EFFECT OF LONG-TERM LOADING
ON GLASS-REINFORCED
PLASTIC LAMINATES
Revised September 1958
INFORV.AT:-,1.1
AND p 77'
No. 2039
FOREST PRODUCTS LABORATOR Y
MADISON 5 WISCONSIN UNITED STATES DEPARTMENT OF AGRICULTURE
FOREST SERVICE
In Cooperation with the University of Wisconsin
EFFECT OF LONG-TERM LOADING ON GLASS-REINFORCED
1
PLASTIC LAMINATES —
By
K. H. BOLLER, Engineer
2 Forest Service
Forest Products Laboratory, —
U. S. Department of Agriculture
Summary
The U. S. Forest Products Laboratory, in cooperation with the Bureau of
Ships, Department of Navy, evaluated the stress-rupture and creep characteristics of several glass-fiber-reinforced plastic laminates typical of those
used in shipboard applications. Seven typical laminates were tested in tension,
flexure, and shear at 73° F. and 50 percent relative humidity and at 73° F. in
water for periods up to 4 years to observe strains and time to failure.
at rupture decreases with time,
The data showed that the tensile stress,
' a- R'
t, so that their relationship may be represented by the equation, cr it =
Mlog t. The stress constants o- and M have been evaluated for durations of
0
stress up to 10,000 hours. The data also showed that the tensile strains may
be represented by the relationship,
E
=
EO
'
sinh olo- + m t tn sinh
e
v/ 6
E is total strain in inches per inch, a- is applied stress level in pounds
, e , m , and am areconstants
per square inch, t is time in hours, and n,
that have been evaluated in this investigation.
-This report covers work done under Bureau of Ships Contract Nos. BuShips/
1700S-540, 1700S-578, and 1700-597-58.
—Maintained at Madison, Wis. , in cooperation with the University of Wisconsin.
Rept. No. 2039 (revised) -1-
Agriculture- Madison
may also
f
be expressed by a similar equation, E f = A + Btn in which the exponent n had
the same value in flexure as it had in tension.
The flexural data showed that the total strain in the outer fibers ,
E
Introduction
Reinforced plastics, in common with other structural material, are known to
fail under long-continued loads at stresses less than the ultimate stress developed in standard short-time tests. In developing design criteria for such
shipboard applications as hulls, decks, roofs, piping and pressure vessels,
the periods during which the laminates are under continuous loads are measured in years. This study was therefore undertaken to obtain stress-rupture
data in tension, flexure, and shear on typical plastic laminates for several
years and to obtain deformation data in tension and in flexure.
This work was conducted at the Forest Products Laboratory from December
1952 to May 1958 at the request of, and in cooperation with, the Navy Bureau
of Ships. Some of the results of this work have been previously reported, as
data became available, in an interim report (1), 3 and in quarterly progress
reports 1 through 9 (3) under this contract. The object of this presentation
is to report under one cover all of the pertinent strength data obtained to date
in this work.
This report presents test data that have been obtained over a period of 4 years.
Some of the data are for durations of stress for the full 4 years while other
data are for lesser durations. Data are presented for 7 glass-reinforced plastic laminates to show the effect of 2 types of resin (polyester and epoxy) in
combination with 5 types of glass reinforcement (mat, woven roving, No. 1000
fabric, 181 fabric, and straight-unidirectional fibers) on the stress-rupture
and creep rupture characteristics at 0° to the warp. The data presented for
these laminates also show the effect of exposure in water at 73° F. compared
with duration of exposure at 73° F. and 50 percent relative humidity. Stressrupture data are presented for tension, flexure, and shear; however, creeprupture data are only presented for tension and flexure. As in all research
projects, limitations restrict the number of replications at a given stress
level; hence, a minimum number of specimens were tested to establish the
trend of the stress-rupture curves. Such a trend was established at the higher
level of stresses that produced failures. Hence, in some instances there is a
lack of strain data at the lower stress levels.
-Underlined numbers in parentheses refer to literature cited at the end of this
report.
Rept. No. 2039 -2-
The data presented here were analyzed so they could be presented in their
most useful form. Many types of engineering and structural material undergo progressively increasing strains with time while they are at constant stress.
The variability and complexibility of this strain-time relationship depend on the
material, the stress, temperature, and other factors. Most materials follow
the classic strain-time pattern in three stages, after the initial strain that results from the application of the load. The first is a transition stage with a
decreasing strain rate. The second is a stage of minimum strain rate, and
the third is an increasing strain-rate-stage to failure. Numerous attempts
have been made to equate the strain to all of the variables that affect it (9),
but most formulas deal with the behavior during the second stage. Of all the
formulas that represent the strain-time behavior of reinforced plastics during
the application of load and in the first and second stages, the best equation for
total strain, E t , that might be usable to designers appears to be in the form,
e t =e o + mtn where the constants e o and m are hyperbolic sine (sinh) functions
of the steady stress applied. This relationship was suggested for plastics and
has been used to some extent by William Findley and his associates (6, 7).
The constants in the relationship and in the sinh function are a means of comparing creep behavior. The comparison may be made for different materials
or for steady stress applications on the same material but in different directions or under different exposure conditions. The analysis of the data with this
equation also provides a means of averaging the stress-rupture and creeprupture data so that the designer may use stress values other than those that
were used in the experiment.
Material
The study of creep- and stress-rupture characteristics was made on 2 types
of resin -- polyester and epoxy -- and on 5 types of glass reinforcements -mat, woven roving, No. 1000 fabric, 181 fabric, and straight fibers. The
following flat-laminated 1/8-inch-thick material combinations were used in
this study:
1.
Laminate A -- polyester resin and 181 glass fabric.
2.
Laminate B -- polyester resin and mat.
3.
Laminate C -- polyester resin and No. 1000 glass fabric
4.
Laminate D -- epoxy resin and 181 glass fabric.
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5.
Laminate E -- polyester resin and woven roving.
6.
Laminate F -- nonrigid polyester resin and 181 glass fabric.
7.
Laminate G -- epoxy resin and straight fibers.
The fabrication data of these laminates are listed in table 1. The resin content listed was obtained by the ignition method, No. 7061, Federal Specification L-P-406b for plastic, organic; the specific gravity listed was calculated
from weight and dimensions of the entire panel before specimens were cut
from it.
The quality of these laminates was also determined from tensile, flexural, and
shear tests at 73° F. and 50 percent relative humidity and at 73° F. in water;
this is in accordance with Federal specification L-P-406b, test method No.
1011 and specimen type 2 for tension, test method No. 1031.1 for flexure, and
test method No. 1041 for rectangular shear specimens.
Since the laminates were 1/8 inch thick, the flexure specimen was 1/8 by 1/2
by 4 inches and was tested on a 2-inch span, and the shear specimen was 1/8
by 1/2 by 3 inches, tested with its shear-rupture plane perpendicular to the
plies. These quality tests were made soon after the laminates were fabricated
and then additional quality tests were made after the material had been exposed.
Only the initial tests were made on some materials while others have been
evaluated after the laminates were 1, 2, or 3 years old. The properties thus
obtained are presented in tables 2 through 14.
Stress-Rupture Equipment
Since the long-term tests in this investigation were to be carried out for a
period of years, it seemed desirable to use simple and inexpensive apparatus
that was still accurate. Such equipment was designed and fabricated at Forest
Products Laboratory. The equipment for each mechanical test was designed
to apply the load with weights and a lever system. The design of the loading
system was such that the specimens could be immersed in water. The equipment for applying tensile loads consists essentially of a weight platform, a
horizontal lever, and the necessary grips and linkages -- all supported by a
tank in which the specimen was tested in a horizontal position as indicated in
figure 1. The details of this apparatus are shown in figure 2.
A special tensile extensometer was used to measure the strains of specimens
in the water-filled tank.
It consisted of a system of levers and mirrors
Rept. No. 2039 -4-
attached to knife edges on the specimen. This system, which is an averaging
device, provided both mechanical and optical magnification. The details of
this extensometer are shown in figures 3 and 4.
The equipment of applying the flexure loads consisted simply of a horizontal
beam pivoted in such a way that a vertical load was applied at midpoint of a
2-inch span on a specimen in a tank. The lever system provided a slight
mechanical advantage. The deflections were measured with dial gages that
read to 0.0001 inch. Figure 5 shows this apparatus.
The equipment for applying the shear loads was the same as that used for applying the tensile loads except that a tensile-type Johnson shear tool is a
modification of the Johnson shear tool described in Federal specification
L-P-406b, test method No. 1041, for rectangular specimens. This modified
version is shown in figure 6.
There were 44 tensile and shear machines and 24 flexure machines used to
make the creep tests in this investigation. These machines were on tables
in a room maintained at 73° F. and 50 percent relative humidity. Each machine was calibrated with a load cell and weights to determine its mechanical
lever ratio, and each extensometer was calibrated with a known movement at
its knife edge to determine the mechanical and optical magnification of the
system.
In addition to the loading and deformation systems, a number of the devices
were equipped with electric clocks to determine time to failure in short-time
tests. However, when time to failure was expected to be in excess of 2,000
hours, such timers were not used. Instead, an electric light signalled a failure, and time to failure was to the nearest day.
Method of Test
After the quality of the various laminates had been determined by the standard
short-time loading methods in a universal-type testing machine, stressrupture and strain-time data were obtained in the machines built for that purpose. The shape of the specimens used for long-term loading was the same
as that used for the short-term loading of all materials except the creep test
specimens from the epoxy straight fiber material and the nonrigid polyester •
resin laminate. Creep specimens from these materials required a smaller
cross section so that their loads would not exceed the capacity of the specially
built machines. The flexure specimens of both these materials were 1/8 by
1/4 by 4 inches. The tension specimens of the epoxy straight fibers had a
net area 1/8 by 1/8 inch in cross section. In addition, two aluminum plates,
Rept. No. 2039
-5-
0.032 by 1 by 3 inches, were glued to the flat sides of the grip area to prevent
shear failures in the shank of the specimen.
The load that was applied to the various specimens depended on the quality of
the material. Stress levels were chosen beginning at 80 percent of the maximum control strength and decreasing at 5 percent intervals until the specimen
continued to support its load. When a specimen failed, another at a lower
stress replaced it. Some specimens have sustained their loads for over 30,000
hours. Eight to 10 specimens were used to establish each stress-rupture
curve. This procedure limited the stress-time-strain relationship to the
higher percentages of stress so that, in a few instances, strain data were obtained at stress levels below the stress-rupture data.
The loading weights -- the value of which was computed from the stress chosen,
the cross section of the specimen, and the lever ratio of the creep machine -were supported on a jack while the specimen was being installed in the creep
machine. The weights were then slowly lowered so that the total load would
be applied to the specimen in about a 2-minute period. While the load was being applied, the deformations were observed. Sometimes the dial on the gears
of the extensometer had to be reset because of limitations in travel. The
moment at which, in the opinion of the operator, the specimen completely
supported the weights marked the beginning of time. Observations of deformation were then made at 0.05, 0.15, 0.65, 1.0, 7.0, and 24 hours, with approximately geometric increases up to 1-month intervals. Strain data were not observed on the shear tests.
Presentation of Data
Quality Data
Tables 1 through 14 present strength properties such as modulus of elasticity,
stress at proportional limit, and the stress at failure. Stresses computed on
the tensile test loads are, of course, direct axial stresses; stresses computed for the flexural test loads are stresses in the outer fibers, assuming a
straight line stress distribution across the depth of the beam. In addition to
the strength properties reported as short-time strengths at 0 years, these
tables report tests of strength properties obtained after exposure for yearly
periods. These tests were made on specimens that had been in the same exposure as the long-term specimens but were not stressed during the exposure.
The strength data show variations in maximum stress after exposure. The
dry maximum stress in general appears to vary more than the wet maximum
stress. The dry maximum stress does not show a trend, but the trend of the
Rept. No. 2039
-6-
wet maximum stress appears to be a decreasing stress with increases in time.
This observation would indicate that there is some deterioration due to prolonged exposure to water; the stress-rupture data would be the sum of both
duration of exposure and duration of stress. No further attempt was made to
isolate these effects.
Tables 15 through 29 present data at applied stress levels on time to failure
and certain information, both observed and computed, that relates to strains.
Tensile Data
The tables presenting tensile creep data show, in columns 1 and 2, the applied
load expressed both as stress and as a percentage of the control strength,
which is the quality at 0-year exposure. Columns 3 and 4 show the period.of
sustaining the applied steady stress at the respective exposures. Columns 5
through 12 show the observed strain data at the periods indicated. Column 13
presents the ratio of the approximate strain just before rupture to the strain
observed at zero hour. These data in columns 5 through 12 are actually a condensation of the observed data. The data were actually observed much more
frequently but not necessarily at the exact period indicated. The original data
were plotted on semilogarithmic paper with strains shown as ordinates in uniform scale and time as the absissa in logarithmic scale. Strains at the indicated periods were recorded and a smoothed curve drawn through these points.
This smooth curve was an average of the observed points and the equation that
represents that curve is e t = c o + mtn where e t is the total strain in inches per
inch, t is the time in hours, and e m, and n are constants in the equation.
O
Columns 14 through 16 of these tables of tensile creep data present the values
of these constants at their respective stress levels. Since there are 3 unknown
constants in the equation for 1 stress level, a minimum of 3 points on the
strain-time curve would be required for their solution. Hence, these constants were evaluated by using 3 periods of time, t 1, t 2 , and t 3 ; these were
— — —
1/2
eat these
chosen so that t 2 = (t i t3 )
and observing the strains e l' E 2,
3
respective periods. Then
33 log e 2 c
n= t2
log ir
e 2
el - eo
31 2
o=
and then m =
E 3 + e l - 2e2
t n
l
E E
or
E
Since there were usually more than 3 points on the strain-time curve from
0.016 hour to failure at each stress level, these equations were only used to
approximate one of the unknowns, and then the others were solved graphically.
Rept. No. 2039
-7-
For example, periods of time were chosen at 1, 10, and 100 hours or at 10,
100, and 1,000 hours; then the strains were noted at these periods so that
either n or e o could be computed by the above equations. If e o was calculated,
n
then the values of E t - E 0 = mt from the original data were plotted on logarithm-logarithmic coordinates as log (e t - e o ) versus log m plus n log t; if
the resulting points were in a straight line, this first approximation of e 0
was correct. If not, another value of e o was used and the plotting was repeated.
If, however, n were approximated first, then the values from the original data
+ m (t11) were plotted on cartesian coordinates with E t values as
of E
t =eo
ordinates and (t n ) as absicissa to solve
for E D and m. The values of e , m,
o
—
—
and n that best agreed with the original data are shown in the tables.
Flexure Data
The tables presenting flexural creep data show in columns 1 and 2 the applied
load, expressed both as stress and as a percentage of the control strength at
0-year exposure. The stress is expressed as pounds per square inch in the
outer fibers at the center of the span. It was computed from the classic equation
Mc
cr
where M is the moment, c is 1/2 the depth of the beam, and I is the moment
of inertia (bh 3 /12 for a rectangular beam).
Columns 3 and 4 of the tables of flexural creep data show the period the specimen sustained the constant load at the center of the beam at the respective exposures. Columns 5 through 12 show the observed deflection data that has
been converted to strains in the outer fiber at the center of the span at the
periods indicated. These strains were computed by assuming a straight-line
stress distribution
across the depth of the beam. The equation for strain, e,
2
where
d is the deflection at midspan, h is the depth, and 1 is
is e = 6dh/1
the span. These data are actually a condensation of the observed data. The
data were actually observed much more frequently, like the tensile creep
data, but not necessarily at the exact period indicated. The original data
were plotted on semilog paper with strains as ordinates on the uniform scale
and time on the abscissa in logarithmic scale. Strains at the indicated periods
were observed on a smoothed curve drawn through the observed points.
Column 13 presents the ratio of the approximate strain just before rupture to
the observed strain at zero hour. Columns 14 and 15 present constants that
approximate the strain-time relation in flexure.
Rept. No. 2039
-8-
An equation similar to that used in the tensile analysis was used for flexural
strain analysis. The equation that approximated the flexural data is e f = A +
Btn where er is the strain in the outer fibers; A is a constant and is a function
of applied stress and the tensile constant, e o ; B is a constant and is a function
of the applied stress and the tensile constant, m'; t is the time of steady stress
exposure; n is the tensile-time constant. Constants A and B were evaluated
at each stress level by plotting the observed strains, e f , as ordinates on
th
cartesian coordinate and the time to n power as abscissas. The value of n
was the same as that determined for the tensile tests. This choice of n was,
in general, good because the strain-time relation was essentially a straight
line for all materials except the polyester resin and 181 glass fabric (dry) and
the polyester resin with,woven roving (wet). The strain-time relation for
these material tests was concaved upward.
Shear Data
Table 29 presents the stress-rupture data in shear (Johnson double shear) of
five glass-reinforced plastic laminates. Those laminates include the four
laminates made of polyester resin and the following orientations of glass fibers
-- mat, woven roving, No. 1000, and 181 fabric. The fifth laminate was made
of epoxy resin and 181 fabric. The other two materials, epoxy with straight
fibers, and nonrigid polyester with 181 were not included. The table shows
the strength values in pounds per square inch and , in percent of control strength
that were sustained for the periods indicated under the conditions indicated.
It should be noted that shear values obtained by the Johnson double shear method
of test are the shear strength of the material in a plane perpendicular to the
laminations. As such, the plane of fracture was also perpendicular to the
glass threads. The ultimate strength in this direction is considerably higher
than when the fracture is in a plane parallel to the laminations.
Discussion of Results
Stress Rupture
The stress-rupture characteristics of seven typical glass-reinforced plastics
are shown in figures 7 through 16. These figures show the familiar reduction
of stress with increases in time. The experiments for most materials have
now been conducted long enough so that lines representing the average stressrupture data have been drawn to 10,000 hours.
Rept. No. 2039
-9-
If these structural materials have an endurance limit as part of their stressrupture characteristics, a stress level that can be sustained indefinitely has
not been conclusively obtained in this experimental work. Stresses have been
sustained for 10,000 hours, which have aided in establishing the present curves.
Stresses have also been sustained for 30,000 hours that, if they fail, will cause
the present curve to be lowered; if they do not fail, the endurance limit has
been reached. If the present curves are correct and were to continue for 10
years, the reduction in stress below the 10,000-hour endurance-limit stress
would be less than 10 percent of the short-term ultimate stress.
The equation describing these lines from 1 hour to 10,000 hours is a R =T o-M
M log t where cr R is the failing stress, To is a constant, M is the slope (a
constant) and t is time in hours.
The values of constants T o and M have been determined and are presented in
table 30. This table also presents the average stress that would be sustained
for 10,000 hours. A comparison of strength values shows a wide range in normal values; however, that range is reduced considerably when the strengths
are compared as a percent of their short-time ultimate strength. For example,
the stress endurance at 10,000 hours ranges from 5,300 to 77,700 pounds per
square inch in the tensile dry test; however, the percentage ranges only from
6 2. 4 to 69.4 percent. Further comparison of stress endurance at 10,000 hours
shows that the stresses obtained in dry conditions for all tests -- tension,
flexure, and shear -- range between 51.4 and 81.1 percent of ultimate strength;
stresses obtained in all wet conditions range between 35.5 and 61.1 percent.
The majority of the stress-rupture curves have been drawn to represent the
average data with a fair degree of certainty; however, laminates reinforced
with a mat or woven roving do yield data with a great degree of scatter, and
the laminates made with nonrigid polyester resin and epoxy with straight fibers
have data for only a short period of time compared with the data from other
laminates. This experimental scatter is partly attributed to the size of specimen used for loading. The data are accurate, but are obtained from a small
area where large variations in reinforcements occur.
Figures 7 through 16 show quite clearly the order from highest to lowest
strength materials. The plastic laminate reinforced with straight parallel
glass fibers has, of course, the highest strength, and the laminate reinforced
with the mat has the lowest. The epoxy resin laminates had a higher strength
than the polyester; the nonrigid polyester was weaker than the rigid type.
Water affects all of the laminates by reducing their ability to sustain loads.
The polyester laminates are affected more than the epoxy laminates.
Rept. No. 2039
-10-
Strain- Time Tension
In addition to obtaining stress-rupture data in this investigation, creep strains
were also measured in the tension and flexure tests. Strains were primarily
obtained on specimens in conjunction with the stress-rupture data and hence
at the failing stress levels, but a few measurements were made on specimens
at low stress levels. The creep data that were obtained are presented in the
tables. The values of the constants in the equation describing the straintime relation at each stress level are also presented. In order to make these
strain-time relations more useful at stress levels other than those for which
they were computed, they are related to stress. The values of c o , m, and n
were plotted on Cartesian coordinates as a function of their respective stress.
Smooth curves were drawn through the points to represent the average values.
The equations of these curves were chosen to be a hyperbolic sine function,
e0 =c
0
sinh —
o-
e
and
cr
m = m' sinh —
o-
where
o
and
e , m', (re,
o
are constants.
These constants were determined by successive approximations until the
curves represented the data ( 1 1 ) . The value of n was a constant that may be
a function of temperature (5), but temperature in this investigation was a
constant.
The values of these constants in the equation now describe the strain-time
stress relation. These constants are presented in table 31. Sufficient data
are not available to evaluate these constants for laminates made of nonrigid
polyester with 181 fabric and epoxy with straight fibers. Tables of similar
constants on other materials are available in other reports (2, 4, 7).
The strain-time-stress curves that , these constants describe are reproduced
on figures 17 through 25 with typical curves of observed data and on approximate line of stress-time-strain failures. These figures depart from the conventional stress-log-time plot, stress-strain plot, or strain-log time plots
inasmuch as their plot is total strain versus time n . Strains are on a uniform
scale and so is time n , but time itself is on a variable scale. The strains at
a constant stress are a straight line with slope m.
The average values of e 0 at each stress level are on the strain ordinate.
These values of e 0 do not necessarily equal the values of strain obtained in
Rept. No. 2039
-11-
conventional load-elongation tests in a universal-type test machine. Such a
conventional test takes time and the values of e 0 are theoretically at zero time.
The stress-time curves of a conventional tesraTe, however, an approximation
of e 0 values. Observed values of the strain at the beginning of time in this ex-
=
periment scatter considerably from the conventional stress-strain curve. The
exact cause of the scatter is unknown; however, it is partly due to variable
initial loads on the specimen in its horizontal position in the creep machine.
The averages of the observed data and its presentation as curves in figures 17
through 25 show good agreement between observed and the average curves.
The amount of strain that takes place due to a steady stress is a small percent
of the initial strain for glass-reinforced plastic laminates at 0° to warp.
The line of failures on figures 17 through 25 is an approximate location of
stress with time. The more accurate values of stress and time have been
shown previously by the equation and data of o- R = cr0 - M log t. The limiting
values of stress in the strain equation
v
h
e t =E o sin
0-
+ m'tn sink
Cr
is therefore
o-R = 0-0 - M log t
Strain- Time Flexure
The tables that present flexural creep data show stresses and strains that
existed in the outer fibers at midspan. This is, of course, the location of
the maximum bending moment. These stresses and strains were computed
from the classic assumption of straight-line distribution across the depth.
The simply supported, centrally loaded beam of plastic material presents a
complicated relationship between tensile, compressive, and shear stresses,
their location, deflections, and bending moments. The relationship is complicated by time and temperature. The evaluation and comparison of relationships is beyond the scope of this investigation; however, a simple analysis
was made to compare the strains observed. For a material such as nylon,
creep-time relations in tension, compression, and shear were applied to
flexure by Marin (10) or, for a grade C canvas laminate, relations were developed by Findley (8). The latter derivation showed that the deflection, W,
of a beam might be a function of constants e (!., me, and n evaluated in the tension test, so that W = C (e 0' + m'tn).
_
Since observed deflections in this program were converted to strains in outer
fibers e f, these strains might be equal to e f = A + Bel where A and B are
Rept. No. 2039
-12-
constants, a function of e 0 1 and m', at a constant stress. Values of e f from
the tables were plotted at their respective durations to the n power, similar
to tensile creep data on figures 17 through 25, and values of A and B were
determined. These values of A and B are listed on the flexure tables. A
majority of the data provided straight-line curves on these coordinates, but
for some materials and test conditions the observed data was either a curve
or scattered too much to establish a trend. Further analysis of the values of
A and B shows that each may be a function of stress so that
A + a' e0'
and
A = b' m'
where a' and b' are new constants. The values of these constants are shown
in table 32. Values for the laminate with woven roving scattered too much to
be included, and there were too few values to analyze for the remaining laminates.
Conclusion
The stress-time studies that are presented here on the properties of seven
typical glass-reinforced plastic laminates indicate that the stress time-torupture characteristics can be represented by the equation, °R = a-0 - M log t.
The study shows that the laminates have a strength order (strongest to weakest)
that remains unchanged for the three mechanical tests at 1 hour and at 10,000
hours. The laminate containing the straight fiber was the strongest and that
containing the mat was the weakest. If the dry tensile strength of these lamiepoxy
nates at 10,000 hours is compared, for example, the resin and
straight parallel fiber laminate will sustain 77,700 pounds per square inch,
and the polyester resin and mat will sustain only 5,300 pounds per square
inch.
The study also shows that the strength sustained in the dry condition for 10,000
hours, and in some cases for 30,000 hours, is not below 51.4 percent of the
ultimate dry static strength for all seven materials. It also shows that the wet
strength that will be sustained is not below 35.5 percent of the ultimate wet
static value.
Rept. No. 2039
-13-
The curves relating stress to the logarithm of time extend from 1 to 10,000
hours as straight lines. Although some data are available to 30,000 hours,
there are not enough to establish a "knee" or endurance limit in the stresstime relationship.
The experimental stress-strain-time data obtained from five laminates in this
study in tensile tests can be represented by the equation,
E t = E o ' sinh
cr
o-
+ m'tn Binh
Cr
Constants in
in this equation were evaluated so that average design curves are
presented on strain-time coordinates at various constant stress levels.
The experimental stress-strain-time data obtained from flexure tests were
analyzed for four materials. The study showed that the strain could be approximated by the equation e f = A + Btn where A and B are constants that are functions of stress and exponent n has the same value in flexure as in tension.
Rept. No. 2039
-14-
Literature Cited
(1) BOLLER, K. H.
1955. Effect of Long-Term Loading on Glass-Fiber-Reinforced Plastic
Laminates. Forest Products Laboratory Report No. 2039. Also
presented to Society of Plastic Industry, February 1956.
(2) 1957. Tensile Stress-Rupture and Creep Characteristics of Two GlassFabric-Base Plastic Laminates. Forest Products Laboratory
Report No. 1863.
(3) 1955-57. Research and Development in Reinforced Plastics and Honeycomb Construction. Bureau of Ships Plastics Program quarterly
reports Nos. 1 through 9, October 1955 through December 1957.
(4) FAIRCHILD KINETICS, Division Fairchild Engine and Airplane Corporation
1958. Manual for the Use of Glass-Reinforced Plastic Laminates in Boat
Construction and in Miscellaneous Shipboard Applications. Report
No. 1412-8. January.
(5) FINDLEY, W. A.
1956. Influence of Temperature on Creep, Stress-Rupture, and Static
Properties of Melamine-Resin and Silicone-Resin Glass-Fabric
Laminates. U. S. National Advisory Committee for Aeronautics
Technical Note No. 3414.
(6) , ADAMS, C. H. , and WORLEY, W. J.
1948. The Effect of the Creep of Two Laminated Plastics as Interpreted
by the Hyperbolic-Sine Law and Activation Energy Theory. Proceedings American Society for Testing Materials, Vol. 48.
(7) , and KHOSLA, Gautam
1956. An Equation for Tension Creep of Three Unfilled Thermoplastics.
Society of Plastics Engineering Journal, Vol. 12, No. 12.
(8)
, and POCZATEK, J. J.
1953. A Relation Between Creep in Tension, Creep in Bending, and
Tension Tests. Research Project of Department of Theoretical
and Applied Mechanics, University of Illinois, Report No. 1,
August.
Rept. No. 2039
-15-
(9) KEMPNER, JOSEPH and HOFF, N. J.
1956. Bibliography of Creep for Structural Engineers. Wright Air
Development Command Technical Report No. 56-40.
(10) MARIN, JOSEPH, WEBBER, A. C., and WEISSMANN, G. F.
1954. Creep-Time Relations for Nylon in Tension, Compression, Bending, and Torsion. American Society for Testing Materials Proceedings, Vol. 54.
(11) NADAL A. and McVETTY, P. G.
1943. Hyperbolic Sine Chart for Estimating Working Stresses of Alloys
at Elevated Temperatures. American Society for Testing Materials
Proceedings, Vol. 43, p. 735.
Rept. No. 2039
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Table 12.--Short-time properties of glass-reinforced plastic laminates
(nonrigid polyester resin plus 181 fabric)
used in long-term tests
Specimen: Tested at 73° F., 50 percent No. :
relative humidity
Tested at 73° F. in water
:Modulus of:Proportional: Maximum :Modulus of:Proportional: Maximum
:elasticity:limit stress: stress :elasticity:limit stress: stress
1A--000
••
p.o.i.
:
1,000
2.181L
: 1,000 • 1 ,00 0
: p.s.i. : p.s.i.
p.s.i.
1,000
: 1,000
p.s.i.
12.40
11.96
12.51
12.61
12.88
12.47
:
:
:
:
:
:
40.05
34.94
34.18
34.20
34.92
35.66
21.78
18.35
:
:
36.90
19.44
:
16.97
:
37.65
36.74
20.70
19.45
:
:
37.12
36.92
TENSILE PROPERTIES
1
2
:
:
2,403
2,395
3
4
5
:
:
Av.
:
:
:
42.00
42.70
:
:
2,387
2,384
2,357
14.90
13,77
12.65
40.48
:
2,196
11.93
11.90
:
:
41.78
40.62
:
:
2,211
2,222
2,385
13.03
:
41.52
:
2,254
2,339
2,300
•
.•
•
.
•.
•
COMPRESSIVE PROPERTIES
1
2
:
:
2,407
2,370
:
:
:
3
4
5
24.07
18.01
:
:
:
2,368
:
17.86
:
:
:
:
20.38
15.60
19.18
:
:
Av.
2,314
2,363
2,364
43.90
41.40
:
:
41.90
44.85
:
:
2,382
2,370
2,383
42.98
43.01
:
:
2,352
2,368
2,354
•
•
36.20
FLEXURAL PROPERTIES
1
2
:
:
2,473
2,427
33.60
34.68
3
4
5
:
:
:
2,363
2,336
38.20
:
Av.
:
34.75
36.80
35.61
:
:
:
2,312
2,382
:
:
55.10
53.35
50.95
54.38
53.95
53.55
:
:
:
:
:
:
1,986
2,168
21.87
24.13
:
2,112
24.05
23.74
:
24.68
23.69
:
:
2,097
2,078
2,088
45.05
45.18
4-4.60
45.33
46.08
45.25
Table 13.--Short-time properties of glass-reinforced plastic laminates
(epoxy resin plus straight fibers) used
in long-term tests
Specimen: Tested at 73 0 F., 50 percent
No. :
relative humidity
Tested at 73 0 F. in water
:Modulus of:Proportional: Maximum :Modulus of:Proportional: Maximum
:elasticity:limit stress: stress :elasticity:limit stress: stress
••
:
1, 0 00
p.s.i.
••
:
1,000
p.s.i.
: 1,000 : 1)000 ••
:
p.s.i. :
p.s.i.
:
1,000:
:
p.s.i.
:
:
:
60.73
71.00
90.75
1,000
TENSILE PROPERTIES
1
: 3,890
:
2
: 4,124
:
: 4,360
: 4,270
: 4,350
Av. : 4,199
3
4
5
72.60
63.30
56.60
64.17
: 92.30 : 3,996
: 104.80 : 4,102
- 93.08 : 4,320
110.70 • 4,220
: 104.70 : 4,267•
: 101.12 : 4,181
: 88.45
: 98.82
: 98.70
• 80.25
•
:
:
74.i6
:
42.02
32.16
89.60
91.16
COMPRESSIVE PROPERTIES
: 4,234
: 4,162
•.
: 4,415
: 4,287
: 4,160
Av. : 4,252
•.
•.
•.
•.
1
2
3
4
5
49.95
49.97
30.90
47.13
: 66.8o : 4,403
: 71.80 : 4,178
: 65.25 : 4,293
: 72.10 : 3,830
:
: 56.00
: 52.75
: 54.10
:
:
33.78
30.84
h Ali
-9.--
:
67.5o : 4,077
:
45.56
: 68.69 : 4,156
:
32.20
34.20
: 54.55
: 50.25
: 53.53
79.10
78.20
: 115.00
: 111.90
78.80
71.95
: 111.60
: 115.40
71.70
: 117.00
75.95
: 114.18
FLEXURAL PROPERTIES
1
: 3,889
2
: 4,072
: 4,350
: 4,340
: 4,270
Av. : 4,184
3
4
5
61.25
74.60
67.82
69.20
88.10
72.19
: 95.20
: 100.50
: 101.50
: 105.20
: 108.40
: 102.16
4,188
: 4,140
4,128
: 4,275
: 4,290
: 4,204
:
:
:
Table 14.--Short-time shear strength' of glass-reinforced
ylastic laminates used in long-term tests
Material
: Test condition
: 73° F. - :
:50 percent:
: relative :
: humidity :
1,000
:
p.s.i.
:
.
Polyester resin plus 181 glass fabric
-.
Average
Polyester resin plus glass mat
Epoxy resin plus 181 glass fabri
1,000
p.s.i.
:
16.75
17.51
:
:
15.32
14.18
14.86
16.71
14.79
10.08
10.89
9.44
9.62
9.20
10.20
10.25
9.74
•
•
.•
16.73
•.
16.81
:
18.26
:
17.47
•.
:
Average
Polyester resin plus 1000 glass fabric :
•
:
Average
:
Polyester resin plus woven roving
glass fabric
:
:
:
:
:
Average
in
water
:
15.87
11.17
12.50
12.70
11.45
Average
73° F.
17.00
18.35
17.76
17.62
16.26
17.87
17.44
17.17
14.47
-.
14.90
15.15
15.55
14.40
14.89
-.
-.
:.
13.31
14.25
13.51
15.00
•.
:
15.81
14.38
:
14.66
13.18
13.90
11.67
13.20
13.32
12.32
12.92
13.18
13.26
12.51
12.84
1
-*Johnson double shear, plane of failure parallel to warp
direction and perpendicular to plane of laminate.
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Table 30.--Summary of constants describing stress-rupture curve
T R =T -
Stresses at 10,000 hours
Material
Glass
Resin
M log t
Wet
Dry
: Dry : Wet : Dry : Wet :
• 1,000 1,000 : 1,000 : 1,000 :Percent : 1,000 :Percent : 1,000
•
p.s.i.: p.s.i.: p.s.i.: p.s.i.:
:
of
: p.s.i.:
of
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•
p.s.i.
TENSION
: 1.500 69.4 : 37.50 : 48.2 : 25.00
Epoxy
: 181 fabric
: 43.50 :
Polyester
: 181 fabric
:•3 2.56 :•2 7.70 :•1 .640 : 3.05 : 64.5 : 26.00 : 39.1 : 15.50
Polyester
: 1000 fabric
:• 2 6.65 :•2 2.50 :•1 .462 : 2.62 ; 63.2 : 20.80 : 39.7 : 12.00
Polyester
! woven roving
: 21.64 :
Polyester
! mat
: 6.40 .
Nonrigid
polTester
Epoxy
:
:
:
1
181 fabric
17.70 :
1.060 : 1.80 i 68.4 i•1 7.40 : 46.1 : 10.50
• .275 • 62.4 : 5.30 31.90 : 26.30 : 2.350 : 3.30 : 53.9 ; 22.50 ; 36.7 : 13.10
•
straight fibers ; 90.70 ; 75.20 :•3.250 ; 4.92 : 68.o : 77.70 : 60.8 :55.50
FLEXURE
Epoxy
: 181 fabric
: 56.90 : 54.70 : 3.100 : 4.750 : 62.4 : 44.50 : 51.8 :
Polyester
: 181 fabric
: 44.70 i 3 9.90 : 2.80o : 5.175 : 6o.5 : 3 3.50 : 35.5 : 19.00
Polyester
: 1000 fabric
: 39.48 ; 30.00 : 2.770 ; 3.475 ; 61.3 ; •2 8.40 : 41.6 : 16.10
Polyester
:• woven roving
: 30.88 ; 23.20 : 1.820 ; 2.400 : 64.4 : •2 3.60 : 48.1 : 13.60
35.70
•
•
; 14.40 : 11.90 ! 1.100 ; .600 ; 55.0 ; 10.00 : 61.1 ; 9.50
: mat
Polyester
Nonrigid
; 42.60 : 33.50 : 3.780 : 4.200 : 51.4 : 27.50 i 36.9 : 16.70
181 fabric
polyester
Epoxy
I
straight fibers : 94.00 : 89.5o : 2.700 : 6.05 : 81.1 ; 83.20 ; 57.1 ; 65.30
SHEAR
Epoxy
: 181 fabric
: 14.64 : 14.18 : .785 : 1.045 : 65.2 : 11.50 : 58.2 ! 10.00
Polyester
: 181 fabric
: 13.64 :
Polyester
: 1000 fabric
: 12.36 : 10.82 : .840 ; .865 ; 60.4 : 9.00 : 55.2 : 7.36
Polyester
: woven roving
: 10.90 : 9.36 : .675 ; 1.135 : 57.1 : 8.20 : 37.6 : 4.82
Polyester
: mat
:
9.30:
11.60 ;
1.055 : 1.125 ; 56.8 : 9.50 : 48.0 ! 7.10
7.82 : .450 i .830 ; 65.5 ; 7.50 : 46.2 ; 4.50
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ZM 97578 F
•
SUBJECT LISTS OF PUBLICATIONS ISSUED BY THE
FOREST PRODUCTS LABORATORY
The following are obtainable free on request from the Director, Forest
Products Laboratory, Madison 5, Wisconsin:
List of publications on
Box and Crate Construction
and Packaging Data
List of publications on
Chemistry of Wood and
Derived Products
List of publications on
Fungus Defects in Forest
Products and Decay in Trees
List of publications on
Glue, Glued Products,
and Veneer
List of publications on
Growth, Structure, and
Identification of Wood
List of publications on
Mechanical Properties and
Structural Uses of Wood
and Wood Products
Partial list of publications for
Architects, Builders,
Engineers, and Retail
Lumbermen
List of publications on
Fire Protection
List of publications on
Logging, Milling, and
Utilization of Timber
Products
List of publications on
Pulp and Paper
List of publications on
Seasoning of Wood
List of publications on
Structural Sandwich, Plastio
Laminates, and Wood-Base
Aircraft Components
List of publications on
Wood Finishing
List of publications on
Wood Preservation
Partial list of publications for
Furniture Manufacturers,
Woodworkers and Teachers of
Woodshop Practice
Note: Since Forest Products Laboratory publications are so varied in
subject no single list is issued. Instead a list is made up
for each Laboratory division. Twice a year, December 31 and
June 30, a list is made up showing new reports for the previous
six months. This is the only item sent regularly to the Laboratory's mailing list. Anyone who has asked for and received the
proper subject lists and who has,had his name placed on the
mailing list can keep up to date on Forest Products Laboratory
publications. Each subject list carries descriptions of all
other subject lists.