CN105468825A - Parameterization simulation method of returner soft landing dynamics - Google Patents
Parameterization simulation method of returner soft landing dynamics Download PDFInfo
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Abstract
The invention relates to a parameterization simulation method of returner soft landing dynamics belonging to the technical field of the deep space exploration. The parameterization simulation method of returner soft landing dynamics is provided for solving the problem in the prior art that the design efficiency and the design precision of the beam structure in analysis of the returner soft landing dynamics are low. The method can generate finite element grid models of every component, automatically finishes beam structure assembly, returner model assembly, solution working condition setting, solution calculation and result extraction, can precisely reflect plastic deformation and beam bearing force state in the returner soft landing process; and the returner comprises a returner front end, a returner side wall, a returner large bottom, a returner large bottom reinforcing beam and a returner beam.
Description
Technical field
The present invention relates to the dynamic (dynamical) parameter simulation method of returner soft landing, belong to field of deep space exploration.
Background technology
The core of current China moon exploration program is manned lunar exploration and ensures that cosmonaut returns safely.In order to ensure the safety of equipment and the personnel that returner carries, Returning ball is surperficial gently, successfully to make manned returner, prevents returner overload or topples over, must carry out strict dynamic analysis and research to returner landing mission.
Cabin body landing shock problem, the scholar of various countries has carried out the research of each side, and research method mainly contains improves trial-production test, empirical theory method and finite element simulation calculation method etc.A large amount of tests can obtain more real result usually, but general costly due to it, and the cycle is longer.For the theoretical method of classics, return landing case seldom due to successfully manned, be difficult to provide reference.Along with the widespread use of Finite Element Method and the development of dynamics analysis software, the landing shock problem of finite element method return capsule is utilized to become a kind of trend.Finite element simulation calculation method has the advantages such as the cycle is short, input cost is low, reproducible, and can describe actual conditions more truly, reflect structure is on the impact of landing impact characteristics comparatively meticulously.
But owing to considering more mechanics factor, the process of establishing of returner finite element model is more complicated.In addition, need to repartition finite element grid while the some characteristic dimensions due to change returner, and the connection of each inter-module of returner is closely related with grid node.So in the initial design stage, any subtle change of returner configuration all can be brought stress and strain model and be connected the repetitive operation arranged, for this large-scale spacecraft structure of returner, repetitive operations a large amount of in modeling is not only loaded down with trivial details but also easily make mistakes, and has a strong impact on design efficiency.
Before, patent CN103678824A proposes the method for parametric simulation for lunar orbiter, but the returner large end, adopts shell structure in returner modeling, original parametric method is difficult to accurate modeling returner large end buttress brace, and accurately describes returner large end buttress brace to the consolidation effect at the returner large end; Returner crossbeam structure is complicated simultaneously, and former method is applied two-dimentional beam modeling, definition beam section and material character and described 3D solid, and this mode has problems, and lacks the careful Modeling and optimization to main force support structure beam.
Summary of the invention
In order to solve the low problem of design efficiency low and girder construction the design accuracy of prior art in returner soft landing process kinetics is analyzed, provide a kind of returner soft landing dynamic (dynamical) parameter simulation method.The finite element grid model that the method can generate each assembly also automatically completes girder construction assembling, returner Model Mounting, solves operating mode setting, solves calculating and result extraction; Accurately can reflect plastic yield and joist support power state in returner landing mission.Returner comprises returner front end, returner sidewall, the returner large end, returner device large end buttress brace, returner crossbeam.
The object of the invention is to be achieved through the following technical solutions.
The dynamic (dynamical) parameter simulation method of returner soft landing, concrete steps are as follows:
Step 1: extract the geometric feature sizes of returner assembly, the assembly relation between component mounting position and adjacent component; Extract the geometric feature sizes of earth soil and the assembly relation of earth soil and returner assembly; Returner assembly is made up of returner front end, returner sidewall, the returner large end, returner crossbeam;
Step 2: extract the geometric feature sizes (installation direction, cross sectional shape) of returner girder construction, the assembly relation between component mounting position and adjacent component.Returner girder construction is made up of returner crossbeam, returner sidewall reinforcing beam, returner large end buttress brace;
Step 3: set up returner assembly and earth soil model configuration file, the geometric feature sizes of returner front end that step 1 extracts, returner sidewall, the returner large end, returner crossbeam and earth soil is deposited in each configuration file, and their respective finite element grid control informations; Finite element grid control information comprises size of mesh opening and trellis-type;
Step 4: set up returner girder construction configuration file, deposits the geometric feature sizes of the returner crossbeam of step 2 extraction, returner sidewall reinforcing beam, returner large end buttress brace in each configuration file;
Step 5: the finite element model setting up returner assembly and earth soil: according to the geometric feature sizes in the configuration file that step 3 is set up and finite element grid control information, set up the geometric model of returner front end, returner sidewall, the returner large end, returner crossbeam and earth soil respectively, and finite element grid is divided to each geometric model.Then actual returner and material properties corresponding to earth soil texture is given to each finite element grid successively.
Step 6: the girder construction setting up returner assembly: according to the geometric feature sizes in the configuration file that step 4 is set up, the respectively geometric model of returner sidewall in modify steps 5, the returner large end and returner crossbeam.
Step 7: the entire assembly model configuration file setting up each assembly of returner, for depositing the assembly relation between the installation site of each assembly that step 1 is extracted and adjacent component.
Step 8: set up returner parametric assembly body Model: according to installation site and the assembly relation of each assembly provided in the assembly configuration file that step 7 is set up, set up global coordinate system; Then the geometric model of the amended returner sidewall of step 6 gained, the returner large end and returner crossbeam is installed to the correspondence position of global coordinate system; Again the geometric model of step 5 returner front end is installed to the correspondence position of global coordinate system; Then set up the annexation between adjacent component, form parameterized entire assembly model for subsequent calculations.
Step 9: set up realistic model configuration file, for depositing emulation work information.Emulation work information comprises the load of returner landing state and boundary condition, the integration step of simulation algorithm and simulation time.
Step 10: set up parameterized simulation model; According to the emulation work information provided in the realistic model configuration file that step 9 is set up, imposed load and boundary condition on the returner parametric assembly body Model that step 8 obtains, select simulation time and integration step, the input file that the solver finally setting up finite element software can identify.
Step 11: FEM (finite element) calculation, submits to finite element software by the input file obtained in step 10 and calculates, and obtains simulation result file.Described simulation result file comprises the response data of finite element node serial number and corresponding node.
Step 12: set up result aftertreatment configuration file, for depositing component Name and the finite element node serial number at the node place needing Output rusults.
Step 13: parameterized results aftertreatment, the node serial number provided according to the result aftertreatment configuration file of step 12 foundation and the component Name at place thereof, the simulation result file that opening steps 11 obtains, therefrom extracts the response data of corresponding node, data is write text and preservation of drawing.
Finite element software described in step 11 comprises in business finite element software Abaqus, MSC.Patran, Ansys or HyperWorks a arbitrarily.
Beneficial effect
1, the invention solves the problem that design efficiency low and girder construction the design accuracy of prior art in returner soft landing process kinetics is analyzed is low, provide a kind of returner soft landing dynamic (dynamical) parameter simulation method.The finite element grid model that the method can generate each assembly also automatically completes girder construction assembling, returner Model Mounting, solves operating mode setting, solves calculating and result extraction; Accurately can reflect plastic yield and joist support power state in returner landing mission.
2, the robotization that present invention achieves returner soft landing kinetic parameter model is set up, and avoids in the finite element modeling process of returner to change grid rezone that some characteristic dimensions cause and assembly annexation and be heavily set to the duplication of labour that designer brings.Modeling and simulation and result post-processing module are integrated into unified Parametric Analysis method, solve the design efficiency problem of prior art in returner soft landing process kinetics is analyzed.The input parameter of Parametric Analysis is separated with executive routine, incorporation engineering field prior art can realize optimal design to returner.
Accompanying drawing explanation
Fig. 1 is the dynamic (dynamical) parametric simulation schematic flow sheet of returner soft landing of the present invention;
Fig. 2 is the assembly geometric model schematic diagram of returner in embodiment;
Fig. 3 is the acceleration responsive of returner large end central point and the contrast of existing test figure in embodiment.
Embodiment
Below in conjunction with embodiment and accompanying drawing, content of the present invention is described further.
Step 1: simplify returner model.
Returner carries multiple useful load, model is very complicated, and the physical dimension related to is various.So before carrying out parametric simulation, first the present invention simplifies the physical model of returner: the basic goal of returner soft landing dynamic response analysis is the mechanical environment in order to obtain useful load on returner, thus formulates the vibration test condition of landing period.And the mechanical environment of useful load is generally weighed by shock response spectrum, the physical quantity obtained therefore is needed to be the acceleration responsive at useful load crossbeam (i.e. its installation site) on crossbeam place.Consider that the quality of useful load (vector engine at the instrument on returner crossbeam, the returner large end and the sampling soil etc. of returner front end) is less, its impact on returner acceleration can be ignored.
Therefore, only to the main force support structure modeling of returner, returner front end, returner sidewall, returner crossbeam and the returner large end can be comprised.The uniform quality of useful load is distributed in contiguous sidewall and crossbeam structure.Primary load bearing plate and shell structure due to returner be all made up of alloy material or composite material interlayer and wall thickness to be far smaller than plate long, so returner can be considered as a purely elastic shell structure.
The returner large end, is due to directly and earth surface, have larger plastic yield, only cannot reflect in reality the large bottom structure local strengthening of returner with shell material, therefore outside the large bottom case structure of returner, set up the buttress brace model at the returner large end, simulate the actual returner large end by setting returner large end buttress brace and the connection at the returner large end.D solid modeling is adopted for buttress brace, and adopts two-dimentional modeling and the method for additional cross-sectional character.Be girder construction in returner crossbeam reality, should two dimensional model be adopted.But due to complex structure, also adopt the mode of d solid modeling to reflect girder construction, the cross section of crossbeam is showed by geometry.
Step 2: extract each assembly of returner (comprising returner front end, returner sidewall, the returner large end) and the geometric feature sizes of earth soil, the assembly relation between installation site and adjacent component.Wherein between the returner large end and returner sidewall for being fixedly connected with, for being fixedly connected with between returner sidewall with returner front end, between the returner large end and earth soil for contact (friction factor gets 0.1).
Step 3: extract the geometric feature sizes of each girder construction of returner (returner crossbeam, returner sidewall reinforcing beam, returner large end buttress brace), the assembly relation between installation site and adjacent component.Wherein returner crossbeam and the returner large end, are for being fixedly connected with; Returner sidewall beam is two-dimentional beam, not Independent modeling; Returner large end buttress brace and the returner large end, are for being fixedly connected with.Returner crossbeam main body is I-beam, and oblique buttress brace is L-type beam; Returner sidewall reinforcing beam is L-type beam; Returner large end buttress brace is Ω type beam.
Step 4: set up working directory empty folder on the computer's hard, catalogue full name is A, for depositing all models and analysis result that emulate and use.Then under file A, empty folder Material (material) is set up, container (returner front end), side (returner sidewall), cross (returner crossbeam), bottom (the returner large end), bottom-copy (returner large end buttress brace), Earth (earth soil), Assembly (assembly), Analysis (analysis), Output (result), be respectively used to deposit the cast material library file being about to set up, returner front end model file, returner side wall model file, returner crossbeam model file, returner large end model file, returner large end buttress brace model file, earth soil model file, returner entire assembly model file, can be used for the model file and the acceleration destination file that carry out returner soft landing emulation.
Step 5: utilize business finite element software Abaqus to set up the material depot material.cae of returner model, for preserving all material of returner model and earth soil.
Step 6: set up (or amendment) returner assembly and earth soil model configuration file, deposits geometric feature sizes and the finite element grid control information (sizing grid and trellis-type) of corresponding assembly that step 2 extracts and earth soil in each configuration file.Namely in file container, side, cross, bottom, Earth, set up (or amendment) model configuration file container.dat, side.dat, cross.dat, bottom.dat, bottom-copy.dat, Earth.dat respectively.
Step 7: set up returner girder construction configuration file, deposit the geometric feature sizes of the girder construction that step 3 is extracted in each configuration file.Namely in file side, cross, bottom, set up (or amendment) model configuration file sidebeam.dat, crossbeam.dat, bottom-copy.dat respectively.
Step 8: set up parametric element and earth soil model
Utilize the Python program of encapsulation, the material.cae file copy first step 4 generated to be pressed from both sides under (container, side, cross, bottom, Earth) to each component file and is renamed container.cae, side.cae, cross.cae, bottom.cae, Earth.cae as assembly and earth soil model file.Then by assembly and the earth soil model configuration file of Python program reading step 5 foundation, Abaqus software is driven to open and revise assembly and earth soil model file (container.cae according to the assembly provided in configuration file and earth soil geometric feature sizes and finite element grid control information, side.cae, cross.cae, bottom.cae, Earth.cae), set up the geometric model of each assembly and earth soil and finite element grid is divided to it, finally give the material properties of actual returner and earth soil texture to zones of different on assembly and earth soil.
Step 9: utilize the girder construction configuration file that Python program reading step 6 is set up,, drive Abaqus software open and revise component model file (side.cae, cross.cae, bottom.cae, bottom-copy.cae, cross.cae) according to the girder construction geometric feature sizes provided in configuration file and finite element grid control information.
Step 10: set up (or amendment) entire assembly model configuration file
(or amendment) assembly configuration file sysassmebly.dat is set up, for depositing the assembly relation between the installation site of each assembly that step 2 is extracted and adjacent component under file Assembly.
Step 11: set up parametric assembly body Model
The Python driven by program Abaqus software of encapsulation is utilized under file assembly, to set up blank entire assembly model file assembly.cae and the assembly established in steps for importing 6 and earth soil model (container.cae, side.cae, cross.cae, bottom.cae, Earth.cae, bottom-copy.cae).The entire assembly model configuration file sysassmebly.dat that read step 7 is set up, according to the component mounting position provided in configuration file and assembly relation, in assembly.cae model file, each assembly be installed to correspondence position and set up the annexation between adjacent component, wherein between the returner large end and sidewall for being fixedly connected with, for being fixedly connected with between sidewall with front end, the large end and crossbeam are for being fixedly connected with, buttress brace of the large end and the large end, for being fixedly connected with, are contact (friction factor gets 0.1) between the large end and earth soil.Finally quality trim is carried out to returner, make its center-of-mass coordinate meet specific design needs.Save and Close assembly.cae file.Entire assembly model schematic diagram as shown in Figure 2.
Step 12: set up (or amendment) realistic model configuration file
(or amendment) realistic model configuration file analysis.dat is set up, for depositing emulation work information under file Analysis.Emulation work information comprises the load of returner landing state and boundary condition, the integration step of simulation algorithm and simulation time.
Step 13: set up parameterized simulation model
The realistic model configuration file analysis.dat utilizing the Python program reading step 9 of encapsulation to set up, renames analysis.cae as under entire assembly model file assembly.cae step 8 established copies to Analysis file.According to the emulation work information that realistic model configuration file analysis.dat provides, Abaqus software is driven to open and revise analysis.cae file, for returner imposed load and boundary condition, selection simulation time and step-length, finally set up solver (Standard solver) the discernible input file analysis.inp of Abaqus software.Save and Close analysis.cae.
Step 14: FEM (finite element) calculation, utilizes the Python program of encapsulation that the input file analysis.inp obtained in step 10 is submitted to Abaqus and calculates, obtain simulation result file analysis.odb.
Step 15: set up (or amendment) result aftertreatment configuration file
(or amendment) result aftertreatment configuration file result.dat is set up, for depositing component Name and the finite element node serial number at the node place needing Output rusults under file Output.
Step 16: parameterized results aftertreatment
Utilize the result.dat file that the Python program reading step 12 of encapsulation is set up, driving Abaqus software is opened simulation result file analysisi.odb and is extracted the response data of corresponding node according to the finite element node serial number that result.dat file provides.Then by Python stop analysisi.odb file, under response data text and time curve thereof are all stored in file Output.The Output rusults of the acceleration responsive of returner large end central point and the contrast of existing test figure as shown in Figure 3.
Above-described specific descriptions; the object of inventing, technical scheme and beneficial effect are further described; be understood that; the foregoing is only specific embodiments of the invention; for explaining the present invention, the protection domain be not intended to limit the present invention, within the spirit and principles in the present invention all; any amendment of making, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (2)
1. the dynamic (dynamical) parameter simulation method of returner soft landing, is characterized in that: concrete steps are as follows:
Step 1: extract the geometric feature sizes of returner assembly, the assembly relation between component mounting position and adjacent component; Extract the geometric feature sizes of earth soil and the assembly relation of earth soil and returner assembly; Returner assembly is made up of returner front end, returner sidewall, the returner large end, returner crossbeam;
Step 2: extract the geometric feature sizes (installation direction, cross sectional shape) of returner girder construction, the assembly relation between component mounting position and adjacent component; Returner girder construction is made up of returner crossbeam, returner sidewall reinforcing beam, returner large end buttress brace;
Step 3: set up returner assembly and earth soil model configuration file, the geometric feature sizes of returner front end that step 1 extracts, returner sidewall, the returner large end, returner crossbeam and earth soil is deposited in each configuration file, and their respective finite element grid control informations; Finite element grid control information comprises size of mesh opening and trellis-type;
Step 4: set up returner girder construction configuration file, deposits the geometric feature sizes of the returner crossbeam of step 2 extraction, returner sidewall reinforcing beam, returner large end buttress brace in each configuration file;
Step 5: the finite element model setting up returner assembly and earth soil: according to the geometric feature sizes in the configuration file that step 3 is set up and finite element grid control information, set up the geometric model of returner front end, returner sidewall, the returner large end, returner crossbeam and earth soil respectively, and finite element grid is divided to each geometric model; Then actual returner and material properties corresponding to earth soil texture is given to each finite element grid successively;
Step 6: the girder construction setting up returner assembly: according to the geometric feature sizes in the configuration file that step 4 is set up, the respectively geometric model of returner sidewall in modify steps 5, the returner large end and returner crossbeam;
Step 7: the entire assembly model configuration file setting up each assembly of returner, for depositing the assembly relation between the installation site of each assembly that step 1 is extracted and adjacent component;
Step 8: set up returner parametric assembly body Model: according to installation site and the assembly relation of each assembly provided in the assembly configuration file that step 7 is set up, set up global coordinate system; Then the geometric model of the amended returner sidewall of step 6 gained, the returner large end and returner crossbeam is installed to the correspondence position of global coordinate system; Again the geometric model of step 5 returner front end is installed to the correspondence position of global coordinate system; Then set up the annexation between adjacent component, form parameterized entire assembly model for subsequent calculations;
Step 9: set up realistic model configuration file, for depositing emulation work information; Emulation work information comprises the load of returner landing state and boundary condition, the integration step of simulation algorithm and simulation time;
Step 10: set up parameterized simulation model; According to the emulation work information provided in the realistic model configuration file that step 9 is set up, imposed load and boundary condition on the returner parametric assembly body Model that step 8 obtains, select simulation time and integration step, the input file that the solver finally setting up finite element software can identify;
Step 11: FEM (finite element) calculation, submits to finite element software by the input file obtained in step 10 and calculates, and obtains simulation result file; Described simulation result file comprises the response data of finite element node serial number and corresponding node;
Step 12: set up result aftertreatment configuration file, for depositing component Name and the finite element node serial number at the node place needing Output rusults;
Step 13: parameterized results aftertreatment, the node serial number provided according to the result aftertreatment configuration file of step 12 foundation and the component Name at place thereof, the simulation result file that opening steps 11 obtains, therefrom extracts the response data of corresponding node, data is write text and preservation of drawing.
2. the dynamic (dynamical) parameter simulation method of returner soft landing as claimed in claim 1, is characterized in that: finite element software described in step 11 comprises in business finite element software Abaqus, MSC.Patran, Ansys or HyperWorks a arbitrarily.
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| CN110442117A (en) * | 2019-08-26 | 2019-11-12 | 北京理工大学 | A kind of pneumatic integrated separation process safety analysis method of Mars probes outsole |
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| CN101074880A (en) * | 2007-07-24 | 2007-11-21 | 北京控制工程研究所 | Method for scanning entry safety landing area in moon detector suspension stage |
| CN103678824A (en) * | 2013-12-25 | 2014-03-26 | 北京理工大学 | Parameterization simulation method of lunar probe soft landing dynamics |
| CN105043395A (en) * | 2015-07-17 | 2015-11-11 | 浙江工业大学 | Real-time dynamic location method for moon surface soft landing of aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101074880A (en) * | 2007-07-24 | 2007-11-21 | 北京控制工程研究所 | Method for scanning entry safety landing area in moon detector suspension stage |
| CN103678824A (en) * | 2013-12-25 | 2014-03-26 | 北京理工大学 | Parameterization simulation method of lunar probe soft landing dynamics |
| CN105043395A (en) * | 2015-07-17 | 2015-11-11 | 浙江工业大学 | Real-time dynamic location method for moon surface soft landing of aircraft |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110442117A (en) * | 2019-08-26 | 2019-11-12 | 北京理工大学 | A kind of pneumatic integrated separation process safety analysis method of Mars probes outsole |
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