AT
london
load
rotation
accurately
shown
ech
airplane
effectivenessof
AA
arc
elasticity
mm2
estimate
SIF
686
loaded
dependence
appropriate
TYFICAL
experimentally
density
photoe
JL
cartwright
reducing
show
jone
ltd
1973
ramesh
involve
MESH
CRACKED
kfa
fracture
1983
3100
9012
panel
sci
already
1981
suitablepath
F7
nondestructive
position
COMPUTATION
table
1able
D6
wa
JO
strengthening
research
alb
considering
jonesand
0'6
application
applicable
rivet
BCD
988
ajiia
0'4
elementsn
specialcrack
hybrid
would
herrmann
EF
significantly
independency
notche
existence
RU
illi
simulation
ofsuch
presente
BI
563
approach
efficacy
arlj
absence
tailored
305
mat
208100
green'
memo
iy31
valid
printed
05mm
appear
area
equation
16J
sheet
exist
INTRODUCTION
four
cty
methodes
rement
affected
600
spec
represented
plastic
fie
vol
aircraft
routine
converged
PATCHED
pernode
TRIM6
near
advance
pre
boron
559
bangalore
many
finite
numerical
act
sunder
ncy
VIA
nonzero
ofli
168
frediani
1974
degreesof
integrating
ASTM
presented
patching
employing
symposium
AI
RAMESHCHANDRA
parameter
fel
tab
tolerant'
1968
stiff
providing
525
published
widely
3100N
engngfracture
length
semi
specimen
the'
2xo
1982
under
mml
k'd
chandra
move
engng
PATCH
PATCHES
layered
raju
velocity
COD
compute
635
laminated
baker
reliable
great
independence
particular
without
moduli
vicinity
department
565
tensity
reduction
integrand
zero
concentration
methodology
order
definitely
data
jfj1cosional
'damage
GURUPRASAD
india
0'3
crackedsheet
integration
assessment
3532
composite
safe'concept
new
centre
evaluation
murthy
reviewed
fji
respectively
562
delhi
problern
integralfor
PL
generated
special
criteria
nocrack
describe
realised
IN
lyd
technological
appl
1105
compared
AIB1C1A
ten
hutchinson
method
material
adhesive
carbon
september
detailed
most
PLATES
inspection
triangular
01mm
560
measurement
gau
again
measurementof
much
part
flight
571
upon
only
correlation
fatigue
structural
reasonable
hlb
convergence
OF
P4
into
advanced
good
translational
alloy
conf
thicknes
state
TRUMPL
sif
francoi
PI
ltion
1977
FAI
uniform
txy
value
displacement
intended
science
specification
EPFM
meth
august
227
tip
some
applied
quadrature
constant
REFERENCES
ahead
non
rhese
evalua
structuresdivision
mechanic
aspect
pergamon
employed
unifonn
vector
elastic
variation
accurate
ultrasomc
experimentalin
'itc
unsatisfactory
cent
numer
tcoe
479
rporating
analytically
contobr
tc5
'fitnes
accuratedetermination
acceptin
evalu
behaviour
variou
pursued
design
055
ter
reiterated
other
term
investigator
perpendicular
oxford
principle
another
15J
P5
powerful
stres
1119
1986
efect
struct
561
well
recent
australia
r201
bolt
297
ajh
pres
unpatched
mmj
fig
P3
r100
figure
node
being
examined
NUMERICAL
witith
different
patchedinvestigation
''ft1isstli
thu
reinforcement
iation
repr
width
int
number
error
erroi
test
100
proved
their
therefore
PRESENT
king
required
also
GX
nonlinear
related
ramamurthy
7644
criterion
agreement
photoelasticity
rooke
1980
correspond
subjected
ha
i'r'
srf
thesi
based
connecting
l1e
FEM
depend
traction
made
field
estimation
such
CRACK
degree
LEFM
edge
example
l1er
mech
7240
member
STRESS
programme
994
patch
evaluate
patched
PJ
ind
governed
geometry
patchand
complex
ajlw
closed
5000
showed
UMPL
element
kobayashi
xperimental
eflection
use
MESHING
1'0
enclose
uniformity
computation
CI
establish
3702
growth
established
mean
numerou
via
une
00mm
THE'FAIL
DIFFER
13J
search
TRIM
208100nfmm2
reinforced
abstract
help
noded
127
NOTATION
020nfmm2
cracked
340
outward
JAI
'integrand'
834
situation
569
there
discontinuity
508
308
plane
entally
selected
IJ
itude
796
366
t'ore
resulting
FEMGEN
POSITIONS
'il
assumption
symmetry
P2
566
line
tegral
result
perimental
solution
plication
need
682
per
computed
tong
physical
809
program
although
period
important
175
comparison
all
INTENSITY
arlf
71020
red
development
limitation
1984
add
factor
analysisof
anisotropic
can1
2024
1976
chosen
modelled
poisson'
3712
modulu
lborawry
estimatiod
contour
extended
olate
SCHEME
ctyey
post
11371984
compendiumof
A3
nfmm2
they
8876
fairly
independ
tott
bonding
according
region
AIAA
TR
jof
reinforcing
pdency
interior
substantially
conventional
edited
tested
energy
model
national
callinan
ctllre
ductile
highly
measured
study
case
regime
proper
rice
crack
824
defined
repaired
1987
lar
568
normal
386
youl
200
'I'
improved
methodology'
adhesivelybonded
photoelastic
formulation
achieved
elongation
distance
establishe
currently
layer
successive
face
'AZ
revealed
provided
roblem
attempt
575
deformation
strain
pian
accuracy
damage
INTEGRATION
force
become
tion
isoparameteric
propertie
1979
edgl
SIF'
FAA
plate
approximate
corresponding
ratwani
D4
APPLIED
shear
FINITE
engineering
scheme
work
pendency
oxd
singularity
tolerance
service
whether
ploye
three
reference
two
each
technique
lastry
CONCLUSION
weight
presentedexperimentaland
829
ultrasonic
efficient
nodulu
494
available
A4
ilacement
however
grow
713
one
estimated
site
laboratory
CHANDRA
epoxy
considered
eel1
mero
theoreticalevaluation
proportion
direction
will
tjowe
389
cause
very
problem
avoid
unexpected
frac
component
usee
BB
strip
thereby
ref
PATH
le2
jptensity
III
D20
107
journal
ratio
HMSO
221
till
suit
direct
amp
J1C
connected
tes
INTEGRAL
ANALYTICAL
due
six
ASKA
UM
dimensional
independent
often
intensity
fiw
similar
evaluated
19J
felt
convert
SECTION
gaussian
astic
ofthe
here
given
ensure
analysi
rack
130
ad
between
828
parallel
3523
aluminium
O'5
tco'ralfor
7944
689
MODELLING
doe
ILLUSTRA
theoretically
determination
tensile
body
564
path
using
FACTORS
SHEET
8mm
critical
pplied
normally
282mm
gauge
compare
literature
aluminium'
313
freedom
integral
obtained
led
concluded
proc
nons
subramanian
ELEMENT
krefl
sre
because
condition
configuration
level
meshe
1978
tit
singular
1971
D3
decrease
1016
experimental
II
techno
originally
used
ENT
FCR
translation
tech
incorporating
finiteelement
USAF
reveal
hence
aeronautical
further
numerically
379
effm
71mm
summary
influence
institute
83444
567
mesh
965
MIL
krishna
7075
point
ked
performance
EJE2
compliance
specified
015
membrane
analytical
amplitude
found
briefly
1140
853
ESTIMATION
aerospace
low
extension
through
sixth
theoretical
patche
received25
loading
linear
transfer
read
surrounding
young'
present
minimal
ARL
bodie
analysed
291
difficultie
general
ijp
noticed
five
2atgt
aeronauticallaboratory
ixd
bntam
0208
theorem
investigation
existing
correction
requirement
mchenry
rwdy
contribution
FACTOR
noted
around
along
not
quarter
rao
P6
unconstrained
2'85
repair
standard
403
1140N
high
demonstrated
fibre
first
vaiue
1985
structure