propellant surveillance report lgm-38 f stage … · 2014. 9. 27. · rd-ai23 35 propellant...

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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-OGDEN AIR LOGISTICS CENTER

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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



9 Modulus 25

Regression Plot, Low Rate Tensile, CBS 2.0 in/min


11 Maximum Stress 29



14 Modulus 32

Regression Plot, High Rate Triaxial Tensile, 1750 in/min




18 Modulus 38

Regression Plot, High Rate Hydrostatic Tensile, 1750 in/min



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


26 Modulus at 100 see 50


Regression Plot, Stress Relaxation, .5Z Strain, -40 F





Regression Plot, Stress Relaxation, 3% Strain, 200F


33 Modulus at 50 see 61





37 Modulus at 50 sec 6738 Modulus at 100 se 68


Regression Plot, Stress Relaxation, 3% Strain, 100°F





v J1

LIST OF FIGURES (cont)Figure Nr Page











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)


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

*



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



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



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

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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

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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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-117 -

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

DD , jAN72 1473 -119- _____ _________

SECURITY CLASSIFICATION Of THIS PAGE (When Dots Entered)

I . . .l--*I i mI - Ii ; ; -,

SECURITY CLASSIFICATION OF THIS PAGIMhen Data Entered)

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.

I I.

*

- 119 -

SECURITY CLASSIFICATION OF THIS PAGE(PI.Ib Data Entered)

FILMED

DIC

propellant surveillance report lgm-38 f stage … · 2014. 9. 27. · rd-ai23 35 propellant...

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