Composite Stress Analysis

Title of Document:(Three Lines Maximum)

FIXED TRAILING EDGESTRUCTURAL ANALYSIS

Doc. Number: RAS-CC670-203

Revision Letter: NC

Date (yyyy-mm-dd): 2000-04-20

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Total of pages : 126

Section number: 16

Section Title:(Two Lines Maximum)

OUTBOARD TRAILING EDGE BUTEDOOR, COMPOSITE PANELS

Initial Approval Names: DATE

PREPARED: SHELLEY CLARKE -----

CHECKED: JOHN HUDDART -----

APPROVED: SALAMON HARAVAN -----

BT0107-01 MW97 1999-03

Enter the applicable data in the respective fields below byclicking the text and do F9 to have the filling box .

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TEMPLATE PREPARED AND MODIFIED AS OF 1999-03-12

Bombardier Inc.Montréal, Canada

CAGE CODE 88308

BOMBARDIER INC., PAR L’INTERMÉDIAIRE DE SES GROUPES,DIVISIONS ET/OU FILIALES CORPORATIVES, FOURNIT LESPRÉSENTS RENSEIGNEMENTS AU GOUVERNEMENT À TITRECONFIDENTIEL. CES RENSEIGNEMENTS ONT UNE TENEURCONFIDENTIELLE, AVEC DROITS DE PROPRIÉTÉ, ET NOUS LESCONSIDÉRONS EXCLUS DE L’APPLICATION DE LA LOI SURL’ACCÈS À L’INFORMATION. ILS PEUVENT AUSSI CONSTITUER UNSECRET INDUSTRIEL DE NOTRE SOCIÉTÉ OU DE TIERCESPARTIES. LA DIVULGATION PUBLIQUE DE CES RENSEIGNEMENTSNUIRAIT À BOMBARDIER INC. OU À DES TIERCES PARTIES. TOUTEINTENTION DE LES DIFFUSER EN TOUT OU EN PARTIE DEVRAÊTRE SIGNIFIÉE À L’AVANCE ET PAR ÉCRIT AU VICE-PRÉSIDENTSERVICES JURIDIQUES , BOMBARDIER AÉRONAUTIQUE.

LES RENSEIGNEMENTS, LES DONNÉES ET DESSINSTECHNIQUES DIVULGUÉS DANS LES PRÉSENTES SONT LAPROPRIÉTÉ EXCLUSIVE DE BOMBARDIER INC. OU COMPORTENTDES DROITS DE PROPRIÉTÉ APPARTENANT À AUTRUI ET NEPEUVENT ÊTRE DIVULGUÉS À QUICONQUE NI UTILISÉS PAR QUIQUE CE SOIT SANS LE CONSENTEMENT ÉCRIT DE BOMBARDIERINC. LE DÉTENTEUR DES PRÉSENTES S’ENGAGE, DANS TOUTESCIRCONSTANCES, À GARDER CONFIDENTIELS LES DONNÉES ETDESSINS TECHNIQUES QU’ELLES CONTIENNENT. CE QUIPRÉCÈDE NE S’APPLIQUE PAS AUX PERSONNES QUI ONT DESDROITS DE PROPRIÉTÉ SUR CES RENSEIGNEMENTS, DONNÉESTECHNIQUES ET DESSINS DANS LA MESURE OÙ CES DROITSEXISTENT.

BOMBARDIER INC., BY ITS GROUPS, DIVISIONS AND/ORCORPORATE SUBSIDIARIES, PROVIDES THIS INFORMATION TOTHE GOVERNMENT IN CONFIDENCE. THIS IS PROPRIETARYCONFIDENTIAL INFORMATION WHICH WE CONSIDER EXCLUDEDFROM THE APPLICATION OF THE ACCESS TO INFORMATION ACTAND MAY ALSO BE TRADE SECRET OF OUR COMPANY OR THIRDPARTIES. PUBLIC RELEASE OF THIS INFORMATION WOULD BEHARMFUL TO BOMBARDIER INC. OR THIRD PARTIES. ANYINTENTION TO DISCLOSE SUCH INFORMATION, OR PARTTHEREOF, MUST BE INDICATED IN ADVANCE AND IN WRITING TOTHE VICE-PRESIDENT LEGAL SERVICES, BOMBARDIERAEROSPACE.

THE INFORMATION, TECHNICAL DATA AND DESIGNS DISCLOSEDHEREIN ARE THE EXCLUSIVE PROPERTY OF BOMBARDIER INC. ORCONTAIN PROPRIETARY RIGHTS OF OTHERS AND ARE NOT TO BEUSED OR DISCLOSED TO OTHERS WITHOUT THE WRITTEN CONSENTOF BOMBARDIER INC. THE RECIPIENT OF THIS DOCUMENT, BY ITSRETENTION AND USE AGREES TO HOLD IN CONFIDENCE THETECHNICAL DATA AND DESIGNS CONTAINED HEREIN. THEFOREGOING SHALL NOT APPLY TO PERSONS HAVING PROPRIETARYRIGHTS TO SUCH INFORMATION, TECHNICAL DATA OR SUCH DESIGNSTO THE EXTENT THAT SUCH RIGHTS EXIST. D.3363-25 REV 1998-03

FOR DISCLOSURE TO THE CANADIAN GOVERNMENT

BT0107-04 MW97 1999-03 © 1999 Bombardier Inc. ® Trademark of Bombardier Inc.

DOCUMENT NO.: RAS-CC670-203

REV: NC

TITLE: FIXED TRAILING EDGESTRUCTURAL ANALYSIS

DOC:PAGE:

RAS-CC670-203ii

INITIAL APPROVAL

FIXED TRAILING EDGE STRUCTURALANALYSIS

THE DISCLOSURE AND PROPRIETARY NOTICES ON THE TITLE PAGE APPLY TO THE DATA CONTAINED ON EACH PAGE OF THIS DOCUMENT.

BT0107-08 MW97 1999-03

DATE

PREPARED

SHELLEY CLARKE

CHECKED

JOHN HUDDART

APPROVED

SALAMON HARAVAN

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FIXED TRAILING EDGE STRUCTURAL ANALYSIS

Section 16: OUTBOARD TRAILING EDGE BUTE DOOR, COMPOSITE PANELS

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SECTION 16

OUTBOARD TRAILING EDGE BUTE DOOR, COMPOSITE PANELS

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TABLE OF CONTENTS

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SECTION TITLE PAGE ............................................................................................... 1-0

TABLE OF CONTENTS................................................................................................ 1-i

LIST OF FIGURES .......................................................................................................1-ii

LIST OF TABLES ........................................................................................................1-iii

(Last Page of Front Matter) ..........................................................................................1-iii

SECTION 16

OUTBOARD TRAILING EDGE BUTE DOOR, COMPOSITE PANELS

16.1 INTRODUCTION ................................................................................... 16.1-1

16.2 DESCRIPTION OF THE BUTE DOOR.................................................. 16.2-1

16.3 MATERIAL PROPERTIES .................................................................... 16.3-1

16.4 LOADS .................................................................................................. 16.4-1

16.5 THE FINITE ELEMENT MODEL ........................................................... 16.5-1

16.5.1 F.E.M. FOR THE CLOSED DOOR............................................ 16.5-6

16.5.2 F.E.M FOR THE OPEN DOOR ................................................. 16.5-8

16.6 STRESS ANALYSIS ............................................................................. 16.6-1

16.6.1 STRESS ANALYSIS OF THE BUTE DOOR IN THE CLOSED DOORPOSITION WITH A +2.5 PSI LOAD APPLIED .......................... 16.6-2

16.6.2 STRESS ANALYSIS OF THE BUTE DOOR IN THE CLOSED DOORPOSITION WITH A –0.8 PSI LOAD APPLIED ........................ 16.6-36

16.6.3 STRESS ANALYSIS OF THE BUTE DOOR IN THE OPENEDDOOR POSITION WITH A +2.0 PSI LOAD APPLIED ............ 16.6-69

16.6.4 STRESS ANALYSIS OF THE BUTE DOOR IN THE OPENED DOORPOSITION WITH A -.65 PSI LOAD APPLIED ....................... 16.6-102

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LIST OF FIGURES

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FIGURE 16.2.1 STRUCTURE OF BUTE DOOR .................................................. 16.2-1

FIGURE 16.2.2 SECTION A:A.............................................................................. 16.2-2

FIGURE 16.2.3 A TYPICAL END CROSS-SECTION........................................... 16.2-2

FIGURE 16.2.4 STRUCTURE OF CC670-17325 ................................................. 16.2-3

FIGURE 16.2.5 GEOMETRY OF CC670-17330................................................... 16.2-4



FIGURE 16.2.8 METAL PLATE ROLLER FITTING .............................................. 16.2-7

FIGURE 16.2.9 ACTUATOR MOVEMENT ........................................................... 16.2-9

FIGURE 16.3.1 MATERIAL PROPERTIES........................................................... 16.3-1

FIGURE 16.5.1 F.E.M. FOR CC670-17325 .......................................................... 16.5-2

FIGURE 16.5.2 F.E.M. FOR CC670-17330 .......................................................... 16.5-3

FIGURE 16.5.3 F.E.M. FOR CC670-17334 .......................................................... 16.5-4

FIGURE 16.5.4 F.E.M. FOR CC670-17339 .......................................................... 16.5-5

FIGURE 16.5.5 CLOSED DOOR F.E.M. AND OPENED DOOR F.E.M............... 16.5-7

FIGURE 16.6.1 DEFLECTION PLOT, IN. (ULTIMATE) ........................................ 16.6-2

FIGURE 16.6.2 NORMALIZED STRESS IN FIBER COMPRESSION.................. 16.6-4

FIGURE 16.6.3 NORMALIZED STRESS IN FIBER TENSION.............................. 16.6-5

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LIST OF FIGURES

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FIGURE 16.6.4 MATRIX NORMALIZED STRESS ............................................... 16.6-6

FIGURE 16.6.5 DEFLECTION PLOT, IN. (ULTIMATE) ...................................... 16.6-10

FIGURE 16.6.6 NORMALIZED STRESS IN FIBER COMPRESSION................ 16.6-12

FIGURE 16.6.7 NORMALIZED STRESS IN FIBER TENSION........................... 16.6-13

FIGURE 16.6.8 MATRIX NORMALIZED STRESS .............................................. 16.6-14

FIGURE 16.6.9 DEFLECTION PLOT, IN. (ULTIMATE) ...................................... 16.6-19

FIGURE 16.6.10 NORMALIZED STRESS IN FIBER COMPRESSION.............. 16.6-21

FIGURE 16.6.11 NORMALIZED STRESS IN FIBER TENSION........................... 16.6-22

FIGURE 16.6.12 MATRIX NORMALIZED STRESS ............................................ 16.6-23

FIGURE 16.6.13 DEFLECTION PLOT, IN.(ULTIMATE) ...................................... 16.6-28

FIGURE 16.6.14 NORMALIZED STRESS IN FIBER COMPRESSION............... 16.6-30

FIGURE 16.6.15 NORMATLIZED STRESS IN FIBER TENSION...................... 16.6-31

FIGURE 16.6.16 MATRIX NORMALIZED STRESS ........................................... 16.6-32

FIGURE 16.6.17 DEFLECTION PLOT, IN. (ULTIMATE) .................................... 16.6-36

FIGURE 16.6.18 NORMALIZED STRESS IN FIBER COMPRESSION............... 16.6-38

FIGURE 16.6.19 NORMALIZED STRESS IN FIBER TENSION......................... 16.6-39




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LIST OF FIGURES

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FIGURE 16.6.26 NORMALIZED STESS IN FIBER COMPRESSION................. 16.6-54



FIGURE 16.6.29 DEFLECTION PLOT OF CC670-17339, CLOSED DOOR...... 16.6-61


FIGURE 16.6.31 NORMALIZED STESS IN FIBER TENSION ........................... 16.6-64






FIGURE 16.6.37 DEFLECTION PLOT FOR CC670-17330, OPEN DOOR........ 16.6-76




FIGURE 16.6.41 DEFLECTION PLOT, IN. (ULTIMATE) ................................... 16.6-85

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LIST OF FIGURES

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FIGURE 16.6.43 NORMALIZED STRESS IN FIBER TENSION........................ 16.6-88


FIGURE 16.6.45 DEFLECTION PLOT FOR CC670-17339, OPEN DOOR........ 16.6-94




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LIST OF TABLES

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TABLE 16.1.1 MARGINS OF SAFETY FOR THE BUTE DOOR .......................... 16.1-1

TABLE 16.3.1 FASTENER SHEAR STRENGTH.................................................. 16.3-1

TABLE 16.4.1 LOADS........................................................................................... 16.4-1

TABLE 16.6.1 HINGE SPC RESULTANTS FOR CC670-17325............................ 16.6-8

TABLE 16.6.2 ROLLER FITTING FASTENER FORCES FOR CC670-17325....... 16.6-9

TABLE 16.6.3 HINGE SPC RESULTANTS FOR CC670-17330......................... 16.6-16

TABLE 16.6.4 ROLLER FITTING FORCES FOR CC670-17330........................ 16.6-18


TABLE 16.6.6 ROLLER FITTING FASTENER FORCES FOR CC670-17334.... 16.6-27


TABLE 16.6.8 ROLLER FITTING FASTENER FORCES FOR CC670-17339.... 16.6-35


TABLE 16.6.10 ROLLER FITTING FASTENER FORCES FOR CC670-17325.. 16.6-42

TABLE 16.6.11 HINGE SPC RESULTANTS FOR CC670-17330....................... 16.6-49





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LIST OF TABLES

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TABLE 16.6.17 ACTUATOR SPC....................................................................... 16.6-68

TABLE 16.6.18 HINGE SPC RESULTANTS FOR CC670-17325........................ 16.6-75


TABLE 16.6.20 HINGE SPC RESULTANTS FOR CC670-17330........................ 16.6-82

TABLE 16.6.21 ROLLER FITTING FASTENER FORCES FOR CC670-17330... 16.6-84



TABLE 16.6.24 HINGE SPC RESULTANTS FOR CC670-17339..................... 16.6-100

TABLE 16.6.25 ROLLER FITTING FASTENER FORCES FOR CC670-17339 16.6-101

TABLE 16.6.26 ACTUATOR SPC FORCS ....................................................... 16.6-101

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Section: 16.1: INTRODUCTION

Prepared: SHELLEY CLARKE Checked: JOHN HUDDART Approved: SALAMONHARAVAN

BT0107-12 MW97 1999-03

16.1 INTRODUCTION

The bute door is a fixed trailig edge structure composed of 4composite parts. These composite parts correspond to drawingnumbers CC670-17325, CC670-17330, CC670-17334, CC670-17339.

A stress analysis was carried out on all 4 composite parts of the butedoor using NASTRAN finte element analysis. PATRAN was usedfor the post processing and also to generate the model from theCATIA model. The margins of safety are shown in Table 16.1.1.

TABLE 16.1.1 MARGINS OF SAFETY FOR THE BUTE DOOR

MARGINS OF SAFETY FOR FAIRINGS

BEARINGLOADCASE

BUTEDOOR

SECTION

FIBRETENSION

FIBRECOMPRESSION

MATRIX

HINGE ROLLER

CC670-17325 4.83 14.4 11.6 64.7 HIGH

CC670-17330 5.5 16.4 13.3 82.7 HIGH

CC670-17334 7.4 20.0 16.7 15.6 HIGH

CLOSEDDOOR

WITH A2.5 PSILOAD CC670-17339 11.4 32.8 27.08 89.7 HIGH

CC670-17325 7.3 16.7 11.1 31.8 43.5

CC670-17330 2.6 10.2 7.4 34.07 41.6

CC670-17334 4.7 12.2 8.9 29.5 29.9

CLOSEDDOOR

WITH A–0.8 PSILOAD CC670-17339 4.6 16.4 11.9 29.9 42.0

CC670-17325 1.6 8.8 3.9 11.4 25.9CC670-17330 .81 4.3 2.4 12.9 15.3CC670-17334 .98 5.9 3.2 9.4 15.2

OPENEDDOOR

WITH A+2.0 PSILOAD

CC670-17339 1.7 7.4 4.2 10.1 15.5


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Section: 16.2: DESCRIPTION OF THE BUTE DOOR


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16.2 DESCRIPTION OF THE BUTE DOOR

The bute door consists of 4 sections made of graphite fabric and a(¼)-inch thick honeycomb core, Fig.16.2.1. Moving from the mostinboard section to the outboard section of the door, the width taperesfrom 3.65 inches to 2.5 inches.

FIGURE 16.2.1 STRUCTURE OF BUTE DOOR

BUTE DOOR HINGE LINE

ROLLER ASSEMBLY

3.65 in.2.5 in.


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The basic lay-up is the same for all sections of the door, Fig.16.2.2.To support the roller fittings the ends of each section are thicker thanthe main part of the door. A typical cross section of an end is shownin Fig.16.2.3.

FIGURE 16.2.2 SECTION A:A

FIGURE 16.2.3 A TYPICAL END CROSS-SECTION

0.427 [45/-45/0/-45/45/film/core/film/45/-45/0/-45/45]

0.116 [45/0/-45/-45/0/-45/45] .116

.3154 in.0.427 in.


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The individual sections are presented in Fig.16.2.4, Fig.16.2.5,Fig.16.2.6 and Fig.16.2.7. Drawing number CC670-17325 is themost inboard section of the bute door and is located between wingstations 163.0 to 175.22, Fig.16.2.4. It is approximately 17.4 inchesin length.The width tapers from 3.65 inches to approximately 3.5inches wide.

FIGURE 16.2.4 STRUCTURE OF CC670-17325

A

A

3.65 in.

3.57 in.

Element4026

Element4024

Element4027

Element4025

Element3701

Element3699

Element3700

Element3698


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Section CC670-17330 of the bute door is located between wingstations 180.9 to 217.54, Fig.16.2.5. This section is approximately43.63 inches in length. The width tapers from 3.5 inches to 3.16inches.

FIGURE 16.2.5 GEOMETRY OF CC670-17330

A

A

3.5 in.

3.16 in.

Element3697

Element3695

Element 3696

Element 3694

Element 3693

Element 3691

Element 3692

Element 3690


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Section CC670-17334 of the bute door is located between wingstations 222.46 and 260.90, Fig.16.2.6. It is approximately 45.6inches in length. The width tapers from 3.1 inches to 2.7 incheswide.


A

A

3.1 in.

2.7 in.

Element3688

Element3687

Element3686

Element3689

Element3685

Element3683

Element3682

Element3684


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Section CC670-17339 of the bute door, is located between wingstations 267.36 and 285.25, Fig.16.2.7. It is approximately 16.95inches in length. The width tapers from 2.7 to 2.56 inches wide.


A

A

2.7 in.

2.56 in.

Element3679

Element3681

Element3680

Element3678

Element4050

Element4048

Element4051

Element4049


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The 4 sections are joined together via roller fittings, which are metalplates to which rollers are fitted. Rollers were placed in 3 differentlocations where the composite sections join and at 2 ends. Theserollers are the contact points between the flaps and the bute door. Oneview of a connecting roller fitting is shown in Fig.16.2.8. Thesefittings are fastened to the upper surface of the doors at each of theirends using 4, 3/16 inch bolts type NAS 1580. The bute door isfastened to the lower wing shroud along its forward edges via metalpiano hinges, using B0205015 type fasteners, which are reduced headrivets.

FIGURE 16.2.8 METAL PLATE ROLLER FITTING

ROLLER FITTING


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The purpose of the bute door is to provide a smooth air flow from theunderneath of the shroud to the underneath of the flaps. The doorassumes two positions. The close door position that occurs when theflaps are retracted which causes the gap between the flaps and theshroud to close. The open door position occurs when the flaps aredeployed and the bute door is automatically pushed open via 3actuator rods. These rods are located at wing stations 178.0, 220.0and 264.0. The door is opened through an angle of approximately15.0°, Fig.16.2.9.


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FIGURE 16.2.9 ACTUATOR MOVEMENT

VIEW LOOKING INBDAT WING STATION 220.0

41.60


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Section: 16.3: MATERIAL PROPERTIES


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16.3 MATERIAL PROPERTIES

The material properties and the material allowables for the 8-harnesssatin weave graphite/epoxy fabric are taken from RAS-000-357 andpresented in Table 16.3.1. The allowables correspond to averageroom temperature values for impact damaged (1mm dent) material.

FIGURE 16.3.1 MATERIAL PROPERTIES

PROPERTIESGRAPHITE / EPOXY

FABRIC

Elastic Modulus, E11 8.31 msi

Elastic Modulus, E22 8.17 msi

Shear Modulus, G12 0.61 msi

Poisson’s Ratio, ν12 0.047

Ply Thickness, in. 0.0166

Tensile Strength σ1t = σ2t = 80 ksiCompressive Strength σ1c = σ2c = 42 ksi

In-Plane Shear Strength τ12 = 17 ksiShort Beam Shear Strength sbs = 11.3 ksi

Matrix Tensile Strain εt = 9000 x 10-6

Matrix Compressive Strain εc = 24000 x 10-6

TABLE 16.3.1 FASTENER SHEAR STRENGTH

FASTENERTYPE

DIAMETER MINIMUMSHEARLOAD(LBS)

B0205015 1/8 724

NAS1580 3/16 2623


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Section: 16.4: LOADS


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16.4 LOADS

There are 4 load cases applied to the door that are found in reportnumber MAU-BA670-113. Table 16.4.1 shows the different loadcases applied to the door. The pressure is constant over the wholedoor.

TABLE 16.4.1 LOADS

FLAP POSITION DOORPOSITION

LIMIT PRESSURE(PSI)*

Retracted Closed +2.5

Retracted Closed -0.8

Deployed Opened +2.0

Deployed Opened -0.65

* Positive pressure closes the door.


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Section: 16.5: THE FINITE ELEMENT MODEL


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16.5 THE FINITE ELEMENT MODEL

Each structure, including its constraints, was modeled as accuratelyas possible within practical limitations. The typical element size is0.50 inch square. The F.E.M. for each section consists of shellelements, CQUAD4 and CTRIA3. There are 3742 elements in themodel. Element properties were defined using PCOMP propertycards and the material properties of individual plies were definedusing MAT8 cards. The material coordinate system is defined withthe x axis(0° direction) parallel to the trailing edge. Note thatelements of the same color have the same property card.

The F.E.M. of all sections are shown in Fig.16.5.1 to Fig.16.5.4. Thebasic lay-up of all sections is the same and is [45/-45/0/-45/45/film/core/film/45/-45/0/-45/45], Fig.16.2.2. The lay-up of theborders is [45/0/-45/-45/0/-45/45], Fig.16.2.3. The ends of eachsection are thickened to support the metal roller fitting plates. Thehoneycomb core is not structurally required, therefore it is left out ofthe model, and only the outer skins surrounding the honeycomb coreis modeled.

The metal roller fitting plates are included in the model and aremodeled with CQUAD4 and CTRIA3 elements. Element propertiesare defined using PSHELL property cards and the material propertiesare defined using MAT1 cards. CBAR elements represent the 4fasteners at each end of each composite section. These bar elementsare used because of the offset that exists between the composite doorsections and the metal plates that are created in the model. Elementproperties for these simple bar elements were defined using PBARproperty cards in NASTRAN.


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In the opened and closed door model nodes coincident with the pianohinge are constrained in 5 degrees of freedom, Tx, Ty, Tz, Ry andRz.

FIGURE 16.5.1 F.E.M. FOR CC670-17325

Honeycomb

[45/0/-45/0/45/0/45/0/45/0/45/0/45/0/45/-45/0/-45/45]

[45/0/-45/0/45/0/45/0/45/0/45/0/-45/0/-45/45]

[45/0/-45/45/0/45/-45/0/-45/45]Node 4526

Node4542Total number of elements = 589


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FIGURE 16.5.2 F.E.M. FOR CC670-17330

[45/-45/0/-45/45/0/45/0/45/0/45/0/45/0/45/0/-45/0/45]

[45/0/-45/0/45/0/45/0/45/0/45/0/45/0/45/-45/0/-45/45]

[45/0/-45/45/0/45/45/-45/-45/45]

Node 5007

Node4927

Total number of elements = 1361


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FIGURE 16.5.3 F.E.M. FOR CC670-17334

[45/0/-45/0/45/0/45/0/45/0/45/0/45/0/-45/0/-45/45]

[45/0/-45/45/0/45/0/45/0/45/0/45/0/-45/0/-45/45]

[45/0/-45/0/45/0/-45/0/-45/45]

Node 5016

Node 5098



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FIGURE 16.5.4 F.E.M. FOR CC670-17339

[45/0/-45/0/45/0/45/0/45/0/45/0/45/-45/0/-45/45] [45/0/-45/0/45/0/45/0/45/0/45/-45/0/-45/45]

[45/0/-45/45/0/45/-45/0/-45/45]

Node 5108

Node 5142



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16.5.1 F.E.M. FOR THE CLOSED DOOR

Two load cases are applied to the bute door in the closed doorposition. To keep the door closed, two different models areproduced. The pressure of +2.5 psi applied to the door, pushes thedoor up against the flaps. To represent this, single point constraintsare placed along the trailing edge of the bute door and constrained inthe vertical, Tz, direction of coordinate 5 . Single point constraintsrepresent the rollers that are placed in the 3 different locations wherethe composite sections are joined and at the 2 ends, Fig.16.5.5. Nodesthat coincide with the 5 rollers are are constrained in the vertical, Tz,direction of coordinate 5. The actuator rod is not included in thismodel.

The suction of -0.8 psi applied to the closed door, pushes the doordown against 3 actuator rods. The air loads are reacted by the hingeloads and the actuator rod. These actuator rods prevent the doorfrom opening. CROD elements are used to model these rods; theirproperties are defined using PROD property cards. The actuator rodsare constrained at their ends in all 6 degrees of freedom Tx, Ty, Tz,Rx, Ry, and Rz. The angle between the actuator rod in the closeddoor position and the open door position is 15.0°, Fig.16.5.5. Insteadof rotating the door 15.0°, the actuator rods are rotated. The 3actuator rods are connected to the door via CTRIA3 elements.Element properties for these elements are defined using PSHELLproperty cards and the material properties are defined using MAT1cards


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FIGURE 16.5.5 CLOSED DOOR F.E.M. AND OPENED DOOR F.E.M.

HINGE LINE

CLOSED DOORACTUATORPOSITION

OPENED DOORACTUATORPOSITON

Actuator 1

Actuator 2

Actuator 3


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16.5.2 F.E.M FOR THE OPEN DOOR

In the open door position the 3 actuator rods are engaged for both the+2.0 psi load and the -.65 psi load. In the open door position the airloads are reacted also by the hinge loads and the actuator rod. Theseactuator rods prevent the door from closing. CROD elements areused to model these rods, Fig.16.5.1.1; their properties are definedusing PROD property cards. The actuator rods are constrained attheir ends in all 6 degrees of freedom Tx, Ty, Tz, Rx, Ry, and Rz.The actuator rods are connected to the door via CTRIA3 elements.Element properties for these elements are defined using PSHELLproperty cards and the material properties are defined using MAT1cards


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16.6-12000-04-20


Section: 16.6: STRESS ANALYSIS


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16.6 STRESS ANALYSIS

A linear static analysis (SOL 101) was carried out under ultimateload conditions for the whole bute door comprising of sectionsCC670-17325, CC670-17330, CC670-17334 and CC670-17339. Theanalyses of the door are presented below. To obtain ultimate loadconditions, a factor of 1.5 is multiplied to the Limit Load Case givenin the load section of this report.

The ply stresses are analyzed using the Canadair Failure Criteria(RAS-000-357). This criterion calculates values of the normalizedstress (NS) using the allowables for impact damaged material. Themargin of safety is given by:

MS = (1/NS) – 1

The value of NS should be increased by 10% to obtain B allowablesand 30% to obtain hot/wet allowables (if applicable). Note this is notrequired for tensile values.

Note, both the upper and lower surfaces are shown in all plots exceptwhere otherwise indicated.


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16.6.1 STRESS ANALYSIS OF THE BUTE DOOR IN THE CLOSED DOORPOSITION WITH A +2.5 PSI LOAD APPLIED

The deflection plot under ultimate load conditions for sectionCC670- 17325 is shown in Fig.16.6.1. The maximum deflection is.00720 inches.

FIGURE 16.6.1 DEFLECTION PLOT, IN. (ULTIMATE)


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A plot of the normalized stress for fiber compression, fiber tensionand matrix are shown in Fig.16.6.2, Fig.16.6.3 and Fig.16.6.4respectively.

The maximum normalized stress in fiber compression is 0.120. Themargin of safety is:

MS = (1/ (0.120 x 1.1 x 1.3 )) - 1 = 4.83.

The maximum normalized stress in fiber tension is .0589. Themargin of safety is:

MS = (1/(0.0589 x 1.1)) - 1 = 14.4.

The maximum normalized stress for the matrix is 0.0556. Themargin of safety is:

MS = (1/(0.0556 x 1.1 x 1.3)) - 1 = 11.6.


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FIGURE 16.6.2 NORMALIZED STRESS IN FIBER COMPRESSION


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FIGURE 16.6.3 NORMALIZED STRESS IN FIBER TENSION


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FIGURE 16.6.4 MATRIX NORMALIZED STRESS


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HINGE FITTING

The node spacing along the hinge line is such that 2 consecutivenodes represents 1 fastener of the hinge fitting. The combinedmaximum resultant SPC forces for 2 consecutive nodes is given bynodes 4542 and 4543 and is used to calculate the maximum bearingstress. The combined resultant SPC force is 29.3 lbs. The spcresultant forces are given in Table 16.6.1.

The hole diameter is .125 inches, the skin thickness is .166 inches.The bearing stress is:

σbr = (maximum resultant force)/(skin thickness x hole diameter)

σbr = ( 20.5 + 8.8 ) lbs/ (0.125 x 0.166)

=1412.0 lbs/in2

The bearing allowable is 72 ksi. The margin of safety is:

MS = (72000/ 1412.0) – 1 = 49.9 High margin of safety.

ROLLER FITTING

The maximum shear load acting on the CBAR, element 3698 is :

Shear load = ( 7.32 + 7.52)1/2 = 10.5 lbs, Table 16.6.2.

The door thickness in this region is .3154 and the bolt diameter is3/16.

σbr = ( 10.5) lbs/ (0.3154 x 0.1875) = 177.6 lbs/in2



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TABLE 16.6.1 HINGE SPC RESULTANTS FOR CC670-17325

Node RESULTANT 4542 2.04758E+01 4543 8.79599E+00 4544 6.38464E+00 4545 4.67269E+00 4546 4.84687E+00 4547 4.84847E+00 4548 4.27148E+00 4549 3.97896E+00 4550 3.91169E+00 4551 3.75858E+00 4552 3.75574E+00 4553 3.64309E+00 4554 3.67512E+00 4555 3.54697E+00 4556 3.55282E+00 4557 3.56123E+00 4558 3.29440E+00 4559 3.42908E+00 4560 3.42758E+00 4561 3.58946E+00 4562 3.71924E+00 4563 3.65306E+00 4564 3.42062E+00 4565 3.43282E+00 4566 4.09864E+00 4521 4.32642E+00 4522 4.89698E+00 4523 3.85495E+00 4524 3.58947E+00 4525 3.28135E+00

4526 2.55333E+00


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TABLE 16.6.2 ROLLER FITTING FASTENER FORCES FOR CC670-17325ELEM. POS. Fx(AXIAL) Fy(SHEAR) Fz(SHEAR)3698 0 -8.71640E+00 -7.34161E+00 7.54239E+003699 0 2.32218E+00 -6.25685E+00 1.41205E+013700 0 5.70498E+00 -4.84099E+00 -8.28637E+003701 0 -9.76427E+00 -1.40868E+01 4.04009E+004024 0 1.11008E+01 1.56213E-01 -1.32491E+014025 0 -3.05445E+01 1.39592E+01 8.35232E+004026 0 5.65767E+00 -6.60980E+00 -1.85058E+004027 0 -1.28315E+01 -7.36100E+00 7.40206E+00

Refer to Fig.16.2.4 for the location of the CBAR elements.


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The deflection plot under ultimate load conditions for sectionCC670- 17330 is shown in Fig.16.6.5. The maximum deflection is.00725 inches which occurs on the lower surface.


Lower surface


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A plot of the normalized stress for fiber compression, fiber tensionand matrix is shown in Fig.16.6.6, Fig.16.6.7 and Fig.16.6.8respectively.


MS = (1/ (0.107 x 1.1 x 1.3 )) - 1 = 5.5.


MS = (1/(0.0522 x 1.1)) - 1 = 16.4.


MS = (1/(0.0489 x 1.1 x 1.3)) - 1 = 13.3.


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HINGE FITTINGThe node spacing along the hinge line is such that 2 consecutivenodes represent 1 fastener of the hinge fitting. The combinedmaximum resultant SPC forces for 2 consecutive nodes is given bynodes 5006 and 5007 and is used to calculate the maximum bearingstress. The combined resultant SPC force is 29.2 lbs. The spcresultant forces are given in Table 16.6.3.



σbr = ( 19.9 + 9.3) lbs/ (0.125 x .166)

= 29.2 / (.021) = 1407.2 lbs/in2


MS = (72000/ 1407.2) – 1 = 50.16 High margin of safety

ROLLER FITTINGS

The maximum shear load acting on the CBAR, element 3695 is :

Shear load =(23.72 +.0582)1/2 = 23.7lbs, Table 16.6.4.

The door thickness in this region is .3154 and the bolt size is 3/16.

σbr = ( 23.7) lbs/ (0.3154 x .1875) = 400.7 lbs/in2.



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Node RESULTANT 4927 0 8.10981E+00 4928 0 8.97899E+00 4929 0 9.79793E+00 4930 0 9.38071E+00

4813 0 5.03958E+00 4932 0 4.03098E+00 4933 0 6.17470E+00 4934 0 6.12427E+00 4935 0 5.57526E+00 4936 0 4.90018E+00 4937 0 4.28469E+00 4938 0 3.85868E+00 4939 0 3.53824E+00 4940 0 3.39109E+00 4941 0 3.44783E+00 4942 0 3.31503E+00 4943 0 3.34931E+00 4944 0 3.56775E+00 4945 0 3.26592E+00 4946 0 3.55208E+00 4947 0 3.34995E+00 4948 0 3.39702E+00 4949 0 3.47004E+00 4950 0 3.48855E+00 4951 0 3.35250E+00 4952 0 3.35477E+00 4953 0 3.55975E+00 4954 0 3.23055E+00 4955 0 3.50276E+00 4956 0 3.30612E+00 4957 0 3.32195E+00 4958 0 3.51006E+00 4959 0 3.20249E+00 4960 0 3.39157E+00 4961 0 3.41014E+00 4962 0 3.25963E+00 4963 0 3.29431E+00 4964 0 3.43459E+00 4965 0 3.24863E+00

4986 0 3.26898E+00 4966 0 3.47212E+00 4967 0 3.14760E+00


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NODE POS RESULTANT4968 0 3.34752E+004969 0 3.37028E+00

4970 0 3.21799E+00 4971 0 3.31656E+00 4972 0 3.24944E+00 4973 0 3.28848E+00 4974 0 3.23358E+00 4975 0 3.41510E+00 4976 0 3.12169E+00 4977 0 3.35094E+00 4978 0 3.25245E+00 4979 0 3.18149E+00 4980 0 3.40666E+00 4981 0 3.10370E+00 4982 0 3.33834E+00

4985 0 3.23972E+00 4983 0 3.22322E+00 4984 0 3.22425E+00 4987 0 3.30178E+00 4988 0 3.32487E+00 4989 0 3.19241E+00 4990 0 3.33899E+00 4991 0 3.17995E+00 4992 0 3.33427E+00 4993 0 3.36012E+00 4994 0 3.24626E+00 4995 0 3.34682E+00 4996 0 3.33668E+00 4997 0 3.28720E+00 4998 0 3.43479E+00 4999 0 3.46230E+00 5000 0 3.32241E+00 5001 0 3.59526E+00 5002 0 3.57501E+00 5003 0 3.93728E+00 5004 0 3.93299E+00 5005 0 6.97634E+00 5006 0 9.26731E+00 5007 0 1.99852E+01


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TABLE 16.6.4 ROLLER FITTING FASTENER FORCES FOR CC670-17330ELEM. POS Fx(AXIAL) Fy(SHEAR) Fz(SHEAR)3690 0 -1.33634E+01 -1.29986E+01 -8.20521E-02

3691 0 1.42843E+01 -6.02832E+00 6.65764E+00 3692 0 -4.24503E-01 -6.68639E+00 -1.91977E+00 3693 0 -6.31540E+00 -1.23852E+00 4.99399E+00 3694 0 4.24961E+00 5.03789E+00 -1.97402E+01 3695 0 -1.35883E+01 2.37278E+01 5.77958E-02 3696 0 1.51393E+01 -1.45102E+01 -5.65971E+00 3697 0 -1.64322E+01 1.84553E+01 8.41802E+00


.


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MS = (1/ (0.0834 x 1.1 x1.3 )) - 1 = 7.4


MS = (1/(0.0432 x 1.1)) - 1 = 20.0.


MS = (1/(0.0396 x 1.1 x 1.3)) - 1 = 16.7.


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HINGE FITTING

The node spacing along the hinge line is such that 2 consecutivenodes represent 1 fastener of the hinge fitting. The combinedmaximum resultant SPC forces for 2 consecutive nodes is given bynodes 5098 and 5101 and is used to calculate the maximum bearingstress. The combined resultant SPC force is 93.9 lbs. The spcresultant forces are given in Table 16.6.5.



σbr = ( 19.2 + 74.7) lbs/ (0.125 x 0.166)

= 93.9 / (.125 x 0.166) = 4525.3 lbs/in2


MS = (72000/ 4525.3) – 1 = 14.9

ROLLER FITTINGS

The maximum shear load acting through CBAR , element 3687 is:

Shear load = (27.42 + 2.82)1/2 = 27.5 , Table 16.6.6.

The door thickness in this region is .2988 inches and the bolt size is3/16 inches.

σbr = ( 27.5) lbs/ (0.2988 x 0.1875) = 488.9 lbs/in2.



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NODE RESULTANT5016 0 5.97591E+005017 0 4.58662E+005018 0 4.65677E+005019 0 5.16304E+00

5020 0 5.03249E+005021 0 5.75005E+005022 0 3.49219E+00

5023 0 3.35068E+00 5024 0 3.62010E+00 5025 0 3.84987E+00 5026 0 3.64036E+00 5027 0 3.42788E+00 5028 0 3.06672E+00 5029 0 3.01835E+00 5030 0 3.00203E+00 5031 0 2.91870E+00 5032 0 2.99350E+00 5033 0 3.02165E+00 5034 0 3.08445E+00 5035 0 2.98821E+00 5036 0 3.01506E+00 5037 0 3.07443E+00 5038 0 3.12831E+00 5039 0 2.93474E+00 5040 0 3.06357E+00 5041 0 3.03296E+00 5042 0 3.04318E+00 5043 0 3.01813E+00 5044 0 2.98783E+00 5045 0 3.04995E+00 5046 0 2.94411E+00 5047 0 2.99188E+00 5048 0 2.95146E+00 5049 0 3.07837E+00 5050 0 2.86646E+00 5051 0 2.99146E+00 5052 0 2.96426E+00 5053 0 3.03431E+00 5054 0 2.85054E+00 5055 0 2.97380E+00 5056 0 2.94615E+00


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NODE RESULTANT5057 0 2.98786E+00

5058 0 2.88468E+00 5059 0 2.93571E+00 5060 0 2.89907E+00 5061 0 3.02380E+00

5062 0 2.84437E+005063 0 2.88777E+005064 0 3.01051E+00

5065 0 2.80001E+00 5066 0 2.92515E+00 5067 0 2.89697E+00

5068 0 2.93896E+00 5069 0 2.83922E+00

5070 0 2.85891E+00 5071 0 2.93811E+00 5072 0 2.89829E+00 5073 0 2.82170E+00 5074 0 2.84075E+00 5075 0 2.95911E+00 5076 0 2.78663E+00 5077 0 2.82552E+00 5078 0 2.88479E+00 5079 0 2.87837E+00 5080 0 2.76355E+00 5081 0 2.85518E+00 5082 0 2.82854E+00 5083 0 2.86720E+00 5084 0 2.76126E+00 5085 0 2.77753E+00 5086 0 2.88659E+00 5087 0 2.70828E+00 5088 0 2.77089E+00 5089 0 2.73068E+00 5090 0 2.82961E+00 5091 0 2.64624E+00 5092 0 2.37610E+00 5093 0 4.05418E+00 5094 0 3.59746E+00 5095 0 3.82531E+00 5096 0 4.21828E+00 5097 0 4.96574E+00 5101 0 7.47125E+00

5098 0 1.91578E+01


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TABLE 16.6.6 ROLLER FITTING FASTENER FORCES FOR CC670-17334ELEM. POS Fx(AXIAL) Fy(SHEAR) Fz(SHEAR)3682 0 -1.02539E+01 1.15849E+01 5.24136E+00

3683 0 7.71806E+00 3.41037E+00 7.02922E+00 3684 0 -1.77333E+00 3.79416E+00 -8.04029E-01 3685 0 -2.82133E+00 -1.41793E-01 4.13568E-01 3686 0 9.13103E+00 1.56591E+01 -1.52567E+01 3687 0 -2.07130E+01 2.73958E+01 -2.77001E+00 3688 0 1.03527E+00 -1.02607E+00 -1.72261E+00 3689 0 2.87131E+00 -1.49176E+01 1.04526E+01



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The deflection plot under ultimate load conditions for sectionCC670-17339 is shown in Fig.16.6.13. The maximum deflection is.00304 inches.

FIGURE 16.6.13 DEFLECTION PLOT, IN.(ULTIMATE)


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The maximum normalized stress in fiber compression is .0563. Themargin of safety is:

MS = (1/ (0.0563 x 1.1 x 1.3 )) - 1 = 11.4.


MS = (1/(0.0269 x 1.1)) - 1 = 32.8.


MS = (1/(0.0249 x 1.1 x 1.3)) - 1 = 27.08.


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FIGURE 16.6.15 NORMATLIZED STRESS IN FIBER TENSION


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HINGE FITTING




σbr = ( 10.86 + 9.5) lbs/ (0.125 x 0.166)

= 20.36 / (.125 x 0.166) = 981.2 lbs/in2



ROLLER FITTINGS

The maximum shear load acting through CBAR, element 3679 is:

Shear load = (19.32 + 3.982 )1/2 = 19.7 lbs, Table 16.6.8.

The door thickness is .282 inches and the bolt diameter is .1875.

σbr = ( 19.7) lbs/ (0.282 x 0.1875)= 372.6 lbs/in2.



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Node RESULTANT 5108 0 9.45634E+00 5109 0 1.08641E+01 5110 0 6.40591E+00 5111 0 3.82483E+00 5112 0 4.63057E+00 5113 0 4.03005E+00 5114 0 4.48895E+00 5115 0 3.86592E+00

5116 0 3.27904E+005117 0 2.87430E+005118 0 2.62072E+00

5119 0 2.56165E+00 5120 0 2.62374E+00

5121 0 2.72495E+00 5122 0 2.71084E+00 5123 0 2.65442E+00 5124 0 2.68879E+00 5125 0 2.76843E+00 5126 0 2.68568E+00 5127 0 2.58624E+00 5128 0 2.58027E+00 5129 0 2.53254E+00 5130 0 2.31349E+00 5131 0 2.38735E+00 5132 0 2.37079E+00 5133 0 2.59045E+00 5134 0 2.57505E+00 5135 0 2.35424E+00 5136 0 2.66556E+00 5137 0 2.83625E+00 5138 0 2.65652E+00 5139 0 2.49519E+00 5140 0 2.36763E+00 5141 0 2.11429E+00 5142 0 2.81559E+00


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TABLE 16.6.8 ROLLER FITTING FASTENER FORCES FOR CC670-17339Ele. Pos Fx(AXIAL) Fy(SHEAR) Fz(SHEAR)

3678 0 2.94156E+00 -4.93356E+00 -1.27451E+01 3679 0 -4.30319E+00 -1.93418E+01 3.98214E+00 3680 0 1.18931E+01 1.31760E+01 -8.29909E+00 3681 0 -1.22824E+01 -7.66640E+00 5.39945E+00 4048 0 -1.18444E+01 1.26034E+01 -3.96881E-01 4049 0 3.46473E+00 2.97307E+00 -5.03036E+00 4050 0 -1.62217E+01 -9.05922E+00 9.47742E+00 4051 0 4.41298E+00 -6.28905E+00 -3.56345E+00



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16.6.2 STRESS ANALYSIS OF THE BUTE DOOR IN THE CLOSED DOORPOSITION WITH A –0.8 PSI LOAD APPLIED

The deflection plot under ultimate load conditions for sectionCC670- 17325 is shown in Fig.16.6.17. The maximum deflection is-0.0775 inches.



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MS = (1/ (0.0840 x 1.1 x 1.3 )) - 1 = 7.3.


MS = (1/(0.0506 x 1.1)) - 1 = 16.7.


MS = (1/(0.0578 x 1.1 x 1.3)) - 1 = 11.1.


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FIGURE 16.6.18 NORMALIZED STRESS IN FIBERCOMPRESSION


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HINGE FITTING




σbr = ( 37.1 + 10.7) lbs/ (0.125 x 0.166)

= 47.8 / (.125 x 0.166) = 2303.6 lbs/in2


MS = (72000/ 2303.6) – 1 = 30.25

ROLLER FITTINGS

The maximum shear load acting through CBAR, element 3701 is:

Shear load = (97.82 + 4.02)1/2 = 97.9 lbs, Table 16.6.10.

The door thickness is .3154 and the bolt size is .1875.

σbr = ( 97.9) lbs/ (0.3154 x 0.1875) = 1655.2 lbs/in2.



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Node POS RESULTANT

4542 0 3.70670E+01 4543 0 1.07243E+01 4544 0 1.36279E+01 4545 0 1.17448E+01 4546 0 1.07002E+01 4547 0 8.66673E+00 4548 0 7.52017E+00 4549 0 6.63136E+00 4550 0 6.17583E+00 4551 0 5.72226E+00 4552 0 5.53271E+00 4553 0 5.25351E+00 4554 0 5.20676E+00 4555 0 4.96343E+00 4556 0 4.82258E+00 4557 0 4.85873E+00 4558 0 4.42064E+00 4559 0 4.29219E+00 4560 0 4.07496E+00 4561 0 3.99390E+00 4562 0 3.87602E+00 4563 0 4.16003E+00 4564 0 4.72133E+00 4565 0 5.15811E+00 4566 0 6.16862E+00 4521 0 6.10366E+00 4522 0 4.91814E+00 4523 0 4.08138E+00 4524 0 8.88586E+00 4525 0 1.21518E+01 4526 0 6.99757E+00

TABLE 16.6.10 ROLLER FITTING FASTENER FORCES FOR CC670-17325

ELEM. POS Fx(AXIAL) Fy(SHEAR) Fz(SHEAR)3698 0 -2.66351E+01 -9.29973E+00 -3.04318E+01

3699 0 3.17064E+01 2.46260E+01 -5.44425E+01 3700 0 -1.74517E+01 5.60003E+01 2.70453E+01 3701 0 5.10074E+01 9.77841E+01 4.01655E+00 4024 0 6.79915E+00 -6.16888E+00 -4.78873E-01 4025 0 -6.62562E+00 2.86479E+00 -6.74607E-01 4026 0 -4.67578E+00 -6.60813E-01 4.20645E+00 4027 0 4.48169E+00 3.95811E+00 -3.05094E+00



RAS-CC670-203NC

16.6-432000-04-20




BT0107-12 MW97 1999-03




RAS-CC670-203NC

16.6-442000-04-20




BT0107-12 MW97 1999-03



MS = (1/ (0.192 x 1.1 x 1.3 )) - 1 = 2.6.


MS = (1/(0.0809 x 1.1)) - 1 = 10.23.


MS = (1/(0.0830 x 1.1 x 1.3)) - 1 = 7.4.


RAS-CC670-203NC

16.6-452000-04-20




BT0107-12 MW97 1999-03



RAS-CC670-203NC

16.6-462000-04-20




BT0107-12 MW97 1999-03



RAS-CC670-203NC

16.6-472000-04-20




BT0107-12 MW97 1999-03



RAS-CC670-203NC

16.6-482000-04-20




BT0107-12 MW97 1999-03

HINGE FITTING




σbr = ( 37.7 + 6.95) lbs/ (0.125 x 0.166)

= 44.65 / (.125 x 0.166) = 2151.8 lbs/in2


MS = (72000/ 2151.8) – 1 = 32.5

The maximum shear load acting through CBAR , element 3696 is:

Shear load= ( 69.92 + 74.32)1/2 = 102.0, Table 16.6.12.

The door thickness in this region is .3154 and the bolt diameter is.1875.

σbr = (102)/(.1875 x .315) = 1726.9 lbs/in2.



RAS-CC670-203NC

16.6-492000-04-20




BT0107-12 MW97 1999-03


Node Pos RESULTANT 4927 0 6.24630E+00 4928 0 1.04327E+01 4929 0 1.98318E+01

4813 0 2.69442E+014930 0 2.80498E+01

4932 0 2.30230E+01 4933 0 1.55176E+01 4934 0 1.20504E+01 4935 0 8.74618E+00 4936 0 6.41619E+00 4937 0 4.73894E+00 4938 0 3.54350E+00 4939 0 2.67095E+00 4940 0 1.98976E+00 4941 0 1.85992E+00 4942 0 1.44788E+00 4943 0 1.47481E+00 4944 0 2.12439E+00 4945 0 1.42495E+00 4946 0 2.29276E+00 4947 0 1.67983E+00 4948 0 1.98022E+00 4949 0 2.24099E+00 4950 0 2.35999E+00 4951 0 1.89947E+00 4952 0 1.94229E+00 4953 0 2.77451E+00 4954 0 1.54216E+00 4955 0 2.66440E+00 4956 0 1.83262E+00 4957 0 1.96286E+00 4958 0 2.72473E+00 4959 0 1.51404E+00 4960 0 2.29594E+00 4961 0 2.41095E+00 4962 0 1.87304E+00 4963 0 1.99488E+00 4964 0 2.62426E+00 4965 0 1.83021E+00

4986 0 1.99126E+00 4966 0 2.87227E+00 4967 0 1.58004E+00 4968 0 2.39327E+00


RAS-CC670-203NC

16.6-502000-04-20




BT0107-12 MW97 1999-03

NODE POS RESULTANT4969 0 2.46160E+00

4970 0 1.81322E+004971 0 2.28329E+004972 0 2.03564E+00

4973 0 2.19874E+00 4974 0 2.04913E+00 4975 0 2.84602E+00 4976 0 1.63834E+00 4977 0 2.64512E+00 4978 0 2.21189E+00 4979 0 2.05628E+00 4980 0 2.95539E+00 4981 0 1.85781E+00 4982 0 2.77673E+00

4985 0 2.35332E+004983 0 2.37451E+00



RAS-CC670-203NC

16.6-512000-04-20




BT0107-12 MW97 1999-03

TABLE 16.6.12 ROLLER FITTING FASTENER FORCES FOR CC670-17330ELEM. POS Fx(AXIAL) Fy(SHEAR) Fz(SHEAR)3690 0 -2.34843E+01 -1.31742E+01 -3.19780E+01

3691 0 1.35260E+01 -6.19723E+00 -6.65797E+01 3692 0 -2.81584E+01 5.16409E+01 5.31364E+01 3693 0 6.96633E+01 3.63737E+01 4.53766E+01 3694 0 -2.24327E+01 -4.82305E+01 6.91192E+01 3695 0 8.32412E+01 -2.94499E+01 5.70862E+01 3696 0 4.13424E+00 -6.98793E+01 -7.43075E+01 3697 0 1.78906E+01 -2.08475E+01 -6.34921E+01



RAS-CC670-203NC

16.6-522000-04-20




BT0107-12 MW97 1999-03

The deflection plot under ultimate load conditions for sectionCC670- 17334 is shown in Fig.16.6.2.9. The maximum deflection is-.102 inches.



RAS-CC670-203NC

16.6-532000-04-20




BT0107-12 MW97 1999-03



MS = (1/ (0.122 x 1.1 x1.3 )) - 1 = 4.73.


MS = (1/(0.687 x 1.1)) - 1 = 12.2.


MS = (1/(0.0708 x 1.1 x 1.3)) - 1 = 8.9.


RAS-CC670-203NC

16.6-542000-04-20




BT0107-12 MW97 1999-03

FIGURE 16.6.26 NORMALIZED STESS IN FIBER COMPRESSION


RAS-CC670-203NC

16.6-552000-04-20




BT0107-12 MW97 1999-03



RAS-CC670-203NC

16.6-562000-04-20




BT0107-12 MW97 1999-03



RAS-CC670-203NC

16.6-572000-04-20




BT0107-12 MW97 1999-03

HINGE FITTING




σbr = ( 24.7 + 26.6) lbs/ (0.125 x 0.116)

= 51.3 / (.1875 x 0.116) = 3537.9 lbs/in2


MS = (72000/ 3537.9) – 1 = 19.4

The maximum shear load acting through the CBAR, element 3685 is;

Shear load = (89.02 + 85.52)1/2 = 123.4 lbs, Table 16.6.14.

The door thickness in this region is .2822 inches and the boltdiameter is 3/16 inches.

σbr = 123.4 lbs/ (.2822 x .1875) = 2324.6 lbs/in2.

MS = (72000/ 2324.6) – 1 = 29.9. High margin of safety.


RAS-CC670-203NC

16.6-582000-04-20




BT0107-12 MW97 1999-03


Node Pos RESULTANT 5016 0 2.47891E+01 5017 0 2.66004E+01 5018 0 2.39609E+01 5019 0 1.56408E+01 5020 0 9.56876E+00 5021 0 5.71761E+00 5022 0 2.61710E+00 5023 0 3.00601E+00 5024 0 4.25342E+00 5025 0 2.66237E+00 5026 0 2.40992E+00 5027 0 2.36497E+00 5028 0 2.51247E+00 5029 0 2.70502E+00 5030 0 2.99305E+00 5031 0 2.91564E+00 5032 0 3.15399E+00 5033 0 3.22393E+00 5034 0 3.26358E+00 5035 0 2.64419E+00 5036 0 2.58629E+00 5037 0 2.67100E+00 5038 0 2.73442E+00 5039 0 1.63024E+00 5040 0 2.18434E+00 5041 0 2.06771E+00 5042 0 2.15192E+00 5043 0 1.90103E+00 5044 0 1.75692E+00 5045 0 2.20896E+00 5046 0 1.58658E+00 5047 0 1.85860E+00 5048 0 1.69705E+00 5049 0 2.52739E+00 5050 0 1.29748E+00 5051 0 2.00845E+00 5052 0 1.83745E+00 5053 0 2.34492E+00 5054 0 1.28290E+00 5055 0 2.00636E+00 5056 0 1.82659E+00 5057 0 2.18237E+00 5058 0 1.54937E+00


RAS-CC670-203NC

16.6-592000-04-20




BT0107-12 MW97 1999-03

NODE POS RESULTANT5059 0 1.83559E+005060 0 1.64633E+005061 0 2.58186E+00

5062 0 1.38187E+00 5063 0 1.65149E+00 5064 0 2.57144E+00 5065 0 1.28204E+00 5066 0 2.03042E+00 5067 0 1.84194E+00 5068 0 2.19053E+00 5069 0 1.60831E+00 5070 0 1.74019E+00 5071 0 2.26117E+00 5072 0 2.03806E+00 5073 0 1.72216E+00 5074 0 1.85539E+00 5075 0 2.63024E+00 5076 0 1.83669E+00 5077 0 2.14260E+00 5078 0 2.51501E+00 5079 0 2.49607E+00 5080 0 2.41369E+00 5081 0 2.96812E+00 5082 0 3.02333E+00 5083 0 3.32480E+00 5084 0 3.57083E+00 5085 0 4.01884E+00 5086 0 4.60617E+00 5087 0 5.02159E+00 5088 0 5.83618E+00 5089 0 6.48797E+00 5090 0 7.21747E+00 5091 0 8.07043E+00 5092 0 8.50871E+00 5093 0 7.20037E+00 5094 0 5.23911E+00 5095 0 3.32173E+00 5096 0 5.24696E+00 5097 0 7.57276E+00 5101 0 9.91269E+00

5098 0 2.64320E+01


RAS-CC670-203NC

16.6-602000-04-20




BT0107-12 MW97 1999-03

TABLE 16.6.14 ROLLER FITTING FASTENER FORCES FOR CC670-17334ELEM. POS Fx(AXIAL) Fy(SHEAR) Fz(SHEAR)3682 0 -2.45327E+01 1.63667E+01 -2.92705E+01

3683 0 2.58801E+01 -2.29807E+01 -2.83025E+01 3684 0 -3.48079E+01 -3.94457E+01 2.47430E+01 3685 0 5.93088E+01 -8.94125E+01 -8.55358E+00 3686 0 -4.28112E+01 -2.91137E+01 5.84573E+01 3687 0 7.70852E+01 -6.46525E+01 6.30935E+01 3688 0 3.89780E+01 -1.39511E+01 -9.17947E+01 3689 0 -2.28137E-01 3.94988E+01 -7.71188E+01



RAS-CC670-203NC

16.6-612000-04-20




BT0107-12 MW97 1999-03

The deflection plot under ultimate load conditions for sectionCC670-17339 is shown in Fig.16.6.2.13. The maximum deflection is-.0523 inches.

FIGURE 16.6.29 DEFLECTION PLOT OF CC670-17339,CLOSED DOOR


RAS-CC670-203NC

16.6-622000-04-20




BT0107-12 MW97 1999-03



MS = (1/ (0.123 x 1.1 x 1.3)) - 1 = 4.6.


MS = (1/(0.0521 x 1.1)) - 1 = 16.4.


MS = (1/(0.0540 x 1.1 x 1.3)) - 1 = 11.9.


RAS-CC670-203NC

16.6-632000-04-20




BT0107-12 MW97 1999-03



RAS-CC670-203NC

16.6-642000-04-20




BT0107-12 MW97 1999-03

FIGURE 16.6.31 NORMALIZED STESS IN FIBER TENSION


RAS-CC670-203NC

16.6-652000-04-20




BT0107-12 MW97 1999-03



RAS-CC670-203NC

16.6-662000-04-20




BT0107-12 MW97 1999-03

HINGE FITTING




σbr = ( 26.5+ 24.1) lbs/ (0.125 x 0.166)

= 50.6 / (.125 x 0.166) = 2438.6 lbs/in2


MS = (72000/ 2438.6) – 1 = 28.5

ROLLER FITTING

The maximum shear load acting through the CBAR, element 3680 is:Shear load = (75.02 +51.12)1/2 = 90.7, Table 16.6.16.

The door thickness in this region is .2822 and the bolt diameter is.1875.

σbr = 90.7/(.2822 x .1875) =1714.2 lbs/in2 . MS = (72000/ 1714.2) – 1 = 42.0 High margin of safety.


RAS-CC670-203NC

16.6-672000-04-20




BT0107-12 MW97 1999-03


Node Pos RESULTANTS 5108 0 1.12856E+01 5109 0 1.90477E+01 5110 0 2.64997E+01 5111 0 2.41418E+01 5112 0 1.87639E+01 5113 0 1.22639E+01 5114 0 6.72406E+00 5115 0 4.09896E+00 5116 0 2.86668E+00 5117 0 2.33893E+00 5118 0 2.03711E+00 5119 0 1.80696E+00 5120 0 1.79471E+00 5121 0 1.95409E+00 5122 0 1.88490E+00 5123 0 1.64301E+00 5124 0 1.66985E+00 5125 0 1.98228E+00 5126 0 1.76494E+00 5127 0 1.54932E+00 5128 0 1.62702E+00 5129 0 1.79731E+00 5130 0 1.35630E+00 5131 0 1.93916E+00 5132 0 1.86005E+00 5133 0 3.40462E+00 5134 0 4.40400E+00 5135 0 3.94177E+00 5136 0 2.92879E+00 5137 0 1.95491E+00 5138 0 2.54038E+00 5139 0 3.11543E+00 5140 0 3.79654E+00 5141 0 5.01860E+00

5142 0 3.59612E+00


RAS-CC670-203NC

16.6-682000-04-20




BT0107-12 MW97 1999-03

TABLE 16.6.16 ROLLER FITTING FASTENER FORCES FOR CC670-17339Ele Pos Fx(AXIAL) Fy(SHEAR) Fz(SHEAR)3678 0 7.81992E+00 4.81932E+01 3.79651E+01

3679 0 4.84256E+01 1.13816E+01 3.99532E+01 3680 0 3.43438E+01 7.50637E+01 -5.11288E+01 3681 0 -1.42023E+01 -1.20926E+00 -3.19674E+01 4048 0 7.13254E+00 -5.78780E+00 2.88724E+00 4049 0 -8.60171E+00 9.92662E+00 1.04029E+00 4050 0 -9.46323E+00 -9.79574E+00 6.11760E-01 4051 0 1.08732E+01 5.66318E+00 -4.57094E+00


TABLE 16.6.17 ACTUATOR SPC

ACTUATOR TX TY TZ *RESULTANT

1 -.33 104.5 40.5 112.02 1.54 107.4 41.2 115

3 1.44 125.3 58.1 138.1

*RESULTANT = AXIAL LOAD IN ACTUATOR ROD


RAS-CC670-203NC

16.6-692000-04-20




BT0107-12 MW97 1999-03

16.6.3 STRESS ANALYSIS OF THE BUTE DOOR IN THE OPENED DOORPOSITION WITH A +2.0 PSI LOAD APPLIED




RAS-CC670-203NC

16.6-702000-04-20




BT0107-12 MW97 1999-03

A plot of the normalized stress for fiber compression, fiber tensionand matrix are shown in Fig.16.6.34, Fig.16.6.35 and Fig.16.6.3.6respectively.


MS = (1/ (0.273 x 1.1 x 1.3 )) - 1 = 1.6.


MS = (1/(0.0927 x 1.1)) - 1 = 8.8.

The maximum normalized stress for the matrix is 0.142. The marginof safety is:

MS = (1/(0.142 x 1.1 x 1.3)) - 1 = 3.9.


RAS-CC670-203NC

16.6-712000-04-20




BT0107-12 MW97 1999-03



RAS-CC670-203NC

16.6-722000-04-20




BT0107-12 MW97 1999-03



RAS-CC670-203NC

16.6-732000-04-20




BT0107-12 MW97 1999-03



RAS-CC670-203NC

16.6-742000-04-20




BT0107-12 MW97 1999-03

HINGE FITTING




σbr = ( 98.2 + 28.1) lbs/ (0.125 x 0.166)

= 126.3 / (.125 x 0.166) = 6086.7 lbs/in2


MS = (72000/ 6086.7) – 1 = 10.8

ROLLER FITTINGS

The maximum shear load acting through the CBAR, element 3699 is:Shear load = (67.22 + 142.32)1/2 = 158.3 lbs, Table 16.6.20.


σbr = ( 158.3) lbs/ (0.3154 x 0.1875) = 2676.8 lbs/in2

MS = (72000/ 2676.8) – 1 = 25.9


RAS-CC670-203NC

16.6-752000-04-20




BT0107-12 MW97 1999-03

TABLE 16.6.18 HINGE SPC RESULTANTS FOR CC670-17325Node Pos RESULTANT

4542 0 9.81784E+01 4543 0 2.81044E+01 4544 0 2.89034E+01 4545 0 2.59491E+01 4546 0 2.46976E+01 4547 0 1.98971E+01 4548 0 1.71653E+01 4549 0 1.50599E+01 4550 0 1.39873E+01 4551 0 1.28579E+01 4552 0 1.23948E+01 4553 0 1.16600E+01 4554 0 1.15678E+01 4555 0 1.09648E+01 4556 0 1.06950E+01 4557 0 1.08813E+01 4558 0 9.76176E+00 4559 0 9.61206E+00 4560 0 9.11023E+00 4561 0 9.04565E+00 4562 0 8.78691E+00 4563 0 9.63410E+00 4564 0 1.11048E+01 4565 0 1.23637E+01 4566 0 1.51435E+01

4521 0 1.51891E+01 4522 0 1.22759E+01 4523 0 9.67766E+00 4524 0 2.15253E+01 4525 0 2.94866E+01 4526 0 1.68740E+01

TABLE 16.6.19 ROLLER FITTING FASTENER FORCES FOR CC670-17325

ELEM. POS Fx(AXIAL) Fy(SHEAR) Fz(SHEAR)3698 0 7.17809E+01 4.44871E+01 7.45966E+01

3699 0 -8.61027E+01 -6.72454E+01 1.47286E+02 3700 0 4.95360E+01 -1.23608E+02 -6.66358E+01 3701 0 -1.27297E+02 -2.49106E+02 -1.53936E+00 4024 0 -1.69501E+01 1.54375E+01 1.21317E+00 4025 0 1.65237E+01 -7.22158E+00 1.70239E+00 4026 0 1.16457E+01 1.69436E+00 -1.05225E+01 4027 0 -1.11677E+01 -9.89329E+00 7.60184E+00



RAS-CC670-203NC

16.6-762000-04-20




BT0107-12 MW97 1999-03

The deflection plot under ultimate load conditions for sectionCC670-17330 is shown in Fig.16.6.37. The maximum deflection is.241 inches.

FIGURE 16.6.37 DEFLECTION PLOT FOR CC670-17330, OPEN DOOR


RAS-CC670-203NC

16.6-772000-04-20




BT0107-12 MW97 1999-03



MS = (1/ (0.386 x 1.1 x 1.3 )) - 1 = .81.

The maximum normalized stress in fiber tension is .172. The marginof safety is:

MS = (1/(0.172 x 1.1)) - 1 = 4.3.


MS = (1/(0.208 x 1.1 x 1.3)) - 1 = 2.4.


RAS-CC670-203NC

16.6-782000-04-20




BT0107-12 MW97 1999-03



RAS-CC670-203NC

16.6-792000-04-20




BT0107-12 MW97 1999-03



RAS-CC670-203NC

16.6-802000-04-20




BT0107-12 MW97 1999-03



RAS-CC670-203NC

16.6-812000-04-20




BT0107-12 MW97 1999-03

HINGE FITTING




σbr = ( 15.2 + 96.9) lbs/ (0.1875 x 0.116)

= 112.1 / (.1875 x 0.116) = 5154.0 lbs/in2


MS = (72000/ 5154.0) – 1 = 12.9

ROLLER FITTINGThe maximum shear load acting through the CBAR, element 3696 is:Shear load = (155.02 + 210.62)1/2 = 261.5 lbs, Table 16.6.21.


σbr = ( 261.5) lbs/ ( .3154 x 0.1875) = 4421.9 lbs/in2

MS = (72000/ 4421.9) – 1 = 15.3


RAS-CC670-203NC

16.6-822000-04-20




BT0107-12 MW97 1999-03

TABLE 16.6.20 HINGE SPC RESULTANTS FOR CC670-17330Node Pos RESULTANT4927 0 1.10470E+01

4928 0 2.58296E+01 4929 0 5.34821E+01

4813 0 7.28606E+01 4930 0 7.48694E+01 4932 0 6.33087E+01 4933 0 4.45354E+01 4934 0 3.39727E+01 4935 0 2.42926E+01 4936 0 1.75086E+01 4937 0 1.24972E+01 4938 0 8.75692E+00 4939 0 6.12522E+00 4940 0 4.22230E+00 4941 0 4.02943E+00 4942 0 3.18585E+00 4943 0 3.71676E+00 4944 0 5.45245E+00 4945 0 3.91898E+00 4946 0 6.00942E+00 4947 0 4.48970E+00 4948 0 5.31590E+00 4949 0 5.87680E+00 4950 0 6.07172E+00 4951 0 4.90638E+00 4952 0 4.98168E+00 4953 0 7.03027E+00 4954 0 3.90140E+00 4955 0 6.73416E+00 4956 0 4.57749E+00 4957 0 4.94697E+00 4958 0 6.81873E+00 4959 0 3.78926E+00 4960 0 5.76367E+00 4961 0 6.03126E+00 4962 0 4.64885E+00 4963 0 5.02076E+00 4964 0 6.56748E+00 4965 0 4.55018E+00 4986 0 4.97763E+00

4966 0 7.18459E+00 4967 0 3.92286E+00 4968 0 5.99043E+00


RAS-CC670-203NC

16.6-832000-04-20




BT0107-12 MW97 1999-03

NODE POS RESULTANT4969 0 6.15739E+00

4970 0 4.51353E+004971 0 5.69206E+004972 0 5.06802E+00

4973 0 5.46831E+00 4974 0 5.08484E+00 4975 0 7.08152E+00 4976 0 4.02316E+00 4977 0 6.55385E+00 4978 0 5.45673E+00 4979 0 5.03615E+00 4980 0 7.32137E+00 4981 0 4.46662E+00 4982 0 6.79613E+00

4985 0 5.71610E+004983 0 5.72773E+00



RAS-CC670-203NC

16.6-842000-04-20




BT0107-12 MW97 1999-03

TABLE 16.6.21 ROLLER FITTING FASTENER FORCES FOR CC670-17330ELEM. POS Fx(AXIAL) Fy(SHEAR) Fz(SHEAR)3690 0 6.02642E+01 3.78518E+01 7.59469E+01

3691 0 -3.65891E+01 1.18874E+01 1.74116E+02 3692 0 7.52167E+01 -1.24200E+02 -1.32403E+02 3693 0 -1.74818E+02 -9.27582E+01 -1.08454E+02 3694 0 6.72390E+01 1.10044E+02 -1.72360E+02 3695 0 -2.09642E+02 8.69287E+01 -1.27457E+02 3696 0 2.08785E+01 1.55231E+02 2.10647E+02 3697 0 -6.77425E+01 7.68708E+01 1.92942E+02



RAS-CC670-203NC

16.6-852000-04-20




BT0107-12 MW97 1999-03




RAS-CC670-203NC

16.6-862000-04-20




BT0107-12 MW97 1999-03



MS = (1/ (0.353 x 1.1 x 1.3 )) - 1 = .98.


MS = (1/(0.131 x 1.1)) - 1 = 5.9.


MS = (1/(0.165 x 1.1 x 1.3)) - 1 = 3.2.


RAS-CC670-203NC

16.6-872000-04-20




BT0107-12 MW97 1999-03



RAS-CC670-203NC

16.6-882000-04-20




BT0107-12 MW97 1999-03



RAS-CC670-203NC

16.6-892000-04-20




BT0107-12 MW97 1999-03



RAS-CC670-203NC

16.6-902000-04-20




BT0107-12 MW97 1999-03

HINGE FITTING




σbr = ( 75.8 +75.4) lbs/ (0.1875 x 0.116)

= 151.2 / (.1875 x 0.116) = 6951.7 lbs/in2


MS = (72000/ 6951.7) – 1 = 9.4

ROLLER FITTINGThe maximum shear load acting through the CBAR, element 3688 is:Shear load = (35.12 + 259.7)1/2 = 262.1 lbs, Table 16.6.23.


σbr = ( 262.1) lbs/ (0.3154 x 0.1875) = 4432.0 lbs/in2

MS = (72000/ 4432.0) – 1 = 15.2


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TABLE 16.6.22 HINGE SPC RESULTANTS FOR CC670-17334Node Pos RESULTANT5016 0 7.57741E+01

5017 0 7.54396E+01 5018 0 6.68787E+01 5019 0 4.42393E+01 5020 0 2.53764E+01 5021 0 1.47459E+01 5022 0 6.68727E+00 5023 0 8.37695E+00 5024 0 1.21917E+01 5025 0 7.91187E+00 5026 0 6.33743E+00 5027 0 5.81690E+00 5028 0 6.19879E+00 5029 0 6.72995E+00 5030 0 7.53082E+00 5031 0 7.44651E+00 5032 0 8.09740E+00 5033 0 8.30214E+00 5034 0 8.39818E+00 5035 0 6.87475E+00 5036 0 6.71088E+00 5037 0 6.87890E+00 5038 0 6.98629E+00 5039 0 4.24333E+00 5040 0 5.56633E+00 5041 0 5.25802E+00 5042 0 5.43837E+00 5043 0 4.77806E+00 5044 0 4.42188E+00 5045 0 5.53539E+00 5046 0 3.95953E+00 5047 0 4.64627E+00 5048 0 4.24921E+00 5049 0 6.31042E+00 5050 0 3.22829E+00 5051 0 5.01463E+00 5052 0 4.59423E+00 5053 0 5.85536E+00 5054 0 3.19884E+00 5055 0 5.01148E+00 5056 0 4.56823E+00 5057 0 5.45222E+00 5058 0 3.87090E+00


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5059 0 4.58718E+00

NODE POS RESULTANT5060 0 4.12013E+005061 0 6.44317E+00


5101 0 2.24180E+015098 0 7.22484E+01


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TABLE 16.6.23 ROLLER FITTING FASTENER FORCES FOR CC670-17334ELEM. POS Fx(AXIAL) Fy(SHEAR) Fz(SHEAR)3682 0 6.45015E+01 -5.62129E+01 7.21384E+01

3683 0 -7.00207E+01 6.60239E+01 7.44050E+01 3684 0 9.42873E+01 8.02515E+01 -6.20751E+01 3685 0 -1.50402E+02 2.26524E+02 3.05702E+01 3686 0 1.15836E+02 6.71702E+01 -1.39331E+02 3687 0 -1.98699E+02 1.67304E+02 -1.48551E+02 3688 0 -8.64334E+01 3.50987E+01 2.59668E+02 3689 0 1.13066E+00 -7.31679E+01 2.11282E+02



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FIGURE 16.6.45 DEFLECTION PLOT FOR CC670-17339, OPEN DOOR


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MS = (1/ (0.262 x 1.1 x 1.3 )) - 1 = 1.67.


MS = (1/(0.108 x 1.1)) - 1 = 7.4.


MS = (1/(0.135 x 1.1 x 1.3)) - 1 = 4.2.


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HINGE FITTING




σbr = ( 72.83 + 68.2) lbs/ (0.1875 x 0.116)

= 141.0 / (.1875 x 0.116) = 6482.8 lbs/in2


MS = (72000/ 6482.8) – 1 = 10.1

The maximum shear load acting through the CBAR, element 3680 is:Shear load = (169.62 + 155.62)1/2 = 230.2 lbs, Table 16.6.25.

The door thickness in this region is .282 inches and the bolt diameteris 3/16 inches.

σbr = ( 230.2) lbs/ (0.282 x 0.1875) = 4353.7 lbs/in2

MS = (72000/ 4353.7) – 1 = 15.5


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TABLE 16.6.24 HINGE SPC RESULTANTS FOR CC670-17339Node Pos RESULTANT



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TABLE 16.6.25 ROLLER FITTING FASTENER FORCES FOR CC670-17339Elem. Pos Fx(AXIAL) Fy(SHEAR) Fz(SHEAR)

3678 0 -8.33705E+00 -1.21292E+02 -1.04431E+02 3679 0 -1.22435E+02 -4.27013E+01 -9.04827E+01 3680 0 -5.19793E+01 -1.69596E+02 1.55606E+02 3681 0 1.34560E+01 -7.01993E+00 1.15014E+02 4048 0 -1.77897E+01 1.44157E+01 -7.21426E+00 4049 0 2.14579E+01 -2.48120E+01 -2.57687E+00 4050 0 2.36008E+01 2.45012E+01 -1.56315E+00 4051 0 -2.71211E+01 -1.41205E+01 1.14332E+01


TABLE 16.6.26 ACTUATOR SPC FORCS

ACTUATOR TX TY TZ *RESULTANT

1 .029 299.7 -.011 299.7

2 -.23 312.5 .17 312.5

3 -.010 383.3 -.003 383.3

*RESULTANT = AXIAL LOAD IN ACTUATOR ROD


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16.6.4 STRESS ANALYSIS OF THE BUTE DOOR IN THE OPENED DOORPOSITION WITH A -.65 PSI LOAD APPLIED

The model for this load case is the same as the +2.5 psi load case.Applying a negative load 3 times smaller than +2.5 psi results indisplacements that are approximately 3 times smaller but in theopposite direction. The results of this analysis is not presentedbecause larger margins are obtained.

Composite Stress Analysis

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