Carrier rocket flight state analysis method, device, equipment and medium

Abstract

The invention provides a carrier rocket flight state analysis method, device and equipment and a medium, and the method comprises the steps: obtaining the flight parameters of a carrier rocket in the flight process of the carrier rocket, carrying out the abnormality analysis of the flight parameters, and generating a flight parameter analysis result; after the carrier rocket completes the current flight action, acquiring evaluation parameters required for evaluating the current flight action, and generating an action analysis result of the current flight action according to an action evaluation rule corresponding to the current flight action and the evaluation parameters; and after the carrier rocket completes satellite-rocket separation, generating a task analysis result of a current flight task by using a task evaluation rule based on a flight action analysis result, a satellite-rocket separation action analysis result and a satellite injection action analysis result of the carrier rocket. By means of the method and device, the flight state is evaluated stably and efficiently, and meanwhile the evaluation rules are repeatedly used.

Description

Technical Field

[0001] The present application relates to the field of aerospace technology, and in particular to a method, device, equipment and medium for analyzing the flight status of a launch vehicle. Background Art

[0002] Rapid assessment of launch vehicle flight refers to the assessment of the rocket's flight process and orbital insertion results. By comprehensively analyzing and interpreting the launch vehicle's real-time flight data, it is determined whether its flight status is normal and flight problems are discovered in a timely manner so that corresponding measures can be taken quickly.

[0003] With the increasing number of space missions, the demand for rapid assessment is also increasing, primarily in terms of reliability, reusability, and real-time performance. However, there is currently no systematic research on launch vehicle flight status assessment. Rapid assessment rules for test missions can only be developed based on engineers' experience and summarizing launch vehicle flight characteristics. Relying solely on engineers' experience to assess launch vehicles is often unreliable. The assessment rules developed by engineers may not be applicable to all launch vehicles, and manual assessment is inefficient, resulting in poor real-time performance. Summary of the Invention

[0004] In view of this, the purpose of this application is to provide a method, device, equipment and medium for analyzing the flight status of a launch vehicle. By analyzing the flight status of the launch vehicle, the analysis is divided into three levels: parameter analysis, action analysis and task analysis, and the corresponding analysis results are determined by pre-set evaluation rules. This solves the problems in the existing technology of poor reliability, poor reusability and low real-time performance caused by the dependence of the flight status evaluation of the launch vehicle on the personal experience of engineers, and realizes stable and efficient assessment of the flight status, while realizing the reuse of evaluation rules.

[0005] In a first aspect, an embodiment of the present application provides a method for analyzing the flight status of a carrier rocket, the method comprising:

[0006] During the flight of the carrier rocket, obtaining flight parameters of the carrier rocket, performing abnormality analysis on the flight parameters, and generating flight parameter analysis results;

[0007] After the carrier rocket completes a current flight action, obtaining evaluation parameters required for evaluating the current flight action, and generating an action analysis result of the current flight action according to an action evaluation rule corresponding to the current flight action and the evaluation parameters;

[0008] After the carrier rocket completes the satellite-rocket separation, the mission analysis result of the current flight mission of the carrier rocket is generated using the mission assessment rules based on the flight action analysis result of the carrier rocket, the satellite-rocket separation action analysis result and the satellite orbit insertion action analysis result.

[0009] Furthermore, performing abnormal analysis on the flight parameters and generating flight parameter analysis results includes:

[0010] Selecting the flight parameters using a cellular automaton model to determine target parameter values ​​of the launch vehicle at each flight time point;

[0011] A parameter range curve is obtained, and an abnormality analysis is performed on the target parameter value corresponding to each flight time point based on the parameter range curve to obtain the flight parameter analysis result.

[0012] Furthermore, the method of selecting the flight parameters using a cellular automaton model to determine the target parameter values ​​of the launch vehicle at each flight time point includes:

[0013] Dividing a two-dimensional plane into a plurality of grids based on the cellular automaton model, and adding the flight parameters into the two-dimensional plane; wherein the abscissa of the two-dimensional plane represents the flight time of the carrier rocket, and the ordinate of the two-dimensional plane represents the flight parameters;

[0014] For each grid corresponding to each flight time point, determine the number of flight parameters belonging to the grid, and determine a score corresponding to the grid based on the number;

[0015] The flight parameter in the grid with the highest score among the multiple grids is determined as the target parameter value corresponding to the flight time point.

[0016] Furthermore, performing an abnormality analysis on the target parameter value corresponding to each flight time point based on the parameter range curve to obtain the flight parameter analysis result includes:

[0017] If the parameter range curve is of the first curve type, for each flight time point, determining the parameter range corresponding to the flight time point in the parameter range curve, and determining a flight parameter analysis result of the target parameter value corresponding to the flight time point based on the parameter range and the target parameter value corresponding to the flight time point;

[0018] If the parameter range curve is of the second curve type, for each flight time point, the flight parameter analysis result of the target parameter value corresponding to the flight time point is determined using the even-odd rule.

[0019] Furthermore, when the current flight maneuver is a takeoff maneuver, obtaining evaluation parameters required for evaluating the current flight maneuver and generating an action analysis result of the current flight maneuver based on an action evaluation rule corresponding to the current flight maneuver and the evaluation parameters includes:

[0020] When the carrier rocket leaves the launch pad during the takeoff period, a signal acquisition parameter is acquired; wherein the signal acquisition parameter indicates whether the carrier rocket sends a takeoff signal and the time when the takeoff signal is received;

[0021] When the carrier rocket leaves the tower vertically, obtaining the attitude angle deviation of the carrier rocket;

[0022] When the thrust of the carrier rocket is established, obtaining a speed change of the carrier rocket;

[0023] Based on the signal acquisition parameters, the attitude angle deviation and the speed change, the action analysis result is determined according to the action evaluation rule.

[0024] Furthermore, the action assessment rule includes a first assessment rule, a second assessment rule, and a third assessment rule, wherein the first assessment rule is that the takeoff signal of the carrier rocket is received within a preset time, the second assessment rule is that the attitude angle deviation does not exceed a first deviation threshold, and the third assessment rule is that the speed of the carrier rocket increases;

[0025] The step of determining the motion analysis result based on the signal acquisition parameter, the attitude angle deviation, and the speed change according to the motion assessment rule includes:

[0026] When the signal acquisition parameter meets the first evaluation rule, the attitude angle deviation meets the second evaluation rule, and the speed change meets the third evaluation rule, then determining that the action analysis result is that the current flight action is normal;

[0027] When the signal acquisition parameter meets the first evaluation rule and the attitude angle deviation does not meet the second evaluation rule, determining that the action analysis result is that the current flight action is abnormal;

[0028] When the signal acquisition parameter does not meet the first evaluation rule, the attitude angle deviation meets the second evaluation rule, and the speed change meets the third evaluation rule, then determining that the action analysis result is that the current flight action is normal;

[0029] When the signal acquisition parameter does not meet the first evaluation rule, the attitude angle deviation does not meet the second evaluation rule, and the speed change meets the third evaluation rule, the action analysis result is determined to be that the current flight action is abnormal.

[0030] Furthermore, the generating of the mission analysis result of the current flight mission of the carrier rocket using the mission assessment rules based on the flight action analysis result of the carrier rocket, the satellite-rocket separation action analysis result, and the satellite orbit insertion action analysis result includes:

[0031] When the flight action analysis result of the carrier rocket is stable flight according to the predetermined orbit, the satellite-rocket separation action analysis result is that the satellite is sent into the predetermined orbit, and the satellite orbit insertion action analysis result is that the satellite orbit insertion parameter deviation does not exceed the second deviation threshold, then the mission analysis result is a mission success;

[0032] When the flight action analysis result of the carrier rocket is stable flight according to the predetermined orbit, the satellite-rocket separation action analysis result is that the satellite is sent into the predetermined orbit, and the satellite orbit insertion action analysis result is that the satellite orbit insertion parameter deviation exceeds the second deviation threshold, then the mission analysis result is that the mission is basically successful;

[0033] When the satellite orbit insertion action analysis result of the carrier rocket is that the satellite has not entered orbit, the mission analysis result is mission failure.

[0034] In a second aspect, an embodiment of the present application further provides a device for analyzing the flight status of a carrier rocket, the device comprising:

[0035] A parameter analysis module is used to obtain the flight parameters of the carrier rocket during the flight of the carrier rocket, perform abnormality analysis on the flight parameters, and generate flight parameter analysis results;

[0036] a motion analysis module, configured to obtain, after the launch vehicle completes a current flight action, evaluation parameters required for evaluating the current flight action, and generate a motion analysis result of the current flight action based on an action evaluation rule corresponding to the current flight action and the evaluation parameters;

[0037] The mission analysis module is used to generate a mission analysis result of the current flight mission of the carrier rocket based on the flight action analysis result of the carrier rocket, the satellite-rocket separation action analysis result and the satellite orbit insertion action analysis result after the carrier rocket completes the satellite-rocket separation.

[0038] In a third aspect, an embodiment of the present application also provides an electronic device comprising: a processor, a memory and a bus, wherein the memory stores machine-readable instructions executable by the processor. When the electronic device is running, the processor and the memory communicate through the bus, and when the machine-readable instructions are executed by the processor, the steps of the method for analyzing the flight status of a launch vehicle as described above are performed.

[0039] In a fourth aspect, an embodiment of the present application further provides a computer-readable storage medium, on which a computer program is stored. When the computer program is run by a processor, the steps of the method for analyzing the flight status of a launch vehicle as described above are executed.

[0040] The embodiments of the present application provide a method, apparatus, equipment and medium for analyzing the flight status of a carrier rocket. First, during the flight of the carrier rocket, the flight parameters of the carrier rocket are obtained, and the flight parameters are analyzed for abnormalities to generate flight parameter analysis results. Then, after the carrier rocket completes the current flight action, the evaluation parameters required for evaluating the current flight action are obtained, and the action analysis results of the current flight action are generated according to the action evaluation rules corresponding to the current flight action and the evaluation parameters. After the carrier rocket completes the separation of the satellite and the rocket, the mission analysis results of the current flight mission of the carrier rocket are generated using the mission evaluation rules based on the flight action analysis results of the carrier rocket, the satellite-rocket separation action analysis results and the satellite orbit insertion action analysis results.

[0041] This application analyzes the flight status of a launch vehicle and divides the analysis into three levels: parameter analysis, motion analysis, and task analysis. The corresponding analysis results are determined by pre-set evaluation rules. This solves the problems in the existing technology of poor reliability, poor reusability, and low real-time performance caused by reliance on the personal experience of engineers in the flight status assessment of launch vehicles. It achieves stable and efficient assessment of the flight status and the reuse of evaluation rules.

[0042] In order to make the above-mentioned objects, features and advantages of the present application more obvious and easy to understand, preferred embodiments are given below and described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following is a brief introduction to the drawings required for use in the embodiments. It should be understood that the following drawings only show certain embodiments of the present application and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without creative work.

[0044] Figure 1 A flowchart of a method for analyzing the flight status of a carrier rocket provided in an embodiment of the present application;

[0045] Figure 2 A schematic diagram of an even-odd rule provided in an embodiment of the present application;

[0046] Figure 3 A schematic diagram of the structure of a device for analyzing the flight status of a carrier rocket provided in an embodiment of the present application;

[0047] Figure 4 A schematic diagram of the structure of an electronic device provided in an embodiment of the present application. DETAILED DESCRIPTION

[0048] In order to make the purpose, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all of the embodiments. The components of the embodiments of the present application generally described and shown in the drawings here can be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of the present application provided in the drawings is not intended to limit the scope of the application for which protection is claimed, but merely represents the selected embodiments of the present application. Based on the embodiments of the present application, each other embodiment obtained by those skilled in the art without making creative work falls within the scope of protection of the present application.

[0049] First, the application scenarios to which this application is applicable are introduced. This application can be applied in the field of aerospace technology.

[0050] Rapid assessment of launch vehicle flight refers to the assessment of the rocket's flight process and orbital insertion results. By comprehensively analyzing and interpreting the launch vehicle's real-time flight data, it is determined whether its flight status is normal and flight problems are discovered in a timely manner so that corresponding measures can be taken quickly.

[0051] With the increasing number of space missions, the demand for rapid assessment is also increasing, primarily in terms of reliability, reusability, and real-time performance. However, there is currently no systematic research on launch vehicle flight status assessment. Rapid assessment rules for test missions can only be developed based on engineers' experience and summarizing launch vehicle flight characteristics. Relying solely on engineers' experience to assess launch vehicles is often unreliable. The assessment rules developed by engineers may not be applicable to all launch vehicles, and manual assessment is inefficient, resulting in poor real-time performance.

[0052] Based on this, an embodiment of the present application provides a method for analyzing the flight status of a launch vehicle, which solves the problems in the prior art of relying on the personal experience of engineers to evaluate the flight status of launch vehicles, resulting in poor reliability, poor reusability, and low real-time performance. It achieves stable and efficient assessment of the flight status and the reuse of assessment rules.

[0053] See also Figure 1 , Figure 1 This is a flow chart of a method for analyzing the flight status of a carrier rocket provided in an embodiment of the present application. Figure 1As shown in , the analysis method provided in the embodiment of the present application includes:

[0054] S101, during the flight of a carrier rocket, obtaining flight parameters of the carrier rocket, performing abnormality analysis on the flight parameters, and generating flight parameter analysis results.

[0055] Here, we first analyze the flight parameters of the launch vehicle. Parameter analysis refers to interpreting the flight parameters during the launch vehicle's flight, analyzing any anomalies in the flight parameters, and generating real-time flight parameter analysis results.

[0056] Regarding step S101 above, during the specific implementation, the launch vehicle's flight parameters are first obtained during the launch vehicle's flight. According to the embodiments provided herein, the launch vehicle's flight parameters can be obtained through various methods, such as radar, Doppler, optical, and GNSS. The flight parameters are then analyzed for anomalies to generate flight parameter analysis results.

[0057] As an optional embodiment, with respect to step S101 above, performing abnormality analysis on the flight parameters and generating flight parameter analysis results includes:

[0058] Step 1011: Use a cellular automaton model to select the flight parameters and determine the target parameter values ​​of the launch vehicle at each flight time point.

[0059] The cellular automata (CA) model is a grid dynamics model in which time, space, and state are all discrete, and spatial interactions and temporal causality are localized. It is capable of simulating the spatiotemporal evolution of complex systems. It can construct systems whose states transition over time. Cells exist in a one-dimensional or multidimensional grid, each with one or more states and neighbors. The flight time points here refer to various points in the launch vehicle's flight.

[0060] Regarding the above step 1011, during specific implementation, the cellular automaton model is used to select the acquired flight parameters to determine the target parameter values ​​of the launch vehicle at each flight time point.

[0061] Specifically, with respect to the above step 1011, the use of the cellular automaton model to select the flight parameters and determine the target parameter values ​​of the launch vehicle at each flight time point includes:

[0062] Step 10111: divide the two-dimensional plane into multiple grids based on the cellular automaton model, and add the flight parameters into the two-dimensional plane.

[0063] Here, the abscissa of the two-dimensional plane represents the flight time of the launch vehicle, and the ordinate of the two-dimensional plane represents the flight parameters.

[0064] In the specific implementation of step 10111, a two-dimensional plane is divided into a grid based on a cellular automaton model. The horizontal axis represents the launch vehicle's flight time, and the vertical axis represents flight parameters collected through various methods such as radar, Doppler, optical, and GNSS. The flight parameters are then added to the two-dimensional plane, and each flight parameter falls into a corresponding grid.

[0065] Step 10112: for each grid corresponding to each flight time point, determine the number of flight parameters belonging to the grid, and determine a score corresponding to the grid based on the number;

[0066] Step 10113: Determine the flight parameter in the grid with the highest score among the multiple grids as the target parameter value corresponding to the flight time point.

[0067] For each grid at the same flight time point, each grid point receives one point for each flight parameter it falls into. Flight parameters may not necessarily fall into the same grid point. The grid with the highest score is the target parameter value for that flight time point. Regarding steps 10112-10113, in specific implementations, for each grid point corresponding to each flight time point, the number of flight parameters belonging to that grid point is determined, and the score corresponding to that grid point is determined based on this number. The flight parameter in the grid with the highest score among the multiple grid points is then determined as the target parameter value for that flight time point.

[0068] Step 1012: Obtain a parameter range curve, and perform an abnormality analysis on the target parameter value corresponding to each flight time point based on the parameter range curve to obtain the flight parameter analysis result.

[0069] Here, the parameter range curve can be a parameter pipeline. Whether a parameter is abnormal is determined by checking whether it falls within the pipeline. If the parameter value is within the pipeline, it is normal; otherwise, it is abnormal. The pipeline refers to the normal range of parameter values ​​in the time dimension.

[0070] Regarding the above step 1012, during specific implementation, a parameter range curve is obtained, and an abnormality analysis is performed on the target parameter value corresponding to each flight time point based on the parameter range curve to obtain a flight parameter analysis result.

[0071] As an optional embodiment, with respect to step 1012, performing an abnormality analysis on the target parameter value corresponding to each flight time point based on the parameter range curve to obtain the flight parameter analysis result includes:

[0072] Step 10121, if the parameter range curve is of the first curve type, for each flight time point, the parameter range corresponding to the flight time point is determined in the parameter range curve, and the flight parameter analysis result of the target parameter value corresponding to the flight time point is determined based on the parameter range and the target parameter value corresponding to the flight time point.

[0073] Here, the first curve type refers to a range curve with only simple upper and lower boundaries. Therefore, it is only necessary to determine whether the target parameter value is greater than (less than) the upper boundary (lower boundary) to determine whether the target parameter value is within the range.

[0074] Regarding step 10121, in a specific implementation, if the parameter range curve is of the first curve type, for each flight time point, the parameter range corresponding to that flight time point is determined in the parameter range curve, and a flight parameter analysis result for the target parameter value corresponding to that flight time point is determined based on the parameter range and the target parameter value corresponding to that flight time point. Here, if the target parameter value is within the parameter range, the flight parameter analysis result for that target parameter value is considered normal; if the target parameter value is not within the parameter range, the flight parameter analysis result for that target parameter value is considered abnormal.

[0075] Step 10122: If the parameter range curve is of the second curve type, for each flight time point, the flight parameter analysis result of the target parameter value corresponding to the flight time point is determined using the even-odd rule.

[0076] Here, the second curve type refers to a range curve with complex boundary characteristics such as a “concave” curve, that is, there are two parameter ranges at the same flight time point.

[0077] Regarding the above step 10122, during specific implementation, if the parameter range curve is of the second curve type, for each flight time point, the flight parameter analysis result of the target parameter value corresponding to the flight time point is determined using the odd-even rule. Specifically, when the parameter range curve is a curve with complex boundary characteristics such as a "concave" curve, simple upper and lower boundary judgments will fail. At this time, the above problem is abstracted into a problem of detecting whether a point is inside a polygon using a spatial topology analysis method, and the odd-even rule in topological graphics is introduced to solve it. The odd-even rule (Odd-Even Rule) is to draw a horizontal ray from an arbitrary position p. If the number of polygons intersecting with the ray is odd, then p is a point inside the polygon, otherwise it is a point outside the polygon. Please refer to Figure 2 , Figure 2 This is a schematic diagram of an even-odd rule provided in an embodiment of the present application. Figure 2As shown in the figure, the number of intersections between the ray starting from the target parameter value point B and the curve is an even number (2), while the number of intersections between the ray starting from the target parameter value point A and the curve is an odd number (3). Therefore, it can be determined that the target parameter value point B is outside the parameter range curve, that is, the flight parameter analysis result of the target parameter value B is abnormal; the target parameter value point A is within the parameter range curve, that is, the flight parameter analysis result of the target parameter value A is normal.

[0078] S102, after the carrier rocket completes the current flight action, obtains the evaluation parameters required for evaluating the current flight action, and generates the action analysis result of the current flight action according to the action evaluation rules corresponding to the current flight action and the evaluation parameters.

[0079] Here, action analysis refers to the collection of relevant evaluation parameters as evaluation factors after the launch vehicle completes a certain action, and the analysis results of the completion of the flight action are obtained based on the action evaluation rules.

[0080] Regarding the above step S102, in the specific implementation, after the carrier rocket completes the current flight action, the evaluation parameters required for evaluating the current flight action are obtained, and the flight action analysis results of the current flight action are generated according to the action evaluation rules and evaluation parameters corresponding to the current flight action.

[0081] As an optional embodiment, with respect to step S102 above, when the current flight maneuver is a takeoff maneuver, obtaining evaluation parameters required for evaluating the current flight maneuver and generating a motion analysis result of the current flight maneuver based on the motion evaluation rules corresponding to the current flight maneuver and the evaluation parameters includes:

[0082] Step 1021: When the carrier rocket leaves the launch pad during the takeoff period, signal acquisition parameters are acquired.

[0083] Here, the signal acquisition parameter indicates whether the carrier rocket sends a takeoff signal and the time when the takeoff signal is received.

[0084] Regarding the above-mentioned step 1021, during the specific implementation, when the carrier rocket leaves the launch pad during the takeoff period, the two parallel takeoff contacts are connected, and the takeoff signal of the carrier rocket is sent. The signal acquisition parameters are the evaluation factors, namely, whether the carrier rocket sends a takeoff signal and the time when the takeoff signal is received.

[0085] Step 1022: When the carrier rocket leaves the tower vertically, obtain the attitude angle deviation of the carrier rocket.

[0086] Regarding the above step 1022, during specific implementation, when the carrier rocket leaves the tower vertically, the attitude angle deviation (ΔΦ, ΔΨ, Δγ) is selected as an evaluation factor to obtain the attitude angle deviation of the carrier rocket.

[0087] Step 1023: When the thrust of the carrier rocket is established, obtain the speed change of the carrier rocket.

[0088] Regarding the above step 1023, during specific implementation, when the thrust of the carrier rocket is established, the speed should gradually increase. At this time, the speed change of the carrier rocket is selected as the evaluation factor to obtain the speed change of the carrier rocket.

[0089] Step 1024: Determine the motion analysis result based on the signal acquisition parameters, the attitude angle deviation, and the speed change according to the motion assessment rule.

[0090] Regarding the above step 1024, during specific implementation, based on the signal acquisition parameters, attitude angle deviation and speed change obtained in the above step, the motion analysis result is determined according to the pre-set motion evaluation rules.

[0091] Specifically, according to the embodiments provided herein, the action assessment rules include a first assessment rule, a second assessment rule, and a third assessment rule. The first assessment rule is that the launch vehicle's takeoff signal is received within a preset time, for example, within 100 seconds. The second assessment rule is that the attitude angle deviation does not exceed a first deviation threshold, for example, the attitude angle deviation does not exceed 100 degrees. The third assessment rule is that the launch vehicle's speed increases.

[0092] As an optional embodiment, with respect to step 1024, determining the motion analysis result according to the motion assessment rule based on the signal acquisition parameter, the attitude angle deviation, and the speed change includes:

[0093] A: When the signal acquisition parameters meet the first evaluation rule, the attitude angle deviation meets the second evaluation rule, and the speed change meets the third evaluation rule, the action analysis result is determined to be that the current flight action is normal.

[0094] B: When the signal acquisition parameter meets the first evaluation rule and the attitude angle deviation does not meet the second evaluation rule, it is determined that the action analysis result is that the current flight action is abnormal.

[0095] C: When the signal acquisition parameter does not meet the first evaluation rule, the attitude angle deviation meets the second evaluation rule, and the speed change meets the third evaluation rule, then the action analysis result is determined to be that the current flight action is normal.

[0096] D: When the signal acquisition parameter does not meet the first evaluation rule, the attitude angle deviation does not meet the second evaluation rule, and the speed change meets the third evaluation rule, the action analysis result is determined to be that the current flight action is abnormal.

[0097] With respect to the above-mentioned steps A to D, during specific implementation, when the signal acquisition parameters meet the first evaluation rule, the attitude angle deviation meets the second evaluation rule, and the speed change meets the third evaluation rule, then the motion analysis result is determined to be normal for the current flight action. When the signal acquisition parameters meet the first evaluation rule, and the attitude angle deviation does not meet the second evaluation rule, then the motion analysis result is determined to be abnormal for the current flight action. When the signal acquisition parameters do not meet the first evaluation rule, the attitude angle deviation meets the second evaluation rule, and the speed change meets the third evaluation rule, then the motion analysis result is determined to be normal for the current flight action. When the signal acquisition parameters do not meet the first evaluation rule, the attitude angle deviation does not meet the second evaluation rule, and the speed change meets the third evaluation rule, then the motion analysis result is determined to be abnormal for the current flight action.

[0098] S103, after the carrier rocket completes the satellite-rocket separation, based on the flight action analysis results of the carrier rocket, the satellite-rocket separation action analysis results and the satellite orbit insertion action analysis results, a mission analysis result of the current flight mission of the carrier rocket is generated using mission assessment rules.

[0099] Here, mission analysis refers to the generation of mission analysis results based on the mission assessment rules after the separation of the carrier rocket and the satellite, based on the comprehensive flight conditions, satellite-rocket separation conditions, and satellite orbit entry conditions.

[0100] Regarding step S103 above, in specific implementation, after the launch vehicle completes satellite-rocket separation, a mission analysis result is generated using pre-set mission assessment rules based on the launch vehicle's flight performance, satellite-rocket separation performance, and satellite orbital insertion performance. Specifically, the input to the mission analysis is the conclusion of the motion analysis results, such as the flight motion analysis results, satellite-rocket separation motion analysis results, and satellite orbital insertion motion analysis results. Mission analysis results include mission success, mission near success, and mission failure. The flight motion analysis results, satellite-rocket separation motion analysis results, and satellite orbital insertion motion analysis results here can be determined through the motion analysis process in step S102 above.

[0101] As an optional embodiment, with respect to the above step S103, generating a mission analysis result of the current flight mission of the carrier rocket using a mission assessment rule based on the flight action analysis result of the carrier rocket, the rocket-satellite separation action analysis result, and the satellite orbit insertion action analysis result includes:

[0102] Step 1031: When the flight action analysis result of the carrier rocket is stable flight according to the predetermined orbit, the satellite-rocket separation action analysis result is that the satellite is sent into the predetermined orbit, and the satellite orbit entry action analysis result is that the satellite orbit entry parameter deviation does not exceed the second deviation threshold, then the mission analysis result is that the mission is successful.

[0103] Step 1032: When the flight action analysis result of the carrier rocket is stable flight according to the predetermined orbit, the satellite-rocket separation action analysis result is that the satellite is sent into the predetermined orbit, and the satellite orbit entry action analysis result is that the satellite orbit entry parameter deviation exceeds the second deviation threshold, then the mission analysis result is that the mission is basically successful.

[0104] Step 1033: When the satellite orbit insertion action analysis result of the carrier rocket is that the satellite has not entered orbit, the mission analysis result is mission failure.

[0105] With respect to steps 1031 to 1033 above, in a specific implementation, when the launch vehicle's flight action analysis result indicates stable flight according to the predetermined orbit, the satellite-rocket separation action analysis result indicates that the satellite is delivered into the predetermined orbit, and the satellite orbit insertion action analysis result indicates that the satellite orbit insertion parameter deviation does not exceed the second deviation threshold, then the mission analysis result indicates that the mission is successful. When the launch vehicle's flight action analysis result indicates stable flight according to the predetermined orbit, the satellite-rocket separation action analysis result indicates that the satellite is delivered into the predetermined orbit, and the satellite orbit insertion action analysis result indicates that the satellite orbit insertion parameter deviation exceeds the second deviation threshold, then the mission analysis result indicates that the mission is basically successful. When the launch vehicle's satellite orbit insertion action analysis result indicates that the satellite has not entered orbit, then the mission analysis result indicates that the mission has failed.

[0106] The method for analyzing the flight status of a carrier rocket provided in an embodiment of the present application first obtains the flight parameters of the carrier rocket during the flight of the carrier rocket, performs an abnormality analysis on the flight parameters, and generates a flight parameter analysis result; then, after the carrier rocket completes the current flight action, obtains the evaluation parameters required for evaluating the current flight action, and generates an action analysis result of the current flight action according to the action evaluation rules corresponding to the current flight action and the evaluation parameters; after the carrier rocket completes the satellite-rocket separation, based on the flight action analysis result of the carrier rocket, the satellite-rocket separation action analysis result, and the satellite orbit insertion action analysis result, a mission analysis result of the current flight mission of the carrier rocket is generated using a mission evaluation rule.

[0107] This application analyzes the flight status of a launch vehicle and divides the analysis into three levels: parameter analysis, motion analysis, and task analysis. The corresponding analysis results are determined by pre-set evaluation rules. This solves the problems in the existing technology of poor reliability, poor reusability, and low real-time performance caused by reliance on the personal experience of engineers in the flight status assessment of launch vehicles. It achieves stable and efficient assessment of the flight status and the reuse of evaluation rules.

[0108] See also Figure 3 , Figure 3 This is a schematic diagram of the structure of a device for analyzing the flight status of a carrier rocket provided in an embodiment of the present application. Figure 3 As shown in , the analysis device 300 includes:

[0109] The parameter analysis module 301 is used to obtain the flight parameters of the carrier rocket during its flight, perform abnormality analysis on the flight parameters, and generate flight parameter analysis results;

[0110] The motion analysis module 302 is configured to obtain evaluation parameters required for evaluating the current flight action after the launch vehicle completes the current flight action, and generate a motion analysis result of the current flight action based on the action evaluation rules corresponding to the current flight action and the evaluation parameters;

[0111] The mission analysis module 303 is used to generate a mission analysis result of the current flight mission of the carrier rocket based on the flight action analysis result of the carrier rocket, the satellite-rocket separation action analysis result and the satellite orbit insertion action analysis result after the carrier rocket completes the satellite-rocket separation.

[0112] Furthermore, when the parameter analysis module 301 is used to perform abnormality analysis on the flight parameters and generate flight parameter analysis results, the parameter analysis module 301 is also used to:

[0113] Selecting the flight parameters using a cellular automaton model to determine target parameter values ​​of the launch vehicle at each flight time point;

[0114] A parameter range curve is obtained, and an abnormality analysis is performed on the target parameter value corresponding to each flight time point based on the parameter range curve to obtain the flight parameter analysis result.

[0115] Furthermore, when the parameter analysis module 301 is used to select the flight parameters using the cellular automaton model and determine the target parameter value of the launch vehicle at each flight time point, the parameter analysis module 301 is further used to:

[0116] Dividing a two-dimensional plane into a plurality of grids based on the cellular automaton model, and adding the flight parameters into the two-dimensional plane; wherein the abscissa of the two-dimensional plane represents the flight time of the carrier rocket, and the ordinate of the two-dimensional plane represents the flight parameters;

[0117] For each grid corresponding to each flight time point, determine the number of flight parameters belonging to the grid, and determine a score corresponding to the grid based on the number;

[0118] The flight parameter in the grid with the highest score among the multiple grids is determined as the target parameter value corresponding to the flight time point.

[0119] Furthermore, when the parameter analysis module 301 is used to perform an abnormality analysis on the target parameter value corresponding to each flight time point based on the parameter range curve to obtain the flight parameter analysis result, the parameter analysis module 301 is further used to:

[0120] If the parameter range curve is of the first curve type, for each flight time point, determining the parameter range corresponding to the flight time point in the parameter range curve, and determining a flight parameter analysis result of the target parameter value corresponding to the flight time point based on the parameter range and the target parameter value corresponding to the flight time point;

[0121] If the parameter range curve is of the second curve type, for each flight time point, the flight parameter analysis result of the target parameter value corresponding to the flight time point is determined using the even-odd rule.

[0122] Furthermore, when the current flight maneuver is a takeoff maneuver, the maneuver analysis module 302 is further configured to:

[0123] When the carrier rocket leaves the launch pad during the takeoff period, a signal acquisition parameter is acquired; wherein the signal acquisition parameter indicates whether the carrier rocket sends a takeoff signal and the time when the takeoff signal is received;

[0124] When the carrier rocket leaves the tower vertically, obtaining the attitude angle deviation of the carrier rocket;

[0125] When the thrust of the carrier rocket is established, obtaining a speed change of the carrier rocket;

[0126] Based on the signal acquisition parameters, the attitude angle deviation and the speed change, the action analysis result is determined according to the action evaluation rule.

[0127] Furthermore, the action assessment rule includes a first assessment rule, a second assessment rule, and a third assessment rule, wherein the first assessment rule is that the takeoff signal of the carrier rocket is received within a preset time, the second assessment rule is that the attitude angle deviation does not exceed a first deviation threshold, and the third assessment rule is that the speed of the carrier rocket increases;

[0128] When the motion analysis module 302 is used to determine the motion analysis result according to the motion assessment rule based on the signal acquisition parameter, the posture angle deviation, and the speed change, the motion analysis module 302 is further used to:

[0129] When the signal acquisition parameter meets the first evaluation rule, the attitude angle deviation meets the second evaluation rule, and the speed change meets the third evaluation rule, then determining that the action analysis result is that the current flight action is normal;

[0130] When the signal acquisition parameter meets the first evaluation rule and the attitude angle deviation does not meet the second evaluation rule, determining that the action analysis result is that the current flight action is abnormal;

[0131] When the signal acquisition parameter does not meet the first evaluation rule, the attitude angle deviation meets the second evaluation rule, and the speed change meets the third evaluation rule, then determining that the action analysis result is that the current flight action is normal;

[0132] When the signal acquisition parameter does not meet the first evaluation rule, the attitude angle deviation does not meet the second evaluation rule, and the speed change meets the third evaluation rule, the action analysis result is determined to be that the current flight action is abnormal.

[0133] Furthermore, when the mission analysis module 303 is used to generate a mission analysis result of the current flight mission of the launch vehicle based on the flight action analysis result of the launch vehicle, the rocket-satellite separation action analysis result, and the satellite orbit insertion action analysis result, using mission assessment rules, the mission analysis module 303 is further used to:

[0134] When the flight action analysis result of the carrier rocket is stable flight according to the predetermined orbit, the satellite-rocket separation action analysis result is that the satellite is sent into the predetermined orbit, and the satellite orbit entry action analysis result is that the satellite orbit entry parameter deviation does not exceed the second deviation threshold, then the mission analysis result is that the mission is successful.

[0135] When the flight action analysis result of the carrier rocket is stable flight according to the predetermined orbit, the satellite-rocket separation action analysis result is that the satellite is sent into the predetermined orbit, and the satellite orbit entry action analysis result is that the satellite orbit entry parameter deviation exceeds the second deviation threshold, then the mission analysis result is that the mission is basically successful.

[0136] When the satellite orbit insertion action analysis result of the carrier rocket is that the satellite has not entered orbit, the mission analysis result is mission failure.

[0137] See also Figure 4 , Figure 4 This is a schematic diagram of the structure of an electronic device provided in an embodiment of the present application. Figure 4 As shown in FIG, the electronic device 400 includes a processor 410 , a memory 420 and a bus 430 .

[0138] The memory 420 stores machine-readable instructions executable by the processor 410. When the electronic device 400 is running, the processor 410 communicates with the memory 420 via the bus 430. When the machine-readable instructions are executed by the processor 410, the above-mentioned Figure 1 The steps of the method for analyzing the flight status of a carrier rocket in the method embodiment shown are specifically implemented in accordance with the method embodiment and will not be described in detail here.

[0139] The embodiment of the present application also provides a computer-readable storage medium on which a computer program is stored. When the computer program is executed by a processor, the computer program can execute the above-mentioned Figure 1 The steps of the method for analyzing the flight status of a carrier rocket in the method embodiment shown are specifically implemented in accordance with the method embodiment and will not be described in detail here.

[0140] Those skilled in the art will clearly understand that, for the convenience and brevity of description, the specific working processes of the systems, devices and units described above can refer to the corresponding processes in the aforementioned method embodiments and will not be repeated here.

[0141] In the several embodiments provided in this application, it should be understood that the disclosed systems, devices and methods can be implemented in other ways. The device embodiments described above are merely schematic. For example, the division of the units is merely a logical function division. There may be other division methods in actual implementation. For example, multiple units or components may be combined or integrated into another system, or some features may be ignored or not executed. Another point is that the mutual coupling or direct coupling or communication connection shown or discussed may be through some communication interface, indirect coupling or communication connection of devices or units, which may be electrical, mechanical or other forms.

[0142] The units described as separate components may or may not be physically separate, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed across multiple network units. Some or all of these units may be selected to achieve the purpose of this embodiment according to actual needs.

[0143] In addition, each functional unit in each embodiment of the present application may be integrated into one processing unit, or each unit may exist physically separately, or two or more units may be integrated into one unit.

[0144] If the functions are implemented in the form of software functional units and sold or used as independent products, they can be stored in a non-volatile computer-readable storage medium that is executable by a processor. Based on this understanding, the technical solution of the present application, or the part that contributes to the prior art, or the part of the technical solution, can be embodied in the form of a software product. The computer software product is stored in a storage medium and includes several instructions for enabling a computer device (which can be a personal computer, a server, or a network device, etc.) to execute all or part of the steps of the method described in each embodiment of the present application. The aforementioned storage medium includes various media that can store program codes, such as a USB flash drive, a mobile hard disk, a read-only memory (ROM), a random access memory (RAM), a magnetic disk or an optical disk.

[0145] Finally, it should be noted that the above-described embodiments are only specific implementation methods of the present application, which are used to illustrate the technical solutions of the present application, rather than to limit them. The scope of protection of the present application is not limited thereto. Although the present application has been described in detail with reference to the above-mentioned embodiments, those skilled in the art should understand that any person skilled in the art can modify or easily conceive of changes to the technical solutions described in the above-mentioned embodiments within the technical scope disclosed in the present application, or perform equivalent replacements for some of the technical features thereof. These modifications, changes, or replacements do not deviate from the spirit and scope of the technical solutions of the embodiments of the present application, and should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. A method for analyzing the flight status of a launch vehicle, characterized in that: The analysis method comprises: During the flight of the carrier rocket, obtaining flight parameters of the carrier rocket, performing abnormality analysis on the flight parameters, and generating flight parameter analysis results; After the carrier rocket completes a current flight action, obtaining evaluation parameters required for evaluating the current flight action, and generating an action analysis result of the current flight action according to an action evaluation rule corresponding to the current flight action and the evaluation parameters; After the carrier rocket completes the satellite-rocket separation, the mission analysis result of the current flight mission of the carrier rocket is generated using the mission assessment rules based on the flight action analysis result of the carrier rocket, the satellite-rocket separation action analysis result and the satellite orbit insertion action analysis result.

2. The analysis method according to claim 1, characterized in that The performing abnormality analysis on the flight parameters and generating flight parameter analysis results includes: Selecting the flight parameters using a cellular automaton model to determine target parameter values ​​of the launch vehicle at each flight time point; A parameter range curve is obtained, and an abnormality analysis is performed on the target parameter value corresponding to each flight time point based on the parameter range curve to obtain the flight parameter analysis result.

3. The analysis method according to claim 2, characterized in that The method of selecting the flight parameters using a cellular automaton model to determine target parameter values ​​of the carrier rocket at each flight time point includes: Dividing a two-dimensional plane into a plurality of grids based on the cellular automaton model, and adding the flight parameters into the two-dimensional plane; wherein the abscissa of the two-dimensional plane represents the flight time of the carrier rocket, and the ordinate of the two-dimensional plane represents the flight parameters; For each grid corresponding to each flight time point, determine the number of flight parameters belonging to the grid, and determine a score corresponding to the grid based on the number; The flight parameter in the grid with the highest score among the multiple grids is determined as the target parameter value corresponding to the flight time point.

4. The analysis method according to claim 2, characterized in that The performing an abnormality analysis on the target parameter value corresponding to each flight time point based on the parameter range curve to obtain the flight parameter analysis result includes: If the parameter range curve is of the first curve type, for each flight time point, determining the parameter range corresponding to the flight time point in the parameter range curve, and determining a flight parameter analysis result of the target parameter value corresponding to the flight time point based on the parameter range and the target parameter value corresponding to the flight time point; If the parameter range curve is of the second curve type, for each flight time point, the flight parameter analysis result of the target parameter value corresponding to the flight time point is determined using the even-odd rule.

5. The analysis method according to claim 1, characterized in that When the current flight maneuver is a takeoff maneuver, obtaining evaluation parameters required for evaluating the current flight maneuver, and generating an action analysis result of the current flight maneuver based on an action evaluation rule corresponding to the current flight maneuver and the evaluation parameters, includes: When the carrier rocket leaves the launch pad during the takeoff period, a signal acquisition parameter is acquired; wherein the signal acquisition parameter indicates whether the carrier rocket sends a takeoff signal and the time when the takeoff signal is received; When the carrier rocket leaves the tower vertically, obtaining the attitude angle deviation of the carrier rocket; When the thrust of the carrier rocket is established, obtaining a speed change of the carrier rocket; Based on the signal acquisition parameters, the attitude angle deviation and the speed change, the action analysis result is determined according to the action evaluation rule.

6. The analysis method according to claim 5, characterized in that The action assessment rule includes a first assessment rule, a second assessment rule, and a third assessment rule, wherein the first assessment rule is that the takeoff signal of the carrier rocket is received within a preset time, the second assessment rule is that the attitude angle deviation does not exceed a first deviation threshold, and the third assessment rule is that the speed of the carrier rocket increases; The step of determining the motion analysis result based on the signal acquisition parameter, the attitude angle deviation, and the speed change according to the motion assessment rule includes: When the signal acquisition parameter meets the first evaluation rule, the attitude angle deviation meets the second evaluation rule, and the speed change meets the third evaluation rule, then determining that the action analysis result is that the current flight action is normal; When the signal acquisition parameter meets the first evaluation rule and the attitude angle deviation does not meet the second evaluation rule, determining that the action analysis result is that the current flight action is abnormal; When the signal acquisition parameter does not meet the first evaluation rule, the attitude angle deviation meets the second evaluation rule, and the speed change meets the third evaluation rule, then determining that the action analysis result is that the current flight action is normal; When the signal acquisition parameter does not meet the first evaluation rule, the attitude angle deviation does not meet the second evaluation rule, and the speed change meets the third evaluation rule, the action analysis result is determined to be that the current flight action is abnormal.

7. The analysis method according to claim 1, characterized in that The step of generating a mission analysis result of the current flight mission of the carrier rocket using a mission assessment rule based on the flight action analysis result of the carrier rocket, the rocket-satellite separation action analysis result, and the satellite orbit insertion action analysis result includes: When the flight action analysis result of the carrier rocket is stable flight according to the predetermined orbit, the satellite-rocket separation action analysis result is that the satellite is sent into the predetermined orbit, and the satellite orbit insertion action analysis result is that the satellite orbit insertion parameter deviation does not exceed the second deviation threshold, then the mission analysis result is a mission success; When the flight action analysis result of the carrier rocket is stable flight according to the predetermined orbit, the satellite-rocket separation action analysis result is that the satellite is sent into the predetermined orbit, and the satellite orbit insertion action analysis result is that the satellite orbit insertion parameter deviation exceeds the second deviation threshold, then the mission analysis result is that the mission is basically successful; When the satellite orbit insertion action analysis result of the carrier rocket is that the satellite has not entered orbit, the mission analysis result is mission failure.

8. A device for analyzing the flight status of a carrier rocket, characterized in that: The analysis device comprises: A parameter analysis module is used to obtain the flight parameters of the carrier rocket during the flight of the carrier rocket, perform abnormality analysis on the flight parameters, and generate flight parameter analysis results; a motion analysis module, configured to obtain, after the launch vehicle completes a current flight action, evaluation parameters required for evaluating the current flight action, and generate a motion analysis result of the current flight action based on an action evaluation rule corresponding to the current flight action and the evaluation parameters; The mission analysis module is used to generate a mission analysis result of the current flight mission of the carrier rocket based on the flight action analysis result of the carrier rocket, the satellite-rocket separation action analysis result and the satellite orbit insertion action analysis result after the carrier rocket completes the satellite-rocket separation.

9. An electronic device, characterized in that: include: A processor, a memory and a bus, wherein the memory stores machine-readable instructions executable by the processor. When the electronic device is running, the processor and the memory communicate through the bus. When the processor is running, the machine-readable instructions execute the steps of the method for analyzing the flight status of a carrier rocket as described in any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that The computer-readable storage medium stores a computer program, which, when executed by a processor, executes the steps of the method for analyzing the flight status of a carrier rocket as described in any one of claims 1 to 7.

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