CN105335582A - Modeling method for airplane composite material wall plate weight analysis - Google Patents
Modeling method for airplane composite material wall plate weight analysis Download PDFInfo
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Abstract
The invention discloses a modeling method for airplane composite material wall plate weight analysis and relates to the airplane weight research direction in the airplane overall design technical field. The modeling method is used for weight control in the airplane composite material structural component production process and includes the steps that S1, structural parameters are defined and comprise parameters of panels and ribs; S2, a composite material wall plate structure finite element model is constructed; S3, loads and boundary constraint of the composite material wall plate structure finite element model are defined; S4, the structural strength and the rigidity of the composite material wall plate structure finite element model are analyzed; S5, structural stability is analyzed; S6, a laying layer of a composite material structure is optimized; S7, the composite material wall plate structure weight is calculated. According to the modeling method for airplane composite material wall plate weight analysis, finite element modeling is fast and accurately performed on an anti-axial-compression composite material wall plate structure at the early stage of airplane design, and therefore the weight, the gravity center and the rotating inertia of the anti-axial-compression composite material wall plate structure can be accurately and fast calculated through numerical simulation.
Description
Technical field
The present invention relates to the aircraft weight research direction in preliminary design of aircraft technical field, in particular to the multiple material wallboard gravimetric analysis modeling method of a kind of aircraft.
Background technology
Need to estimate the mass property of overall aircraft and each sub-component in Aircraft Concept Design stage and concept phase.Aircraft Quality characteristic estimation is had to the purposes of two aspects: one be aircraft weight, center of gravity, moment of inertia as the basic input parameters flying control, performance, behaviour surely analyze, decide the security of aircraft, maneuverability, stability; Two is that the multi-scheme assessment carried out for the airplane design type selecting stage provides reference frame.
The mass property estimation accurately of Aircraft Conceptual Design stage is prerequisite and the basis of aircraft weight control, is also alleviate airplane design weight most critical, the most effective stage.Experience shows, more than 80% of all losss of weight of aircraft were implemented in this stage.And in the follow-up phase of airplane design, the limitation of loss of weight measure and the raising of loss of weight cost, be difficult to the weight loss effect reaching expection.Therefore, advanced Aircraft Quality characteristic estimation method research must be launched.
At present the conceptual level of airplane design calculate the multiple material wall panel structure weight of anti-axial compression conventional have following two kinds of methods: weight coefficient method, statistical analysis method.Wherein weight coefficient method and statistical analysis method can only be used for and former accurate machine or the little airplane design of statistical sample difference, and error is larger.
The technical matters needing now solution badly how to design the multiple material wallboard gravimetric analysis modeling method of a kind of aircraft, to overcome the defect existed in prior art.
Summary of the invention
The object of the invention is to solve above-mentioned deficiency of the prior art, provide a kind of aircraft of advantages of simple multiple material wallboard gravimetric analysis modeling method.
Technical scheme provided by the invention solves classic method in the airplane design initial stage antagonism axial compression problem that material wallboard weight estimation error is larger again.A kind of modeling method can assessing the multiple material wallboard weight of resistance of airplane axial compression is accurately and fast provided, and successful Application in the development of aircraft.
Object of the present invention is achieved through the following technical solutions: the multiple material wallboard gravimetric analysis modeling method of a kind of aircraft, the mass property for the airplane design stage is estimated, adopts finite element method, comprises the steps:
S1, definition structure parameter, aforementioned structure parameter comprises panel and rib;
S2, builds multiple material wall panel structure finite element model;
S3, to finite element model definition load and the boundary constraint of multiple material wall panel structure;
S4, multiple material wall panel structure finite element model structural static strength, stiffness analysis;
S5, structural stability analysis;
S6, the laying optimization of composite structure;
S7, multiple material wall panel structure Weight computation.
, in S1, the panel in structural parameters comprises plate thickness, panel material and panel finite element unit numbering in such scheme preferably; Rib in structural parameters comprises rib initial sum and stops layout points, the shape of edge strip up and down of rib and area, the thickness of rib web, the material of rib and rib finite element unit are numbered, whether rib is reinforcement judgement.
In above-mentioned either a program preferably, the multiple material wall panel structure finite element model in S2 comprises geometric parameter, material mechanical performance, density, load, edge-restraint condition, the composite plys order of multiple material wall panel structure.
In above-mentioned either a program preferably, in S3, the finite element model definition load of multiple material wall panel structure and the foundation of boundary constraint way choice are comprised to structure stand under load and the type of attachment of multiple material wallboard.
In above-mentioned either a program preferably, in S4, the foundation of multiple material wall panel structure finite element model structural static strength, stiffness analysis is multiple material wall panel structure finite element model load profile data, edge-restraint condition, geometrical parameters.
In above-mentioned either a program preferably, in S6, the mode according to multiple material wallboard carrying carries out simulation optimization analysis to the laying of composite structure, and the laying simulation optimization analysis of composite structure comprises wing flapping degree, thickness.
In above-mentioned either a program preferably, in S7, the mode of multiple material wall panel structure Weight computation is volume density computing method.
The beneficial effect of the multiple material wallboard gravimetric analysis modeling method of aircraft provided by the present invention is, resist the multiple material wall panel structure of axial compression fast and accurately at the airplane design initial stage and carry out finite element modeling, and then can numerical simulation be passed through, calculate the weight of the multiple material wall panel structure of anti-axial compression, center of gravity and moment of inertia accurately and fast, solve traditional means at one stroke and can only estimate roughly the multiple material wallboard weight of the anti-axial compression of assessment.
Accompanying drawing explanation
Fig. 1 is the schematic flow sheet of the preferred embodiment according to the multiple material wallboard gravimetric analysis modeling method of aircraft of the present invention;
Fig. 2 is the schematic flow sheet according to structural static strength, degree stiffness analysis in the multiple material wallboard gravimetric analysis modeling method S4 embodiment illustrated in fig. 1 of aircraft of the present invention;
Fig. 3 is the schematic flow sheet according to structural stability analysis in the multiple material wallboard gravimetric analysis modeling method S5 embodiment illustrated in fig. 1 of aircraft of the present invention;
Fig. 4 is the schematic flow sheet optimized according to the laying of composite structure in the multiple material wallboard gravimetric analysis modeling method S6 embodiment illustrated in fig. 1 of aircraft of the present invention.
Embodiment
In order to understand according to the multiple material wallboard gravimetric analysis modeling method of the aircraft of the present invention program better, be further elaborated explanation below in conjunction with the preferred embodiment of accompanying drawing to the multiple material wallboard gravimetric analysis modeling method of aircraft of the present invention.
As Figure 1-4, the multiple material wallboard gravimetric analysis modeling method of aircraft provided by the invention, for the Weight control in Aircraft Composite Structure part production run, comprises the steps:
S1, definition structure parameter, described structural parameters comprise panel and rib;
S2, builds multiple material wall panel structure finite element model;
S3, to finite element model definition load and the boundary constraint of multiple material wall panel structure;
S4, multiple material wall panel structure finite element model structural static strength, stiffness analysis;
S5, structural stability analysis;
S6, the laying optimization of composite structure;
S7, multiple material wall panel structure Weight computation.
In the multiple material wallboard gravimetric analysis modeling method S1-S7 of the aircraft that the invention described above provides, the panel in S1 structural parameters comprises plate thickness, panel material and panel finite element unit numbering; Rib in structural parameters comprises rib initial sum and stops layout points, the shape of edge strip up and down of rib and area, the thickness of rib web, the material of rib and rib finite element unit are numbered, whether rib is reinforcement judgement; Multiple material wall panel structure finite element model in S2 comprises geometric parameter, material mechanical performance, density, load, edge-restraint condition, the composite plys order of multiple material wall panel structure; In S3, the finite element model definition load of multiple material wall panel structure and the foundation of boundary constraint way choice are comprised to structure stand under load and the type of attachment of multiple material wallboard.In S4, the foundation of multiple material wall panel structure finite element model structural static strength, stiffness analysis is multiple material wall panel structure finite element model load profile data, edge-restraint condition, geometrical parameters.In S6, the mode according to multiple material wallboard carrying carries out simulation optimization analysis to the laying of composite structure, and the laying simulation optimization analysis of composite structure comprises wing flapping degree, thickness.In S7, the mode of multiple material wall panel structure Weight computation is volume density computing method.
In the preferred embodiment of the invention described above, definition structure parameter: the multiple material wallboard primary structure of anti-axial compression comprises panel and reinforcement (beam, vertical wall, stringer etc.) two class formations; Panel defines: panel characterising parameter comprises: 1. plate thickness 2. material and numbering.Reinforcement defines: the constructional function of reinforcement strengthens the multiple anti-axial compression Buckling of material wallboard.Single reinforcement characterising parameter comprises: 1. initial sum stop layout points, 2. up and down edge strip shape, area, 3. web thickness, 4. material and numbering, 5. whether be reinforcement.Consider the layout feature of reinforcement, can adopt grouping management to reinforcement, single group reinforcement characterising parameter comprises reinforcement quantity, reinforcement arrangement, the panel number connected and reinforcement list information.Definition load and boundary constraint: for different structure stands under load and type of attachment, select corresponding boundary constraint mode.Build multiple material wall panel structure finite element model: model should comprise the information such as geometric parameter, material mechanical performance, density, load, edge-restraint condition, composite plys order of structure, should be divided into groups according to version and loading characteristic to the element of composition model, guarantee can correctly export the multiple weight of material wall panel structure and the weight of its minor structure according to the division of element set.
Structural static strength stiffness analysis: according to load profile data, edge-restraint condition, geometrical parameters, carries out structural static strength and rigidity simulation analysis;
The laying optimization of composite structure: carry out simulation optimization analysis to the thickness of laying and ply stacking-sequence, ensures that the minimum weight of composite structure distributes;
Structural stability analysis: for completing structural stability analysis, should build the material characteristic data needed for stability analysis, typical unstability structural profile characteristic, all kinds of stability failure mode, all kinds of stability inefficacy formula, all kinds of stability failure curves etc.Calculate desirable load path on this basis, optimization information is provided, ensure that the minimum weight of pressurized primary structure distributes.
Multiple material wall panel structure Weight computation: after completing structure simulation Optimization analyses, calculates the weight of whole multiple material wall panel structure according to volume density method.
In the process of the multiple material wallboard gravimetric analysis modeling method of embody rule aircraft provided by the invention, carry out finite element gravimetric analysis modeling to the multiple material wallboard of the anti-axial compression of aircraft parts, instantiation is as follows:
1) definition structure parameter:
The multiple material wallboard primary structure of certain anti-axial compression is long purlin, Ω cross section wall panel structure;
Panel defines: panel characterising parameter comprises: 1. plate thickness 2. material and numbering.
Reinforcement defines: definition structural I-beam parameter comprises: 1. initial sum stops layout points 2. upper and lower edge strip shape, area 3. web thickness 4. material and numbering.Adopt grouping management to reinforcement, single group reinforcement characterising parameter comprises reinforcement quantity, reinforcement arrangement, the panel number connected and reinforcement list information.
2) load and boundary constraint is defined
For different structure stands under load and type of attachment, select corresponding boundary constraint mode, as both sides freely-supported, simply supported on four sides etc.
3) multiple material wall panel structure finite element model is built:
Multiple material wall panel structure finite element model model contains the information such as size, material mechanical performance, density, load, edge-restraint condition, composite plys order of structure, the element of composition model is divided into groups respectively according to panel and I-beam, according to panel and each I-beam element set can distinguish the weight of output slab structure and the weight of each structural I-beam, and may be combined with into the element set of whole multiple material wall panel structure, provide the weight of whole multiple material wall panel structure.
4) structural static strength stiffness analysis:
According to load profile data, edge-restraint condition, geometrical parameters, carry out structural static strength and rigidity simulation analysis, analysis process is shown in Fig. 2;
5) structural stability analysis:
Build material characteristic data needed for stability analysis, typical unstability structural profile characteristic, all kinds of stability failure mode, all kinds of stability inefficacy formula as
(h, b are thickness and width, and k relies on side ratio and boundary condition) }, all kinds of stability failure curves etc.Calculate desirable load path on this basis, optimization information is provided, ensure that the minimum weight of pressurized primary structure distributes.
6) the laying optimization of composite structure:
Simulation optimization analysis is carried out to the thickness of laying and ply stacking-sequence, ensures that the minimum weight of composite structure distributes.The laying Optimizing Flow of composite structure is shown in Fig. 4.
7) multiple material wall panel structure Weight computation:
After completing the multiple material wall panel structure simulation optimization analysis of pressurized, calculate the mass property of whole multiple material wall panel structure according to volume density method.
The multiple material wallboard gravimetric analysis modeling method of aircraft provided by the invention is in the airplane design initial stage antagonism axial compression problem that material wallboard weight estimation error is larger again.Resist the multiple material wall panel structure of axial compression fast and accurately at the airplane design initial stage and carry out finite element modeling, and then can numerical simulation be passed through, the weight of the multiple material wall panel structure of the anti-axial compression of calculating accurately and fast, center of gravity and moment of inertia, solve the difficult problem that traditional means can only estimate roughly the multiple material wallboard weight of the anti-axial compression of assessment at one stroke.
More than be described in detail in conjunction with the multiple material wallboard gravimetric analysis modeling method specific embodiment of aircraft of the present invention, but be not limitation of the present invention, everyly according to technical spirit of the present invention, technical scope of the present invention is all belonged to any simple modification made for any of the above embodiments, also it should be noted that, comprise the combination in any between each part mentioned above according to the category of the multiple material wallboard gravimetric analysis modeling method technical scheme of aircraft of the present invention.
Claims (7)
1. the multiple material wallboard gravimetric analysis modeling method of aircraft, the mass property for the airplane design stage is estimated, it is characterized in that, adopts finite element method, comprises the steps:
S1, definition structure parameter, described structural parameters comprise panel and rib;
S2, builds multiple material wall panel structure finite element model;
S3, to finite element model definition load and the boundary constraint of multiple material wall panel structure;
S4, multiple material wall panel structure finite element model structural static strength, stiffness analysis;
S5, structural stability analysis;
S6, the laying optimization of composite structure;
S7, multiple material wall panel structure Weight computation.
2. the multiple material wallboard gravimetric analysis modeling method of aircraft as claimed in claim 1, is characterized in that, in S1, the panel in structural parameters comprises plate thickness, panel material and panel finite element unit numbering; Rib in structural parameters comprises rib initial sum and stops layout points, the shape of edge strip up and down of rib and area, the thickness of rib web, the material of rib and rib finite element unit are numbered, whether rib is reinforcement judgement.
3. the multiple material wallboard gravimetric analysis modeling method of aircraft as claimed in claim 1, it is characterized in that, the multiple material wall panel structure finite element model in S2 comprises geometric parameter, material mechanical performance, density, load, edge-restraint condition, the composite plys order of multiple material wall panel structure.
4. the multiple material wallboard gravimetric analysis modeling method of the aircraft as described in claim 1 or 3, it is characterized in that, in S3, the finite element model definition load of multiple material wall panel structure and the foundation of boundary constraint way choice are comprised to structure stand under load and the type of attachment of multiple material wallboard.
5. the multiple material wallboard gravimetric analysis modeling method of aircraft as claimed in claim 1, it is characterized in that, in S4, the foundation of multiple material wall panel structure finite element model structural static strength, stiffness analysis is multiple material wall panel structure finite element model load profile data, edge-restraint condition, geometrical parameters.
6. the multiple material wallboard gravimetric analysis modeling method of aircraft as claimed in claim 1, it is characterized in that, in S6, the mode according to multiple material wallboard carrying carries out simulation optimization analysis to the laying of composite structure, and the laying simulation optimization analysis of composite structure comprises wing flapping degree, thickness.
7. the multiple material wallboard gravimetric analysis modeling method of aircraft as claimed in claim 1, is characterized in that, in S7, the mode of multiple material wall panel structure Weight computation is volume density computing method.
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| CN107818203A (en) * | 2017-10-22 | 2018-03-20 | 南京理工大学 | A kind of mortar seat metal plate light weight method |
| CN108052700A (en) * | 2017-11-22 | 2018-05-18 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft flat-type optimum structure design method |
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| CN105760619B (en) * | 2016-03-10 | 2018-06-29 | 北京航空航天大学 | A kind of composite plys optimum design method for considering fatigue reliability |
| CN107563033A (en) * | 2017-08-23 | 2018-01-09 | 成都飞机工业（集团）有限责任公司 | A kind of Optimization Design of composite air intake duct |
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| CN108052700A (en) * | 2017-11-22 | 2018-05-18 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft flat-type optimum structure design method |
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| CN110659525B (en) * | 2018-06-29 | 2023-08-29 | 上海波客实业有限公司 | Optimized design method for composite structure |
| CN110990957A (en) * | 2019-12-19 | 2020-04-10 | 中国航空工业集团公司沈阳飞机设计研究所 | Wing structure weight analysis method in aircraft overload performance design |
| CN111539134A (en) * | 2019-12-25 | 2020-08-14 | 中国航空工业集团公司西安飞机设计研究所 | Method for processing large-curvature aircraft panel |
| CN111539134B (en) * | 2019-12-25 | 2023-10-20 | 中国航空工业集团公司西安飞机设计研究所 | Processing method of large-curvature aircraft panel |
| CN111382477A (en) * | 2020-03-02 | 2020-07-07 | 上海索辰信息科技有限公司 | Composite material wallboard analysis method based on structural genome technology |
| CN112699489A (en) * | 2020-12-29 | 2021-04-23 | 中国航空工业集团公司西安飞机设计研究所 | Control surface wallboard structure configuration determining method |
| CN114676508A (en) * | 2022-05-26 | 2022-06-28 | 中国飞机强度研究所 | Large-gradient fast time-varying extreme high-temperature environment aerospace plane structure heat strength evaluation method |
| CN114722509A (en) * | 2022-06-09 | 2022-07-08 | 华中科技大学 | Conical reinforced cabin layering sequence optimization method based on fiber continuous model |
| CN114722509B (en) * | 2022-06-09 | 2022-09-09 | 华中科技大学 | Conical reinforced cabin layering sequence optimization method based on fiber continuous model |
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