58-iR S LGH-38B STAGE 11 DISSECTED ROTOR TEST REPORTCU) …

58-iR S LGH-38B STAGE 11 DISSECTED ROTOR TEST REPORTCU) loAIR LOGISTICS CENTER HILL AFB UT PROPELLANT ANALYSISLAB E M OALRBA JAN 86 XAQCP-514(86)

UNCLASSIFIED F/G 2t/92 MIL

I'L 12.2

MICROCfloy 2 C) N TEST CHART

N9ATIONAL fluRCAv OF STANDARDS -1963 -

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HEADQUARTERSOGDEN AIR LOGISTICS CENTERUNITED STATES AIR FORCE

cHILL AIR FORCE BASE, UTAH 84056

I LGM-30B

STAGE II

DISSECTED

TEST REPORT

PROPELLANT ANALYSIS LABORATORY

MAQCP REPORT NR 514(86) DTIC" IELECTE

APR 1 0 1986

January 1986

APPROVED FOR PUBLIC RELEASE, DISTRIBUTION UNLIMITED

AU FILE COp '

MAQCP REPORT NR 514(86)

LGM-30B, STAGE II

DISSECTED MOTOR

TEST REPORT

Author

ELIZABETH DALABA, ChemistComponent & Combustion Test Unit

Statistical Review By

REONA CHRISTENSEN, Math/Stat.

Data Analysis Unit

Engineering Review By

BRYAN L. BELL, Project EngineerService Engineering

Approved,By

o./ / 2 / z ,tr / . A

ANTHONY J' "V'RO, ChiefPropellant Analysis Laboratory

January 1986

Prod Qlty & Reliability DivisionDirectorate of MaintenanceOgden Air Logistics CenterUnited States Air Force

Hill Air Force Base, Utah 84056

ABSTRACT

- Data analysis in this report represents three test periods on dissected

motor S/N 0022687. Two of the tests were performed prior to a change in the

specimen conditioning requirements.

A Scheffe' test was used to determine where significant differences in

test data occurred. Regressions of individual motor trends for many para-

meters are included in this report. There are statistically significant

trend lines when compared to a slope of zero except for stress relaxation

modulus. The three points used represent two populations since a change in

humidity conditioning occurred in 1985 testing. Therefore, regressions are

for visual reference only.

Multi-motor plots are included to show the relationship of motor S/N

0022687 to the other RSLP motors. The data for all Stage II dissected

motors tested at 00-ALC are shown on these plots. k_ 0 .4 , -. -

Acession For

NTIS GRA&IDTIC TABUnannoiiced ElJustifiation

Distribution/

Availability Codes

Avail and/or

Dist Special-4, !*

,_ eii

TABLE OF CONTENqTS Page

Abstract i

Ref erences vi

IntroductionI

Figure 1, Dissection Layout of Cuts3

Figure 2, Section 3 and 4 Segments Layout and Letter Identification 4

Figure 3, Specimen Cutting Plan 5

Statistical Analysis 6

Definition of Master Stress Relaxation Curve 8

Test Results 9

Conclusions and Recommendations 13

Table 1, Analysis of Variance 15

Table 2, Regression Trend Line Summary 18

Table 3, Minithin Tensile Data 19

Table 4, Analysis of Variance for Minithin Data 21

Table 5, Stress Relaxation Data 23

Table 6, Hardness Data 24

Table 7, Hardness Data Comparison 25

Table 8, Bond Properties 26

Table 9, Miscellaneous Properties 27

Figure Nr Regression Figures

4 Very Low Rate Tensile, Max Stress, Outer 28

5 Very Low-Rate Tensile, Strain at Rupture, Outer 31

6 Very Low Rate Tensile, Modulus, Outer 34

7 Low Rate Tensile, Max Stress, Outer 37

8 Low Rate Tensile, Strain at Rupture, Outer 40

9 Low Rate Tensile, Modulus, Outer 43

Figure Nr TABLE OF CONTENTS (cont) Page

10 Very Low Rate Tensile, Max Stress, Inner 46

11 Very Low Rate Tensile, Strain at Rupture, Inner 50

12 Very Low Rate Tensile, Modulus, Inner 53

13 Low Rate Tensile, Max Stress, Inner 56

14 Low Rate Tensile, Strain at Rupture, Inner 59

15 Low Rate Tensile, Modulus, Inner 62

16 Bi-Propellant, 0.0002 in/min, Max Stress 65

17 Bi-Propellant, 0.0002 in/min, Strain at Rupture 68

18 Bi-Propellant, 0.0002 in/min, Modulus 71

19 Biaxial Tensile, 0.2 in/mn, Max Stress, Outer 74

20 Biaxial Tensile, 0.2 in/min, Strain at Rupture, Outer 77

21 Biaxial Tensile, 0.2 in/min, Modulus, Outer 80

22 Biaxial Tensile, 0.2 in/min Max Stress, Inner 83

23 Biaxial Tensile, 0.2 in/min, Strain at Rupture, Inner 86

24 Biaxial Tensile, 02. in/min, Modulus, Inner 89

25 High Rate Hydrostatic Tensile, Max Stress, Outer 92

26 High Rate Hydro Tensile, Strain at Rupture, Outer 95

27 High Rate Hydrostatic Tensile, Modulus, Outer 98

28 High Rate Hydrostatic Tensile, Max Stress, Inner 101

29 High Rate Hydro Tensile, Strain at Rupture, Inner 104

30 High Rate Hydrostatic Tensile, Modulus, Inner 107

31 Minithin Tensile, Max Stress, Outer 110

32 Minithin Tensile, Strain at Max Stress, Outer il1

33 Minithin Tensile, Stress at Rupture, Outer 112

34 Minithin Tensile, Strain at Rupture, Outer 113

35 Minithin Tensile, Modulus, Outer 114

TABLE OF CONTENTS (cont)

Figure Nr Page

36 Minithin Tensile, Max Stress, Inner 115

37 Minithin Tensile, Strain at Max Stress, Inner 116

38 Minithin Tensile, Stress at Rupture, Inner 117

39 Minithin Tensile, Strain at Rupture, Inner 118

40 Minithin Tensile, Modulus, Inner 119

41 Master Stress Curve, Motor S/N 0022687, 1985, Outer 120

42 Master Stress Curve, Motor S/N 0022687, 1985, Inner 121

Regression Plot, Stress Relaxation, 3% Strain, Outer

43 Modulus at 10 seconds 122

Regression Plot, Stress Relaxation, 3% Strain, Inner

51 TCLE, Below Tg, Outer 146

52 TCLE, Above Tg, Outer 149

53 TCLE, Glass Point, Outer 152

54 TCLE, Below Tg, Inner 155

55 TCLE, Above Tg, Inner 158

56 TCLE, Glass Point, Inner 161

57 Hardness, Shore A, 10 second, Outer 164

58 Hardness, Shore A, 10 second, Inner 167

DD 1473 170

Distribution List 172

REFERENCES

Title and Report Nr Page

Ten Year Aging and Storage Program, Wings Nov 1967I Through V Minuteman Second-Stage MotorsAnd Components, Aerojet-General Report0162-01FAS-R

LGM-30 Stage II Dissected Jun 1973Motors Test Report 269(73)

LGM-30 Stage II Dissected May 1976Motors Test Report 338(76)

LGM-30 Stage II Dissected Dec 1977Motors Test Report 384(77)

LG2-30 Stage II Dissected Mar 1979Motors Test Report 414(79)

LM-30B Stage II Dissected Jul 1980Motors Test Report 443(80)

LGM-30B Stage II Dissected Jul 1982Motors Test Report 471(82)

LGM-30B Stage II Dissected Feb 1984Motors Test Report 496(84)

GLOSSARY OF ABBREVIATIONS AND TERMS

Aging Trend (Refer to Figure 3 or statistical analysis)A change in properties or performance resulting fromaging of material or component

ANX Outer propellant, ANP-2862

ANY Inner Propellant, ANP-2864

ASPC Aerojet Strategic Propulsion Company

Bi-Propellant Equal sections of ANP-2862 and ANP-2864 in one specimen

CSA Cross Sectional Area

DB Dogbone

Degradation Gradual deterioration of properties or performance

E Modulus (psi), defined as the slope of the line drawn

tangent to the initial linear portion of the curve

EB End bonded

EGL Effective Gage Length

em Strain at Maximum Stress (in/in)

er Strain at Rupture (in/in)

"F" ratio The ratio of the variance accounted for by the regressionfunction to the random unexplained variance. The regres-

sion function having the most significant "F" ratio is usedfor plotting data. The ratio is also used in detectingsignificant changes in random variation between succeedingtime points.

JANNAF Joint Army, Navy, NASA, Air Force Committee

MAQCP Propellant Laboratory at OO-ALC

OO-ALC Ogden Air Logistics Center

Regression The general form of the regression equation is Y = a + bX

Regression Line Line representing mean test values with respect to time

Sb Standard error of estimate of the regression coefficient

Se or Sy. X Standard deviation of the data about the regression line

S mMaximum Stress (psi)

GLOSSARY OF TERMS AND ABBREVIATIONS (cont)

S rStress at Rupture (psi)

Standard Square root of varianceDeviation (Sy)

Strain Rate Crosshead speed divided by the EGL

't' Test A statistical test used to detect significant differencesbetween a measured parameter and an expected value of theparameter (determines if regression slope differs fromzero at the 95% confidence level).

Variance The sum of squares of deviations of the test results fromthe mean of the series after division by one less thanthe total number of test results

3 Sigma Band The area between the upper and lower 3 sigma limit. It canbe expected that 99.73% of the inventory represented by thetest samples would fall within this range assuming that thepopulation is normally distributed

90-90 Band It can be stated with 90% confidence that 90% of the inven-tory represented by the test samples would fall within thisrange assuming that the population is normally distributed

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INTRODUCTION

PURPOSE: The purpose of this program is to continue surveillance testing

of Minuteman Reentry System Launch Program Stage Il propellant. This sur-

% veillance will elucidate the aging characteristics of the propellant and,

using statistical trends derived from laboratory testing, will help to

establish the service life expectancy of similar motors in the inventory.

BACKGROUND: Surveillance testing was initiated in 1963 on cartons of pro-

pellant cast from the same propellant used in motor manufacture.

En 1971, all laboratory prepared insulation material and case-to-pro-

pellant bond specimens were destroyed in a conditioning chamber malfunction.

The number of cartons of propellant were also near depletion, which would

have terminated the 00-ALC Surveillance Program.

A force modernization program made available some older Minuteman I

Stage II motors. In 1973, three of these motors were selected to represent

the motor inventory and were dissected for laboratory surveillance testing.

The motors selected were SIN 0022135, cast date June 1963; SIN 0022583,

cast date January 1964; and S/N 0022788, cast in July 1964. An additional

motor, S/N 0022687, cast in April 1964, became available and was dissected

in 1981 for continuing surveillance testing. The test data from Stage II

dissected motors were assumed to have a normal population that could be

combined. This was a fallacious assumption as shown in MAMPA Report Nr.

496(84) where individual regressions for each motor were made with SIN

0022687 visually displayed on the multi plots.

Motor SIN 0022687 was dissected in a different manner from other

motors. The distance between cuts B and C, and cuts C and D was increased

to 16 inches (figures 1 and 2).

Segments D, E and F from section 4 of motor S/N 0022687 were used for

testing. Figure 3 illustrates the cutting plan for the latest test period.

The general test directive (GTD-2 Dissect Amendment 2, April 1984) speci-

fied that test specimens be conditioned at controlled relative humidity.

Other changes were different test temperatures for stress relaxation, dele-

tion of some testing, and addition of mini-thin tensile from the bore area.

Motors which have been dissected to date are:

Motor SIN Cast Date

0022135 63162

0022583 64008

0022788 64197

0022687 64096

-T 410.*4

Cut BA 8.5 1a

CutC 0 24.5

0u 56.5

Cut E --

C u t F - - - s o w_

_ _ _ _ _ _ _ __70_ _

Figure 1 Dissection layout of Cuts,

Locations and Section Numibers

V v -T ---

189.50

"145.5° 0212"5°*

122.50 235.50

55.5 30325.5

-A 32 5 0 9 3 3 5

?9 .o5 0 0 0

Fizure 2 Section 3 and 4 SegmentLavout and Letter IdentLficntion

*lr 06d

1007;r1

91. I, Z1

STATISTICAL. ANALYSIS

Statistical analyses have been performed to determine what statistic-

ally significant aging trends are occurring in the propellant. Test data

for this report have been derived from the physical/chemical testing of a

Stage II dissected motor, S/N 0022687.

For this test period, analyses were made to determine: (1) what aging

trends are demonstrated for motor S/N 0022687 within three test periods

(1982, 1983 and 1985) and (2) the visual relationship between the data

from motor S/N 0022687 and data from previously dissected motors S/Ns

0022135, 0022583 and 0022788. Statistically, no direct motor-to-motor

comparisons can be made using the combined motor regressions.

At the present time, there are three data points for motor S/N 0022687

two of which were tested prior to a change in specimen conditioning. With

-. this change another variable is introduced. Furthermore, a statistical

bias is introduced when only three data points are used. Therefore, the

individual regression plots are for visual observation only. At least

two more test periods under the current test conditions will be required

before there is any stability in the data base. A summrary for the regres-

sion trend lines can be found in Table 2.

The linear regression program was used to show aging trends. The lin-

ear equation Y - a + bX was found to be the best fit model for the data in

this report. The unique mathematical regression equation is listed on the

4%~ top of each regression plot.

The multi-symbol combined plot program uses a unique plotting code for

each motor's data point on the regression plots. This type of reporting is

not reliable at this time since the motors cannot be statistically combined

as discussed in MANPA Report Nr. 496(84), February 1984. However, this

4 method of data plotting allows a visual display of the mean data from each

.4 motor and the overall relationships between dissected motors.

The data from motor S/N 0022687 were statistically compared for com-

binability using Analysis of Variance at the 5% significance level (Table

1). By comparing the mean values and variances within these values, it

was determined which data groups have a non-significant difference and

which are combinable.

The Scheffe' test determines where the significant differences lie

between data groups in the incompatability of the "F" test results, using

Analysis of Variance. The significance of these data groups may be attri-

buted, in part, to aging and random variations in testing. These varia-

tions are being investigated. The Scheffe' test was used only if the cal-

culated "F" value was significant. The Scheffe' test is fairly consistent

for the outer high rate hydrostatic tensile test, the inner stress relaxa-

tion test and for the TCLE inner and outer tests.

The Shore A hardness information consisting of conditioned and uncon-

ditioned data was statistically compared for combinability by comparing

data variations ("F" test) and mean values ('t' test). Hardness compari-

sons (Table 4) resulted in significant differences resulting from vari-

ance and mean testing. The inner, Shore A, 10 second hardness has a non-

significant difference and these data are combinable. Table 6 contains

individual hardness values.

For a comparison of minithin values between four blocks, the mean

values were checked for compatability. Table 4 contains the Analysis of

Variance results for inner and outer propellant. Individual minithin

values are found in Table 3.

DEFINITION OF THE MASTER STRESS RELAXATION CURVE

The master stress relaxation curve is a composite curve representing

the behavior of a polymer over a wide range of time and temperature rela-

tionships. From a curve constructed at a given strain level, any combi-

nation of time and temperature can be used to determine a corresponding

stress relaxation modulus.

DETERMINATION OF STRESS RELAXATION MODULUSUSING A MASTER STRESS RELAXATION CURVE

From test data at a particular strain level, a polymer's stress relax-

ation modulus corresponding to any combination of time and temperature can

4: be determined. The horizontal axis of the master stress relaxation plot is

a logarithmic value (t/aT), and the vertical axis is a linear value, E(t)

298/T, where E(t) is the stress relaxation modulus dependent on time. T

is temperature in degrees Kelvin, aT equals any relaxation time at tempera-

ture T divided by the corresponding time at the reference temperature (298

degrees Kelvin or 770F), and 't' is relaxation time in seconds. The stress

relaxation modulus for any combination of temperature and time can be deter-

mined by using the following steps:

a. For each stress relaxation plot there is associated a plot of tem-

perature in degrees F versus log aT. From this plot, determine log aT cor-* '.

responding to the temperature at which stress relaxation modulus is desired.

b. Determine log 't' or log of the desired stress relaxation time.

c. Determine log (t/aT) by using the equation:

log (t/aT) - log t - log aT.

d. Place the determined value of log (t/aT) in the horizontal axis

of the large plot and reference the master stress relaxation curve to deter-

mine the corresponding value E(t)298/T in the vertical axis.

e. Determine 298/T and divide into E(t)298T to find E(t), the stress

relaxation modulus at the desired time and temperature.

A. TEST RESULTS

INTRODUCTION:

Testing in 1985 represents the third test period for motor SIN 0022687.

This is the first time testing with specimens conditioned at controlled RH.

Consequently, the 1985 data represent a different population than earlier

testing.

A different statistical approach was used in which the means were

analyzed for the 1982, 1983 and 1985 test data. This type of analysis will

demonstrate any change between the data from the three test periods. Table

1, Analysis of Variance, shows the significance or non-significance of means.

From the table it can be seen that only a few year-to-year comparisons are

not significant in means. Stress relaxation modulus of outer propellant is

an exception.

A summary of the regression trend lines is shown ini*Tabie. 2.

A sample size summary follows the regression plot to which it applies.

Multi-motor regression plots using other dissected motor data, were

made to show the relationship of data from motor S/N 0022687 to the other

motors.

Table 3 shows the 1985 mini-thin tensile data and Table 4 is an analy-

sis of variance for this data. Table 5 lists the stress relaxation data for

all three years and shows the change in test temperatures based on the revised

GTD. Hardness data for 1985, showing changes in data caused by conditioning,

are shown in Table 6, with "F" and 't' test significance given in Table 7.

Bond pro'perties are shown in Table 8 and the miscellaneous data in Table 9.

A. UNIAXIAL TENSILE TEST:

OUITER: Very low rate tensile at 0.0002 in/mmn shows a significant

decrease in the regression trend line for maximum stress and modulus

(figures 4 and 6) with a corresponding increase in strain at rupture (fig-

ure 5). The regression trend lines for low rate tensile at 2.0 in/min

however, shows a significant increase in strain at rupture (figure 8) with

non-significant changes in the other parameters (figures 7 and 9).

INNER- Very low rate tensile shows a significant increase in the trend

line for maximum stress (figure 10). The other parameters do not show a

.44 significant trend (figures 11 and 12). At 2.0 in/min, both maximum stress

and modulus shov a significant increase in the regression trend line (fig-

ures 13 and 15). Strain at rupture does not show a trend (figure 14).

BI-PROPELLANT: Very low rate tensile shows a significant increase in

regression trend lines for all parameters (figures 16, 17 and 18).

B. BIAXIAL TENSILE TEST: Biaxial rails tested at 0.2 in/min show a sig-

nificant increase in the slope for strain at rupture (figures 20 and 23),

and a significant decreasing trend line in modulus for outer propellant

(figure 21). Inner propellant does not show a significant change in mod-

ulus (figure 24). Neither propellant shows a significant change in maximum

stress (figures 19 and 22).

C. HIGH RATE HYDROSTATIC TENSILE: Shortened dogbones are tested at 1750

in/mmn with 500 psi pressure. Under these conditions, the outer propellant

shows a significant increase in the slope for maximum stress and strain at

rupture (figures 25 and 26) with a significant decrease in the trend line

for modulus (figure 27).

Inner propellant, on the other hand, shows a significant decrease in

the slope for maximum stress and modulus (figures 28 and 30) while strain

at rupture does not show a significant change (figure 29).

* -10-

D. MINITHIN TENSILE: Minithin tensile specimens are cut from the case

and bore areas as shown in figure 3. A change in the General Test Direc-

tive stipulated certain slices to be tested, i.e., 0.*1, 0.2, 0.3, 0.6,

and 1.0 inch intervals. This was done for the inner propellant and two

blocks of outer propellant. In some instances, no valid data for these

particular specimens was obtained. 'When additional blocks from the outer

propellant were cut (blocks 4EU5 and 4E1J6), a decision was made to test all

slices so that if one point was missed the adjacent specimen would provide

useable data. No regressions were made since only current data are shown

on the plots. The influence of the liner is evident by the variability in

the first few slices adjacent to the liner (figures 31 thru 35). Bore pro-

pellant data also show variability as shown in figures 36 through 40.

Data are listed in Table 3 and analysis of variance is provided in Table 4.

E. STRESS RELAXATION: The latest General Test Directive mandated a change

in the temperatures at which the specimens were tested. Prior testing at

-65 0F and -40 0F resulted in so many bond failures that representative data

could not be obtained. Less severe temperatures of 0 0F and 40 0 F were sub-

stituted. Data are show in Table 5. The master curves for 1985 testing

are shown in figures 41 and 42. These curves appear to be quite similar to

those published in MANPA Report Nr. 496(84). There are no significant

changes in relaxation modulus for either outer or inner propellants (fig-

ures 43 thru 50).

F. THERMAL COEFFICIENT OF LINEAR EXPANSION (TCLE):

Both outer and inner propellant show a significant increasing trend

line slope for the coefficient of linear expansion above the glass transi-

tion temperature (figures 52 and 55). Neither propellant shows a significant

change in glass transition temperature (figures 53 and 56) or in expansion

below the glass transition temperature (figures 51 and 54).

G. HARDNESS: Tensile specimens were tested for hardness when the specimens

were first machined. They were then conditioned at 35 t 5% RH for 14 days

and ardessreaing wee tkenfor a second time. These data are shown in

Table 6. Statistically, there is a significant difference between the con-

ditioned and unconditioned test data except for inner propellant at 10 sec-

ond hardness readings (Table 7).

Regressions were made using unconditioned data. The outer propellant

9... shows a significant decrease in the trend line slope at 10 seconds (figure

57). There is no significant change in the inner propellant (figure 58).

H. BOND PROPERTIES:

SHEAR: Shear strength tested at 2.0 in/mmn, 500 psi does not show a

change from 1983 testing (Table 8). These specimens had the Avcoat removed

from the metal case before testing. Tensile specimens were tested at 20 in,

min and 500 psi. There is a marked difference in the two sets of data, and

the difference shown at 20 in/mmn between 1983 and 1985 is striking. There

was failure in the propellant at less than 2mm deep in five of the six

specimens with a crystalline appearance on the failed surface. This appar-

ent crystallinitv may be the result of a higher concentration of MH 4ClO4

since this surface appearance was not noticable in previous years.

CONSTANT LOAD TENSILE: The specimens showed liner to propellant failure

at high loads. As loads decreased, failure within the propellant increased.

There was a crystalline appearance to the failed surface. See Table 8.

4 I. MISCELLANEOUS PROPERTIES: Swell ratio, gel fraction and moisture were

done on specimens of insulation and liner. These specimens were obtained

from the barrel section. Data are provided in Table 9, and represent means

of two replicates.

CONCLUSIONS AND RECOMMENDATIONS

Tighter control of humidity has had an effect on the data, and may

account for the shift in means (see hardness study). This change in pre-

conditioning does not affect all tests or all parameters to the same

degree.

There are significant increases in strain at rupture in the outer pro-

pellant. If both maximum stress and modulus showed decreases of similar

magnitude, the probability of the increase being real is greater. There

is no such consistency evident at this time. Moreover, a decrease in

N strain is of greater concern than an increase because the loss of strain

capability leads to potential motor failure.

Stress relaxation testing at 77F does not show significant changes.

Shore A hardness (10 sec) readings would tend to suggest that elasticity

of the propellant is decreasing.

Inner propellant does not show the same magnitude of changes as is

suggested by the data for outer propellant.

Statistically, the distribution of variance is significant in most tests.

However, since three test periods are the minimum required for regression,

and one represents a change here, only further testing will determine if the

trend lines remain significant. At least two more test periods with the same

conditions are needed to provide a stable data base.

The relationship of motor S/N 0022687 to previously dissected motors is

ambiguous. Testing did not begin until the motor was nearly 18 years old

whereas other motors were approximately half that age when initially tested.

Therefore, no comparisons can be made at similar ages.

RECOMMENDATIONS:

Testing of this motor should be continued in order to determine if

changes in means and variance are real or if they are random.

Greater emphasis should be placed on maintaining the same test condi-

.%d tions. Elimination of some tests is understandable, but wherever possible

the program should reamin essentially the same as it presently exists.

Although the regressions show two data points from unconditioned

specimens and one from conditioned, the same general trend is observed

and the regression trend line may be correct. Therefore, it is strongly

recommended that this motor be tested as soon as possible to verify this

trend.

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TABLE 2

REGRESSION TREND LINE SUMMARY

Test Sm er E

Uniaxial Tensile, 0.0002 in/minOuter S(-) S(+) S(-)Inner S(+) NS NSBipropellant S(+) S(+) s(+)

Uniaxial Tensile, 2.0 in/minOuter NS S(+) NSInner S(+) NS S(+)

Biaxial Tensile, 0.2 in/minOuter NS S(+) S(-)Inner NS S(+) NS

High Rate Hydrostatic Tensile. 1750 in/minOuter S(+) S(+) S(-)Inner S(-) NS S(-)

Stress Relaxation, 3% Strain, 770 F 10 sec 50 sec 100 sec 1000 secOuter NS NS NS NSInner NS NS NS NS

Thermal Coefficient of Linear Expansion Below Tg Above Tg TgOuter NS S(+) NSInner NS S(+) NS

Hardness, 10 sec, UnconditionedOuter S(-)Inner NS

NS N Non-significant Difference

S(+) - Significant difference in trend line slope in the positive directionS(-) = Significant differencein trend line slope in the negative direction

- 18 -

TABLE 3

MINITHIN TENSILE DATATest Temp 77*F, Cfl5 - 1.0 in/minMotor SIN 0022687, 1985 data only

Outer Propellant

StrainSpecimen Max at Max Strain at Stress atLocation Stress Stress Rupture Rupture Modulus

4EU11 116.4 0.729 0.802 110.2 63612 120.8 0.731 0.772 116.9 61513 127.0 0.782 0.876 120.6 586A 124.2 0.707 __ 557

Block 1 Y 122.1 0.7373 0.8167 115.9 598.5S.D. 4.568 0.03175 0.05353 5.27162 34.4335N: 4 4 3 3 4

4EU21 119.8 0.712 0.775 115.3 60322 124.9 0.764 0.806 122.2 58723 126.6 0.733 0.786 122.4 58026 122.4 0.755 0.849 116.7 507

Block 2 X 123.43 0.7410 0.8040 119.15 369.25S.D. 2.9691 0.02331 0.0326 3.683 42.6019N:= 4 4 4 4 4

4EU51 98.1 0.628 0.724 92.3 75952 106.5 0.567 0.726 95.8 82253 97.2 0.522 0.665 88.7 56754 101.4 0.492 0.642 90.7 69555 102.4 0.494 0.661 89.0 63156 102.7 0.485 0.645 93.0 70457 102.2 0.486 0.614 94.0 67758 102.8 0.490 0.683 89.4 67759 100.9 0.479 0.684 85.2 693A 104.3 0.495 0.648 93.8 674B 103.9 0.491 0.643 92.5 708

Block 5 T 102.04 0.5117 0.66682 91.31 691.55S.D. 2.65114 0.04584 0.03489 3.0389 64.74313

4EU61 61.6 0.601 0.731 55.5 55862 73.8 0.532 0.649 66.3 54063 81.0 0.511 0.606 74.9 57264 89.7 0.477 0.626 79.7 66365 91.2 0.444 0.589 80.1 74166 91.0 0.444 0.595 81.3 71667 93.3 0.431 0.560 82.9 73868 95.2 0.439 0.592 83.0 73369 96.3 0.441 0.612 83.6 733A 97.2 0.429 0.617 80.5 756B 96.7 0.435 0.598 82.6 697

Block 6 X 87.91 0.4713 0.6159 77.31 677.0S.D. 11.30836 0.05504 0.44426 8.79471 81.48742

TABLE 3 (cont)

Inner Propellant

StrainSpecimen Max at Max Strain at Stress atLocation Stress Stress Rupture Rupture Modulus

4EU11 54.2 0.553 0.646 50.5 52712 55.4 0.603 0.697 52.2 39113 73.7 0.574 0.739 66.5 579A 88.8 0.416 0.590 76.9 678

Block 1 X 68.025 0.5365 0.6680 61.5250 543.75S.D. 16.4755 0.08291 0.06442 12.51196 119.553IN 4 4 4 4 4

4EU21 68.8 0.618 0.793 61.1 56722 73.7 0.604 0.823 64.3 51223 81.1 0.532 0.670 74.5 59126 87.2 0.440 0.651 74.4 665A 89.3 0.437 0.598 79.9 632

Block 2 X80.02 0.5262 0.7070 70.840 593.4S.D. 8.72737 0.08646 0.09649 7.83888 59.0449N 5 5 5 5 5

4EU32 89.6 0.439 0.601 78.0 61833 90.1 0.442 0.609 79.2 59236 88.1 0.444 0.607 77.1 651A 86.3 0.429 0.506 79.6 670

Block 3 K88.5250 0.4350 0.58075 78.4750 63.75S.D. 1.70953 0.006658 0.4995 1.14127 34.6350N = 4 4 4 4 4

4EUJ42 84.1 0.465 0.526 79.9 51243 85.2 0.467 0.665 73.2 61246 85.7 0.456 0.560 78.7 622A 79.8 0.357 0.392 76.1 576

Block 4 K 83.7 0.4362 0.53575 76.975 580.5S.D. 2.68452 0.05305 0.112624 2.97475 49.75607

sg .4 *4L

TABLE 4

ANALYSIS OF VARIANCE FOR MINITHIN DATAat The 5% Significance Level

OUTER PROPELLANTTest Nr Samples Cal F Sig of

Parameter Location Per Group Mean Std Dev Value F-Test

y Max Stress 4EU1 4 122.10 4.56804EU2 4 123.43 2.9691 33.9429 S4EU5 11 102.04 2.6511

• 4EU6 11 87.91 11.3084

Strain at 4EU1 4 0.7373 0.03175Max Stress 4EU2 4 0.7410 0.02331 57.1172 5

4EU5 11 0.5117 0.045844EU6 11 0.4713 0.05504

Strain at 4EUI 3 0.8167 0.05353Rupture 4EU2 4 0.8040 0.03260 0.6875 NS

4EU5 11 0.6668 0.34894EU6 11 0.6159 0.44426

Stress at 4EUl 3 115.90 5.27162Rupture 4EU2 4 119.15 3.68300 60.9510 54EU5 11 91.31 3.03890

4EU6 11 77.31 8.79471

Modulus 4EU1 4 598.50 34.43354EU2 4 569.25 42.6019 4.5810 54EU5 11 691.55 64.7431

* 4EU6 11 677.00 81.4874

INNER PROPELLANT

Max Stress 4EU1 4 68.025 16.47554EU2 5 80.020 8,7274 3.4647 54EU3 4 88.525 1.70954EU4 4 83.700 2.6845

Strain at 4EUI 4 0.5365 0.08291Max Stress 4EU2 5 0.5262 0.08646 2.7287 NS

4EU3 4 0.4385 0.006664EU4 4 0.4362 0.05305

Strain at 4EUI 4 0.6680 0.6442 0.4175 NS, Rupture 4EU2 5 0.7070 0.09649

4EU3 4 0.5808 0.499504EU4 4 0.53575 0.11262

Stress at 4EUl 4 61.525 12.51196Rupture 4EU2 5 70.840 7.83888 4.1371 5

4EU3 4 78.475 1.141274EU4 4 76.975 2.97475

TABLE 4 (cont)

Test Nr Samples Cal F Sig ofParameter Location Per Group Mean Std Dev Value F-Test

Modulus 4EU1 4 543.75 119.55304EU2 5 593.40 59.0449 1.0355 NS4EU3 4 632.75 34.63504EU4 4 580.50 49.7561

SS = A significant difference between the 4 means.NS - No significant difference between the 4 means.

'.** - 22 -

TABLE 5

STRESS RELAXATION DATA3% STRAIN, MEAN VALUES

OUTERTemp Year 10 sec 50 sec 100 sec 1000 secC~F) Tested (psi) _(psi)- (psi) (psi)

0 1985 3638 2015 1623 834

20 1982 1635 958 793 444I.1983 1959 1058 866--

1985 2003 1075 876 492

40 1985 992 600 506 304

77 1982 506 352 318 2421983 467 340 301 229

4.1985 531 369 328 244

120 1982 399 322 300 2451983 313 246 233 1681985 306 242 221 183

160 1982 275 229 214 1651983 337 269 248 1841985 251 203 185 139

INNiER

0 1985 3383 1881 1531 857

20 1982 1470 791 622 3421983 1567 817 661 2731985 1672 965 798 467

40 1985 955 576 474 314

77 1982 529 380 340 253-b1983 402 289 261 185

1985 480 332 297 219

120 1982 399 297 279 2201983 302 231 220 1741985 338 264 246 193

1 ~160 1982 294 253 238 1901983 268 214 201 1621985 277 228 209 166

5, 4 2."es&~- ~

TABLE 6

HARDNESS DATA, SHORE A

Motor S/N 0022687, 1985 Data

Specimen Unconditioned ConditionedLocation Initial 10 sec Initial 10 sec

*Outer 71 63 70 5974 65 70 6071 63 71 6071 60 71 60

*71 62 63 5272 62 67 5873 62 70 6072 63 71 6273 62 72 6271 61 71 6072 64 72 6173 63 71 62

X = 72.0 62.50 69.92 59.67S.D. =1.044 1.314 2.539 2.708

Inner 65 58 66 6066 57 72 6371 60 71 6271. 59 71 6072 60 70 6074 61 71 6274 65 71 6272 64 70 5664 60 66 5775 65 68 6473 62 71 6272 62 68 60

x- 70.75 61.08 69.58 60.67S.D. 3.696 2.610 2.065 2.348

TABLE 7

HARDNESS DATA COMPARISONF and t Tests

Unconditioned Conditioned ComparisonTest X N S.D. X N S.D. Results

HardnessOuter Initial 72.0 12 1.044 69.92 12 2.539 S/F

10 sec 62.50 12 1.314 59.67 12 2.708 S/F

Inner Initial 70.75 12 3.696 69.58 12 2.065 S/F10 sec 61.08 12 2.610 60.67 12 2.348 NS

NS = "F" and 't' results are not significant at the 5% significance level.S/F - "F" test results are significant.S/t = "F" test results are not significant, but the 't' test results are significant.

NOTE:The F-test compares the variance within data groups.The t-test compares the means between data groups.The t-test is not applicable when the F-test shows a significant difference.

-, - 25 -

TABLE 8

BOND PROPERTIES

Without AvcoatTest Conditions 1982 X 1983 X 1985 K

. Shear Strength, Composite (psi) 171 153.2 152.72.0 in/min, 500 psi

Tensile Strength, Composite (psi) 508 419.5 249.7P. 20 in/min, 500 psi

Constant Load Tensile @ 1 min 79.73 @ 1 min 82.69(Log Stress (psi) vs @ 10 min 51.23 @ 10 min 56.74• Log Time to Failure/min) @ 100 min 37.8 @ 100 min 32.9 @ 100 min 38.93

@ 1000 min 26.72

,j r .;.'/-' . , V%'.' '.','%,, , L . .,'." , .... j ¢ " ' ../ ,,. : .. , •. -. .- -2 6 -- '.'.',.." ,.

TABLE 9

MISCELLANEOUS PROPERTIES

Test 1982 K 1983 X 1985 X

Swell RatioInsulation 1.47 1.58 1.15Liner 2.42 2.07 2.09

Gel FractionInsulation 89.69 87.59 91.16Liner 63.33 67.52 67.93

Moisture M%Insulation 0.92 1.57 1.37

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SECURITY CLASSIFICATION OF THIS PAGE ("aien Does ntersd)

REPORT DOCUMENTATION PAGE READ INSTRUCTIONSREPORT__ DOCUMENTATIONPAGE_ BEFORE COMPLETING FORM

1. REPORT NUMBER 2. GOVT ACCESSION NO. . RECIPIENT'S CATALOG NUMBER

MAQCP REPORT NR 514(86). TITLE (and Subtitle) S. TYPE OF REPORT & PERIOD COVERED

LGM-30B, STAGE II DISSECTED MOTOR TEST REPORT Annual

6. PERFORMING ORG. REPORT NUMBER

7. AUTHOR(&) U. CONTRACT OR GRANT NUMBER(&)

ELIZABETH M. DALABA

9 9. PERFORMING ORGANIZATION NAME AND ADDRESS 10. PROGRAM ELEMENT. PROJECT, TASKAREA 6 WORK UNIT NUMBERS

2 Propellant Analysis LabDirectorate of MaintenanceH-l1 & R ITrth R~An-;1Q&Q

II. CONTROLLING OFFICE NAME AND ADDRESS 12. REPORT DATE

Service Engineering Division January 1986Directorate of Materiel Management 13. NUMBER OF PAGES

Hill AnB, Utah 84056-5149 18014. MONITORING AGENCY NAME & ADDRESS(If different from Controlllng Office) IS. SECURITY CLASS. (of this report)

Unclassified

ISa. DECLASSI FICATION/DOWNGRADINGSCHEDULE

.4w': 1. DISTRIBUTION STATEMENT (of thle Report)

Approved for Public Release Distribution Unlimited--

17. DISTRIBUTION STATEMENT (of the abetract entered In Block 20, If different from Report)-A-.

• ", Is. SUPPLEMENTARY NOTES

19. KEY WORDS (Continue on reveres aide It neceeeary nd Identify by block number)

Dissected Motor Solid PropellantMinutemanRSLP

20. ABSTRACT (Continue an reveree olde If necessary and Identify by block number)

Data analysis in this report represents three test periods on dissectedmotor S/N 0022687. Two of the tests were performed prior to a change in thespecimen conditioning requirements.

A Scheffe' test was used to determine where significant differences in testdata occurred. Regressions of individual motor trends for many parameters areincluded in this report. There are statistically significant trend lines when

DD 1 1473 - 170 -

SECURITY CLASSIFICATION OF THIS PAGE (Whien Date Entered)

• " .Wi

SECURITY CLASSIFICATION OF THIS PAGE(Whme Dote Eantored)

compared to a slope of zero except for stress relaxation modulus. The threepoints used represent two populations since a change in humidity conditioningoccurred in 1985 testing. Therefore, regressions are for visual reference only.Multi-motor plots are included to show the relationship of motor S/N0022687 to the other RSLP motors. The data for all Stage II dissected motorstested at 00-ALC are shown on these plots.

171-SECURITY CLASSIFICATION Off THIS IDAGE(Wbsa DAINa Ent..e)

DISTRIBUTION

NRCOPIES

OOLMMWR 1MMGRMP 1

DDC (TISIR) Cameron Station, Alexandria, VA 22314 2

SAMSO, Norton AFB, CA 92409 1Attn: Mr. Sanford Collins, Bldg 562, Room 613

AFPRO, Aerojet, Sacramento, CA 95813 1

N Aerojet Strategic Propulsion Company 1P. 0. Box 15699C, Sacramento, CA 95813Attn: Mr. R. Kiefer for Mr. Stan Lake

AFRPL (MKPB) Edwards AFB, CA 93523 1

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U. S. Naval Ordnance Station, Indian Head, MD 20460 1M. E. Loman, Code 3012A4Air Launched Weapons BranchWeapons Quality Engineering Center

CPIA, Johns Hopkins University 1

Applied Physics Lab* John Hopkins Road, Laurel, MD 20810

Attn: Mr. Ronald D. Brown

.4 r.rwrrv '~' rr u-s -u-~ rJrVWW ri, w- w-. - -

a ~' **~ x:.-.:-.<~ *~ - ~ y~a".,Ir%.9;~x~1

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58-iR S LGH-38B STAGE 11 DISSECTED ROTOR TEST REPORTCU) …

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