Modifications and additions incorporated into the BOPACE 3-D program are described. Updates to the program input data formats, error messages, file usage, size limitations, and overlay schematic are included

Straayer, J. W.

Vos, R. G.

English

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https://ntrs.nasa.gov/search.jsp?R=19760009723 2020-03-22T16:34:00+00:00Z
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D180-18677-2
SOPACE 3-D (ADDENDUM)
(The toeing Plastic .Analysis Capability for 3-Dimensional i
Solids Usin g Isoparametric Finite Elements)
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Contract 11AS8-30615
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September 1, 1975
(NASA-CE-144120)
	 EOPACE 3-D ADDENDUM:
	 THE
	 N76-16811 )BOEING PLASTIC ANAL_SIS CAIABILITIES FOR
3-DIMENSIONAL SOLIDS USING .ISOPARAMETRIC aFINITE ELEMENTS
	 ( B(;'eing Aerospace Co.,
	 G3	 UnclasSeattZs,
 Wash*) --14 p,
-HC $3,5- -
	 CSCL 09B JW/'6G
	 67427
j Prepared by
R. G, VosY^ , 	 p d2^
J. 41. Straayer - Program Manager o^5
S Prenared for
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
F
George C. Marshall Soace Fli ght Center
Marshall Space Flight Center, Alabama	 35812
9
1
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BGEING AEROSPACE COMPANY
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Research and Enaineerin g Division t
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-- Seattle, 11ashington 98124
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TABLE OF COPITENTS
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Section Page
Table of Contents AM
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A.1 Introduction A.1-1 t
A.2 Innut Data A.2-1
A.3 Size Limitations A.3-1 JI
A.4 Error Messages A.4-1
A.5 File, Usage A.5-1
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A.6 Overlay
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A.1
	
INTRODUCTION
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This addendum to the SOPACE 3-D (Boeing Plastic Analysis Ca pability for
3-Dimensional solids using isoparametric finite elements) program document
(Ref.,,1), describes modifications and additions incorporated into the program
version dated September 1, 1975. These include the follnwing major items.
1. Restructuring of the program to allow solution of certain 3000-DOF
problems within64K words of core. (This also increases the
allowable equation bandwidth/wavefront for larger core storage
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t	 allocations).
2. Generalization of the isoparametric element library, which now
allows "e of an element with any number °of total nodes from 8--to 44,
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with any individual edge having from 2 to 5 nodes arbitrarily
spaced along its length.
3. Generalization of the numerical integration scheme to allow an
arbitrary number of Gauss-points (from 1 to 10) in each coordinate
direction, with a default o ption which automatically selects the
number of points in each direction such that the stiffness matrix
will be exactly integrated. (This integration is generally exact
only if the material properties are uniform within the element and
all edges are straight lines).
Reference 1. BOPACE !3-D, Final Re port by The Boein g Company to the MASA
Marsha'1 Space Flight Center, Contract NAS8-30615, April 15,
1	 „>
1975.	 Document D180-13677-1.
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ORIGINAL PAGE IS
OF POOR QUALUT
3
4., Provision of user-selected coordinate systems for describing the
integration point locations and defining the integration point
variables
	
(stresses, strains, etc.). 
S. Elimination of.;the prohibition .against disol psement constraints
between nodes on the same element.
6. Addition of a capability for including elastic anisotropic
materials, through user definition of the anisotronic thermal-strain
behavior and stress-strain matrix, as functions of temperature.
€
The following sections discuss the program modifications in more detail. 	 Included
are updates to the program input data formats, error messages, file usage, size
limitations, and overiav schematic.
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A.2	 INPUT DATA
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	 This section describes the items of BOPACE 3-D in put data which have been undated
for the current version duri q incorporation of the new capabilities. In neneral,
these u''dates are trans parent to users of previous data decks, i.e., previous
data decks can be run essentially without modification.
C-3.	 The actual Drooram format for this item has been corrected to agree with
the format given in the document. The correct format is (6I5/3FI0.0)
instead of (6I5,3F10.0).	 This now requires that inout item C-3 use
two data cards instead of one (both cards may be blank if default values
are used for the various constants in this item).
I-1.	 Number of anisotronic materials (0-5), number of isotrop ic materials (0-5),
fabrication temperature, and default values for four intearation scheme
G
i	 codes.
I
Format (6X, 2I2, 1OX, F10.0, 30X, I4, 3I2)
i The number of anisotronic or isotropic materials may be zero, but the total
number of materials must be from 1 to 10.
The four integration scheme codes are defined as follows.
1.
	
	
The first code defines the type of integration scheme, and in the
current prog ram version may be given as either 0 (blank) or 1.
Both of these current o ptions result in r,-oduct Gauss formula
integration, with a variable number of points in each of the three
parent	 coordinate directions. The 0 specifies an au/"o-
matic scheme, in which the nroaram automaticall y selects the number
of points in each direction sucL that the stiffness matrix will be
ORIGINAII PAGk^
OF POOR QUAI1'1'X1	 A.2-1
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exactl y inte g rated. (This intearation is generally exact only if
the material properties are uniform within the element and all
edges are strainht lines), The 1 s pecifies user- provided values
for number of ooints in each direction, given as codes 2-4.
2-4. These three codes are given if the first code has a value of 1.
Thev are the number of points (from 1 to 10) in each of the ;.
C, n,s coordinate directions, respectively. Total number
of points may not exceed 600. It should be noted that the
DRIB $ pU G,	 stiffness generation time for an element is highly dependentQF POOR	 upon the number of intearatinn points, as well as the number
of element nodes. For example on the IB11 370, generation time
for an 8-node element with 8 intearation points is less than
1 second, while generation time for a 44-node element with
125 integration points is almost 1 minute.
I-2
	
This item now includes first the isotro pic and then the"anisotronic material
data. (If the number of isotro pic or anisntropic materials is 0, the
corresnondinn, data is omitted). The isotro pic data is given as before.
The anisotronic data is given for each consecutive anisotronic material as
described in the items below.
a.	 Thermal strain curves. For each coordinate direction (in
integration- point-variable coordinate system) give the following.
Material number (intener from 6 to 10), coordinate component
number (1, 2 or 3).
Format (2110)
Thermal strain curve for this coordinate direction. For each
curve point give tem perature and strain value, with points in orde-
of increasina tem perature. User has ontion of from l to 4 points
per card.
A.2-2
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b.	 Elasticity matrix definition. (Actual elasticity matrix relating
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total stress to total elastic strain, is comnu,;ed at anv temperature
as an inter polated factor times the in put matrix. The factor and 	 j
input matrix are defined by the following).
i	 a
8
Material number (integer from 6 to 10).
Format (I10)
Curve of elastic matrix factors. For each curve point give
temnerature and factor, with noints in order of increasing
temperature. User has option of from 1 to 4 points ner card.
Format (8F10.0)
Blank card after last point of curve.
Elasticit y matrix by rows, with six entries per row. (Order is
XX ,YY, ZZ, XY, XZ, YZ). Matrix must be symmetric, and defines
relationshin bettreen stresses and engineerin g strains.
Format (6F10.0)
For each element: element I.D. number, material number (1-5 for iso;>
tropic or 6-10 for anisotronic material), the ei ght corner nodes of the
element, the maximum number of intermediate nodes along the edges, I.D.
number of coordinate s ystem to describe integratior " noint locations
( = 0, l or 2), I.O. number of coordinate system to define integration -
point variables (= D, 1, 2 or other), and the four integration scheme
codes (if these codes are not given they are assir .ned the default values
'from input item I-1).
ORIGVAL 
PAGD
pF POOR Q1JAL?Ll'S9	 A.2-3 1	 '.
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Format (10I5, I5, I1, I4, I4, 3I2)
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If intermediate edge nodes are used, they are inout next for each edoe
in the order sho%,n in the figure (see Ref.	 1).	 The same number of inputs
per edge is expected (i.e., the maximum number of nodes ner edge as input
on the previous card), with zeros used for edge-s which do not have the
maximum number of intermediate nodes.	 Up to three intermediate nodes her
edge may be used, and the total number of intermediate nodes may be un
to 36.
I-8.	 For each degree of freedom with a s pecified displacement or constraint:
give node I.D. number, comnonent number (1, 2 or 3) and code. 	 The code to
be given is:
1.	 For specified displacement, a blank (or ma y give the neaative of
the node I.D. number).
2.	 For dependent constrained DOF, the node I.D. number of the
inde pendent DOF in constraint.
3
User has option of sDecifying from one to four DOF on each card.
,
Format (4(315,5X1)
Blank card after last displacement-cnnstraint DOF.
Note:	 Specified forces may be denoted by giving the code e qual to the node
I.D. number.	 However, this is not necessary because any DOF not soecified
is automatically assumed to be a specified force.
A.2-4
A.3
	
Size Limitations
The followi„g variables are used to specify
 maximum size limitations in
BRACE 3-D. The values sew for these variables are given in Table A.3-1. The
first set of values corresponds to the basic 64Y, nroaram version, while the
second set indicates the capabilities which would be obtainable throuah use
of 128K core.
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NMAXI
	 NMAX14 = values as defined in Ref. 1.
MAXNPE	 = maximum number of nodes per element
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MAXINT	 = maximum number of integration points per element
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B	 = maximum wavefront (in nodes)
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A-3-1	 3
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Table A.3-1:	 MAXIMUM PROG°AM SIZE LIMITATIONS
VARIABLE 64 K CORE	 .. 128 K CORE
Problem OOF 3000 3000 1
NMAX1 5 5
NMAX2 1000	 ^`	 ^^
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1000
NMAX3 500 500
NMAX4 5000 5000
NMAX5 2000 2000
NMAX6 20 20
NMAX7
-	
6	
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NMAX8A 30 30
NMAX8B 20 20 "	 •^
}	 NMAX8C 30	 -% 30
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NMAX9 10 10
NMAX10 6 6
NMAXII 10 W I
NMAX12
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1000 1000
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NM.4X13 2 2
NMAX14I 60 60
MAXNPE 44 44
MAXINT 600 600
s	 B* 61 ,99 I
* Based on MAIN program STOR array dimension of 38,000 for 64 K, and 102,000
for 128 K.	 -Larner STOP, array allovis larger B.
4
A.3-2
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AA	 ERROR', MESSAGES	 a
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( )	 The following error message sto p
 code definitions have been added, deleted or
modified.
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351'--. Wronq material number innut on an anistropic thermal strain card.
352 Number of Doints input for an anisotropic thermal strafn curve exceeds
j maximum.`
355
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No points input for an anisotro p ic thermal strain curve.
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481 Wrong material number input on an anisotro pic elastic matrix factor card.
482 —:NuMbe:r of points input for an anisotropic elastic matrix factor curveF
maximum._exceeds
385 No points input for an anisotropic elastic matrix factor curve.
718 I.D. of an integration point location coordinate system not equal to 0,
('	 ) 1 or 2:
r'	 719 I.D. of 'an integration point displacement coordinate s ystem is less thin
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zero or greater than the maximum.
721 The number of	 interior edoe `,nodes on * a side of the next elam?nt exceeds 3.
'	 720 The total number of integration points of an element is zero, negative,
r or exceeds the maximum.
805 (Deleted)
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-A.5	 FILE USAGE _.
The following files have been P.A ed to BOPACE.
Uni t 'Dumber Descrintion Defined by
)
INODAL (=21) Nodal data BLKDTA
ISCR1	 (=22) Contains temporary element data BLKDTA
when BIGSC is called.	 Otherwise
contains the load array	 PREF.
ISCR2 (=23) Contains data that is to be added BLKDTA
to the checkoolnt tape
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A.5
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A.6.	 OVERLAY
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The overlay of ROPP.CE was designed to minimize loading of seoments and to
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maximize the size of the '4AIN program STOR array (common JLB) for a given
core size.
	 A schematic of the overlay is shown in Figure A.6-1.
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BOPACE 3-D addendum: The Boeing plastic analysis capabilities for 3-dimensional solids using isoparametric finite elements

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