CN114996868B - Pin seat strength analysis method - Google Patents
Pin seat strength analysis method Download PDFInfo
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- CN114996868B CN114996868B CN202210543510.8A CN202210543510A CN114996868B CN 114996868 B CN114996868 B CN 114996868B CN 202210543510 A CN202210543510 A CN 202210543510A CN 114996868 B CN114996868 B CN 114996868B
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- 238000004458 analytical method Methods 0.000 title claims abstract description 15
- 230000005540 biological transmission Effects 0.000 claims abstract description 5
- 238000004088 simulation Methods 0.000 claims 1
- 238000000034 method Methods 0.000 abstract description 3
- 238000001125 extrusion Methods 0.000 description 2
- 238000003780 insertion Methods 0.000 description 2
- 230000037431 insertion 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
- 230000000694 effects Effects 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
- 238000012546 transfer Methods 0.000 description 1
Classifications
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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
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- General Engineering & Computer Science (AREA)
- Computer Hardware Design (AREA)
- Computational Mathematics (AREA)
- Mathematical Analysis (AREA)
- Mathematical Optimization (AREA)
- Pure & Applied Mathematics (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention provides a pin seat strength analysis method, and belongs to the field of connection analysis. According to the invention, the direct load transmission between the pin and the pin seat is accurately simulated by a finite element method, so that the strength analysis of the pin seat is accurately completed. The invention has wide application space in connection analysis of aviation, aerospace, automobiles and the like, is also suitable for calculation of nail seats or sleeves with non-rectangular wall cross sections and lugs subjected to eccentric loads, and has wide application prospect in practical engineering.
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 inserted into a sleeve or into a pin holder or socket, and a cross section taken along a centerline of the parallel pin is typically rectangular or nearly rectangular. The pin is loaded in the pin seat mainly by extrusion load, and the extrusion 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 inability of existing engineering methods to accurately calculate the direct load transfer between the pin and the pin holder.
Disclosure of Invention
The invention aims at overcoming the defects of the existing method, and provides a pin seat strength analysis method which can accurately simulate the direct load transmission 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 seat strength analysis method, comprising the steps of:
Step 1, obtaining the maximum linear distribution support reaction w 1 on the pin base through the following formula:
Wherein P represents a concentrated load acting on the pin; a represents the distance from the concentrated load acting point to the end head of the pin seat; l denotes the depth of insertion of the pin into the pin seat.
And 2, taking a pin seat section structure, and establishing a detail finite element model, wherein the pin seat section structure is simulated by adopting a shell unit, and the thickness of the shell unit adopted by the pin seat section structure is set to be 1mm.
And 3, taking a pin profile structure corresponding to the pin seat, and establishing a detail finite element model, wherein the pin profile structure is simulated by adopting a shell unit, and the thickness of the shell unit adopted by the pin profile structure is set to be 1mm.
And 4, establishing a nonlinear gap unit (CGAP unit) between the pin profile structure and the pin seat profile structure to simulate mutual contact.
And 5, applying a detail finite element model boundary constraint consisting of the steps 2, 3 and 4 and applying the maximum linear distribution branch counter force w 1 obtained in the step 1 at the bottom of the pin profile, wherein the applied detail finite element model boundary constraint comprises the following steps: the constraint pin seat bottom all nodes in 6 degrees of freedom and the constraint pin bottom node in 5 of 6 degrees of freedom, while the released degree of freedom is the constraint consistent with the direction of the concentrated load P acting on the pin in step 1.
And 6, obtaining 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 calculation of nail seats or sleeves with non-rectangular wall cross sections and lugs subjected to eccentric loads, and has wide application prospect in practical engineering.
Drawings
FIG. 1 is a flow chart of a pin seat strength analysis method embodying the present invention.
Fig. 2 is an axial cross section of a pin and pin holder.
Fig. 3 is a schematic diagram of a finite element model.
Wherein, the concentrated load of P effect on the pin, a concentrated load action point to the distance of pin seat end, L pin inserts the degree of depth in the pin seat, the biggest linear distribution branch counter force on the w1 pin seat, the linear distribution branch counter force of the deepest in the pin seat is inserted to the pin on the w2 pin seat.
Detailed Description
The following describes specific embodiments of the present invention in detail with reference to the drawings.
As shown in fig. 1, a pin seat strength analysis method includes the following steps:
Step 1, obtaining a maximum linear distribution support reaction force w 1 (shown in fig. 2) on a pin seat through the following formula;
Wherein P represents a concentrated load acting on the pin; a represents the distance from the concentrated load acting point to the end head of the pin seat; l denotes the depth of insertion of the pin into the pin seat.
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 1mm.
And 3, taking the geometric dimension of the pin profile structure corresponding to the pin seat, establishing a detailed finite element model of the pin profile structure corresponding to the pin seat through finite element preprocessing software, simulating the pin profile structure by adopting a two-dimensional shell unit, and setting the thickness of the shell unit adopted by the pin profile structure to be 1mm.
And 4, establishing a nonlinear CGAP unit between the pin profile structure and the pin seat profile structure through finite element preprocessing software, setting related information such as contact clearance, contact rigidity and the like of the CGAP unit, and simulating mutual contact between the pin profile structure and the pin seat profile structure through the CGAP unit (gap unit) (shown in figure 3).
And 5, applying boundary constraint to the detail finite element model formed by the steps 2, 3 and 4 through finite element preprocessing software, and simultaneously applying the maximum linear distribution branch counter force w 1 obtained by the formula (1) in the step 1 at the bottom of the pin profile, wherein the applied detail finite element model boundary constraint is as follows: the 6 degrees of freedom on all nodes at the bottom of the constraint pin seat, the 5 degrees of freedom on the nodes at the bottom of the constraint pin, release the constraint consistent with the direction of the concentrated load P acting on the pin in step 1.
And 6, further finishing load working condition setting aiming at the detail finite element model and the applied boundary constraint and load in the step 5, and obtaining 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 examples described above represent only embodiments of the invention and are not to be understood as limiting the scope of the patent of the invention, it being pointed out that several variants and modifications may be made by those skilled in the art without departing from the concept of the invention, which fall within the scope of protection of the invention.
Claims (1)
1. A pin seat strength analysis method, comprising the steps of:
Step 1, obtaining the maximum linear distribution support reaction w 1 on the pin base through the following formula:
wherein P represents a concentrated load acting on the pin; a represents the distance from the concentrated load acting point to the end head of the pin seat; l represents the depth of the pin inserted into the pin seat;
Step 2, taking a pin seat section structure, and establishing a detail finite element model, wherein the pin seat section structure is simulated by adopting a shell unit, and the thickness of the shell unit adopted by the pin seat section structure is set to be 1mm;
Step 3, taking a pin profile structure corresponding to the pin seat, and establishing a detail finite element model, wherein the pin profile structure is simulated by adopting a shell unit, and the thickness of the shell unit adopted by the pin profile structure is set to be 1mm;
step 4, establishing nonlinear gap unit simulation mutual contact between the pin profile structure and the pin seat profile structure;
and 5, applying a detail finite element model boundary constraint consisting of the steps 2, 3 and 4 and applying the maximum linear distribution branch counter force w 1 obtained in the step 1 at the bottom of the pin profile, wherein the applied detail finite element model boundary constraint comprises the following steps: constraining 6 degrees of freedom on all nodes at the bottom of the pin seat and 5 degrees of freedom on the nodes at the bottom of the pin, wherein the released degrees of freedom are constraints consistent with the direction of the concentrated load P acting on the pin in the step 1;
And 6, obtaining 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 CN114996868B (en) | 2022-05-18 | 2022-05-18 | Pin seat strength analysis method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210543510.8A CN114996868B (en) | 2022-05-18 | 2022-05-18 | Pin seat strength analysis method |
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| Publication Number | Publication Date |
|---|---|
| CN114996868A CN114996868A (en) | 2022-09-02 |
| CN114996868B true CN114996868B (en) | 2024-06-14 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202210543510.8A Active CN114996868B (en) | 2022-05-18 | 2022-05-18 | Pin seat strength analysis method |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2692668B2 (en) * | 1995-10-31 | 1997-12-17 | 日本電気株式会社 | Contact analysis method and system using finite element method |
| US7467070B2 (en) * | 2004-10-26 | 2008-12-16 | Meyer Eric S | Methods and systems for modeling stress intensity solutions for integrally stiffened panels |
| CN107577846B (en) * | 2017-08-07 | 2021-02-26 | 许继集团有限公司 | A method for determining the strength of a wind turbine nacelle cover |
| CN108959835B (en) * | 2018-09-28 | 2023-10-13 | 苏州上声电子股份有限公司 | Intensity simulation analysis method of loudspeaker basin stand in screw installation process |
| CN109726435B (en) * | 2018-12-04 | 2022-11-22 | 中国航空工业集团公司西安飞机设计研究所 | A Method for Calculating the Load of Joint Nail Group |
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2022
- 2022-05-18 CN CN202210543510.8A patent/CN114996868B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
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