CN102867097A - Method for designing photo-cure quickly formed wind tunnel model in consideration of influence of static elastic deformation - Google Patents
Method for designing photo-cure quickly formed wind tunnel model in consideration of influence of static elastic deformation Download PDFInfo
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Abstract
The invention discloses a method for designing a photo-cure quickly formed wind tunnel model in consideration of influence of static elastic deformation. Mapping relation between structural deformation of the model and aerodynamic force is predicted by an aerodynamic/structure coupling analysis method in order to overcome shortcomings of low rigidity, easiness in deformation and the like of thin positions (such as wing tips, wing edges and control plane edges) of the photo-cure quickly formed wind tunnel model, and the aerodynamic shape of the model after the model deforms in a wind tunnel test is consistent with the shape of a cruise required to be researched by searching for a coupling optimization design for the aerodynamic shape of the model by a response surface method, so that corresponding aerodynamic force characteristics of the model are obtained, and accuracy and feasibility of the method are tested by verifying results of practical wind tunnel tests by a typical high-aspect-ratio aircraft model.
Description
Technical field
The invention belongs to the experimental aerodynamics technical field, particularly a kind of photocureable rapid shaping wind tunnel model method for designing of taking into account the static elasticity deformation effect.
Background technology
Wind tunnel model is the object of wind tunnel test, is the prerequisite that obtains accurate test figure.
Traditional high-speed wind tunnel modelling take metal as material and the process-cycle is long, cost is high, the complex appearance model forming is difficult, has seriously restricted the wind tunnel test progress, affect model and develops node.The high-speed wind tunnel model of metal material causes being difficult to control the mass distribution and counterweight ratio of wind tunnel model on the one hand because relying on numerical control cutting processing; Cause on the other hand that the manufacturing cycle is long, cost is high, is processed as example with wing, easily cause machining stress after the digital control processing, can cause the wing distortion, therefore usually need arrange repeatedly heat treatment step, eliminate forming residual stress, thereby increased model manufacturing cycle and cost.
The high-speed wind tunnel model lead time accounts for 70% of the aerodynamic configuration of aircraft design cycle at present, has become to promote aircraft conceptual design speed and the topmost bottleneck of model Development Schedule.
For better future aircraft design requirement, the quickening model development process of adapting to, the design of high-speed wind tunnel model and job operation are badly in need of improving at present, in order in the Flight Vehicle Design process, finish design, processing and the correction of the flank shape of wind tunnel model and promote design level, finish faster and better wind tunnel test, obtain accurate test figure.
Introduction To Stereolithography can with arbitrarily complicated three-dimensional CAD model discrete be that one group of parallel cut is cumulative, this has been avoided the geometrical interference and the unrelieved stress phenomenon that occur in the cut, therefore has following advantage:
(1) shape face machining precision and the surface quality of wind tunnel model are high, and the utmost point is suitable for making the aircraft wind tunnel model with complicated surface;
(2) be convenient to control quality and the Stiffness Distribution of wind tunnel model;
(3) proportion of photosensitive resin is far below metal material, therefore be convenient to make the high-speed wind tunnel model of lightweight.
Given this, the many wind tunnel experimental researches mechanism of present generally carries out model in wind tunnel method for designing and the applied research based on the photocuring rapid technology, to solve the development difficult problem of large scale high-speed wind tunnel model, provide technical support for accelerating model development process and model in wind tunnel correction of the flank shape etc.At rapid prototyping model forming technical elements, US and European maintains the leading position always, U.S. NASA Marshall flight research center has verified that the photocureable rapid shaping model carries out the feasibility of high-speed wind tunnel test, the result show " the model expense done of steel or aluminum is 15000 dollars, three first quarter moons consuming time; and the production costs of the lightweight wind tunnel model of photocureable rapid shaping between 3000 to 3500 dollars, 2-3 consuming time week, and quality is down to original 3/4 ".
The Europe Air Passenger confirms " geometric shape based on the wind tunnel model of Introduction To Stereolithography is more accurate, makes it in the improvement of wing end lift improved 3% " in the results of wind tunnel of Britain cloth reason Manfred Stohl.Also there is own unique mould processing technology in Russia central fluid mechanics study institute (TsAGI), also introduced the model rapid forming equipment from the U.S. in 2009, tentative confirmation " rapid shaping technique can produce parts and the model that single fighter plane wind tunnel model parts and composite manufacturing go out combination with high precision ".The advance of Introduction To Stereolithography is mainly reflected in CAD/CAM modelling and the aspects such as machining software, mould, material and process technology, especially can realize the rapid shaping (such as the moulding in several days of X-33 model) of wind tunnel model, and according to circumstances also can be to real-time correction of the flank shape of model in the wind tunnel test process, thereby make wind tunnel test CFDization.Like this, both greatly reduce the cost of mould processing, shortened again the model lead time.
Therefore, carry out photocureable rapid shaping wind tunnel model method for designing and high-speed wind tunnel applied research, development photocureable rapid shaping wind tunnel model method for designing, exploration high-speed wind tunnel application feasibility, not only to solve photocureable rapid shaping wind tunnel model design challenges, shorten the mould processing cycle, cut down finished cost significant, and to improving wind tunnel test efficient, shortening the model lead time larger benefit is arranged.
But regrettably, domestic at photocureable rapid shaping the development of high-speed wind tunnel model and the relevant report of wind tunnel test seldom.In recent years, preliminary pilot study has been carried out in photocureable rapid shaping high-speed wind tunnel modelling theory, method and application facet in China's aerodynamic investigation and centre of development, obtain challenging progress, found some technological difficulties that need to further investigate and key issues.
In the research process in early stage, processed photosensitive resin rapid shaping AGARD-B wind tunnel model based on photosensitive resin proportion much smaller than the advantage of metal material, model quality reduces greatly, and changed model-support system natural frequency, the low peak frequency of avoiding the pneumatic pulsation of transonic wind tunnel test section has realized vibration damping; Metallic framework adopts configuration simple in structure, standard in the model, and profile adopts the photosensitive resin configuration of photocureable rapid shaping.
The AGARD-B wind tunnel model demonstration test result of photocureable rapid shaping shows:
(1) photocureable rapid shaping high-speed wind tunnel model composite structural design method basic feasible solution, and obtain china national practical new-type patent (patent No. ZL200720082763.0);
(2) shorten the mould processing cycle approximately 69.5%;
(3) reduce mould processing cost approximately 70.3%;
(4) improve model first natural frequency approximately 73.2%;
(5) alleviate model weight approximately 38.9%.
Above-mentioned information slip Benq can be applied to the high-speed wind tunnel test in the lightweight high-speed wind tunnel model of Introduction To Stereolithography, but photosensitive resin profile ratio of rigidity metal material model is low, yielding under high aerodynamic loading, the pneumostatic bounce effect is more obvious, the result is influential to photocureable rapid shaping high-speed wind tunnel model aerodynamic test, there are differences with metal pattern, therefore present photocureable rapid shaping wind tunnel model both domestic and external also only is used for initial stage aerodynamic configuration type selecting and member profile type Selection Test, can't satisfy at present to a certain extent aircraft model wind tunnel model development demand fully, be difficult to form engineering practical value.
For this reason, the technician is actively developing photocureable rapid shaping wind tunnel model design theory, method and the applied research of taking into account the static elasticity deformation effect both at home and abroad, in order to the photocureable rapid shaping wind tunnel model is generalized to meticulousr pneumatic type Selection Test.
Summary of the invention
In order to overcome the above-mentioned shortcoming of prior art, the invention provides a kind of photocureable rapid shaping wind tunnel model method for designing of taking into account the static elasticity deformation effect, for photocureable rapid shaping wind tunnel model thin location (such as wing tip, the wing edge, rudder face edges etc.) rigidity is low, the defective such as yielding, adopt the mapping relations between pneumatic/structure coupling analysis method forecast model malformation and aerodynamic force, by response surface method search model coupling optimal design aerodynamic configuration, so that the aerodynamic configuration behind the model deformation is consistent with the profile of cruising that needs research in the wind tunnel test, thereby obtain the corresponding aerodynamic characteristics of model, and utilize correctness and the feasibility of typical high aspect ratio dummy vehicle checking example results of wind tunnel checking the method.
The technical solution adopted for the present invention to solve the technical problems is: a kind of photocureable rapid shaping wind tunnel model method for designing of taking into account the static elasticity deformation effect comprises the steps:
Step 1, set up CFD/CSD Coupled Numerical computation model and the grid of photocureable rapid shaping wind tunnel model:
(1) sets up the three-dimensional structure geometric parameter database of describing photocureable rapid shaping model structure profile, obtain the three-dimensional structure schematic diagram of photocureable rapid shaping model;
(2) the photocureable rapid shaping model surface is carried out discretize, the non-structure triangular mesh of partitioning model object plane, partitioning model inner structure zoning grid is finished the generation of model structure analysis grid model again;
(3) the photocureable rapid shaping model surface is carried out discretize, partitioning model surface structure quadrilateral mesh, extrapolate at the numerical evaluation area of space according to model object plane grid again, divide the fluid zoning and analyze grid, finish the generation that reaches fluid zoning, space grid model in model object plane, the boundary layer;
The pneumostatic dynamic elasticity distortion of the photocureable rapid shaping model elastic construction under step 2, the employing CFD/CSD Coupled Numerical software prediction study condition:
(1) according to the different requirements of structure and fluid calculation, borderline region and the condition of photocureable rapid shaping model structure and fluid calculation is set;
(2) the three dimensions node with all subject coupled interfaces projects on the two-dimensional parameter space plane, carries out aerodynamic loading and the transmission of displacement structure data;
(3) carrying out photocureable rapid shaping MODEL C FD/CSD Coupled Numerical calculates;
(4) adopt the dual-time Push Technology, in real physical time iterative process, call fluid calculation software and obtain photocureable rapid shaping model object plane aerodynamic force load, by the coupling data transmission method aerodynamic loading parameter is transmitted to the structure analysis grid cell, carry out structural stress, deformation analysis, finish a time step fluid and structure Coupling and calculate; Enter into next time step along this time step fluid and structure analysis and carry out iterative computation;
(5) when the model deformation after fluid calculation and the Structure Calculation process iteration and the satisfied constraint condition of setting of changes in aerodynamic forces, then illustrate based on the CFD/CSD coupling calculating of fluid and structure and satisfy the condition of convergence, fluid and structure coupling analysis process finish, and obtain the construction profile under the photocureable rapid shaping model cruising condition;
Step 3, based on the optimizing pneumatic profile of the pneumostatic dynamic elasticity deformation effect of response surface method search photocureable rapid shaping model:
(1) according to the numerical grid model parameterization software of fairing Free Transform, sets up and optimize the variable shape Optimal Parameters model of computation complexity;
(2) utilize based on the photocureable rapid shaping model of response surface method pneumatic/the structure Coupling Optimization Software, to the photocureable rapid shaping model pneumatic/disturbance in the structure Coupling optimal design feasible zone carries out parametric modeling, obtains designing optimal structural design in the feasible zone by the operation of fairing Free Transform;
Step 4, set up the composite structure form of photocureable rapid shaping model wind tunnel test model, finish design and the processing of model;
Step 5, photocureable rapid shaping model aerodynamic characteristic wind-tunnel demonstration test.
Described to the photocureable rapid shaping model pneumatic/method that parametric modeling is carried out in disturbance in the structure Coupling optimal design feasible zone is: photocureable rapid shaping model original shape is carried out pneumatic/structure Coupling and calculates, obtain model convergence profile, obtain the response of node configuration load and malformation, be designated as
, as initial value, bring Optimized Program into, obtain node configuration along different coordinate direction coefficient of indentations
, design parameter is optimized
, formula is as follows:
,
,
Utilization based on the photocureable rapid shaping model of response surface method pneumatic/the structure Coupling Optimization Software obtains the optimum profile of model structure.
Compared with prior art, good effect of the present invention is: for photocureable rapid shaping lightweight wind tunnel model under the aerodynamic loading effect, the model thin location easily deforms, thereby cause model test aerodynamic configuration and the profile of cruising to have the key issue of larger difference, propose to adopt pneumatic/structure Coupling Optimization Design to set up the photocureable rapid shaping wind tunnel model method for designing of taking into account pneumostatic dynamic elasticity deformation effect, process by the optimizing of response surface method, obtain desirable model aerodynamic configuration, to satisfy high-speed wind tunnel test demand.
Embodiment
A kind of photocureable rapid shaping wind tunnel model method for designing of taking into account the static elasticity deformation effect comprises the steps:
Step 1, set up CFD/CSD Coupled Numerical computation model and the grid of photocureable rapid shaping wind tunnel model:
(1) sets up the three-dimensional structure geometric parameter database of describing photocureable rapid shaping model structure profile, obtain photocureable rapid shaping model three-dimensional structure schematic diagram;
(2) the photocureable rapid shaping model surface is carried out discretize, the non-structure triangular mesh of partitioning model object plane, partitioning model inner structure zoning grid is finished the generation of model structure analysis grid model again;
(3) the photocureable rapid shaping model surface is carried out discretize, partitioning model surface structure quadrilateral mesh, extrapolate at the numerical evaluation area of space according to model object plane grid again, divide the fluid zoning and analyze grid, finish the generation that reaches fluid zoning, space grid model in model object plane, the boundary layer.
The pneumostatic dynamic elasticity distortion of the photocureable rapid shaping model elastic construction under step 2, the employing CFD/CSD Coupled Numerical software prediction study condition:
(1) according to the different requirements of structure and fluid calculation, borderline region and the condition of photocureable rapid shaping model structure and fluid calculation is set;
(2) at first carry out photocureable rapid shaping model object plane structure and the relationship analysis of fluid analysis mesh fitting, solve calculating parameter and a data transmission difficult problem between Structure Calculation software and the fluid calculation software.The three dimensions node of all subject coupled interfaces is projected on the two-dimensional parameter space plane, carry out aerodynamic loading and the transmission of displacement structure data;
(3) carrying out photocureable rapid shaping MODEL C FD/CSD Coupled Numerical calculates, namely utilize on the synchronization model object plane grid topological relation between CFD and CSD grid cell constant, and consider that coupled interface is improved quality, the conservation condition of momentum, energy, set up the Local Fairing means of communication of the higher stress-strain field of universality/flow field coupling physical amount (comprising displacement, velocity and acceleration), solved the inconsistent and fluid of CFD fluid surface grids and CSD works surface grids and the exchanges data problem between the structured grid model.
(4) adopt the dual-time Push Technology, in real physical time iterative process, call fluid calculation software and obtain photocureable rapid shaping model object plane aerodynamic force load, by the coupling data transmission method aerodynamic loading parameter is transmitted to the structure analysis grid cell, carry out structural stress/strain, deformation analysis, finish a time step fluid and structure Coupling and calculate; Enter into next time step along this time step fluid and structure analysis and carry out iterative computation.
(5) when the model deformation after fluid calculation and the Structure Calculation process iteration and changes in aerodynamic forces satisfy certain constraint condition, then think and satisfy the condition of convergence based on the CFD/CSD coupling calculating of fluid and structure, fluid and structure coupling analysis process finish, and just can obtain the construction profile under the photocureable rapid shaping model cruising condition.
Step 3, based on the optimizing pneumatic profile of the pneumostatic dynamic elasticity deformation effect of response surface method search photocureable rapid shaping model:
Some shortcomings when (1) being applied to the design of photocureable rapid shaping model optimization for existing response surface method (can have a strong impact on the adaptive faculty of response surface model such as the span of design variable, larger design space will increase the prediction error of response surface, then so that estimate that flow performance is inaccurate, the increase meeting that assesses the cost with the design variable number of response surface method increases fast), according to the numerical grid model parameterization software of fairing Free Transform, set up and optimize the variable shape Optimal Parameters model of computation complexity;
(2) utilize based on the photocureable rapid shaping model of response surface method pneumatic/the structure Coupling Optimization Software, to the photocureable rapid shaping model pneumatic/disturbance in the structure Coupling optimal design feasible zone carries out parametric modeling, obtains designing optimal structural design in the feasible zone by the operation of fairing Free Transform.
Concrete grammar is: photocureable rapid shaping model original shape is carried out pneumatic/structure Coupling and calculate acquisition model convergence profile, grasp the response of node configuration load and malformation, be designated as
, as initial value, bring Optimized Program into, obtain node configuration along different coordinate direction coefficient of indentations
, design parameter is optimized
, formula is as follows:
Photocureable rapid shaping model based on the response surface method is pneumatic/and the structure Coupling Optimization Software obtains the optimum profile of model structure.
Step 4, set up the composite structure form of photocureable rapid shaping model wind tunnel test model, finish design and the processing of model:
(1) according to the model structure profile, finish model structure complex form design, mainly be to finish the aerodynamic configuration structure of photosensitive resin material of descriptive model aerodynamic configuration and the design of model interior metal skeleton structure;
(2) assembling form of finishing between model interior metal skeleton structure and photosensitive resin aerodynamic configuration Standard and model interior metal skeleton structure and force balance designs;
(3) the general design shape of interior metal skeleton structure is comparatively regular, be conducive on the one hand easy to process, save process time, be conducive on the other hand carry out structure analysis, and the analysis data to regular shape are comparatively reliable, therefore adopt traditional machining mode to make, such as common car, mill, brill, line cutting etc.;
(4) the mode shape parts adopt light-curing quick moulding method processing, and its processing model precision is high, and surface quality is good, can make complex-shaped, meticulous part, and efficient is high; Material selection high speed liquid photosensitive resin, can make have high strength, the part of the function such as high temperature resistant, waterproof; In addition, the layout of model and put, manufacturing accuracy that forming direction directly affects profile.Therefore in first being processed, according to the accuracy requirement of model different parts, 3 d structure model is arranged and is put, adds support and cut layer processing, use again light-curing rapid forming equipment and finish processing;
(5) finish model interior metal skeleton structure and photosensitive resin aerodynamic configuration structure processing after, inspection model contoured surface formed precision and quality are finished the assembling of model material object and the check of mould processing quality.
Step 5, photocureable rapid shaping model aerodynamic characteristic wind-tunnel demonstration test:
(1) adopts structure analysis software to finish photocureable rapid shaping mold strength, rigidity check, finish in the simulation laboratory and adopt the ground load mode to finish mold strength and rigidity check;
(2) formulate photocureable rapid shaping model wind tunnel test conceptual design, comprise wind tunnel test condition and project, Data Processing Method, experiment error analysis etc.;
(3) finish the wind-tunnel demonstration test, the analytical test result compares with relevant list of references and all-metal model test findings, feasibility and the correctness of checking Optimization Design.
Claims (2)
1. a photocureable rapid shaping wind tunnel model method for designing of taking into account the static elasticity deformation effect is characterized in that: comprise the steps:
Step 1, set up CFD/CSD Coupled Numerical computation model and the grid of photocureable rapid shaping wind tunnel model:
(1) sets up the three-dimensional structure geometric parameter database of describing photocureable rapid shaping model structure profile, obtain the three-dimensional structure schematic diagram of photocureable rapid shaping model;
(2) the photocureable rapid shaping model surface is carried out discretize, the non-structure triangular mesh of partitioning model object plane, partitioning model inner structure zoning grid is finished the generation of model structure analysis grid model again;
(3) the photocureable rapid shaping model surface is carried out discretize, partitioning model surface structure quadrilateral mesh, extrapolate at the numerical evaluation area of space according to model object plane grid again, divide the fluid zoning and analyze grid, finish the generation that reaches fluid zoning, space grid model in model object plane, the boundary layer;
The pneumostatic dynamic elasticity distortion of the photocureable rapid shaping model elastic construction under step 2, the employing CFD/CSD Coupled Numerical software prediction study condition:
(1) according to the different requirements of structure and fluid calculation, borderline region and the condition of photocureable rapid shaping model structure and fluid calculation is set;
(2) the three dimensions node with all subject coupled interfaces projects on the two-dimensional parameter space plane, carries out aerodynamic loading and the transmission of displacement structure data;
(3) carrying out photocureable rapid shaping MODEL C FD/CSD Coupled Numerical calculates;
(4) adopt the dual-time Push Technology, in real physical time iterative process, call fluid calculation software and obtain photocureable rapid shaping model object plane aerodynamic force load, by the coupling data transmission method aerodynamic loading parameter is transmitted to the structure analysis grid cell, carry out structural stress, deformation analysis, finish a time step fluid and structure Coupling and calculate; Enter into next time step along this time step fluid and structure analysis and carry out iterative computation;
(5) when the model deformation after fluid calculation and the Structure Calculation process iteration and the satisfied constraint condition of setting of changes in aerodynamic forces, then illustrate based on the CFD/CSD coupling calculating of fluid and structure and satisfy the condition of convergence, fluid and structure coupling analysis process finish, and obtain the construction profile under the photocureable rapid shaping model cruising condition;
Step 3, based on the optimizing pneumatic profile of the pneumostatic dynamic elasticity deformation effect of response surface method search photocureable rapid shaping model:
(1) according to the numerical grid model parameterization software of fairing Free Transform, sets up and optimize the variable shape Optimal Parameters model of computation complexity;
(2) utilize based on the photocureable rapid shaping model of response surface method pneumatic/the structure Coupling Optimization Software, to the photocureable rapid shaping model pneumatic/disturbance in the structure Coupling optimal design feasible zone carries out parametric modeling, obtains designing optimal structural design in the feasible zone by the operation of fairing Free Transform;
Step 4, set up the composite structure form of photocureable rapid shaping model wind tunnel test model, finish design and the processing of model;
Step 5, photocureable rapid shaping model aerodynamic characteristic wind-tunnel demonstration test.
2. the photocureable rapid shaping wind tunnel model method for designing of taking into account the static elasticity deformation effect according to claim 1, it is characterized in that: described to the photocureable rapid shaping model pneumatic/method that parametric modeling is carried out in disturbance in the structure Coupling optimal design feasible zone is: photocureable rapid shaping model original shape is carried out pneumatic/structure Coupling and calculates, obtain model convergence profile, obtain the response of node configuration load and malformation, be designated as
, as initial value, bring Optimized Program into, obtain node configuration along different coordinate direction coefficient of indentations
, design parameter is optimized
, formula is as follows:
Utilization based on the photocureable rapid shaping model of response surface method pneumatic/the structure Coupling Optimization Software obtains the optimum profile of model structure.
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| CN110415350A (en) * | 2018-04-27 | 2019-11-05 | 中国航天科工飞航技术研究院（中国航天海鹰机电技术研究院） | A kind of pipeline transportation tool aerodynamic model construction method and system |
| CN108984834A (en) * | 2018-06-08 | 2018-12-11 | 哈尔滨工程大学 | A kind of wing reliability evaluation system and method based on response phase method |
| CN108984834B (en) * | 2018-06-08 | 2022-07-12 | 哈尔滨工程大学 | Wing reliability evaluation system and method based on response surface method |
| CN111177853A (en) * | 2019-12-31 | 2020-05-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Wing type framework design method |
| CN114329315A (en) * | 2022-01-04 | 2022-04-12 | 中国空气动力研究与发展中心计算空气动力研究所 | Static aeroelastic rapid solving method based on dynamic modal decomposition technology |
| CN114329315B (en) * | 2022-01-04 | 2023-03-31 | 中国空气动力研究与发展中心计算空气动力研究所 | Static aeroelastic rapid solving method based on dynamic modal decomposition technology |
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