CN117407974A - Parameterized multi-scale digital twin modeling method for aircraft body - Google Patents
Parameterized multi-scale digital twin modeling method for aircraft body Download PDFInfo
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Abstract
The application belongs to the technical field of aircraft design, and particularly relates to an aircraft body parameterized multi-scale digital twin modeling method. S1, forming a whole-machine body digital twin simulation model capable of expressing macroscopic load transfer differences among different physical single-machine structures; s2, forming a region-refined digital twin simulation model capable of expressing stress and response of the key region; s3, forming a key detail digital twin simulation model capable of expressing the support damage tolerance performance evaluation of the stress concentration area; s4, constructing a damage-containing mesoscopic digital twin simulation model with damage expansion analysis capability; and S5, constructing a data association relation among the level models to form a complete aircraft body parameterized multi-scale digital twin model. According to the method, the digital twin technology is adopted, so that the characteristic parameter change process affecting the flight capacity of the aircraft can be synchronously twin, and the change trend and range of the characteristic parameter can be accurately predicted.
Description
Technical Field
The application belongs to the technical field of aircraft design, and particularly relates to an aircraft body parameterized multi-scale digital twin modeling method.
Background
The Digital Twin (Digital Twin) is to fully utilize data such as a physical model, sensor update, operation history and the like, integrate simulation processes of multiple disciplines, multiple physical quantities, multiple scales and multiple probabilities, and complete mapping in a virtual space, thereby reflecting the whole life cycle process of corresponding entity equipment, realizing the connection fusion of the physical world and the Digital world, and essentially requiring the Digital Twin to have virtual-real mapping capability, dynamic updating capability, scene copying capability, autonomous thinking capability and decision/guidance capability. The digital twin technology is used as one of the most important subversion technologies in the future in the aviation field, the design mode of the traditional aircraft is changed, the lean design level of the aircraft can be remarkably improved in the design stage, the performance lead verification can be performed in the digital domain in advance, the development risk is effectively reduced, and meanwhile, the design period and the cost are shortened; in the use stage, the accurate prediction and fault diagnosis of the performance of the aircraft can be realized, more scientific operation decisions can be assisted, and the safety, stability and economy of the aircraft are improved, so that the method is an essential technology for the design of future aviation aircrafts.
The digital twin of the aircraft body is an important component of the digital twin of the aircraft, is used for simulating and mapping the state of a complex aircraft body structure system in the real use process, and a digital twin model of the aircraft body structure which can be used for accurately describing, diagnosing faults, predicting performance, analyzing trend and assisting decision-making of the aircraft body platform system is urgently needed at present.
Disclosure of Invention
In order to solve the above problems, the present application provides an aircraft body parameterized multi-scale digital twin modeling method, mainly comprising:
s1, selecting parameters or variables which affect the transfer of the overall macrostructure of the aircraft to construct an updating interface of first measured twin data of each physical single-machine structure so as to form a whole-aircraft digital twin simulation model capable of expressing the macroscopical transfer difference between different physical single-machine structures;
s2, for each physical single machine structure, constructing an update interface of second measured twin data according to parameters or variables with influence on stress and response states of a key area designated by a designer, so as to form an area refined digital twin simulation model capable of expressing the stress and response of the key area;
s3, aiming at the stress concentration area of the aircraft body, constructing an update interface of third measured twin data according to parameters or variables of structural damage and multi-field environment of the stress concentration area so as to form a key detail digital twin simulation model capable of expressing the support damage tolerance performance evaluation of the stress concentration area;
s4, applying structural damage to the mesoscopic model of corresponding dimensions according to the type and the size of the damage in the process of aircraft production, manufacturing and use, updating material parameters in the multiscale model based on interface parameters between the mesoscopic model and the multiscale model, and constructing a damage-containing mesoscopic digital twin simulation model with damage expansion analysis capability;
and S5, constructing a data association relation among the level models to form a complete aircraft body parameterized multi-scale digital twin model.
Preferably, in step S1, a homogeneous continuous plate shell and beam model is adopted, and the geometric characteristics of the first-scale physical single-machine structure are constructed by reflecting the influence of the rib secondary structure through the in-plane and bending torsional rigidity equivalence of the homogeneous continuous plate shell and beam model.
Preferably, the first dimension is from 10m to 100m.
Preferably, in step S2, the geometric features of the region structure including the skin, the girders, the tendons, and the openings or layered structures exceeding the set dimensions are constructed in a second scale.
Preferably, the second dimension is 1m-10m.
Preferably, in step S3, the construction of a third scale of detail structure geometric features is included, wherein the detail structure includes tabs, bolts, cracks and layered damage structures.
Preferably, the third dimension is 0.01m-1m.
According to the method and the device, the characteristic parameter change process affecting the flight capacity of the aircraft can be synchronously twinned, and the change trend and range of the characteristic parameter can be accurately predicted, so that the flight capacity of the aircraft can be estimated in real time, the use and maintenance of the aircraft can be guided, and the method and the device have an important role in improving the safety and the use efficiency of the aircraft.
Drawings
FIG. 1 is a flow chart of a parameterized multi-scale digital twin modeling method for an aircraft fuselage of the present application.
FIG. 2 is a schematic diagram of an all-machine digital twin simulation model.
FIG. 3 is a schematic diagram of a region-refined digital twin simulation model.
FIG. 4 is a schematic diagram of a loss-containing mesoscopic digital twin simulation model.
Detailed Description
For the purposes, technical solutions and advantages of the present application, the following describes the technical solutions in the embodiments of the present application in more detail with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, of the embodiments of the present application. The embodiments described below by referring to the drawings are exemplary and intended for the purpose of explaining the present application and are not to be construed as limiting the present application. All other embodiments, which can be made by one of ordinary skill in the art without undue burden from the present disclosure, are within the scope of the present disclosure. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
The application provides an aircraft body parameterized multi-scale digital twin modeling method, which mainly comprises the following steps as shown in fig. 1:
s1, selecting parameters or variables which affect the transfer of the overall macrostructure of the aircraft to construct an updating interface of first measured twin data of each physical single-machine structure so as to form a whole-aircraft digital twin simulation model capable of expressing the macroscopical transfer difference between different physical single-machine structures;
s2, for each physical single machine structure, constructing an update interface of second measured twin data according to parameters or variables with influence on stress and response states of a key area designated by a designer, so as to form an area refined digital twin simulation model capable of expressing the stress and response of the key area;
s3, aiming at the stress concentration area of the aircraft body, constructing an update interface of third measured twin data according to parameters or variables of structural damage and multi-field environment of the stress concentration area so as to form a key detail digital twin simulation model capable of expressing the support damage tolerance performance evaluation of the stress concentration area;
s4, applying structural damage to the mesoscopic model of corresponding dimensions according to the type and the size of the damage in the process of aircraft production, manufacturing and use, updating material parameters in the multiscale model based on interface parameters between the mesoscopic model and the multiscale model, and constructing a damage-containing mesoscopic digital twin simulation model with damage expansion analysis capability;
and S5, constructing a data association relation among the level models to form a complete aircraft body parameterized multi-scale digital twin model.
In step S1, the building of the digital twin simulation model of the whole aircraft body is firstly modeled according to the reference design data of the aircraft structure, and is executed in place according to the corresponding finite element modeling requirement, which mainly aims at accurately expressing the transmission form, route, distribution and the like of the macroscopic structure, so that key parameters or variables affecting the transmission of the overall macroscopic structure are selected, an update interface of the first measured twin data of the physical single structure is built, and the hierarchical simulation model can accurately express macroscopic transmission differences among different physical single structures.
In some alternative embodiments, in step S1, a homogeneous continuous plate shell and beam model is used, and the geometric features of the first-scale physical single-machine structure are constructed by reflecting the influence of the rib secondary structure through the in-plane and bending stiffness equivalent thereof.
In some alternative embodiments, the first dimension is between 10m and 100m.
In the embodiment, taking a civil aircraft as an example, the full-aircraft-level structural model is used for constructing structural geometric features on the scale of 10m-100m, and the static and dynamic responses of the full-aircraft structure can be reflected. As shown in fig. 2, the actual engineering structure 21 may be a stiffened plate, which forms a continuous homogenizing unit 22 through rigidity equivalence, in the continuous homogenizing unit 22, if the unit includes a more important feature structure, such as an opening or a longer crack, it may use unit subdivision to obtain a more accurate equivalent rigidity 24, the continuous homogenizing unit 22 and the more accurate equivalent rigidity 24 together construct a full-machine-level structure model 23, that is, a full-machine-body digital twin simulation model, the constructed full-machine-level structure model 23 may perform global-level structure analysis, so as to obtain an elastic constraint coefficient of the component-level model, or interpolate parameters such as a node load of the component-level model through node force, so as to form a component-level structure model 25 with elastic constraint or node load, in the component-level structure model 25, if structural damage has a greater development, the subdivision of the subunit needs to be updated, and then the more accurate equivalent rigidity 24 is updated.
In step S2, the establishing of the region-refinement digital twin simulation model is based on the overall simulation model, the sub-model or Global-Local form is used to extract the key region therein, the key parameters or variables having influence on the stress and response state of the region structure are selected, and the update interface of the second measured twin data of the physical single machine structure is established, so that the hierarchical simulation model can more accurately express the difference between the Local stress and response of different structure regions than the overall model.
In some alternative embodiments, in step S2, constructing a second scale of geometric features of the area structure including the skin, girders, tendons, and openings or layered structures exceeding the set dimensions is included.
In some alternative embodiments, the second dimension is 1m-10m.
In the embodiment, the region refinement component digital twin model can construct structural geometric features on the scale of 1m-10m, such as skins, girders, ribs, larger openings or layering and the like, and can reflect static and dynamic responses of the structure on the scale. As shown in fig. 3, the critical area in the component-level structure needs to construct superunits 31, for superunits 31, on one hand, the (coarse grid) units in the superunit area can be subdivided according to structural details, the equivalent stiffness of each unit can be obtained through numerical integration, the superunit stiffness matrix 35 is generated by condensing the internal degrees of freedom of the superunits to the boundary degrees of freedom, on the other hand, the node displacement 32 of the superunits can be obtained through component-level analysis, for the node displacement 32, the boundary displacement conditions of the local model (fine grid) can be interpolated according to the parameters of the boundary displacement interpolation function of the minimum strain energy principle, and further the elastic analysis statistical strain energy 33 of the local model can be obtained, the initiation and the expansion 34 of fatigue cracks are simulated through iterative convergence, and the initiation and the expansion 34 of the fatigue cracks can further update the superunit stiffness matrix 35.
In step S3, the establishment of the key detail digital twin model is based on the two-stage models with different scales, and the twin modeling is performed by taking the accurate prediction of the performance of the supporting structure as the target, and the three-dimensional detail model is established for the stress concentration serious area of the aircraft body, and meanwhile, key parameters and variables capable of representing structural damage and multi-field environment are introduced to construct an update interface of third measured twin data, so that the twin model capable of supporting damage tolerance related performance evaluation is established.
In some alternative embodiments, step S3 includes constructing a third scale of detail structure geometric features including tabs, bolts, cracks, and layered damage structures.
In some alternative embodiments, the third dimension is from 0.01m to 1m.
In the embodiment, the key detail level digital twin simulation model constructs structural geometric features on the scale of 0.01m-1m, and can reflect the development process of fatigue cracks (layering).
In step S4, the aircraft generates various damage forms during the production, manufacture and use, and in order to accurately predict the structural strength/rigidity of the aircraft, the damage needs to be truly reflected into the digital twin body, and the damage expansion rule is predicted according to the load form. According to the type and size of the damage, constructing a damage-containing microscopic digital twin simulation model, applying structural damage to the model with corresponding dimensions, and updating material parameters in the multi-scale model to enable the model to have damage expansion analysis capability, wherein the corresponding dimensions refer to millimeter or micrometer. Fatigue crack growth simulation is mainly based on local structural analysis scale. Fatigue crack initiation prediction is based on microscopic (mesoscopic) single-cell scale analysis. Once the fatigue crack is initiated, the local structural analysis model introduces a macroscopic crack by adopting an extended finite element method, and simultaneously updates material parameters in the multi-scale model to enable the model to have the capability of damage extension analysis, as shown in fig. 4, for the local structure 41, hot spot (alternating) stress 42 is obtained through analysis, and a full-period or partial-period (alternating) boundary condition 43 is implemented on the stress 42, so that a microscopic unit cell model 44 or a microscopic unit cell model 45 can be formed, wherein the microscopic unit cell model 44 is aimed at a metal material, and the microscopic unit cell model 45 is aimed at a composite material.
Finally, in step S5, a data association relationship between the hierarchical models is established by adopting a substructure/superunit technology, and then the multi-scale model is fused into a complete model system by taking the data association relationship as a tie. In the step, complex load, environment and damage conditions are considered in the small-scale model, and then the small-scale model is assembled orderly to form the macro-scale model. And establishing a data association relation among the hierarchical models, and fusing the multi-scale models into a complete model system by taking the data association relation as a tie.
In step S5, as shown in fig. 1, the 3d FEM model of the whole machine structure 11 is composed of a plate-shell unit, a beam unit, a homogeneous thick unit with equivalent rigidity, and the like, the crack/damage of which is equivalent to the unit rigidity, the node constraint force spectrum and the node displacement spectrum obtained by analyzing the whole machine structure 11 are applied to the component-level structure 12 as part load spectrums (boundary conditions) of component analysis, and in the component-level structure 12, a superunit is selected to be built at a critical part, and the built FEM model is composed of a plate-shell unit+superunit (local model) containing geometric information such as ribs, holes, and the like, and information such as larger-size cracks or layering. The component-level structure 12 is further analyzed to obtain a node displacement spectrum, a displacement load spectrum of a local analysis is interpolated and applied to the local structure 13, in the local structure 13, a built FEM model of the local structure 13 is composed of a block unit/laminated plate unit and comprises local structure information, crack/damage information and the like, in the local structure 13, if a crack (A) exists, the expansion amount of the metal structure crack 144 and the composite structure damage 135 can be predicted based on macroscopic fatigue fracture damage criteria 141, macroscopic fatigue test data 142, data of expansion limitation and data of the laminated plate model 143 to form predicted data 14, if no crack (B) exists, the local stress spectrum at a local analysis hot spot is used as a microscopic unit cell period boundary condition (load) spectrum and applied to the microscopic unit cell 15, the FEM model of the microscopic unit cell 15 is composed of a block unit and an interface unit and comprises microscopic defect/damage information and is used for carrying out crack/damage germination prediction based on the microscopic crack/damage germination model 16, and the microscopic crack/damage germination model 16 is used for carrying out microscopic initial defect statistics 161, fatigue test statistical fatigue test life statistics and mathematical crack growth theory 163 based on physical test and mathematical analysis.
In the above model, the analysis of the microscopic unit cells 15 is further capable of updating the local model fracture/damage state in the local structure 13, the prediction data 14 is further capable of updating the crack/damage in the local structure 13, and the analysis of the local structure 13 is further capable of updating the superunit stiffness matrix of the component-level structure 12. Meanwhile, the analysis of the component level structure 12 can further update the equivalent stiffness of the whole machine level structure 11, and it should be noted that the analysis of the component level structure 12 includes first performing sub-division on a unit area of the whole machine model, performing numerical integration on the sub-division and accumulating the obtained equivalent stiffness 17 of a homogeneous unit of the whole machine model, and then performing equivalent stiffness update of the whole machine level structure 11 based on the equivalent stiffness 17. In addition, the models of the all-computer-level structure 11 and the part-level structure 12 need to be calculated by numerical transmission based on the probability statistical theory 111 and the load spectrum 112, the all-computer-level structure 11, the part-level structure 12 and the local structure 13 are analyzed on a macroscopic scale (C), the material is regarded as homogeneous, the micro unit cell 15 is analyzed on a microscopic scale (D), and the material is regarded as heterogeneous.
According to the method, the digital twin technology is adopted, the characteristic parameter change process affecting the flight capacity of the aircraft can be synchronously twin, the change trend and range of the characteristic parameter can be accurately predicted, and therefore the flight capacity of the aircraft can be estimated in real time, the use and maintenance of the aircraft can be guided, and the method plays an important role in improving the safety and the use efficiency of the aircraft.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. An aircraft body parameterized multi-scale digital twin modeling method is characterized by comprising the following steps:
s1, selecting parameters or variables which affect the transfer of the overall macrostructure of the aircraft to construct an updating interface of first measured twin data of each physical single-machine structure so as to form a whole-aircraft digital twin simulation model capable of expressing the macroscopical transfer difference between different physical single-machine structures;
s2, for each physical single machine structure, constructing an update interface of second measured twin data according to parameters or variables with influence on stress and response states of a key area designated by a designer, so as to form an area refined digital twin simulation model capable of expressing the stress and response of the key area;
s3, aiming at the stress concentration area of the aircraft body, constructing an update interface of third measured twin data according to parameters or variables of structural damage and multi-field environment of the stress concentration area so as to form a key detail digital twin simulation model capable of expressing the support damage tolerance performance evaluation of the stress concentration area;
s4, applying structural damage to the mesoscopic model of corresponding dimensions according to the type and the size of the damage in the process of aircraft production, manufacturing and use, updating material parameters in the multiscale model based on interface parameters between the mesoscopic model and the multiscale model, and constructing a damage-containing mesoscopic digital twin simulation model with damage expansion analysis capability;
and S5, constructing a data association relation among the level models to form a complete aircraft body parameterized multi-scale digital twin model.
2. The parameterized multi-scale digital twin modeling method of an aircraft body according to claim 1, wherein in step S1, a homogeneous continuous plate shell and beam model is adopted, and the influence of a rib secondary structure is reflected through the in-plane and bending stiffness equivalence thereof, so as to construct the geometric feature of a first-scale physical single-machine structure.
3. The aircraft body parametric multi-scale digital twin modeling method of claim 2, wherein the first scale is 10m-100m.
4. The method of parameterized multi-scale digital twin modeling of an aircraft fuselage of claim 1, comprising constructing a second scale region structure geometry including skins, girders, tendons, and openings or layered structures exceeding a set size in step S2.
5. The aircraft body parametric multi-scale digital twin modeling method of claim 4, wherein the second scale is 1m-10m.
6. The method of parameterized multi-scale digital twin modeling of an aircraft fuselage of claim 1, comprising constructing third-scale detail structure geometric features including tabs, bolts, cracks, and layered damage structures in step S3.
7. The method of parameterized multi-scale digital twin modeling of an aircraft body of claim 6, wherein the third scale is 0.01m-1m.
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