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RD-Ai23 35 PROPELLANT SURVEILLANCE REPORT LGM-38 F & 6 STAGE i 1/2PHASE G SERIES I TP-H,.(U) OGDEN AIR LOGISTICS CENTERHILL AFB UT PROPELLANT ANALYSIS LA.. J A THOMPSON
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ENHEADQUARTERS
-OGDEN AIR LOGISTICS CENTER
UNITED STATES AIR FORCE
HILL AIR FORCE BASE, TEAH 84056
PROPELLANT
SURVEILLANCE REPORT
LGM-30 F&G STAGE 1
PHASE G, SERIES I
TP-H1011
PROPELLANT ANALYSIS LABORATORY
MANPA REPORT "-
* 476(82)
4A November 1982 -
APPROVED FOR PUBLIC RELEASE, DISTRIBUTION UNLIMITED
83 01 12 042'
MANPA REPORT NR 476(82)
PROPELLANT SURVEILLANCE REPORT SLGK-30F & G STAGE I (TP-HlOl1)]
AUTH9
Cminen C ustn Test Unit
Engineering & Statistical Review By
0 . SCAMBIA, Project Engineer EDWARD E ON, Math/StatService Engineering Data Analysis Unit
Recommended Approval By
LEONIDAS A. BROWN, ChiefComponent & Combustion Test Unit
-7 Approv 9B,
Propellant Analysis Laboratory
'1NOVEMBER 1982
Industrial Products and Landing Gear DivisionDirectorate of MaintenanceOgden Air Logistics CenterUnited States Air Force
Hill Air Force Base, Utah 84056
fS
ABSTRACT
This report contains propellant test results from cartons of TP-HlOll
bulk propellant representing LGM-30F and G First Stage Minuteman Motors.
This report uses a statistical approach to analyze the bulk carton pro-
pellant data. Testing was accomplished in accordance with MWRA Project rM34929C.
The data from this test period are combined with data from previous
testing and entered into the G085 Computer for storage, analysis, and
regression analysis. From the statistical analysis of all data tested
to date (sixteen years for F & G), significant degradation of the pro-
pellant does not appear likely for at least two years past the oldest
data point.
Each point on the regression plot represents the mean of all samples
at that particular age. The number of samples at each point is indicated
on the sample size summary sheet on the page accompanying each regression
plot or group of regression plots. The data range at any age can be found
by suitable inquiry of the G085 System.
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TABLE 07 CONTENTSPage
Abstract ii
List of Figures iv
List of References viii
Glossary of Terms and Abbreviations xiii
Introduction 1
Table 1 - Test Program 2
Statistical Approach 3
Test Results 5
Conclusions 9
Table 2 - Regression Sutary 10
Distribution List 118
DD1473 119
4. 5
I
LIST OF FIGURES
Figure Nr PageRegression Plot, Very Low Rate Tensile, CHS 0.002 in/win
1 Strain at Maximum Stress 15
2 Maximum Stress 16
3 Strain at Rupture 17
4 Stress at Rupture 18
5 Modulus 19
Regression Plot, Low Rate Biaxial Tensile, CHS 0.2 in/min
6 Maximum Stieess 22
7 Strain at Rupture 23
8 Stress at Rupture 24
9 Modulus 25
Regression Plot, Low Rate Tensile, CBS 2.0 in/min
10 Strain at Maximum Stress 28
11 Maximum Stress 29
12 Strain at Rupture 30
13 Stress at Rupture 31
14 Modulus 32
Regression Plot, High Rate Triaxial Tensile, 1750 in/min
15 Strain at Maximum Stress 35
16 Maximum Stress 36
17 Strain at Rupture 37
18 Modulus 38
Regression Plot, High Rate Hydrostatic Tensile, 1750 in/min
19 Strain at Maximum Stress 41
20 Maximum Stress 42
21 Strain at Rupture 4322 Stress at Rupture 44
iv
LIST OF FIGURES (cont)Figure Nr Page
23 Modulus 45
Regression Plot, Stress Relaxation, .5% Strain, -65°F
24 Modulus at 10 sec 48
25 Modulus at 50 sec 49
26 Modulus at 100 see 50
27 Modulus at 1000 sec 51
Regression Plot, Stress Relaxation, .5Z Strain, -40 F
28 Modulus at 10 sec 54
29 Modulus at 50 sec 55
30 Modulus at 100 sec 56
31 Modulus at 1000 sec 57
Regression Plot, Stress Relaxation, 3% Strain, 200F
32 Modulus at 10 sec 60
33 Modulus at 50 see 61
34 Modulus at 100 sec 62
35 Modulus at 1000 sec 63
Regression Plot, Stress Relaxation, 3% Strain, 770F
36 Modulus at 10 sec 66
37 Modulus at 50 sec 6738 Modulus at 100 se 68
39 Modulus at 1000 sec 69
Regression Plot, Stress Relaxation, 3% Strain, 100°F
40 Modulus at 10 sec 72
41 Modulus at 50 sec 73
42 Modulus at 100 sec 74
43 Modulus at 1000 sec 75
v J1
LIST OF FIGURES (cont)Figure Nr Page
Regression Plot, Stress Relaxation, 3% Strain, 1400F
44 Modulus at 10 sec 78
45 Modulus at 50 sec 79
46 Modulus at 100 sec 80
47 Modulus at 1000 sec 81
Regression Plot, Stress Relaxation, 3% Strain, 1800F
48 Modulus at 10 sec 84
49 Modulus at 50 sec 85
50 Modulus at 100 sec 86
51 Modulus at 1000 sec 87
Regression Plot, Sol Gel
52 Gel Swell Ratio 89
53 Crosslink Density 90
54 Regression Plot, Constant Strain 93
55 Regression Plot, Hardness, Shore A 96
Regression Plot, TCLE
56 TCLE Above Tg 99
57 TCLE Below Tg 100
Regression Plot, TGA
58 Ignition Temperature, 90C rise/min 102
59 % Wt. Loss at Ignition, 90C rise/min 103
Regression Plot, DTA, 120 C rise/min
60 Endotherm 1 106
61 Exotherm 1 107
62 Exotherm 2 110
63 Exotherm 3 112
vi
LIST OF FIGURES (cant)Figture Nr Page
64 Ignition Temperature 115
65 Regression Plot, Burning Rate 117
vii0
LIST OF REFERENCES
Report Nr Title Report Date
LGM-30 First Stage, wing I Test Reports
29A Test Report (Missile in silo) 13 Jan 64
29B Zero Time Test Results 29 Jan 64
29C Zero Time Test Results (Supplement 1) 30 Mar 64
29D Zero Time Test Results (Aft Closure) 9 Jun 64
29E Zero Time (Aft Closure Supplement 1) 24 Jun 64
29F ATP Phase I Test Results 30 Mar 65
29G AT? Phase I Test Results 19 Aug 65
29H ATP Phase I Test Results 10 Sep 65
32A Zero Time, Wings II-V Test Results 17 Mar 65
323 Zero Time, Wings II-V Test Results 18 Mar 65(Aft Closure)
32C ATP Phase I, Wings 11-V Test Results 3 Nov 65
49 ATP Phase I, Wings I1-V (First Group) 18 Mar 66
53 ATP Phase 1, Wings I-V (Second Group) 22 Apr 66
55 ATP Phase I, Wings 11-V (Third Group) 29 Apr 66
58 AT? Phase I, Wings 1I-V (Fourth Group) 6 May 660!
61 ATP Phase I, Wings II-V (Fifth Group) 10 Jun 66
66 ATP Phase I, Wings I-V (Sixth Group) 22 Jul 66
76 ATP Phase 1I, wing I Test iesults 24 Jan 67
78 Zero Time, Wing VI Test Results 3 Feb 67
104 ATP Phase I, wing VI (First Group 12 Oct 67
118 ATP Phase II, Wings I-V (First Group) 5 Mar 68
S!
viiiri0.
LIST OF REFERENCES (CONT)
Report Nr Title Report Date
126 ATP Phase II, wings II-V (Second Group) 11 Apr 68
130 ATP Phase II, Wings II-V (Third Group) 3 May 68
162 ATP Phase I, wing VI (Second Group) 30 Sep 69
176 ATP Phase II, Wing VI (First Group) 15 Apr 70
181 ATP Phase I1, Wing 1 7 May 70
185 ATP Phase I, Wing VI (Third Group) 22 Jun 70
195 ATP Phase III, wings II-V (Retest) 29 Oct 70
223 Surveillance Report LGM-30 Stage I Sep 71(TP-HlOll)
239 Surveillance Report LGM-30 Stage A Apr 72(TP-H1Oll and TP-U1043)
258 Surveillance Report LGM-30 A & B Stage I Nov 72(TP-H1011)
268 Surveillance Report LGM-30 A & B Stage I May 73(TP-H1 011)
271 Surveillance Report LGM-30 F & G Stage I Jul 73Phase A Series I, (TP-lO11)
277 Surveillance Report LGM-30 F & G Stage I Oct 73Phase A Series II, (TP-H1O11)
280 Surveillance Report LGM-30 A & B Stage I Nov 73(l?-H1011)
288 Propellant Surveillance Report Mar 74LGM-30 A & B, Stage I, TP-H1043
290 Propellant Surveillance Report Mar 74LGM-30 F & G, Stage I, Phase B, Series ITP-Hloll
300 Minuteman Stage I Motor May 74Reliability Improvement ProgramSurveillance
ix
*
LIST OF REFERENCES (CONT)
Report Nr Title Report Date
302 Propellant Surveillance Report LGM-30 Nov 74A & B Stage 1, TP-HlOl1
313 Stage 1 Propellant Surveillance Report, Oct 74Propellant Containing Glacial AcrylicAcid
315 Propellant Surveillance Report LGM-3( Jan 75F & G Stage 1, TP-HlOU
316 Propellant Surveillance Report LGM-3C Feb 75A & B Stage 1, TP-HlOl1
319 Propellant Surveillance Report LGM-30 Apr 75Dissected Motors, Phase VI, TP-HlOll
321 Propellant Surveillance Report LGH-30 Apr 75F & G Stage 1, Phase B, Series II,TP-HiOlI
325 Propellant Surveillance Report LGM-30 Jun 75A & B Stage 1, TP-H011
328 Propellant Surveillance Report LGM-30 Sep 75A & B Sta~e 1, TP-HlOll
330 Propellant Surveillance Report LGM-30 Oct 75F & G Stage 1, TP-HlOll
335 Stage 1 Motor Reliability Improvement Dec 75Program
337 Propellant Surveillance Report LGM-30 Feb 76A & B, Stage 1, TP-H1043
339 Stage 1, New MAPO & ERL-510 Qualification Mar 76
341 Propellant Surveillance Report LGM-30 Mar 76Dissected Motors, Phase VII, TP-H1011
*x
I
LIST OF REFERENCES (CONT)
Report Nr Title Report Date
343 Propellant Surveillance Report LGM-30 Jun 76A & B, Stage 1, TP-HIOII
345 Propellant Surveillance Report LGM-30 Jun 76F & G, Stage 1 Phase B, Series III, TP-H1011
350 Qualification of a New MAPO Source and Sep 76ERL-510 Curing Agent for Minuteman, Stage 1,UF-2121 Liner
351 Propellant Surveillance Report LGM-30 Sep 76A & B, Stage 1, TP-HlOll
354 Minuteman Stage 1 Motor Reliability Sep 76Improvement Program Surveillance
S358 Propellant Surveillance Report LGM-30 Oct 76
Dissected Motors, Phase VIII, TP-HIOll
360 Propellant Surveillance Report LGM-30 Nov 76F & G, Stage 1 Phase E, Series III, TP-HlOll
367 Propellant Surveillance Kport LGM-30 Apr 77A & B, Stage 1, TP-HIOll
370 Propellant Surveillance Report LGM-30 Apr 77F & G, Stage 1, Phase E, Series II, TP-H1011
377 Qualification of a New MAPO Source and ERL-510 Oct 77Curing Agent for Minuteman Stage 1, UF-2121 Liner
379 Final RIP Report, Minuteman Stage 1 Motor Oct 77Reliability Improvement Program Surveillance
385 Propellant Surveillance Report LGM-30 Dec 77A, B, F, & G, Stage 1, TP-H1043
388 Propellant Surveillance Report LbqM-30 A & B Jan 78Stage 1, TP-HI011
390 Propellant Surveillance Report LGM-30 F & G Feb 78Stage 1, Phase E, Series IV TP-Hl011
392 Propellant Surveillance Report LGM-30 Mar 78Dissected Moto1s, Phase IX, TP-HlOll
393 Propellant Surveillance Report LGM-30 A & B May 78
Stage I, TP-HlOll
xi
&l
LIST OF REFERENCES (CONT)
Report Nr Title Report Date
396 Propellant Surveillance Report LGM-30 F & G Jun 78Stage I, TP-HI011
405 Propellant Surveillance Report LGM-30 F & G Oct 78Stage I, TP-HlOll
406 Propellant Surveillance Report LGM-30 Nov 78Dissected Motors, Phase X, TP-HlOl
416 Propellant Surveillance Report LGM-30 F and G Apr 79Stage I, TP-HlOll
423 Propellant Surveillance Report LGM-30 F and G Oct T9Stage I, TP-HlOll
424 Propellant Surveillance Report LGM-30 Nov T9Stage I, TP-H1043
425 Propellant Surveillance Report LGM-30 A and B Nov T9Stage I, TP-HlOlI
427 Propellant Surveillance Report LGM-30 Nov 79Dissected Motors, Phase XI, TP-HlOIl
438 Propellant Surveillance Report LGM-30 F and G Apr 80Stage I, TP-H1Ol1
445 Propellant Surveillance Report LGK-30 F and G Sep 80Stage I, TP-HlOll
448 Propellant Surveillance Report LGM-30 A and B Nov 80Stage I, TP-HlOll
452 Propellant Surveillance Report LGM-30 Jan 81Dissected Motors, Phase XII, TP-HlOll
458 Propellant Surveillance Report LGM-30 F and G May 81Stage I, TP-HlOll
462 Propellant Surveillance Report LGM-30 Oct 81Stage I, TP-H1043
465 Propellant Surveillance Report LGM-30 F and G Feb 82Stage I, TP-Hl0ll
470 Propellant Surveillance Report LGM-30 May 82Dissected Motors, Phase XIII, TP-HI011
xii
4v
GLOSSARY OF TERMS AND ABBREVIATIONS
Aging Trend A change in properties or performance resultingfrom aging of material or component
CSA Cross btctional Area
1Dogbone
Degradation Gradual deterioration of properties or performance
E Modulus (psi), defined as stress divided by strainalong the initial linear portion of the curve.
EB End Bonded
EGL Effective Gage Length
em Strain at maximum stress
er Strain at rupture
"F1 ratio The ratio of the variance accounted for by theregression function to the random unexplainedvariance. The regression function having themost significant 'F' ratio is used for plottingdata. The ratio is also used in detecting signi-ficant changes in random variation betweensucceeding time points
JANNAF Joint Army, Navy, NASA, Air Force Committee
MANPA Propellant Lab Section at Ogden Air Logistics Center
Ogden ALC Ogden Air Logistics Center, Air Force LogisticsCommand
r or R The Correlation Coefficient is a measure of thedegree of closeness of the linear relationshipbetween two variables
Linear The general form of the linear regression equationRegression is Y - a + bxEquation
Regression Line representing mean test values with respectLine to time
Standard error of estimate of the regressioncoefficient
xiii
GLOSSARY OF TERMS AND ABBREVIATIONS (cont)
S. or Sy.X Standard deviation of the data about the
regression line
Sm Maximum S tress
Sr Stress at rupture
Standard Square root of varianceDeviation (Sy)
Strain Rate Crosshead speed divided by the EGL
"t" test A statistical test used to detect significantdifferences between a measured parameter and anexpected value of the parameter (determines ifregression slope differs from zero at the 95%confidence level)
Variance The sum of squares of deviations of the testresults from the mean of the series after divi-sion by one less than the total number of testresults
3 Sigma Band The area between the upper and lower 3 sigmalimit. It can be expected that 99.73% of theinventory represented by the test samples wouldfall within this range assuming that the popu-lation is normally distributed.
90-90 Band It can be stated with 90% confidence that 90% ofthe inventory represented by the test sampleswould fall within this range assuming that thepopulation is normally distributed
Significant As used in the statistical sense, means adifference unlikely to have been the result ofrandom sampling from some specified population.
xiv
INTRODUCTION
A. PURPOSE:
Laboratory testing has been performed for sixteen years on First Stage
LG-30F and G Minuteman Motor Propellant blocks to evaluate the effects of
aging on TP-HlOl1 propellant. This report contains those tests conducted
on propellant as instructed in MGRBA Test Directive GTD-1C, Amendment 2,
LGM-30 First Stage Operational Propellant Laboratory testing.
Statistical analysis of the data from tests performed will provide
early warning if serious degradation trends develop. Annual-evaluation
of the propellant provides data for input into engineering reliability
analysis for service life predictions.
B. BACKGROUND:
LGM-30F and G testing was started in 1966 with phase testing at 24 month
intervals (Report Numbers 78 - Zero time; 104, 162, 185 - Phasel; 176, 239,
257 - Phase 1I; 271 - Phase III). Report number 257 was the first time that
LGM-30F and G data were statistically analyzed separately from LGM-30 A and
B data. The present report is a continuation of testing and statistical
analysis.
Zero time testing for LGK-30 A, B, F and G was started as soon as pos-
sible after receipt of the propellant by MANPA. Data from these tests were
used to establish a baseline for each test parameter.
The LGM-30F and G propellant test matrix (Table 1) is used to determine
the number of specimens to be taken from each propellant loaf and the ape-
cific test or tests to which these specimens are to be subjected. Very low
rate and low rate tensile specimens are taken on all LGM-30F and G blocks.
Specimens for other physical and combustion tests are taken from every third
LGQ-30F and G block.K --Kl, l
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STATISTICAL APPROACH
In order to determine aging trends for shelf/service life predictions,
as directed by Service Engineering, First Stage LGM-30 F and G Minuteman
TP-HlOll propellant blocks have been undergoing testing since 1966, statis-
tically analyzed and reported on a regular test cycle by this laboratory.
The primary reason for performing statistical analysis on test data is
for the detection of propellant changes due to aging that would affect motor
reliability. Regression analysis was the method used to examine data and
to aid in drawing conclusions about dependency relationships that may exist
i.e., relationship between age versus test results.
In selecting the best fit model for the regression equation, the linear
model Y = a +bX was found to be the best fit model for the regression plots.
Individual data points from different time periods were used to estab-
lish a least squares trend line for the data. The variance about the regres-
sion line, obtained using individual values of the dependent variable, was
used to compute a tolerance interval such that at the 90% confidence level
90% of the sample distribution falls within this interval. This tolerance
interval was extrapolated to a maximum of 24 months into the future from
age of the oldest motor tested. The 't' value and the significance of this
statistic, which are reported for each regression model, give an indication
of the "statistical significance" of the slope of the trend line as compared
to a line of zero slope. When a regression slope is indicated to be signifi-
cant, it should be noted that the slope of the regression line is significant
from a statistical standpoint and it is an indication that a change over time
is occurring, but does not necessarily mean that the indicated change in the
- --
value obtained during testing is significant in regards to motor operational
performance. In a few cases, this small change has become the apparent trend
in data variance and regression line trends. However, the changes are grad-
ual and no operational problems are expected at this time.
The data were plotted by computer. The 'y' axis is computed so that the
values at one inch intervals are peculiar to the data spread of the parameter
tested. Plotted data points represent means at the particular ages at which
testing occurred. The number of specimens at each age point is indicated on
the sample size sunmary sheet accompanying the regression plot. Variance at
each test age can be determined by consulting the G085 data storage system.
A regression sumary of all test parameters is included in Table 2.
The direction of the regression trend lines are also indicated in Table 2.
The slopes that are "statistically" not significant from a line of zero
slope are labeled as such and are not included in this report.
4
-4-
TEST RESULTS
VERY LOW RATE TENSILE:
Very low rate regressions show a statistically significant decrease
for strain at maximum stress and strain at rupture. The stresses and
modulus show a statistically significant increase (Figures 1 thru 5).
The trends are gradual for the respective regressions and no operational
problems from the propellant are expected for at least two years beyond
the last test date.
LOW RATE BIAXIAL TENSILE:
The strain at maximum stress regression shows no significant trend
direction with the strain at rupture showing a statistically significant
decrease. The stresses and modulus show a statistically significant
increase (Figures 6 thru 9).
LOW RATE TENSILE:
Low rate tensile regressions show a statistically significant gradual
decrease for strains and a statistically significant increase for stresses
and modulus (Figures 10 thru 14).
HIGH RATE TRIAXIAL TENSILE:
The strain at maximum stress, strain at rupture and modulus regres-
sions show a statistically significant decrease. Maximum stress shows
a statistically significant increase. Stress at rupture shows no sig-
nificant trend direction (Figures 15 thru 18).
HIGH RATE HYDROSTATIC TENSILE:
The strains show a statistically significant decrease. The stresses
and modulus show a statistically significant increase (Figures 19 thru 23).P
" --
TEAR ENERGY:
The cohesive energy tested at 1800F and a CHS of 0.002 in/min shows
a non significant trend direction.
TENSILE SUMMARY:
The test data regressions show that the strain is gradually decreas-
ing and the stress and modulus are gradually increasing.
Based on the analysis of test data regressions, it does not appear
that meaningful degradation is occurring at this time and no operational
problems are expected in the propellant for at least two years beyond
the last data point.
STRESS RELAXATION MODULUS:
For the 0.5% strain at -650 F, the regressions for data at 10, 50, 100,
and 1000 seconds show a statistically significant increase (Figures 24
thru 27).
At -400 F, the 10, 50, and 100 second regressions show a statistically
significant increase. The 1000 second regression shows a statistically
significant decrease (Figures 28 thru 31).
The 3% strain regressions at 200F, 770F, 1000 F, 1400F, and 1800F all
show a statistically significant increase (Figures 32 thru 51).
SOL GEL:
The Z extractables and density slopes are not significant when com-
pared with a line of zero slope. The gel swell ratio and crosslink den-
sity regressios show a statistically significant increase (Figures 52
and 53).
CONSTANT STRAIN:
A statistically significant decreasing trend is shown (Figure 54).
-6-
i
HARDNESS:
Shore A 10 second hardness shows a statistically significant increas-
ing trend (figure 55).
SUMMARY OF SOL GEL, TENSILE, AND HARDNESS DATA:
The crosslink density, constant strain, and hardness data regressions
correlate well with the tensile data. As the polymer continues to cross-
link, the strains decrease and the stresses increase.
TCLE (Thermal Coefficient of Linear Expansion):
The TCLE for both above and below the glass transition point (Tg)
shows a statistically significant increasing trend (Figures 56 and 57).
TGA (Thermal Gravimetric Analysis):
A statistically significant increase is shown for the ignition tem-
perature (90C rise/min), and weight loss at ignition. No significant
0trend direction was observed for wieght loss at 250 0C hold (12 C rise/
min to hold), (Figures 58 and 59).
DTA (Differential Thermal Analysis):
The endotherm and first and second exotherms show a statistically
significant decreasing trend direction. The third exotherm and ignition
temperature shows a statistically significant increasing trend direction
(Figures 60 thru 64).
BURNING RATE:
The burning rate shows a statistically significant increasing trend
(Figure 65).
7
-7-
THERM&L AND COMBUSTION SUMMARY:
From the analyses of the regressions, no combustion problems are
expected for at least two years beyond the oldest data point.
L- 8 -
CONCLUSIONS
Sixteen years of aging at ambient temperature (770F) has not greatly
changed the properties of the propellant. Some test parameters indicate
slight aging trends, but nothing that would adversely affect the opera-
tional characteristics of the rocket motor propellant.
From the statistical analysis, it does not appear that significant
propellant degradation is occurring. Based on sixteen years of accumu-
lated data, there is no reason to suspect that properties will show much
change for at least two years past the last data point. Therefore, pro-
pellant reliability should not change appreciably over that time period.
Since failure limits are not available for the parameters tested, this
statement is based on the fact that the slope of the regression curves
where statistically significant are, with few exceptions, relatively flat
or close to a line of zero slope and have not changed appreciably from
the last test period.
-9--- -
TABLE 2
Regression Summary
Test Parameter Slope
Very Low Rate TensileStrain at Maximum StressMaximum Stress +Strain at RuptureStress at Rupture +Modulus +
Low Rate Biaxial TensileStrain at Maximum Stress NSMaximum Stress +Strain at RuptureStress at Rupture +Modulus +
Low Rate TensileStrain at Maximum StressMaximum Stress +Strain at RuptureStress at Rupture +Modulus +
High Rate Triaxial TensileStrain at Maximum StressMaximum Stress +Strain at RuptureStress at Rupture NSModulus
High Rate Hydrostatic TensileStrain at Maximum StressMaximum Stress +Strain at RuptureStress at Rupture +Modulus +
Tear Energy
Stress Relaxation-650, 10 sec +-650, 50 sec +-650, 100 sec +-650, 1000 sec +
-400, 10 sec +-400, 50 sec +-400, 100 sec +-400, 1000 sec
- 10 -
TABLE 2 (cont)
Regression SummaryTest Parameter Slope
+200, 10 sec +
+200, 50 sec +
+200, 100 sec +0+
+20 , 1000 sec +
+770 , 10 sec ++770 , 50 sec +
+770, 100 see +
+770, 1000 sec +
iI +1000, 10 sec ++1000, 50 sec ++1000, 100 sec +
+1000, 1000 sec +
+1400, 10 sec +
+1400, 50 see + F+1400, 100 sec ++1400, 1000 sec +
+1800, 10 sec ++1800, 50 sec +
+1800, 100 sec +
+1800, 1000 sec +
Sol Gel% Extractables NS
Density NS
Gel Swell Ratio +
Crosslink Density +
Constant Strain
Hardness, Shore A, 10 sec +
Pressure TimeNot tested due to equipment problems
TCLEAbove Tg +
Below Tg +
TGA Ignition Temperature +
% Weight Loss at 2500 NS
% ',eight Loss at Ignition +
-i11-
TABLE 2 (cant)
Test Parameter RersinStaySlope
DYTAEndotherm 1Exotherm 1Exotherm. 2
WEExotherm 3 +4Ignition Temperature +
Burn Rate, 1000 psi +
* NS - Not Significant-- Negative Slope
+ - Positive Slope
40
-12-
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-R123 315 PROPELLANT SURVEILLANCE REPORT LGM-30 F & G STAGE 1- 2/2PHASE G SERIES I TP-H..(U) OGDEN AIR LOGISTICS CENTERHILL AFB UT PROPELLANT ANALYSIS LA.. J A THOMPSON
UNCUISSIFIED NOV 82 NANPA-476(82) F/G 21/9.2 NL
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4|
DISTRIBUTION
NRCOPIES
OOALC!4(WRB!4 1I4WRAM 1
DDC (TISIR) Cameron Station, Alexandria, VA 22314 2
SAMSO, Norton AFB, CA 92409 1Attn: Mr. Sanford Collins, Bldg 562, Room 613
APPRO, Thiokol Chemical Corporation 2Wasatch DivisionP.O. Box 524Brigham City, UT 84302(Cy to Larry Hales)
AFRPL (PB) Edwards AFB, CA 93523 1
SAC (LGBM) ofrutt AFB, RB 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 1Applied Physics LabJohn Hopkins Road, Laurel, MD 20810Attn: Mr. Ronald D. Brown
- 118 -
* . . .-" o -- - . .' t - . . .
'1
0 [SECURITY CLASSIFICATION OF THIS PAGE ("oben Date Entered)REPORT DOCUMENTATION PAGE READ INSTRUCTIONS
BEFORE COMPLETING FORM1. REPORT NUMISR2. GOVT ACCESSION NO. S. RECIPIENT'S CATALOG NUM8ER
MANPA Report Nr. 476(82) /) , 2 3/5
4. TITLE (and Subtitle) S. TYPE OF REPORT & PERIOD COVERED
Propellant Surveillance Report Test Results - Semi AnnualLQM-30 F & G Stage I, Phase G Series 1 6. PERFORMING ORG. REPORT NUMBERTP-HlOll
7. AUTHOR(e) 8. CONTRACT OR GRANT NUMIER(,)
JOHN A. THOMPSON
9. PERFORMING ORGANIZATION NAME AND ADDRESS 10. PROGRAM ELEMENT. PROJECT. TASKPropellant Analysis Laboratory AREA A WORK UNIT NUMMERSDirectorate of Maintenance MMWA Project M34929COOALC Hill AFB, UT 84056
* ,1 CONTROLLING OFFICE NAME AND ADDRESS 12. REPORT DATEU Service Engineering Division November 1982
Directorate of Materiel Management 13. NUMBER OF PAGESOOALC Hill AFB, UT 84056 137
14. MONITORING AGENCY NAME & AODRESS(il different from Controlling Office) 15. SECURITY CLASS. (of this report)
Unclassified
ISa. DECLASSIFICATION,'DO4NGRADINGSCNEDULE
I6. DISTRIBUTION STATEMENT (of this Report)
Approved for Public Release, Distribution Unlimited
I?. DISTRIBUTION STATEMENT (of the abstract entered In Block 20, If different from Report)
18. SUPPLEMENTARY NOTES
IS. KEY WORDS (Continue on reverse side It neceery and identify by block number)
Solid PropellantMinuteman
20., STRACT (Continue an reveres side If necessery and identify by block number)This report contains propellant test results from cartons of TP-H1011 bulk
propellant representing LGM-30F & G First Stage Minuteman Motors. This reportuses a statistical approach to analyze the bulk carton propellant data. Testingwas accomplished in accordance with MMRA Project M34929C.
The data from this test period are combined with data from previous testingand entered into the G085 Computer for storage, analysis, and regression analysisFrom the statistical analysis of all data tested to date (sixteen years for F and
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G), significant degradation of the propellant does not appear likely for at
least two years past the oldest data point.Each point on the regression plot represents the mean of all samples at
that particular age. The number of samples at each point is indicated on thesample size summary sheet on the page accompanying each regression plot or group
of regression plots. The data range at any age can be found by suitable inquiryof the G085 System.
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