CN109325284A - It is a kind of to consider probabilistic strong robustness discrimination method of honeycomb rudder face equivalent parameters - Google Patents
It is a kind of to consider probabilistic strong robustness discrimination method of honeycomb rudder face equivalent parameters Download PDFInfo
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Abstract
Probabilistic strong robustness discrimination method of honeycomb rudder face equivalent parameters is considered the invention discloses a kind of, the present invention uses strain energy equivalent method that the equivalent entity elasticity modulus of honeycomb is calculated first, then it is directed to the feature of rudder face practical structures, using shell unit and solid element grid division, obtain the equivalent rudder face model of honeycomb, the consistency checking of the modal analysis result validity of the equivalent process.Then it is combined using the model equivalent method based on static(al) with genetic algorithm, honeycomb equivalent model is further equivalent to hardened structure.By this equivalent process, so that plate structural model is very close with the response of rudder face archetype under load effect.The present invention considers the uncertain influence to rudder face model simplification of structural elasticity parameter, proposes the robustness index based on non-probability Interference Model, obtains the robustness identification result of structure elasticity modulus under the effect of multiple operating conditions.
Description
Technical field
The present invention relates to uncertainty structure model equivalence techniques fields, in particular to a kind of to consider probabilistic honeycomb
The strong robustness discrimination method of structure rudder face equivalent parameters, this method considers the uncertain but bounded of structural elasticity parameter, using power
The identification Method that properties equivalent method and the model equivalent method based on static(al) are combined with genetic algorithm, with multiple loads
The non-probability Interference Model of displacement interval vector of the displacement section vector sum accurate model corresponding position of simplified model under lotus operating condition
Robustness index is established, and gives related optimized calculation method.This method can be the rudder face bee containing uncertain parameters
The model equivalent-simplification of nest structure provides theoretical method for hardened structure.
Background technique
Structure dynamics load identification belongs to the indirect problem of Structural Dynamics, it according to the dynamic characteristic of known structure system and
Dynamic load suffered by dynamic response inverse structure is surveyed, so that complicated Service Environment lower outer portion excitation be overcome to be difficult to directly measure
Or immeasurablel objective engineering specifications restricts.The determination of dynamic loads is the key that realize one of structural loads design, this is right
It is particularly important in the lighting design for realizing Air-breathing hypersonic vehicle structure.Inverse problem be typically all ill-posed problem and
Nonlinear problem, dynamic state loading identification are no exception.Due to the vibration ill-posedness of inverse problem and non-linear, so that research is efficient
Practical inversion method encounters very big difficulty.Nevertheless, since exact dynamic load can be dynamic design, Dynamic Optimum
And the problems such as damping vibration-isolating, provides reliable foundation, is the important guarantee of engineering structure reliability and safety.
The importance of dynamic state loading identification problem is accepted extensively, however, being currently directed to air suction type hypersonic flight
The research of device dynamic state loading identification is mostly still in theoretical research and Qualify Phase, success of the research achievement to practical implementation
It is converted to and is rarely reported.To find out its cause, for complex load operating condition in the full flight envelope of Air-breathing hypersonic vehicle and more
Under the application environment of source uncertainty cross influence, there are still rigidity under complex model multi-state for current main-stream load recognition method
The universality of high-precision equivalent model is insufficient, the strong robust control policy of nonlinear structure system DYNAMIC DISTRIBUTION load is difficult under low signal-to-noise ratio
The problems such as.In order to simplify problem, need to simplify on model.Due to the material parameter and load value of model all have it is certain
Uncertainty needs the strong robustness identification model equivalent for uncertainty building structural parameters, to realize uncertainty
The legal equivalents of model.
Summary of the invention
The technical problem to be solved by the present invention is overcoming the deficiencies of the prior art and provide a kind of probabilistic bee of consideration
The strong robustness discrimination method of nest structure rudder face equivalent parameters.The present invention considers the uncertainty of practical rudder face honeycomb, uses
The equivalent entity elasticity modulus of honeycomb is calculated in equivalent formulation, is then directed to the feature of rudder face practical structures, utilizes shell
Unit and solid element grid division obtain the equivalent rudder face model of honeycomb；Then the efficacious prescriptions such as the model based on static(al) are used
Method is combined with genetic algorithm, and honeycomb equivalent model is further equivalent to hardened structure.The plate structure mould obtained by this method
Type is very close with the response of rudder face archetype under load effect, is capable of providing reasonable rudder face simplified model.
The technical solution adopted by the present invention are as follows: a kind of to consider probabilistic strong robustness of honeycomb rudder face equivalent parameters
Discrimination method, this method can provide reason for the model equivalent-simplification of the rudder face honeycomb containing uncertain parameters for hardened structure
By method, implementation step is as follows:
Step 1: the honeycomb of model is reduced to entity structure by the equivalent form of mechanical property, constructs rudder face honeycomb
Equivalent structure obtains the equivalent mechanical parameter formula of rudder face honeycomb sandwich structures:
Wherein, EsAnd GsThe respectively elasticity modulus and modulus of shearing of sandwich material, t are the thickness of honeycomb thin-walled, and nt is bee
The thickness of nest heavy wall, l are the length for forming cellular regular hexagon, cellular sandwich with a thickness of hc=b, ρsFor the density of cell element；
Ecx,Ecy,EczIt is in honeycomb face respectively along x, y, the elasticity modulus in z-axis direction, μxy,μyz,μxzIt is honeycomb respectively
Along x, y, the Poisson's ratio in z-axis direction, Gcxy,Gcyz,GczxIt is xoy respectively, yoz, the transverse shear modulus in the face zox；
Step 2: by the honeycomb Equivalent finite element model of rudder face by stiffnes s equivalent to pass identification Method in principle equivalent
For hardened structure, different according to different subregions rudder face thickness divide subregion to rudder face structure, assign respectively for different subregions
Elasticity modulus:
E1,E2,…,En
Wherein, n indicates the rudder face number of partitions；
Step 3: considering the dispersibility of structural material, and the elastic parameter of honeycomb equivalent structure is set as interval number；
Step 4: considering the dispersibility of vehicle construction material, with the displacement section of simplified model under multiple load working conditions
VectorWith the displacement interval vector of accurate model corresponding positionNon- probability Interference Model is built
Vertical robustness index:
Wherein,u i,rWithRespectively simplify the modal displacement lower bound and the upper bound of i-th of freedom degree of structure,u i,aWithPoint
Not Wei i-th of freedom degree of precision architecture modal displacement lower bound and the upper bound, KjFor the rigidity in j-th of region of simplified model, Δ KjFor
The variable quantity of rigidity；Subscript i, r and a respectively represent i-th of load working condition, simplified model and accurate model；
Step 5: it is directed to k-th of operating condition, according to the upper bound of original structure elastic parameter and lower bound, using sensitivity analysis side
Method is calculated the corresponding shift value of accurate model material parameter bound, obtains the elasticity modulus of equivalent model by iteration
Central value Kj,kWith variation delta Kj,k；
Step 6: based on elasticity modulus central value and variable quantity that multiple condition calculatings obtain, using genetic algorithm
The optimal solution of robustness index is calculated, obtaining structure, also the elasticity modulus with robustness recognizes under the effect of multiple operating conditions
As a result.
Wherein, the honeycomb of model is reduced to by entity structure, structure by the equivalent form of mechanical property in the step 1
Build rudder face honeycomb equivalent structure.
Wherein, rudder face Equivalent Plate structure is directed in the step 2, different according to rudder face thickness divide rudder face structure
Subregion simultaneously assigns elasticity modulus respectively.
Wherein, the dispersibility that structural material is considered in the step 3, the elastic parameter of honeycomb equivalent structure is set as
Interval number.
Wherein, the step 4 is with the displacement interval vector of simplified model under multiple load working conditionsAnd essence
The displacement interval vector of true model corresponding positionNon- probability Interference Model establishes robustness index.
Wherein, the step 5 obtains the elasticity modulus central value K of equivalent model by iterationj,kWith variation delta Kj,k。
Wherein, it is calculated based on the elasticity modulus central value obtained under multi-state and variable quantity using heredity in the step 6
The optimal solution of robustness index is calculated in method, and obtaining structure, also the elasticity modulus with robustness is distinguished under the effect of multiple operating conditions
Know result.
The advantages of the present invention over the prior art are that:
Probabilistic strong robustness discrimination method of honeycomb rudder face equivalent parameters is considered the present invention provides a kind of.?
On the basis of the uncertainty for considering practical rudder face honeycomb, pass through the equivalent equivalent reality for having obtained honeycomb of mechanical property
Honeycomb equivalent model is further equivalent to hardened structure by body, the model equivalent method and genetic algorithm for being then based on static(al).The party
The problem of method overcomes original rudder face structure is complicated, is greatly reduced the calculation amount of load identification process, also simplifies for carrying
Lotus identifies unnecessary structure feature, this has very important significance for the quick identification tool of dynamic load.
Detailed description of the invention
Fig. 1 is the flow chart that the present invention carries out rudder face model equivalent-simplification；
Fig. 2 is the model schematic that the present invention carries out rudder face model equivalent-simplification embodiment；
Fig. 3 is the honeycomb cell element horizontal single-headed stress and its equivalent schematic of the embodiment of the present invention, wherein Fig. 3 (a) is single
Born of the same parents' stress analysis figure, Fig. 3 (b) are unit cell equivalent force and torque schematic diagram；
Fig. 4 is the schematic diagram of rudder face honeycomb equivalent model in the embodiment of the present invention；
Fig. 5 is the schematic diagram that the embodiment of the present invention simplifies obtained Equivalent Plate finite element model；
Fig. 6 be the embodiment of the present invention at 2 ° of the angle of attack equivalent structure and original structure z to displacement comparison (the modulus upper bound)
Figure；
Fig. 7 be the embodiment of the present invention at 2 ° of the angle of attack equivalent structure and original structure z to displacement comparison (modulus lower bound)
Figure；
Fig. 8 be the embodiment of the present invention at 5 ° of the angle of attack equivalent structure and original structure z to displacement comparison (the modulus upper bound)
Figure；
Fig. 9 be the embodiment of the present invention at 5 ° of the angle of attack equivalent structure and original structure z to displacement comparison (modulus lower bound)
Figure.
Specific embodiment
With reference to the accompanying drawing and specific embodiment further illustrates the present invention.
As shown in Figure 1, considering probabilistic strong robustness of honeycomb rudder face equivalent parameters the invention proposes a kind of
Discrimination method, comprising the following steps:
(1) honeycomb of model is reduced to entity structure by the equivalent form of mechanical property, building rudder face honeycomb is equivalent
Structure obtains the equivalent mechanical parameter formula of rudder face honeycomb sandwich structures.
By taking the elasticity modulus of x-axis direction and Poisson's ratio formula as an example, illustrate the deriving method of equivalent mechanical parameter formula.Bee
Nest is made of a series of regular hexagons.The top view of honeycomb is as shown below.And establish rectangular coordinate system, horizontally to the right for
X-axis is y-axis in horizontal direction, is z-axis in vertical plane.Due to the limitation of technique, along the cellular sandwich on the direction y thickness with
Difference elsewhere, if n times of the thickness with a thickness of other directions along the direction y.If EsFor the springform of sandwich material
Amount, t are the thickness of honeycomb thin-walled, and nt is the thickness of honeycomb heavy wall, and l is the length for forming cellular regular hexagon, cellular sandwich
With a thickness of hc=b.For the ease of being analyzed and being derived, honeycomb is divided into cell element one by one, such as the dotted line side Fig. 2
Shown in frame.
In order to derive the elastic modulus E in honeycomb face along the x-axis directioncx, the left and right sides of present cell element applies equal
Even pure stress σ1, as shown in Fig. 3 (a).A is arrived by stress is equivalent, C two o'clock obtains concentrated force P and torque M, such as Fig. 3 (b)
It is shown.
It is equal available by resultant force:
P=σ1b(l+l sinθ) (1)
Since the corner at point A is 0, then there is θM+θP=0, and then available:
Thin-walled AB can regard cantilever beam as, and cross sectional shape is rectangle.Then the thin-walled AB as caused by power P and torque M is vertical
Its axial amount of deflection are as follows:
The axial elongation of thin-walled AB are as follows:
By symmetry, the deformation of thin-walled BC is identical with the deformation of thin-walled AB.So available cell element is in the side x
Upward equivalent strain are as follows:
The equivalent strain of cell element in y-direction are as follows:
The then equivalent elastic modulus in the direction x are as follows:
The equivalent Poisson's ratio in the direction x are as follows:
Because of θ=π/6, substituting into formula (8) and formula (9), abbreviation can be obtained:
The formula of other elastic parameters can be exported with the method for above-mentioned all fours, obtain rudder face honeycomb sandwich structures
Equivalent mechanical parameter formula:
Wherein, EsAnd GsThe respectively elasticity modulus and modulus of shearing of sandwich material, t are the thickness of honeycomb thin-walled, and nt is bee
The thickness of nest heavy wall, l are the length for forming cellular regular hexagon, cellular sandwich with a thickness of hc=b, ρsFor the density of cell element；
Ecx,Ecy,EczIt is in honeycomb face respectively along x, y, the elasticity modulus in z-axis direction, μxy,μyz,μxzIt is honeycomb respectively
Along x, y, the Poisson's ratio in z-axis direction, Gcxy,Gcyz,GczxIt is xoy respectively, yoz, the transverse shear modulus in the face zox.
(2) the honeycomb Equivalent finite element model of rudder face is equivalent to plate by the identification Method of passing in principle of stiffnes s equivalent
Structure, different according to different subregions rudder face thickness divide subregion to rudder face structure, assign elasticity respectively for different subregions
Modulus:
E1,E2,…,En
Wherein, n indicates the rudder face number of partitions.
(3) dispersibility for considering structural material, is set as interval number for the elastic parameter of honeycomb equivalent structure.Such as set bullet
Property parameter EiBound be limited to:
(4) dispersibility of vehicle construction material is considered, with the displacement interval vector of simplified model under multiple load working conditionsWith the displacement interval vector of accurate model corresponding positionNon- probability Interference Model is established steady
Strong property index:
Wherein,u i,rWithRespectively simplify the modal displacement lower bound and the upper bound of i-th of freedom degree of structure,u i,aWithPoint
Not Wei i-th of freedom degree of precision architecture modal displacement lower bound and the upper bound, KjFor the rigidity in j-th of region of simplified model, Δ KjFor
The variable quantity of rigidity；Subscript i, r and a respectively represent i-th of load working condition, simplified model and accurate model.
(5) it is directed to k-th of operating condition, according to the upper bound of original structure elastic parameter and lower bound, using Sensitivity Analysis Method, meter
Calculation obtains the corresponding shift value of accurate model material parameter bound, obtains the elasticity modulus central value of equivalent model by iteration
Kj,kWith variation delta Kj,k。
Firstly, the displacement for the honeycomb Equivalent finite element model being calculated under aerodynamic loading effect, then extracts honeycomb etc.
Imitate the coordinate (x of face node in finite element modelj,yj,zj) and z to shift value uz,j, wherein subscript j indicates complete finite element model
The number of middle face node, if face number of nodes is n in modelm, then j=1,2 ..., nm。
Extract Slab node coordinate (xi,yi,zi), i=1,2 ..., n, according to the node coordinate of Slab and front
Coordinate (the x of face node in the honeycomb equivalent model acquiredj,yj,zj) and z to shift value uz,j, using Interpolation Property of Radial Basis Function side
Method obtains the reference displacement components u of Slabi0。
To Slab structure in this present embodiment, the initial elastic modulus E of three subregions is given1,0、E2,0And E3,0, just
The shift value u of Slab node can be calculatedn×1.Define error function are as follows:
E=u0-u (14)
Wherein e is the column vector of n × 1, u0Reference to acquire is displaced column vector.If p=[E1,E2,E3]T, then e and u be
It is the function of p, it may be assumed that
E (p)=u0-u(p) (15)
Substitute into Ku0=F can be obtained:
E (p)=K-1F-u(p) (16)
Wherein, K, F are respectively global stiffness matrix and load vectors.
First order Taylor expansion is carried out to formula (17), is obtained:
If sensitivity matrix are as follows:
Wherein:
The error function of defining scalar are as follows:
J (p)=e (p+ Δ p)Te(p+Δp) (20)
It enablesIt can obtain:
STS Δ p=-STe(p) (21)
By formula (22), its least square solution can be acquired are as follows:
Δ p=- (STS)-1STe(p) (22)
According to above iterative solution process, upper bound displacement or lower bound misalignment under an operating condition can be calculated
Under elastic modulus E1、E2And E3, so that further equivalent obtained Slab and complete finite element model are under Static behavior
Displacement difference minimize.
(6) it based on elasticity modulus central value and variable quantity that multiple condition calculatings obtain, is calculated using genetic algorithm
The optimal solution of robustness index is obtained, obtaining structure, also the elasticity modulus with robustness recognizes knot under the effect of multiple operating conditions
Fruit.
Embodiment:
The characteristics of in order to more fully understand the invention and its to the actual applicability of engineering, the present invention is directed to such as Fig. 2 institute
The vehicle rudder structure shown carries out model equivalent-simplification, and simple flow is as shown in Figure 1.Here rudder face load working condition is winged
Scanning frequency degree 3Ma, flying height 20000m, the angle of attack is respectively 2 ° and 5 °.The elastic parameter of honeycomb equivalent structure is set with 2% mistake
Poor (as shown in table 1), due to μxyClose to 1, here it is considered that its only downward deviation 2%, passes through building and considers probabilistic mould
Type identifying index, to meet the robustness requirement of identification result.
The distributed area of 1 elastic parameter of table
For Slab structure, the initial elastic modulus E of three subregions is given1,0、E2,0And E3,0.Based on deterministic process,
It using 2 ° of the angle of attack and the interval solutions of 5 ° of two operating conditions of the angle of attack as initial value, is solved, is counted using the genetic algorithm in MATLAB
It calculates and obtains the robustness identification result of three elasticity modulus of Slab it is as shown in the table, the corresponding Slab of elasticity modulus bound
(at 2 ° and 5 ° of the angle of attack, equivalent structure and original structure z are to position as shown in Fig. 6-Fig. 9 for displacement and master mould displacement comparison result
The modulus upper bound of shifting, lower bound comparison diagram, see Detailed description of the invention).It can see from Fig. 6-Fig. 9, the identification result being calculated above
With preferable robustness, for different loading conditions, structural response is all consistent with original structure substantially, and displacement is basic
It is overlapped.
The robustness identification result of three elasticity modulus of 2 Slab of table
The above is only specific steps of the invention, are not limited in any way to protection scope of the present invention；Its is expansible to answer
Equivalent, simplified field, all technologies formed using equivalent transformation or equivalent replacement for uncertain complicated rudder face structure
Scheme is all fallen within rights protection scope of the present invention.
Part of that present invention that are not described in detail belong to the well-known technology of those skilled in the art.
Claims (7)
1. a kind of consider probabilistic strong robustness discrimination method of honeycomb rudder face equivalent parameters, this method can be for containing not
Determine that the model simplification of the honeycomb rudder face of factor provides approach, which is characterized in that realize that steps are as follows:
Step 1: the honeycomb of model is reduced to entity structure by the equivalent form of mechanical property, building rudder face honeycomb is equivalent
Structure obtains the equivalent mechanical parameter formula of rudder face honeycomb sandwich structures:
Wherein, EsAnd GsThe respectively elasticity modulus and modulus of shearing of sandwich material, t are the thickness of honeycomb thin-walled, and nt is that honeycomb is thick
The thickness of wall, l are the length for forming cellular regular hexagon, cellular sandwich with a thickness of hc=b, ρsFor the density of cell element；Ecx,
Ecy,EczIt is in honeycomb face respectively along x, y, the elasticity modulus in z-axis direction, μxy,μyz,μxzHoneycomb respectively along
X, y, the Poisson's ratio in z-axis direction, Gcxy,Gcyz,GczxIt is xoy respectively, yoz, the transverse shear modulus in the face zox；
Step 2: the honeycomb Equivalent finite element model of rudder face is equivalent to plate by the identification Method of passing in principle of stiffnes s equivalent
Structure, different according to different subregions rudder face thickness divide subregion to rudder face structure, assign elasticity respectively for different subregions
Modulus:
E1,E2,…,En
Wherein, n indicates the rudder face number of partitions；
Step 3: considering the dispersibility of structural material, and the elastic parameter of honeycomb equivalent structure is set as interval number；
Step 4: considering the dispersibility of vehicle construction material, with the displacement interval vector of simplified model under multiple load working conditionsWith the displacement interval vector of accurate model corresponding positionNon- probability Interference Model is established steady
Strong property index:
Wherein,u i,rWithRespectively simplify the modal displacement lower bound and the upper bound of i-th of freedom degree of structure,u i,aWithRespectively
The modal displacement lower bound of i-th of freedom degree of precision architecture and the upper bound, KjFor the rigidity in j-th of region of simplified model, Δ KjFor rigidity
Variable quantity；Subscript i, r and a respectively represent i-th of load working condition, simplified model and accurate model；
Step 5: being directed to k-th of operating condition, according to the upper bound of original structure elastic parameter and lower bound, using Sensitivity Analysis Method, meter
Calculation obtains the corresponding shift value of accurate model material parameter bound, obtains the elasticity modulus central value of equivalent model by iteration
Kj,kWith variation delta Kj,k；
Step 6: it based on elasticity modulus central value and variable quantity that multiple condition calculatings obtain, is calculated using genetic algorithm
The optimal solution of robustness index is obtained, obtaining structure, also the elasticity modulus with robustness recognizes knot under the effect of multiple operating conditions
Fruit.
2. a kind of probabilistic strong robustness identification side of honeycomb rudder face equivalent parameters of consideration according to claim 1
Method, it is characterised in that: the honeycomb of model is reduced to entity structure by the equivalent form of mechanical property in the step 1.
3. a kind of probabilistic strong robustness identification side of honeycomb rudder face equivalent parameters of consideration according to claim 1
Method, it is characterised in that: pass the honeycomb Equivalent finite element model of rudder face in principle model by stiffnes s equivalent in the step 2
Discrimination method is equivalent to hardened structure, and different according to different subregions rudder face thickness divide subregion to rudder face structure, for different
Subregion assigns elasticity modulus respectively.
4. a kind of probabilistic strong robustness identification side of honeycomb rudder face equivalent parameters of consideration according to claim 1
Method, it is characterised in that: the elastic parameter of honeycomb equivalent structure is set as interval number in the step 3.
5. a kind of probabilistic strong robustness identification side of honeycomb rudder face equivalent parameters of consideration according to claim 1
Method, it is characterised in that: the step 4 is corresponding with the displacement section vector sum accurate model of simplified model under multiple load working conditions
The non-probability Interference Model of the displacement interval vector of position establishes robustness index.
6. a kind of probabilistic strong robustness identification side of honeycomb rudder face equivalent parameters of consideration according to claim 1
Method, it is characterised in that: the step 5 is directed to specific operating condition, and according to the upper bound of original structure elastic parameter and lower bound, use is sensitive
Analysis method is spent, the corresponding shift value of accurate model material parameter bound is calculated, equivalent model is obtained by iteration
Elasticity modulus central value Kj,kWith variation delta Kj,k。
7. a kind of probabilistic strong robustness identification side of honeycomb rudder face equivalent parameters of consideration according to claim 1
Method, it is characterised in that: in the step 6 based on elasticity modulus central value and variable quantity that multiple condition calculatings obtain, adopt
The optimal solution of robustness index is calculated with genetic algorithm.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110472312A (en) * | 2019-07-29 | 2019-11-19 | 武汉科技大学 | Self similarity honeycomb optimization method, device and storage medium in a kind of shape |
| CN110532607A (en) * | 2019-07-24 | 2019-12-03 | 北京航空航天大学 | The sensor placement method of hypersonic aircraft rudder face structure distribution load identification |
| CN111027125A (en) * | 2019-12-26 | 2020-04-17 | 东南大学 | Honeycomb equivalent unit and parameter calculation method based on same |
| CN112685906A (en) * | 2021-01-05 | 2021-04-20 | 广州大学 | Method, system, device and medium for analyzing accordion cellular structure constitutive relation |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110042524A1 (en) * | 2008-02-21 | 2011-02-24 | Cornerstone Research Group | Passive adaptive structures |
| CN105844025A (en) * | 2016-03-25 | 2016-08-10 | 北京航空航天大学 | Non-probability aerothermoelasticity reliability designing method for hypersonic control surface |
| CN106021802A (en) * | 2016-06-06 | 2016-10-12 | 上海宇航***工程研究所 | Finite element calculation method for strength of embedded-beam-containing honeycomb sandwich structure |
-
2018
- 2018-09-14 CN CN201811071742.8A patent/CN109325284B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110042524A1 (en) * | 2008-02-21 | 2011-02-24 | Cornerstone Research Group | Passive adaptive structures |
| CN105844025A (en) * | 2016-03-25 | 2016-08-10 | 北京航空航天大学 | Non-probability aerothermoelasticity reliability designing method for hypersonic control surface |
| CN106021802A (en) * | 2016-06-06 | 2016-10-12 | 上海宇航***工程研究所 | Finite element calculation method for strength of embedded-beam-containing honeycomb sandwich structure |
Non-Patent Citations (1)
| Title |
|---|
| 蔡逸如等: ""考虑宏细观等效的双材料连续体结构可靠性拓扑"", 《中国力学大会-2017暨庆祝中国力学学会成立60周年大会》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110532607A (en) * | 2019-07-24 | 2019-12-03 | 北京航空航天大学 | The sensor placement method of hypersonic aircraft rudder face structure distribution load identification |
| CN110472312A (en) * | 2019-07-29 | 2019-11-19 | 武汉科技大学 | Self similarity honeycomb optimization method, device and storage medium in a kind of shape |
| CN110472312B (en) * | 2019-07-29 | 2022-12-27 | 武汉科技大学 | Method and device for optimizing shape internal self-similarity honeycomb structure and storage medium |
| CN111027125A (en) * | 2019-12-26 | 2020-04-17 | 东南大学 | Honeycomb equivalent unit and parameter calculation method based on same |
| CN111027125B (en) * | 2019-12-26 | 2024-01-26 | 东南大学 | Honeycomb equivalent unit and parameter calculation method based on same |
| CN112685906A (en) * | 2021-01-05 | 2021-04-20 | 广州大学 | Method, system, device and medium for analyzing accordion cellular structure constitutive relation |
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