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TALAT Lecture 2711: Appendix

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This lecture presents design of the main structural parts of an aluminium alloy helicopter deck. Contains figures and tables.

Text of TALAT Lecture 2711: Appendix

  • TALAT Lectures 2711 - Appendix

    Design of A Helicopter deck

    81 pages, 7 figures

    Advanced Level

    Prepared by Federico M. Mazzolani, University of Naples Federico II, Napoli

    Update from the TAS Project :

    TAS Leonardo da Vinci program Training in Aluminium Alloy Structural Design

    Remark The design of the main structural parts of an aluminium alloy helicopter deck is shown in this document. The design of a bolted connection on the supporting structure is also presented. The calculations carried out hereafter are based on the European Standard prENV 1999 (version April 1997). Date of Issue: 1999 EAA - European Aluminium Association

  • TALAT 2711 Appendix 2

    2711 Design of A Helicopter deck - Appendix

    Contents ! 2711 Design of A Helicopter deck - Appendix ........................................................... 2 ! FIG. 1 DISPLACEMENT AND STRESS CONTOUR, LOAD CONDITION

    1,ULTIMATE LIMIT STATE.................................................................................................. 3

    ! FIG. 2 DISPLACEMENT AND STRESS CONTOUR, LOAD CONDITION 2,

    ULTIMATE LIMIT STATE..................................................................................................... 8

    ! FIG. 3 DISPLACEMENT AND STRESS CONTOUR, LOAD CONDITION 3,

    ULTIMATE LIMIT STATE................................................................................................... 13

    ! FIG. 4 DISPLACEMENT AND STRESS CONTOUR, LOAD CONDITION 1,

    SERVICEABILITY LIMIT STATE....................................................................................... 18

    ! FIG. 5 DISPLACEMENT AND STRESS CONTOUR, LOAD CONDITION 2,

    SERVICEABILITY LIMIT STATE....................................................................................... 23

    ! FIG. 6 DISPLACEMENT AND STRESS CONTOUR, LOAD CONDITION 3,

    SERVICEABILITY LIMIT STATE....................................................................................... 28

    ! TAB. 1 DISPLACEMENTS AND STRESSES, LOAD CONDITION 1, ULTIMATE

    LIMIT STATE ........................................................................................................................ 33

    ! TAB. 2 DISPLACEMENTS AND STRESSES, LOAD CONDITION 2, ULTIMATE

    LIMIT STATE ........................................................................................................................ 42

    ! TAB. 3 DISPLACEMENTS AND STRESSES, LOAD CONDITION 3, ULTIMATE

    LIMIT STATE ........................................................................................................................ 50

    ! TAB. 4 DISPLACEMENTS AND STRESSES, LOAD CONDITION 1,

    SERVICEABILITY LIMIT STATE....................................................................................... 58

    ! TAB. 5 DISPLACEMENTS AND STRESSES, LOAD CONDITION 2,

    SERVICEABILITY LIMIT STATE....................................................................................... 66

    ! TAB. 6 DISPLACEMENTS AND STRESSES, LOAD CONDITION 3,

    SERVICEABILITY LIMIT STATE....................................................................................... 74

  • TALAT 2711 Appendix 3

    FIG. 1 DISPLACEMENT AND STRESS CONTOUR, LOAD CONDITION 1,ULTIMATE LIMIT STATE

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    FIG. 2 DISPLACEMENT AND STRESS CONTOUR, LOAD CONDITION 2, ULTIMATE LIMIT STATE

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    FIG. 3 DISPLACEMENT AND STRESS CONTOUR, LOAD CONDITION 3, ULTIMATE LIMIT STATE

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    FIG. 4 DISPLACEMENT AND STRESS CONTOUR, LOAD CONDITION 1, SERVICEABILITY LIMIT STATE

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    FIG. 5 DISPLACEMENT AND STRESS CONTOUR, LOAD CONDITION 2, SERVICEABILITY LIMIT STATE

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    FIG. 6 DISPLACEMENT AND STRESS CONTOUR, LOAD CONDITION 3, SERVICEABILITY LIMIT STATE

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    TAB. 1 DISPLACEMENTS AND STRESSES, LOAD CONDITION 1, ULTIMATE LIMIT STATE

  • TALAT 2711 Appendix 34

    ABAQUS VERSION 5.6-1 DATE 07-MAR-98 TIME 15:51:47

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    THIS PROGRAM HAS BEEN DEVELOPED BY

    HIBBITT, KARLSSON AND SORENSEN, INC.1080 MAIN STREET

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  • TALAT 2711 Appendix 35

    INPUT FILE (LOAD CONDITION 1 - U.L.S.)

    *HEADING*PREPRINT, ECHO=YES, MODEL=YES**

    ** BASE NODES**

    *NODE1,0.,0., 0.1001, 3000., 0., 0.2001, 6000., 0., 0.28, 0., 8100., 0.1028, 3000., 8100., 0.2028, 6000., 8100., 0.*NGEN, NSET=GIRDER-A1,28,1*NGEN, NSET=GIRDER-B1001,1028,1*NGEN, NSET=GIRDER-C2001,2028,1*NFILL, NSET=DECKGIRDER-A, GIRDER-B, 10, 100GIRDER-B, GIRDER-C, 10, 100*NSET, NSET=RES1, 28, 1001, 1028, 2001, 2028**

    **

    ** ELEMENTS**

    **

    *ELEMENT, TYPE=S4R10001, 1, 101, 102, 2*ELGEN, ELSET=DECK10001,20,100,1,27,1,20*ELSET,ELSET=ELPR11*ELEMENT, TYPE=B3120001, 1, 101*ELGEN, ELSET=STIFF20001, 20, 100, 1, 28, 1, 20**

    **

    **GIRDERS**

    *ELEMENT, TYPE=B311, 1, 2*ELGEN, ELSET=GIRDER-A1, 27, 1, 1*ELEMENT, TYPE=B311001, 1001, 1002*ELGEN, ELSET=GIRDER-B1001, 27, 1, 1*ELEMENT, TYPE=B312001, 2001, 2002*ELGEN, ELSET=GIRDER-C2001, 27, 1, 1**

    ** MATERIAL PROPERTIES**

    **

    *BEAM SECTION, SECTION=I, ELSET=GIRDER-A, MATERIAL=ALLOY1225., 450., 200., 200., 20., 20., 12.

  • TALAT 2711 Appendix 36

    1.,0.,0.*BEAM SECTION, SECTION=I, ELSET=GIRDER-B, MATERIAL=ALLOY1225., 450., 200., 200., 20., 20., 12.1.,0.,0.*BEAM SECTION, SECTION=I, ELSET=GIRDER-C, MATERIAL=ALLOY1225., 450., 200., 200., 20., 20., 12.1.,0.,0.*SHELL SECTION, ELSET=DECK, MATERIAL=ALLOY34., 5*BEAM SECTION, SECTION=BOX, ELSET=STIFF, MATERIAL=ALLOY2200., 125., 4.5, 4., 4.5, 6.50.,-1.,0.*MATERIAL, NAME=ALLOY1*ELASTIC70000.,.3*MATERIAL, NAME=ALLOY2*ELASTIC70000.,.3*MATERIAL, NAME=ALLOY3*ELASTIC, TYPE=ENGINEERING COSTANTS70000., 1890000., 70000., .01, .3, .01, 27000., 27000.27000.**

    ** BOUNDARY CONDITIONS**

    *BOUNDARYRES, 1RES, 2RES, 3*RESTART, W, F=1**

    ** STEP(S)**

    *STEP, INC=1*STATIC1.,,,,,*CLOAD501,3,-116000.*MONITOR, NODE=501, DOF=3**MONITOR, NODE=507, DOF=3**MONITOR, NODE=513, DOF=3*NODE PRINT, NSET=DECK, F=1U3*NODE PRINT, NSET=GIRDER-A, F=1U3*NODE PRINT, NSET=GIRDER-B, F=1U3*NODE PRINT, NSET=GIRDER-C, F=1U3*EL PRINT, ELSET=GIRDER-ASM1, SM2, SM3, SF1, SF2*EL PRINT, ELSET=GIRDER-BSM1, SM2, SM3, SF1, SF2*EL PRINT, ELSET=GIRDER-CSM1, SM2, SM3, SF1, SF2*EL PRINT, ELSET=DECK, F=1SM1, SM2, SM3, SF4, SF5*EL PRINT, ELSET=STIFF, F=1SM1, SM2, SM3, SF1, SF2*RESTART, WRITE, F=1*ENDSTEP

  • TALAT 2711 Appendix 37

    E L E M E N T O U T P U T

    THE FOLLOWING TABLE IS PRINTED FOR ELEMENT TYPE B31AND ELSET GIRDER-A

    ELEMENT PT FOOT- SM1 SM2 SM3 SF1 SF2NOTE

    1 1 -9.7756E+05 2.3777E+05 -6.0890E+05 -231.0 3.4010E+042 1 -1.5852E+06 4.7613E+05 -6.7429E+05 4204. 2.5225E+043 1 -2.0960E+06 1.3437E+05 -4.8968E+05 4052. 1.8247E+044 1 -2.2674E+06 -2.4037E+04 -3.3491E+05 2764. 1.2785E+045 1 -2.2416E+06 -6.1569E+04 -2.2402E+05 1558. 8882.6 1 -2.1123E+06 -5.7197E+04 -1.4895E+05 692.2 6208.7 1 -1.9329E+06 -4.3914E+04 -9.9155E+04 125.8 4397.8 1 -1.7339E+06 -3.1565E+04 -6.6347E+04 -228.5 3170.9 1 -1.5325E+06 -2.2098E+04 -4.4764E+04 -442.7 2333.

    10 1 -1.3384E+06 -1.5310E+04 -3.0557E+04 -567.0 1757.11 1 -1.1569E+06 -1.0581E+04 -2.1196E+04 -634.5 1355.12 1 -9.9059E+05 -7332. -1.5023E+04 -666.6 1070.13 1 -8.4048E+05 -5118. -1.0950E+04 -677.2 863.514 1 -7.0666E+05 -3617. -8264. -674.9 711.015 1 -5.8861E+05 -2604. -6496. -665.8 595.816 1 -4.8551E+05 -1925. -5333. -653.4 506.817 1 -3.9629E+05 -1474. -4571. -640.6 436.518 1 -3.1980E+05 -1183. -4071. -629.1 380.019 1 -2.5483E+05 -1003. -3742. -620.6 333.820 1 -2.0011E+05 -906.1 -3523. -616.8 295.721 1 -1.5438E+05 -873.2 -3371. -619.3 264.122 1 -1.1637E+05 -896.9 -3258. -630.9 237.823 1 -8.4811E+04 -985.9 -3158. -655.4 215.924 1 -5.8412E+04 -1223. -3051. -699.3 197.725 1 -3.5853E+04 -1997. -2912. -774.1 182.426 1 -1.5719E+04 -4288. -2704. -900.6 168.927 1 3669. -5526. -2354. -1166. 155.9

    MAXIMUM 3669. 4.7613E+05 -2354. 4204. 3.4010E+04ELEMENT 27 2 27 2 1

    MINIMUM -2.2674E+06 -6.1569E+04 -6.7429E+05 -1166. 155.9ELEMENT 4 5 2 27 27

    THE FOLLOWING TABLE IS PRINTED FOR ELEMENT TYPE B31AND ELSET GIRDER-B

    ELEMENT PT FOOT- SM1 SM2 SM3 SF1 SF2NOTE

    1001 1 1.2

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