PROPELLANT SURVEI LLANCE REPORT LGM-3Q A&B STAGE 1 · 2011. 10. 11. · ABSTRACT This report...
Transcript of PROPELLANT SURVEI LLANCE REPORT LGM-3Q A&B STAGE 1 · 2011. 10. 11. · ABSTRACT This report...
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HEADQUARTERS
OGDEN AIR LOGISTICS CENTER
UNITED STATES AIR FORCE
HILL AIR FORCE BASE, UTAH 84406
PROPELLANT
SURVEI LLANCE REPORT
LGM-3Q A&B STAGE 1
PROPELLANT LAB SECTION
MANCP REPORT
NR 388(78)
JANUARY 1978
APPROVED FOR PUBLIC RELEASE, DISTRIBUTION UNLIMITED
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MANCP REPORT NR 388(78)UMEMP PROJECT M82934C-=1L25&4r
PROPELLANT SURVEILLANCE REPORT
LQI-30 A & B STAGE I
TP-H1O1l
Auth r
Component & Combustion Test Unit
Engineering & Statistical Review By
JOHN K. SCANBIA, Project Engineer ED icanService Engineering Data Analysis Unit
Recommended Approval By
RONALD F. LARSEN, Chief B ChiefPhysical & Mechanical Test Unit Component & Combustion Test Unit
Approved By
DON F. WOODS, ChiefPropellant Laboratory Section
January 1978
Industrial Products & Landing Gear DivisionDirectorate of MaintenanceOgden Air Logistics CenterUnited States Air Force
Hill Air Force Base, Utah 84406
APPROVED FOR PUBLIC RELEASE, DISTRIBUTION UNLIMITED
COPY AVAILAr!t P '" " NOTPERMIT FULY ,iii
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ABSTRACT
This report contains propellant test results from cartons of TP-Hl0I
bulk propellant representing LGM-30 A and B First Stage Minuteman Motors.
This report is the thirteenth time that a statistical approach has been used
to analyze First Stage bulk carton propellant. Testing was accomplished
in accordance with MMFMP Project M82934C-WNL17514.
The purpose of testing was to determine and provide early warning of
any serious degradation trends occurring in the propellant for service
life predictions.
An analysis of all parameters indicates that no potential problems
are expected in the propellant for at least two years past the oldest
data point.
Data stored in the G085 System were plotted utilizing the IBM 360-65
Computer and CAL-COMP Plotter. The data range at any age can be found by
suitable inquiry of the G085 System.
Each point on the regression plot represents the mean of all samples
at that particular age. The number of specimens at each point is indi-
cated on the sample size summary sheet accompanying each regression plot
or group of regression plots.
Section
Section
eS
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erTY COUD[S
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TABLE OF CONTENTS
Page
Abstract ii
List of Figures iv
List of References vii
Glossary of Terms and Abbreviations xi
Introduction 1
Table I - Test Program 3
Statistical Approach 4
Test Results 7
Conclusions 10
Distribution List 84
DD Form 1473 85
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LIST OF FIGURES
Figure Nr Page
Regression Plot, Very Low Rate Tensile
1 Strain at Maximum Stress 12
2 Maximum Stress 13
3 Strain at Rupture 14
4 Stress at Rupture 15
5 Modulus 16
Regression Plot, Low Rate Biaxial Tensile
6 Strain at Maximum Stress 18
7 Maximum Stress 19
8 Strain at Rupture 20
9 Stress at Rupture 21
10 Modulus 23
Regression Plot, Low Rate Tensile
11 Strain at Maximum Stress 25
12 Maximum Stress 26
13 Strain at Rupture 27
14 Stress at Rupture 28
15 Modulus 29
Regression Plot, High Rate Tensile
16 Strain at Maximum Stress 31
17 Maximum Stress 32
18 Strain at Rupture 33
19 Stress at Rupture 34
20 Modulus 35
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LIST OF FIGURES (CONT)
Figure Nr
Regression Plot, High Rate Triaxial Tensile
21 Strain at Maximum Stress 37
22 Maximun Stress 38
23 Strain at Rupture 39
24 Stress at Rupture 40
25 Modulus 41
Regression Plot, Stress Relaxation, 3% Strain
26 Modulus at 10 sec 43
27 Modulus at 50 sec 44
28 Modulus at 100 sec 45
29 Modulus at 1000 sec 46
Regression Plot, Stress Relaxation 5% Strain
30 Modulus at 10 sec 48
31 Modulus at 50 sec 49
32 Modulus at 100 sec 50
33 Modulus at 1000 sec 51
34 Regression Plot, Hardness, Shore A 53
Regression Plot, Dynamic Response
35 Shear Storage 200 Hz 55
36 Loss Tangent 200 Hz 56
37 Shear Storage 400 Hz 57
38 Loss Tangent 400 Hz 58
39 Regression Plot, Constant Strain 60
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LIST OF FIGURES (CONT)
Figure Nr Pafe
Regression Plot, TCLE
40 Thermal Coefficient of Linear 62Expansion Below T
g41 Thermal Coefficient of Linear 63
Expansion Above Tg
Regression Plot, Sol Gel
42 Crosslink Density 65
43 % Extractables 67
44 Weight Swell Ratio 69
Regression Plot, DTA 120C rise/mmn
45 Endotherm 71
46 First Exotherm 72
47 Second Exotherm 74
48 Third Exotherm 76
49 Ignition 78
Regression Plot, Pressure Time
50 Maximum Pressure 80
51 Time to Maximum Pressure 81
52 Regression Plot, Burning Rate 83
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I a - II I I I I I I I
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LIST OF REFERENCES
Report Nr Title Report Date
LGH-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 ATP Phase I Test Results 19 Aug 65
29H ATP Phase I Test Results 10 Sep 65
32A Zero Time, Wings I-V Test Results 17 Mar 65
32B Zero Time, Wings II-V Test Results 18 Mar 65
(Aft Closure)
32C ATP Phase I, Wings II-V Test Results 3 Nov 65
49 ATP Phase I, Wings II-V (First Group) 18 Mar 66
53 ATP Phase I, Wings II-V (Second Group) 22 Apr 66
55 ATP Phase I, wings II-V (Third Group) 29 Apr 66
58 ATP Phase I, Wings II-V (Fourth Group) 6 May 66
61 ATP Phase I, Wings II-V (Fifth Group) 10 Jun 66
66 ATP Phase I, Wings II-V (Sixth Group) 22 Jul 66
76 AT? Phase II, Wing I Test Results 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 II-V (First Group) 5 Mar 68
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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 III, Wing I 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-H1011)
239 Surveillance Report LGM-30 Stage I Apr 72(TP-HlOll and TP-I1043)
258 Surveillance Report LGM-30 A & B Stage I Nov 72(TP-H1Oll)
268 Surveillance Report LGM-30 A & B Stage I May 73
(TP-IfO1)
271 Surveillance Report LGM-30 F & G Stage I Jul 73Phase A Series II, (TP-HIOl1)
277 Surveillance Report LGM-30 F & G Stage I Oct 73
Phase A Series III, (TP-u11011)
280 Surveillance Report LGM-30 A & B Stage I Nov 73
(TP-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-HIOll
300 Minuteman Stage I Motor May 74Reliability Improvement ProgramSurveillance
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LIST OF REFERENCES (CONT)
Report Nr Title Report Date J302 Propellant Surveillance Report LGM-30 Nov 74
A & B Stage 1, TP-H10ll
313 Stage I Propellant Surveillance Report, Oct 74Propellant Containing Glacial AcrylicAcid
315 Propellant Surveillance Report LGM-30 Jan 75F & G Stage 1, TP-H1Oll
316 Propellant Surveillance Report LCM-30 Feb 75A & B Stage 1, TP-HI011
319 Propellant Surveillance Report LGM-30 Apr 75Dissected Motors, Phase VI, TP-H1011
321 Propellant Surveillance Report LGM-30 Apr 75F & G Stage 1, Phase B, Series II,TP-Hl11
325 Propellant Surveillance Report LGM-30 Jun 75A & B Stage 1, TP-HlO1l
328 Propellant Surveillance Report LGM-30 Sep 75A & B Stage 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-R1043
339 Stage 1, New MAPO & ERL-510 Qualification Mar 76
341 Propellant Surveillance Report LGM-30 Mar 76Dissected Motors, Phase VII, TP-HlOll
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LIST OF REFERENCES (CONT)
Report Nr Title Report Date
343 Propellant Surveillance Report LGM-30 Jun 76
A & B, Stage 1, TP-HlOlI
345 Propellant Surveillance Report LGM-30 Jun 76
F & G, Stage I Phase B, Series III, TP-HlOll
350 Qualification of a New MAPO Source and Sep 76
ERL-510 Curing Agent for Minuteman, Stage 1,UF-2121 Liner
351 Propellaat Surveillance Report LGM-30 Sep 76
A & B, Stage 1, TP-HlOll
354 Minuteman Stage 1 Motor Reliability Sep 76
Improvement Program Surveillanc e
358 Propellant Surveillance Report LGM-30 Oct 76
Dissected Motors, Phase VIII, TP-HlOll
360 Propellant Surveillance Report LGM-30 Nov 76"F & G, Stage 1 Phase E, Series III, TP-HlOll
367 Propellant Surveillance Report LGM-30 Apr 77
A & B, Stage 1, TP-HlOll
370 Propellant Surveillance Report LGM-30 Iay 77
F & G, Stage 1, Phase E, Series II, TP-HlOll
377 Qualification of a New MAPO Source and ERL-510 Oct 77
Curing Agent for Minuteman Stage 1, UF-2121 Liner
379 Final RIP Report, Minuteman Stage 1 Motor Oct 77
Reliability Improvement Program Surveillance
385 Propellant Surveillance Report LGM-30 Dec 77A, B, F, & G, Stage I, TP-H1043
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GLOSSARY OF TERM AND ABBREVIATIONS
Aging Trend A change in properties or performance result-ing from aging of material or component
CSA Cross Sectional Area
DB Dogbone
Degradation Gradual deterioration ot properties or performance
E Modulus (psi), defined as stress divided bystrain along the initial linear portion of thecurve.
EB End Bonded
EGL Effective Gage Length
em Strain at maximum stress
er Strain at rupture
"F" ratio The ratio of the variance accounted for by the
regression 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
MANCP 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 the degreeof closeness of the linear relationship between twovariables
Regression The general form of the regression equationEquation is Y - a + bx
Regression Line representing mean test values with respectLine to time
Sb Standard error of estimate of the regressioncoefficient
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GLOSSARY OF TERMS AND ABBREVIATIONS (cont)
Se or Sy.x Standard deviation of the data about theregression line
Sm Maximum Stress
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
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INTRODUCTION
A. PURPOSE:
Quality assurance tests have been conducted for fourteen and one half
years on First Stage LM-30A and B Minuteman Motor Propellant blocks to
evaluate the effects of aging on TP-H1011 propellant.
Statistical analysis of the tests performed, as directed by
Engineering, should provide early warning if serious degradation
trends occur. Annual evaluation of the propellant provide data
that can be directly input into engineering reliability and service
life predictions. Testing was performed in aLcurdance with MMWRM
Directive GTD-lC and GTD-IC Amendments I and 2.
B. BACKGROUND:
Testing was first accomplished at MANCP on LGM-30A TP-HlOll
propellant blocks in 1963 and was designated Zero-Time Testing
(MAGCP Report Nrs 29B, 29C and 29F). Subsequent testing was accom-
plished at approximately 24 month intervals (MAGCP Report Mrs 29G,
29H - Phase I; 76 - Phase II; 181 - Phase III).
LGM-30B Zero-Time testing was accomplished in 1964 with sub-
sequent testing at intervals of 24 months (MAGCP Report Nrs 32A-
Zero-Time; 32C, 49, 53, 55, 58, 61, 66 - Phase I: 118, 126, 130-
Phase II; 195, 268 - Phase III).
Reports prior to MAGCP Report Nr 223(72) contained raw data
using sigma relation to compare to Zero-Time variance. MANCP
Report Nr 239(72) published in April of 1972 contained all the
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data on LGM-30A, B, F and G in the GO85 System at that time.
Report Nrs 258(72), 268(73) reported LGM-30A and B data
in statistical analysis by itself. This report is the eighth
time that LGM-30A and B data have been reported in this manner.
Zero-Time testing was started as soon as possible after
receipt of the propellant by MANCP. Data from these tests were
used to establish a base line for each test to which each sub-
sequent test data (ATP - Accelerated Test Plan) were compared
in the reports listed above.
The LGM-30A and B propellant test matrix (Table 1) were used
to determine the number of specimens to be taken from each pro-
pellant loaf and the specific test or tests to which these specimens
were subjected. Low rate tensile and hardness specimens were taken
from all LGM-30A and B blocks. Specimens for other physical and
combustion tests were taken from every seventh block.
Some tests were not conducted at the earlier test periods
(0-6 years) and, therefore, data are not available for inclusion
in the regressions.
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Table 1
Test Program
The test matrix is taken from GTD-1C, Amendment 2, and the tests, conditions,number of specimens and test methods are listed below.
Per
Test Condition-i Description Cond
Hardness 10 Sec Dogbone Ends 3
Low Rate Tensile 2.0 in/min 1/2" JANNAF Dogbone 3
High Rate Tensile 1750 in/min 3/4" Dogbone 3
High Rate Triaxial 600 psi, 1750 3/4" GL Rail End Bonded 1Tensile in/min
Low Rate Biaxial 0.2 in/min 3/4" GL Rail End Bond 1Tensile
Stress Relaxation 3% & 5%" 1/2" x 1/2" x 4" EB 3
Dynamic Response 70 gm ct wt 3.3" dia x .33" disc 1
Sol Gel 1/2" x 1/2" 8
VLR 2 x 10- 3 in/min 1/2" JANNAF Dogbone 3
Ignitability 168 cal/cm 2 sec .050" wafer 3
TCLE .200" wafer 3
Pressure Time 500 psi 1/2" x 3/8" x 1" 3
Burning Rate 1000 psi .156" x .156" x 5" Strand 3
DTA 120 C Rise/min .040" wafer 3
DSC .040" wafer 3
Poisson's Ratio 770F + 20 15% .50" x .50" x 4" 6S train
Tear Energy 70°F + 20 0.1" x 1.18" x 3" 6
Failure Envelope JANNAF Dogbone 3
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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-30A and B Minuteman
Motor propellant (TP-HlOll) blocks have been under-going testing since 1963,
statistically 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, six models
were fitted to the data (see regression models at the end of this statistical
approach). The linear model Y - a + bX was found to be the best fit model
for the regressions in this report 98% of the time. The model used is shown
in the regression equation at the top of every regression plot and those
which are not linear will also be listed and discussed in the test results
section.
Individual data points from different time periods were used to estab-
lish a least squares trend line for the data. The variance about the
regression line, obtained using individual vilues of the Jependent vari-
able, was used to compute a tolerance interval such that at the 90% con-
fidence 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 odest motor tested. The 't' values and the
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significance of this statistic, which are reported for each regres-
sion model, give an indication of the 'statistical significance' of
the slope of the trend line as compared to a line of zero slope.
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 summary sheet
accompanying each regression plot or group of regression plots.
Variance at each test age can be determined by consulting the G085
data storage system.
In a few cases, a small change has become apparent in data
variance and regression trend lines. However, the changes are
gradual and no operational problems are expected at this time.
A post cure effect (propellant stabilizing after the first
year or two) has been observed on some of the early test data
(pressure time, low rate biaxial tensile, high rate tensile, and
high rate trlaxial tensile) which tended to bias and skew the pro-
jected trend lines. To overcome this factor, two methods of analy-
sis were performed: First, where possible, non-linear models were
used that would best fit the total data (pressure time (max pressure));
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second, where non-linear models did not fit the data, this early datat was
eliminated (Low Rate Biaxial, High Rate Tensile, and High Rate Triaxial).
By compensating for this post cure biasing,a more accurate aging trend
line for service life prediction is provided.
REGRESSION MODELS
Reciprocal of X Y - a + b (1/X)
Natural log of X Y - a + b (LN X)
LOG to the base 10 of X Y - a + b (LOG X)
Square Root of X Y = a - b k
Cube Root of X Y s a + b -
Linear equation Y - a + bX
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TEST RESULTS
A. TENSILE:
Regressions for very low rate tensile data show a statistically
significant decrease for strain at maximum stress and strain at rupture.
The maximum stress regression shows a statistically significant increase
with stress at rupture showing no significant change. The regression
for modulus shows a statistically significant increase. However, the
regression slopes that do show a statistically significant change are
gradual (Figures 1 thru 5).
Low rate tensile for strains and stress at rupture show a statistically
significant decrease. Maximum stress and modulus show a statistically
significant increase (Figures 6 thru 10).
For low rate biaxial tensile testing, strain at madimum stress does
not show a significant trend with strain at rupture showing a statistically
significant decrease. Maximum stress and modulus show a statistically
significant increase. There is no significant change for stress at
rupture (Figures 11 thru 15).
The high rate tensile strain at maximum stress shows a statistically
significant increase. Maximum stress, strain at rupture and stress at
rupture all show a statistically significant decrease (Figure 16 thru 20).
For triaxial tensile testing, strain at maximum stress and strain at
rupture show a statistically significant increase. Maximum stress and
stress at rupture do not show a significant change. Modulus shows a
statistically significant decrease (Figures 21 thru 25).
For all of the tensile tests, the regressions show trends that are
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gradual and no operational problems are expected in the propellant for
at least two years beyond the oldest data point.
B. STRESS RELAXATION:
Modulus at both 3% and 5% strain shows a statistically significant
increase for all time periods (Figures 26 thru 33). However, the slope
of the trend lines are gradual and no operational problems with the
propellant are expected.
C. HARDNESS:
There is a statistically significant increase in hardness data (Figure 34).
The increase in hardness correlates with the tensile testing data where the
strains, in general, show a decrease and stresses and modulus show an
increase.
D. DYNAMIC RESPONSE:
The storage shear modulus at 200 and 400 Hz show a statistically
significant decrease while the loss tangent at 200 and 400 Hz shows a
statistically significant increase (Figures 35 thru 38).
E. CONSTANT STRAIN:
Strain at rupture for constant strain does not show a significant
change (Figure 39).
F. TCLE (Thermal Coefficient of Linear Expansion):
The thermal coefficient of linear expansion below and above the glass
transition point shows a statistically significant increase (Figures 40 & 41).
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G. SOL GEL:
The cross link density shows a statistically significant increase with
a statistically significant decrease shown for percent extractables and
weight swell ratio (Figures 42 thru 44).
The increasing cross link density trend correlates well with the other
physical properties. The tensile testing shows an increase in maximum
stress and modulus with the strain decreasing. In addition, hardness is
increasing as would be expected with increased cross linking and the stress
relaxation, dynamic response and constant strain also correlates with
cross link density.
H. DTA (Differential Thermal Analysis):
For the DTA regressions the endotherm and first and second exotherms
show a statistically significant decrease. The third exotherm and ignition
temperature shows a statistically significant increase (Figures 45 thru 49).
In all cases the changes are gradual and no problems are indicated for
the propellant at this time.
I. PRESSURE TIME:
Maximum pressure shows a statistically significant decrease and the
time to maximum pressure shows a statistically significant increase
(Figures 50 and 51).
J. BURNING RATE:
The burning rate shows a statistically significant decrease (Figure 52).
This correlates with the increasing time to maximum pressure.
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CONCLUSIONS
This report includes LGM-30 A and B bulk propellant test results
presently in the G085 System and covers the past fourteen and one half
years of testing.
The test results show that under present storage conditions the
physical/mechanical and combustion properties of the propellant are
remaining relatively stable with age. This is indicated by the regression
plots where the slope of the trend line is relatively flat or close to a
line of zero slope and have not changed appreciably from the last test
period.
From the statistical analyses, all tests conducted indicate that
motor propellant reliability will not be affected for two years past
the last data point on the regression.
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-
DISTRIBUTION NRCOPIES
OOALC
MMWRE 1
MHWiRMT 1
DDC (TISIR) Cameron Station, Alexandria, VA 22314 2
SAMSO, Norton AFB, CA 92409MNNP 1
TWR Systems, Norton AFB, CA 92409Attn: Mr. J. C. Metcalf, Bldg. 523/315 1
AFPRO, Thiokol Chemical Corporation 2Wasatch DivisionP. 0. Box 524Brigham City, UT 84302
(Cy to R. E. Keating)
AFRPL (MKPB) Edwards AFB, CA 93523 1
SAC (LGMB) Offutt AFB, NB 68113 1
U. S. Naval Ordnance Station, Indian Head, MD 20640 1Attn: Dr. James H. WiegandFleet Support Dept., PropulsionSystem Development Division, Code FS7
CPIA, Johns Hopkins University IAttn: Dr. P. L. NicholsApplied Physics LaboratoryJohns Hopkins RoadLaurel, MD 20810
Naval Plant Branch Representative 1Attn Mr. David W. PrattP. 0. Box 157, Bacchus Works IMagna, UT 84044
- 84 -
-
SECURITY CLASSIFICATICN OF THiS PAGE 'Ifhr, Da. ntarad)REPOkT D0CUAMENTA7,i0N PAGE READ INSTRUCTIONS
9EFORE COMPLETING FORM
I1. REP:RT NUMBER Zr/C -1* SSION NO 3. RECIPIENT' CATALOG NUMBER
"".. -- N. PERFORMING ORG. REPORTK
i ATHOpR.Fe t . CONTRACT Oft GRANT NUMS4EIra)s. PTRFOR NG ORGANSZATuOb NAA" AND AUDRESS to. ROGRAM ELEMENT. PROJECT. TASK
Propellan Lab SecLion RE T NUM
Directorate of Maintenance MMWRI4 Project M82934C- .-OO-ALC lill AFB, Utah 8440b 154
I.. CONTROLLING e.F.C. .. .A .AORIS 12. REREPOR TRT NUTE
Service Eng :zeeri ng Division, ,; j an ;Directorate of Materian Management T. PUMBEROj PAGec -
O0-ALC Hill AFB, Utah 84406 _ :. i'i I14. MON!TORING AGENCY NAME & ACRESSif1 different row Controliing Office, 15. SECURITY CLASS. (of Ie empoet)
Unclassified
lea. tECLASSIFICATION/OOWNGRADINGI SCHEDULE
16. DISTRIBUTION STATEMENT (of thir Report)
Approved for Public kci=isC, Distribution Unlimited
17. DISTRIBUTION STATEMENT (of the abstract entered In Block 20. it different fromn Report)
16. SUPPLEMENTARY NCTFS
19. KEY WORDS (Continue on reverse side if ncepeary and Identify by block number)
Solid PropellantMinuteman
. ABSTRACT (Cotlntte ont re~Or8, - 1.i.-" Ii ncexary mid Identify by block nambpr
This report cuntaias propellanM test results from cartons of TP-HlOll bulkpropeilant representing LM-30 A and B First Stage Minuteman Motors. This reportiS the Lhirteent tilac that a statistical approach has been used to analyze FirstStage bulk carton pr ,,pfillat. Testing was accomplished in accordance with MfIDProj -ct M82934C-1,WNL17514."'he purpose of testing was to determine and provide early warning of any ser-ious degradation trends occurring in the propellant for service life predictions.
DD OH1,3 1473 EDITION OF I NOV 65 IS OBSOLETE _ 65 -SECURITY CLASSIFICATION OF THIS PAGE (Man Data
,' 3 s7
-
SECURITY CLASSIFICATION Of THIS PAOE(PWhwi Deae EteM0
(cont't)
An analysis of all parameters indicates that no potential problems areexpected in the propellant for at least two years Past the oldest data point.
Data stored in the G085 System were plotted utilizing the IBM 360-65Computer and CAL-COMP Plotter. The data range at any age can be found bysuitable inquiry of the G085 System.
Each point on the regression plot represents the mean of all samples atthat particular age. The number of specimens at each point is indicated onthe sample size sumnary sheet accompanying each regression plot or group ofregression plots.
-86-SECURITY CLASSIFICATION OF THIS PAGE(ten Data Entere1