Technical paper on CFRP Sandwich Construction

Discussion in 'Composites' started by Lamaface, Sep 14, 2015.

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  1. Sep 27, 2015 #41

    berridos

    berridos

    berridos

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    Sounds like the technique is ideal for moving surfaces like flaps, ailerons?
     
  2. Sep 28, 2015 #42

    tunnels

    tunnels

    tunnels

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    china is my home , place of work but was born in N
    Ok I will ask yet again !! what is the type of glass fabrics that are used to manufacture the web or channels ?? also what are the types of glass that are used for the skins ??what the orientation of the fibres ?? what direction do they run at ??
    Most buckling problems can be minimized simply by changing the direction of the fibres being used !!
     
  3. Sep 30, 2015 #43

    tunnels

    tunnels

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    don't want to answer ?? cant answer ?? or plain don't want to part with secrets ??
     
  4. Sep 30, 2015 #44

    proppastie

    proppastie

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    Aircraft Spruce sells homebuilder supplies, Carbon Fiber/Graphite from Aircraft Spruce

    if you have an autoclave might want to check out:

    Aerospace Solutions

    Lots of stuff out there if you are willing to spend the time to do the research.

    Very complicated subject as to the how....... Lots of stress analysis expertise required ..... Very few know how to do it, and I would imagine the answers are aircraft configuration specific.(I do not know how either .... sorry)

    Good Luck.
     
  5. Oct 1, 2015 #45

    SpainCub

    SpainCub

    SpainCub

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    Did you use the ICAN/JAVA framework?

    you loose all the vitamins on the fur!!!! :gig:
     
  6. Oct 3, 2015 #46

    autoreply

    autoreply

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    Possibly. Bob's website (HP24) has a nice analysis of a Alexander Schleicher flap or aileron analysis. Can't find it back though. There though, the foam/skin glue joint is probably an easy 20-30% of the total weight. Given the requirement to balance it, that's massive potential weight savings.



    ICAN doesn't ring a bell?
     
  7. Oct 5, 2015 #47

    SpainCub

    SpainCub

    SpainCub

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    Auto, I'm talking about the following:

    [​IMG]

    More here: Integrated Composite Analyzer (ICAN/JAVA)

    Also, there is an API that let's you build your own wrapper and get custom reports and fancy plotting, but the output looks like this:

    Laminate Configuration [0/45/-45/90]S

    Forces Force Displacement Relations Displ. T-Forces H-Forces E-Forces

    Nxx 2.9877E+05 9.4097E+04 0.0 4.5475E-13 1.0658E-14 0.0 Uxx -1.2487E+02 0.0 0.0
    Nyy 9.4097E+04 2.9877E+05 1.0914E-11 1.7764E-14 -3.2685E-13 0.0 Vyy -1.2487E+02 0.0 0.0
    Nxy 0.0 1.0914E-11 1.0234E+05 0.0 0.0 7.1054E-15 VxpUy 1.7764E-15 0.0 0.0

    Mxx 4.5475E-13 1.7764E-14 0.0 6.7047E+01 1.0497E+01 4.1935 Wxx 5.5511E-17 0.0 0.0
    Myy 1.0658E-14 -3.2685E-13 0.0 1.0497E+01 1.6724E+01 4.1935 Wyy -5.5511E-17 0.0 0.0
    Mxy 0.0 0.0 7.1054E-15 4.1935 4.1935 1.1595E+01 Wxy 0.0 0.0 0.0



    $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ PRINT REDSTIF $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$

    Laminate Configuration [0/45/-45/90]S

    Reduced Stiffness Matrix Reduced Bending Rigidities

    2.98769E+05 9.40972E+04 1.07642E-29 6.70468E+01 1.04966E+01 4.19355
    9.40972E+04 2.98769E+05 1.09139E-11 1.04966E+01 1.67242E+01 4.19355
    1.07642E-29 1.09139E-11 1.02336E+05 4.19355 4.19355 1.15951E+01



    U S E F U L D A T A F O R "MSC/NASTRAN PSHELL CARD"
    USE THIS DATA FOR "MID4" ON PSHELL TO INCLUDE MEMBRANE/BENDING COUPLING ON A MAT2 CARD
    G11,G12,G13,G22,G23,G33

    2.84217E-10 6.66134E-12 0.0 -2.04281E-10 0.0 4.44089E-12

    $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ PRINT FEMDATA $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$

    S O M E U S E F U L D A T A F O R F. E. A N A L Y S I S

    Composite thickness for F. E. Analysis = 4.00000E-02

    Properties for F. E. Analysis E11, E12, E13, E22, E23, E33 (properties scaled by 1E-6)
    1.48626E-01 -4.68096E-02 -4.99217E-18 1.48626E-01 1.58507E-17 3.90870E-01

    Bending equivalent properties nuCxy, nuCyx, Ecxx, Ecyy, Gcxy
    6.27631E-01 1.56557E-01 1.13360E+07 2.82766E+06 2.17408E+06

    NASTRAN membrane equivalent elastic coefficients G11,G12,G13,G22,G23,G33
    7.46921E+06 2.35243E+06 0.0 7.46921E+06 2.72848E-10 2.55839E+06

    NASTRAN bending equivalent elastic coefficients G11,G12,G13,G22,G23,G33
    1.25713E+07 1.96811E+06 7.86290E+05 3.13578E+06 7.86290E+05 2.17408E+06



    $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ PRINT DISPFOR $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$


    Laminate Configuration [0/45/-45/90]S

    DISP. DISPLACEMENT FORCE RELATIONS COMBINED FORCES

    -1- -2- -3- -4- -5- -6-

    1 -3.1785E-04 3.7156E-06 -1.1702E-06 1.2480E-22 -2.3571E-20 -1.3837E-20 1.3529E-20 -1.2487E+02

    2 -3.1785E-04 -1.1702E-06 3.7156E-06 -3.9627E-22 -4.2893E-21 8.3212E-20 -2.8544E-20 -1.2487E+02

    3 5.1257E-20 1.2480E-22 -3.9627E-22 9.7718E-06 1.7074E-22 1.5504E-21 -6.6106E-21 1.7764E-15

    4 4.9450E-18 -2.3571E-20 -4.2893E-21 1.7074E-22 1.6604E-02 -9.8044E-03 -2.4591E-03 5.5511E-17

    5 -1.3179E-17 -1.3837E-20 8.3212E-20 1.5504E-21 -9.8044E-03 7.1546E-02 -2.2330E-02 -5.5511E-17

    6 2.9779E-18 1.3529E-20 -2.8544E-20 -6.6106E-21 -2.4591E-03 -2.2330E-02 9.5209E-02 0.0


    Note: The displacements are reference plane membrane strains (UX , VY , VXPUY) and curvatures (WXX , WYY , WXY)


    $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ PRINT PLYRESP $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$

    P L Y H Y G R O T H E R M O M E C H A N I C A L P R O P E R T I E S / R E S P O N S E


    For Load Conditions:
    Membrane Loads NBS(X,Y,XY-M) are 0.0 0.0 0.0
    Bending Loads MBS(X,Y,XY-M) are 0.0 0.0 0.0
    Out-of-plane Loads upper/lower are 0.0 0.0
    Shear Loads Ncxz, Ncyz are 0.0 0.0
    Centrifugal Load rpm, radius are 0.0 0.0
    Note: No Moisture; For Temperature see row 50.


    Layer Properties, rows=property, columns=layer


    ------------------------------------------------------------------------------------------------------------------------------
    PLY NUMBER 1 2 3 4 5 6 7 8
    MATERIAL SYSTEM T300/IMHS T300/IMHS T300/IMHS T300/IMHS T300/IMHS T300/IMHS T300/IMHS T300/IMHS
    ORIENTATION 0.0 45.0 -45.0 90.0 90.0 -45.0 45.0 0.0
    ------------------------------------------------------------------------------------------------------------------------------
    1 KV 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0
    2 KF 5.5000E-01 5.5000E-01 5.5000E-01 5.5000E-01 5.5000E-01 5.5000E-01 5.5000E-01 5.5000E-01
    3 KF' 5.5000E-01 5.5000E-01 5.5000E-01 5.5000E-01 5.5000E-01 5.5000E-01 5.5000E-01 5.5000E-01
    4 KM 4.5000E-01 4.5000E-01 4.5000E-01 4.5000E-01 4.5000E-01 4.5000E-01 4.5000E-01 4.5000E-01
    5 KM' 4.5000E-01 4.5000E-01 4.5000E-01 4.5000E-01 4.5000E-01 4.5000E-01 4.5000E-01 4.5000E-01
    6 RHOL 5.5000E-02 5.5000E-02 5.5000E-02 5.5000E-02 5.5000E-02 5.5000E-02 5.5000E-02 5.5000E-02
    7 TL 5.0000E-03 5.0000E-03 5.0000E-03 5.0000E-03 5.0000E-03 5.0000E-03 5.0000E-03 5.0000E-03
    8 DELTA 5.8496E-05 5.8496E-05 5.8496E-05 5.8496E-05 5.8496E-05 5.8496E-05 5.8496E-05 5.8496E-05
    9 ILDC 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0
    10 ZB 2.5000E-03 7.5000E-03 1.2500E-02 1.7500E-02 2.2500E-02 2.7500E-02 3.2500E-02 3.7500E-02
    11 ZGC -1.7500E-02 -1.2500E-02 -7.5000E-03 -2.5000E-03 2.5000E-03 7.5000E-03 1.2500E-02 1.7500E-02
    12 THCS 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0
    13 THLC 0.0 4.5000E+01 -4.5000E+01 9.0000E+01 9.0000E+01 -4.5000E+01 4.5000E+01 0.0
    14 THLS 0.0 4.5000E+01 -4.5000E+01 9.0000E+01 9.0000E+01 -4.5000E+01 4.5000E+01 0.0
    15 SC11 5.6101E-08 5.6101E-08 5.6101E-08 5.6101E-08 5.6101E-08 5.6101E-08 5.6101E-08 5.6101E-08
    16 SC12 -1.5007E-08 -1.5007E-08 -1.5007E-08 -1.5007E-08 -1.5007E-08 -1.5007E-08 -1.5007E-08 -1.5007E-08
    17 SC13 -1.5007E-08 -1.5007E-08 -1.5007E-08 -1.5007E-08 -1.5007E-08 -1.5007E-08 -1.5007E-08 -1.5007E-08
    18 SC22 8.8757E-07 8.8757E-07 8.8757E-07 8.8757E-07 8.8757E-07 8.8757E-07 8.8757E-07 8.8757E-07
    19 SC23 -3.9487E-07 -3.9487E-07 -3.9487E-07 -3.9487E-07 -3.9487E-07 -3.9487E-07 -3.9487E-07 -3.9487E-07
    20 SC33 8.8757E-07 8.8757E-07 8.8757E-07 8.8757E-07 8.8757E-07 8.8757E-07 8.8757E-07 8.8757E-07
    21 SC44 2.4547E-06 2.4547E-06 2.4547E-06 2.4547E-06 2.4547E-06 2.4547E-06 2.4547E-06 2.4547E-06
    22 SC55 1.9657E-06 1.9657E-06 1.9657E-06 1.9657E-06 1.9657E-06 1.9657E-06 1.9657E-06 1.9657E-06
    23 SC66 1.9657E-06 1.9657E-06 1.9657E-06 1.9657E-06 1.9657E-06 1.9657E-06 1.9657E-06 1.9657E-06
    24 CTE11 -8.8640E-08 -8.8640E-08 -8.8640E-08 -8.8640E-08 -8.8640E-08 -8.8640E-08 -8.8640E-08 -8.8640E-08
    25 CTE22 1.6669E-05 1.6669E-05 1.6669E-05 1.6669E-05 1.6669E-05 1.6669E-05 1.6669E-05 1.6669E-05
    26 CTE33 1.6669E-05 1.6669E-05 1.6669E-05 1.6669E-05 1.6669E-05 1.6669E-05 1.6669E-05 1.6669E-05
    27 HK11 2.2204 2.2204 2.2204 2.2204 2.2204 2.2204 2.2204 2.2204
    28 HK22 2.5709E-02 2.5709E-02 2.5709E-02 2.5709E-02 2.5709E-02 2.5709E-02 2.5709E-02 2.5709E-02
    29 HK33 2.5709E-02 2.5709E-02 2.5709E-02 2.5709E-02 2.5709E-02 2.5709E-02 2.5709E-02 2.5709E-02
    30 HCL 2.3080E-01 2.3080E-01 2.3080E-01 2.3080E-01 2.3080E-01 2.3080E-01 2.3080E-01 2.3080E-01
    31 EL11 1.7825E+07 1.7825E+07 1.7825E+07 1.7825E+07 1.7825E+07 1.7825E+07 1.7825E+07 1.7825E+07
    32 EL22 1.1267E+06 1.1267E+06 1.1267E+06 1.1267E+06 1.1267E+06 1.1267E+06 1.1267E+06 1.1267E+06
    33 EL33 1.1267E+06 1.1267E+06 1.1267E+06 1.1267E+06 1.1267E+06 1.1267E+06 1.1267E+06 1.1267E+06
    34 GL23 4.0738E+05 4.0738E+05 4.0738E+05 4.0738E+05 4.0738E+05 4.0738E+05 4.0738E+05 4.0738E+05
    35 GL13 5.0872E+05 5.0872E+05 5.0872E+05 5.0872E+05 5.0872E+05 5.0872E+05 5.0872E+05 5.0872E+05
    36 GL12 5.0872E+05 5.0872E+05 5.0872E+05 5.0872E+05 5.0872E+05 5.0872E+05 5.0872E+05 5.0872E+05
    37 NUL12 2.6750E-01 2.6750E-01 2.6750E-01 2.6750E-01 2.6750E-01 2.6750E-01 2.6750E-01 2.6750E-01
    38 NUL21 1.6908E-02 1.6908E-02 1.6908E-02 1.6908E-02 1.6908E-02 1.6908E-02 1.6908E-02 1.6908E-02
    39 NUL13 2.6750E-01 2.6750E-01 2.6750E-01 2.6750E-01 2.6750E-01 2.6750E-01 2.6750E-01 2.6750E-01
    40 NUL31 1.6908E-02 1.6908E-02 1.6908E-02 1.6908E-02 1.6908E-02 1.6908E-02 1.6908E-02 1.6908E-02
    41 NUL23 4.4489E-01 4.4489E-01 4.4489E-01 4.4489E-01 4.4489E-01 4.4489E-01 4.4489E-01 4.4489E-01
    42 NUL32 4.4489E-01 4.4489E-01 4.4489E-01 4.4489E-01 4.4489E-01 4.4489E-01 4.4489E-01 4.4489E-01
    43 DPL1 9.7200E-08 9.7200E-08 9.7200E-08 9.7200E-08 9.7200E-08 9.7200E-08 9.7200E-08 9.7200E-08
    44 DPL2 5.5810E-08 5.5810E-08 5.5810E-08 5.5810E-08 5.5810E-08 5.5810E-08 5.5810E-08 5.5810E-08
    45 DPL3 5.5810E-08 5.5810E-08 5.5810E-08 5.5810E-08 5.5810E-08 5.5810E-08 5.5810E-08 5.5810E-08
    46 BETAL1 4.1655E-05 4.1655E-05 4.1655E-05 4.1655E-05 4.1655E-05 4.1655E-05 4.1655E-05 4.1655E-05
    47 BETAL2 1.1473E-03 1.1473E-03 1.1473E-03 1.1473E-03 1.1473E-03 1.1473E-03 1.1473E-03 1.1473E-03
    48 BETAL3 1.1473E-03 1.1473E-03 1.1473E-03 1.1473E-03 1.1473E-03 1.1473E-03 1.1473E-03 1.1473E-03
    49 ILMFC 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0
    50 TEMPD -2.8000E+02 -2.8000E+02 -2.8000E+02 -2.8000E+02 -2.8000E+02 -2.8000E+02 -2.8000E+02 -2.8000E+02
    51 LSC11T 1.9496E+05 1.9496E+05 1.9496E+05 1.9496E+05 1.9496E+05 1.9496E+05 1.9496E+05 1.9496E+05
    52 LSC11C 1.4614E+05 1.4614E+05 1.4614E+05 1.4614E+05 1.4614E+05 1.4614E+05 1.4614E+05 1.4614E+05
    53 LSC11D 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0
    54 LSC22T 1.2844E+04 1.2844E+04 1.2844E+04 1.2844E+04 1.2844E+04 1.2844E+04 1.2844E+04 1.2844E+04
    55 LSC22C 2.9970E+04 2.9970E+04 2.9970E+04 2.9970E+04 2.9970E+04 2.9970E+04 2.9970E+04 2.9970E+04
    56 LSC12 1.0864E+04 1.0864E+04 1.0864E+04 1.0864E+04 1.0864E+04 1.0864E+04 1.0864E+04 1.0864E+04
    57 LSC23 9.9235E+03 9.9235E+03 9.9235E+03 9.9235E+03 9.9235E+03 9.9235E+03 9.9235E+03 9.9235E+03
    58 LSCC23 0.0 8.1158E+04 8.6246E+04 9.0804E+04 9.5870E+04 9.0804E+04 8.6246E+04 8.1158E+04
    59 LSCC13 0.0 9.0804E+04 8.6246E+04 8.1158E+04 7.6638E+04 8.1158E+04 8.6246E+04 9.0804E+04
    60 LSCDF 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0
    61 KL12AB 1.0653 1.0653 1.0653 1.0653 1.0653 1.0653 1.0653 1.0653
    62 MDEIE 8.4497E-01 8.4497E-01 8.4497E-01 8.4497E-01 8.4497E-01 8.4497E-01 8.4497E-01 8.4497E-01
    63 RELROT 0.0 1.0000 1.0000 1.0000 1.0000 1.0000 1.0000 1.0000
    64 EPS11 -3.1785E-04 -3.1785E-04 -3.1785E-04 -3.1785E-04 -3.1785E-04 -3.1785E-04 -3.1785E-04 -3.1785E-04
    65 EPS22 -3.1785E-04 -3.1785E-04 -3.1785E-04 -3.1785E-04 -3.1785E-04 -3.1785E-04 -3.1785E-04 -3.1785E-04
    66 EPS12 -8.5743E-22 2.2032E-36 5.4210E-20 -4.3812E-20 -5.8701E-20 3.7947E-19 -4.3368E-19 1.0337E-19
    67 SIG11 -4.8190E+03 -4.8190E+03 -4.8190E+03 -4.8190E+03 -4.8190E+03 -4.8190E+03 -4.8190E+03 -4.8190E+03
    68 SIG22 4.8190E+03 4.8190E+03 4.8190E+03 4.8190E+03 4.8190E+03 4.8190E+03 4.8190E+03 4.8190E+03
    69 SIG12 -4.3619E-16 1.1208E-30 2.7578E-14 -2.2288E-14 -2.9862E-14 1.9304E-13 -2.2062E-13 5.2586E-14
    70 DELFI 0.0 -7.0161E-21 5.4210E-20 -1.0322E-19 0.0 2.2653E-19 -4.3368E-19 3.2274E-19
    71 HFC 7.1539E-01 7.1539E-01 7.1539E-01 7.1539E-01 7.1539E-01 7.1539E-01 7.1539E-01 7.1539E-01
    72 MPCTGE 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0
    73 SIG13 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0
    74 SIG23 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0
    75 SIG33 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0
    ------------------------------------------------------------------------------------------------------------------------------

    $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$ PRINT FREESTR $$$$$$$$$$$$$$$$$$$$$$$$$$$$$$

    F R E E E D G E S T R E S S E S

    ---------------------------------------------------------------------------------------------------
    Ply Theta sigmaxx sigmayy sigmaxy Y Decay Len. sigmazy sigmazz sigmazx
    ---------------------------------------------------------------------------------------------------

    1 0.0 -4.8190E+03 4.8190E+03 -4.3619E-16 4.8232 0.0 1.2356E-01 0.0
    2 45.0 -4.8190E+03 4.8190E+03 1.1208E-30 5.3557 3.1109E+01 3.0062E-01 1.3497E+01
    3 -45.0 -4.8190E+03 4.8190E+03 2.7578E-14 5.3557 6.2217E+01 5.0104E-01 2.6994E+01
    4 90.0 -4.8190E+03 4.8190E+03 -2.2288E-14 1.9185E+01 2.6054E+01 5.4668E-02 1.1304E+01
    5 90.0 -4.8190E+03 4.8190E+03 -2.9862E-14 1.9185E+01 2.6054E+01 5.4668E-02 1.1304E+01
    6 -45.0 -4.8190E+03 4.8190E+03 1.9304E-13 5.3557 6.2217E+01 5.0104E-01 2.6994E+01
    7 45.0 -4.8190E+03 4.8190E+03 -2.2062E-13 5.3557 3.1109E+01 3.0062E-01 1.3497E+01
    8 0.0 -4.8190E+03 4.8190E+03 5.2586E-14 4.8232 0.0 1.2356E-01 0.0
    ---------------------------------------------------------------------------------------------------


    Note: The interlaminar stresses are between plies (I-1) and (I).
    Note: If the ply number is repeated, the the second one indicates stresses in the secondary composite.
    Note: For angle ply laminates, sigmayy = 0. Consequently sigmazy and sigmazz are computed as zero.
    To obtain non-trivial sigmazy and sigmazz, one must specify a thin interply layer.
    The interply layer thickness may be obtained from the ply property table.

     
  8. Oct 6, 2015 #48

    BJC

    BJC

    BJC

    Well-Known Member HBA Supporter

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    Reference third element in line 42: Are you certain that it is 4.4489E-01 and not 4.4488E-01?

    :) :) :)


    BJC
     
    BoKu likes this.

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