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. Rept. No. 2039 -3- 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. 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Ca ;..1 CO 0 •• • rO rd • -P a) m M 0 H CU 0 .41 OT 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 -. 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H-1 *** .... o........ ........ ............ 000 00oo o H ouw H s.0 H 4,4. § 11 4c.; § 4., 11 11 g -v4-v4 H 0H--IND H0 --IND H 4.+40 0 0 SM P&BPP&OT17,R2P PaP8PP,58S re 4 .P 14 lj oo lw (9t7NPIReRP.Mk -r-1̀,-1PNNA-941`^" U 0 4 •04. dA oj'.oal oj'.o al n0-4oo.ONHNo.[ HHHHHHH 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 :ultimate: :ultimate: • 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 00 0 0\ H 0• al• oo oo 00 noN 00N orcN HN HH NW • • • • • • 0 • • • • • • •• •• •• V• •• •• •• •• •• •• • • •• •• •• 00 00 0 00 b -4r-I r—I fir 00 oo 00 oH 0 '0 0 0 0 0 0 n 00 •• coo al -4N •• •-• •••• • • IV • •• •• •• •• •• •• •111 •• •• •• •• • • •• •• •• On tiTh irt 0 H 00 H 00 00 0 00 00 0 00 • • • • 0 IN F A •• ••• • •• Al •• •• •-• •••• •• •• •• 0 0 0 00 0., 0., CC\0 H CO bWr bl •• •• • 1 5-1 •• blinw •• 0O H .4.) v-i 4 0 • 0 •• o 0 0 O •I• •• C-- ii-n re) W A 0, 00 00 • • 0 0 I—r .. .. .. 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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.