CN103699757B - A kind ofly take into account pneumatic and mini-sized flap wings analytical system and method structure Coupling characteristic - Google Patents

A kind ofly take into account pneumatic and mini-sized flap wings analytical system and method structure Coupling characteristic Download PDF

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CN103699757B
CN103699757B CN201410007193.3A CN201410007193A CN103699757B CN 103699757 B CN103699757 B CN 103699757B CN 201410007193 A CN201410007193 A CN 201410007193A CN 103699757 B CN103699757 B CN 103699757B
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sized flap
flap wings
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aerodynamic
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CN103699757A (en
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杨文青
王利光
王进
付鹏
宋笔锋
宋文萍
李洋
薛栋
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Northwestern Polytechnical University
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Abstract

The present invention proposes a kind of take into account pneumatic and mini-sized flap wings analytical system and method structure Coupling characteristic, comprise main control computer, server, Structural Static step response test macro, Structure dynamic characteristics test macro, aerodynamic response analytical system, structural response analysis system, coupling response analytical system, be connected to become unified entirety by fibre system. Main control computer is connected with server with structure static state, dynamic characteristic test equipment respectively, server connects also control structure, pneumatic, coupling response analytical system, three each specialty analysis instruments of the each self-operating of responding system, the most at last analysis result return service device output feedback. The present invention has solved mini-sized flap wings design and pneumatic and the comprehensive analysis of structure Coupling characteristic and the data exchange difficulty of two subjects effectively, comprehensive analysis and the automatic synchronization operation of the challenge that relates to pneumatic and two subjects of structure are realized, shorten the design cycle of mini-sized flap wings, improved design efficiency.

Description

A kind ofly take into account pneumatic and mini-sized flap wings analytical system and method structure Coupling characteristic
Technical field
The present invention relates to Aircraft Conceptual Design technology, specifically a kind ofly take into account pneumatic and the miniature of structure Coupling characteristic and flutterWing analytical system and method.
Background technology
Flapping wing aircraft is to imitate birds and the insect bionic Aircraft that wing flies of flapping, with conventional aircraft notRely on the cycle movement of flapping wing to produce completely with fly required lift and thrust of, flapping wing aircraft, flapping wing pneumaticPerformance just becomes the key factor that affects aircraft performance. Research shows to have Reasonable Rigidity and distribute and plastic deformationThe aeroperformance of the Computation of Flexible Flapping-Wing of ability is significantly better than rigidity flapping wing, is the main direction of current flapping wing aircraft development.In the reciprocating process of flapping wing, be subject to the acting in conjunction of aerodynamic loading and inertial load, Computation of Flexible Flapping-Wing can be passivelyChange profile, amplitude of deformation is fairly obvious on the impact of aeroperformance. Therefore, the process of fluttering of Computation of Flexible Flapping-Wing is carried outAeroperformance analysis just must be considered pneumatic structure coupled problem, solves aerodynamic force in the situation that taking into account malformation.
Existing pneumatic structure coupling analysis mainly for be Flutter Problem, consider structure under deformation, be subject to by a small marginProduce the process of self-excited vibration to aerodynamic loading. Main have following two kinds of modes: the first, and constant during based on microvariationsSuppose, solve respectively malformation and aerodynamic force, and do not consider Dynamic Coupling impact between the two; The second, to gasMoving N-S equation and structure finite element equation carry out iteration numerical solution, and the construction profile in an above moment is as lower a period of timeCarve the geometric shape that solves of aerodynamic force, then using the aerodynamic force that obtains as the load that solves next moment malformation, thisThe processing method of kind method based on simplification and assumption, has reflected pneumatic and reciprocation structure to a certain extent, but pneumaticLong with the cycle of structure iterative, convergence cannot ensure, inappropriate model hypothesis may cause numerical solution knotFruit is not inconsistent with actual conditions. Said method has obvious limitation for the pneumatic structure coupled problem that solves Computation of Flexible Flapping-Wing:There is significantly periodically deforming in the Computation of Flexible Flapping-Wing process of fluttering, constant hypothesis while no longer meeting microvariations, must fully examineConsider the coupling of pneumatic structure; The flapping wing size of imitating birds and insect is little, and the anisotropic character of structure is obvious,Accurately obtain architectural characteristic and be used in solution procedure and just become a difficult problem.
And Computation of Flexible Flapping-Wing belongs to significantly forced movement, different from the self-excited vibration of flutter, its surperficial local speed is by flutterringMoving speed and deformation velocity determine jointly. This problem and classical gas bullet problem have remarkable difference, miniature in order to studyWhen flapping flight, true effect and the effect of pneumatic and structure Coupling, must divide for the inherent characteristics of Computation of Flexible Flapping-WingAnalyse, carry out pneumatic and two interdisciplinary complete Coupling Research of structure, setting up one can automatic synchronization comprehensive analysisHolonomic system.
Summary of the invention
The technical problem solving
Cannot take into full account the coupling of Computation of Flexible Flapping-Wing pneumatic structure in order to overcome in prior art, solve poor astringency,The deficiency that precision is low, the present invention proposes a kind of take into account pneumatic and mini-sized flap wings analytical system and side structure Coupling characteristicMethod, for analyzing the Computation of Flexible Flapping-Wing being made up of the coated flexible covering of flexible back bone.
Technical scheme
Technical scheme of the present invention is:
Described a kind of pneumatic and mini-sized flap wings analytical system structure Coupling characteristic taken into account, is characterized in that: by main control computer,Server, Structural Static step response test macro, Structure dynamic characteristics test macro, aerodynamic response analytical system, structureResponse analysis system and Coupling Characteristics system composition; Structural Static step response test macro collection composition mini-sized flap wingsThe elastic modelling quantity of each material and Poisson's ratio, Structure dynamic characteristics test macro gathers the intrinsic frequency of mini-sized flap wings and shakesType; Main control computer is sent the collection result of Structural Static step response test macro and Structure dynamic characteristics test macro into serviceDevice; Shape data, state of flight after motion mode or the distortion of server transmission mini-sized flap wings arrive aerodynamic response analysisSystem, aerodynamic response analytical system is set up three-dimensional space grid according to time propelling course, calculates mini-sized flap wings motionAerodynamic characteristic in process, by result of calculation return service device; Server sends motion mode, the profile of mini-sized flap wingsData, the gentle dynamic load(loading) course of material properties are to structural response analysis system, and structural response analysis system is by outer figurate numberAccording to geometrical model, the partition structure dynamics grid of setting up mini-sized flap wings, moving according to aerodynamic force load history analytical structureState response process, calculates mini-sized flap wings malformation result, by result of calculation return service device; Server sends miniatureAerodynamic characteristic in flapping wing motion process or mini-sized flap wings malformation result are to Coupling Characteristics system, coupled characteristicAerodynamic characteristic in analysis system processes mini-sized flap wings motion process and generate the aerodynamic force load for structural response analysisCourse, Coupling Characteristics system is processed mini-sized flap wings malformation result and is generated the distortion of analyzing for aerodynamic responseDisplacement data, and calculate the error of the adjacent twice malformation result of mini-sized flap wings, the calculating of Coupling Characteristics systemResult return service device; Whether server restrains according to the error judgment analytic process of adjacent twice malformation result,Select to continue to analyze or Output rusults according to convergence.
Described a kind of pneumatic and mini-sized flap wings analytical method structure Coupling characteristic of taking into account, is characterized in that: below employingStep:
Step 1: measure elastic modelling quantity and the Poisson's ratio of each material of composition mini-sized flap wings, measure consolidating of mini-sized flap wingsThere are frequency and the vibration shape;
Step 2: according to profile, state of flight after the motion mode of mini-sized flap wings or distortion, advance and go through according to the timeCheng Jianli three-dimensional space grid, calculates the aerodynamic data in mini-sized flap wings motion process;
Step 3: the aerodynamic data in the mini-sized flap wings motion process obtaining according to step 2, transmit by dataTo the force transmission matrix on different densities grid, the power on mini-sized flap wings aerodynamic grid node is transferred to Structure NetworkOn lattice node, obtain the aerodynamic force load history for structural response analysis;
Step 4: what obtain according to the motion mode of mini-sized flap wings, shape data, material properties and step 3 is pneumaticPower load history, sets up the geometrical model, partition structure dynamics grid of mini-sized flap wings, advances course mould according to the timeIntend the structure dynamic response process of mini-sized flap wings, calculate mini-sized flap wings malformation result;
Step 5: the mini-sized flap wings malformation result obtaining according to step 4, obtains different densities by data transmissionDisplacement transfer matrix on grid, is delivered to the displacement on mini-sized flap wings structured grid node on aerodynamic grid node,Obtain the deformation displacement data of analyzing for aerodynamic response;
Step 6: repeating step 2~step 5, the error of the adjacent twice malformation result of calculating mini-sized flap wings, judgementWhether analytic process restrains, if convergence, Output rusults, continues repeating step 2~step 5 if do not restrain.
Described a kind of pneumatic and mini-sized flap wings analytical method structure Coupling characteristic of taking into account, is characterized in that: in step 2,Generate mini-sized flap wings surface mesh according to the profile after the motion mode of mini-sized flap wings or distortion, then by based on unlimited interpolationThe grid generation method three-dimensional CO type structural topology structure that obtains solving for Viscous Flow, by solving pretreatmentAfter three-dimensional non-steady averaged Navier-Stokes equation obtain the aerodynamic data in mini-sized flap wings motion process.
Described a kind of pneumatic and mini-sized flap wings analytical method structure Coupling characteristic of taking into account, is characterized in that: in step 4,Set up geometrical model according to the motion mode of mini-sized flap wings and shape data, and in geometrical model, define material properties withCross section property, then partition structure dynamics grid, carries out variation based on Hamiton's principle to kinetic energy and strain energy,To the dynamics equations of mini-sized flap wings, utilize Newmarket method to carry out discrete solving to dynamics equations,Obtain mini-sized flap wings Structure dynamic characteristics under external force, obtain mini-sized flap wings malformation result.
Described a kind of pneumatic and mini-sized flap wings analytical method structure Coupling characteristic taken into account, is characterized in that: step 3 andIn step 5, realize data transmission by RBF, obtain force transmission matrix and position on different densities gridMove transfer matrix.
Beneficial effect
Compared with the existing technology, the present invention takes full advantage of the reciprocating feature of flapping wing, for the cycle of repeatedly reappearingProperty feature is carried out iterative approach, has ensured numerical value existence of solution, has reduced iterations, has improved solution efficiency.Use the method for experiment measuring to obtain flexible structure anisotropic architectural characteristic, carry out pneumatic structure iterative itFront elder generation, according to measurement result iteration correcting principle FEM model, has effectively improved in pneumatic structure iterative process and has tiedStructure is out of shape the precision of calculating, and has also just improved the precision of final acquisition aerodynamic characteristic. Native system is applicable to analyzing mini-sized flap wingsThe interaction process of aerodynamic force and distortion under truth, utilizes this invention in the mini-sized flap wings design phase, can designGo out not only to meet aeroperformance weight but also light structure simultaneously, the definite of mini-sized flap wings General layout Plan played wellReference role, thus the design cycle shortened, improve design efficiency.
Brief description of the drawings
Accompanying drawing 1 is to take into account pneumatic and mini-sized flap wings analytical system hardware composition frame chart structure Coupling characteristic.
Wherein, 1 is main control computer, and 2 is server, and 3 is Structural Static step response test macro, and 4 is Structure dynamic characteristicsTest macro, 5 is aerodynamic response analytical system, and 6 is structural response analysis system, and 7 is Coupling Characteristics system.
Accompanying drawing 2 is Structural Static step response test system hardware composition schematic diagrames. Wherein, 31 is measuring object, and 32 is folderHold device, 33 is loading equipemtn, and 34 is non-contact type strain measurement instrument, and 35 is stabilizing base.
Accompanying drawing 3 is Structure dynamic characteristics test system hardware composition schematic diagrames. Wherein, 41 is measuring object, and 42 is folderHold device, 43 is exciting force hammer, and 44 is laser displacement sensor.
Accompanying drawing 4 is operation module composition and operational flow diagram of aerodynamic response analytical system.
Accompanying drawing 5 is operation module composition and operational flow diagram of structural response analysis system.
Accompanying drawing 6 is operation module composition and operational flow diagram of Coupling Characteristics system.
Detailed description of the invention
Below in conjunction with specific embodiment, the present invention is described:
With reference to accompanying drawing 1, the mini-sized flap wings analytical system of taking into account pneumatic and structure Coupling characteristic in the present embodiment is by master controlMachine, server, Structural Static step response test macro, Structure dynamic characteristics test macro, aerodynamic response analytical system,Structural response analysis system and Coupling Characteristics system composition; Between hardware device, connect by 100,000,000 optical fiber. When execution,First given an order by main control computer, control structure static characteristic test macro (3), measures the static structure spy of mini-sized flap wingsProperty, specifically describe as shown in Figure 2. Secondly, main control computer control structure dynamical property test system (4), measures as miniatureThe dynamic structure characteristic of flapping wing, specifically describes as shown in Figure 3. Obtain, after the Static and dynamic characteristic of structure, sending the data toServer. That server calls is respectively pneumatic, structure, coupling response analytical system, specifically describes as shown in Figs. 4-6. PneumaticResponse analysis network analysis miniature flexible flapping wing low speed, low reynolds number, time-dependent aerodynamic characteristic. Structural response analysis system is dividedThe structural dynamic characteristics becoming while analysing the large deformation of miniature flexible flapping wing, anisotropic. Coupling response analytical system is set up pneumatic and is dividedData passing interface between analysing, and carry out the convergence calculating of coupling analysis. After convergence to be analyzed, by server Output rusultsTo specific file, common user analysis. Be described in detail item by item design and the implementation of modules below.
As shown in Figure 2, Structural Static step response test macro mainly comprises measuring object (31), forms mini-sized flap wingsMaterial sample, the present embodiment is carbon fiber bar composite rib and polyester film covering, and experimental facilities, this realityThe experimental facilities of executing in example adopts tiny sample architectural characteristic measuring instrument---the IST all-electronin of American I nstron companyTesting machine. Material sample two ends are separately fixed in clamping device (32), are loaded by loading equipemtn (33),Last until destroy. Stress is controlled by loading equipemtn, and strain is obtained by non-contact type strain measurement instrument (35).In measuring process, keep the steadiness of stabilizing base (35), finally measure the elasticity of mini-sized flap wings composition materialModulus and Poisson's ratio. So far structure static response analysis process finishes.
As shown in Figure 3, Structure dynamic characteristics test macro mainly comprises measuring object (41), i.e. mini-sized flap wings model,And experimental facilities, the experimental facilities in the present embodiment adopts the SCADAS data collecting system of Belgian LMS company.Mini-sized flap wings model one end is fixed in clamping device (42), and one end is unsettled, hammers (43) into shape specific by exciting forceNode applies pulse excitation, is measured the displacement response of specific node by laser displacement sensor (44), thereby analyzeTo the dynamic structure characteristic of mini-sized flap wings model, comprise intrinsic frequency and the vibration shape. So far structure dynamic response analytic processFinish.
Server receives after the instruction of main control computer, sets up analysis state. According to the structure Static and dynamic spy who receivesProperty data, server according to pneumatic-> coupling-> structure-> coupling--> pneumatic-> coupling-> structure-> coupling--> ... order constantly send instruction and analyze, and receiving and analyzing return data, divides until receive coupling responseAfter the judgement of analysis system analysis convergence, analyze and finish, by analysis result writing in files, for user.
First server sends instruction and parameter to aerodynamic response analytical system, comprises motion mode or the change of mini-sized flap wingsProfile after shape, state of flight. Aerodynamic response analytical system receives after the instruction of server, starts to carry out pneumatic spyProperty analyze, advance course Time Created, if first calculate, at each time step according to default motion modeGenerate mini-sized flap wings surface mesh, calculate first if non-, generate current time according to the profile after malformationMini-sized flap wings surface mesh, then the three-dimensional that is obtained solving for Viscous Flow by the grid generation method based on unlimited interpolationCO type structural topology structure, grid external boundary shape invariance, grid density along with the wing slightly flutter position and in real time adjustWhole, obtain mini-sized flap wings and moved by solving pretreated three-dimensional non-steady averaged Navier-Stokes equationAerodynamic data in journey, is advanced to the calculating of next time step. When result of calculation reaches after convergence, by aerodynamic characteristicResult return service device, comprises state of flight, the motion mode of mini-sized flap wings and the aerodynamic force producing in-flight. ItsIn " pretreated three-dimensional non-steady averaged Navier-Stokes equation " visible bibliography of method for solving: Korea SproLoyal China, Qiao Zhide, Xiong Juntao, what light flood .Navier-Stokes equation preprocess method and to profile flow Numerical-ModeThe application [J] of intending. Northwestern Polytechnical University's journal, 2006,24 (3): 275-280; And " grid based on unlimited interpolation generatesThe three-dimensional CO type structural topology structure that method obtains solving for Viscous Flow " the visible bibliography of process: Xie Hui, SongWen Ping, Song Bifeng. the N-S equation numerical simulation [J] that mini-sized flap wings streams. the journal .Vol.26 of Northwestern Polytechnical University,No.1,2008,pp.104-109.
Flow chart has been shown in the present embodiment as shown in Figure 4, the specific design flow process of aerodynamic response analytical system, firstExecution step 51, from server receive the motion mode of mini-sized flap wings, the process of fluttering distortion after profile, flyThe parameters such as row state. Secondly creation-time course, was initially for 0 moment, execution step 52. Carry out according to model parameterStep 53, according to the flapping wing surface mesh of the profile generation current time after malformation. Due to aerodynamic surface grid phaseMuch larger for structure node number density, the present embodiment adopts the method for again layouting after spline interpolation to generate pneumaticSurface mesh. The method both can ensure the accurate transmission of areal deformation, can ensure again the smooth continuous of aerodynamic surfaceProperty. Perform step afterwards 54, generate the flapping wing space lattice of current time. The mesh space topological structure of the present embodimentFor three-dimensional CO type, obtained by the grid generation method based on unlimited interpolation. Perform step afterwards 55, solve when currentThe aerodynamic characteristic of carving. The present embodiment has solved pretreated three-dimensional averaged Navier-Stokes equation, and adoptsMultiple grid method accelerating ated test, in calculating, can use respectively three kinds of turbulence models, be respectively BL, SA and SST,There is the adaptability of computational analysis Various Complex state of flight. Calculating finishes rear execution determining step 56, calculates and does not restrainTime, be advanced to next time step, perform step 57. After this repeated execution of steps 53 to 55, until analyze convergenceAfter, execution step 58, by aerodynamic characteristic return service device.
Server, according to receiving after the data of aerodynamic response analytical system, sends instruction and parameter to coupling response analysisSystem, comprises the aerodynamic force of motion mode, state of flight and the generation of mini-sized flap wings. Coupling response analytical system will connectThe aerodynamic data of receiving is processed, and generates the aerodynamic force load history loading for structure, return service device.
Server, from coupling response analytical system receives structure function force data, sends instruction and parameter and rings to structureAnswer analytical system, comprise motion mode, shape data, material properties, the aerodynamic force load history of mini-sized flap wings. KnotStructure response analysis system receives after the instruction of server, starts to carry out structural dynamic characteristics analysis, comprises according to micro-Motion mode and the shape data of type flapping wing are set up geometrical model, and in geometrical model, define material properties and cross section spyProperty, then partition structure dynamics grid, carries out variation based on Hamiton's principle to kinetic energy and strain energy, obtains miniatureThe dynamics equations of flapping wing, utilizes Newmarket method to carry out discrete solving to dynamics equations, obtainsMini-sized flap wings Structure dynamic characteristics under external force, obtains mini-sized flap wings malformation result. Structural response analysisAfter system end of run, by architectural characteristic data return service device, comprise mini-sized flap wings motion mode, architectural characteristic,Deformation process after stressed. The process of wherein " based on Hamiton's principle, kinetic energy and strain energy being carried out to the variation " literary composition that sees referenceOffer: E.T.Whittaker, Atreatiseontheanalyticaldynamicsofparticlesandrigidbodie s, 4thEd., CambridgeUniv.Press, Cambridge, 1952. and bibliography Qian Weichang, the calculus of variations and finite element,The first volume, Science Press, Beijing, 1980; Document: the Newmark and Newmarket procedure sees reference, N.M.AMethodofComputationforStructuralDynamics[J].JournalofEngineeringMechanics.ASCE,1959.85(3):249-260.
Flow chart has been shown in the present embodiment as shown in Figure 5, the specific design flow process of structural response analysis system, firstExecution step 61, the profile, material properties, motion mode, the aerodynamic force load that receive mini-sized flap wings from server are gone throughThe data such as journey. Secondly execution step 62, sets up geometrical model according to profile. Carry out successively afterwards the following step: definitionMaterial properties and cross section property, i.e. step 63; Assembly system grid division, step 64; Create external force load history,Step 65; Analyze dynamic response process, step 66. Finally, execution step 67, returns to modal displacement characteristic to clothesBusiness device.
Server receives after the data of structural response analysis system, sends instruction and parameter to coupling response analytical system,Comprise the motion mode, architectural characteristic of mini-sized flap wings, deformation process after stressed. Coupling response analytical system will receiveTo malformation data process, generate the displacement data for aerodynamic surface distortion, and calculate adjacent twice knotThe modal displacement error that structure analysis obtains, for convergence test, by result return service device.
Flow chart has been shown in the present embodiment as shown in Figure 6, the specific design flow process of coupling response analytical system, firstExecution step 71, receives and calls the calculated data that last module obtains from server. Carry out determining step 72, if connectReceive Pneumatic Calculation data, perform step 73 and 74, generate the active force for structural analysis according to aerodynamic dataData. Be not Pneumatic Calculation data if received, what show to receive is Structure Calculation data, i.e. execution step75 to 77, generate the deformation data for aerodynamic analysis according to structured data, and calculate the distortion inaccuracy of adjacent twice.Finally perform step 78, will transmit data return service device.
In coupling response analytical system, the present embodiment adopts RBF to realize data transmission, obtains different densitiesForce transmission matrix on grid and displacement transfer matrix, ensured power and knot on mini-sized flap wings aerodynamic grid nodePower on structure grid node is done work equal: Fa TUa=Fs TUs, wherein: FsFor structured grid nodal force; FaFor gasDynamic mesh nodal force; UaFor aerodynamic grid modal displacement; UsFor structured grid modal displacement. The power of pneumatic structure nodeTransfer on structure structure node: Fs=[G]TFa, the Displacement transfer of structure structure node is to pneumatic structure node:Ua=[G]Us, [G] is displacement transfer matrix.
Server is from coupling response analytical system receives malformation process data, and whether discriminatory analysis process restrains:If do not restrained, repeat to analyze running. If convergence, Output rusults is to file.
The present invention has solved mini-sized flap wings design and pneumatic and comprehensive analysis and two subjects structure Coupling characteristic effectivelyData exchange difficulty, realized comprehensive analysis and the automatic synchronization of the challenge that relates to pneumatic and two subjects of structureMove, shortened the design cycle of mini-sized flap wings, improved design efficiency.

Claims (5)

1. take into account pneumatic and mini-sized flap wings analytical system structure Coupling characteristic, it is characterized in that: formed by main control computer, server, Structural Static step response test macro, Structure dynamic characteristics test macro, aerodynamic response analytical system, structural response analysis system and Coupling Characteristics system; Elastic modelling quantity and the Poisson's ratio of each material of Structural Static step response test macro collection composition mini-sized flap wings, Structure dynamic characteristics test macro gathers intrinsic frequency and the vibration shape of mini-sized flap wings; Main control computer is sent the collection result of Structural Static step response test macro and Structure dynamic characteristics test macro into server; Shape data, state of flight after motion mode or the distortion of server transmission mini-sized flap wings arrive aerodynamic response analytical system, aerodynamic response analytical system is set up three-dimensional space grid according to time propelling course, calculate the aerodynamic characteristic in mini-sized flap wings motion process, by result of calculation return service device; Server sends the gentle dynamic load(loading) course of motion mode, shape data, material properties of mini-sized flap wings to structural response analysis system, structural response analysis system by motion mode and the shape data of mini-sized flap wings set up the geometrical model of mini-sized flap wings, in geometrical model, define material properties and cross section property, partition structure dynamics grid, according to aerodynamic force load history analytical structure dynamic response process, calculate mini-sized flap wings malformation result, by result of calculation return service device; Aerodynamic characteristic or mini-sized flap wings malformation result that server sends in mini-sized flap wings motion process arrive Coupling Characteristics system, Coupling Characteristics system is processed the aerodynamic characteristic in mini-sized flap wings motion process and is generated the aerodynamic force load history for structural response analysis, Coupling Characteristics system is processed mini-sized flap wings malformation result and is generated the deformation displacement data of analyzing for aerodynamic response, and calculate the error of the adjacent twice malformation result of mini-sized flap wings, the result of calculation return service device of Coupling Characteristics system; Whether server restrains according to the error judgment analytic process of adjacent twice malformation result, selects to continue to analyze or Output rusults according to convergence; Server receives after the instruction of main control computer, sets up analysis state; According to the structure static state and the dynamic Characteristic Data that receive, server constantly sends instruction according to the order of pneumatic, coupling, structure, coupling, pneumatic, coupling, structure, coupling and analyzes, and receiving and analyzing return data, until receive after the judgement of coupling response analytical system analysis convergence, analyze and finish, by analysis result writing in files, for user.
2. utilize mini-sized flap wings analytical system described in claim 1 to take into account pneumatic and mini-sized flap wings analytical method structure Coupling characteristic, it is characterized in that: adopt following steps:
Step 1: measure elastic modelling quantity and the Poisson's ratio of each material of composition mini-sized flap wings, measure intrinsic frequency and the vibration shape of mini-sized flap wings;
Step 2: according to profile, state of flight after the motion mode of mini-sized flap wings or distortion, set up three-dimensional space grid according to time propelling course, calculate the aerodynamic data in mini-sized flap wings motion process;
Step 3: the aerodynamic data in the mini-sized flap wings motion process obtaining according to step 2, obtain the force transmission matrix on different densities grid by data transmission, power on mini-sized flap wings aerodynamic grid node is transferred on structured grid node, obtained the aerodynamic force load history for structural response analysis;
Step 4: the aerodynamic force load history obtaining according to the motion mode of mini-sized flap wings, shape data, material properties and step 3, set up the geometrical model, partition structure dynamics grid of mini-sized flap wings, according to the structure dynamic response process of time propelling course simulation mini-sized flap wings, calculate mini-sized flap wings malformation result;
Step 5: the mini-sized flap wings malformation result obtaining according to step 4, obtain the displacement transfer matrix on different densities grid by data transmission, displacement on mini-sized flap wings structured grid node is delivered on aerodynamic grid node, obtains the deformation displacement data of analyzing for aerodynamic response;
Step 6: repeating step 2~step 5, the error of the adjacent twice malformation result of calculating mini-sized flap wings, whether discriminatory analysis process restrains, if convergence, Output rusults, continues repeating step 2~step 5 if do not restrain.
3. a kind ofly according to claim 2 take into account pneumatic and mini-sized flap wings analytical method structure Coupling characteristic, it is characterized in that: in step 2, if calculate first, generate mini-sized flap wings surface mesh at each time step according to default motion mode, calculate first if non-, generate the mini-sized flap wings surface mesh of current time according to the profile after malformation, the three-dimensional CO type structural topology structure that is obtained solving for Viscous Flow by the grid generation method based on unlimited interpolation again, grid external boundary shape invariance, grid density along with the wing slightly flutter position and in real time adjust, obtain the aerodynamic data in mini-sized flap wings motion process by solving pretreated three-dimensional non-steady averaged Navier-Stokes equation.
4. take into account pneumatic and mini-sized flap wings analytical method structure Coupling characteristic according to a kind of described in claim 2 or 3, it is characterized in that: in step 4, set up geometrical model according to the motion mode of mini-sized flap wings and shape data, and in geometrical model, define material properties and cross section property, then partition structure dynamics grid, based on Hamiton's principle, kinetic energy and strain energy are carried out to variation, obtain the dynamics equations of mini-sized flap wings, utilize Newmarket method to carry out discrete solving to dynamics equations, obtain mini-sized flap wings Structure dynamic characteristics under external force, obtain mini-sized flap wings malformation result.
5. a kind ofly according to claim 4 take into account pneumatic and mini-sized flap wings analytical method structure Coupling characteristic, it is characterized in that: in step 3 and step 5, realize data transmission by RBF, obtain force transmission matrix and displacement transfer matrix on different densities grid.
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