5240.3.ComposeIT - User Documentation

8/13/2019 5240.3.ComposeIT - User Documentation

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ComposeITStrength Analysis of composite laminates for the yachting industry

User guide

November 2012

DEV/UG/ComposeIT/rev 7

MARINE DIVISIONDEVELOPMENT DEPARTMENT

67/71 Boulevard Du Chteau92571 Neuilly-sur-Seine: + 33 (0)1 55 24 74 60: + 33 (0)1 55 24 70 27

: [email protected]


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ComposeIT user guide

Bureau Veritas 2 / 32

Chapter 1: GENERAL COMMENTS ....................................................................................... 31.1 Software purpose .................................................................................................... 31.2 Rules applied .......................................................................................................... 31.3 Axis systems ........................................................................................................... 3

1.3.1 Global Axis System .......................................................................................... 31.3.2 Local Axis System ............................................................................................ 4

Chapter 2: DATA INPUT ........................................................................................................ 51.1 Ship Data ................................................................................................................ 51.2 Individual Layer Data ............................................................................................... 6

1.2.1 Adding an individual layer ................................................................................ 61.2.2 Individual layer Form for Unidirectional, Woven Roving, Mat ............................ 61.2.3 Individual layer Form for User Defined Layer ................................................... 71.2.4 Deleting, duplicating an individual layer ............................................................ 8

1.3 Laminate Data ......................................................................................................... 91.3.1 Adding a laminate ............................................................................................ 91.3.2 Laminate input form: Global presentation ......................................................... 91.3.3 Selecting an layer ............................................................................................101.3.4 Defining a new layer ........................................................................................10

1.3.5 Laminate input form: Other functionalities .......................................................121.3.6 Deleting, Duplicating a Laminate ....................................................................121.4 Plate Data ..............................................................................................................13

1.4.1 Adding a Plate .................................................................................................131.4.2 Plate General Data ..........................................................................................131.4.3 Plate loaded with Pressures ............................................................................141.4.4 Plate loaded with Forces .................................................................................141.4.5 Plate loaded with Deformations .......................................................................141.4.6 Deleting, Duplicating a Plate ...........................................................................15

1.5 Stiffener Data .........................................................................................................151.5.1 Adding a Stiffener ............................................................................................151.5.2 Stiffener General Data .....................................................................................16

1.5.3 Stiffener loaded with Pressures .......................................................................181.5.4 Stiffener loaded by Forces ..............................................................................181.5.5 Stiffener loaded by Deformation ......................................................................191.5.6 Deleting, Duplicating a Stiffener ......................................................................19

Chapter 3: RESULTS DISPLAY ........................................................................................... 201.1 Global Laminate Parameters ..................................................................................201.2 Laminate results by load ........................................................................................21

1.2.1 Key concepts ..................................................................................................211.2.2 Calculation point ..............................................................................................221.2.3 Calculation status ............................................................................................221.2.4 In-plane criterias: 1, 2, 12, Tsa Wu ...........................................................231.2.5 Interlaminar criterias: IL1, IL2 ......................................................................24

1.3 Laminate results summarized for all loads ..............................................................251.4 Plate Results ..........................................................................................................26

1.4.1 Computing a plate ...........................................................................................261.4.2 Plate under external loading ............................................................................261.4.3 Plate Buckling Check ......................................................................................28

1.5 Stiffener Results .....................................................................................................291.5.1 Computing a stiffener ......................................................................................291.5.2 Stiffener under external loading .......................................................................29

1.6 Report Display and Printing ....................................................................................301.6.1 Print Commands .............................................................................................301.6.2 Report Browser ...............................................................................................31

Chapter 4: INTEROPERABILITY WITH SteelWin SOFTWARE ............................................ 321.1 Introduction ............................................................................................................321.2 General Calculation Process ..................................................................................32


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Chapter 1: GENERAL COMMENTS

1.1 Software purpose

ComposeIT is a software developed by Bureau Veritas which allows the detailedstrength analysis of composite panels or stiffeners for yachting industry.

ComposeIT provides an user interface to define Individual layers, laminates, plates,stiffeners, and loads on these structural elements.

Composite then checks that criteria required by the rules are met, layer by layer.

1.2 Rules applied

ComposeIT is written according to:

Rules for the classification and the certification of yachts, March 2012BV Reference: NR 500 DT R01 E

Hull in Composite Materials and Plywood, Material Approval, DesignPrinciples, Construction and Survey, March 2012BV Reference: NR 546 DT R00 E

Important Warning:The software ComposeIT is only dedicated for the analysis of composite

structure for YACHTS. The safety coefficient introduced in this software may not beused other ship types than YACHTS.

1.3 Axis systems

1.3.1 Global Axis System

For each laminate, plate or stiffener, ComposeIT uses a global axis system {x, y, z}

Laminates / platesEach laminate or plate taken individually is supposed to lay in {x , y } plane.(exception : web of a stiffener)

{x} is an arbitrary chosen axis. It is referred as laminates global axis.Usually {x} axis is taken as the ship longitudinal axis

{x} is the reference axis to define the orientation of each individual layer inside thelaminate. See figure (1)


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Stiffener

{x} is taken as the stiffener axis .

1.3.2 Local Axis System

For each layer of a laminate, ComposeIT use a local axis system {1, 2, 3}.These local axis systems are defined by the rules, depending of individual layer type.For unidirectional, see NR546, Sec 5, [3.1.1]For woven roving, see NR546, Sec 5, [3.2.1]

The orientation between each individual layers local axis and laminates global axisis defined in figure (1)

Figure (1) - Orientation of individual layer


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Chapter 2: DATA INPUT

1.1 Ship Data

Name, Builder, Description, Section Number: text strings for information purpose

Rule Length: ship rule length

Note:Length is used when calculating dynamical amplification coefficientfor panels under slamming and impact loads (see NR546, Sec 6, [5.3.2])

Fabrication Process: Default fabrication process for laminates. May be overriddenfor each laminate.


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1.2 Individual Layer Data

Individual Layers are parts of a catalog. There are 4 catalogs: Unidirectional,Woven Roving, Mat, and User Defined

Creating an individual layer enriches the catalog of layers that will be later

instantiated in a laminate.

1.2.1 Adding an individual layer

In object tree, right-click on either Unidirectional, Woven Roving, Mat,User Defined and then click Add. Corresponding input form is then shown.

1.2.2 Individual layer Form for Unidirectional, Woven Roving, Mat

Fibre, Resin: Raw materials chosen amongst those defined in NR546, Sec 4

Blue fields are input data fields. Green fields are computed fields, refreshed each

time an input data is modified.

Elastic coefficients are computed according to NR546, Sec 5, [3]Breaking stresses are computed according to NR546, Sec 5, [5.1.1]


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1.2.3 Individual layer Form for User Defined Layer

Choosing user Defined type, user is able to enter manually all coefficients, allbreaking stresses of an individual layer.

This possibility allows simulating behaviour of layers made with materials still notmentioned by the rules.

Only actual value will be computed for such layers, as knowing rule value requiresreal experimentations in laboratories.

Layer Type: Reinforcement Fabric or Core

This parameter has following influence:- if core is chosen , Sig1, Sig2, Tau12 stresses will be computed at

top and bottom of each layer .If reinforcement fabric is chosenstresses will be computed at middle.

- If core is chosen, laminates including this layer will be consideredas Sandwich laminates.

Notations:

Results are given in layer local axis {1,2,3}

E1,E2 : youngs moduli in direction 1,2

Nu12, Nu21: Poissons coefficients

G12,G12,G13: shear moduli

Sig1 T: tensile breaking stress in the direction 1 (main direction) of the layer.

Sig2 T: tensile breaking stress in the direction 2 of the layer.

Sig1 C :compressive breaking stress in the direction 1

Sig2 C :compressive breaking stress in the direction 2

Tau12 : in-plane breaking stress

TauIL1,TauIL2 : interlaminar breaking stresses in direction 1 and 2


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1.2.4 Deleting, duplicating an individual layer

In object tree, right-click on an existing Individual layer.

Delete removes the individual layer, and all the layers using it in all the laminates.

Duplicate creates an exact copy of the individual layer with a different name


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This form allows building a laminate layer by layer. Left part of the formcontains tools to help user to add layers, and right part shows laminate inconstruction.

As mentioned, layers are added under the selected line. It is thus necessarythat selected line is visible on screen.

Users may add layers through two ways:

By selecting a layeralready defined with Individual layer forms.This is the most straightforward way.

By defining a new layer:This is the way to define a new layer on the fly.

1.3.3 Selecting an layer

1) Click on Unidirectional, Woven Roving Mat , or User Defined radiobutton to select a catalog and make appear available correspondinglayers.

2) Click then on a layer to instantiate this layer in the laminate with anangle (a small dialog box allow you to enter angle)

1.3.4 Defining a new layer

1) Choose a Type:

Select Unidirectional, Woven Roving or Mat, to create a new

individual layer. This individual layer will be added to the laminate and also tothe corresponding individual layer catalog.

Select Core to create a core material layer.Created layer wont be added to any catalog. There is no catalog of users

created Core material.

Select Adhesive to create an adhesive layer.Created layer wont be added to any catalog. There is no catalog of users

created Adhesive material.


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1.3.5 Laminate input form: Other functionalities

Duplicate Layers:

User is able to duplicate last input layers (maximum 5 last layers), orduplicate any group of contiguous layers (Choose layers option)User can also duplicate any single layer by right-clicking on it.

Mirror Laminate :

This function mirrors the laminate. It means existing layers are duplicatedand resulting new layers are added in reverse order they have been added.

Important: Last layer is not mirrored if it is an adhesive layer or a corelayer.

Delete Layer :

Removes the selected (yellow) layer from the laminate.User can also delete any single layer by right-clicking on it.

1.3.6 Deleting, Duplicating a Laminate

In object tree, right-click on an existing laminate.

Delete removes the laminate, and all the plates and stiffeners using it

Duplicate creates an exact copy of the laminate with a different name.

Duplicate as laminate for web flange creates an exact copy of the laminatewith a different name, and places it under Laminate for web flange node.


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1.4 Plate Data

1.4.1 Adding a Plate

Right-click on Bottom , Side, Deck or Bulkhead node then add.These nodes are for classification purpose only.

1.4.2 Plate General Data

Label: Plate label, users choice

Laminate: A laminate amongst Laminates for plating

Length of side along x: Plate dimension along {x} axis of chosen laminate.(See 1.3 Axis systems). Referenced as a in NR 546,Sec6, [5] ,fig. 6

Length of side along y:Plate dimension along {y} axis of chosen laminate.Referenced as b in NR 546, Sec6, [5] ,fig. 6


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Width of Omega Base along x: To be valued in case of shell plating withstiffener wide base. Referenced as Ws,x in NR 546,Sec6, [5] ,fig. 7

Width of Omega Base along y: To be valued in case of shell plating withstiffener wide base. Referenced as Ws,y in NR 546,Sec6, [5] ,fig. 7

1.4.3 Plate loaded with Pressures

Users may define four pressure loads for a plate. Four load types are alsoavailable. Load Types and plate location are not connected. It is thus possible todefine a Bottom Slamming load on a Side plate.

Load Type: Hydrostatic, Bottom Slamming, Side Shell ImpactLoad Type affects plate calculation methodology. See NR 546,

Sec6, [5] and safety coefficients values NR500, Pt. B, Ch. 7, Sec 4 [1.4]

P: Pressure Value, always positive.

Pressed layer of Laminate: Indicates on which side of the plate pressure isapplied

1.4.4 Plate loaded with Forces

User may load a plate directly with forces. Part B, Ch 9 describes the

methodology to compute forces given a pressure and a load type. But, in somecases, user may find interesting to input directly forces he computed with anothermethodology.

6 forces may be input to compute in-plain strains, as described in NR 546,Sec6, [3.2.1]

2 forces may be input to perform interlaminate shear analysis, as in NR 546,Sec6, [3.3.1]

A load type is required to set safety coefficients.

1.4.5 Plate loaded with Deformations

User may also input directly global deformations for a plate. 3 deformations areavailable, on a total of 6. (See NR 546, Sec6, [3.2.1] )

0

x : Tensile or compression strain of the middle plane of the laminate in X direction.0

y : Tensile or compression strain of the middle plane of the laminate in Y direction.

0

xy : Shear strain of the middle plane of the laminate in X direction.

A load type is required to set safety coefficients.


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1.4.6 Deleting, Duplicating a Plate

Right-click on an existing plate:

Delete removes the plate

Duplicate creates an exact copy with a different name

1.5 Stiffener Data

1.5.1 Adding a Stiffener

Right-click on Bottom , Side, Deck or Bulkhead node then add..Note1: Added stiffeners are ordinary stiffeners by default.

Note2: If Deck location is chosen, reduction coefficients calculated in NR 546, Sec7, [3.2.1] (Bending and shear check calculation) are taken equal to 1( deck ordinarystiffener case)


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1.5.2 Stiffener General Data

Label: Stiffener label, users choice

Attached plating Laminate: A laminate amongst Laminates for plating

Web Laminate: A laminate amongst Laminates for Web / Flange

Flange Laminate: A laminate amongst Laminates for Web / Flange

Type: Stiffener section Type amongst Angle, T, Flat, Omega

Note: If Omega is chosen, Web laminate will be automaticallymirrored to reflect that an Omega has two identical webs. User shouldonly input one half of the total web.

Web height, flange width(mm) stiffener dimensions

Span, spacing: (m). these data are used to compute Moment and forcesapplied on a stiffener NR 546, Sec 7, [3.2.1]

Attached Plating Width: (mm). This data is used to compute geometricalcharacteristics of a stiffener (see NR 546, Sec 7, [2])Attached plating width may be different than spacing. SeeNR 546, Sec 7, [2.1.2])

End Conditions: Stiffener end conditions as described in see NR 546,Sec7,[3.1.2] . These end conditions influence bending moment

and shear force calculation for an ordinary stiffenersustaining lateral pressure. NR 546,Sec 7,[3.2.1]Note: this parameter has no influence when loading

stiffener directly with forces.


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Stiffener Orientation

Parallel to x axis of attached plating

Normal to x axis of attached plating

Stiffener Position: Vertical or Horizontal

This data drives pressures calculation for hydrodynamic loads.When stiffener is Vertical, 2 pressures are needed, Plowand Pup,tocompute Lateral pressures used in NR 546,Sec 7,[3.2.1]

Stiffener On, Web On:

These data allow building a stiffener model taking into accountthe way Attached plating, web, and flanges are assembled.

In example below, stiffener is connected to the layerN ofattached plating laminate, and stiffener web is connected to Layer1 offlange laminate. This is the default configuration when creating astiffener

Input data:

xy

Attached plating

xy

Flange

xy

Attached plating

xy

Flange


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Corresponding model:

1.5.3 Stiffener loaded with PressuresUsers may define four loads for a stiffener. Four load types are also available.Load Types and plate location are not connected. It is thus possible to define aBottom Slamming load on a Side stiffener.

Load Type: Hydrostatic, Bottom Slamming, Side Shell ImpactLoad Type affects stiffener calculation methodology and safetycoefficients values.See NR 546,Sec 7,[3.2.1] and NR500, Pt. B, Ch. 7, Sec 4 [1.4]

P/ Pup: Pressure Value, always positive. In case of an Hydrostatic load

on a vertical stiffener, this value is the pressure at the top ofstiffener

Plow: In case of an Hydrostatic load on a vertical stiffener, this valueis the pressure at the bottom of stiffener

Pressed layer of Attached plating: Indicates on which side of the Attachedplating pressure is applied

1.5.4 Stiffener loaded by Forces

User may load a stiffener directly with forces.

3 input forces are available:-Bending moment Mxand shear force Tyz as See NR 546,Sec 7,[3.2.1]-Normal force Nxin the main axis of stiffener

A load type is required to set safety coefficients

SEM2RM+4UD

Web

LAM1Layer 1

Layer N

Layer N

Layer 1


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1.5.5 Stiffener loaded by Deformation

User may load a stiffener directly with a deformation EpsXin the main axis ofstiffener.

Each stiffener part is submitted to the same deformation EpsX.

A load type is required to set safety coefficients

1.5.6 Deleting, Duplicating a Stiffener

Right-click on an existing stiffener:

Delete removes the stiffener

Duplicate creates an exact copy with a different name


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Chapter 3: RESULTS DISPLAY

1.1 Global Laminate Parameters

Click on Compute Results icon in Laminate Input Form:

In the lower part of screen, a result form is then displayed:

Results displayed are obtained from NR546, Sec6, [2]

In case of a sandwich Laminate, Three set of results are displayed: Globalresults for the whole laminate, and results for the two skins.

Note: Results for skins does not take into account adhesive layers.


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1.2.2 Calculation point

In general, ComposeIT checks by the above methodology 6 criteria by layer:

1 (Sigma1) : local stress in {1} axis

2 (Sigma2) : local stress in {2} axis 12 (Tau12) : local stress in {1,2} plane

Combined : Tsai-Wu combined stress NR500, Pt., Chap 7, Sec 4, [1.4.3]

IL1 (TauIL1) : Interlaminar local stress in 1 local axis

IL2 (TauIL2) : Interlaminar local stress in 2 local axis

For a pressure load on a plate, ComposeIT checks the plate at 2 locations,named A and B .( See picture below )The reason is that bending moments are different at these two locations.

1.2.3 Calculation status

After computing a plate or a stiffener, a calculation status is displayed in thetree.

: Calculation is successful, and all criteria are met.

: Calculation is successful, but at least one criterion is not met.

: Calculation has failed. Please check your date or contactassistance.


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1.2.4 In-plane criteria: 1, 2, 12, Tsa Wu

For criteria 1, 2, 12 following values are displayed for each individual

layer of the laminate

An Actual value: computed as NR546, Sec6, [3.2.3] , at mid-thicknessofeach individual layer.

A Rule value: computed as NR546, Sec5, [5.1.1]

A Ratio value: computed as: rule value / actual value

A Safety Factor (SF) value: computed as NR500,Pt B, Ch 7, Sec 4, [1.4.1]

If Ratio is Inferior to Safety Factor, Cell is colored in red

Example:1 detailed results display for 3 layers.

For combined criterion (Tsa Wu) following values are displayed

An Actual value: computed as NR546, Sec6, [1.3.3]


If Actual value is inferior to Safety Factor, Cell is colored in red

Example: Tsa Wu detailed results display for 3 layers.


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1.2.5 Interlaminar criteria: IL1, IL2

following values are displayed:

An Actual value: computed as NR 546, Sec 6, [3.3.2]

Note: IL1,IL2 are also referenced as 23 and 13 in the rules

A Rule value: computed as NR546, Sec5, [5.1.1]

A Ratio value: computed as: rule value / actual value


If Ratio is Inferior to Safety Factor, Cell is colored in red


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1.3 Laminate results summarized for all loads

For a laminate loaded by several loads, a synthetic view of layers resistanceis available

For each load and for each of the six previously defined criteria, a ratiocomparable to 1 have been defined:

Ratio (load) =

)valueActual

valueRule(

FactorSafety

For each criterion, and each load, if Ratio is inferior to 1, then criterion is met.

Once all Ratios are calculated for every load, a Global Ratio is defined as themaximum of these ratios for all loads

Global Ratio = ))(( loadRatioMaxLOADS

Example:1 synthesis results display for 3 layers.

If Global Ratio is superiorto 1, Cell is colored in red.Then:For Layer 1, for Load P4 (at least), Criteria 1 is not metFor Layer 3, Criteria 1 is met for all loads, and Load P1 gives the mostsevere results.


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1.4 Plate Results

1.4.1 Computing a plate

Right-click on a Plate node and click on Analyse Plate, or use generalCompute Menu.

1.4.2 Plate under external loading

Synthesis of results for all loads defined on a plate is immediately visible onthe lower part of the screen.

Note :

P1Astands for results computed at location A of a plate under P1 pressureloadP1Bstands for results computed at location B of a plate under P1 pressure

load


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To view detailed results, click on Show details. A pop-up panel then appears:

Detailed results panels contains one tab per load

All tabs may be printed through Print and Preview buttons.

For pressure loads, user can select 3 sets of results:

o Results at Location Ao Results at Location Bo Synthesis Results: this view shows for each layer, what location (A or

B) is the most critical, for each criterion.

Tabs

Location choice


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1.4.3 Plate Buckling Check

Buckling check is performed according to NR 546, Sec 6, [4]

Note:Only Rule values are computed, and also required safety factor.

ComposeIT does not compute actual value in the plate, and therefore criteria cannotbe checked directly with the software


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1.5 Stiffener Results

1.5.1 Computing a stiffener

Right-click on a Plate node and click on Analyse Stiffener, or use generalCompute Menu.

1.5.2 Stiffener under external loading

Synthesis Results are available for attached plating, web, and flange.Click on radio Button to select which part to display

Click on Show details to see corresponding detailed results.


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On Detailed results view, it is possible to click on another radio button to view resultsfor other parts.

1.6 Report Display and Printing

1.6.1 Print Commands

Print Data and Print Results command are available under File Menu.They respectively trigger the creation of a data report and a result report in a PDFformat.


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5240.3.ComposeIT - User Documentation