding to each critical action; Determine the flight trajectory of the rocket within the current rocket flight segment and the information on whether the shutdown quantity requirement is met, and combine the critical action evaluation results within the current rocket flight segment to use the result evaluation criteria matching the current rocket flight segment to determine the rocket stage flight situation evaluation results of the current rocket flight segment; After the separation of the satellite and the rocket, use the real-time task evaluation results of each rocket subsystem, the rocket stage flight situation evaluation results, the critical action evaluation results, and the parameter values of the satellite's orbit injection parameters within each rocket flight segment, and use the result evaluation criteria matching the space launch mission to determine the mission evaluation results of the space launch mission; Wherein, the rocket subsystem includes multiple 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 using the preset process evaluation criteria corresponding to each preset evaluation element and matching the current rocket flight segment to determine in real time the element evaluation results of each evaluation element includes: For each subsystem, use the element-level process evaluation criteria corresponding to each preset evaluation element of the subsystem and matching the current rocket flight segment to determine in real time the element evaluation results of each evaluation element of the subsystem; use the element evaluation results of each evaluation element and the subsystem-level process evaluation criteria matching the current rocket flight segment to determine the sub-task execution evaluation results of the subsystem within the current rocket flight segment; wherein, the subsystem-level process evaluation criteria corresponding to different subsystems are different; The rocket subsystem includes at least one critical parameter; the preset process evaluation criteria include critical parameter process evaluation criteria matching each critical parameter; The combining the result evaluation criteria of each rocket subsystem that match the current rocket flight segment and the element evaluation results of each evaluation element to determine respectively the real-time task evaluation results of each rocket subsystem within the current rocket flight segment includes: For each rocket subsystem, the parameter evaluation results of each key parameter within the current rocket flight segment are determined respectively by using the process evaluation criteria of each key parameter matching the current rocket flight segment and the parameter values of each key parameter. Using the parameter evaluation results of each key parameter within the current rocket flight segment and the sub-task execution evaluation results of each subsystem within the current rocket flight segment, and combining the result evaluation criteria of this rocket subsystem that match the current rocket flight segment, the real-time task evaluation result of this rocket subsystem within the current rocket flight segment is determined. The following operations are also performed during the rocket flight segment: Based on the real-time task evaluation results of each rocket subsystem, the rocket stage flight situation evaluation results, and the key action evaluation results within this rocket flight segment, the task evaluation result of this rocket flight segment is determined by using the result evaluation criteria that match the flight task of this rocket flight segment.

2. The method according to claim 1, characterized in that, It also includes: Receiving the raw data collected by the launch test mission data acquisition system using the specified source UDP multicast method and the primary and standby duplex mode; where the raw data includes at least one of the following: the parameter values of the engine temperature, fuel consumption rate, flight attitude data, structural stress state, satellite orbit injection parameters, rocket flight trajectory, and environmental monitoring data. Filtering the raw data or correcting the data packets with incorrect formats to obtain the data to be forwarded. Using the specified source UDP multicast method to forward the data to be forwarded to the corresponding processing module to execute the space launch mission evaluation method.

3. The method according to claim 1, characterized in that, The determination of multiple rocket flight segments for the space launch mission includes: Defining the flight segments of each rocket stage with the rocket timing string parameters to obtain multiple rocket flight segments.

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

5. The method according to claim 1, characterized in that, It also includes: Generating a web version evaluation report by using at least one of the real-time task evaluation results of each rocket subsystem, the rocket stage flight situation evaluation results, the key action evaluation results, the task evaluation results of the space launch mission, and the task evaluation results of each rocket flight segment within each rocket flight segment; where the web version evaluation report is presented in an animated way.

6. A space launch mission evaluation system, characterized in that, It includes: A flight segment determination module for determining multiple rocket flight segments of the space launch mission. A real-time evaluation module for performing the following operations for each rocket flight segment to determine the real-time task evaluation results, rocket stage flight situation evaluation results, and key action evaluation results of each rocket subsystem within the corresponding rocket flight segment: Obtaining in real time the parameter values of each preset evaluation element of each rocket subsystem that match the current rocket flight segment respectively; determining in real time the element evaluation results of each preset evaluation element by using the preset process evaluation criteria corresponding to each preset evaluation element and matching the current rocket flight segment; and determining the real-time task evaluation results of each rocket subsystem within the current rocket flight segment respectively by combining the result evaluation criteria of each rocket subsystem that match the current rocket flight segment and the element evaluation results of each preset evaluation element. Determine the key actions within the current rocket flight segment, and based on the real-time task evaluation results of each rocket subsystem within the current rocket flight segment, the execution criteria of each key action, and the expected target results of each key action, use the result evaluation criteria matching each key action to respectively determine the key action evaluation results corresponding to each key action; Determine the flight trajectory of the rocket within the current rocket flight segment and the information on whether the shutdown quantity requirement is met, and in combination with the key action evaluation results within the current rocket flight segment, use the result evaluation criteria matching the current rocket flight segment to determine the rocket stage flight situation evaluation result of the current rocket flight segment; A result evaluation module, used after the separation of the satellite and the rocket, to determine the mission evaluation result of the space launch mission by using the real-time task evaluation results of each rocket subsystem within each rocket flight segment, the rocket stage flight situation evaluation result, the key action evaluation result, and the parameter values of the satellite's orbit insertion parameters, and by using the result evaluation criteria matching the space launch mission; Among them, the rocket subsystem includes multiple 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 real-time determination of the element evaluation results of each preset evaluation element by using the preset process evaluation criteria corresponding to each preset evaluation element and matching the current rocket flight segment includes: For each subsystem, use the element-level process evaluation criteria corresponding to each preset evaluation element of the subsystem and matching the current rocket flight segment to real-time determine the element evaluation results of each preset evaluation element of the subsystem; use the element evaluation results of each preset evaluation element and the subsystem-level process evaluation criteria matching the current rocket flight segment to determine the sub-task execution evaluation result of the subsystem within the current rocket flight segment; among them, the subsystem-level process evaluation criteria corresponding to different subsystems are different; 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 real-time task evaluation results of each rocket subsystem within the current rocket flight segment are respectively determined by combining the result evaluation criteria of each rocket subsystem matching the current rocket flight segment and the element evaluation results of each preset evaluation element, including: For each rocket subsystem, use the key parameter process evaluation criteria matching the current rocket flight segment and the parameter values of each key parameter to respectively determine the parameter evaluation results of each key parameter within the current rocket flight segment; Use the parameter evaluation results of each key parameter within the current rocket flight segment and the sub-task execution evaluation results of each subsystem within the current rocket flight segment, and in combination with the result evaluation criteria of the rocket subsystem matching the current rocket flight segment, to determine the real-time task evaluation result of the rocket subsystem within the current rocket flight segment; During the rocket flight segment, the real-time evaluation module also performs the following operations: Based on the real-time mission evaluation results of each rocket subsystem, the evaluation results of the rocket stage flight conditions, and the evaluation results of key actions during this rocket flight segment, the mission evaluation result of this rocket flight segment is determined using the result evaluation criteria that match the flight mission of this rocket flight segment.

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