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CHOOSEPLOT (user chooses what
in Fig. Copyright 1997, American Institute of Aeronautics and Astronautics, Inc.
The "localbuck(vinson)" margin provides a parallel prediction of what PANDA2 has always computed with analysis type IQUICK=1, that is, local buckling analysis of the panel module segments with use of Eq.(57) in [21] with subsequent "knockdown" as described in Section 8.2 of [14] to account for the effect of transverse shear deformation. For local buckling of the panel skin, the previously (and still) available PANDA2 margins that represent the same phenomenon as "localbuck(vinson)" read: buck.(donl) simp-support local buck... buck.(sand) simp-support local buck... in which the string "DONL" means "Donnell theory" and "SAND" means "Sanders theory".
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in which Copyright 1997, American Institute of Aeronautics and Astronautics, Inc.
The stresses, <T zl, T^p and T j play a significant role in the stress constraints to be discussed later in the subsection entitled "Additional
compute Copyright 1997, American Institute of Aeronautics and Astronautics, Inc.
Copyright 1997, American Institute
curvature give rise to tension in the core normal to the face sheets.
"sandwichcore tension margin...". IMPLEMENTATION
BEGIN Introduce
implementation of the "sandwich" capability occur in SUBROUTINE BUCPAN. strain energy in a manner analogous to that done in BUCPAN2 Introduce the elastic foundation modulus term, EFOUND^, into the coefficient a 33 (see Eq. 55f, p.
the constraint conditions involving the maximum allowable
deformation-induced sandwich core crushing pressure. (See discussion above associated with Eqs.(31) - (33)). SUBROUTINE STRCON was modified to compute x-z and
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some negative margins, provided that
Copyright 1997, American Institute
transverse shear deformation is neglected. Since the width/thickness ratio
margins remain essentially the same. Those that are significantly affected by the introduction of finite initial face sheet waviness, W 0 / L = 0.001, are the core crushing margin, the x-z ("L-direction") core transverse shear stress margin,
which a reasonable level of initial facesheet waviness is present. The results for the final optimum design are listed in Table
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(bottom facesheet has higher destabilizing resultants than
while the work was in progress. Dr. Frank Weiler helped
Copyright 1997, American Institute
!i
5.!i V H da o a S I 1 h ''! i j H H H H H H I p t* *o r- * r* 1 J rt «* H ^# (O I < v> 01 w> H m
Copyright 1997, American Institute
Copyright 1997, American Institute
>ioooooo
h ftt **H * ««. H *. H fc H i-4 h rl H I I H H H J«I IJ I I?! S' ah: III HHHHHMHHHHHHMHHHHMH^H I I
Seg. 3 (Iseg numbering) Seg.
Objective 14 16 18 H- 05 (O hi I P< C H H- rt P- 3 H- IS) rt H- o H fl>
D 3.1.1 eff.stress:matl=1; MID.
ff &<D ZZ LU 111 _J _l 99 ; ^^ OCD zz 111 111 _J _J QQ CM A-'cvT CD CD <D CD O O J?j$ H as «+ ca a a 99 5S ^- ^- 7^^-
«- CO 01 m 4) 5 o a) D m 1) O (0 U-J O rt o 4J 3 H a IS) o m H o n) tn U6JS9Q O-Q ro- 2200
1-022 5.5 6.0 Design Parameters "d H- W O H H- O O Hi cr o> *; oo o oh 01 to 3* M H O pi h ' tf[ rt 0 rt 3 H- 9) O H 13 3 1 O OH, (D < O PJ O O Hi ID H O H 3 H- O> (D
tc(2 )(SKN):thickness x10'