CN103984803A - Finite element load application method - Google Patents
Finite element load application method Download PDFInfo
- Publication number
- CN103984803A CN103984803A CN201410156494.2A CN201410156494A CN103984803A CN 103984803 A CN103984803 A CN 103984803A CN 201410156494 A CN201410156494 A CN 201410156494A CN 103984803 A CN103984803 A CN 103984803A
- Authority
- CN
- China
- Prior art keywords
- load
- finite element
- point
- distributed
- node
- 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.)
- Granted
Links
Landscapes
- Management, Administration, Business Operations System, And Electronic Commerce (AREA)
- Feedback Control In General (AREA)
Abstract
The invention, which belongs to the field of aircraft designs, relates to a finite element load application method. The finite element load application method is characterized by comprehensively taking the affection of the simplification or distribution of various loads on calculation results and the difficulty level of loading implementation into consideration, the finite element load application method divides aircraft loads into concentrated loads and distributed loads and divides the distributed loads into subareas; nodes to be loaded are chosen from a finite element model and divided into subareas according to the pattern of the distributed load subareas; the concentrated loads and the distributed loads are respectively applied. When the method is adopted to carry out finite element model loading, the precision of engineering calculation can be met, and moreover, computers can be conveniently used for batch processing.
Description
Technical field
The invention belongs to airplane design field, relate to a kind of applying method of finite element load.
Background technology
Finite element is the important means of present generation aircraft intensive analysis, and in finite element model, the order of accuarcy of load applying is directly connected to the correctness of result of calculation.Applying of finite element load is exactly that the various load on aircaft configuration are discrete to finite element node, and this is a complexity, time-consuming, the difficult work accurately realizing, and this work at present does not also have unified implementation method and evaluation criterion.
Summary of the invention
This patent provides a kind of finite element load applying method, and the method has considered various load to be simplified or the discrete impact on result of calculation, and loads the complexity realizing.Adopt this method to carry out finite element loading and can meet engineering calculation precision, and computing machine batch processing easy to use.
Technical scheme of the present invention is: a kind of finite element load applying method, it is characterized in that, and comprise the steps:
The first, Aircraft Load is divided into centre-point load and distributed load, and distributed load is carried out to subregion by structure;
The second, in finite element model, pick out the node that will load, and the node that will load carries out subregion by the form of distributed load subregion;
The 3rd, the method that applies centre-point load is: centre-point load is added on finite element interdependent node; Applying distributed load step is:
A) distributed load of a certain subregion and finite element are loaded to node all by principle of identity division reference section;
B) the distributed load integration between two reference sections is asked to gross load P and load point m, then by the method for mechanics equivalence, load p is assigned on two adjacent reference sections, size is respectively Pa and Pb, and the load point on reference section is ma and mb;
C) on reference section, load application point place sets up node, and load p a and Pb are applied on the load point ma and mb of reference section.
D) on load point and reference section, each finite element loads between node and sets up MPC(RBE3) unit;
E) all subregions are all pressed to the step operation of a-d, completed applying of full machine distributed load.
Described load point refers to that the concentrated force applying at that point does not produce moment of flexure.
Described " MPC unit ", refers at load point and the internodal a kind of multi-point constraint of finite element, and the load that makes to be added on load point is converted on finite element node by mathematical formulae.
Described " reference section " refers to the natural structure existing on aircraft, for aerofoil, generally refers to rib, for fuselage, generally refers to frame.
Described " node that will load ", refers to the node existing in finite element model, adds load and can not exert an influence to the correctness of analysis result on these nodes.
Described " method of mechanics equivalence ", refer to lever principle by a certain load distribution to adjacent two reference sections.
Advantage of the present invention is: considered various load and simplified or the discrete impact on result of calculation, and loaded the complexity realizing, when guaranteeing loading accuracy, made load applying process simplification, be convenient to program and implement.
Accompanying drawing explanation
Accompanying drawing 1 is the subregion of certain aircraft distributed load
The applying method of accompanying drawing 2 wing distributed loads
Between accompanying drawing 3 reference sections and load point, set up MPC
Embodiment
Below by specific embodiment, also the present invention is described in further detail by reference to the accompanying drawings.
One, take the load applying of certain aircraft is research object, finds out the centre-point load in all load of this aircraft, comprises engine load, guided missile load, radar load, and distributed load is divided into fuselage, wing, horizontal tail, four subregions of vertical fin, sees accompanying drawing 1.
Two, select the node that can load in finite element model, and select finite element node is carried out to subregion by accompanying drawing 1.
Three, engine load is added to the joint that engine is connected with body, guided missile load is added to the joint that guided missile is connected with body, radar load is added to radar in the fixed point of fuselage.
Four, the subregion of wing is pressed to rib and divided reference section, distributed load P and load point m that adjacent two intercostals of integral and calculating are total, and by lever principle, P is dispensed on adjacent reference section, load is respectively Pa and Pb, load point is respectively ma and mb, sees shown in accompanying drawing 2.
Five, at ma place and the imposed load Pa of mb place and Pb, and set up MPC unit between the finite element node on ma and mb and reference section.According to said method complete the load applying of all aerofoil subregion reference sections.
Six, the same wing of the scheme that applies of fuselage, horizontal tail, vertical fin distributed load, the reference section of fuselage is frame section.
Claims (1)
1. a finite element load applying method, is characterized in that,
Aircraft Load is divided into centre-point load and distributed load, and distributed load is carried out to subregion by structure;
In finite element model, pick out the node that will load, and the node that will load carries out subregion by the form of distributed load subregion;
The method that applies centre-point load is: centre-point load is added on finite element interdependent node;
Applying distributed load step is:
A) distributed load of a certain subregion and finite element are loaded to node all by principle of identity division reference section;
B) the distributed load integration between two reference sections is asked to gross load P and load point m, then by the method for mechanics equivalence, load p is assigned on two adjacent reference sections, size is respectively Pa and Pb, and the load point on reference section is ma and mb;
C) on reference section, load application point place sets up node, and load p a and Pb are applied on the load point ma and mb of reference section;
D) on load point and reference section, each finite element loads between node and sets up MPC unit;
E) all subregions are all pressed to the step operation of a-d, completed applying of full machine distributed load.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410156494.2A CN103984803B (en) | 2014-04-17 | 2014-04-17 | Finite element load application method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410156494.2A CN103984803B (en) | 2014-04-17 | 2014-04-17 | Finite element load application method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103984803A true CN103984803A (en) | 2014-08-13 |
| CN103984803B CN103984803B (en) | 2017-02-15 |
Family
ID=51276772
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410156494.2A Active CN103984803B (en) | 2014-04-17 | 2014-04-17 | Finite element load application method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103984803B (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105701305A (en) * | 2016-01-18 | 2016-06-22 | 东风柳州汽车有限公司 | CAE load-step automatic setting method |
| CN106021781A (en) * | 2016-05-31 | 2016-10-12 | 中国航空工业集团公司西安飞机设计研究所 | General plane fuselage axis type load processing method |
| CN106156444A (en) * | 2016-07-27 | 2016-11-23 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft aerodynamic loading processing method and strength of aircraft computational methods |
| CN108052711A (en) * | 2017-11-29 | 2018-05-18 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of coupled thermal mechanical method of parallel combination engine installation structure |
| CN109684679A (en) * | 2018-12-04 | 2019-04-26 | 中国航空工业集团公司西安飞机设计研究所 | A kind of dome-shaped reinforcing frame Parameters design for bearing antisymmetry concentrfated load |
| CN110008521A (en) * | 2019-03-11 | 2019-07-12 | 东南大学 | A kind of distribution dynamic loading Time domain identification method based on subregion interpolation |
| CN113553736A (en) * | 2021-06-25 | 2021-10-26 | 江苏锐天信息科技有限公司 | Method for quickly loading structural finite elements |
| CN113704878A (en) * | 2021-08-05 | 2021-11-26 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for applying landing gear load to aircraft structure full-aircraft finite element model |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6125333A (en) * | 1997-11-06 | 2000-09-26 | Northrop Grumman Corporation | Building block approach for fatigue spectra generation |
| CN101710360A (en) * | 2009-12-23 | 2010-05-19 | 西北工业大学 | Optimization design method of skeleton structure of airplane assembly tool |
| CN102750408A (en) * | 2012-06-08 | 2012-10-24 | 中国航空工业集团公司西安飞机设计研究所 | Pull rod installing layout method of airplane auxiliary power device |
| CN103324778A (en) * | 2013-01-05 | 2013-09-25 | 中国航空工业集团公司西安飞机设计研究所 | Ground load determination method of multi-fulcrum airplane |
-
2014
- 2014-04-17 CN CN201410156494.2A patent/CN103984803B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6125333A (en) * | 1997-11-06 | 2000-09-26 | Northrop Grumman Corporation | Building block approach for fatigue spectra generation |
| CN101710360A (en) * | 2009-12-23 | 2010-05-19 | 西北工业大学 | Optimization design method of skeleton structure of airplane assembly tool |
| CN102750408A (en) * | 2012-06-08 | 2012-10-24 | 中国航空工业集团公司西安飞机设计研究所 | Pull rod installing layout method of airplane auxiliary power device |
| CN103324778A (en) * | 2013-01-05 | 2013-09-25 | 中国航空工业集团公司西安飞机设计研究所 | Ground load determination method of multi-fulcrum airplane |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105701305A (en) * | 2016-01-18 | 2016-06-22 | 东风柳州汽车有限公司 | CAE load-step automatic setting method |
| CN106021781A (en) * | 2016-05-31 | 2016-10-12 | 中国航空工业集团公司西安飞机设计研究所 | General plane fuselage axis type load processing method |
| CN106156444A (en) * | 2016-07-27 | 2016-11-23 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft aerodynamic loading processing method and strength of aircraft computational methods |
| CN108052711A (en) * | 2017-11-29 | 2018-05-18 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of coupled thermal mechanical method of parallel combination engine installation structure |
| CN109684679A (en) * | 2018-12-04 | 2019-04-26 | 中国航空工业集团公司西安飞机设计研究所 | A kind of dome-shaped reinforcing frame Parameters design for bearing antisymmetry concentrfated load |
| CN109684679B (en) * | 2018-12-04 | 2023-05-26 | 中国航空工业集团公司西安飞机设计研究所 | Parameter design method for circular arch reinforcement frame bearing antisymmetric concentrated load |
| CN110008521A (en) * | 2019-03-11 | 2019-07-12 | 东南大学 | A kind of distribution dynamic loading Time domain identification method based on subregion interpolation |
| CN113553736A (en) * | 2021-06-25 | 2021-10-26 | 江苏锐天信息科技有限公司 | Method for quickly loading structural finite elements |
| CN113553736B (en) * | 2021-06-25 | 2024-06-07 | 江苏锐天智能科技股份有限公司 | Structure finite element quick loading method |
| CN113704878A (en) * | 2021-08-05 | 2021-11-26 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for applying landing gear load to aircraft structure full-aircraft finite element model |
| CN113704878B (en) * | 2021-08-05 | 2023-10-10 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for applying load of landing gear by using aircraft structure full-aircraft finite element model |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103984803B (en) | 2017-02-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103984803A (en) | Finite element load application method | |
| Liu et al. | Vortex dynamics and new lift enhancement mechanism of wing–body interaction in insect forward flight | |
| CN105975645B (en) | A kind of aircraft flow field of region containing shock wave quick calculation method based on multistep | |
| Mian et al. | Numerical investigation of structural geometric nonlinearity effect in high-aspect-ratio wing using CFD/CSD coupled approach | |
| Buning et al. | CFD approaches for simulation of wing-body stage separation | |
| CN107633117B (en) | Global sensitivity analysis method based on Gaussian process model | |
| CN113609600B (en) | Multi-body separation compatibility measurement and characterization method suitable for aircraft | |
| Sitaraman et al. | Rotor loads prediction using helios: A multisolver framework for rotorcraft aeromechanics analysis | |
| Oruc et al. | Towards real-time pilot-in-the-loop CFD simulations of helicopter/ship dynamic interface | |
| Rasquin et al. | Scalable fully implicit finite element flow solver with application to high-fidelity flow control simulations on a realistic wing design | |
| Tesfahunegn et al. | Surrogate-based airfoil design with space mapping and adjoint sensitivity | |
| CN109325279A (en) | A kind of method of discrete aircraft aerodynamic loading parametrization | |
| Clifton et al. | Determining the stability and control characteristics of high-performance maneuvering aircraft using high-resolution CFD simulation with and without moving control surfaces | |
| Timmermans et al. | Aeroelastic Challenges in the Aircraft Design Process | |
| Skujins et al. | Toward an unsteady aerodynamic ROM for multiple mach regimes | |
| Da Ronch et al. | Benchmarking CEASIOM software to predict flight control and flying qualities of the B-747 | |
| Ghoreyshi et al. | From spreadsheets to simulation-based aircraft conceptual design | |
| Hadjiev et al. | Comparative Investigation of VLM Codes for Joined-Wing Analysis | |
| Meckstroth | An Evaluation of Aerodynamic Analysis Software for use in Aircraft MDO | |
| Wang et al. | Static aeroelastic analysis of flexible aircraft with large deformations | |
| Moreno-Ramos et al. | Computationally efficient simulation of unsteady aerodynamics using POD on the fly | |
| Eliasson et al. | Acceleration of URANS for application to separated high-lift flows | |
| Hoke et al. | Comparison of overset grid and grid deformation techniques applied to 2-dimensional naca airfoils | |
| Liu et al. | Static aeroelasticity analysis of high aspect ratio wing and the jig-shape design based on multi-block structural grid | |
| Qiu et al. | Aircraft preliminary design stage Inertia load distribution optimization |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |