CN116738893B - Spacecraft simulation prediction system based on analysis of synchronous transmitter - Google Patents
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Abstract
The invention relates to the technical field of spacecraft simulation prediction, in particular to a spacecraft simulation prediction system based on analysis by a synchronous transmitter. It includes a data processing module and a model optimization module. According to the invention, through combining various predicted data by the set data processing module, a corresponding simulation image is planned, a monitoring person can determine various data change conditions in the spacecraft simulation process in real time by the simulation image, the simulation image simulation data are compared by combining the model optimization module with the actual spacecraft operation reference standard, the simulation error is analyzed, the simulation model is regulated in real time by combining the simulation error, the accurate simulation model is continuously perfected, the simulation data accuracy of the simulation model is improved, the simulation error is reduced, and simulation conditions are provided for simulation of later different structural spacecraft and different environmental states.
Description
Technical Field
The invention relates to the technical field of spacecraft simulation prediction, in particular to a spacecraft simulation prediction system based on analysis by a synchronous transmitter.
Background
The spacecraft design and flight test work in the aerospace field requires a large amount of data statistics, calculation, analysis and processing work to ensure that the spacecraft can carry out flight test and task execution according to design requirements, and more weather condition influence exists in the flight process of the spacecraft: namely, weather conditions in the atmosphere and space weather conditions are included, because weather such as strong wind, thunderstorm and the like can cause fatal influence on the carrying spacecraft, the launching time of the spacecraft is selected to be carried out under clear weather conditions as much as possible, and the launching task of the spacecraft is likely to fail due to severe space weather such as solar blackness activity, high-energy radiation, electromagnetic storm and the like outside the atmosphere, so that a great amount of weather monitoring and forecasting work is needed before the launching of the spacecraft, and the noise of the launching time also needs to avoid the weather conditions.
In order to predict the flight state of the spacecraft in advance by combining with environmental factors and avoid the launching operation work of the spacecraft in an inadaptive environment, a spacecraft simulation prediction system for analyzing based on a synchronous transmitter is needed.
Disclosure of Invention
The invention aims to provide a spacecraft simulation prediction system based on analysis of a synchronous transmitter, so as to solve the problems in the background technology.
In order to achieve the above purpose, a spacecraft simulation prediction system based on analysis of a synchronous transmitter is provided, which comprises a data management module, a simulation platform, a data processing module and a model optimization module;
the data management module collects various environmental data in the flying process of the spacecraft, analyzes the affected data change in the flying process by combining the quality, the shape and the flying speed of the spacecraft, and manages the data through the synchronous transmitter;
the output end of the data management module is connected with the input end of the simulation platform, the simulation platform is combined with various environmental data transmitted by the synchronous transmitter and the affected data change in the flight process, a spacecraft flight simulation model is planned, the spacecraft flight simulation data are monitored, the spacecraft noise, the flight state, the spacecraft surface temperature, the thermal stress distribution and the strength of the spacecraft are predicted, predicted data are generated, and the predicted data are processed by the synchronous transmitter for data signal processing;
the output end of the simulation platform is connected with the input end of the data processing module, and the data processing module combines each item of prediction data to plan a corresponding simulation image;
the output end of the data processing module is connected with the input end of the model optimizing module, the model optimizing module is combined with an actual spacecraft operation reference standard, analog image analog data are compared, analog errors are analyzed, and the analog model is adjusted in real time by combining the analog errors.
As a further improvement of the technical scheme, the simulation platform comprises a spacecraft acoustic simulation module, an aerodynamic simulation module, a heat transfer simulation module and a structural mechanics simulation module;
the spacecraft acoustic simulation module is used for planning a spacecraft acoustic model by combining various environmental data and spacecraft shape structures in the flying process of the spacecraft, and predicting spacecraft noise generated in different states of the spacecraft;
the aerodynamic simulation module is used for planning an aerodynamic model of the spacecraft by combining various environmental data and the shape and structure of the spacecraft in the flight process of the spacecraft to predict the flight state and aerodynamic characteristics of the spacecraft in the atmosphere;
the heat transfer simulation module is used for analyzing the heat distribution and transfer process of the spacecraft structure by combining various environmental data and the shape structure of the spacecraft in the flight process of the spacecraft, planning a heat transfer mathematical model of the spacecraft and predicting the surface temperature and thermal stress distribution of the spacecraft;
the structural mechanics simulation module is used for planning a structural mechanics model by combining various environmental data and a spacecraft shape structure in the flying process of the spacecraft to predict the influence of the spacecraft operation environment on the strength of the spacecraft.
As a further improvement of the technical scheme, the spacecraft acoustic model planning method of the spacecraft acoustic simulation module comprises the following steps:
s1, determining the external structure of a spacecraft;
s2, determining an external structure of the spacecraft, which is in direct contact with the environment, by combining different running states of the spacecraft, and marking the external structure as an acoustic source point;
s3, monitoring sound source point sound changes under different states, determining influence rules on the flight state and aerodynamic characteristics of the spacecraft under different environments, and establishing an acoustic model of the spacecraft.
As a further improvement of the technical scheme, the spacecraft heat transfer science model planning method in the spacecraft acoustic simulation module comprises the following steps:
step one, determining the flow direction of heat energy in the flight process of a spacecraft;
sequentially determining materials of all equipment of the spacecraft according to the heat energy flowing direction to obtain heat resistance of the spacecraft;
and thirdly, analyzing heat energy loss in the flowing process, and determining the surface temperature and thermal stress distribution of each device of the spacecraft.
As a further improvement of the technical scheme, the data management module comprises an environmental factor determining unit and an influence value determining unit, wherein the environmental factor determining unit is used for determining environmental factors influencing the flight state of the spacecraft, the output end of the environmental factor determining unit is connected with the input end of the influence value determining unit, and the influence value determining unit acquires influence values corresponding to the environmental factors influencing the flight state of the spacecraft.
As a further improvement of the technical scheme, the output end of the influence value determining unit is connected with an influence range planning unit, and the influence range planning unit is used for determining the influence range of each environmental factor.
As a further improvement of the technical scheme, the data processing module comprises a prediction data analysis unit and a simulation image planning unit, wherein the prediction data analysis unit combines all prediction data to determine all parameters in the simulation image, the output end of the prediction data analysis unit is connected with the input end of the simulation image planning unit, and the simulation image planning unit combines all parameters in the simulation image to formulate an adaptive simulation image.
As a further improvement of the technical scheme, the model optimization module comprises a reference standard acquisition unit and a trend analysis unit, wherein the reference standard acquisition unit is used for acquiring spacecraft operation reference standards, the output end of the reference standard acquisition unit is connected with the input end of the trend analysis unit, and the trend analysis unit is combined with analog image analog data to determine various analog image change trends and is compared with spacecraft operation reference standards to determine error trends.
Compared with the prior art, the invention has the beneficial effects that:
in the spacecraft simulation prediction system based on the analysis of the synchronous transmitter, the data processing module is combined with each item of prediction data to plan a corresponding simulation image, a monitoring person can determine each item of data change condition in the spacecraft simulation process in real time through the simulation image, the model optimization module is combined with an actual spacecraft operation reference standard to compare the simulation image simulation data, the simulation error is analyzed, the simulation model is regulated in real time by combining with the simulation error, the accurate simulation model is continuously perfected, the simulation data accuracy of the simulation model is improved, the simulation error is reduced, and simulation conditions are provided for simulation of later-stage different-structure spacecrafts and different environmental states.
Drawings
FIG. 1 is a schematic diagram of the overall structure of the present invention;
FIG. 2 is a schematic diagram of a data management module according to the present invention;
FIG. 3 is a schematic diagram of a data processing module according to the present invention;
FIG. 4 is a schematic diagram of a model optimization module according to the present invention.
The meaning of each reference sign in the figure is:
10. a data management module; 110. an environmental factor determination unit; 120. an influence value determining unit; 130. an influence range planning unit;
20. the spacecraft acoustic simulation module;
30. an aerodynamic simulation module;
40. a heat transfer simulation module;
50. a structural mechanics simulation module;
60. a data processing module; 610. a prediction data analysis unit; 620. a simulation image planning unit;
70. a model optimization module; 710. a reference standard acquisition unit; 720. and a trend analysis unit.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Referring to fig. 1-4, a spacecraft simulation prediction system based on analysis of synchronous transmitters is provided, which comprises a data management module 10, a simulation platform, a data processing module 60 and a model optimization module 70;
the data management module 10 collects various environmental data in the flying process of the spacecraft, analyzes the change of the affected data in the flying process by combining the quality, the shape and the flying speed of the spacecraft, and manages the data through the synchronous transmitter;
the output end of the data management module 10 is connected with the input end of the simulation platform, the simulation platform is combined with various environmental data transmitted by the synchronous transmitter and the affected data change in the flight process, a spacecraft flight simulation model is planned, the spacecraft flight simulation data are monitored, the spacecraft noise, the flight state, the spacecraft surface temperature and thermal stress distribution and the strength of the spacecraft are predicted, prediction data are generated, and the prediction data are subjected to data signal processing through the synchronous transmitter;
the output end of the simulation platform is connected with the input end of the data processing module 60, and the data processing module 60 combines each item of prediction data to plan a corresponding simulation image;
the output end of the data processing module 60 is connected with the input end of the model optimizing module 70, the model optimizing module 70 combines the actual spacecraft operation reference standard, compares the simulation image simulation data, analyzes the simulation error, and adjusts the simulation model in real time in combination with the simulation error.
When the system is specifically used, in the process of simulating the flight of a spacecraft, various environmental data in the process of the flight of the spacecraft are collected through the data management module 10, for example: the method comprises the steps of analyzing affected data changes in the flight process by combining the air resistance, the shape and the flight speed of a spacecraft in the air and the operation state in a vacuum environment, namely, after the spacecraft flies and leaves each level of fuel bins of operation equipment, determining fuel supply time points and gravity change of the spacecraft after the spacecraft leaves the operation equipment, managing each item of data through a synchronous transmitter, transmitting each item of data to a simulation platform, simulating the environment changes in the operation process of the spacecraft by the simulation platform, combining the quality, the shape and the flight speed of the spacecraft, simulating the operation track of the spacecraft in different states, predicting the noise, the flight state, the surface temperature and the thermal stress distribution of the spacecraft and the strength of the spacecraft, generating prediction data, carrying out data signal processing on the prediction data by the simulation platform, namely, carrying out filtering processing, modulating and demodulating on the prediction data signals by the simulation platform, then combining each item of prediction data by the data processing module 60, planning corresponding simulation images, determining each item of data change conditions in the simulation process of the spacecraft in real time by the simulation image, combining the actual spacecraft operation reference standard by the model optimization module 70, comparing the simulation image with the simulation image, and analyzing simulation error by the simulation error in real time.
According to the invention, through the combination of the set data processing module 60 and various predicted data, corresponding simulation images are planned, monitoring staff can determine various data change conditions in the spacecraft simulation process in real time through the simulation images, the simulation image simulation data are compared through the model optimization module 70 and combined with actual spacecraft operation reference standards, simulation errors are analyzed, and the simulation models are adjusted in real time by combining with the simulation errors, so that the accuracy of simulation data of the simulation models is improved, the simulation errors are reduced, and simulation conditions are provided for simulation of later different structural spacecraft and under different environmental conditions.
In addition, the simulation platform comprises a spacecraft acoustic simulation module 20, an aerodynamic simulation module 30, a thermal conductivity simulation module 40 and a structural mechanics simulation module 50;
the spacecraft acoustic simulation module 20 is used for planning a spacecraft acoustic model by combining various environmental data and spacecraft shape structures in the flying process of the spacecraft to predict spacecraft noise generated in different states of the spacecraft;
the aerodynamic simulation module 30 is used for planning an aerodynamic model of the spacecraft by combining various environmental data and the shape and structure of the spacecraft in the flight process of the spacecraft to predict the flight state and aerodynamic characteristics of the spacecraft in the atmosphere;
the heat transfer simulation module 40 is used for analyzing the heat distribution and transfer process of the spacecraft structure by combining various environmental data and the shape structure of the spacecraft in the flight process of the spacecraft, planning a heat transfer mathematical model of the spacecraft and predicting the surface temperature and thermal stress distribution of the spacecraft;
the structural mechanics simulation module 50 is used for planning a structural mechanics model by combining various environmental data and spacecraft shape structures in the flying process of the spacecraft to predict the influence of the spacecraft operation environment on the strength of the spacecraft.
When the method is specifically used, in the process of planning a simulation model, firstly, a spacecraft acoustic model is planned by combining various environmental data and spacecraft shape structures in the flight process of a spacecraft through a spacecraft acoustic simulation module 20, for example, under the same environment, the noise generated by different sizes of the head of the spacecraft can be different, the noise generated by different shapes of the spacecraft is analyzed, the rules of the shape and the noise generation of the spacecraft are obtained, and the spacecraft noise generated by different states of the spacecraft is predicted;
various environmental data and spacecraft shape structures in the flying process of the spacecraft are combined through the aerodynamic simulation module 30, for example, the flying states of the spacecraft are changed due to different air resistances under different environments, the influence rules of the flying states and the aerodynamic characteristics of the spacecraft under different environments are analyzed, and a spacecraft aerodynamic model is planned for predicting the flying states and the aerodynamic characteristics of the spacecraft in the atmosphere in the later period;
the heat transfer simulation module 40 is used for analyzing heat distribution and transmission processes of the spacecraft structure by combining various environmental data and the spacecraft shape structure in the flying process of the spacecraft, monitoring the heat energy transmission structure of the spacecraft and the heat resistance of the spacecraft material, determining the heat energy change rule of each area of the spacecraft in different environmental states, planning a heat transfer mathematical model of the spacecraft, and predicting the surface temperature and the thermal stress distribution of the spacecraft;
the structural mechanics simulation module 50 is used for planning a structural mechanics model by combining various environmental data and spacecraft shape structures in the flying process of the spacecraft to predict the influence of the spacecraft operation environment on the strength of the spacecraft.
Further, the spacecraft acoustic simulation module 20 spacecraft acoustic model planning method includes the following steps:
s1, determining the external structure of a spacecraft;
s2, determining an external structure of the spacecraft, which is in direct contact with the environment, by combining different running states of the spacecraft, and marking the external structure as an acoustic source point;
s3, monitoring sound source point sound changes under different states, determining influence rules on the flight state and aerodynamic characteristics of the spacecraft under different environments, and establishing an acoustic model of the spacecraft.
Because the partial area of the spacecraft is shielded in the flight process and noise is not generated in the flight process of the spacecraft, the external structure of the spacecraft is required to be determined, the external structure of the spacecraft, which is in direct contact with the environment, is determined by combining different running states of the spacecraft, the external structure is marked as a sound source point, the sound changes of the sound source point in different states are monitored, the data analysis is carried out through the sound spectrum, the influence rule on the flight state and the aerodynamic characteristics of the spacecraft in different environments is determined, and the acoustic model of the spacecraft is established.
Still further, the spacecraft thermal mathematical model planning method in the spacecraft acoustic simulation module 20 comprises the steps of:
step one, determining the flow direction of heat energy in the flight process of a spacecraft;
sequentially determining materials of all equipment of the spacecraft according to the heat energy flowing direction to obtain heat resistance of the spacecraft;
and thirdly, analyzing heat energy loss in the flowing process, and determining the surface temperature and thermal stress distribution of each device of the spacecraft.
The method comprises the steps of firstly determining the flow direction of heat energy in the flight process of the spacecraft, sequentially determining the materials of each device of the spacecraft according to the flow direction of the heat energy to obtain the heat resistance of the spacecraft, analyzing the heat energy loss in the flow process, determining the surface temperature and the thermal stress distribution of each device of the spacecraft, and establishing a thermal conductivity model of the spacecraft.
Specifically, the data management module 10 includes an environmental factor determining unit 110 and an impact value determining unit 120, where the environmental factor determining unit 110 is configured to determine an environmental factor affecting the flight state of the spacecraft, an output end of the environmental factor determining unit 110 is connected to an input end of the impact value determining unit 120, the impact value determining unit 120 collects an impact value corresponding to the environmental factor affecting the flight state of the spacecraft, and in the process of collecting the running data of the spacecraft, the environmental factor affecting the flight state of the spacecraft is determined by the environmental factor determining unit 110 first, and then the impact number corresponding to the environmental factor affecting the flight state of the spacecraft is collected by the impact value determining unit 120 for performing simulation in a later period.
Because the influence intensities of the environmental factors on the flying of the spacecraft are different, when the change value of the environmental factors with too low influence intensity is too low, the influence value of the spacecraft is very little, so that the change of the influence value is difficult to obtain, in addition, the output end of the influence value determining unit 120 is connected with the influence range planning unit 130, the influence range planning unit 130 is used for determining the influence range of the environmental factors, and the influence unit value is planned for the environmental factors according to the influence intensity of the environmental factors on the flying of the spacecraft, namely, the influence unit value is planned in the simulation process, so that the obvious change rule is obtained.
Further, the data processing module 60 includes a prediction data analysis unit 610 and a simulation image planning unit 620, the prediction data analysis unit 610 combines each item of prediction data to determine each item of parameter in the simulation image, the output end of the prediction data analysis unit 610 is connected with the input end of the simulation image planning unit 620, the simulation image planning unit 620 combines each item of parameter in the simulation image to formulate an adapted simulation image, during the prediction data processing process, each item of parameter in the simulation image, namely, an influence environment variation value and a corresponding influence value in the spacecraft operation process, for example, an influence value between an air pressure variation value and a resistance influence value received in the spacecraft flight process, is determined by the prediction data analysis unit 610, then the simulation image planning unit 620 combines each item of parameter in the simulation image to formulate an adapted simulation image, and influences of each item of environment factors on the spacecraft flight process are simulated in real time.
Still further, the model optimization module 70 includes a reference standard acquisition unit 710 and a trend analysis unit 720, the reference standard acquisition unit 710 is used for acquiring a spacecraft operation reference standard, an output end of the reference standard acquisition unit 710 is connected with an input end of the trend analysis unit 720, the trend analysis unit 720 combines analog image analog data to determine various analog image change trends, the analog image change trends are compared with the spacecraft operation reference standard to determine an error trend, the reference standard acquisition unit 710 is used for acquiring the spacecraft operation reference standard, namely, various environmental factors affect the spacecraft flight state change trend in a normal state, and then the trend analysis unit 720 combines analog image analog data to determine various analog image change trends, the comparison is performed with the spacecraft operation reference standard to determine an error trend, and the simulation model is modified perfectly through the error trend.
The foregoing has shown and described the basic principles, principal features and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the above-described embodiments, and that the above-described embodiments and descriptions are only preferred embodiments of the present invention, and are not intended to limit the invention, and that various changes and modifications may be made therein without departing from the spirit and scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (5)
1. Spacecraft simulation prediction system based on synchronous transmitter analysis, its characterized in that: comprises a data management module (10), a simulation platform, a data processing module (60) and a model optimization module (70);
the data management module (10) collects various environmental data in the flying process of the spacecraft, analyzes the change of the affected data in the flying process by combining the quality, the shape and the flying speed of the spacecraft, and manages the data through the synchronous transmitter;
the output end of the data management module (10) is connected with the input end of the simulation platform, the simulation platform is combined with various environmental data transmitted by the synchronous transmitter and the change of the affected data in the flight process, a spacecraft flight simulation model is planned, the spacecraft flight simulation data are monitored, the spacecraft noise, the flight state, the spacecraft surface temperature and thermal stress distribution and the strength of the spacecraft are predicted, prediction data are generated, and the prediction data are processed by data signals of the synchronous transmitter;
the output end of the simulation platform is connected with the input end of the data processing module (60), and the data processing module (60) combines each item of prediction data to plan a corresponding simulation image;
the output end of the data processing module (60) is connected with the input end of the model optimizing module (70), the model optimizing module (70) combines the actual spacecraft operation reference standard, compares the simulation image simulation data, analyzes the simulation error, and combines the simulation error to adjust the simulation model in real time;
the simulation platform comprises a spacecraft acoustic simulation module (20), an aerodynamic simulation module (30), a heat transfer simulation module (40) and a structural mechanics simulation module (50);
the spacecraft acoustic simulation module (20) is used for planning a spacecraft acoustic model by combining various environmental data and spacecraft shape structures in the flying process of the spacecraft, and predicting spacecraft noise generated in different states of the spacecraft;
the aerodynamic simulation module (30) is used for planning an aerodynamic model of the spacecraft by combining various environmental data and the shape and structure of the spacecraft in the flight process of the spacecraft to predict the flight state and aerodynamic characteristics of the spacecraft in the atmosphere;
the heat transfer simulation module (40) is used for analyzing the heat distribution and transmission process of the spacecraft structure by combining various environmental data and the shape structure of the spacecraft in the flight process of the spacecraft, planning a heat transfer mathematical model of the spacecraft and predicting the surface temperature and thermal stress distribution of the spacecraft;
the structural mechanics simulation module (50) is used for planning a structural mechanics model by combining various environmental data and a spacecraft shape structure in the flying process of the spacecraft to predict the influence of the spacecraft operation environment on the strength of the spacecraft;
the data management module (10) comprises an environmental factor determining unit (110) and an influence value determining unit (120), wherein the environmental factor determining unit (110) is used for determining environmental factors influencing the flight state of the spacecraft, the output end of the environmental factor determining unit (110) is connected with the input end of the influence value determining unit (120), and the influence value determining unit (120) acquires an influence value corresponding to the environmental factors influencing the flight state of the spacecraft;
an influence range planning unit (130) is connected to the output end of the influence value determining unit (120), and the influence range planning unit (130) is used for determining the influence range of each environmental factor.
2. The synchronous transmitter based analysis spacecraft simulation prediction system of claim 1, wherein: the spacecraft acoustic simulation module (20) spacecraft acoustic model planning method comprises the following steps:
s1, determining the external structure of a spacecraft;
s2, determining an external structure of the spacecraft, which is in direct contact with the environment, by combining different running states of the spacecraft, and marking the external structure as an acoustic source point;
s3, monitoring sound source point sound changes under different states, determining influence rules on the flight state and aerodynamic characteristics of the spacecraft under different environments, and establishing an acoustic model of the spacecraft.
3. The synchronous transmitter based analysis spacecraft simulation prediction system of claim 1, wherein: the spacecraft thermal conductivity model planning method in the spacecraft acoustic simulation module (20) comprises the following steps:
step one, determining the flow direction of heat energy in the flight process of a spacecraft;
sequentially determining materials of all equipment of the spacecraft according to the heat energy flowing direction to obtain heat resistance of the spacecraft;
and thirdly, analyzing heat energy loss in the flowing process, and determining the surface temperature and thermal stress distribution of each device of the spacecraft.
4. The synchronous transmitter based analysis spacecraft simulation prediction system of claim 1, wherein: the data processing module (60) comprises a prediction data analysis unit (610) and a simulation image planning unit (620), wherein the prediction data analysis unit (610) combines all prediction data to determine all parameters in a simulation image, the output end of the prediction data analysis unit (610) is connected with the input end of the simulation image planning unit (620), and the simulation image planning unit (620) combines all parameters in the simulation image to formulate an adaptive simulation image.
5. The synchronous transmitter based analysis spacecraft simulation prediction system of claim 1, wherein: the model optimization module (70) comprises a reference standard acquisition unit (710) and a trend analysis unit (720), wherein the reference standard acquisition unit (710) is used for acquiring a spacecraft operation reference standard, the output end of the reference standard acquisition unit (710) is connected with the input end of the trend analysis unit (720), and the trend analysis unit (720) combines simulation image simulation data to determine various simulation image change trends and compares the simulation image change trends with the spacecraft operation reference standard to determine error trends.
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