NASA LaRC05复合材料强度计算新理论详解

#

Symbol

Description

1

E11

纵向杨氏模量

2

E22

横向杨氏模量

E33

E33=E22 for transverse isotropic lamina

3

ν12

泊松比

ν13

Poisson’s ratio (ν13=ν12 for transverse isotropic lamina)

4

ν23

泊松比

5

G12

面内剪切模量

G23

Transverse shear modulus 2-3 plane (G23=E22/2(1+ ν23) for transverse
isotropic lamina)

G13

In plane shear modulus 1-3 plane (g13=g12 for transverse isotropic lamina)

6

XT

纵向拉伸强度

7

XC

纵向压缩强度

8

YT

横向拉伸强度

9

YC

横向压缩强度

10

SL

面内剪切强度

11

α0

压缩断裂角 (default=53˚)

12

φ0

压缩破坏偏折角

13

ST

横向剪切强度

14

ηL

纵向剪切摩擦系数

15

ηT

横向剪切摩擦系数

*Material, name=ABQ_LARC05_DMGCRT_Material-1
*Elastic, type=ENGINEERING CONSTANTS
171420., 9080., 9080., 0.32, 0.32, 0.32, 5290., 5290.
3026.,
*USER OUTPUT VARIABLES,PROPERTIES=15
4,
**E11, E22, ν12, ν23, G12, XT, XC, YT
171420., 9080., 0.32, 0.5, 5290., 2326.2, 1200.1, 62.3
** YC, SL, α0, φ0, ST, ηL, ηT
199.8, 92.3, 53., 2.544, 101.2, 0.082, 0.29,

*Material, name=ABQ_LARC05_DMGINI_Material-1
*Depvar, delete=16
16,
*Elastic, type=ENGINEERING CONSTANTS
171420.,9080.,9080., 0.32, 0.32, 0.32,5290.,5290.
3026.,
*DAMAGE INITIATION, CRITERION=USER, FAILURE
MECHANISMS=4,PROPERTIES=15,tol=0.1
**E11, E22, ν12, ν23, G12, XT, XC, YT
171420., 9080., 0.32, 0.5, 5290., 2326.2, 1200.1, 62.3
** YC, SL, α0, φ0, ST, ηL, ηT
199.8, 92.3, 53., 2.544, 101.2, 0.082, 0.29,
*DAMAGE EVOLUTION,FAILURE INDEX=1,TYPE=ENERGY, mixed mode
behavior=BK, power=2.
** Γb ,ΓT ,ΓL
0.25, 0.5, 0.5
*DAMAGE EVOLUTION,FAILURE INDEX=2,TYPE=ENERGY
** ΓKINK
100.
*DAMAGE EVOLUTION,FAILURE INDEX=3,TYPE=ENERGY
** ΓSPLIT
50.
*DAMAGE EVOLUTION,FAILURE INDEX=4,TYPE=ENERGY
** ΓFT
80.

UVARM子程序

Symbol

Description

UVARM1

基体损伤系数

UVARM2

纤维拐折损伤系数

UVARM3

纤维分裂损伤系数

UVARM4

纤维拉伸损伤系数

DMGINI子程序

Symbol

Description

SDV8

基体损伤系数

SDV9

纤维拐折损伤系数

SDV10

纤维分裂损伤系数

SDV11

纤维拉伸损伤系数