CN107992656A - A kind of lower method for determining common frame sectional parameter of concentrfated load effect - Google Patents

A kind of lower method for determining common frame sectional parameter of concentrfated load effect Download PDF

Info

Publication number
CN107992656A
CN107992656A CN201711175402.5A CN201711175402A CN107992656A CN 107992656 A CN107992656 A CN 107992656A CN 201711175402 A CN201711175402 A CN 201711175402A CN 107992656 A CN107992656 A CN 107992656A
Authority
CN
China
Prior art keywords
frame
parameter
msub
edge strip
common frame
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.)
Pending
Application number
CN201711175402.5A
Other languages
Chinese (zh)
Inventor
田晶晶
薛应举
张引利
尹凯军
陈卫锋
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Xian Aircraft Design and Research Institute of AVIC
Original Assignee
Xian Aircraft Design and Research Institute of AVIC
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Xian Aircraft Design and Research Institute of AVIC filed Critical Xian Aircraft Design and Research Institute of AVIC
Priority to CN201711175402.5A priority Critical patent/CN107992656A/en
Publication of CN107992656A publication Critical patent/CN107992656A/en
Pending legal-status Critical Current

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
    • 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
    • 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
    • G06F2119/06—Power analysis or power optimisation
    • 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
    • G06F2119/18—Manufacturability analysis or optimisation for manufacturability

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Theoretical Computer Science (AREA)
  • General Physics & Mathematics (AREA)
  • Evolutionary Computation (AREA)
  • General Engineering & Computer Science (AREA)
  • Computer Hardware Design (AREA)
  • Computational Mathematics (AREA)
  • Mathematical Analysis (AREA)
  • Mathematical Optimization (AREA)
  • Pure & Applied Mathematics (AREA)
  • Automation & Control Theory (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)

Abstract

The present invention relates to a kind of lower method for determining common frame sectional parameter of concentrfated load effect, belong to aircraft structure strength design field, it includes：1) concentrfated load P is assigned on interior edge strip, outer edge strip and frame web：2) respective geometric parameter is calculated according to interior edge strip, outer edge strip and the respective allowable load of frame web, geometric parameter is outer rim area of section, inner edge area of section and frame web thickness；3) after the completion of Section Design, FEM calculation and parameter optimization are carried out, determines final common frame sectional parameter.The concentrfated load effect of the present invention is lower to determine that the method for common frame sectional parameter primarily determines that common frame sectional parameter first by theoretical calculation, finite element analysis is carried out to structure again, a small amount of parameter optimization is only needed finally to determine sectional parameter of the common frame under concentrfated load effect on this basis, reduce the iterations of finite element analysis computation, save and calculate time and cost.

Description

A kind of lower method for determining common frame sectional parameter of concentrfated load effect
Technical field
The invention belongs to technical field of aircraft structure design, more particularly to a kind of lower definite common frame of concentrfated load effect The method of sectional parameter.
Background technology
The main function of the common frame of fuselage is the cross sectional shape for maintaining fuselage, and supporting function is played to covering and stringer.Commonly The Main Load that frame is born is the air force that covering is passed to fuselage, and distribution pressure caused by fuselage flexural deformation.Effect Another kind of load on common frame is the concentrfated load that other structures pass over, such as floor strut, the luggage of civil aircraft Holding bay, the freight transport system connector of military aircraft, two layers of floor joint, gas-tight door opener triangle rocker arm, steerable system are slided The structures such as wheel support.
Need to make the intensity of the common frame of use by finite element method (fem) analysis concentrfated load in the past, being such as unsatisfactory for intensity will Ask, then partial structurtes are strengthened, and finite element analysis is carried out again to strengthened structure, so iterate, until Meet intensity requirement.Finite element analysis requirement has accurate boundary condition, and Modeling Calculation heavy workload, design week Phase is longer.
The content of the invention
The task and purpose of the present invention is to obtain a kind of lower method for determining common frame sectional parameter of concentrfated load effect, To shorten the design cycle of common frame section under concentrfated load effect, change needs to iterate by finite element analysis in the past Calculate.
To reach above-mentioned purpose, the technical solution adopted by the present invention is：A kind of concentrfated load effect is lower to determine that common frame cuts open The method of face parameter, it includes
1) concentrfated load P is assigned on interior edge strip, outer edge strip and frame web：
2) respective geometric parameter, institute are calculated according to the interior edge strip, outer edge strip and the respective allowable load of frame web It is outer rim area of section, inner edge area of section and frame web thickness to state geometric parameter；
3) after the completion of Section Design, FEM calculation and parameter optimization are carried out, determines final common frame sectional parameter.
In a preferred embodiment of the invention, the formula that concentrfated load P is assigned on interior edge strip, outer edge strip and frame web is：
Outer frame edge load：
Frame inner edge load：
Frame web load：
In a preferred embodiment of the invention, the geometric parameter is outer rim area of section, inner edge area of section and frame web The computational methods of thickness are：
Outer edge strip compress allowable stress according to covering follow closely between unstability stress [σc] control, it can obtain common outer frame edge section Area：
Interior edge strip stretches tensile ultimate strength [σ of the allowable stress according to frame materialt] control, it can obtain common frame inner edge Area of section：
Frame web failure by shear allowable stress is according to shearing field computation：
The thickness of common frame web can be obtained：
The lower method for determining common frame sectional parameter of concentrfated load effect of the present invention is due to the use of theoretical calculation with having Finite element analysis, the method that is combined of optimization, common frame sectional parameter is primarily determined that first by theoretical calculation, then to structure into Row finite element analysis, only needs a small amount of parameter optimization finally to determine that common frame is made in concentrfated load on this basis Sectional parameter under, reduces the iterations of finite element analysis computation, and the design cycle shortens dramatically.
Brief description of the drawings
Attached drawing herein is merged in specification and forms the part of this specification, shows the reality for meeting the present invention Example is applied, and for explaining the principle of the present invention together with specification.
Fig. 1 is force analysis figure of the common frame under concentrfated load effect.
Fig. 2 is the common frame profile designed by full machine operating mode.
Fig. 3 is common frame diagrammatic cross-section under concentrfated load effect.
Embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction with the embodiment of the present invention Attached drawing, the technical solution in the embodiment of the present invention is further described in more detail.
The method and technology solution of common frame sectional parameter is determined under the concentrfated load effect of the present invention is：
1) concentrfated load P is assigned on interior edge strip, outer edge strip and frame web first：
Force analysis of the common frame under concentrfated load effect, two sides are assigned to by concentrfated load P with reference to shown in figure 1 Upward component PnAnd Pτ, and edge strip in common frame section, outer edge strip, frame web load are calculated respectively：
Outer edge strip load：
Interior edge strip load：
Frame web load：
2) respective geometric parameter is calculated according to respective allowable load；
Their preliminary geometric parameter can be designed that according to bonding force on common outer frame edge, inner edge, frame web.
Outer edge strip compress allowable stress according to covering follow closely between unstability stress [σc] control, it can obtain common outer frame edge area (section)：
Interior edge strip stretches tensile ultimate strength [σ of the allowable stress according to frame materialt] control, it can obtain common frame inner edge Area (section)：
Frame web failure by shear allowable stress is according to shearing field computation：
The thickness of common frame web can be obtained：
3) the common frame section according to designed by full machine operating mode is shown in Fig. 2；For diffusion joint concentrfated load, foundation The parameter that step 2 is calculated carries out structural strengthening on the basis of section shown in Fig. 2, and the common mount structure after being strengthened is such as Shown in Fig. 3.
4) after the completion of Section Design, FEM calculation, and parameter optimization is carried out, determines final common frame sectional parameter.
Section Design of the lower one side with the common frame of certain aircraft under the effect of crane load, carries out calculating verification.
1) according to its stand under load feature, calculation block inner edge, outer rim, the load of web, as shown in table 1：
Each position load of 1 frame of table
2) structural parameters of the interior edge strip of common frame, outer edge strip and web are primarily determined that according to above-mentioned parameter
Outer edge strip compress allowable stress according to covering follow closely between unstability stress [σc] control, then [σc]=280MPa, can obtain general Logical outer frame edge strip area：
Interior edge strip stretches tensile ultimate strength [σ of the allowable stress according to frame materialt] control, then [σt]=469MPa, Common frame inner edge area can be obtained：
Frame web failure by shear allowable stress is according to shearing field computation：
Wherein σb=405MPa, σ0.2=270MPa, τb=270MPa, by complete shearing field computation, tension field COEFFICIENT K takes 1。
The thickness that common frame web can be obtained is：
3) finite element analysis is carried out；
4) carry out Parameters Optimal Design is carried out, determines final common frame sectional parameter.
The lower method for determining common frame sectional parameter of concentrfated load effect of the present invention is due to the use of theoretical calculation with having Finite element analysis, the method that is combined of optimization, common frame sectional parameter is primarily determined that first by theoretical calculation, then to structure into Row finite element analysis, only needs a small amount of parameter optimization finally to determine that common frame is made in concentrfated load on this basis Sectional parameter under, reduces the iterations of finite element analysis computation, saves and calculates time and cost.
The above, is only the optimal embodiment of the present invention, but protection scope of the present invention is not limited to This, any one skilled in the art the invention discloses technical scope in, the change that can readily occur in or replace Change, should be covered by the protection scope of the present invention.Therefore, protection scope of the present invention should be with the guarantor of the claim Protect subject to scope.

Claims (3)

  1. A kind of 1. lower method for determining common frame sectional parameter of concentrfated load effect, it is characterised in that：Including
    1) concentrfated load P is assigned on interior edge strip, outer edge strip and frame web：
    2) respective geometric parameter is calculated according to the interior edge strip, outer edge strip and the respective allowable load of frame web, it is described several What parameter is outer rim area of section, inner edge area of section and frame web thickness；
    3) after the completion of Section Design, FEM calculation and parameter optimization are carried out, determines final common frame sectional parameter.
  2. 2. the lower method for determining common frame sectional parameter of concentrfated load effect according to claim 1, it is characterised in that collection The formula that middle load p is assigned on interior edge strip, outer edge strip and frame web is：
    Outer frame edge load：
    Frame inner edge load：
    Frame web load：
  3. 3. the lower method for determining common frame sectional parameter of concentrfated load effect according to claim 2, it is characterised in that institute Stating the computational methods that geometric parameter is outer rim area of section, inner edge area of section and frame web thickness is：
    Outer edge strip compress allowable stress according to covering follow closely between unstability stress [σc] control, it can obtain common outer frame edge area of section：
    Interior edge strip stretches tensile ultimate strength [σ of the allowable stress according to frame materialt] control, it can obtain common frame inner edge section face Product：
    Frame web failure by shear allowable stress is according to shearing field computation：
    <mrow> <msub> <mi>&amp;tau;</mi> <mrow> <mi>a</mi> <mi>l</mi> <mi>l</mi> </mrow> </msub> <mo>=</mo> <mn>0.9</mn> <msub> <mi>&amp;sigma;</mi> <mn>0.2</mn> </msub> <mo>&amp;lsqb;</mo> <mn>1</mn> <mo>+</mo> <mfrac> <mn>1</mn> <mn>2</mn> </mfrac> <msup> <mrow> <mo>(</mo> <mfrac> <msub> <mi>&amp;sigma;</mi> <mi>b</mi> </msub> <msub> <mi>&amp;sigma;</mi> <mn>0.2</mn> </msub> </mfrac> <mo>-</mo> <mn>1</mn> <mo>)</mo> </mrow> <mn>2</mn> </msup> <mo>&amp;rsqb;</mo> <mo>&amp;lsqb;</mo> <mfrac> <mn>1</mn> <mn>2</mn> </mfrac> <mo>+</mo> <msup> <mrow> <mo>(</mo> <mn>1</mn> <mo>-</mo> <mi>K</mi> <mo>)</mo> </mrow> <mn>3</mn> </msup> <msup> <mrow> <mo>(</mo> <mfrac> <msub> <mi>&amp;tau;</mi> <mi>b</mi> </msub> <msub> <mi>&amp;sigma;</mi> <mi>b</mi> </msub> </mfrac> <mo>-</mo> <mfrac> <mn>1</mn> <mn>2</mn> </mfrac> <mo>)</mo> </mrow> <mn>2</mn> </msup> <mo>&amp;rsqb;</mo> </mrow>
    The thickness of common frame web can be obtained：
CN201711175402.5A 2017-11-22 2017-11-22 A kind of lower method for determining common frame sectional parameter of concentrfated load effect Pending CN107992656A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201711175402.5A CN107992656A (en) 2017-11-22 2017-11-22 A kind of lower method for determining common frame sectional parameter of concentrfated load effect

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201711175402.5A CN107992656A (en) 2017-11-22 2017-11-22 A kind of lower method for determining common frame sectional parameter of concentrfated load effect

Publications (1)

Publication Number Publication Date
CN107992656A true CN107992656A (en) 2018-05-04

Family

ID=62032006

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201711175402.5A Pending CN107992656A (en) 2017-11-22 2017-11-22 A kind of lower method for determining common frame sectional parameter of concentrfated load effect

Country Status (1)

Country Link
CN (1) CN107992656A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109657337A (en) * 2018-12-14 2019-04-19 中国航空工业集团公司西安飞机设计研究所 A kind of bolted modeling method of Fast simulation single lap joint part
CN110276107A (en) * 2019-05-29 2019-09-24 上海宇航系统工程研究所 It is a kind of consider the more sphere tanks of spacecraft between weak dependence more sphere tank structural parameter determining methods

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170046462A1 (en) * 2012-10-09 2017-02-16 The Boeing Company Methods and systems for structural health monitoring
CN106503411A (en) * 2016-12-19 2017-03-15 中国航空工业集团公司沈阳飞机设计研究所 A kind of method for designing of fuselage primary load bearing reinforcing frame
CN106709185A (en) * 2016-12-26 2017-05-24 中国航空工业集团公司西安飞机设计研究所 Composite-material stiffened-plate stringer parameter determination method
US20170308633A1 (en) * 2016-04-26 2017-10-26 The Boeing Company System for finite element modeling and analysis of a structural product

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170046462A1 (en) * 2012-10-09 2017-02-16 The Boeing Company Methods and systems for structural health monitoring
US20170308633A1 (en) * 2016-04-26 2017-10-26 The Boeing Company System for finite element modeling and analysis of a structural product
CN106503411A (en) * 2016-12-19 2017-03-15 中国航空工业集团公司沈阳飞机设计研究所 A kind of method for designing of fuselage primary load bearing reinforcing frame
CN106709185A (en) * 2016-12-26 2017-05-24 中国航空工业集团公司西安飞机设计研究所 Composite-material stiffened-plate stringer parameter determination method

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109657337A (en) * 2018-12-14 2019-04-19 中国航空工业集团公司西安飞机设计研究所 A kind of bolted modeling method of Fast simulation single lap joint part
CN109657337B (en) * 2018-12-14 2023-04-18 中国航空工业集团公司西安飞机设计研究所 Modeling method for rapidly simulating bolt connection of single-side lap joint
CN110276107A (en) * 2019-05-29 2019-09-24 上海宇航系统工程研究所 It is a kind of consider the more sphere tanks of spacecraft between weak dependence more sphere tank structural parameter determining methods

Similar Documents

Publication Publication Date Title
CN106156449B (en) A kind of composite wing siding optimum design method
CN103752651B (en) Welding integral wallboard laser-impact straightening method
Shroff et al. Design, analysis, fabrication, and testing of composite grid-stiffened panels for aircraft structures
JP5666594B2 (en) A method for analytically determining the dimensions of each part of a reinforced panel by a computer
CN108153981A (en) A kind of composite material fuselage Material Stiffened Panel Post-Buckling Analysis of Structures method based on finite element analysis
JP3892652B2 (en) Creating a tire analysis model
CN103345545A (en) Method for predicating composite material Pi-shaped non-planar glue joint strength based on triangular envelopes
CN106202598B (en) The analysis method of residual compressive strength after a kind of damage of composite impact
CN107992656A (en) A kind of lower method for determining common frame sectional parameter of concentrfated load effect
CN105005671A (en) Dynamics simulation analysis method of uniformly distributed load bearing system
Denny et al. Conceptual design and numerical validation of a composite monocoque solar passenger vehicle chassis
CN107463746B (en) Method for calculating circumferential stress of fuselage bulkhead under airtight load
Reinoso et al. Postbuckling behaviour of a pressurized stiffened composite panel–Part I: Experimental study
CN106621621B (en) A kind of construction and method enhancing H-shaped section Column stability
JP2009538778A (en) Body structure and manufacturing method thereof
CN107247838A (en) The light weight method and device of automotive back door
CN111914351B (en) Method for calculating overall stability of reinforced wallboard of fuselage structure
CN105844039A (en) Method for evaluating local rigidity contribution degrees of body structure
CN105447249B (en) A kind of slow test load calculation method of power structure for pod
CN112141360A (en) Vertical fin box section test support dummy and test equipment
CN107451315A (en) A kind of strength check methods based on hatch door detail model
CN105912805A (en) Modeling method and device of finite element model of metal plate welding line
Oh et al. Buckling analysis of a composite shell with multiple delaminations based on a higher order zig-zag theory
CN109117569A (en) Collision finite element model modeling method with octagon spot welding heat-affected zone structure
CN106326502A (en) Computation method for static rigidity of support

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
RJ01 Rejection of invention patent application after publication

Application publication date: 20180504

RJ01 Rejection of invention patent application after publication