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58-iR S LGH-38B STAGE 11 DISSECTED ROTOR TEST REPORTCU) …
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58-iR S LGH-38B STAGE 11 DISSECTED ROTOR TEST REPORTCU) lo AIR LOGISTICS CENTER HILL AFB UT PROPELLANT ANALYSIS LAB E M OALRBA JAN 86 XAQCP-514(86) UNCLASSIFIED F/G 2t/92 MIL
Transcript of 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 -
* jrwhI~ ~ - ~ 's v~ ~w :cr4'
HEADQUARTERSOGDEN AIR LOGISTICS CENTERUNITED STATES AIR FORCE
cHILL AIR FORCE BASE, UTAH 84056
to
to
I LGM-30B
STAGE II
DISSECTED
MOTOR
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
.7 -a
"hr.
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
By
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
iiJi
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
iv
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
44 Modulus at 50 seconds 125
45 Modulus at 100 seconds 128
46 Modulus at 1000 seconds 131
Regression Plot, Stress Relaxation, 3% Strain, Inner
47 Modulus at 10 seconds 134
48 Modulus at 50 seconds 137
49 Modulus at 100 seconds 140
50 Modulus at 1000 seconds 143
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
v
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)
vi
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)
vii
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
4'2
-T 410.*4
Cut BA 8.5 1a
CutC 0 24.5
40.5
0u 56.5
Cut E --
C u t F - - - s o w_
_ _ _ _ _ _ _ __70_ _
Figure 1 Dissection layout of Cuts,
Locations and Section Numibers
- -3-
V v -T ---
189.50
"145.5° 0212"5°*
122.50 235.50
99. 0
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
-4-
A-o
*lr 06d
1007;r1
91. I, Z1
.4,.4
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.
-6-
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.
7
J.
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.
-8
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
-11
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.
-12-
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
-13-
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.
-14 -
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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
-19-
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
-20-
sg .4 *4L
a r
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
NOTE:
SS = A significant difference between the 4 means.NS - No significant difference between the 4 means.
.. 2
'.** - 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
-23
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
-24-
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
4',
4.
4,
-, - 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
,2
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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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169
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
SAC (LGBM) Offutt AFB, NB 68113 1
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?.'
-172-
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