CN109614701B - Satellite solar cell array multidisciplinary simulation system and method - Google Patents
Satellite solar cell array multidisciplinary simulation system and method Download PDFInfo
- Publication number
- CN109614701B CN109614701B CN201811508952.9A CN201811508952A CN109614701B CN 109614701 B CN109614701 B CN 109614701B CN 201811508952 A CN201811508952 A CN 201811508952A CN 109614701 B CN109614701 B CN 109614701B
- Authority
- CN
- China
- Prior art keywords
- analysis
- parameters
- solar cell
- cell array
- model
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/06—Power analysis or power optimisation
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- Geometry (AREA)
- General Engineering & Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Photovoltaic Devices (AREA)
- Management, Administration, Business Operations System, And Electronic Commerce (AREA)
Abstract
The invention provides a satellite solar cell array multidisciplinary simulation system, which comprises: the system comprises a modal analysis module, a rigid-flexible coupling mechanism kinematics analysis module, an intensity analysis module, an electromechanical coupling analysis module, a man-machine interaction interface module, a basic database module and a calculation scheduling module. The simulation method comprises the steps of calling analysis software to perform modal analysis, rigid-flexible coupling mechanism kinematics analysis, strength analysis and electromechanical coupling analysis on a satellite solar cell array; and acquiring satellite solar cell array parameters input by a user through a man-machine interaction interface, displaying a calculation result, storing a material library, a parameter library and a model library required by simulation analysis through a basic database, and carrying out calculation scheduling on calculation resources. The system and the method are used for model early scheme feasibility demonstration, performance optimization and reliability design, and provide powerful guarantee for improving the development quality, accelerating the development period and improving the reliability of the satellite solar cell array.
Description
Technical Field
The invention relates to the field of aerospace, in particular to a satellite solar cell array multidisciplinary simulation system and method.
Background
The design of the satellite solar cell array needs to carry out a large amount of simulation analysis work, has strong specialization and wide professional scope, and relates to professions such as institutions, structures, electrons, heat, control, computer software and the like, and the subjects of each profession are mutually coupled and restrained. Multiple rounds of design iteration from simple to complex are required to be carried out according to the coupling relation among disciplines, and a large number of scheme comparisons are carried out so as to finally complete the research and development process. In the past, the modeling and analysis of the solar cell array are carried out manually, the time length and the iteration are difficult, and the design period of the solar cell array is longer.
Disclosure of Invention
The invention provides a satellite solar cell array multidisciplinary simulation system and method, which are used for solving the problems of long service time and difficult iteration existing in the existing satellite solar cell design.
According to a first aspect of the present invention, there is provided a satellite solar array multidisciplinary simulation system, comprising:
the system comprises a modal analysis module, a parameter analysis module and a whole machine flexible body file, wherein the modal analysis module is used for creating a parameterized analysis model of the solar cell array according to solar cell array parameters, the parameterized analysis model comprises a furling model and an unfolding model, modal analysis is carried out to obtain a modal analysis result of each order of modal frequency comprising a furling state and an unfolding state, and the whole machine flexible body file is generated;
the rigid-flexible coupling mechanism kinematics analysis module is used for creating a rigid-flexible coupling mechanism dynamics model of the solar cell array on the calculation node according to the modal analysis result, carrying out rigid-flexible coupling mechanism dynamics analysis, obtaining the unfolding process and the unfolding time of the solar cell array, and generating a rigid-flexible coupling mechanism dynamics analysis result;
the intensity analysis module is used for setting analysis working conditions according to the dynamic analysis results of the rigid-flexible coupling mechanism, and carrying out intensity analysis of the unfolding impact state and the quasi-static overload state of the launching stage on the solar cell array model on the calculation nodes to obtain the stress of the solar cell array in the unfolding impact state and the quasi-static overload state of the launching stage;
an electromechanical coupling analysis module; the system is used for carrying out mechanism dynamics analysis of the driving mechanism on the calculation node according to the whole machine flexible body file to obtain a voltage, current and load moment change curve of the driving mechanism;
the man-machine interaction interface module is used for obtaining input solar cell array parameters and displaying analysis results of the modal analysis module, the rigid-flexible coupling mechanism kinematics analysis module, the strength analysis module and the electromechanical coupling analysis module;
the basic database module is used for storing a material library, a parameter library and a model library required by simulation analysis;
and the calculation scheduling module is used for managing the calculation nodes subjected to simulation analysis.
Optionally, the mode analysis module obtains the displacement and stress cloud image of the front ten-order mode vibration frequency and the vibration mode of the whole machine after performing mode analysis, and parameters and images in the mode analysis result are automatically output to a report.
Optionally, the kinematic analysis module of the rigid-flexible coupling mechanism reads the modal analysis result to obtain a flexible body file of the connecting frame and the substrate, and performs rigid-flexible coupling to obtain an initial furling state model; the whole solar cell array frame in the initial furling state model is a rigid body, the connecting frame and the base plate are flexible bodies, and the coordinate system is the same as that of the furling model.
Optionally, the strength analysis module extracts the maximum load of the whole unfolding process according to the dynamic analysis result of the rigid-flexible coupling mechanism, refines the solar cell array model, loads the load to the stress position of the solar cell array component and sets a boundary, then performs strength analysis, simulates to obtain the stress of the substrate and the hinge, and generates a report.
Optionally, after the electromechanical coupling analysis module reads the complete machine flexible body file, an electromechanical integrated model of the solar cell array and the driving mechanism is established, and mechanism dynamics analysis is performed on the system to obtain a driving mechanism voltage, current and load moment change curve and generate a report.
Optionally, the man-machine interaction interface module includes: a parameter interface and an analysis interface; the parameters of the parameter interface include: the system comprises a modal analysis module, a rigid-flexible coupling mechanism kinematics analysis module, an intensity analysis module, parameters of an electromechanical coupling analysis module and solar cell array parameters, wherein the solar cell array parameters comprise: overall parameters, connector parameters, substrate parameters, unfolding locking mechanism parameters and compaction release mechanism parameters; the analysis interface comprises: an analysis parameter input part, a save button and a result preview part.
Optionally, the material library is stored in the form of xml file, the parameter library is stored in a table in the Oracle database, and the model library is stored in the form of model file.
Optionally, the computing scheduling module includes:
the adding and deleting computing node unit is used for adding and deleting the IP of the computing node;
a computing node path unit, configured to set a software path of a computing node;
the idle node allocation unit is used for automatically allocating idle nodes during simulation analysis, if all the computing nodes are occupied, the computing task enters a waiting state, and the computing resource is released in time when the task is completed, so that the computing task in waiting starts to compute.
According to a second aspect of the present invention, there is provided a satellite solar cell array multidisciplinary simulation method comprising the steps of:
s1: determining and inputting solar array parameters, wherein the solar array parameters comprise: overall parameters, connector parameters, substrate parameters, unfolding locking mechanism parameters and compaction release mechanism parameters;
s2: creating a parameterized analysis model of the solar cell array according to the solar cell array parameters, wherein the parameterized analysis model comprises a furling model and an unfolding model, performing modal analysis to obtain a modal analysis result of each-order modal frequency comprising a furling state and an unfolding state, and generating a complete machine flexible body file;
s3: creating a rigid-flexible coupling mechanism dynamics model of the solar cell array on the computing node according to the modal analysis result, performing rigid-flexible coupling mechanism dynamics analysis to obtain the unfolding process and the unfolding time of the solar cell array, and generating a rigid-flexible coupling mechanism dynamics analysis result;
s4: setting analysis working conditions according to the dynamic analysis results of the rigid-flexible coupling mechanism, and carrying out intensity analysis on the unfolding impact state and the quasi-static overload state of the launching stage on the solar cell array model on the calculation nodes to obtain the stress of the solar cell array in the unfolding impact state and the quasi-static overload state of the launching stage;
s5: according to the complete machine flexible body file, mechanism dynamics analysis of a driving mechanism is carried out on the calculation node, and a voltage, current and load moment change curve of the driving mechanism is obtained;
s6: judging whether the results of the steps S2, S3, S4 and S5 meet the design requirements: if yes, ending the simulation; if not, returning to the step S1 to redetermine and input the solar cell array parameters.
Optionally, the overall parameters include: the configuration, the number of the substrates, the unfolding mode and whether the solar cell array comprises a connecting frame or not; the parameters of the connecting frame comprise: the left side height of the connecting frame, the length of the connecting frame, the configuration of the connecting frame, the material parameters of each beam of the connecting frame and the section parameters of the beams, and the quality of the connecting frame after adjustment; the substrate parameters include: the method comprises the steps of (1) substrate length, substrate height, pressing hole position, whether binding a connecting frame, material parameters and beam section parameters of a substrate frame, material parameters and thickness direction of each layer of a substrate battery plate, substrate adjusted quality and substrate pressing hole reinforcing region radius; the deployment locking mechanism parameters include: the rigidity coefficient, pretightening moment, equivalent rigidity in all directions and CCL assembly parameters of the hinge between the root hinge and the plate; the compression release mechanism parameters include: material parameters, equivalent radius and mass.
The satellite solar cell array multidisciplinary simulation system and the satellite solar cell array multidisciplinary simulation method provided by the invention realize the processes of parameterized finite element modeling, various analysis, calculation result generation and the like of the solar cell array, rapidly design and iterate optimization of the solar cell array, and shorten the design period of the solar cell array.
Drawings
In order to more clearly illustrate the embodiments of the invention or the technical solutions of the prior art, the drawings which are used in the description of the embodiments or the prior art will be briefly described, it being obvious that the drawings in the description below are only some embodiments of the invention, and that other drawings can be obtained according to these drawings without inventive faculty for a person skilled in the art.
FIG. 1 is a schematic diagram of an exemplary solar array composition used in an embodiment of the present invention;
FIG. 2 is a schematic diagram of a satellite solar array multidisciplinary simulation system provided in an embodiment of the present invention;
fig. 3 is a flowchart of a satellite solar cell array multidisciplinary simulation method provided in an embodiment of the present invention.
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.
The terms "first," "second," "third," "fourth" and the like in the description and in the claims and in the above drawings, if any, are used for distinguishing between similar objects and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used may be interchanged where appropriate such that the embodiments of the invention described herein may be implemented in sequences other than those illustrated or otherwise described herein. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
The technical scheme of the invention is described in detail below by specific examples. The following embodiments may be combined with each other, and some embodiments may not be repeated for the same or similar concepts or processes.
As shown in fig. 1, the satellite solar cell array multidisciplinary simulation system provided in this embodiment includes: the system comprises a modal analysis module 10, a rigid-flexible coupling mechanism kinematics analysis module 20, an intensity analysis module 30, an electromechanical coupling analysis module 40, a man-machine interaction interface module 50, a basic database module 60 and a calculation scheduling module 70. Wherein:
the modal analysis module 10 is configured to create a parameterized analysis model of the solar cell array according to the obtained solar cell array parameters, where the parameterized analysis model includes a furling model and an unfolding model, perform modal analysis to obtain a modal analysis result of each order of modal frequencies including a furling state and an unfolding state, and generate a complete machine flexible body file;
the rigid-flexible coupling mechanism kinematics analysis module 20 is configured to create a rigid-flexible coupling mechanism dynamics model of the solar cell array on the computing node according to the modal analysis result generated by the modal analysis module 10, perform the rigid-flexible coupling mechanism dynamics analysis, obtain the unfolding process and the unfolding time of the solar cell array, and generate a rigid-flexible coupling mechanism dynamics analysis result;
the intensity analysis module 30 is configured to set an analysis working condition according to the dynamic analysis result of the rigid-flexible coupling mechanism, perform intensity analysis of the unfolding impact state and the quasi-static overload state of the launching stage on the solar cell array model on the calculation node, and obtain stress of the solar cell array in the unfolding impact state and the quasi-static overload state of the launching stage;
an electromechanical coupling analysis module 40; the system is used for carrying out mechanism dynamics analysis of the driving mechanism on each calculation node according to the whole machine flexible body file generated by the modal analysis module 10 to obtain a voltage, current and load moment change curve of the driving mechanism;
the man-machine interaction interface module 50 is used for obtaining input solar cell array parameters and displaying analysis results of the modal analysis module 10, the rigid-flexible coupling mechanism kinematics analysis module 20, the strength analysis module 30 and the electromechanical coupling analysis module 40;
a base database module 60 for storing a material library, a parameter library, and a model library required for simulation analysis;
a computation scheduling module 70 for managing the computation nodes of the simulation analysis.
The modal analysis module 10 obtains the displacement and stress cloud image of the front ten-order modal vibration frequency and the vibration mode of the whole machine after modal analysis, and parameters and images in the modal analysis result are automatically output to a report.
Further, the kinematic analysis module 20 of the rigid-flexible coupling mechanism reads the modal analysis result to obtain a flexible body file of the connecting frame and the substrate, and performs rigid-flexible coupling to obtain an initial furled state model. In the initial furling state model, the whole solar cell array frame is a rigid body, the connecting frame and the base plate are flexible bodies, and the coordinate system is the same as that of the furling model created in the modal analysis. And then, carrying out dynamic analysis on the model in the unfolding process to obtain unfolding time, each key part, a transmission joint, a hinge, star mounting surface load information and CCL tension change curves, and generating a report.
Further, the strength analysis module 30 extracts the maximum load of the whole unfolding process according to the dynamic analysis result of the rigid-flexible coupling mechanism, refines the solar cell array model, loads the load to the stress position of the solar cell array component and sets the boundary, then performs strength analysis, simulates to obtain the stress of the substrate and the hinge, and generates a report.
After the electromechanical coupling analysis module 40 reads the complete machine flexible body file generated by the modal analysis module 10, an electromechanical integrated model of the solar cell array and the driving mechanism is established, and mechanism dynamics analysis is performed on the system to obtain a voltage, current and load moment change curve of the driving mechanism and generate a report, wherein the report specifically adopts a word form.
The man-machine interaction interface module 50 of the system comprises two types of interfaces, namely: a parameter interface and an analysis interface. Wherein, the parameters of the parameter interface include: the mode analysis module, the kinematic analysis module of the rigid-flexible coupling mechanism, the intensity analysis module, the parameters of the electromechanical coupling analysis module and the solar cell array parameters in the embodiment include: overall parameters, link parameters, substrate parameters, deployment locking mechanism parameters, and compression release mechanism parameters. And the analysis interface includes: an analysis parameter input part, a save button and a result preview part. The results file supports downloads where Word reports also support online previews.
In the base database module 60, the material library is stored in the form of xml files, the parameter library is stored in a table in the Oracle database, and the model library is stored in the form of model files.
The computing scheduling module 70 further includes: the adding and deleting computing node unit is used for adding and deleting the IP of the computing node; a computing node path unit, configured to set a software path of a computing node; the idle node allocation unit is used for automatically allocating idle nodes during simulation analysis, if all the computing nodes are occupied, the computing task enters a waiting state, and the computing resource is released in time when the task is completed, so that the computing task in waiting starts to compute.
Referring to fig. 2, a satellite solar cell array multidisciplinary simulation method is characterized by comprising the following steps:
s1: determining and inputting solar array parameters, wherein the solar array parameters comprise: overall parameters, connector parameters, substrate parameters, unfolding locking mechanism parameters and compaction release mechanism parameters;
s2: creating a parameterized analysis model of the solar cell array according to the solar cell array parameters, wherein the parameterized analysis model comprises a furling model and an unfolding model, performing modal analysis to obtain a modal analysis result of each-order modal frequency comprising a furling state and an unfolding state, and generating a complete machine flexible body file;
s3: creating a rigid-flexible coupling mechanism dynamics model of the solar cell array on the computing node according to the modal analysis result, performing rigid-flexible coupling mechanism dynamics analysis to obtain the unfolding process and the unfolding time of the solar cell array, and generating a rigid-flexible coupling mechanism dynamics analysis result;
s4: setting analysis working conditions according to the dynamic analysis results of the rigid-flexible coupling mechanism, and carrying out intensity analysis on the unfolding impact state and the quasi-static overload state of the launching stage on the solar cell array model on the calculation nodes to obtain the stress of the solar cell array in the unfolding impact state and the quasi-static overload state of the launching stage;
s5: according to the complete machine flexible body file, mechanism dynamics analysis of a driving mechanism is carried out on the calculation node, and a voltage, current and load moment change curve of the driving mechanism is obtained;
s6: judging whether the results of the steps S2, S3, S4 and S5 meet the design requirements: if yes, ending the simulation; if not, returning to the step S1 to redetermine and input the solar cell array parameters.
Wherein, the overall parameters include: the configuration, the number of the substrates, the unfolding mode and whether the solar cell array comprises a connecting frame or not; the parameters of the connecting frame comprise: the left side height of the connecting frame, the length of the connecting frame, the configuration of the connecting frame, the material parameters of each beam of the connecting frame and the section parameters of the beams, and the quality of the connecting frame after adjustment; the substrate parameters include: the method comprises the steps of (1) substrate length, substrate height, pressing hole position, whether binding a connecting frame, material parameters and beam section parameters of a substrate frame, material parameters and thickness direction of each layer of a substrate battery plate, substrate adjusted quality and substrate pressing hole reinforcing region radius; the deployment locking mechanism parameters include: the rigidity coefficient, pretightening moment, equivalent rigidity in all directions and CCL assembly parameters of the hinge between the root hinge and the plate; the compression release mechanism parameters include: material parameters, equivalent radius and mass.
Application example:
referring to fig. 3, a typical solar cell array applied to the present application example performs a multi-disciplinary simulation of a satellite solar cell array by using the satellite solar cell array multi-disciplinary simulation system shown in fig. 1 according to the flow of the satellite solar cell array multi-disciplinary simulation method shown in fig. 2.
As shown in fig. 3, the typical solar cell array includes three substrates, an inner plate 11, a middle plate 12, and an outer plate 13, which are sequentially connected by an unfolding locking mechanism 21. The other side of the inner plate 11 is connected to the satellite body through a connecting frame 31, wherein a connecting frame CCL assembly 41 is disposed at the edge of the connecting frame 31, inter-plate CCL assemblies are disposed at the edges of the three base plates, and a compression release mechanism 51 is disposed on the outer plate 13. The spreading fundamental frequency of the three substrates of the solar cell array is 0.25Hz, the illuminated area of the solar cell array needs to be increased in the current design, the number of the substrates is increased to 4 under the condition that the size of the substrates is not modified, the mass of the connecting frame is adjusted to 7.8kg due to the increase of the mass of accessories such as embedded parts, wires and the like, the spreading fundamental frequency is not less than 0.15Hz, and the mechanism, the strength and the driving coupling analysis are carried out.
And S1, determining parameters of the solar cell array. The method comprises the following steps: entering a system interface, creating and opening a scheme, wherein a system background reads data from a basic database at the moment, and setting default parameters for the scheme; modifying the overall parameters, changing the number of the substrates from 3 to 4, keeping other overall parameters unchanged by default, clicking the saved parameters, and saving the overall parameters to a basic database; modifying parameters of a connecting frame, checking quality adjustment, changing estimated quality into 7.8Kg, keeping other parameters of the connecting frame unchanged by default, clicking storage parameters, and storing the parameters of the connecting frame into a basic database; the parameters of the base plate, the unfolding locking mechanism and the compressing release mechanism are kept unchanged by default values;
and S2, modal analysis. The method comprises the following steps: clicking a calculation button of a modal analysis module to start modal analysis, calling a calculation scheduling module by a system background to find an idle calculation node, reading solar cell array parameters required by modal analysis from a basic database on the calculation node, carrying out finite element modeling, calling Nastran to carry out modal analysis to obtain a front tenth-order modal vibration frequency and displacement and stress cloud image of a vibration mode of the whole machine, automatically outputting the result parameters and images into a Word report, and after calculation is finished, previewing the result Word report on an interface on line, wherein the 1 st-order frequency is found to be 0.152Hz and is larger than 0.15Hz, and the conditions are met;
and S3, dynamic analysis of the rigid-flexible coupling mechanism. Clicking a calculation button of a dynamics analysis module of the rigid-flexible coupling mechanism to start dynamics analysis of the rigid-flexible coupling mechanism, calling a calculation scheduling module by a system background to find an idle calculation node, reading solar cell array parameters required by dynamics analysis of the rigid-flexible coupling mechanism and flexible body files of a connecting frame and a substrate obtained by modal analysis from a basic database on the calculation node, importing the solar cell array parameters and flexible body files into Adams to perform rigid-flexible coupling to obtain an initial furled state Adams model, wherein the whole solar cell array frame in the model is a rigid body, the connecting frame and the substrate are flexible bodies, a coordinate system is the same as a coordinate system of the furled model created in the modal analysis, then carrying out dynamics analysis on the Adams model in a developing process to obtain a developing time, each key part, a transmission joint, a hinge, load information of a star mounting surface and a CCL tension change curve, generating a Word report, and after calculation, previewing the result Word report on line from an interface, and completely developing at 13 s; the opening mechanism analyzes the animation, and can see the scheme that the unfolding mode is confirmed to be the base 90-degree unfolding and 180-degree unfolding are performed between plates;
and S4, analyzing the intensity. Clicking a calculation button of an intensity analysis module to start intensity analysis, calling a calculation scheduling module by a system background to find an idle calculation node, reading a solar cell array parameter required by the intensity analysis from a basic database on the calculation node, carrying out a refinement model, loading the load to a stress position of a part and setting a boundary, carrying out the intensity analysis by Nastran to obtain stress of a substrate and a hinge and generating a Word report, and after the calculation is finished, previewing the result Word report on the interface, wherein the expansion stress is about 27.0MPa, and the emission stress is about 9.5MPa and 4.3MPa;
and S5, electromechanical coupling analysis. Clicking a calculation button of an electromechanical coupling analysis module to start driving coupling analysis, calling a calculation scheduling module by a system background to find an idle calculation node, reading solar cell array parameters and modal analysis result files required by driving coupling analysis from a basic database on the calculation node, establishing a detailed electromechanical integrated model of a solar cell array and a driving mechanism by using Simulink and Adams, carrying out mechanism dynamics analysis on the whole system to obtain a voltage, current and load moment change curve of the driving mechanism, generating a Word report, and after calculation is finished, previewing the result Word report on line from an interface to check a calculation result;
step S6, judging whether the results of the steps S2, S3, S4 and S5 meet the design requirements: if yes, ending the simulation; if not, returning to the step S1 to redetermine and input the solar cell array parameters.
The simulation system and the simulation method provided by the invention are used for carrying out modal analysis, kinematic analysis of a rigid-flexible coupling mechanism, strength analysis and electromechanical coupling analysis of the satellite solar cell array by calling analysis software; and acquiring satellite solar cell array parameters input by a user through a man-machine interaction interface, displaying a calculation result, storing a material library, a parameter library and a model library required by simulation analysis through a basic database, and carrying out calculation scheduling on calculation resources. The system and the method are suitable for model early scheme feasibility demonstration, performance optimization and reliability design, and provide powerful guarantee for improving the development quality, accelerating the development period and improving the reliability of the satellite solar cell array.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and not for limiting the same; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit of the invention.
Claims (5)
1. A satellite solar array multidisciplinary simulation system, comprising:
the system comprises a modal analysis module, a parameter analysis module and a whole machine flexible body file, wherein the modal analysis module is used for creating a parameterized analysis model of the solar cell array according to solar cell array parameters, the parameterized analysis model comprises a furling model and an unfolding model, modal analysis is carried out to obtain a modal analysis result of each order of modal frequency comprising a furling state and an unfolding state, and the whole machine flexible body file is generated;
the rigid-flexible coupling mechanism kinematics analysis module is used for creating a rigid-flexible coupling mechanism dynamics model of the solar cell array on the calculation node according to the modal analysis result, carrying out rigid-flexible coupling mechanism dynamics analysis, obtaining the unfolding process and the unfolding time of the solar cell array, and generating a rigid-flexible coupling mechanism dynamics analysis result;
the intensity analysis module is used for setting analysis working conditions according to the dynamic analysis results of the rigid-flexible coupling mechanism, and carrying out intensity analysis of the unfolding impact state and the quasi-static overload state of the launching stage on the solar cell array model on the calculation nodes to obtain the stress of the solar cell array in the unfolding impact state and the quasi-static overload state of the launching stage;
an electromechanical coupling analysis module; the system is used for carrying out mechanism dynamics analysis of the driving mechanism on the calculation node according to the whole machine flexible body file to obtain a voltage, current and load moment change curve of the driving mechanism;
the man-machine interaction interface module is used for obtaining input solar cell array parameters and displaying analysis results of the modal analysis module, the rigid-flexible coupling mechanism kinematics analysis module, the strength analysis module and the electromechanical coupling analysis module;
the basic database module is used for storing a material library, a parameter library and a model library required by simulation analysis;
the calculation scheduling module is used for managing the calculation nodes subjected to simulation analysis;
the modal analysis module obtains the front ten-order modal vibration frequency and the displacement of the vibration mode and the stress cloud picture after modal analysis, and parameters and pictures in a modal analysis result are automatically output to a report;
the kinematic analysis module of the rigid-flexible coupling mechanism reads the modal analysis result to obtain a flexible body file of the connecting frame and the substrate, and rigid-flexible coupling is carried out to obtain an initial furling state model; the whole solar cell array frame in the initial furling state model is a rigid body, the connecting frame and the base plate are flexible bodies, and the coordinate system is the same as that of the furling model;
the strength analysis module extracts the maximum load of the whole unfolding process according to the dynamic analysis result of the rigid-flexible coupling mechanism, refines the solar cell array model, loads the load to the stress position of the solar cell array part and sets a boundary, then performs strength analysis, simulates to obtain the stress of the substrate and the hinge, and generates a report;
after the electromechanical coupling analysis module reads the complete machine flexible body file, an electromechanical integrated model of the solar cell array and the driving mechanism is established, and mechanism dynamics analysis is carried out on the system to obtain a driving mechanism voltage, current and load moment change curve and generate a report;
the man-machine interaction interface module comprises: a parameter interface and an analysis interface; the parameters of the parameter interface include: the system comprises a modal analysis module, a rigid-flexible coupling mechanism kinematics analysis module, an intensity analysis module, parameters of an electromechanical coupling analysis module and solar cell array parameters, wherein the solar cell array parameters comprise: overall parameters, connector parameters, substrate parameters, unfolding locking mechanism parameters and compaction release mechanism parameters; the analysis interface comprises: an analysis parameter input part, a save button and a result preview part.
2. The satellite solar array multidisciplinary simulation system of claim 1, wherein the library of materials is stored in an xml file, the library of parameters is stored in a table in an Oracle database, and the library of models is stored in a model file.
3. The satellite solar array multidisciplinary simulation system of claim 1, wherein the computational scheduling module comprises:
the adding and deleting computing node unit is used for adding and deleting the IP of the computing node;
a computing node path unit, configured to set a software path of a computing node;
the idle node allocation unit is used for automatically allocating idle nodes during simulation analysis, if all the computing nodes are occupied, the computing task enters a waiting state, and the computing resource is released in time when the task is completed, so that the computing task in waiting starts to compute.
4. A satellite solar array multidisciplinary simulation method, characterized in that the satellite solar array multidisciplinary simulation system of any one of claims 1 to 3 is applied, the simulation method comprising the steps of:
s1: determining and inputting solar array parameters, wherein the solar array parameters comprise: overall parameters, connector parameters, substrate parameters, unfolding locking mechanism parameters and compaction release mechanism parameters;
s2: creating a parameterized analysis model of the solar cell array according to the solar cell array parameters, wherein the parameterized analysis model comprises a furling model and an unfolding model, performing modal analysis to obtain a modal analysis result of each-order modal frequency comprising a furling state and an unfolding state, and generating a complete machine flexible body file;
s3: creating a rigid-flexible coupling mechanism dynamics model of the solar cell array on the computing node according to the modal analysis result, performing rigid-flexible coupling mechanism dynamics analysis to obtain the unfolding process and the unfolding time of the solar cell array, and generating a rigid-flexible coupling mechanism dynamics analysis result;
s4: setting analysis working conditions according to the dynamic analysis results of the rigid-flexible coupling mechanism, and carrying out intensity analysis on the unfolding impact state and the quasi-static overload state of the launching stage on the solar cell array model on the calculation nodes to obtain the stress of the solar cell array in the unfolding impact state and the quasi-static overload state of the launching stage;
s5: according to the complete machine flexible body file, mechanism dynamics analysis of a driving mechanism is carried out on the calculation node, and a voltage, current and load moment change curve of the driving mechanism is obtained;
s6: judging whether the results of the steps S2, S3, S4 and S5 meet the design requirements: if yes, ending the simulation; if not, returning to the step S1 to redetermine and input the solar cell array parameters.
5. The satellite solar array multidisciplinary simulation method of claim 4, wherein the overall parameters comprise: the configuration, the number of the substrates, the unfolding mode and whether the solar cell array comprises a connecting frame or not; the parameters of the connecting frame comprise: the left side height of the connecting frame, the length of the connecting frame, the configuration of the connecting frame, the material parameters of each beam of the connecting frame and the section parameters of the beams, and the quality of the connecting frame after adjustment; the substrate parameters include: the method comprises the steps of (1) substrate length, substrate height, pressing hole position, whether binding a connecting frame, material parameters and beam section parameters of a substrate frame, material parameters and thickness direction of each layer of a substrate battery plate, substrate adjusted quality and substrate pressing hole reinforcing region radius; the deployment locking mechanism parameters include: the rigidity coefficient, pretightening moment, equivalent rigidity in all directions and CCL assembly parameters of the hinge between the root hinge and the plate; the compression release mechanism parameters include: material parameters, equivalent radius and mass.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811508952.9A CN109614701B (en) | 2018-12-11 | 2018-12-11 | Satellite solar cell array multidisciplinary simulation system and method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811508952.9A CN109614701B (en) | 2018-12-11 | 2018-12-11 | Satellite solar cell array multidisciplinary simulation system and method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109614701A CN109614701A (en) | 2019-04-12 |
| CN109614701B true CN109614701B (en) | 2023-08-11 |
Family
ID=66007922
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811508952.9A Active CN109614701B (en) | 2018-12-11 | 2018-12-11 | Satellite solar cell array multidisciplinary simulation system and method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109614701B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110502783A (en) * | 2019-07-08 | 2019-11-26 | 上海宇航系统工程研究所 | Satellite vapour image analogue system and method |
| CN112507453B (en) * | 2020-12-03 | 2022-10-18 | 中国空气动力研究与发展中心计算空气动力研究所 | Multidisciplinary coupling analysis system and method taking pneumatics as core |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103970953A (en) * | 2014-05-12 | 2014-08-06 | 上海宇航系统工程研究所 | Spacecraft solar wing dynamics rapid modeling method and system |
| CN104965963A (en) * | 2015-07-31 | 2015-10-07 | 桂林电子科技大学 | Parametric modeling method of rigid-flexible coupled model |
-
2018
- 2018-12-11 CN CN201811508952.9A patent/CN109614701B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103970953A (en) * | 2014-05-12 | 2014-08-06 | 上海宇航系统工程研究所 | Spacecraft solar wing dynamics rapid modeling method and system |
| CN104965963A (en) * | 2015-07-31 | 2015-10-07 | 桂林电子科技大学 | Parametric modeling method of rigid-flexible coupled model |
Non-Patent Citations (1)
| Title |
|---|
| 《卫星太阳电池阵动力学研究综述》;田林等;《现代制造技术与装备》;20181015;第123-125页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109614701A (en) | 2019-04-12 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8060458B2 (en) | Method and system of knowledge component based engineering design | |
| Shyamsundar et al. | Collaborative virtual prototyping of product assemblies over the Internet | |
| CN102193781B (en) | Integrated design application | |
| CN109614701B (en) | Satellite solar cell array multidisciplinary simulation system and method | |
| CN110399684B (en) | Data extraction method, system and computer readable storage medium for ABAQUS crack propagation | |
| EP1715411A1 (en) | A data processing system and method | |
| CN113642069B (en) | Building wind load rapid iteration design method based on BIM and heterogeneous system | |
| CN111459621B (en) | Cloud simulation integration and scheduling method and device, computer equipment and storage medium | |
| CN110502783A (en) | Satellite vapour image analogue system and method | |
| CN102929636B (en) | A kind of human-computer interaction interface creation method and device | |
| US8869101B2 (en) | Automated implementation of business service communication and/or linkage of executable processes through automatic generation and population of variables | |
| US8024158B2 (en) | Management system and management method of CAD data used for a structural analysis | |
| Sheldon et al. | Investigation and application of multi-disciplinary optimization for automotive body-in-white development | |
| CN113821874A (en) | Ship equipment modeling method and system based on virtual-real interaction and readable storage medium | |
| CN110472307B (en) | Optical cement stripping simulation method for display system | |
| CN109671140B (en) | Cloud rendering service processing method adopting micro-service | |
| CN109002663B (en) | Simulation method and simulation platform | |
| CN113609633A (en) | Complex system collaborative simulation and verification evaluation system and method based on model | |
| Huang et al. | Web Application Development Lifecycle for Small Medium-Sized Enterprises (SMEs)(Short Paper) | |
| Xu et al. | Supporting flexibility of the CMMI process framework with a multi-layered process model | |
| Guiotto et al. | MaTeLo: automated testing suite for software validation | |
| Li et al. | Applying formal description techniques to software architectural design | |
| KR20110045262A (en) | System for Designing Architecture Engineering and Method for Using the Same | |
| CN112559612B (en) | Dynamic data extraction and sharing method and device | |
| Brdjanin et al. | UML-business profile-based business modeling in iterative-incremental software development |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |