propellant survei llance report lgm-3q a&b stage 1 · 2011. 10. 11. · abstract this report...

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

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

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

..... ....- . . . . . . . .

erTY COUD[S

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

lii

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


7 Maximum Stress 19



10 Modulus 23

Regression Plot, Low Rate Tensile


12 Maximum Stress 26



15 Modulus 29

Regression Plot, High Rate Tensile


17 Maximum Stress 32



20 Modulus 35

iv

LIST OF FIGURES (CONT)

Figure Nr

Regression Plot, High Rate Triaxial Tensile


22 Maximun Stress 38



25 Modulus 41

Regression Plot, Stress Relaxation, 3% Strain

26 Modulus at 10 sec 43




Regression Plot, Stress Relaxation 5% Strain





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

v

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

vi

I a - II I I I I I I I

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

vii

LIST OF REFERENCES (CONT)


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

viii


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

ix

LI



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

l3L

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

xi

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

xii

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

-- -

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.

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

-3-

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

-4-

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));

-5-

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

-6-

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

-7-

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).

-8

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.

-9-

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.

-10-

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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

propellant survei llance report lgm-3q a&b stage 1 · 2011. 10. 11. · abstract this report...

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