EFFECTIVITY PAGE DATE ISSUE PAGE DATE ISSUE PAGE DATE ISSUE 24/07/14 24/07/14

Size: px
Start display at page:

Download "EFFECTIVITY PAGE DATE ISSUE PAGE DATE ISSUE PAGE DATE ISSUE 24/07/14 24/07/14"

Transcription

1

2 173 ROCHEFORT FAX: (33) EFFECTIVITY PAGE DATE ISSUE PAGE DATE ISSUE PAGE DATE ISSUE /7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/14 24/7/ /7/14 24/7/14 ILA-655D /32

3

4

5 173 ROCHEFORT FAX: (33) INTENTIONALLY BLANK ILA-655D /32

6 TABLE OF CONTENTS 173 ROCHEFORT FAX: (33) TITLE PAGE... 1 EFFECTIVITY... 2 BLANK PAGE... 3 REVISION... 4 BLANK PAGE... 5 TABLE OF CONTENTS INTRODUCTION LIST OF DRAWING TOOLS OF CALCULATION LIST OF REFERENCE UNITS LIST OF ACRONYMS AIRCRAFT REFERENCE SYSTEM AXIS AIRCRAFT INTERFACE MECHANICAL PROPERTIES LOAD CASES DEFINITION CENTER OF GRAVITY REARWARD RIGHT GALLEY A13/15-J11 P/N 655D29826 WEIGHT MESH GENERATION A/C INTERFACE POINTS AND BOUNDARY CONDITIONS MATERIALS AND FASTENERS MECHANICAL PROPERTIES Metallic materials Inserts mechanical properties Fasteners mechanical properties Sandwich panels dimensions and composition Sandwich panels mechanical properties CONCLUSION ILA-655D /32

7 173 ROCHEFORT FAX: (33) INTRODUCTION The purpose of this analysis is to produce a Interface Load Analysis Report Type of structure: REARWARD RIGHT GALLEY A13/15-J11 Part number: P/N 655D29826 Aircraft: n/a Location: Rwd Right Type of aircraft: ATR 42/72. The results of the analysis are the forces applied on aircraft mechanical interfaces LIST OF DRAWING The finite element model (FEM) of the stowage was performed according to the following drawing: General arrangement drawing: SMRD TOOLS OF CALCULATION Meshing, solver, pre - and post-processing : Patran 28r2 & Nastran 28 r1a ILA-655D /32

8 173 ROCHEFORT FAX: (33) LIST OF REFERENCE Applicable standards - documents references: EASA/CS 25: ATR Technical specifications: DT/MD-59/14 ed ed. 1: ATR 42 & ATR 72 Aménagement cabine new look Spécification technique d'équipements ed. 19: ATR Spécification technique d'équipements Simair specification: A iss.3: Calculation datas ATR programs CDCC-DT/MD-59/14 iss.: Technical Specification Rearward right galley A13/15-J11 Technical reference book: Airframe Stress Analysis and Sizing, Michael Chun-Yung NIU 1.4. UNITS The units used in this report are: Length mm Mass kg Force N Moment N.mm Stiffness N/mm Pressure MPa (N/mm 2 ) Acceleration translation gravity m/s 2 Density kg/m 3 ILA-655D /32

9 173 ROCHEFORT FAX: (33) LIST OF ACRONYMS A/C Aircraft CS e SRW M n x, n y, n z F x F y F z Mx M y M z g G Γ x Γ y Γ z ρ K x K y K z RF SM Rwd Fwd Swd Uwd Dwd Coordinate System Thickness Simulated Reconstituted Weight Mass Load factors Load Load Load Load Load Load Acceleration translation gravity Acceleration translation gravity Acceleration translation gravity Acceleration translation gravity Acceleration translation gravity Density Stiffness Stiffness Stiffness Reserve Factor Safety Margin Rearward Forward Sideward Upward Downward ILA-655D /32

10 173 ROCHEFORT FAX: (33) AIRCRAFT REFERENCE SYSTEM AXIS The loading directions are given in Aircraft axes. +X: -X: +Y: -Y: +Z: -Z: REARWARD direction FORWARD direction RIGHT direction LEFT direction UP direction DOWN direction ILA-655D /32

11 173 ROCHEFORT FAX: (33) AIRCRAFT INTERFACE MECHANICAL PROPERTIES Following values are extracted from document ref. A iss.3, 5. Lower attachments on seat tracks Kx = 15 N/mm Ky = 15 N/mm Kz = 5 N/mm Upper attachments with tie rod 15 N/mm in rod axis direction Table 1.7-1: Aircraft interface stiffness 1.8. LOAD CASES DEFINITION Ultimate loads for cabin furniture are extracted from document ref. CDCC-AJ-DT-MD iss., Appendix A. Load case number Max flight and landing loads description 1 3.2g Upward 2 9.g Forward 3 3.g Sideward RH 4 3.g Sideward LH 5 7.8g Downward 6 2.1g Rearward g Fwd + 1.5g Swd RH + 2.g Uwd 8.6g Fwd + 1.5g Swd LH + 2.g Uwd 9 ABUSE LOAD (1) Table 1.8-1: Load cases description (1) An abuse load is considered to substantiate the mechanical behavior of the sliding table (see 1.1). This table must support a maximum loading of 4Kg modeled applying a equally distributed pressure on its surface and oriented down. ILA-655D /32

12 173 ROCHEFORT FAX: (33) CENTER OF GRAVITY The estimated coordinates of the center of gravity for Rearward right galley A13/15-J11 P/N 655D29826 are provided in the aircraft axis by the Table Nota: Internal equipments are represented by pressure loads on compartment surfaces (see 1.1), so the CoG location for galley with loading depends on which compartment face loads are applied. Then the CoG with loading determined below is the average location. CoG coordinate Without loadings With loadings (mm) (mm) CoG X coordinate CoG Y coordinate CoG Z coordinate Table 1.9-1: Coordinates of center of gravity in global system aircraft. ILA-655D /32

13 173 ROCHEFORT FAX: (33) REARWARD RIGHT GALLEY A13/15-J11 P/N 655D29826 WEIGHT All internal equipments of the REARWARD RIGHT GALLEY A13/15-J11 P/N 655D29826 and their masses are detailed in the following Figure 1.1-1, Table and Table This finite element modeling was done with a total mass of kg Figure 1.1-1: Internal equipments location ILA-655D /32

14 173 ROCHEFORT FAX: (33) ITEM DESIGNATION CAPACITIES Qty STRUCTURAL WEIGHT 8 kg 1 1 HOT-JUG 18 kg 1 2 WORKING AREA 2 kg 1 3 WATER-HEATER 1.6 kg 1 4 STOWAGE 3 kg 1 5 BASIN WATER TANK 2 kg 1 8 HALF-SIZE TROLLEY 6 kg 1 9 HALF-SIZE TROLLEY 6 kg 1 1 DF 115 OVEN 51 kg 1 11 STOWAGE 12 kg 1 12 WASTE BIN 1 kg 1 13 SU 2 kg 1 14 SU 2 kg 1 15 STOWAGE 3 kg 1 EXTERNAL WEIGHT (STOWAGE) 4 kg 1 TOTAL WEIGHT kg TOTAL WEIGHT WITHOUT TROLLEY 37.6 kg Table 1.1-1: Weight description of internal equipments The maximum loading of the two tables are given by the Table TABLES MAXIMUM LOADING ITEM DESIGNATION CAPACITIES Qty 6 FOLDING TABLE 4 kg 1 16 SLIDING TABLE 4 kg 1 Table 1.1-2: Tables maximum loading In load case 7.8g downward, trolleys weight are not taken into account, because trolleys forces are applied onto floor panels, the total weight for this load case without trolley is 37.6 kg. ILA-655D /32

15 173 ROCHEFORT FAX: (33) MESH GENERATION The finite element model is detailed below: Nodes: 9538 Elements: Lumped Mass: Rigid element: 229 Thin shell linear quadrilateral: 9632 Thin shell linear triangle: 18 Linear rod: 3 Solid linear tetrahedron: Node to ground translational spring: 6 Constraint element: 3 The folding table is meshed in closed position and the sliding table is fully extended. The finite element model is detailed in the following figures. ILA-655D /32

16 173 ROCHEFORT FAX: (33) FEM CAD model Internal and external metal sheets of reinforcement (3mm thickness) [PRT D / PRT D ] replaced by 2 external corners in aluminum 217T4 (3mm thickness) (see Figure ) Composite panels are meshed with coincident nodes except for regions detailed below Figure : Galley A13/15-J11 meshing (1/4) ILA-655D /32

17 173 ROCHEFORT FAX: (33) FEM CAD model Panels connected to others with metallic plates (no coincident mesh) Panels connected to others with metallic plates (no coincident mesh) Figure : Galley A13/15-J11 meshing (2/4) ILA-655D /32

18 173 ROCHEFORT FAX: (33) FEM CAD model Panels connected to others with metallic corners (no coincident mesh) Cut in the decorative band FEM Figure : Galley A13/15-J11 meshing (3/4) ILA-655D /32

19 173 ROCHEFORT FAX: (33) FEM CAD model Two panels connected with rigid elements Figure : Galley J11 meshing (4/4) Lines of 5 fasteners NAS attached to panels 22 mm 24 mm 24 mm 26 mm Faces of the two corners in aluminum 217 T4 are parallel to the panels with which they are attached. Figure : Galley J11 meshing Dimensions and attachment of corners added ILA-655D /32

20 173 ROCHEFORT FAX: (33) A/C INTERFACE POINTS AND BOUNDARY CONDITIONS The Figure and Table provide the location of the fitting points where the boundary conditions are applied and the constrained directions Figure : Lower attachments ILA-655D /32

21 173 ROCHEFORT FAX: (33) Figure : Upper attachments Constraints (X: Fixed / -: Free) Location Type Ux Uy Uz Rx Ry Rz Point 2 ( ;635.;4215.5) Tie rod X X X X Point 4 ( ;724.;4119.) Tie rod Y X X X Point 6 (2983.;733.;4119.) Tie rod Y X X X Point 1 (2115.7;325.;2338.7) Seat track X X X Point 11 ( ;325;2338.7) Seat track X X X Point 12 ( ;325.;2338.7) Seat track X X X Point 13 (2115.7;96.;2338.7) Seat track X X X Point 14 ( ;96.;2338.7) Seat track X X X Point 15 ( ;96.;2338.7) Seat track X X X Table : Coordinate locations of attachments in global system ILA-655D /32

22 173 ROCHEFORT FAX: (33) MATERIALS AND FASTENERS MECHANICAL PROPERTIES Metallic materials E (MPa) ν ρ (kg/mm 3 ) Ultimate tensile strength (MPa) Yield tensile strength (MPa) 224T3 & E T4 (1) 217A T4 (1) E H111 (1) E T6 (1) E Z1CNF18-9 (1) E (1) values issue from document ref. A iss. 3, 8.1 Table : Metallic material properties For 224T3 & 224T4, the stress-strain curve is represented by the Ramberg-Osgood method: ε total =(σ/e) +.2 (σ/σ.2 ) n with: ε total : total strain σ: stress σ.2 ; yield stress E: modulus of elasticity n: Ramberg-Osgood parameter (n=11 for 224 series, and n=16 for 7175 series) n/a Inserts mechanical properties ILA-655D /32

23 173 ROCHEFORT FAX: (33) Fasteners mechanical properties Reference Diameter [mm] Ftu [N/mm²] Fsu [N/mm²] Tensile/Compression allowable load [N] Single shear allowable load [N] Rivet ASNA-78-A5-3 (1) NAS (1) NAS 665 (1) NSA514P-132 (1) Screw NAS 134 (1) NAS 135 (1) NAS181-3 (2) SP1 (1) Nut NSA 55-4 (3) NSA 55-5 (3) Rod end NSA (1) NSA (1) (1) values extracted from A Calculations datas ATR Iss 3 (2) see standard: 16ksi=113 MPa (3) see standard NSA55 Table : Fasteners strength ILA-655D /32

24 173 ROCHEFORT FAX: (33) Sandwich panels dimensions and composition These panels consist of a composite sandwich structure Skins Honeycomb ID THICKNESS CORE PLIES THICKNESS Honeycomb 2x2 Fabric mm HRH1 3/ /38%/ mm Honeycomb 2x3 Fabric 1B 12.7 mm HRH1 3/ /38%/ mm Honeycomb 2x4 Fabric mm HRH1 3/ /38%/ mm Honeycomb 2x6 Fabric mm HRH1 3/ /38%/ mm 3B 12.7 mm 1x6 Fabric Honeycomb 1x4 Fabric HRH1 3/ /38%/ mm Honeycomb 2x8 Fabric mm HRH1 3/ /38%/ mm mm Honeycomb HRH1 3/ x1 Fabric 26/38%/7781 Table : Sandwich panels composition.21 mm Nota : Some panels have a specific area designed with metallic plate between glasses plies. They are specified in drawings of panel s molding and detailed in figures below. All panels are sandwich panels defined within an optimized configuration, so: = 2x2 plies means: 2 plies + honeycomb + 2 plies = 2x4 plies means: 4 plies + honeycomb + 4 plies = 2x6 plies means: 6 plies + honeycomb + 6 plies = aluminum sheet (1mm) + 2 plies + honeycomb + 2 plies + aluminum sheet (1mm) ILA-655D /32

25 173 ROCHEFORT FAX: (33) mm 487 mm Figure 3: Galley A13/15-J11 Laminate areas description (1/5) ILA-655D /32

26 173 ROCHEFORT FAX: (33) mm 287 mm 198 mm Figure 4: Galley A13/15-J11 Laminate areas description (2/5) ILA-655D /32

27 173 ROCHEFORT FAX: (33) mm 22 mm Figure 5: Galley A13/15-J11 Laminate areas description (3/5) ILA-655D /32

28 173 ROCHEFORT FAX: (33) mm 6mm 11mm 4mm 6mm 8mm 12mm 12mm Figure 6: Galley A13/15-J11 Laminate areas description (4/5) ILA-655D /32

29 173 ROCHEFORT FAX: (33) mm 1mm 43mm 61mm 112mm 185mm 165mm 125mm Figure 7: Galley A13/15-J11 Laminate areas description (5/5) ILA-655D /32

30 173 ROCHEFORT FAX: (33) Sandwich panels mechanical properties Characteristics (1) HONEYCOMB HRH1 3/16 2. FABRIC 26/38%/7781 E1 (MPa) 1 27 E2 (MPa) 1 27 ν G12 (MPa) 1 42 G13 (MPa) G23 (MPa) ρ (kg/mm 3 ) 3.2E E-6 σ t1 (MPa) σ c1 (MPa).8 2 σ t2 (MPa) σ c2 (MPa).8 2 τ 12 (MPa) ply thickness (mm).21 (1) values issue from ref. A iss. 3, 8.7, except for G12, G13 and G23 values extracted from doc - CAQ/DT/NT/25 iss.a - SA-653B iss. Table : Sandwich panels mechanical properties ILA-655D /32

31 173 ROCHEFORT FAX: (33) The following Table provides the action load of galley A and D onto aircraft structure. Loads components are defined in aircraft axis system. Table : Interface loads ILA-655D /32

32 173 ROCHEFORT FAX: (33) CONCLUSION The Table provides the maximum and minimum forces at aircraft interfaces into its coordinate: Table : Max and min interface loads (N) ILA-655D /32

PRELIMINARY PREDICTION OF SPECIMEN PROPERTIES CLT and 1 st order FEM analyses

PRELIMINARY PREDICTION OF SPECIMEN PROPERTIES CLT and 1 st order FEM analyses OPTIMAT BLADES Page 1 of 24 PRELIMINARY PREDICTION OF SPECIMEN PROPERTIES CLT and 1 st order FEM analyses first issue Peter Joosse CHANGE RECORD Issue/revision date pages Summary of changes draft 24-10-02

More information

Stress Analysis and Validation of Superstructure of 15-meter Long Bus under Normal Operation

Stress Analysis and Validation of Superstructure of 15-meter Long Bus under Normal Operation AIJSTPME (2013) 6(3): 69-74 Stress Analysis and Validation of Superstructure of 15-meter Long Bus under Normal Operation Lapapong S., Pitaksapsin N., Sucharitpwatkul S.*, Tantanawat T., Naewngerndee R.

More information

UNIVERSITY OF SASKATCHEWAN ME MECHANICS OF MATERIALS I FINAL EXAM DECEMBER 13, 2008 Professor A. Dolovich

UNIVERSITY OF SASKATCHEWAN ME MECHANICS OF MATERIALS I FINAL EXAM DECEMBER 13, 2008 Professor A. Dolovich UNIVERSITY OF SASKATCHEWAN ME 313.3 MECHANICS OF MATERIALS I FINAL EXAM DECEMBER 13, 2008 Professor A. Dolovich A CLOSED BOOK EXAMINATION TIME: 3 HOURS For Marker s Use Only LAST NAME (printed): FIRST

More information

D : SOLID MECHANICS. Q. 1 Q. 9 carry one mark each. Q.1 Find the force (in kn) in the member BH of the truss shown.

D : SOLID MECHANICS. Q. 1 Q. 9 carry one mark each. Q.1 Find the force (in kn) in the member BH of the truss shown. D : SOLID MECHANICS Q. 1 Q. 9 carry one mark each. Q.1 Find the force (in kn) in the member BH of the truss shown. Q.2 Consider the forces of magnitude F acting on the sides of the regular hexagon having

More information

Mechanical Engineering Ph.D. Preliminary Qualifying Examination Solid Mechanics February 25, 2002

Mechanical Engineering Ph.D. Preliminary Qualifying Examination Solid Mechanics February 25, 2002 student personal identification (ID) number on each sheet. Do not write your name on any sheet. #1. A homogeneous, isotropic, linear elastic bar has rectangular cross sectional area A, modulus of elasticity

More information

FEM Validation. 12th January David Schmid Teamleader Structural Analysis

FEM Validation. 12th January David Schmid Teamleader Structural Analysis FEM Validation 12th January 2012 David Schmid Teamleader Structural Analysis FEM Validation and Verification Each FE model which is used to substantiate flight material must be verified Depending on the

More information

Spring Elements In Nastran Blog Post pdf

Spring Elements In Nastran Blog Post pdf Spring Elements In Nastran Blog Post pdf Author: Surya Batchu Senior Stress Engineer Founder, STRESS EBOOK LLC. http://www.stressebook.com 1 P a g e In this post, you will discover some interesting aspects

More information

IDE 110 Mechanics of Materials Spring 2006 Final Examination FOR GRADING ONLY

IDE 110 Mechanics of Materials Spring 2006 Final Examination FOR GRADING ONLY Spring 2006 Final Examination STUDENT S NAME (please print) STUDENT S SIGNATURE STUDENT NUMBER IDE 110 CLASS SECTION INSTRUCTOR S NAME Do not turn this page until instructed to start. Write your name on

More information

Comparison of Ply-wise Stress-Strain results for graphite/epoxy laminated plate subjected to in-plane normal loads using CLT and ANSYS ACP PrepPost

Comparison of Ply-wise Stress-Strain results for graphite/epoxy laminated plate subjected to in-plane normal loads using CLT and ANSYS ACP PrepPost Comparison of Ply-wise Stress-Strain results for graphite/epoxy laminated plate subjected to in-plane normal loads using CLT and ANSYS ACP PrepPost 1 Mihir A. Mehta, 2 Satyen D. Ramani 1 PG Student, Department

More information

Finite Element Analysis Of A High-Speed Suspension Boat Fuselage

Finite Element Analysis Of A High-Speed Suspension Boat Fuselage Lehigh University Lehigh Preserve Theses and Dissertations 2017 Finite Element Analysis Of A High-Speed Suspension Boat Fuselage Lean Fang Lehigh University Follow this and additional works at: https://preserve.lehigh.edu/etd

More information

Impact and Crash Modeling of Composite Structures: A Challenge for Damage Mechanics

Impact and Crash Modeling of Composite Structures: A Challenge for Damage Mechanics Impact and Crash Modeling of Composite Structures: A Challenge for Damage Mechanics Dr. A. Johnson DLR Dr. A. K. Pickett ESI GmbH EURO-PAM 99 Impact and Crash Modelling of Composite Structures: A Challenge

More information

Effect of Specimen Dimensions on Flexural Modulus in a 3-Point Bending Test

Effect of Specimen Dimensions on Flexural Modulus in a 3-Point Bending Test Effect of Specimen Dimensions on Flexural Modulus in a 3-Point Bending Test M. Praveen Kumar 1 and V. Balakrishna Murthy 2* 1 Mechanical Engineering Department, P.V.P. Siddhartha Institute of Technology,

More information

Introduction to Aerospace Engineering

Introduction to Aerospace Engineering Introduction to Aerospace Engineering Lecture slides Challenge the future 1 Aircraft & spacecraft loads Translating loads to stresses Faculty of Aerospace Engineering 29-11-2011 Delft University of Technology

More information

AERSYS KNOWLEDGE UNIT

AERSYS KNOWLEDGE UNIT -7016 1. INTRODUCTION The scope of this document is to provide a clarification and a deeper understanding of the two different ways to move the mid plane of the element out of the nodal plane. Although

More information

Initial Stress Calculations

Initial Stress Calculations Initial Stress Calculations The following are the initial hand stress calculations conducted during the early stages of the design process. Therefore, some of the material properties as well as dimensions

More information

EXPERIMENTAL AND NUMERICAL STUDY OF OBLIQUE IMPACT ON HELICOPTER BLADES INFLUENCE OF THE CURVATURE

EXPERIMENTAL AND NUMERICAL STUDY OF OBLIQUE IMPACT ON HELICOPTER BLADES INFLUENCE OF THE CURVATURE EXPERIMENTAL AND NUMERICAL STUDY OF OBLIQUE IMPACT ON HELICOPTER BLADES INFLUENCE OF THE CURVATURE F. Pascal a, P. Navarro a*, S. Marguet a, J.F. Ferrero a, J. Aubry b, S. Lemaire b a Université de Toulouse,

More information

NATURAL FREQUENCIES OF A HONEYCOMB SANDWICH PLATE Revision F. A diagram of a honeycomb plate cross-section is shown in Figure 1.

NATURAL FREQUENCIES OF A HONEYCOMB SANDWICH PLATE Revision F. A diagram of a honeycomb plate cross-section is shown in Figure 1. NATURAL FREQUENCIES OF A HONEYCOMB SANDWICH PLATE Revision F By Tom Irvine Email: tomirvine@aol.com August 5, 008 Bending Stiffness of a Honeycomb Sandwich Plate A diagram of a honeycomb plate cross-section

More information

Plate Forces and Moments Blog Post pdf

Plate Forces and Moments Blog Post pdf Plate Forces and Moments Blog Post pdf Author: Surya Batchu Senior Stress Engineer Founder, STRESS EBOOK LLC. http://www.stressebook.com 1 P a g e Plate Forces and Moments - Intro: You may have heard these

More information

STRUCTURAL ANALYSIS OF THE LIFTING DEVICE DETECTOR SUPPORTS FOR THE LHCb VERTEX LOCATOR (VELO)

STRUCTURAL ANALYSIS OF THE LIFTING DEVICE DETECTOR SUPPORTS FOR THE LHCb VERTEX LOCATOR (VELO) National Institute for Nuclear Physics and High Energy Physics Kruislaan 409 1098 SJ Amsterdam The Netherlands NIKHEF Reference no.: MT-VELO 04-2 EDMS no: 466608 OF THE LIFTING DEVICE DETECTOR SUPPORTS

More information

Procedure for Performing Stress Analysis by Means of Finite Element Method (FEM)

Procedure for Performing Stress Analysis by Means of Finite Element Method (FEM) Procedure for Performing Stress Analysis by Means of Finite Element Method (FEM) Colaboração dos engºs Patrício e Ediberto da Petrobras 1. Objective This Technical Specification sets forth the minimum

More information

Telescope Mechanical Design

Telescope Mechanical Design Telescope Mechanical Design Albert Lin The Aerospace Corporation (310) 336-1023 albert.y.lin@aero.org 6/27/06 6/27/06 Telescope Mechanical Design 1 Overview Design Overview Instrument Requirements Mechanical

More information

OPTIMIZATION OF THE COMPOSITE MATERIALS OF TANKS USING FINITE ELEMENT METHOD AND STRAIN GAUGES

OPTIMIZATION OF THE COMPOSITE MATERIALS OF TANKS USING FINITE ELEMENT METHOD AND STRAIN GAUGES Annals of the University of Petroşani, Mechanical Engineering, 13 (2011), 143-150 143 OPTIMIZATION OF THE COMPOSITE MATERIALS OF TANKS USING FINITE ELEMENT METHOD AND STRAIN GAUGES A. STANCIU 1, I. CURTU

More information

EDEXCEL NATIONAL CERTIFICATE/DIPLOMA SCIENCE FOR TECHNICIANS OUTCOME 1 - STATIC AND DYNAMIC FORCES TUTORIAL 3 STRESS AND STRAIN

EDEXCEL NATIONAL CERTIFICATE/DIPLOMA SCIENCE FOR TECHNICIANS OUTCOME 1 - STATIC AND DYNAMIC FORCES TUTORIAL 3 STRESS AND STRAIN EDEXCEL NATIONAL CERTIFICATE/DIPLOMA SCIENCE FOR TECHNICIANS OUTCOME 1 - STATIC AND DYNAMIC FORCES TUTORIAL 3 STRESS AND STRAIN 1 Static and dynamic forces Forces: definitions of: matter, mass, weight,

More information

ANALYSIS AND SIMULATION OF AN AIRPLANE SEAT DURING VERTICAL IMPACTS

ANALYSIS AND SIMULATION OF AN AIRPLANE SEAT DURING VERTICAL IMPACTS ANALYSIS AND SIMULATION OF AN AIRPLANE SEAT DURING VERTICAL IMPACTS ABSTRACT Luís Carlos das Neves Ferreira luis.neves.ferreira@ist.utl.pt Instituto Superior Técnico, Universidade de Lisboa, Portugal December

More information

Failure analysis of serial pinned joints in composite materials

Failure analysis of serial pinned joints in composite materials Indian Journal of Engineering & Materials Sciences Vol. 18, April 2011, pp. 102-110 Failure analysis of serial pinned joints in composite materials Alaattin Aktaş* Department of Mechanical Engineering,

More information

Finite Element Modeling of an Aluminum Tricycle Frame

Finite Element Modeling of an Aluminum Tricycle Frame Finite Element Modeling of an Aluminum Tricycle Frame A. Rodríguez, B. Chiné*, and J. A. Ramírez Costa Rica Institute of Technology, School of Materials Science and Engineering, Cartago, Costa Rica *Corresponding

More information

SECTION 23 - METRIC DESIGN INFORMATION. Table of Contents

SECTION 23 - METRIC DESIGN INFORMATION. Table of Contents SECTION 23 - METRIC DESIGN INFORMATION Table of Contents Metric System Conversions and Abbreviations... 23-3 EXTREN Availability List... 23-4 EXTREN vs. Traditional Materials... 23-6 SECTION 23 METRIC

More information

Special edition paper

Special edition paper Development of New Aseismatic Structure Using Escalators Kazunori Sasaki* Atsushi Hayashi* Hajime Yoshida** Toru Masuda* Aseismatic reinforcement work is often carried out in parallel with improvement

More information

BTECH MECHANICAL PRINCIPLES AND APPLICATIONS. Level 3 Unit 5

BTECH MECHANICAL PRINCIPLES AND APPLICATIONS. Level 3 Unit 5 BTECH MECHANICAL PRINCIPLES AND APPLICATIONS Level 3 Unit 5 FORCES AS VECTORS Vectors have a magnitude (amount) and a direction. Forces are vectors FORCES AS VECTORS (2 FORCES) Forces F1 and F2 are in

More information

and F NAME: ME rd Sample Final Exam PROBLEM 1 (25 points) Prob. 1 questions are all or nothing. PROBLEM 1A. (5 points)

and F NAME: ME rd Sample Final Exam PROBLEM 1 (25 points) Prob. 1 questions are all or nothing. PROBLEM 1A. (5 points) ME 270 3 rd Sample inal Exam PROBLEM 1 (25 points) Prob. 1 questions are all or nothing. PROBLEM 1A. (5 points) IND: In your own words, please state Newton s Laws: 1 st Law = 2 nd Law = 3 rd Law = PROBLEM

More information

Aircraft Structures Design Example

Aircraft Structures Design Example University of Liège Aerospace & Mechanical Engineering Aircraft Structures Design Example Ludovic Noels Computational & Multiscale Mechanics of Materials CM3 http://www.ltas-cm3.ulg.ac.be/ Chemin des Chevreuils

More information

Finite Element Method in Geotechnical Engineering

Finite Element Method in Geotechnical Engineering Finite Element Method in Geotechnical Engineering Short Course on + Dynamics Boulder, Colorado January 5-8, 2004 Stein Sture Professor of Civil Engineering University of Colorado at Boulder Contents Steps

More information

PROBLEM #1.1 (4 + 4 points, no partial credit)

PROBLEM #1.1 (4 + 4 points, no partial credit) PROBLEM #1.1 ( + points, no partial credit A thermal switch consists of a copper bar which under elevation of temperature closes a gap and closes an electrical circuit. The copper bar possesses a length

More information

Principles of Finite Element for Design Engineers and Analysts. Ayman Shama, Ph.D., P.E., F.ASCE

Principles of Finite Element for Design Engineers and Analysts. Ayman Shama, Ph.D., P.E., F.ASCE Principles of Finite Element for Design Engineers and Analysts Ayman Shama, Ph.D., P.E., F.ASCE Outline Principles of Engineering Analysis The development of the finite element method Types of elements

More information

MINE ROOF SUPPORT DESIGN AND ANALYSIS. Document no : Revision no : 1.0

MINE ROOF SUPPORT DESIGN AND ANALYSIS. Document no : Revision no : 1.0 MINE ROOF SUPPORT DESIGN AND ANALYSIS Document no : 1806-2697-23 Revision no : 1.0 DOCUMENT TITLE : MINE ROOF SUPPORT DESIGN AND ANALYSIS DOCUMENT NUMBER : 1806-2697-23 ISSUE : Issue 1.0 DATE : 7 October

More information

COMPARISON OF NUMERICAL SIMULATION AND EXPERIMENT OF A FLEXIBLE COMPOSITE CONNECTING ROD

COMPARISON OF NUMERICAL SIMULATION AND EXPERIMENT OF A FLEXIBLE COMPOSITE CONNECTING ROD 10th International DAAAM Baltic Conference "INDUSTRIAL ENGINEERING - 12-13 May 2015, Tallinn, Estonia COMPARISON OF NUMERICAL SIMULATION AND EXPERIMENT OF A FLEXIBLE COMPOSITE CONNECTING ROD Sedláček,

More information

Lab Exercise #3: Torsion

Lab Exercise #3: Torsion Lab Exercise #3: Pre-lab assignment: Yes No Goals: 1. To evaluate the equations of angular displacement, shear stress, and shear strain for a shaft undergoing torsional stress. Principles: testing of round

More information

Direct and Shear Stress

Direct and Shear Stress Direct and Shear Stress 1 Direct & Shear Stress When a body is pulled by a tensile force or crushed by a compressive force, the loading is said to be direct. Direct stresses are also found to arise when

More information

1-1 Locate the centroid of the plane area shown. 1-2 Determine the location of centroid of the composite area shown.

1-1 Locate the centroid of the plane area shown. 1-2 Determine the location of centroid of the composite area shown. Chapter 1 Review of Mechanics of Materials 1-1 Locate the centroid of the plane area shown 650 mm 1000 mm 650 x 1- Determine the location of centroid of the composite area shown. 00 150 mm radius 00 mm

More information

Design of AAC wall panel according to EN 12602

Design of AAC wall panel according to EN 12602 Design of wall panel according to EN 160 Example 3: Wall panel with wind load 1.1 Issue Design of a wall panel at an industrial building Materials with a compressive strength 3,5, density class 500, welded

More information

Optimum Height of Plate Stiffener under Pressure Effect

Optimum Height of Plate Stiffener under Pressure Effect The st Regional Conference of Eng. Sci. NUCEJ Spatial ISSUE vol., No.3, 8 pp 459-468 Optimum Height of Plate Stiffener under Pressure Effect Mazin Victor Yousif M.Sc Production Engineering University of

More information

N = Shear stress / Shear strain

N = Shear stress / Shear strain UNIT - I 1. What is meant by factor of safety? [A/M-15] It is the ratio between ultimate stress to the working stress. Factor of safety = Ultimate stress Permissible stress 2. Define Resilience. [A/M-15]

More information

MESH MODELING OF ANGLE-PLY LAMINATED COMPOSITE PLATES FOR DNS AND IPSAP

MESH MODELING OF ANGLE-PLY LAMINATED COMPOSITE PLATES FOR DNS AND IPSAP 16 TH INTERNATIONAL CONFERENCE ON COMPOSITE MATERIALS MESH MODELING OF ANGLE-PLY LAMINATED COMPOSITE PLATES FOR DNS AND IPSAP Wanil Byun*, Seung Jo Kim*, Joris Wismans** *Seoul National University, Republic

More information

Mechanics of Materials MENG 270 Fall 2003 Exam 3 Time allowed: 90min. Q.1(a) Q.1 (b) Q.2 Q.3 Q.4 Total

Mechanics of Materials MENG 270 Fall 2003 Exam 3 Time allowed: 90min. Q.1(a) Q.1 (b) Q.2 Q.3 Q.4 Total Mechanics of Materials MENG 70 Fall 00 Eam Time allowed: 90min Name. Computer No. Q.(a) Q. (b) Q. Q. Q.4 Total Problem No. (a) [5Points] An air vessel is 500 mm average diameter and 0 mm thickness, the

More information

TESTING AND ANALYSIS OF COMPOSITE SANDWICH BEAMS

TESTING AND ANALYSIS OF COMPOSITE SANDWICH BEAMS TESTING AND ANALYSIS OF COMPOSITE SANDWICH BEAMS I. M. Daniel, J. L. Abot, and K. A. Wang Walter P. Murphy Professor, Departments of Civil and Mechanical Engineering, Robert R. McCormick School of Engineering

More information

EDEXCEL NATIONAL CERTIFICATE/DIPLOMA MECHANICAL PRINCIPLES AND APPLICATIONS NQF LEVEL 3 OUTCOME 1 - LOADING SYSTEMS TUTORIAL 3 LOADED COMPONENTS

EDEXCEL NATIONAL CERTIFICATE/DIPLOMA MECHANICAL PRINCIPLES AND APPLICATIONS NQF LEVEL 3 OUTCOME 1 - LOADING SYSTEMS TUTORIAL 3 LOADED COMPONENTS EDEXCEL NATIONAL CERTIICATE/DIPLOMA MECHANICAL PRINCIPLES AND APPLICATIONS NQ LEVEL 3 OUTCOME 1 - LOADING SYSTEMS TUTORIAL 3 LOADED COMPONENTS 1. Be able to determine the effects of loading in static engineering

More information

Finite Element Simulation of Bar-Plate Friction Welded Joints Steel Product Subjected to Impact Loading

Finite Element Simulation of Bar-Plate Friction Welded Joints Steel Product Subjected to Impact Loading Finite Element Simulation of Bar-Plate Friction Welded Joints Steel Product Subjected to Impact Loading Yohanes, a,* Muftil Badri, a Panji Adino, a Dodi Sofyan Arief, a and Musthafa Akbar, a a) Department

More information

Level 7 Postgraduate Diploma in Engineering Computational mechanics using finite element method

Level 7 Postgraduate Diploma in Engineering Computational mechanics using finite element method 9210-203 Level 7 Postgraduate Diploma in Engineering Computational mechanics using finite element method You should have the following for this examination one answer book No additional data is attached

More information

σ = F/A ε = L/L σ ε a σ = Eε

σ = F/A ε = L/L σ ε a σ = Eε Material and Property Information This chapter includes material from the book Practical Finite Element Analysis. It also has been reviewed and has additional material added by Sascha Beuermann. Hooke

More information

Two Tier projects for students in ME 160 class

Two Tier projects for students in ME 160 class ME 160 Introduction to Finite Element Method Spring 2016 Topics for Term Projects by Teams of 2 Students Instructor: Tai Ran Hsu, Professor, Dept. of Mechanical engineering, San Jose State University,

More information

Response Spectrum Analysis Shock and Seismic. FEMAP & NX Nastran

Response Spectrum Analysis Shock and Seismic. FEMAP & NX Nastran Response Spectrum Analysis Shock and Seismic FEMAP & NX Nastran Table of Contents 1. INTRODUCTION... 3 2. THE ACCELEROGRAM... 4 3. CREATING A RESPONSE SPECTRUM... 5 4. NX NASTRAN METHOD... 8 5. RESPONSE

More information

FE-MODELLING GUIDELINES FOR THE DIMENSIONING OF AIRCRAFT CABIN INTERIOR UNDER STATIONARY DYNAMIC LOADS

FE-MODELLING GUIDELINES FOR THE DIMENSIONING OF AIRCRAFT CABIN INTERIOR UNDER STATIONARY DYNAMIC LOADS FE-MODELLING GUIDELINES FOR THE DIMENSIONING OF AIRCRAFT CABIN INTERIOR UNDER STATIONARY DYNAMIC LOADS R. Seemann*, B. Plaumann*, J. Oltmann*, D. Krause* * Hamburg University of Technology (TUHH), Keywords:

More information

Dynamic (Vibrational) and Static Structural Analysis of Ladder Frame

Dynamic (Vibrational) and Static Structural Analysis of Ladder Frame Dynamic (Vibrational) and Static Structural Analysis of Ladder Frame Ketan Gajanan Nalawade 1, Ashish Sabu 2, Baskar P 3 School of Mechanical and building science, VIT University, Vellore-632014, Tamil

More information

EQUILIBRIUM and ELASTICITY

EQUILIBRIUM and ELASTICITY PH 221-1D Spring 2013 EQUILIBRIUM and ELASTICITY Lectures 30-32 Chapter 12 (Halliday/Resnick/Walker, Fundamentals of Physics 9 th edition) 1 Chapter 12 Equilibrium and Elasticity In this chapter we will

More information

DISPENSA FEM in MSC. Nastran

DISPENSA FEM in MSC. Nastran DISPENSA FEM in MSC. Nastran preprocessing: mesh generation material definitions definition of loads and boundary conditions solving: solving the (linear) set of equations components postprocessing: visualisation

More information

Finite element modelling of infinitely wide Angle-ply FRP. laminates

Finite element modelling of infinitely wide Angle-ply FRP. laminates www.ijaser.com 2012 by the authors Licensee IJASER- Under Creative Commons License 3.0 editorial@ijaser.com Research article ISSN 2277 9442 Finite element modelling of infinitely wide Angle-ply FRP laminates

More information

A Repeated Dynamic Impact Analysis for 7x7 Spacer Grids by using ABAQUS/ Standard and Explicit

A Repeated Dynamic Impact Analysis for 7x7 Spacer Grids by using ABAQUS/ Standard and Explicit A Repeated Dynamic Impact Analysis for 7x7 Spacer Grids by using ABAQUS/ Standard and Explicit Kim, Jae-Yong, and Yoon, Kyung-Ho* * Korea Atomic Energy Research Institute ABSTRACT Spacer grids(sg) are

More information

MECHANICS OF MATERIALS. Prepared by Engr. John Paul Timola

MECHANICS OF MATERIALS. Prepared by Engr. John Paul Timola MECHANICS OF MATERIALS Prepared by Engr. John Paul Timola Mechanics of materials branch of mechanics that studies the internal effects of stress and strain in a solid body. stress is associated with the

More information

Mechanical Properties of Materials

Mechanical Properties of Materials Mechanical Properties of Materials Strains Material Model Stresses Learning objectives Understand the qualitative and quantitative description of mechanical properties of materials. Learn the logic of

More information

Vibrationdata FEA Matlab GUI Package User Guide Revision A

Vibrationdata FEA Matlab GUI Package User Guide Revision A Vibrationdata FEA Matlab GUI Package User Guide Revision A By Tom Irvine Email: tom@vibrationdata.com March 25, 2014 Introduction Matlab Script: vibrationdata_fea_preprocessor.zip vibrationdata_fea_preprocessor.m

More information

Chapter 12. Static Equilibrium and Elasticity

Chapter 12. Static Equilibrium and Elasticity Chapter 12 Static Equilibrium and Elasticity Static Equilibrium Equilibrium implies that the object moves with both constant velocity and constant angular velocity relative to an observer in an inertial

More information

Bending of Simply Supported Isotropic and Composite Laminate Plates

Bending of Simply Supported Isotropic and Composite Laminate Plates Bending of Simply Supported Isotropic and Composite Laminate Plates Ernesto Gutierrez-Miravete 1 Isotropic Plates Consider simply a supported rectangular plate of isotropic material (length a, width b,

More information

Downloaded from Downloaded from / 1

Downloaded from   Downloaded from   / 1 PURWANCHAL UNIVERSITY III SEMESTER FINAL EXAMINATION-2002 LEVEL : B. E. (Civil) SUBJECT: BEG256CI, Strength of Material Full Marks: 80 TIME: 03:00 hrs Pass marks: 32 Candidates are required to give their

More information

my!wind Ltd 5 kw wind turbine Static Stability Specification

my!wind Ltd 5 kw wind turbine Static Stability Specification my!wind Ltd 5 kw wind turbine Static Stability Specification 1 P a g e 0 3 / 0 4 / 2 0 1 4 Contents Contents... 2 List of Changes... 2 Appendixes... 2 General remarks... 3 1. Introduction... 4 2. Geometry...

More information

Civil & Structural Engineering Design Services Pty. Ltd.

Civil & Structural Engineering Design Services Pty. Ltd. Client: Extreme Marquees Pty Ltd Project: Design check 6m, 8m, 8m, 10m, 12m, 14m & 16m Single Pole Star Shade Structure for 45km/hr Wind Spead Reference: Extreme Marquees Technical Data Report by: KZ Checked

More information

Sample Question Paper

Sample Question Paper Scheme I Sample Question Paper Program Name : Mechanical Engineering Program Group Program Code : AE/ME/PG/PT/FG Semester : Third Course Title : Strength of Materials Marks : 70 Time: 3 Hrs. Instructions:

More information

PREDICTION OF OUT-OF-PLANE FAILURE MODES IN CFRP

PREDICTION OF OUT-OF-PLANE FAILURE MODES IN CFRP PREDICTION OF OUT-OF-PLANE FAILURE MODES IN CFRP R. R. Pinto 1, P. P. Camanho 2 1 INEGI - Instituto de Engenharia Mecanica e Gestao Industrial, Rua Dr. Roberto Frias, 4200-465, Porto, Portugal 2 DEMec,

More information

SPECIAL CONDITION. Water Load Conditions. SPECIAL CONDITION Water Load Conditions

SPECIAL CONDITION. Water Load Conditions. SPECIAL CONDITION Water Load Conditions Doc. No. : SC-CVLA.051-01 Issue : 1d Date : 04-Aug-009 Page : 1 of 13 SUBJECT : CERTIFICATION SPECIFICATION : VLA.51 PRIMARY GROUP / PANEL : 03 (Structure) SECONDARY GROUPE / PANEL : -- NATURE : SCN VLA.51

More information

Name :. Roll No. :... Invigilator s Signature :.. CS/B.TECH (CE-NEW)/SEM-3/CE-301/ SOLID MECHANICS

Name :. Roll No. :... Invigilator s Signature :.. CS/B.TECH (CE-NEW)/SEM-3/CE-301/ SOLID MECHANICS Name :. Roll No. :..... Invigilator s Signature :.. 2011 SOLID MECHANICS Time Allotted : 3 Hours Full Marks : 70 The figures in the margin indicate full marks. Candidates are required to give their answers

More information

The LAT Electronics consists of five distinct box assemblies as follows:

The LAT Electronics consists of five distinct box assemblies as follows: I. SYNOPSIS The preliminary stress analyses for the DAQ Electronics assemblies have been performed per the conditions specified in the Environmental Specification LAT-SS-00778. The analysis considered

More information

D : SOLID MECHANICS. Q. 1 Q. 9 carry one mark each.

D : SOLID MECHANICS. Q. 1 Q. 9 carry one mark each. GTE 2016 Q. 1 Q. 9 carry one mark each. D : SOLID MECHNICS Q.1 single degree of freedom vibrating system has mass of 5 kg, stiffness of 500 N/m and damping coefficient of 100 N-s/m. To make the system

More information

NORMAL STRESS. The simplest form of stress is normal stress/direct stress, which is the stress perpendicular to the surface on which it acts.

NORMAL STRESS. The simplest form of stress is normal stress/direct stress, which is the stress perpendicular to the surface on which it acts. NORMAL STRESS The simplest form of stress is normal stress/direct stress, which is the stress perpendicular to the surface on which it acts. σ = force/area = P/A where σ = the normal stress P = the centric

More information

Solution to Multi-axial Fatigue Life of Heterogenic Parts & Components Based on Ansys. Na Wang 1, Lei Wang 2

Solution to Multi-axial Fatigue Life of Heterogenic Parts & Components Based on Ansys. Na Wang 1, Lei Wang 2 5th International Conference on Information Engineering for Mechanics and Materials (ICIMM 215) Solution to Multi-axial Fatigue Life of Heterogenic Parts & Components Based on Ansys Na Wang 1, Lei Wang

More information

SOLAR ORBITER ENERGETIC PARTICLE DETECTOR

SOLAR ORBITER ENERGETIC PARTICLE DETECTOR Page: 1 de 65 EPT-HET Structural Document ID: SO-EPD-KIE-RP-0040 Issue: 3 Revision: 3 Signature not needed if electronically approved by route Written Checked Approved Configuration Control Approved QA

More information

SKIN-STRINGER DEBONDING AND DELAMINATION ANALYSIS IN COMPOSITE STIFFENED SHELLS

SKIN-STRINGER DEBONDING AND DELAMINATION ANALYSIS IN COMPOSITE STIFFENED SHELLS SKIN-STRINER DEBONDIN AND DELAMINATION ANALYSIS IN COMPOSITE STIFFENED SHELLS R. Rikards, K. Kalnins & O. Ozolinsh Institute of Materials and Structures, Riga Technical University, Riga 1658, Latvia ABSTRACT

More information

Donald P. Shiley School of Engineering ME 328 Machine Design, Spring 2019 Assignment 1 Review Questions

Donald P. Shiley School of Engineering ME 328 Machine Design, Spring 2019 Assignment 1 Review Questions Donald P. Shiley School of Engineering ME 328 Machine Design, Spring 2019 Assignment 1 Review Questions Name: This is assignment is in workbook format, meaning you may fill in the blanks (you do not need

More information

Design Structural Analysis and Fatigue Calculation of Wing Fuselage Lug Attachment of a Transport Aircraft

Design Structural Analysis and Fatigue Calculation of Wing Fuselage Lug Attachment of a Transport Aircraft Design Structural Analysis and Fatigue Calculation of Wing Fuselage Lug Attachment of a Transport Aircraft Abraham J Pulickal Machine Design Department of Mechanical Engineering Malla Reddy College of

More information

International Journal for Ignited Minds (IJIMIINDS) Design and Analysis of Effect of Core Thickness in UAV Wing

International Journal for Ignited Minds (IJIMIINDS) Design and Analysis of Effect of Core Thickness in UAV Wing International Journal for Ignited Minds (IJIMIINDS) Design and Analysis of Effect of Core Thickness in UAV Wing Puttappa H R 1, Ravi Prakash M 2 & Madhusudhan Reddy 3 1 P G Scholar, Dept of Mechanical

More information

Purpose of this Guide: To thoroughly prepare students for the exact types of problems that will be on Exam 3.

Purpose of this Guide: To thoroughly prepare students for the exact types of problems that will be on Exam 3. ES230 STRENGTH OF MTERILS Exam 3 Study Guide Exam 3: Wednesday, March 8 th in-class Updated 3/3/17 Purpose of this Guide: To thoroughly prepare students for the exact types of problems that will be on

More information

BIAXIAL STRENGTH INVESTIGATION OF CFRP COMPOSITE LAMINATES BY USING CRUCIFORM SPECIMENS

BIAXIAL STRENGTH INVESTIGATION OF CFRP COMPOSITE LAMINATES BY USING CRUCIFORM SPECIMENS BIAXIAL STRENGTH INVESTIGATION OF CFRP COMPOSITE LAMINATES BY USING CRUCIFORM SPECIMENS H. Kumazawa and T. Takatoya Airframes and Structures Group, Japan Aerospace Exploration Agency 6-13-1, Ohsawa, Mitaka,

More information

Table of Contents. Preface...xvii. Part 1. Level

Table of Contents. Preface...xvii. Part 1. Level Preface...xvii Part 1. Level 1... 1 Chapter 1. The Basics of Linear Elastic Behavior... 3 1.1. Cohesion forces... 4 1.2. The notion of stress... 6 1.2.1. Definition... 6 1.2.2. Graphical representation...

More information

Samantha Ramirez, MSE. Stress. The intensity of the internal force acting on a specific plane (area) passing through a point. F 2

Samantha Ramirez, MSE. Stress. The intensity of the internal force acting on a specific plane (area) passing through a point. F 2 Samantha Ramirez, MSE Stress The intensity of the internal force acting on a specific plane (area) passing through a point. Δ ΔA Δ z Δ 1 2 ΔA Δ x Δ y ΔA is an infinitesimal size area with a uniform force

More information

ME FINITE ELEMENT ANALYSIS FORMULAS

ME FINITE ELEMENT ANALYSIS FORMULAS ME 2353 - FINITE ELEMENT ANALYSIS FORMULAS UNIT I FINITE ELEMENT FORMULATION OF BOUNDARY VALUE PROBLEMS 01. Global Equation for Force Vector, {F} = [K] {u} {F} = Global Force Vector [K] = Global Stiffness

More information

VEGA LAUNCH VEHICLE: PAYLOAD FAIRING SEPARATION ANALYSIS

VEGA LAUNCH VEHICLE: PAYLOAD FAIRING SEPARATION ANALYSIS VEGA LAUNCH VEHICLE: PAYLOAD FAIRING SEPARATION ANALYSIS P. F. Dezio, E. Mastrella, D. Fotino, G. Leto, M. Linari, F. Battie, D. Barbagallo The Payload Fairing (PLF) is the upper structural part of a launcher.

More information

Stress Analysis Lecture 3 ME 276 Spring Dr./ Ahmed Mohamed Nagib Elmekawy

Stress Analysis Lecture 3 ME 276 Spring Dr./ Ahmed Mohamed Nagib Elmekawy Stress Analysis Lecture 3 ME 276 Spring 2017-2018 Dr./ Ahmed Mohamed Nagib Elmekawy Axial Stress 2 Beam under the action of two tensile forces 3 Beam under the action of two tensile forces 4 Shear Stress

More information

Aluminum shell. Brass core. 40 in

Aluminum shell. Brass core. 40 in PROBLEM #1 (22 points) A solid brass core is connected to a hollow rod made of aluminum. Both are attached at each end to a rigid plate as shown in Fig. 1. The moduli of aluminum and brass are EA=11,000

More information

Hilti North America Installation Technical Manual Technical Data MI System Version

Hilti North America Installation Technical Manual Technical Data MI System Version MIC-SA-MAH 174671 Hilti North America Installation Technical Manual Technical Data MI System Version 1. 08.017 Terms of common cooperation / Legal disclaimer The product technical data published in these

More information

Stress analysis of deflection analysis flexure and obif Vertical Load orientation

Stress analysis of deflection analysis flexure and obif Vertical Load orientation Stress analysis of deflection analysis flexure and obif Vertical Load orientation Note: Do not base your design decisions solely on the data presented in this report. Use this information in conjunction

More information

PRACTICE 2 PROYECTO Y CONSTRUCCIÓN DE PUENTES. 1º Máster Ingeniería de Caminos. E.T.S.I. Caminos, canales y puertos (Ciudad Real) 01/06/2016

PRACTICE 2 PROYECTO Y CONSTRUCCIÓN DE PUENTES. 1º Máster Ingeniería de Caminos. E.T.S.I. Caminos, canales y puertos (Ciudad Real) 01/06/2016 PRACTICE 2 PROYECTO Y CONSTRUCCIÓN DE PUENTES 1º Máster Ingeniería de Caminos E.T.S.I. Caminos, canales y puertos (Ciudad Real) 01/06/2016 AUTHOR: CONTENT 1. INTRODUCTION... 3 2. BRIDGE GEOMETRY AND MATERIAL...

More information

ENG1001 Engineering Design 1

ENG1001 Engineering Design 1 ENG1001 Engineering Design 1 Structure & Loads Determine forces that act on structures causing it to deform, bend, and stretch Forces push/pull on objects Structures are loaded by: > Dead loads permanent

More information

Mechanics of Solids. Mechanics Of Solids. Suraj kr. Ray Department of Civil Engineering

Mechanics of Solids. Mechanics Of Solids. Suraj kr. Ray Department of Civil Engineering Mechanics Of Solids Suraj kr. Ray (surajjj2445@gmail.com) Department of Civil Engineering 1 Mechanics of Solids is a branch of applied mechanics that deals with the behaviour of solid bodies subjected

More information

Numerical Analysis of Delamination Behavior in Laminated Composite with Double Delaminations Embedded in Different Depth Positions

Numerical Analysis of Delamination Behavior in Laminated Composite with Double Delaminations Embedded in Different Depth Positions Numerical Analysis of Delamination Behavior in Laminated Composite with Double Delaminations Embedded in Different Depth Positions Numerical Analysis of Delamination Behavior in Laminated Composite with

More information

Job No. Sheet No. Rev. CONSULTING Engineering Calculation Sheet

Job No. Sheet No. Rev. CONSULTING Engineering Calculation Sheet E N G I N E E R S Consulting Engineers jxxx 1 Material Properties Characteristic strength of concrete, f cu ( 60N/mm 2 ; HSC N/A) 35 N/mm 2 OK Yield strength of longitudinal steel, f y 460 N/mm 2 Yield

More information

Rutgers University Department of Physics & Astronomy. 01:750:271 Honors Physics I Fall Lecture 19. Home Page. Title Page. Page 1 of 36.

Rutgers University Department of Physics & Astronomy. 01:750:271 Honors Physics I Fall Lecture 19. Home Page. Title Page. Page 1 of 36. Rutgers University Department of Physics & Astronomy 01:750:271 Honors Physics I Fall 2015 Lecture 19 Page 1 of 36 12. Equilibrium and Elasticity How do objects behave under applied external forces? Under

More information

MECHANICAL BEHAVIOUR OF DAMAGED HDPE GEOMEMBRANES

MECHANICAL BEHAVIOUR OF DAMAGED HDPE GEOMEMBRANES MECHANICAL BEHAVIOUR OF DAMAGED HDPE GEOMEMBRANES Guangming Xu, Mingchang Yang, Xianghai Zong Geotechnical Engineering Department, Nanjing Hydraulic Research Institute, China gmxu@nhri.cn Abstract HDPE

More information

NUMERICAL ANALYSIS OF SANDWICH PANELS SUBJECTED TO POINT LOADS

NUMERICAL ANALYSIS OF SANDWICH PANELS SUBJECTED TO POINT LOADS ECCOMAS Congress 216 VII European Congress on Computational Methods in Applied Sciences and Engineering M. Papadrakakis, V. Papadopoulos, G. Stefanou, V. Plevris (eds.) Crete Island, Greece, 5 1 June 216

More information

Composite Sandwich Structures with Honeycomb Core subjected to Impact

Composite Sandwich Structures with Honeycomb Core subjected to Impact Clemson University TigerPrints All Theses Theses 12-212 Composite Sandwich Structures with Honeycomb Core subjected to Impact Lei He Clemson University, he6@clemson.edu Follow this and additional works

More information

my!wind Ltd 5 kw wind turbine Static Stability Specification

my!wind Ltd 5 kw wind turbine Static Stability Specification my!wind Ltd 5 kw wind turbine Static Stability Specification 1 P a g e 0 3 / 0 4 / 2 0 1 4 Contents Contents... 2 List of Changes... 2 Appendixes... 2 General remarks... 3 1. Introduction... 4 2. Geometry...

More information

Determine the resultant internal loadings acting on the cross section at C of the beam shown in Fig. 1 4a.

Determine the resultant internal loadings acting on the cross section at C of the beam shown in Fig. 1 4a. E X M P L E 1.1 Determine the resultant internal loadings acting on the cross section at of the beam shown in Fig. 1 a. 70 N/m m 6 m Fig. 1 Support Reactions. This problem can be solved in the most direct

More information

Analysis of Shear Lag Effect of Box Beam under Dead Load

Analysis of Shear Lag Effect of Box Beam under Dead Load Analysis of Shear Lag Effect of Box Beam under Dead Load Qi Wang 1, a, Hongsheng Qiu 2, b 1 School of transportation, Wuhan University of Technology, 430063, Wuhan Hubei China 2 School of transportation,

More information