CN114996868A - Pin seat strength analysis method - Google Patents
Pin seat strength analysis method Download PDFInfo
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- CN114996868A CN114996868A CN202210543510.8A CN202210543510A CN114996868A CN 114996868 A CN114996868 A CN 114996868A CN 202210543510 A CN202210543510 A CN 202210543510A CN 114996868 A CN114996868 A CN 114996868A
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- 238000004458 analytical method Methods 0.000 title claims abstract description 14
- 230000005540 biological transmission Effects 0.000 claims description 3
- 238000000034 method Methods 0.000 abstract description 4
- 238000012546 transfer Methods 0.000 abstract description 3
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000003780 insertion Methods 0.000 description 2
- 230000037431 insertion Effects 0.000 description 2
- 230000000452 restraining effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000012407 engineering method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
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- 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]
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2111/00—Details relating to CAD techniques
- G06F2111/04—Constraint-based CAD
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The invention provides a pin boss strength analysis method, and belongs to the field of connection analysis. The invention accurately simulates the direct load transfer of the pin and the pin seat by a finite element method, thereby accurately completing the strength analysis of the pin seat. The invention has wide application space in connection analysis of aviation, aerospace, automobiles and the like, is also suitable for calculating a nail seat or a sleeve with a non-rectangular wall cross section and a lug of an eccentric load, and has wide actual engineering application prospect.
Description
Technical Field
The invention belongs to the field of connection analysis, and relates to a pin seat strength analysis method.
Background
The pin and pin holder connection is typically a pin having a circular cross-section that is inserted into a sleeve or pin or socket, and the cross-section taken along the centerline of the parallel pin is generally rectangular or nearly rectangular. The loading mode of the pin in the pin seat is mainly compression load, and the compression load depends on the fixed matching condition in the pin seat and the relative rigidity of the pin and the pin seat. This results in the fact that the existing engineering methods cannot accurately calculate the direct load transfer between the pin and the pin receptacle.
Disclosure of Invention
The invention aims to overcome the defects of the existing method, and provides a pin seat strength analysis method, which can accurately simulate the direct load transfer between a pin and a pin seat through a finite element method, so as to accurately complete the strength analysis of the pin seat.
The technical scheme of the invention is as follows:
a pin boss strength analysis method comprises the following steps:
step 1, obtaining the maximum linear distribution support reaction force w on the pin seat through the following formula 1 ：
Wherein P represents a concentrated load acting on the pin; a represents the distance from the concentrated load action point to the end of the pin seat; l represents the depth of insertion of the pin into the pin holder.
And 2, taking a pin seat sectional structure, establishing a detail finite element model, simulating the pin seat sectional structure by using a shell unit, and setting the thickness of the shell unit adopted by the pin seat sectional structure to be 1 mm.
And 3, taking a pin section structure corresponding to the pin seat, establishing a detailed finite element model, simulating the pin section structure by using a shell unit, and setting the thickness of the shell unit adopted by the pin section structure to be 1 mm.
And 4, establishing nonlinear gap units (CGAP units) between the pin section structure and the pin seat section structure to simulate mutual contact.
Step 5, applying the boundary constraint of the detail finite element model composed of the step 2, the step 3 and the step 4 and applying the maximum linear distribution support reaction force w obtained in the step 1 to the bottom of the pin section 1 Wherein the applied detail finite element model boundary constraints comprise: and (3) constraining 6 degrees of freedom at all nodes at the bottom of the pin seat and constraining 5 of the 6 degrees of freedom at the nodes at the bottom of the pin, and the released degrees of freedom are constraints in the same direction as the concentrated load P acting on the pin in step 1.
And 6, solving the load transmission condition of the pin and the pin seat and the stress of the pin seat through a finite element nonlinear solver.
The invention has the beneficial effects that: the invention has wide application space in connection analysis of aviation, aerospace, automobiles and the like, is also suitable for calculating a nail seat or a sleeve with a non-rectangular wall cross section and a lug of an eccentric load, and has wide actual engineering application prospect.
Drawings
FIG. 1 is a flow chart of a pin holder strength analysis method implemented by the present invention.
Fig. 2 is an axial section of the pin and pin holder.
FIG. 3 is a schematic diagram of a finite element model.
The pin seat structure comprises a pin seat, a pin seat, a pin, a w2, a pin seat and a pin, wherein P is a concentrated load acting on the pin, a distance from a concentrated load acting point to the end of the pin seat, a depth of the L pin inserted into the pin seat, a maximum linearly distributed support reaction force on the w1 pin seat, and a linearly distributed support reaction force on the w2 pin seat at the deepest part of the pin inserted into the pin seat.
Detailed Description
The following describes the embodiments of the present invention in detail with reference to the technical solutions.
As shown in fig. 1, a method for analyzing pin boss strength includes the following steps:
step 1, obtaining the maximum linear distribution support reaction force w on the pin seat through the following formula 1 (as shown in FIG. 2);
wherein P represents a concentrated load acting on the pin; a represents the distance from the concentrated load action point to the end of the pin seat; l represents the depth of insertion of the pin into the pin holder.
And 2, taking the geometric dimension of the pin seat section structure, establishing a detailed finite element model of the pin seat section structure through finite element preprocessing software, simulating the pin seat section structure by adopting a two-dimensional shell unit, and setting the thickness of the shell unit adopted by the pin seat section structure to be 1 mm.
And 3, taking the geometric dimension of the pin section structure corresponding to the pin seat, establishing a detailed finite element model of the pin section structure corresponding to the pin seat through finite element preprocessing software, simulating the pin section structure by adopting a two-dimensional shell unit, and setting the thickness of the shell unit adopted by the pin section structure to be 1 mm.
And 4, establishing a nonlinear CGAP unit between the pin section structure and the pin seat section structure through finite element preprocessing software, setting relevant information such as contact gap, contact rigidity and the like of the CGAP unit, and simulating mutual contact between the pin section structure and the pin seat section structure through the CGAP unit (gap unit) (as shown in figure 3).
And 5, applying boundary constraint to a detailed finite element model formed by the steps 2, 3 and 4 through finite element preprocessing software, and applying the maximum linear distribution support reaction force w obtained through the formula (1) in the step 1 to the bottom of the pin section at the same time 1 Wherein the applied detail finite element model boundary constraints are: and (3) restraining 6 degrees of freedom on all nodes at the bottom of the pin seat, restraining 5 degrees of freedom on the nodes at the bottom of the pin, and releasing the restraint in the direction consistent with the direction of the concentrated load P acting on the pin in the step 1.
And 6, further finishing the setting of load working conditions aiming at the detail finite element model in the step 5 and the applied boundary constraint and load, and solving the load transmission condition of the pin and the pin seat and the stress of the pin seat through a finite element nonlinear solver.
The above-mentioned embodiments only express the embodiments of the present invention, but not should be understood as the limitation of the scope of the invention patent, it should be noted that, for those skilled in the art, many variations and modifications can be made without departing from the concept of the present invention, and these all fall into the protection scope of the present invention.
Claims (1)
1. A pin boss strength analysis method is characterized by comprising the following steps:
step 1, obtaining the maximum linear distribution support reaction force w on the pin seat through the following formula 1 ：
Wherein P represents a concentrated load acting on the pin; a represents the distance from the concentrated load action point to the end of the pin seat; l represents the depth of the pin inserted into the pin seat;
step 2, taking a pin seat sectional structure, establishing a detail finite element model, simulating the pin seat sectional structure by using a shell unit, and setting the thickness of the shell unit adopted by the pin seat sectional structure to be 1 mm;
step 3, taking a pin section structure corresponding to the pin seat, and establishing a detail finite element model, wherein the pin section structure is simulated by a shell unit, and the thickness of the shell unit adopted by the pin section structure is set to be 1 mm;
step 4, establishing nonlinear gap units between the pin section structure and the pin seat section structure to simulate mutual contact;
step 5, applying the boundary constraint of the detail finite element model composed of the step 2, the step 3 and the step 4 and applying the maximum linear distribution support reaction force w obtained in the step 1 to the bottom of the pin section 1 Wherein the applied detail finite element model boundary constraints comprise: 6 degrees of freedom on all nodes at the bottom of the constraint pin seat and 5 degrees of freedom in the 6 degrees of freedom on the nodes at the bottom of the constraint pin, wherein the released degrees of freedom are constraints in the direction consistent with the direction of the concentrated load P acting on the pin in the step 1;
and 6, solving the load transmission condition of the pin and the pin seat and the stress of the pin seat through a finite element nonlinear solver.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210543510.8A CN114996868A (en) | 2022-05-18 | 2022-05-18 | Pin seat strength analysis method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210543510.8A CN114996868A (en) | 2022-05-18 | 2022-05-18 | Pin seat strength analysis method |
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| CN114996868A true CN114996868A (en) | 2022-09-02 |
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| CN202210543510.8A Pending CN114996868A (en) | 2022-05-18 | 2022-05-18 | Pin seat strength analysis method |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH09145493A (en) * | 1995-10-31 | 1997-06-06 | Nec Corp | Contact analysis method using finite element method and its system |
| US20060089823A1 (en) * | 2004-10-26 | 2006-04-27 | The Boeing Company | Methods and systems for modeling stress intensity solutions for integrally stiffened panels |
| CN104133925A (en) * | 2014-04-17 | 2014-11-05 | 中国航空工业集团公司沈阳飞机设计研究所 | Nonlinear analysis method applicable to cockpit canopy structure static intensity |
| CN104965950A (en) * | 2015-07-02 | 2015-10-07 | 许继集团有限公司 | Method for calculating ultimate strength and fatigue strength of rear frame of fan |
| CN107577846A (en) * | 2017-08-07 | 2018-01-12 | 许继集团有限公司 | A kind of engine room cover of wind turbine strength determining method |
| CN109726435A (en) * | 2018-12-04 | 2019-05-07 | 中国航空工业集团公司西安飞机设计研究所 | A kind of method of connector nail group's LOAD FOR |
| WO2020063802A1 (en) * | 2018-09-28 | 2020-04-02 | 苏州上声电子股份有限公司 | Simulation and analysis method for speaker basket strength during screw mounting |
-
2022
- 2022-05-18 CN CN202210543510.8A patent/CN114996868A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH09145493A (en) * | 1995-10-31 | 1997-06-06 | Nec Corp | Contact analysis method using finite element method and its system |
| US20060089823A1 (en) * | 2004-10-26 | 2006-04-27 | The Boeing Company | Methods and systems for modeling stress intensity solutions for integrally stiffened panels |
| CN104133925A (en) * | 2014-04-17 | 2014-11-05 | 中国航空工业集团公司沈阳飞机设计研究所 | Nonlinear analysis method applicable to cockpit canopy structure static intensity |
| CN104965950A (en) * | 2015-07-02 | 2015-10-07 | 许继集团有限公司 | Method for calculating ultimate strength and fatigue strength of rear frame of fan |
| CN107577846A (en) * | 2017-08-07 | 2018-01-12 | 许继集团有限公司 | A kind of engine room cover of wind turbine strength determining method |
| WO2020063802A1 (en) * | 2018-09-28 | 2020-04-02 | 苏州上声电子股份有限公司 | Simulation and analysis method for speaker basket strength during screw mounting |
| CN109726435A (en) * | 2018-12-04 | 2019-05-07 | 中国航空工业集团公司西安飞机设计研究所 | A kind of method of connector nail group's LOAD FOR |
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