CN105825035B - The equivalent way of surface distributed force when a kind of wing strut axial compression - Google Patents
The equivalent way of surface distributed force when a kind of wing strut axial compression Download PDFInfo
- Publication number
- CN105825035B CN105825035B CN201610323059.3A CN201610323059A CN105825035B CN 105825035 B CN105825035 B CN 105825035B CN 201610323059 A CN201610323059 A CN 201610323059A CN 105825035 B CN105825035 B CN 105825035B
- Authority
- CN
- China
- Prior art keywords
- force
- wing strut
- strut
- finite element
- surface distributed
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Geometry (AREA)
- General Physics & Mathematics (AREA)
- Computer Hardware Design (AREA)
- General Engineering & Computer Science (AREA)
- Evolutionary Computation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Pure & Applied Mathematics (AREA)
- Mathematical Optimization (AREA)
- Mathematical Analysis (AREA)
- Computational Mathematics (AREA)
- Automation & Control Theory (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The present invention relates to a kind of equivalent ways of surface distributed force when wing strut axial compression, belong to aircraft structure strength test field.Global finite element model including initially setting up the wing strut and its both ends jointing, secondly the wing strut axial isometric is divided into several segments along it, a finite element node is taken on either segment, using bending direction of the wing strut in surface distributed force as the application direction of concentrated force；Apply point for the corresponding finite element node of the equivalent deformation as concentrated force；Final concentrated force size is finally determined by successive ignition for adjusting concentrated force size according to the ratio of the node lateral displacement of surface distributed force situation and the node lateral displacement of concentrated force situation.In strength test, it can determine whether strut meets Intensity Design by applying axial compression load and the concentrated force of strut, simplify test load.
Description
Technical field
The invention belongs to surfaces when aircraft structure strength test field more particularly to a kind of wing strut axial compression to be distributed
The equivalent way of power.
Background technique
For the aircraft using diagonal brace rod-type wing, the design of strut is most important, especially when strut bears axial pressure
When contracting load, unstability is easy to happen to lose bearing capacity, while the also effect of wing strut surfaces has aerodynamic loading generation
Distributed force, this but will substantially reduce its compress bearing capacity.
In order to verify whether the design of strut meets intensity requirement, need to make a strength test, and guarantee its stress shape
State is as far as possible close to true.It but since the aerodynamic loading of strut surfaces belongs to EDS maps load, and is non-uniform, or even in strut
Different cross section on load be reversed, if loaded in strict accordance with truth, it is difficult to implement, it is therefore desirable to a kind of strut table
The equivalent way of force per unit area is implemented in the case where guaranteeing that strut stress characteristic is constant convenient for test.
Summary of the invention
To solve the above-mentioned problems, surface distributed force is equivalent when the invention of this hair provides a kind of wing strut axial compression
The surface distributed force of the wing strut is equivalent to concentrated force by processing method, consequently facilitating being carried in its strength test
The application of lotus, equivalent process mainly comprise the steps that
S1, the global finite element model for establishing the wing strut and its both ends jointing, in the global finite element
In model, the wing strut stress includes axial compression load and surface distributed force；
S2, by the wing strut along its it is axial it is isometric be divided into several segments, a finite element node is taken on either segment, is calculated
The wing strut the first deformation in the case of by axial compression load and surface distributed force simultaneously, and record any described limited
First lateral displacement of first node；
S3, using wing strut bending direction in step s 2 as the application direction of concentrated force；
The initial set power is applied direction point by the concentrated force determined in step S3 by S4, a given initial set power
It does not act on each finite element node of the wing strut, any finite element node is at the same time by identical with step S2
Corresponding one second deformation in the case of axial compression load and initial set power is found out in several second deformations with described first
Immediate equivalent deformation is deformed, and records the second lateral displacement of any finite element node, by the equivalent deformation pair
The finite element node answered applies point as concentrated force；
S5, the second lateral displacement under maximum value and corresponding node in the first lateral displacement of each finite element node is calculated
Ratio, using the initial set power by the amplified power size of the ratio as the size of new concentrated force, using described
New concentrated force repeats step S4-S5, until the first lateral displacement and the second side are less than threshold value to shift differences.
Preferably, in the step S2, the wing strut is not less than 10 sections along the number of segment that it is axially divided.
It is preferably in the above scheme, in the step S2, the finite element node is located on the end face of either segment,
And the spacing between each finite element node is identical.
Be preferably in the above scheme, in the step S2, the first side of any finite element node to
Displacement is the average value of the node lateral displacement under the distributed force of different series surfaces.
It is preferably in the above scheme, the series of the surface distributed force is not less than 3 grades.
Be preferably in the above scheme, multi-level table force per unit area include using strut close to unstability when load series as
Afterbody, and other load series are retrodicted with 10% differential.
It is preferably in the above scheme, in the step S3, by the wing strut in step s 2 last
Application direction of the bending direction of grade surface distributed force as concentrated force.
It is preferably in the above scheme, in the step S5, the threshold value is 3%.
Present invention introduces an equivalent concentrated forces to substitute surface non-uniform dispersion force everywhere, that is, pass through a concentrated force
Carry out all surface distributed force suffered by equivalent strut surfaces.The position that the concentrated force applies is determined by theoretical comparative analysis
And size.In strength test, can determine whether strut is full by applying axial compression load and the concentrated force of strut
Sufficient Intensity Design simplifies test load.
Detailed description of the invention
One preferred embodiment of the equivalent way of surface distributed force when Fig. 1 is wing strut axial compression of the present invention
Flow chart.
Fig. 2 is schematic diagram of the wing strut by axial compression load and surface distributed force of embodiment illustrated in fig. 1.
Fig. 3 is that the equivalent front and back node of wing strut concentrated force of embodiment illustrated in fig. 1 deviates comparison schematic diagram.
Fig. 4 is position, direction and the big logotype of the equivalent rear concentrated force of embodiment illustrated in fig. 1.
Specific embodiment
To keep the purposes, technical schemes and advantages of the invention implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the present invention
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall within the protection scope of the present invention.Under
Face is described in detail the embodiment of the present invention in conjunction with attached drawing.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom" "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the present invention
The limitation of range.
The present invention is described in further details below by embodiment.
For the aircraft using diagonal brace rod-type wing, wing strut is easy to happen unstability when bearing axial compression load
To lose bearing capacity, while the distributed force that the also effect of wing strut surfaces has aerodynamic loading to generate, this but will be dropped significantly
Low its compresses bearing capacity, and in order to verify the intensity of strut, when test must apply above two load, for strut both ends
The load such as stretching, torsion can directly apply, and for its surface distributed force then since shape contact area etc. is difficult to by reality
Situation applies, for this purpose, present invention introduces an equivalent forces to reach above-mentioned purpose, i.e., by a concentrated force come equivalent strut table
All surface distributed force suffered by face.
Therefore, the determination process of concentrated force mainly includes following three aspect in the present embodiment:
Determine the application direction of concentrated force；
Determine the application position of concentrated force；
Determine the size of concentrated force.
As shown in Figure 1, when wing strut axial compression of the present invention surface distributed force equivalent way, mainly include with
Lower step:
S1, the global finite element model for establishing the wing strut and its both ends jointing, in the global finite element
In model, the wing strut stress includes axial compression load and surface distributed force；
S2, by the wing strut along its it is axial it is isometric be divided into several segments, a finite element node is taken on either segment, is calculated
The wing strut the first deformation in the case of by axial compression load and surface distributed force simultaneously, and record any described limited
First lateral displacement of first node；
S3, using wing strut bending direction in step s 2 as the application direction of concentrated force；
The initial set power is applied direction point by the concentrated force determined in step S3 by S4, a given initial set power
Do not act on each finite element node of the wing strut, any finite element node at the same time by with identical axis in step S2
Corresponding one second deformation, finds out in several second deformations and becomes with described first in the case of to compressive load and initial set power
The immediate equivalent deformation of shape, and the second lateral displacement of any finite element node is recorded, the equivalent deformation is corresponding
Finite element node as concentrated force apply point；
S5, the second lateral displacement under maximum value and corresponding node in the first lateral displacement of each finite element node is calculated
Ratio, using the initial set power by the amplified power size of the ratio as the size of new concentrated force, using described
New concentrated force repeats step S4-S5, until the first lateral displacement and the second side are less than threshold value to shift differences.
It should be noted that the wing strut is not less than 10 sections along the number of segment that it is axially divided in the present embodiment
It is understood that the present embodiment for wing strut surface distributed force using an equivalent concentrated force come
Processing, so that load is more convenient when test, as shown in Fig. 2, in addition to wing strut both ends or in which the axial direction of one end application
Other than the load of 25933N, several surface distributed forces are also distributed at each surface in axial direction, in fact, these surfaces
Distributed force size, direction etc. may be different, or even the surface distributed force direction having is mutually on the contrary, this is difficult to during the test
Apply, for this purpose, the present invention is replaced using concentrated force, as shown in figure 4, be it is equivalent after a 450N concentrated force, below it is right
Its direction, size, the determination method of position are described in detail.
Firstly, in step sl, establishing the finite element model of wing strut, the connection including strut ontology and both ends is connect
Head, both ends carry out hinged constraint by the actual conditions of structure, and load includes axial compression load and surface distributed force, such as Fig. 2 institute
Show.
Secondly, in step s 2, progress node division first, by wing strut ontology along its axial equal part in the present embodiment
Be 25 sections, it comprises 25 sections, finite element node is located on the end face of either segment in (or section), and each finite element node it
Between spacing it is identical.In alternate embodiment, finite element node also be can be set on each section of center.
In the present embodiment, in the step S2, the first lateral displacement of any finite element node is difference
The average value of the node lateral displacement under the distributed force of series surface.For example, the Nonlinear FEM by considering geometrical large distortion
Analysis method, the deformation under by axial compression load and surface distributed load effect at the same time of Wings strut, and record
80%, on 90%, 100%, 110% and 120% 5 lower 25 section of load series finite element node lateral displacement,
In, the average value of all node lateral displacements on each section can be chosen as the lateral displacement at the section, can also be incited somebody to action
Lateral displacement under every level-one load carries out record mark, as shown in figure 3, horizontal axis indicates stay length direction, the longitudinal axis is section
The lateral displacement of point, coordinate origin is the bottom terminal ends of strut, by taking solid line in diagram as an example, indicates the node under raw payload
Lateral displacement situation, i.e., in step s 2, before not equivalent concentrated force, the side of each finite element node under surface distributed force effect
To misalignment.
The series of surface distributed force of the present invention is not less than 3 grades, and the present embodiment is illustrated for 5 grades, wherein
100% load is test requirements document load, and the load more than 100% is overload, and 120% load is collapsing load, multistage surface
Distributed force include using strut close to unstability when load series retrodict other load grades as afterbody, and with 10% differential
Number, i.e., in the present embodiment, first determine 120% load as afterbody, thus retrodict locate 110% load, 100% load,
90% load and 80% load, it should be noted that the selection of load series is it is desirable that the series where 100% load is
Intermediate series, i.e., if load when unstability is 130%, differential is 10%, then generally chooses 7 load series；If unstability
When load be 120%, differential is 5%, then generally choose 9 load series.
In the present embodiment, first have to determine the application direction of concentrated force by this method, specifically, in the step S3
In, using the bending direction of the afterbody surface distributed force of the wing strut in step s 2 as the application side of concentrated force
To the direction of the application of concentrated force should make strut by curved direction and the final unstability of the calculated strut in front (120% load)
Bending direction is identical.
Followed by determine the position of concentrated force, as shown in step s 4, first initially the size of a given concentrated force is
400N is applied on 25 sections by the direction determined in step S3 one by one, while considering the axial compression load of strut, respectively
Calculate each case lower supporting rod deformation, and record lower 25 sections of 5 load series at lateral displacement, then with step 3
In the lateral displacement that is calculated compare, by comparison, it was found that under same load series, concentrated force be applied to the 16th
(from strut lower end to upper end number) at section, the ratio that load simplifies each section lateral displacement in front and back is closest, i.e. load letter
Deformation form and the simplification for changing rear pole are preceding closest, it is thus determined that concentrated force is applied at the section.
As shown in figure 3, dotted line indicates the drift condition of each node when applying concentrated force, two changes of equivalent front and back are determined
The whether identical modes such as variance that can introduce of shape situation are determined, for example, the two lines any node of equivalent front and back includes
One difference, the variance of 25 differences is smaller, indicates that the shape of this two lines is closer.It further include leading in alternate embodiment
It crosses the way of contrast such as standard deviation or parabola opening angle and determines whether the shape of two lines approaches.
Present invention introduces an equivalent concentrated forces to substitute surface non-uniform dispersion force everywhere, that is, pass through a concentrated force
Carry out all surface distributed force suffered by equivalent strut surfaces.The position that the concentrated force applies is determined by theoretical comparative analysis
And size.In strength test, can determine whether strut is full by applying axial compression load and the concentrated force of strut
Sufficient Intensity Design simplifies test load.
Finally determine that the size for applying concentrated force is known by the calculating of front in 100% load series in step S5
When, as shown in figure 3, the 14th section (from strut lower end to upper end) at lateral displacement it is maximum, load simplifies its lateral position of front and back
Moving ratio is 1.12, therefore new concentrated force size is 400N*1.12=448N.
Since the relationship between concentrated force size and node lateral displacement is non-linear relation, the present embodiment finally can be with
Cyclic check is carried out, i.e., in new concentrated force, new concentrated force is replaced into initial set power, repeats step S4-S5, directly
Curve to equivalent front and back is almost the same, in the present embodiment, specifically according to new concentrated force size, while considering the axial direction of bar
Compressive load calculates the deformation of strut, by being compared with strut lateral displacement obtained in abovementioned steps, 80%, 90%,
100%, 110% is consistent with the lateral displacement of finite element node on lower 25 sections of 120% 5 load series, it will be understood that
In the present embodiment, if the lateral displacement of two nodes is less than 3%, it is believed that lateral displacement is consistent, if inconsistent, using 448N as
New concentrated force repeats step S4 and S5.The distributed force of strut surfaces is finally reduced to a concentrated force, such as final determining
Concentrated force size 450N, be axially applied at the 16th section perpendicular to strut (from strut lower end to upper end number).
Finally it is noted that the above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Present invention has been described in detail with reference to the aforementioned embodiments for pipe, those skilled in the art should understand that: it is still
It is possible to modify the technical solutions described in the foregoing embodiments, or part of technical characteristic is equally replaced
It changes；And these are modified or replaceed, the essence for technical solution of various embodiments of the present invention that it does not separate the essence of the corresponding technical solution
Mind and range.
Claims (8)
1. the surface of the wing strut is distributed by the equivalent way of surface distributed force when a kind of wing strut axial compression
Power is equivalent to concentrated force characterized by comprising
S1, the global finite element model for establishing the wing strut and its both ends jointing, in the global finite element model
In, the wing strut stress includes axial compression load and surface distributed force；
S2, by the wing strut along its it is axial it is isometric be divided into several segments, a finite element node is taken on either segment, described in calculating
The first deformation in the case of by axial compression load and surface distributed force simultaneously of wing strut, and record any finite element section
First lateral displacement of point；
S3, using wing strut bending direction in step s 2 as the application direction of concentrated force；
S4, a given initial set power, apply direction by the concentrated force determined in step S3 for the initial set power and make respectively
With on each finite element node of the wing strut, any finite element node is at the same time by axial pressure identical with step S2
Corresponding one second deformation, finds out in several second deformations and deforms most with described first in the case of contracting load and initial set power
Close equivalent deformation, and record the second lateral displacement of any finite element node has the equivalent deformation is corresponding
First node is limited as concentrated force and applies point；
The ratio of the second lateral displacement under maximum value and the maximum value corresponding node in S5, the first lateral displacement of calculating, will
The initial set power presses size of the amplified power size of the ratio as new concentrated force, uses the new concentrated force
Step S4-S5 is repeated, until the first lateral displacement and the second side are less than threshold value to shift differences,
S6, apply point and concentrated force size according to the concentrated force finally determined to wing strut application active force.
2. the equivalent way of surface distributed force when wing strut axial compression as described in claim 1, it is characterised in that:
In the step S2, the wing strut is not less than 10 sections along the number of segment that it is axially divided.
3. the equivalent way of surface distributed force when wing strut axial compression as described in claim 1, it is characterised in that:
In the step S2, the finite element node is located on the end face of either segment, and the spacing between each finite element node is identical.
4. the equivalent way of surface distributed force when wing strut axial compression as described in claim 1, it is characterised in that:
In the step S2, the first lateral displacement of any finite element node is the section under the distributed force of different series surfaces
The average value of point lateral displacement.
5. the equivalent way of surface distributed force when wing strut axial compression as claimed in claim 4, it is characterised in that:
The series of the surface distributed force is not less than 3 grades.
6. the equivalent way of surface distributed force when wing strut axial compression as claimed in claim 5, it is characterised in that:
Multi-level table force per unit area include using strut close to unstability when load series retrodict it as afterbody, and with 10% differential
Its load series.
7. the equivalent way of surface distributed force when wing strut axial compression as claimed in claim 6, it is characterised in that:
In the step S3, the bending direction of the afterbody surface distributed force using the wing strut in step s 2 is as concentration
The application direction of power.
8. the equivalent way of surface distributed force when wing strut axial compression as described in claim 1, it is characterised in that:
In the step S5, the threshold value is 3%.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610323059.3A CN105825035B (en) | 2016-05-16 | 2016-05-16 | The equivalent way of surface distributed force when a kind of wing strut axial compression |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610323059.3A CN105825035B (en) | 2016-05-16 | 2016-05-16 | The equivalent way of surface distributed force when a kind of wing strut axial compression |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105825035A CN105825035A (en) | 2016-08-03 |
| CN105825035B true CN105825035B (en) | 2019-03-22 |
Family
ID=56529689
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610323059.3A Active CN105825035B (en) | 2016-05-16 | 2016-05-16 | The equivalent way of surface distributed force when a kind of wing strut axial compression |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105825035B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108414170B (en) * | 2018-03-15 | 2019-05-10 | 哈尔滨工业大学 | Stiffness measurement device under a kind of synchronous loading environment of large-size axis parts shape part bending |
| CN109490114B (en) * | 2018-12-12 | 2021-05-07 | 中国航空工业集团公司西安飞机设计研究所 | Full-size fatigue test flap load loading method |
| CN109490098B (en) * | 2018-12-14 | 2021-07-16 | 中国航空工业集团公司西安飞机设计研究所 | Method for improving test precision of wing body joint test |
| CN109807269B (en) * | 2019-01-02 | 2020-06-23 | 中国原子能科学研究院 | Design method of special-shaped building blank |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08298246A (en) * | 1995-04-27 | 1996-11-12 | Nec Kyushu Ltd | Wafer boat |
| CN103364170A (en) * | 2013-07-05 | 2013-10-23 | 北京航空航天大学 | Ground simulation predicting method and system for aeroelasticity stability |
| CN103630346A (en) * | 2013-11-19 | 2014-03-12 | 北京航空航天大学 | Test table and test method of emergency breaking off pin of undercarriage |
| CN104778325A (en) * | 2015-04-21 | 2015-07-15 | 北京云道智造科技有限公司 | Surface element-based surface load processing method and surface element-based surface load processing device |
-
2016
- 2016-05-16 CN CN201610323059.3A patent/CN105825035B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08298246A (en) * | 1995-04-27 | 1996-11-12 | Nec Kyushu Ltd | Wafer boat |
| CN103364170A (en) * | 2013-07-05 | 2013-10-23 | 北京航空航天大学 | Ground simulation predicting method and system for aeroelasticity stability |
| CN103630346A (en) * | 2013-11-19 | 2014-03-12 | 北京航空航天大学 | Test table and test method of emergency breaking off pin of undercarriage |
| CN104778325A (en) * | 2015-04-21 | 2015-07-15 | 北京云道智造科技有限公司 | Surface element-based surface load processing method and surface element-based surface load processing device |
Non-Patent Citations (1)
| Title |
|---|
| 某型客机主起落架收放动力学分析及试验方法研究;樊蕊;《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》;20150215;第C031-126页 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105825035A (en) | 2016-08-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105825035B (en) | The equivalent way of surface distributed force when a kind of wing strut axial compression | |
| CN105930616B (en) | A kind of aircraft moves the load distribution method of aerofoil statically indeterminate structure | |
| CN110516293B (en) | Finite element calculation method for ultimate bearing capacity under bending, shearing and twisting combined action of midship structure | |
| CN110983977A (en) | Method for calculating initial tension of suspender of beam-arch combined bridge | |
| CN109092944A (en) | A kind of large complicated curvature component accurate forming method | |
| AU722639B2 (en) | A method for testing the stability of vertically anchored masts | |
| CN205715111U (en) | A kind of column and the attachment structure of crossbeam | |
| CN105857638B (en) | A kind of wing loads loading device | |
| CN106339604B (en) | A kind of pressurized strut piston rod calculating method for stability | |
| CN105117519B (en) | Electrostatic drive step type micro cantilever structure evaluation method and system | |
| CN103207206A (en) | Stagnation temperature computing method of bending steel members | |
| Ilgamov | Bending and stability of a thin plate under vacuuming its surfaces | |
| CN205831525U (en) | A kind of folding bedstead | |
| CN108170893A (en) | A kind of length of unstressed cable of cable-stayed bridge computational methods, device, terminal and storage medium | |
| CN111506956A (en) | Controllability design method for extra-large cross-chamber supporting structure | |
| CN110501166B (en) | Method for simulating deformation moment of pump backswing engine in inflation state | |
| CN107862142B (en) | Method for analyzing mechanical strength of slotted casing | |
| CN111368483A (en) | Supporting structure slope stability evaluation method based on finite element strength reduction method | |
| Becque | Solutions to simplified von Kármán plate equations | |
| WO2008001348A2 (en) | Method for estimating the strength of bodies and structures | |
| CN207157490U (en) | It is a kind of can it is preset fracture angle broken plate | |
| CN109340286A (en) | The method that multistage gradual change steel-degree band spring, vehicle and multistage gradual change steel-degree band spring manufacture and design | |
| Esche et al. | The effect of modeling parameters and bending on two-dimensional sheet metal forming simulation | |
| CN110704947B (en) | Load loading method of inner cavity structure calculation model with vertical ribs | |
| CN110605822A (en) | Method for manufacturing long rod-shaped MIM product in non-shaping state |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |