5.4.2. Двумерные элементы

5.
5.4.2.
(Plane Elements)
,
( . 5.4). #
!
,
$
. %
.
,
!
"
!
!
.
Y
3
3
6
5
θ
xm
X
2
1
4
1
2
3
face 5
)
Y
face 4
4
3
4
4
face 1
3
7
face 2
2
face 6
X
α
8
α=(β+γ)/2
β
6
xm
γ
θ
face 3
1
5
1
2
1
2
)
& . 5.4. '
: )
“
”
(
.
“
& . 5.5.
, )
”
face1. #
). (
$
face2. *
face3 – face6. (
$
$
,
(
$
$
–
”
“
!
”
face2, )
face1
$
face6
$
,
.+
“
,
.,
!
.-
$
10°
),
!
$
,
“
(
face (
. 5.5). #
”,
,
,
$
,
$
-
$
Plate,
..
'
–“
”,
,
,
“
)
.
-
”
Shear Panel
.
,
$
$
.
.(
),
Shear Panel
"
$
$
,
,
(
"
.
. 5.6).
$"
$
,
– $
"
(
.%
$
$
-
5.
Y
4
3
θ
xm
2
1
& . 5.6 '
Shear Panel
.%
NASTRAN.
.
./
X
1
4. /
$
X
. .
.
(Thickness),
"
"
.,
$
,
,
,
),
$
1–2
, Ap –
"
# "
,
,
"
F2
"
F1tA p
( L12 + L34 )
"
F1 F2
Shear Panel,
1–2
$
.
NASTRAN
..
.(
,
.
. 5.4.
.+
$
"
.0
.
$
..
.(
(Thickness),
.
. 5.4.
..
3–4. .
-
3–4.
-
.0
(2–3
A1 = 0.5F1t .
4–1).
,
!
$
PSHEAR.
,
$
Shear Panel.
. #
"
.
-
1
2. / Y
. 5.4 . +
,
, .
. 5.4 . /
$
X
.
"
(Nonstructural mass/area).
NASTRAN: CTRIA3, CQUAD4, CTRIA6, CQUAD8, PSHELL.
Bending Only
Bending Only (
Plate.
)
$,
3,
.
.#
,
-
2
X
!
,
1–2
Shear Panel
"
,
1–2
..
L34 –
3–4
,
!
X,
X
Xm
Plate.
F1 ≤ 1.01 ,
4–1. 0
$
$
Membrane
Membrane
$
-
,
,
,
$
$
.#
,
"
NASTRAN: CSHEAR
.0
(
)
$
F2
%
$
,
.
- $
$
"
$
1–2
F1 > 1.01 ,
*
"
– 1–2, 2–3, 3–4
:
3–4
F1
X,
-
,
"
, L12
.
Y
$
"
F1 = 1.0 ,
,
"
,
5.6,
Xm
$
(Nonstructural mass/area),
F1 F2 ,
.# $
$
$
.
F2 .
,
A1 =
t–
2,
"
(Effectiveness Factors) F1
"
,
$
.%
!
$
,
"
,
X
,
Membrane.
NASTRAN
.
-
-
5.
..
$
(Thickness),
"
$
. %
I 0 = t 3 / 12 ,
)
"
(Nonstructural mass/area),
"
(Bending Stiffness),
(Top Fiber)
$
(Bot Fiber).
$
t –
,
"
Thickness. *
,
Stiffness
I
$
bs = 0.0 ,
.0
,
! ,
I0 . ,
bs = I ⋅ t 3 / 12 . %
,
. Plate (
, )
.1
..
, .
-
Bending
,
,
-
bs = 1.0 .
NASTRAN: CTRIA3, CQUAD4, CTRIA6, CQUAD8,
Plate
)
.
,
,
,
..
.
.
,
!
. 5.4.
,
PSHELL.
-
Membrane.
"
(Thickness);
"
$
(Bending Stiffness);
!
,
"
(Transverse shear/Membrane thickness);
$
(Top Fiber)
$
(Bot Fiber). #
$
,
"
(Bending)
(Transverse Shear).
$
"
(Membrane-Bending Coupling).
.,
Bending Stiffness
$,
Bending Only.
0
Transverse shear/Membrane thickness,
0.833333.
,
"
"
(Offset)
./
$
$
,
Membrane-Bending Coupling
. ' "
(Offset)
"
Modify
Update Element
Adjust Plate... ( .
3.12.4).
#
"
.
.0
NASTRAN: CTRIA3, CQUAD4, CTRIA6, CQUAD8, PSHELL.
.1
,
(Nonstructural mass/area);
"
,
"
.
(
.
. 5.7).
$,
$
Laminate
Laminate (
)
Plate,
$
,
.
$
,
-
90
Z
3
X
2
Y
n
n-1
4
1
3
2
1
& . 5.7. '
..
Laminate
./
,
!
,
.
. 5.4.
..
$
1-2
.
$,
X
.
-
Xm
Membrane. #
.+
$
5.
.
(Angle)
(Material),
(Thickness). ,
(Bottom Surface),
"
(Nonstructural mass/area),
$
(Bond Shear Allowable),
(Damping).
(Failure Theory).
.' "
$
).
NASTRAN $
!
%
$
"
:
X
-
"
$
(Reference Temp),
"
$
z = −0.5 (
-
"
:
!
*** Laminate Elements were written with default orientation. Usually Laminates require a specified
orientation
(
Laminate
,
.
)
'
2
,
"
Element/Property Type,
,
), .
$
,
"
.
.
Element Material Orientation, .
5.5.
$
Modify
Update Element Material Angle… (
3.12.4.
,
,
Reference Temp.
.
NASTRAN: CTRIA3, CQUAD4, CTRIA6, CQUAD8,
.
3
,
$
.0
,
-
$
$
$
,
-
PCOMP.
Plain Strain
.
Plain Strain (
)
,
( σ z = τ xz = τ yz = 0 ).
.(
.
,
$
,
.
"
..
(Thickness),
$,
.
.0
Plot Only
. Plot Only (
.
$
,
"
,
$
Fiber),
$
4
$
..
,
( ε z = γ xz = γ yz = 0; τ xz = τ yz = 0 ).
! –
Membrane, .
. 5.4.
"
(Nonstructural mass/area)
(Top Fiber)
$
NASTRAN: CTRIA3, CQUAD4, CTRIA6, CQUAD8,
)–
"
.
..
. 3
,
$
$
-
(Bot
PSHELL.
$
.'
-