CN103970953A - Spacecraft solar wing dynamics rapid modeling method and system - Google Patents
Spacecraft solar wing dynamics rapid modeling method and system Download PDFInfo
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- CN103970953A CN103970953A CN201410197456.1A CN201410197456A CN103970953A CN 103970953 A CN103970953 A CN 103970953A CN 201410197456 A CN201410197456 A CN 201410197456A CN 103970953 A CN103970953 A CN 103970953A
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Abstract
The invention discloses a spacecraft solar wing dynamics rapid modeling method and system. Design parameters of a spacecraft solar wing are determined, a finite element analytical model of the solar wing is generated automatically through a program, analysis software is called for conducting dynamics analysis on the solar wing model, the whole spacecraft solar wing dynamics simulation analysis process is completed automatically, and the spacecraft solar wing dynamics rapid modeling method and system are economical and efficient. The spacecraft solar wing dynamics rapid modeling method and system can be widely applied to spacecraft solar wing dynamics automatic simulation analysis design, can rapidly and effectively conduct dynamics analysis and iterative optimization on the solar wing, and greatly shorten the research and development cycle of the solar wing.
Description
Technical field
The present invention relates to aerospacecraft technical field, particularly a kind of spacecraft sun wing dynamics fast modeling method and system.
Background technology
At present, the sun wing of most of expandable type all mainly adopts the interconnective version of hinge between composite substrate and plate, at initiatively transmitter section of spacecraft, its folded gathering is to be pressed on spacecraft sidewall, spacecraft enter the orbit after its automatic unlocking launch, for spacecraft operation on orbit provides power, it is the requisite ingredient of each spacecraft.As large-scale flexible parts of spacecraft, the dynamic performance of sun wing rounding state and deployed condition is most important, directly affect the wrong design frequently of spacecraft secondary structure powered phase, launch rear whole star attitude control and load problem in-orbit, be therefore necessary it to carry out dynamic analysis.The sun wing is carried out to Dynamic Modeling in the past and all adopt manual mode to complete, analytic process is tediously long, and iteration optimization difficulty, the design cycle that is difficult to accelerate the sun wing.
Do not find at present explanation or the report of technology similar to the present invention, not yet collect both at home and abroad similarly data yet.
Summary of the invention
The present invention is directed to prior art above shortcomings, a kind of spacecraft sun wing dynamics fast modeling method is provided.The present invention is achieved through the following technical solutions:
A kind of spacecraft sun wing dynamics fast modeling method, comprises step:
S1, determine and the parameter of the sun wing comprise sun wing design parameter, mechanism performance parameter, input UltraEdit text edit software;
S2, taking MATLAB program as platform, call UltraEdit text edit software and automatically generate sun wing finite element analysis numerical model;
S3, utilize the outside solver of MATLAB routine call to carry out dynamic analysis to sun wing finite element analysis numerical model;
Operating mode is analyzed in S4, setting, and sun wing finite element analysis numerical model is carried out to multi-state analysis, and multi-state analysis comprises sinusoidal vibration response analysis, Random vibration analysis, shock analysis, nonlinear analysis;
S5, according to analysis result data curve plotting;
The extreme value of S6, extraction curve, judges whether to meet design requirement, the row iteration design optimization of going forward side by side;
S7, if the determination result is YES, generates final analysis report the test; If judged result is no, return to step S1 and redefine the parameter of the sun wing.
Preferably, sun wing design parameter comprises length and width, the plate number of sun wing scale, the long and short length of side of link, the long length of side, link cross section is wide, height and thickness, the sun wing draws in and expansion plate spacing, sun wing material and plate thickness, honeycomb thickness, mechanism performance parameter comprises hinge six direction stiffness parameters between the root of the sun wing and plate, compresses releasing mechanism stiffness parameters.
Fast modeling method provided by the invention can complete automatically from finite element modeling, analysis, design optimization, to generating a series of processes such as report, can carry out dynamic analysis and iteration optimization to the sun wing quickly and efficiently, greatly shorten the sun wing R&D cycle.
The present invention is directed to prior art above shortcomings, a kind of spacecraft sun wing dynamics rapid modeling system is provided.The present invention is achieved through the following technical solutions:
A kind of spacecraft sun wing dynamics rapid modeling system, comprises interconnective:
MATLAB program, in order to the platform as spacecraft sun wing dynamics rapid modeling system;
Parameter input module, in order to input the parameter of the sun wing, parameter comprises sun wing design parameter, mechanism performance parameter;
Generate substrate module, in order to automatically to generate sun wing finite element analysis numerical model according to the parameter of input;
Operating mode is selected module, and in order to select the required multi-state analysis of carrying out, multi-state analysis comprises sinusoidal vibration response analysis, Random vibration analysis, shock analysis, nonlinear analysis;
Computing module, carries out multi-state analysis according to selected multi-state analysis to sun wing finite element analysis numerical model;
Post-processing module, according to the multi-state analysis result data curve plotting of computing module, and extracts curve extreme value;
Generate reporting modules, in order to generate final analysis report the test according to the result of computing module and post-processing module.
Preferably, sun wing design parameter comprises length and width, the plate number of sun wing scale, the long and short length of side of link, the long length of side, link cross section is wide, height and thickness, the sun wing draws in and expansion plate spacing, sun wing material and plate thickness, honeycomb thickness, mechanism performance parameter comprises hinge six direction stiffness parameters between the root of the sun wing and plate, compresses releasing mechanism stiffness parameters.
Rapid modeling system provided by the invention can complete automatically from finite element modeling, analysis, design optimization, to generating a series of processes such as report, can carry out dynamic analysis and iteration optimization to the sun wing quickly and efficiently, greatly shorten the sun wing R&D cycle.
Brief description of the drawings
Shown in Fig. 1 is the process flow diagram of the spacecraft sun wing dynamics fast modeling method that provides of the embodiment of the present invention;
Shown in Fig. 2 is the structural representation of the spacecraft sun wing dynamics rapid modeling system that provides of the embodiment of the present invention;
Shown in Fig. 3-5 is respectively front elevation, vertical view, the right view of the aircraft solar wing spreading state that provides of the embodiment of the present invention;
Shown in Fig. 6-8 is respectively front elevation, vertical view, the right view of the aircraft sun wing rounding state that provides of the embodiment of the present invention.
Embodiment
Below with reference to accompanying drawing of the present invention; technical scheme in the embodiment of the present invention is carried out to clear, complete description and discussion; obviously; as described herein is only a part of example of the present invention; it is not whole examples; based on the embodiment in the present invention, the every other embodiment that those of ordinary skill in the art obtain under the prerequisite of not making creative work, belongs to protection scope of the present invention.
For the ease of the understanding to the embodiment of the present invention, be further explained as an example of specific embodiment example below in conjunction with accompanying drawing, and each embodiment does not form the restriction to the embodiment of the present invention.
As shown in Figure 1, a kind of spacecraft sun wing dynamics fast modeling method provided by the invention, comprises step:
Step 1, determine the parameter of the sun wing, comprise sun wing design parameter, mechanism performance parameter, input UltraEdit text edit software, UltraEdit text edit software is a kind of existing text editor, can Edit Text, sexadecimal, ASCII code;
Step 2, taking MATLAB program as platform, UltraEdit input text in invocation step 1, realized and generated fast and automatically sun wing finite element analysis numerical model by self-compiling program, MATLAB program is a kind of advanced techniques computational language and interactive environment for algorithm development, data visualization, data analysis and numerical evaluation.Except matrix operation, draw the common functions such as functions/data image, MATLAB can also be used to create user interface and with the program of calling other Languages (comprising C, C++ and FORTRAN) and writing;
Step 3, utilize the self-compiling program in step 2, by the outside solver NASTRAN of MATLAB platform invoke business software, sun wing finite element analysis numerical model is carried out to dynamic analysis, NASTRAN solver is widely used in Aero-Space industry, it has powerful static analysis, dynamic analysis, the numerous functions of nonlinear analysis and structure optimization etc., become domestic and international Aero-Space industry standard analysis software, but NASTRAN software lacks pretreatment process, step 1 and step 2 generate NASTRAN software input file according to actual needs, directly submit to it to carry out computational analysis,
Operating mode is analyzed in step 4, setting, and carry out multi-state analysis, multi-state analysis comprises sinusoidal vibration response analysis, Random vibration analysis, instantaneous response analysis, shock analysis, nonlinear analysis etc., can increase sinusoidal vibration response and the Random vibration analysis of three direction multi-states, instantaneous response analysis, solar wing spreading shock analysis and other nonlinear analyses, can once set, avoid repetition redjustment and modification, convenient and swift;
Step 5, extract the data in NASTRAN software analysis result, fast automatic generation response curve based on the self-compiling program of MATLAB platform;
Step 6, key position based on generating in step 5 or pay close attention to the curve map at position, extract its response curve extreme value, and the extreme value of acquisition and predefined constraint condition compared to judgement, if judged result is very, generates final analysis report the test; If judged result is no, return to step 1 and redefine the parameter of the sun wing.Realize iteration, optimal design by said process;
Overall process modeling, analysis, the iteration optimization of step 7, process step 1 ~ step 6, obtain meeting the analysis result of designing requirement, and automatically generate the report of WORD document.
As shown in Figure 2, a kind of spacecraft sun wing dynamics rapid modeling system provided by the invention, comprising: MATLAB program 1, in order to the platform as spacecraft sun wing dynamics rapid modeling system; Parameter input module 2, in order to input the parameter of the sun wing, parameter comprises sun wing design parameter, mechanism performance parameter; Generate substrate module 3, in order to automatically to generate sun wing finite element analysis numerical model according to the parameter of input; Operating mode is selected module 4, and in order to select the required multi-state analysis of carrying out, multi-state analysis comprises sinusoidal vibration response analysis, Random vibration analysis, shock analysis, nonlinear analysis; Computing module 5, carries out multi-state analysis according to selected multi-state analysis to sun wing finite element analysis numerical model; Post-processing module 6, according to the multi-state analysis result data curve plotting of computing module, and extracts curve extreme value; Generate reporting modules 7, in order to generate final analysis report the test according to the result of computing module and post-processing module.
The present invention is by adopting above method, system to determine aircraft sun wing primary structure design parameter, automatically generate sun wing finite element analysis model by program, call analysis software sun wing model is carried out to dynamic analysis, aircraft sun wing Dynamics Simulation Analysis whole-course automation is completed, and economical, efficient.Can be widely used in aircraft sun wing dynamics automatic simulation analysis design, can carry out dynamic analysis and iteration optimization to the sun wing quickly and efficiently, greatly shorten the R&D cycle of the sun wing.
In the present invention, sun wing design parameter comprises length and width, the plate number of sun wing scale, the long and short length of side of link, the long length of side, link cross section is wide, height and thickness, the sun wing draws in and expansion plate spacing, sun wing material and plate thickness, honeycomb thickness, mechanism performance parameter comprises hinge six direction stiffness parameters between the root of the sun wing and plate, compresses releasing mechanism stiffness parameters.
Embodiment
As shown in Fig. 3-8, the present embodiment provides a kind of spacecraft sun wing dynamics rapid modeling and design optimization method, and the method comprises the steps:
Step 1: determine sun wing design parameter; The present invention chooses altogether 17 structural parameters, is specially: 1) substrate plate is counted N1; 2) the long L1 of substrate plate; 3) the wide H1 of substrate plate; 4) the long H3 of link minor face; 5) the long length of side H2 of link; 6) the long L2 of link; 7) deployed condition distance between plates D2; 8) the long D1 of root hinge; 9) the wide L3 in link cross section; 10) the high H4 in link cross section; 11) the thick T3 in link cross section; 12) real estate thickness of slab T1; 13) the thick T2 of substrate honeycomb; 14) compress some number N2; 15) compress some long spacing G; 16) compress the wide spacing I of point; 17) rounding state distance between plates D3;
Step 2: set up sun wing dynamic analysis digital model; Particularly, utilize the selected structural parameters of step 1, taking MATLAB as platform, routine call UltraEdit text edit software generates sun wing finite element analysis numerical model file automatically;
Step 3: selection analysis type, is used outside solver to carry out dynamic analysis to the sun wing;
Step 4: set and analyze operating mode, and carry out multi-state analysis;
Step 5: according to analysis result data curve plotting;
Step 6: extract curve extreme value, whether judged result meets design requirement, and carries out design optimization;
Step 7: generate final analysis report the test.
The above; only for preferably embodiment of the present invention, but protection scope of the present invention is not limited to this, is anyly familiar with in technical scope that those skilled in the art disclose in the present invention; the variation that can expect easily or replacement, within all should being encompassed in protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with the protection domain of claim.
Claims (4)
1. a spacecraft sun wing dynamics fast modeling method, is characterized in that, comprises step:
S1, determine and the parameter of the sun wing comprise sun wing design parameter, mechanism performance parameter, input UltraEdit text edit software;
S2, taking MATLAB program as platform, call UltraEdit text edit software and automatically generate sun wing finite element analysis numerical model;
S3, utilize the outside solver of MATLAB routine call to carry out dynamic analysis to described sun wing finite element analysis numerical model;
Operating mode is analyzed in S4, setting, and described sun wing finite element analysis numerical model is carried out to multi-state analysis, and described multi-state analysis comprises sinusoidal vibration response analysis, Random vibration analysis, shock analysis, nonlinear analysis;
S5, according to analysis result data curve plotting;
The extreme value of S6, extraction curve, judges whether to meet design requirement, the row iteration design optimization of going forward side by side;
S7, if the determination result is YES, generates final analysis report the test; If judged result is no, return to step S1 and redefine the parameter of the sun wing.
2. spacecraft sun wing dynamics fast modeling method according to claim 1, it is characterized in that, described sun wing design parameter comprises length and width, the plate number of sun wing scale, the long and short length of side of link, the long length of side, link cross section is wide, height and thickness, the sun wing draws in and expansion plate spacing, sun wing material and plate thickness, honeycomb thickness, and described mechanism performance parameter comprises hinge six direction stiffness parameters between the root of the sun wing and plate, compression releasing mechanism stiffness parameters.
3. a spacecraft sun wing dynamics rapid modeling system, is characterized in that, comprises interconnective:
MATLAB program, in order to the platform as described spacecraft sun wing dynamics rapid modeling system;
Parameter input module, in order to input the parameter of the sun wing, described parameter comprises sun wing design parameter, mechanism performance parameter;
Generate substrate module, in order to automatically to generate sun wing finite element analysis numerical model according to the parameter of input;
Operating mode is selected module, and in order to select the required multi-state analysis of carrying out, described multi-state analysis comprises sinusoidal vibration response analysis, Random vibration analysis, shock analysis, nonlinear analysis;
Computing module, carries out multi-state analysis according to selected multi-state analysis to described sun wing finite element analysis numerical model;
Post-processing module, according to the multi-state analysis result data curve plotting of described computing module, and extracts curve extreme value;
Generate reporting modules, in order to generate final analysis report the test according to the result of described computing module and described post-processing module.
4. spacecraft sun wing dynamics fast modeling method according to claim 3, it is characterized in that, described sun wing design parameter comprises length and width, the plate number of sun wing scale, the long and short length of side of link, the long length of side, link cross section is wide, height and thickness, the sun wing draws in and expansion plate spacing, sun wing material and plate thickness, honeycomb thickness, and described mechanism performance parameter comprises hinge six direction stiffness parameters between the root of the sun wing and plate, compression releasing mechanism stiffness parameters.
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104484498A (en) * | 2014-11-18 | 2015-04-01 | 中国空间技术研究院 | Solar sail transient dynamic analyzing method for determining effective propulsion acceleration breakage |
| CN106168998A (en) * | 2016-07-06 | 2016-11-30 | 北京理工大学 | Consider that the full electricity of solar wing radiation damage pushes away spacecraft orbit transfer optimization method |
| CN106934217A (en) * | 2017-02-16 | 2017-07-07 | 北京空间飞行器总体设计部 | A kind of spacecraft power fast synthesis method and system based on mission program |
| CN109614701A (en) * | 2018-12-11 | 2019-04-12 | 上海宇航***工程研究所 | A kind of multidisciplinary analogue system of Satellite vapour image and method |
| CN113361001A (en) * | 2021-04-27 | 2021-09-07 | 山东大学 | Solar wing structure optimization method and device combining finite element method and gradient method and storage medium |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101236573A (en) * | 2007-05-25 | 2008-08-06 | 清华大学 | Flex wing minisize aerial craft fluid-solid coupling numerical value emulation method |
-
2014
- 2014-05-12 CN CN201410197456.1A patent/CN103970953B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101236573A (en) * | 2007-05-25 | 2008-08-06 | 清华大学 | Flex wing minisize aerial craft fluid-solid coupling numerical value emulation method |
Non-Patent Citations (2)
| Title |
|---|
| 蒋建平，李东旭: "《智能太阳翼有限元建模与振动控制研究》", 《动力学与控制学报》 * |
| 覃正 等: "《柔性多体***动力学研究及存在的问题》", 《力学进展》 * |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104484498A (en) * | 2014-11-18 | 2015-04-01 | 中国空间技术研究院 | Solar sail transient dynamic analyzing method for determining effective propulsion acceleration breakage |
| CN104484498B (en) * | 2014-11-18 | 2017-07-28 | 中国空间技术研究院 | It is determined that effectively pushing the solar sail transient dynamic analysis method that acceleration is lost |
| CN106168998A (en) * | 2016-07-06 | 2016-11-30 | 北京理工大学 | Consider that the full electricity of solar wing radiation damage pushes away spacecraft orbit transfer optimization method |
| CN106168998B (en) * | 2016-07-06 | 2019-07-23 | 北京理工大学 | Consider that the full electricity of solar wing radiation injury pushes away spacecraft orbit transfer optimization method |
| CN106934217A (en) * | 2017-02-16 | 2017-07-07 | 北京空间飞行器总体设计部 | A kind of spacecraft power fast synthesis method and system based on mission program |
| CN106934217B (en) * | 2017-02-16 | 2019-03-12 | 北京空间飞行器总体设计部 | A kind of spacecraft power fast synthesis method and system based on mission program |
| CN109614701A (en) * | 2018-12-11 | 2019-04-12 | 上海宇航***工程研究所 | A kind of multidisciplinary analogue system of Satellite vapour image and method |
| CN109614701B (en) * | 2018-12-11 | 2023-08-11 | 上海宇航***工程研究所 | Satellite solar cell array multidisciplinary simulation system and method |
| CN113361001A (en) * | 2021-04-27 | 2021-09-07 | 山东大学 | Solar wing structure optimization method and device combining finite element method and gradient method and storage medium |
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Effective date of registration: 20170705 Address after: 201108 D, room 101, No. 730, Lu Chun Road, Shanghai, Minhang District Patentee after: Shanghai Aiyisi Aerospace Science and Technology Co Ltd Address before: 201108 Minhang District, Shanghai Jin Road, No. 3805 Patentee before: Shanghai Aerospace System Engineering Research Inst |
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