DEFLAGRATiON IN PARTIAL CONFINEMENT · KA-Ill, Phase C, M-1 Propellant Tests: Defiagration in Partial Confinement 6. AUTHOR(S) Charles E. Joachim 7. PERFORMING ORGANIZATION NAME(S)

AD-A240 185 TECHNICAL REPORT 3L-91-11

1KA-Ill, PHASE C, M-1 PROPELLANT TESTS:DEFLAGRATiON IN PARTIAL CONFINEMENT

by

Charles E. Joachim

Structures Laboratory

DEPARTMENT OF THE ARMYWaterways Experiment Station, Corps of Engineers

3909 Halls Ferry Road, Vicksburg, Mississippi 39180-6199

DTICrS ELECTSEP11 1991

;;J D

July 1991-a Final Report

Approved For Public Release; Distribution Is Unlimited

91-10272

Prepared for US DoD Explosives Saiety Board,

LT Norwegian Defence Construction Service, andLABORATORY ,afety 6evit.s Organisation, Ministry of Defence, United Kingdom

)i :- !, G7 3

form ApprovedREPORT DOCUMENTATION PAGE OMB No. 0704-0188

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I July 1991 Final report4. TITLE AND SUBTITLE 5. FUNDING NUMBERS

KA-Ill, Phase C, M-1 Propellant Tests: Defiagration in PartialConfinement6. AUTHOR(S)

Charles E. Joachim

7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) 8. PERFORMING ORGANIZATIONREPORT NUMBER

USAE Waterways Experiment Station, Structures Laboratory, Technical Report3909 Halls Ferry Road, Vicksburg, MS 39180-6199 SL-91-11

9. SPONSORING / MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSORING / MONITORING

AGENCY REPORT NUMBER

US DOD Explosives Safety Board, Norwegian Defence ConstructionService, and Safety Services Organisaio,:, Ministry of Defence,United Kingdom

11. SUPPLEMENTARY NOTES

12a. DISTRIBUTION /AVAILABILITY STATEMENT 12b. DISTRIBUTION CODE

Approved for public release; distribution is unlimited

13. ABSTRACT (Maximum 200 words)

When a propellant material is stored under confined conditions, US and NATO explosives safetyregulations require that the safety hazard quantity-distance (Q-D's) used for Hazard Class 1.1 (massdetonating) explosives be applied, rather than the less restrictive Q-D's normally used for propellantsand other Class 1.3 materials. This is based on the assumption that high gas pressures produced byan accidental burning of propellant in a confined volume will cause the burning (defiagration) totransition to a detonation. To test this assumption, a series of experiments were conducted in whichincreasing amounts of propellants were ignited and burned inside a heavy concrete structure with aninternal chamber volume of 5 m3. Pressure and temperatures were measured inside the chamber, in aconnecting exhaust vent, and in the free field beyond the exhaust vent pipe. Although there was noevidence that a detonation occurred, the high gas pressures produced by burning of the largestpropellent charge (250 kg) were sufficient to fail the structure.

14. SUBJECT TERMS 15. NUMBER OF PAGES

Deflagration/detonation Munitions storage 143M-1 propellant Propellant bum 16. PRICE CODE

17. SECURITY CLASS!FICATION 18. SECURITY CLASSIFICATION 19. SECURITY CLASSIFICATION 20. LIMITATION OF ABSTRACTOF REPORT OF THIS PAGE OF ABSTRACT

UNCLASSIFIED UNCLASSIFIED I INSN 7540-01-280-5500 Standard Form 298 (Rev 2-89)

Prescrbed by ANSI St Z39-18298-102

PREFACE

The KA-III Test Program was a series of explosive tests conducted as a

follow-on to the Defense Nuclear Agency's (DNA) MISERS COLD EVENT (June 1989).

The KA-III, Phase A and B tests were jointly sponsored by DNA and the

Norwegian Defence Construction Service, and subjected several Norwegian

structures previously tested on MISERS COLD to detonation effects of fuel-air

explosives (FAE), conventional bombs, and bigh explosive charges. The KA-III,

Phase C Test Program was sponsored by the US Department of Defense Explosives

Safety Board (DDESB), the Norwegian Defence Constructicn S.r.. 'NDCOS, ,iLd

the Safety Services Organisation (SSO) of the Ministry of Defence, United

Kingdom.

The KA-III Test Program was conducted on the DNA's MISERS GOLD Test Bed

at the White Sands Missile Range. LCDR W. F. Taylor was the DNA Test Director

and Mr. R. !. Flory, Washington Research Center, was Program Coordinator. The

DDESB, NDCS, and SSO Technical Monitors for Phase C were Dr. C. E. Canada,

Mr. Arnfinn Jenssen, and Dr. N. J. M. Rees, respectively.

The KA-III, Phase C, propellant burn study was performed by the

Explosion Effects Division (EED), Structures Laboratory (SL), US Army Engineer

Waterways Experiment Station (WES). Mr. Charles E. Joachim, EED, was Project

Manager and is the author of this report. The work was performed under the

general supervision of Mr. L. K. Davis, Chief, EED, and Mr. Bryant Mather,

Chief, SL. Field support was provided by Messrs. D. P. Hale, EED, and W. W.

Tennant, WES Engineering and Construction Services Division. Messrs. J. W.

Johnson and D. P. Biggs, WES Instrumentation Services Division, provided

timing and firing and instrumentation support for the field tests. Messrs. R.

Edgar and R. Campbell, Ballistec Systems, Inc., Quebec, Canada provided

digital recording and final data plots of all transducer-time histories.

COL Larry B. Fulton, EN, was the Commander and Director of WES, and

Dr. Robert W. Whalin was the Technical Director. Accczioo ror

NTIS CV. -ID , O iL '2

J -, U. a 3 iAv*1.i

CONTENTS

Page

PREFACE....................................i

LIST OF FIGURES................................iv

LIST OF TABLES................................xi

CONVERSION FACTORS, SI (METRIC) TO NON-SI UNITS OF MEASUREMENT . . . . xii

SECTION 1 INTRODUCTION............................1

1.1 BACKGROUND AND REQUIREMENT ........................ 1

1.2 OBJECTIVES................................2

SECTION 2 TEST PROCEDURES..........................3

2.1 GENERAL APPROACH.............................3

2.2 TEST STRUCTURE..............................3

2.3 PROPELLANT DESCRIPTION ......................... 4

2.4 ARMING AND FIRING............................5

2.5 INSTRUMENTATION.............................6

2.6 VIDEO COVERAGE..............................7

SECTION 3 TEST RESULTS............................8

3.1 INSTRUMENTATION PERFORMANCE ........................ 8

3.2 RESULTS OF TEST C-i (10-kg Charge) .................... 8

3.3 RESULTS OF TEST C-2 (25-kg Charge) .................... 9

3.4 RESULTS OF TEST C-3 (100-kg Charge) .................. 10

3.5 RESULTS OF TEST C-4 (250-kg Charge) .................. 11

SECTION 4 ANALYSIS OF RESULTS.......................13

SECTION 5 CONCLUSIONS...........................15

SECTION 6 RECOMMENDATIONS.........................16

REFERENCES.................................17

ii

CONTENTS (Continued)

Page

APPENDIX Al TEST C-I, 10-kg M-1 PROPELLANT BURN,DATA-TIME HISTORIES ...... ................... . 56

APPENDIX A2 TEST C-2, 25-kg M-1 PROPELLANT BURN,DATA-TIME HISTORIES . . . . . . . . . . . . . . . . . . . 72

APPENDIX A3 TEST C-3, 100-kg M-1 PROPELLANT BURN,DATA-TIME HISTORIES . . . . . . . . . . . . . . . . . . . 91

APPENDIX A4 TEST C-4, 250-kg M-1 PROPELLANT BURN,DATA-TIME HISTORIES ...... ................... . 109

iii

LIST CF FIGURES

Page

1. MISERS GOLD test site location ...... .................. .. 18

2. Vertical cross-section of horn antenna bunker with vent pipeattached. The M-l propellant charge was placed in a cardboardbox for Tests C-l, C-2, and C-3 and poured directly on thebunker floor for Test C-4 ....... .................... 19

3. Test C-2 charge (25 kg of M-1 propellant) placed in a cardboard

box on the floor of the bunker with booster (electric matchsurrounded by 50 gm of pistol powder) laid on the top surface ofthe charge ........... ............................ 20

4. Test C-3 charge (100 kg of M-1 propellant) placed in fourcardboard boxes taped together, with booster laid on the surfaceof the charge .......... .......................... . 20

5. Chamber pressure gage mount (ABII80) directly below vent pipe.Note: accelerometer mounting bracket (lower left) was left over

from M.iSERS GOLD EVENT ........ ...................... . 21

6. Water filled cylinder with five pressure gages. Note pipe with900 elbow connecting the cylinder to the interior of horn antenna

bunker ........... ............................ 21

7. Vent pipe with one free-field, side-on overpressure gage(ABEl73). Cables are seen for two internal vent pipe

transducers: thermal flux gage (TF192, left) and side-onoverpressure gage (ABEl72) ....... .................... . 22

8. Instrumentation layout (plan view) showing internal and externaltransducer locations. Five pressure gages were attached to thewater filled cylinder which was connected to the chamber via theair-filled pipe (upper left corner of drawing) .. .......... . 23

9. Recording bunker protecting digital recording system. A shallowcable ditch can be seen running (left to center background) fromthe recording bunker to the horn antenna bunker . ......... .. 24

10. Plan view of external airblast instrumentation and photo marker

locations ........... ............................ 25

11. Test C-1: length of exhaust gas plume (from end of vent pipe) asa function of relative time. Zero-time was not recorded, so alltimes are relative to an arbitrarily chosen start time ...... . 26

12. Test C-1: measured peak pressures as a function of distance fromthe center of the 10-kg M-1 propellant charge .. .......... . 27

iv

LIST OF FIGURES (Continued)

Page

13. Test C-i: tIerral flux at mid-length in the vent pipe (Gage

Tf!91) versus the differential of measured temperature (Gage

THCI7 0) wi1i respect to time. Each data point represents a *"pair" of values; an x-value from a given dT/dt, and a y-value

from the thermal flux record corresponding to the same timeinstant .after zero time) as the dT/dt value .. ........... . 28

14. Test C-l: calculated pseudo-thermal flux (from temperaturemeasurements of Gage THCI90) in the bunker chamber compared to

measured thermal flux-time histories in the vent pipe (GagesTF191 and TF192) .......... ......................... .. 29

15. Test G-2: length of exhaust gas plume (from end of vent pipe) as

a function of relative time. Zero-time was not recorded, so alltimes are L"iaLive to an arbitrarily chosen start time ...... .. 30

16. Test C-2: measured peak pressures as a function of distance from

the center of the 25-kg M-1 propellant charge .. .......... . 31

17. Test C-2: thermal flux at mid-length in the vent pipe (Gage

TFl91) versus the differential of measured temperature (GageTHCI90) with respect to time. Each data point represents a"pair" of values; an x-value from a given dT/dt, and a y-value

from the thermal flux record corresponding to the same time

instant (after zero time) as the dT/dt value .. ........... . 32

18. Test C-2: calculated pseudo-thermal flux (from temperature

measurement of (Gage THCI90) in the bunker chamber compared to

measured themal flux-time histories in the vent pipe (Gages

(TFl91 and TF192) ......... ........................ . 33

19. Test C-3: length of exhaust gas plume (from end of vent pipe) asa function of relative time. Zero-time was not recorded so all

times are relative to an arbitrarily chosen start time ...... .. 34

20. Test C-3: measured peak pressures as a function of distance fromthe center of the 100-kg M-1 propellant charge .. .......... . 35

21. Test C-3: thermal flux at mid-length in the vent pipe (Gage

TFl91) versus the differential of measured temperature (GageTHCI90) with respect to time. Each data point represents a"pair" of values; an x-value from a given dT/dt, and a y-value

from the thermal flux record corresponding to the same time

instant (after zero time) as the dT/dt value .. ........... . 36

V


Page

22. Test C-3: calculated pseudo-thermal flux (from temperaturemeasurement of (Gage THCl90) in the bunker chamber compared to

measured themal flux-time histories in the vent pipe (Gages

(TFI91 and TF192) ......... ........................ 37

23. Test C-4: length of exhaust gas plume (from end of vent pipe) asa function of relative time. Zero-time was not recorded so alltimes are relative to an arbitrarily chosen start time ...... .. 38

24. Test C-4: measured peak pressure as a function of distance from

the center of the 250-kg M-1 propellant charge .. .......... . 39

25. Peak overpressure versus distance from the center of the M-1propellant charge, KA-III, Phase C ..... ................ . 40

26. Peak chamber pressure versus M-1 propellant loading density,KA-III, Phase C; comparison with previous data from BRL testswith one and three ignition points of propellant charge ..... 41

27. Peak overpressure at end of vent pipe versus chamber loadingdensity; KA-III, Phase C ....... ..................... . 42

28. Peak total free-field pressure versus distance from the center of

the M-1 propellant charge, KA-III, Phase C ... ............ . 43

29. Peak thermal flux versus distance from the center of the M-1

propellant charge; KA-III, Phase C. Note: chamber thermal fluxdata Are calculated from thermocouple measurements ......... .. 44

30. Peak thermal flux versus M-1 propellant loading density, KA-III,

Phase C .............. ............................ 45

31. Peak chamber temperature versus loading density, KA-III, Phase C;comparison with previous data from BRL model test with one and

three ignition points of propellant charge ...... ............ 46

Al-l. Test C-l, airblast overpressure-time history at mid-length

inside the vent pipe, Gage ABEl71 .... ............... . 57

Al-2. Test C-l, airblast overpressure-time history at the exteriorend of the vent pipe, Gage ABEl72 .... ............... .. 58

Al-3. Test C-l, free-field airblast overpressure-time history at

0.3-m from the end of vent pipe, Gage ABEl73 .. .......... . 59

AI-4. Test C-1, free-field airblast overpressure-time history at

0.9-m from the end of the vent pipe, Gage ABEl74 ......... .. 60

vi


Page

Al-5. Test C-l, free-field airblast overpressure-time history at

2.1-m from end of vent pipe, Gage ABEl75 ... ............ . 61

Al-6. Test C-I, free-field airblast overpressure-time history at4.5-m from end of vent pipe, Gage ABEl76 .. ........... . 62

Al-7. Test C-l, free-field airblast total pressure-time history at2.1-m from end of vent pipe, Gage ABEl78 .. ........... . 63

Al-8. Test C-i, chamber airblast pressure-time history, Gage ABI180 64

Al-9. Test C-i, chamber airblast pressure-time history, Gage ABI182 65

Al-lO. Test C-l, chamber (water filled cylinder) airblast

pressure-time history, Gage ABI184 .... .............. . 66

Al-ll. Test C-1, chamber (water filled cylinder) airblastpressure-time history, Gage ABI185 .... .............. . 67

Al-12. Test C-I, chamber (water filled cylinder) airblastpressure-time history, Gage ABI187 .... .............. . 68

Al-13. Test C-l, chamber temperature, Gage THC190 .. .......... . 69

Al-14. Test C-l, thermal flux-time history at mid-length inside thevent pipe, Gage ABE191 ........... .................... /0

Al-15. Test C-1, thermal flux-time history at the extprio-r end ofthe vent pipe, Gage ABEl92 ...... .................. 71

A2-1. Test C-2, airblast overpressure-time history at mid-length

inside the vent pipe, Gage ABEl71 .... ............... . 73

A2-2. Test C-2, airblast overpressure-time history at the exteriorend of the vent pipe, uage ABZI72 .... ............. 74

A2-3. Test C-2, free-field airblast overpressure-time history at0.3-m from the end of vent pipe, Gage ABEl73 .. .......... . 75

A2-4. Test C-2, free-field airblast overpressure-time history at

0.9-m from the end of the vent pipe, Gage ABEl74 ......... .. 76

A2-5. Test C-2, free-field airblast overpressure-time history at2.1-m from end of vent pipe, Gage ABEl75 ... ............ . 77



vii


P;ige

A2-7. Test C-2, free-field airblast total pressure time- histrorv N'

0.9-m from end of vent pipe, Cage ABF177 .. ..... . .

A2-8. Test C-2, free-field airblast total pressutep-tim hivrnv,

2.1-m from end of vent pipe, Gage ABE8 ........... . 0

A2-9. Test C-2, chamber airblast pressure-time histni\, ,npe AWO 81

A2-10. Test C-2 chamber airblast pressure-time histoiv, Gage IBTPI+Y 82

A2-11. Test C-2, chamber airblast pressure-time histor-, Coge :\.1 83

A2-12. Test C-2, chamber airblast pressure-t-imp histov, -,w 9\:. 44

A2-13. Test C-2, chamber (water filled cylinder) airhlot:

pressure-time history, Gage ABI185 .................... 85

A2-14. Test C-2, chamber (water filled cylinder) airblint

pressure-time history, Cage ABI186 .................. 86

A2-15. Test C-2, chamber (water filled cylinder) airhlot,pressure-time history, Gage ABI187 .. .......... .

A2-16. Test C-2, chamber temperature, Gage THG1CO . . 88

A2-17. Test C-2, thermal flux-time history at mid-length inqidp :u cvent pipe, Gage TF191 ........ .................. 89

A2-18. Test C-2, thermal flux-time history at the oleyioy eld ot

the vent pipe, Gage TF192 ......... ................ 90

A3-1. Test C-3, airblast overpressure-time hist ,i v :i m d lene'l

inside the vent pipe, Gage ABE7I1 . . . .

A3-2. Test C-3, airblast overpressure-time histn,'v at Ac V.:;riv,

end of the vent pipe, Gage ABE172 . .. .. 03

A3-3. Test C-3, free-field airblast overpregsure-t e h h ,ov a!0.3-m from the end of vent pipe, Gage AF17I 91:4

A3-4. Test C-3, free-field airblast overpressura-tim: , nte w

0.9-m from the end of thp vent pipe, Gag,. 17. 95

A3-5. Test C-3, free-field airblast overpressurv- 1> i hsi: .t2.1-m from end of vent pipe, Gage AE1l75 .. Q

A3-6. Test C-3, free-field airblast o''erp r s ui :< hjw v ,>

4 5-m from end of vent pipe, Cage A PF1. 97

viii


Page

A3-7. Test C-3, free-field airblast total pressure-time history at

2.1-m from end of vent pipe, Gage ABEHl78 .. ........... . 98

A3-8. Test C-3, chamber airblast pressure-time history, Gage ABII80 99

A3-9. Test C-3, chamber airblast pressure-time history, Gage ABI181B 100

A3-10. Test C-3, chamber airblast pressure-time history, Gage ABI182 101

A3-11. Test C-3, chamber (water filled cylinder) airblastpressure-time history, Gage ABI185 .... .............. . 102


A3-13. Test C-3, chamber (water filled cylinder) airblast




A3-15. Test C-3, chamber temperature, Gage THC190 .. .......... 106

A3-16. Test C-3, thermal flux-time history at mid-length inside thevent pipe, Gage TFi91 ....... ..................... . 107

A3-17. Test C-3, thermal flux-time history at the exterior end ofthe vent pipe, Gage TF192 ...... ................... .. 108

A4-1. Test C-4, a4 blast overpressure-time history at mid-length

inside the vent pipe, Gage ABEl71 ....... ............... 110

A4-2. Test C-4, airblast overpressure-time history at the exteriorend of the vent pipe, Gage ABEl72 .... ............... . i

A4-3. Test C-4, free-field airblast overpressure-time history at0.3-m from the end of vent pipe, Gage ABEl73 .. .......... . 112

A4-4. Test C-4, free-field airblast overpressure-time history at0.9-m from the end of the vent pipe, Gage ABEl74 ......... .. 113

A4-5. Test C-4, tree-field airblast overpressure-time history at




ix

LIST OF FIGURES (Concluded)

Page

A4-7. Test C-4, free-field airblast total pressure-time history at

0.9-m from end of vent pipe, Gage ABPH177 .. ........... . 116

A4-8. Test C-4, chamber airblast pressure-time history, Gage ABII80 117

A4-9. Test C-4, chamber airblast pressure-time history, Gage ABI181B 118

A4-10. Test C-4, chamber airblast pressure-time history, Gage ABI182 119

A4-11. Test C-4, cbamber airblast pressure-time history, Gage ABI183T 120








A4-16. Test C-4, chamber temperature, Gage THC190 .. .......... . 125

A4-17. Test C-4, thermal flux-time history at mid-length inside the

vent pipe, Gage TF191 ....... ..................... . 126

A4-18. Test C-4, thermal flux-time history at the exterior end of

the vent pipe, Gage TF192 ...... ................... .. 127

x

LIST OF TABLES

Page

1. KA-III, Phase C: Configuration larameters for M-1 PropellantCharges ........... ............................ 47

2. Test C-I (Loading Density 2 kg/m3): Pre-Test Gage Location andDigital System Set-up Data ....... .................... .. 48

3. Test C-2 (Loading Density 5 kg/m3): Pre-Test Gage Location andDigital System Set-up Data ....... .................... .. 49



6. Test C-I (Loading Density 2 kg/m3): Gage Location and Peak

Measured Data .......... .......................... . 52

7. Test C-2 (Loading Density 5 kg/m3): Gage Location and Peak

Measured Data .......... .......................... . 53

8. Test C-3 (Loading Density 20 kg/'m3): Gage Location and PeakMeasured Data .......... .......................... . 54

9. Test C-4 (Loading Density 50 kg/m3 ): Gage Location and PeakMeasured Date ... . ...... .......................... 55

xi

CONVERSION FACTORS, SI (METRIC) TO NON-SIUNITS OF MEASUREMENT

SI (Metric) units of measurement used in this report can be converted toNon-SI units as follows:

Divide By To Obtain

calories per square centimeter-second 0.2712459 BTU per square foot-seconds

cubic metres 0.02831685 cubic feet

degrees Celsius* 1.8 C + 32 degrees Fahrenheit

kilograms 0.45359237 pound (mass)

kilograms per cubic metre 16.01846 pounds (mass) per cubic foot

kilopascals 6.894757 pounds (force) per square inch

metres 0.3048 feet

square metres 0.9290304 square feet

* To obtain Fahrenheit (F) temperature readings from Celsius (C) readings,

use the following formula: F - 1.8 C + 32. To obtain kelvin (K)readings, use: K - C + 273.14.

xii

KA-III, PHASE CM-1 PROPELLANT TESTS: DEFLAGRATION IN PARTIAL CONFINEMENT

SECTION 1

INTRODUCTION

1.1 BACKGROUND AND REQUIREMENT

In order to maintain a satisfactory level of combat readiness, the armed

forces of NATO nations must store large amounts of ammunition and propellant

for artillery and naval guns. Ammunition usually contains high explosives

that are classified as Class 1.1 explosion hazards by US and NATO guidelines,

due to the fact that they will "mass detonate"; i.e., an accidental explosion

of a single round will sympathetically detonate the entire mass of ammo rounds

in close proximity. Consequently, large separation distances, or "Quantity

Distances (Q-D's)," are required between a given quantity of stored ammunition

and other magazines (or other ammo storage or explosive operations areas),

inhabited buildings, public traffic routes, etc.

Under most conditions, propellants may burn, but they will not mass

detonate. They are therefore designated as Hazard Class 1.3 materials, and

are subject to much less restriction and have much smaller Q-D's than 1.1

materials. The theory exists, however, that if propellant is stored in a

chamber or other confined area, an accidental fire could quickly ignite the

propellant mass and rapidly produce a large volume of combustion gases.

Because this rapid buildup of gases can only vent through the relatively small

entrance into the chamber, the chamber becomes highly pressurized. The theory

postulates that such high pressures can cause the deflagration of the

propellant to transition to a detonation. Consequently, propellant stored

under confined conditions must be classified as a mass-detonating explosive,

or Hazard Class 1.1, instead of 1.3. This, in turn, requires much larger

"buffer zones", or Quantity-Distance (Q-D) separations between magazines,

inhabited buildings, public traffic routes, etc.

1.2 OBJECTIVES

The objective of the Phase C tests was to determine the combination of

confinement pressure and loading density required for M-1 propellant to

transition from deflagration to detonation, in the event of an accidental

1

fire. The tests also measured the temperatures, thermal flux and internal andexternal pressures generated by the deflagration of the various propellant

loading densities.

2

SECTION 2

TEST PROCEDURES

2.1 GENERAL APPROACH

Following the MISERS GOLD explosion test (1 June 1989) at White Sands

Missile Range, NM, several relatively undamaged, full-scale structures were

available for further testing at the MISERS GOLD site (Fig-ure 1). The KA-III

Test Series was developed to exploit these structures in an extensive program

of tests to evaluate the detonation effects of conventional (l.e., non-

nuclear) munitions. Phase C of the KA-III Series was planned to consist of up

to five deflagration and/or detonation tests, using M-1 propellant, inside a

small concrete bunker. The Phase C plan called for increasing the propellant

loading density with each successive test (loading densities of 2, 5, 20, 50

and 100 kg/m3)* until either (a) a transition from burning to a detonation

occured, or (b) the structure failed from the buildup of internal pressures.

The test program would be terminated at either point.

2.2 TEST STRUCTURE

The test structure, known as the Horn Antenna Bunker (MISERS GOLD

Structure #6410G), had internal dimensions of 1.4 m (side-to-side), 1.9 m

(front-to-back) and 1.9 m (height). The reinforced concrete walls, roof, and

floor of the structure were 30 cm thick. For the KA-III-C tests, the bunker

was modified by the addition of a vent tube welded into the observation port

opening, and by strengthening of the access hatch to resist internal pressures

from the propellant burn tests. The vent tube cross-sectional area was

selected to simulate the chamber and access tunnel proportions of the Shallow

Underground Tunnel/Chamber Explosion Test conducted at China Lake, CA, in

1988. The chamber and access tunnel at China Lake had the following

dimensions (volume, cross-sectional area and length):

Chamber: V. - 331.2 m 3 Tunnel: Vt - 132.5 m 3

Ac - 18.4 m2 At - 5.3 m2

LC - 18 m Lt - 25 m

• A table of factors for converting SI (metric) units of measurement to non-SI

units is presented on page xii.

3

The volume of the Horn Antenna Bunker (Vb) was 5 m3. If the vent area ratio

(vent area/chamber volume) of the China Lake facility is applied to the bunker

test design, then

At/VC - 5.3/331.2 - 0.016, A,/Vb - 0.016,

A, - 0.016 x 5.0 - 0.08 M 2.

A steel pipe was selected whose diameter gave a vent area closest to this

value. The pipe was 35.6 cm (14 in.) in diameter, with an extra heavy

(12.7 mm, or 0.50 in.) wall thickness. With an inside diameter of 33.02 cm

(13 in.), this pipe provided a vent area of:

A, - 3.1416 x (33.02/2)2 - 0.0857 m2 .

For the tunnel and vent pipe, the following ratios apply:

nIn/It - (Av/At) 112

The length of pipe required was computed from this ratio as:

L.,L t (At/At)"12 = 25 (0.0857/5.3)1/2 - 3.18 m.

The Horn Antenna Bunker with vent tube attached is shown in plan view in

Figure 2.

2.3 PROPELLANT DESCRIPTION

The M-1 propellant used in the Phase C test program was demilitarized

material obtained from the US Army Armament, Munitions and Chemical Command's

Rock Island (Illinois) Arsenal (stock number 1376-451-2881). It was shipped

to the White Sands Missile Range in metal-lined, wooden containers (type M-24)

with a stated propellant weight of 64 kg in each canister. The actual

propellant weight in each canister was found to average approximately 45 kg.

The propellant grains were examined at WES under an electron microscope, and

average dimensions were obtained. The propellant grain was cylindrical, with

a single perforation (a perforation is a hole through the entire length of the

4

grain cylinder). The grains were nominally 5 mm long, with a 1.1-mm outside

diameter, a 0.5-mm inside diameter, and, a 0.36 mm WEB (web thickness).

Shipping labels indicated the material was all from Lot No. RAD 69214.

For Tescs C-I - C-3, the M-1 propellant charge was placed in a cardboard

box at the center of the chamber floor (Figure 3). For Test C-3, four boxes

were taped together, as shown in Figure 4. The individual boxes were 4.92 cm

wide, 6.50 cx. long, and 4.92 cm deep. For Test C-4, the propellant was poured

onto the floor, forming an approximately conical shape. Charge weight,

volume, and surface area data for each test are given in Table 1.

2.4 ARMING AND FIRING

Atlas electric matches were used to initiate all M-1 propellant burns.

The match was placed in a plastic bag along with a booster charge of 50 grams

of smokeless pistol powder to assure ignition. The electric match lead wires

were connected to separate leads of a 4-conductor shielded cable which exited

the bunker through a cable grommet installed in the hatcn cover. The firing

line was approximately 200 m long, running from the bunker to a sandbagged

junction box containing a 12-volt battery and a single-pole, double-throw

relay. The shorted side of the relay was connected to the cable from the

electric match, and the other side to the test event control system.

All tests were computer controlled from North Park Bunker #1. The event

controller provided relay signals to start the Digistar digital system at

T-100 msec. A closure at T-0 msec (zero-time) switched the firing line from

short to 12 volts, which initiated the electric match. After the deflagration

and/or detonation was complete, the firing control unit was disconnected from

the firing line and the test area inspected for possible hazards by a reentry

team consisting of the WES blaster, WES Project Officer, and DNA Site Safety

Officer. When no visual signs of internal burning were evident, the bunker

was approached from the rear and a hand-held, digital, temperature meter was

attached to the thermocouple cable to monitor the temperature inside the

bunker chamber. The hatch cover was reopened when the temperature monitor

indicated that the internal temperature had fallen below 130°F. A ventilrtion

duct, connected to an exhaust fan, was then placed inside the chamber through

the open hatch to exhaust fumes from the chamber. When gas sampling indicated

5

that the carbon dioxide content of the interior was safe, personnel were then

allowed to reenter the bunker for cleanup and instrumentation work.

2.5 INSTRUMENTATION

Instrumentation for all Phase C tests included four flush-mounted

airblast pressure gages on the interior bunker walls. Two pressure gages were

mounted on the center of the side wall (right side as observed from outside

through the vent pipe); one at a height of 63 cm and the other at 1.27 cm.

The other two internal gages were mounted at the center (mid-height and

mid-width) of the front (under the vent pipe, Figure 5) and rear walls. The

pressure gages were placed in mounts that were glueti with epoxy into holes

drilled through the bunker concrete wall. These gage mounts included a metal

baffle system and nylon bushings to protect the airblast gages from direct

heating by the burning propellant.

Five additional airblast gages were mounted on a water-filled cylinder

which was connected to the bunker interior through an air-filled steel vent

pipe, 12.7 mm in diameter (inside) and 2.8 m long. The pipe penetrated the

chamber wall at the upper rear corner of the chamber (wall on right side),

with the other end connected to the water-filled cylinder through a 90° elbow

(Figure 6). The vent pipe was instrumented at two internal points for

side-on airblast and thermal flux measurements. Four additional side-on

airblast pressure gages were installed on the ground surface outside the

bunker along the extended vent pipe centerline to measure side-on

overpressure, and two total-pressure probe gage mounts were placed along the

extended centerline of the vent pipe. The vent pipe, with the first of the

four free-field, side-on overpressure gages, is shown in Figure 7. The

temperature inside the bunker during the propellant burns was monitored with a

Type K thermocouple, mounted in the hatch cover. Gage locations are shown in

Figure 8. Gage types, locations, and predicted peak values are given in

Tables 2 through 5.

Kulite Model HKS-375 series pressure gages were used in all locations

where predicted peak pressures exceeded 1.5 MPa. Kulite XT-190 Series gages

were used for lower pressures. Thermal flux measurements were made with

Medtherm Model #64-250SB-17 heat flux transducers. These gages use a

6

Schmidt-Buelter thermopile with a capacity of 250 BTU/ft2-sec, with an

over-range capability of 150%. Bunker temperatures during propellant burns

were monitored with Medtherm Model TC-K1212UP thermocouples. These gages use

a Type K Chromel/Alumel junction. Temperatures were digitally recorded during

the burns.

Transducer analog signals were digitized and recorded by Ballistech

Systems, Incorporated (BSI) using their Digistar II digital system. The

transducer signals were transmitted to the recording bunker (Figure 9) on

4-conductor, shielded cable (approximately 200 m long) with a floating ground.

Each channel was electrically calibrated at the digitizer by the equivalent

voltage method. The digital records were field processed for quick-look data

assessments. BSI provided final, filtered time-history plots at a later date.

These plots akL presented in Appendix Al through A4.

2.6 VIDEO COVERAGE

A VHS video camera was used to obtain visual data on the external effects

of the propellant burn. The camera was positioned to provide coverage of the

bunker, vent tube and a region approximately 25 m to the front of the vent

tube. The video camera was started just prior to each test and ran unat-

tended. There was no visual zero time indicator. Photo markers were emplaced

on both sides of the extended vent tube centerline to provide reference points

from which to estimate flame spread and other visual effects. The markers

were 61-cm square plywood sheets, attached to 10-cm square posts and painted

with alternating 30-cm black and white squares. Photo marker locations are

shown in Figure 10.

7

SECTION 3

TEST RESULTS

3.1 INSTRUMENTATION PERFORMANCE

Because preshot predictions of the peak overpressure levels expected in

the bunker from the propellant burns were too high, a number of gages failed

to record useful records on Tests C-1 and C-2. Of the 20 data channels on

Test C-i, eight produced good quantitative data, eight produced records useful

for a qualitative analysis, and four produced no data. On Test C-2, seven

channels provided good quantitative data, ten produced qualitative

information, and two had no data. Nineteen channels were operational on

Tests C-3 and C-4, with 15 providing gcod records on C-3 and 11 on C-4. One

channel was overdriven on Test C-3, and seven on C-4, but these still produced

useful qualitative information.

For all tests, the data was digitized at a rate of one sample per

220 micro-seconds, which gave a nominal recording time of 60 seconds on each

channel.

3.2 RESULTS OF TEST C-1 (10-kg Charge)

The initial visual indication of the internal M-1 propellant burn was

black smoke that was projected some 3 meters beyond the end of the vent pipe.

The smoke quickly changed to flame and, by 4 seconds after (assumed)

initiation, the flame extended approximately 5 meters from the end of the

pipe. Total duration of the external flame was approximately 11 seconds. The

position of the fire plume is plotted versus time in Figure 10. Since the

video does not have a zero (initiation) time indicator, an arbitrary start

time was assumed. As shown in Figure 11, the initial gas flow out the vent

pipe had a velocity of 3.47 m/sec. Although not seen in the video, an orange

vapor or smoke persisted more than an hour after burning ceased, seeping out

through the antenna port, vent pipe and around the imperfectly-sealed hatch

cover.

Measured peak pressure data are presented in Table 6. Peak side-on

overpressures (Figure 12) produced by the burning of the 10-kg M-1 propellant

charge were very low. Pressures beyond the vent pipe were higher than the

8

very low transducer signals indicated for the overpressure inside the bunker.

This fact suggests that uncombusted gas and propellant was carried outside and

secondary burning occurred in the vented gas plume. When the bunker was

reentered, the propellant charge container (cardboard box) was charred but not

destroyed, indicating a lack of sufficient oxygen during deflagration. The

video record shows the presence of a pulsing flame in the gas plume released

through the vent pipe. Herrera (1984) reports that, in an earlier study, un-

burned propellant was transported outside a similar test structure in a plume

with overpressures on the order of 1.6 kPa.

The temperature history recorded by the thermocouple inside the bunker on

Test C-1 was differentiated with respect to time by computing the slope

between digitized data points. This yielded a value, "dT/dt", for each time

interval sampled. In Figure 13, the different dT/dt values obtained from the

thermocouple record have been matched with the thermal flux levels recorded

for the same time intervals, at the mid-point of the vent pipe, by Gage TFI91.

These "pairs" of dT/dt and thermocouple readings are used as x and y values

for the data points shown in Figure 12. A linear least squares fit to the

data in Figure 12 therefore relates the temperature time differential to the

thermal flux. Although the thermocouple (Gage THCI90), located in the bunker

hatch cover directly above the burning propellant, was separated from the

thermal flux transducer by a distance of 2.55 m, this curve provides a crude

method for relating temperature to a "pseudo"-thermal flux. Applying the

relation shown in Figure 12, a pseudo-thermal flux-time history was calculated

from the temperature history (Gage (THC190). The calculated pseudo-thermal

flux for the chamber is compared with the measured flux in the vent pipe

(Gages TF191 and TF192) in Figure 14. As shown here, the calculated and

measured data are in good agreement.


The initial visual indication of the M-1 propellant burn inside the

bunker for Test C-2 was a glowing plume projected some 3 meters beyond the end

of the vent pipe, within approximately one second after initiation. The plume

of smoke and flame quickly extended, reaching a length of 10 m after

approximately 10 seconds. The position of the leading edge of the plume is

plotted versus time i Figure 15. As shown in the figure, the initial plumc

9

velocity was 3.13 m/sec. Although it continued to burn violently, the length

of the plume decreased after 10 seconds, retreating to the end of the vent

pipe. Total duration of the external gas plume was approximately 18 seconds.

The orange residual vapor observed after Test C-1 was not present after

burning of the Test C-2 propellant charge had ceased.

Measured peak pressure and thermal flux data are presented in Table 7.

Peak side-on overpressures (Figure 16) produced inside the bunker by the

burning of the 25-kg propellant charge were very low. Although the peak

external overpressures were approximately 20 percent higher for Event C-2 than

for Event C-l, the results still indicated that uncombusted gas and unburned

propellant were carried outside by the gas plume for external burning. Once

again, when the bunker was reentered, the propellant charge container

(cardboard box) was charred but not destroyed, indicating a deficiency of

oxygen during deflagration. The video recording again showed the presence of

a pulsing flame in the gas plume released through the vent pipe.

As was done for Test C-l, the temperature history recorded by the thermo-

couple on Test C-2 was differentiated with respect to time (dT/dt) by comput-

ing the slope between digitized data points. Thermal flux values recorded at

the mid-point of the vent pipe (Gage TFI91) are plotted versus dT/dt in

Figure 16. An "eyeball" fit was made to the data through the point

(dT/dt) - 0 and Q - 3.459 cal/m2-sec. Applying the relation shown in

Figure 17, a pseudo thermal flux-time history was calculated from the tempera-

ture history. The calculated pseudo-thermal flux for the chamber is compared

with the measured flux in the vent pipe (Gages TF191 ano TF192) in Figure 18.

As shown here, the calculated and measured data are in good agreement.


The initial visual indication of the propellant burn in Test C-3 was a

smoke plume projected some 1.5 meters beyond the end of the vent pipe within

approximately in 0.2 seconds. The plume of smoke and flame reached a length

of 16 m in approximately 6 seconds. The position of the leading edge of the

plume is plotted versus an arbiLtaLy Linik itk Figure 19. As shown in

Figure 18, the initial plume velocity was 5.58 m/sec, which was slightly

higher than seen on the first two experiments. Although it continued to burn

10

violently, the length of the plume began to decrease after 6 seconds,

retreating towards the end of the vent pipe. At approximately 11 seconds, a

violent gas exhaust was noted, which had an estimated velocity of 29.5 m/sec

and a duration of about one second. This sudden jet ripped up clods of earth

from the ground surface, throwing them into the air at velocities approaching

11 m/sec. The total duration of the external gas plume , including the late

jetting phenomena, was approximately 12 seconds. The orange residual vapor

observed after Test C-1 was again observed after burning of the Test C-3

propellant charge ceased, although it did not persist once ventilation of the

bunker was begun.

Measured peak pressure and thermal data are presented in Table 8. Peak

side-on overpressures (Figure 20) produced by the burning of the 100-kg

propellant charge were still low compared to predictions. The data presented

in Figure 19 show a consistent trend of decreased side-on overpressure with

distance from the center of the bunker. The attenuation rate increases beyond

the end of the vent pipe, where the jet was allowed to expand in three

dimensions. The results still indicated that uncombusted gas and unburned

propellant are carried outside by the gas plume for external burning. Once

again, when the bunker was reentered, the propellant charge container

(cardboard box) was found to be charred but not destroyed, indicating a

deficiency of surplus oxygen during deflagration. The video recording showed

the presence of a pulsing flame in the gas plume released through the vent

pipe.

Thermal flux values recorded at the mid-point of the vent pipe (Gage

TFI91) were again matched with dT/dt values from the thermocouple gage,as

shown in Figure 21. An eyeball-fitted line was forced through the point

(dT/dt) = 0 and Q = 3.459 cal/m 2-sec. The calculated pseudo-thermal flux

(Gage THCI90) for the chamber is compared with the measured flux in the vent

pipe (Gages TF191 and TF192) in Figure 22. As shown here, the calculated and

measured data are in good agreement. All three time-histories show the pres-

ence of a later peak at about 15 seconds after initiation. This peak occurs

in the vent pipe first, indicating movement back into the chamber from the

free-field outside the bunker. This is postulated to be an indication of

reignition of hot gages, progressing from the exterior back into the bunker.

11


The initial visual indication of the propellant burn for Test C-4 was a

smoke plune projected some 1.3 meters beyond the end of the vent pipe within

approximately in 0.3 seconds. The plume of smoke and flame quickly extended

from the vent, filling the video field of view (a distance greater than 25 m)

in approximately 5.3 seconds. The position of the leading edge of the plume

is plotted versus an arbitrary time in Figure 23. The initial plume velocity

was 3.88 m/sec, which is slightly higher than seen on the first two ex-

periments but less than that measured from Test C-3. Shortly afterwards (at

approximately 6 sec), the structure failed, releasing all internal pressure in

the process. The remaining unburned propellant then burned rapidly in the

oxygen-rich outside air.

In Test C-4, the Horn Antenna Bunker clearly failed from excess internal

pressure. Visual observation of the post-test structure showed that the

concrete bond to the reinforcing rods had failed, and the rods were pulled out

of the concrete. Only a small number of rods showed necked-down sections

characteristic of tensile failure of the steel. At the time of failure, the

hatch cover and roof section were hurled high into the air. The video record

shows the hatch cover, although tumbling, moving with an average velocity

upward velocity of 33.3 m/sec shortly after failure. Similarly, the roof

section moved upward at an average velocity of 11.4 m/sec.

Measured peak pressure and thermal data for Test C-4 are presented in

Table 9. Peak side-on overpressures (Figure 24) produced by the burning of

the 250-kg propellant charge were the highest measured in this test series,

but still seemed relatively low by weapons effects standards. The data

presented in Figure 24 shows a consistent trend of decreasing side-on

overpressure with distance from the center of the bunker. The attenuation

rate increases beyond the end of the vent pipe, where the jet was allowed to

expand i~n three dimensions.

12

SECTION 4

ANALYSIS OF RESULTS

The peak overpressures measured in the Phase C tests are plotted versus

distance from the center of the burn chamber in Figure 25. Least squares fit

lines are shown for Tests C-1 and C-3 (vent tube and free-field data).

Average peak pressures are plotted in Figure 25 for the overpressure

measurements in the chamber and water-filled cylinder. The measured peak

chamber pressures are plotted versus the chamber loading densities in

Figure 26.

The Ballistic Research Laboratories (BRL) conducted a series of

experiments modeling the KA-Ill/Phase C experiments prior to the actual tests.

The model chamber was 25.4 cm in diameter by 184 cm long, with a volume of

93180 cm3 (0.93 M3). The vent tube was 10 cm in diameter by 257 cm long, with

a volume of 2047 cm3. Venting was further restricted at the chamber/tube

interface by a 5.1 cm diameter opening. The BRL data (unpublished) is shown

for comparison in Figure 26. A significant difference is seen in the model

results between experiments using one-point ignition and three-point ignition.

The additional ignition points increased the energy release rate, which

apparently increased the measured peak overpressures. As seen in Figure 26,

the model and prototype results from experiments using one-point ignition are

in good agreement.

The pressures measured at the end of the vent pipe for each test are

plotted versus loading density in Figure 27. Peak exit pressure increases as

the loading density to the 1.653 power, for loading densities grelter than

5 kg/m 3. For loading densities below 5 kg/m3, the relatively large chamber

volume appears to inhibit the exit pressures.

Figure 28 is a plot of peak total pressure versus distance from the

center of the M-i propellant charge. Total-pressure gages were positioned

outside the bunker along the extended vent pipe centerline to measure jetting

effects. The side-on pressure gage located at the same range as the

successful total-pressure measurement (Gage ABEl78) on Test C-3 was

over-driven, indicating an overpressure in excess of 70 kPa. For Test C-4,

the side-on pressure gage at the same 0.9 m location as the total-pressure

13

gage recorded a peak of 34.5 kPa, which appears to be abnormally low when

compared to the data trend. Therefore, these total-pressure measurements

indicate that jetting is not a significant problem compared to the fire and

gas plume hazards outside the vent tube.

Figure 29 gives a comparison of thermal flux versus distance from the

center of M-1 propellant charge. Chamber thermal flux is calculated from the

thermocouple records. The thermocouple was located beneath the bunker hatch

cover, directly above the charge. This distance was approximately 1.5 m above

the charge surface. The thermal flux measurements from Test C-4 were

over-driven, so the actual peak data are somewhat greater. The peak thermal

flux data in Figure 29 shows the effects of loading density and distance from

the source. Thermal flux increased with increasing propellant loading density

and, at any particular loading density, the flux decreased with distance.

Thermal flux is plotted versus loading density in Figure 30. The

calculated chamber thermal flux indicates that the energy release increased in

almost linear proportion to the propellant loading density. The vent pipe

measurements show a two-slope relation, with a lower flux gradient at lower

loading densities (< 5 kg/m3). At greater loading densities, the curve

essentially parallels the thermal flux-loading density relation for the

chamber.

Chamber temperature is plotted versus propellant loading density in

Figure 31. Temperature data from the BRL model tests are included in

Figure 31 for comparison. The KA-III chamber temperature measurements were

made at the the mocouple location; i.e., beneath the bunker hatch cover

directly above the center of the propellant charge. Thermocouples for the BRL

model experiments were located at the chamber wall. As shown in Figure 31,

the number of ignition points influenced peak chamber temperature. The model

test data also indicates an increase in temperature with loading density.

This trend is not seen in the KA-III data.

14

SECTION 5

CONCLUSIONS

While the peak overpressures measured during the KA-Ill/Phase C

experiments were relatively low, these experiments demonstrate that a serious

flame and gas venting problem exists in front of a storage chamber exit. The

catastrophic failure of the bunker roof from Test C-4 indicates that

structural failure may occur, releasing the gas pressures from a propellant

burn before the internal pressures can build enough to cause a transition from

a deflagration to a detonation.

The pressures generated are a direct function of the loading density. It

is suggested that, when M-I propellant is stored in underground facilities

with sufficient overburden to prevent cover venting, an accidental burn will

produce far greater overpressures at loading densities above 50 kg/m3 than was

indicated by the KA-II/Phase C Tests. Rupture of the bunker roof

substantially reduced the pressures generated by Test C-4.

Chamber overpressures are also a function of the number of burn ignition

points. The BRL model tests demonstrated that higher pressures are generated

when more than one ignition point is used. Exit pressures are a function of

chamber volume, below a loading density of 5 kg/m3 . The test data indicates a

similar volume relation exists for thermal flux at loading densities below

5 kg/m3. The peak chamber temperatures measured in the KA-Ill/Phase C tests

were essentially constant, irrespective of loading density.

15

SECTION 6

RECOMMENDATIONS

Additional testing should be done to investigate the effect of gas

pressures from propellant burns in underground storage situations where cover

rupture will not occur. These tests should include a measurement system to

collect data on heat release rate (related to the change in mass of the

unburned propellant with respect to time) of the propellant burn. This

quantity is proportional to the product of the burn rate and propellant

surface area. These data are required to fully assess the influence of the

surface burn area on the deflagration gas pressures generated.

16

REFERENCES

Herrera, William R., Vargas, Luis M., Bowles, Patricia M., Baker, Dr. WilfredE., "A Study of Fire Hazards from Combustible Ammunition, Effects of Scale andConfinement (Phase II)," Final Report, December 1984, Southwest ResearchInstitute, San Antonio, Texas 78284

Zardos, Steve; unpublished data (personal communication), US Army LaboratoryCommand, Ballistic Research Laboratory, Aberdeen Proving Ground, Maryland21005-5066

17

PERMANENT HIGH EXPLOSIVE TEST SITE

IUP LAUNCHERE XPERIMENT

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18

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19

Figure 3. Test C-2 charge (25 kg of M-l propellant) placedin a cardboard box on the floor of bunker withbooster (electric match surrounded by 50 gm ofp~stol powder) laid on the surface of the charge.

Figue /* T~t . 3har (100 kg, ot M-1 propellant) placed

n tom- c ardbilard boxes t aped t oget her , with11OStt or Ilaid on the surface of the charge.

20

S ti ' 3. (h~mLbc, p- pre,-re j e runt (ABI 180) directlv

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Figure 7. Vent pipe with one free-field, side-onoverpressure gage (ABEl73). Cables are seen

for two internal vent pipe transducers; thermalflux gage (TF192, left) and side-on overpressure

gage (ABEl72).

22

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8TEST C-12 kg/m3

M-1 PROPELLAINT

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Figure Ii. Test C-I: length of exhaust gas plume (from end of ventpipe) as a function of relative time. Zero-time was notrecorded, so all times are relative to an arbitrarilychosen start time.

26

i0 3 -

TEST C-i 1O~ ~ 2kg/n3 II

m-i1 PROPELLANT

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10 0 Fre-ielda Water-Filed Cylinder

0-11 10DISTANCE, m

Figure 12. Test C-i: measured peak pressures as a function ofdistance from the center of the 10-kg M-i propellantcharge.

27

TEST C-idT/dt - DIFFERENTIAL OF CHAMBER TEMPERATURE (THC190)

30 q - THERMAL FLUX (TF191), cal/rn-sec0

25

Eq = 0.2604 (dT/dt) + 3.459

0

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40 -20 0 20 40 60 80 100dT/dt

Figure 13. Test C-i: thermal flux at mid-length in the vent pipe(Gage TF1l9) versus the differential of measuredtemperature (Gage THCl90) with respect to time. Each datapoint represents a "pair" of values; an x-value from agiven dT/dt, and a y-value from the thermal flux recordcorresponding to the same time instant (after zero time)as the dT/dt value.

28

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29

12 TEST C-2

5 kg/m3

N-1 PROPELLANT

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O2 0 4 6 8 10 12 14 16 1 20

TIME, secFigure 15. Test C-2: length of exhaust gas plume (from end of vent

pipe) as a function of relative time. Zero-time was notrecorded, so all times are relative to an arbitrarilychosen start time.

30

10 I I

TEST C-2 I I5 5kg/m3 I

M-1 PROPELLANT 1 0

: .I I

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DISTANCE, rmFigure 16. Test C-2: measured peak pressures as a function of

distance from the center of the 25-kg M-1 propellantcharge.

31

m • • l n i m mu n n l

50

q = 0.6090 (dT/dt) + 3.459

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q -THERMAL FLUX (TF1 91 ), cal/ma-sec

dT/dt

Figure 17. Test C-2: thermal flux at mid-length in the vent pipe(Gage TF19l) versus the differential of measuredtemperature (Gage THCl90) with respect to time. Each datapoint represents a "pair" of values; an x-value from agiven dT/dt, and a y-value from the thermal flux recordcorresponding to the same time instant (after zero time)as the dT/dt value.

32

_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _4-4 4)

m U

G4.

T:I r-4I- F- 020 r

.4

4)24

f~ 0 -4

- 0 E-4

r 4 0 C%

44O 44E U

~oo

Z. 0.JJJ

>r4 . 4)

o 4 2

V-4

0

O 0. C

000O 0 0 0 0

I -4

44

D~~S-~UI/TjD I~lI IVNHHH1

33

18 r Event ;-320 kg/m

M-1 Propellant

Fireball

.14-uJZ12

W510

Sr LATE STAGE JET

6-

I2- I

0 2 0 2 4 6 8 1'2

TIME, sec

Figure 19. Test C-3: length of exhaust gas plume (from end of ventpipe) as a function of relative time. Zero-time was notrecorded, so all times are relative to an arbitrarilychosen start time.

34

I S

103-

D. ~iI

TEST C-3 Io 20 kg/=3

0. . M-1 PROPELLANT I

LU

V) I(n 0

> GAGE LOCATIONS IO I1 0 * Fre-Field

a Vent pipe I>& Chamber Wall I0

Li * Water-Filled Cylinder

II

0-1 10DISTANCE. m

Figure 20. Test C-3: measured peak pressures as a function ofdistance from the center of the 100-kg M-1 propellantcharge.

35

1500

o q = 4.145 (dT/dt) + 3.459

0

N 100E

0

50 0o

0 0

x 0

0 P

~-50Li

TEST C-3dT/dt - DIFFERENTIAL OF CHAMBER TEMPERATURE (THC190)

q - THERMAL FLUX (TF191), cal/m 2 -sec

-1 0 0 -0 0 2 400 8 0dT/dt

Figure 21. Test C-3: thermal flux at mid-length in the vent pipe(Gage TFgl9) versus the differential of measuredtemperature (Gage THCl90) with respect to time. Each datapoint represents a "pair" of values; an x-value from agiven dT/dt, and a y-value from the thermal flux recordcorresponding to the same time instant (after zero time)as the dT/dt value.

36

4-4 4)

~LLLL (AI-___ __LOa

CC

cu 0 -4l-.44

0) A.E4.4 0 '-4

T-4 E-o

(C)4 0"-4

E4 41 -4 -4 (

___ __ __ .~ 4)

EA 0

:3 ) Ia.f4).M"

I. 4)

-4

37O

16TEST C-4SO kg/ 3

1 4 M-1 PROPELLANT

14-Fireball

12 0i oCOO,

10 0

Z 8

VHatch Cover

56

Bunker Roof4

2

_02 468TIME, sec

Figure 23. Test C-4: length of exhaust gas plume (from end of ventpipe) as a function of relative time. Zero-time was notrecorded, so all times are relative to an arbitrarilychosen start time.

38

10 4

I I

TEST C-4 Io 50 kg/ 3

0.. 1-1 PROPELLANT

II

.10 3-o

"biiV)

CL

LJ GAGE LOCATIONSo

lo = o Free-Fleidloll a Vent pipe .1

a Chamber Wall IlJ 0 Water-Flled Cylinder

I I©1

II S I I m II I I , , I i ,Ii

1%441

1 10DISTANCE, m

Figure 24. Test C-4: measured peak pressures as a function ofdistance from the center of the 250-kg M-1 propellantcharge.

39

I!I10

4 -

(I)0

i'I

LiLJ

Q- 10

a..uIGi

(1. 4.-kg/rnI ILIJ-

I~l

:i , i | I i I I i -- I I i I 1- ii

0 I1I I10DISTANCE,

Figure 25. Peak overpressure versus distance from the center of the

M-l propellant charge, KA-Ill, Phase C.

40

CHAMBER

0~0

0103-

Uf) P 0.5502 (Q /V) 0bJ

a_

010 2

NUMBEROF IGNITERS

o KA-IlI. 1 Igniter0 BRL Model, 1 IgniterA BRI Model. 3 Igniters

10 1 10 10 2

LOADING DENSITY, kg/rnFigure 26. Peak chamber pressure versus M-1 propellant loading

density, KA-ITI, Phase C; comparison with previous datafrom BRL tests with one and three ignition points ofpropellant charge.

41

10 -

o ~VW PMP EXICL PRESSURE

wD10

(/)

IL

LUJ

10 = 0.6156 (Q V ,)1 -65

10 10LOADING DENSITY, kg/r 3

Figure 27. Peak overpressure at end of vent pipe versus chamberloading density; KA-Ill, Phase C.

42

103

0

I 50• 0 kg/=3

(nI I

IJ

a- Ios 20Ig

..

0I-- ['"GAGE LOCATIONS

11

DISIANCE, m

Figure 28. Peak total free-field pressure versus distance from thecenter of the M-1 propellant charge, KA-, Phase C.

43

I iBH Hiin l n a aan anIli n l I

03

5kg/n 3

Ij 2.---. 5

1E-11DITNE0

Fiue2.Pa hra lxvru itnefo h etro hM-1 ropllat carge KAM, has C. ote chmbe

thra lxdt r acuae rmtemculmesueens

-44

1 0 3

U (Overdriven Data Points)4)U)

N /

E_ .//t

4L'4t

~10 1~

"--Il, /e

45

'< /

I

11 10 10'LOADING DENSITY, kg/rn3

Figure 30. Peak thermal flux versus M-l propellant loading density,KA-III, Phase C.

45

103& Oft ME de. 3 lontif/

~/a OM Modl. 1 Igniter

(0 KA-11

LL

Ix"0

2DFCHAMBER

LIJ NUMBEROF IGNITERS

W 0 KA-III, 1 Igniter0 BRL Model. 1 IgniterA BRL Model. 3 Igniters

1 i i i i ia ii p 1 a ill1 0 103LOADING DENSITY, kg/r 3

Figure 31. Peak chamber temperature versus loading density, KA-III,Phase C; comparison with previous data from BRL model testwith one and three ignition points of propellant charge.

46

Table 1 KA III, Phase C: Configuration Parameters for M-1 PropellantCharges

Charge Surface AreaCharge Surface Charge To VolumeWeight Area Volume Ratio

Test Aky-L (M2) - (Mn3 ) (fir1)

C-1 10 0.1334 0.01771 7.796

c-2 25 0.1334 0.04277 3.118

C-3 100 0.5335 0.1771 3.118

C-4 250 1.95* 0.4277 4.547

*Estimnated

47

0 1

. 0 0 0 0 0 0 0 0 0 ,

U 0>

1(

L) 4

CCa

4) 41 4)

41 0 0 ( -A (A (A Wfa A

CU CL a. IL 9L IL ID U (

w ) 0 w 0 u uA 0 u

'0 '0IL)

4141 141 1 4141 4 41 1 >0~ j L L L L 1 1 I. L L L L

0U C CD L tv Lr L L c

"L L L L L f- L

a o 0 0 0 0 0 0 L L L La. a. a. a. a. a.' a. a.15

c c

0) > -> 4 >U >4'- '- U U ~ > . > ) . . 4

w '0 'O 0'If 0.. Ki -

(Uk (U. 0. (U. IL CL z. .

.2 u01 m1 Cl QC W! 41 41 W! 4

ig 414141 141 C41 ZLL Z 14

(U LnLn VC., 41

V (U

1 L

L 1- (U ( (U U ~ U48

-4,,

4,~0 60 0 In 00 0 u ~ .

0 -- 0 (A W (0 M (A-o a>

00W

U, 'A)

- u~ u ci c, u u* 2 x~

41 v v 4j 4.41 4

C .I. L IL CL C 41L L L L L L L L

00 )

W! 0: Lf L

4.1 4, 4*

~~~6 4, 4 , jL

0 Lu

It -* -&nL. 9) L

C) C

In L

4) 4

-~~~~I .IZOA ;

n-t - 0 - - - -n t- - ~ O

4, 40

lw a U0 a a a a . a .a .C 0 3 C a in a. a. in

A L" M ~ -

Y± a 0 0 L 0 CL a

0, 4 , , 4 4, Co Co 404 , (4, 4,0, 4, u

~ IL3 L Lt L. L. U 0 IU UL~ E IU U

LA .

o 01 4- 4- IS 5 U

to L A w w. L, L) u L) u

S0 a 0

0S 0 0 0 . L- L - L

L) C.U

EE~~ EK EE O .

0 - CD, ~ -~ , 0 0

L - L L-5

4, 4p 4, 4, 4, 4

o > > .U .U .4,

, U)

>. &. &, 4 U m UL C L CL 0

a In .1,4 U! 4 , U %. . a

It %r 0

CotLA 't 'LA LA - 00

a- 00na nC

0 0 ~ A 0 - -- ; In a

I- I- 00 000 00 7

x' x x

I.-

50

0

0 0 41 4P 0 , 4, 0

AUU

41

us s ).0.0 0 0 0 0 a. 0. 0.0 00 0 00 0.

oL IL m C C I C I a. C' a

.-

0 . . 4. 4D on 6 '1 V

-~~C C 0 0 0 0 :A.

01 Z

w3 W

4.~Z f E - 4.4L4.*~~~ 7S 4 4~ . .

I-4 ~ 4. .-' L AL A I A 6 60x

x x x x A LI m;3 3

LiA L L A

In U

A.. 51

... .... .. ... .. .. .... 66

Table 6 Test C-I (Loading Density 2 kg/m3): Gage Location and Peak Measured Data.

Transducer

Designation Location Measurement Type Measured Peak Data

ABEl71 Vent Tube, 1.6 m from Portal Side-on Pressure <0.9 kPa


ABEl73 Free-Field, 0.3 m from Portal Side-on Pressure 5.6 kPa



ABE176 Free-Field, 4.5 m from Portal Side-on Pressure 1.3 Kpa

ABEl77 Free-Field, 0.9 m from Portal Total Pressure <0.7 kPa

ABE178 Free-Field, 2.1 m from Portal Total Pressure <1.0 kPa

ABI180 Front Wall of Chamber Chamber Pressure <1.4 kPa

ABI181B Right Wall of Chamber Chamber Pressure(1/3 Height)

ABI182 Back Wall of Chamber Chamber Pressure <1.5 kPa

ABI183T Right Wall of Chamber Chamber Pressure(2/3 Height)

ABI184 Water Filled Cylinder Chamber Pressure <1.0 kPa


ABI186 Water Filled Cylinder Chamber Pressure ----

1BI187 Water Filled Cylinder Chamber Pressure 290. kPa


THVlO Chamber Hatch Cover Chamber Temperature 630. °C

TF11 Vent Thbe, 1.6 m from Portal Thermal Flux 34. cal2-sec

TF192 Vent Tube, 0.3 m from Portal Thermal Flux 27. cal2-sec

Note: The digitizer sample rate was one sample per 220 micro-sec, for a total recordlength of 60 sec.

52

Table 7 Test C-2 (Loading Density 5 kg/m3): Gage Location and Peak Measured Data.

Transducer

Designation Location Measure!,nt Type Measured Peak Data




ABE174 Free-Field, 0.9 m from Portal Side-on Pressure 7.1 kPa

ABE175 Free-Field, 2.1 m from Portal Side-on Pressure 3.5 kPa

ABE176 Free-Field, 4.5 m from Portal Side-on Pressure 6.4 Kpa

ABE177 Free-Field, 0.9 m from Portal Total Pressure <2.2 kPa

ABEl78 Free-Field, 2.1 m from Portal Total Pressure <1.9 kPa

ABI180 Front Wall of Chamber Chamber Pressure <4.0 kPa

ABI181B Right Wall of Chamber Chamber Pressure <3.4 kPa(1/3 Height)

ABI182 Back Wall of Chamber Chamber Pressure <4.0 kPa

ABI183T Right Wall of Chamber Chamber Pressure <2.7 kPa(2/3 Height)



ABI186 Water rilled Cylinder Chamber Pressure ----

IBI187 Water Filled Cylinder Chamber Pressure <13.5 kPa


THV190 Chamber Hatch Cover Chamber Temperature 604.OC

TF191 Vent Tube, 1.6 m from Portal Thermal Flux 42. cal2-sec

TF192 Vent Tube, 0.3 m from Portal Thermal Flux 34. cal2 -sec


53

Table 8 Test C-3 (Loading Density 20 kg/m3): Gage Location and Peak Measured Data.

Transducer


ABEl71 Vent Tube, 1.6 m from Portal Side-on Pressure 335.kPa

ABE172 Vent Tube, 0.3 m from Portal Side-on Pressure 56.1kPa

ABE173 Free-Field, 0.3 m from Portal Side-on Pressure ----


, BE175 Free-Field, 2.1 m from Portal Side-on Pressure >70.0 kPa

ABEl76 Free-Field, 4.5 m from Portal Side-on Pressure 11.2 Kpa

ABEl77 Free-Field, 0 9 m from Portal Total Pressure ----

ABEl78 Free-Field, 2.1 m from Portal Total Pressure 104. kPa

ABI180 Front Wall of Chamber Chamber Pressure 235. kPa

ABI181B Right Wall of Chamber Chaber Pressure 196.kPa(1/3 Height)

ABI182 Back Wall of Chamber Chamber Pressure 155. kPa

ABI183T Right Wall of Chamber Chamber Pressure ----

(2/3 Height)


ABI185 Water Filled Cylinder Chamber Pressure 155. kPa



&B1188 Water Filled Cylinder Chamber Pressure 69.0 kPa

THC190 Chamber Hatch Cover Chamber Temperature 616. °C

TF1l Vent Tube, 1.6 m from Portal Thermal Flux 220. cal/m -sec

TF192 Vent Tube, 0.3 m from Portal Thermal Flux 166. cal/m2-sec


54

Table 9. Test C-4 (Loading Density 50 kg/m3): Gage Location and Peak Measured Data

Transducer


ABEl71 Vent Tube, 1.6 m from Portal Side-on Pressure >1400. kPa

ABEl72 Vent Tube, 0.3 m from Portal Side-on Pressure 350. kPa

ABEl73 Free-Field, 0.3 m from Portal Side-on Pressure 382. kPa


ABE175 Free-Field, 2.1 m from Portal Side-on Pressure

ABEl76 Free-Field, 4.5 m from Portal Side-on Pressure

ABE177 Free-Field, 0.9 m from Portal Total Pressure 285. kPa

ABEl78 Free-Field, 2.1 m from Portal Total Pressure -

ABI18O Front Wall of Chamber Chamber Pressure ----

ABI181B Right Wall of Chamber Chamber Pressure 889. kPa(1/3 Height)

ABI182 Back Wall of Chamber Chamber Pressure 587. kPa

ABI183T Right Wall of Chamber Chamber Pressure 1833. kPa(2/3 Height)






THC190 Chamber Hatch Cover Chamber Temperature ----

TF191 Vent Tube, 1.6 m from Portal Thermal Flux >372. cal/m2-sec

TF192 Vent Tube, 0.3 m from Portal Thermal Flux >372. cal/m 2-sec


55

APPENDIX Al

KA-III, PHASE C

TEST C-1

10 kg M-1 PROPELLANT BURN

DATA-TIME HISTORIES

56

C3

,0 00

oa 0 0

00 0

co a

e r=

>C C[

-- 0I

C~

0 -L

xw

4- -

(n

L C

-

00

o0 0 0 00 0 0 0 00o 00

(led) anSSa~1duaAO

57

0 00

0 010 0

00 0

0 0

40 0 IN II

fnJ

0

cu

C~

L IonI W C

-- o0

AI-)

(n

LL

0co %

58.

IMPULSE (kPa x sec)

Co a4 a 0 0 0 0 0C. (D 03 003 0 0 0 0

p 0P

a CM v E

0 w0

m in

NL W> m

C a)

c- C.)

a Ij* c w49I - I

* ( (nm

co 3

E- L

/ 44

0 in

>4l N C

/ C-uda~

H C-59

IMPULSE (kPa sec)

o 0 00 0 00000

fn0

.0 EII" 0

ru 7

0 0 E

w r'0

X- 0 -

CU :

0 _O

-. 0)

42 0)L

-. ~ co 2.42j~ 42 /42 w

COD ( (n

L C

00

(0

0C 0L :3

C-* 7I C

60(

IMPULSE (kPa x sec)

.0-

0(n

C : Cu.u

01 5

x 01

x 7nU -9

CL cux.

X. CMuxi

z ~, -0.4-41c

a)

w a)

0 c0

L (13<- U

zxaw

to C,

cn

oo

0 U)cu 0

7L

(edx)aunssuciaa

61z

IMPULSE (kPa ~Esec)

o 0 0 0 0

0 0

it 0~

0. 0. a

inwE

c a)-4-

0. CU (n :

CC

%D

00 0 0

ul 0 tn 0

(RC13 H~n~q~dlH3A62C

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C, 0C,0. aC

cuu

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0-

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441

_ _ xwC

00

1-4

ONl

40 I 'n_______

0 0 0 C-'

_____ ____ 463

m CL 0

00 0v 0n0u0 7

- 0

0 0

> CE

U'

C Dua _ _ _ _ _ _ _ _ _ _ _ _ _L

Fc

4 _ _ _ _ _ _ _ _ _ _ _ _ _ _C) _ _ _ _ _ _ _ _ _ _ _ _ _Lo~~~E

Z__ __ _ _ __ _-

00

03 4

0 Ul 0

644

0. C.

in G

(1v 0j

40 tv

- LL

> 0O

C-D

c'"a a

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0 01

ru 0 0

00

(Rdx)aunss~d~I0

650

00 00.00-0t0

C, 0

00

00 x

- 04

000

a,

-4-0

a a)

C-L CL

0 fnUl 1 0 F

001ex 2 isauua_ _ _ _ _ _ _ _ 66

* ru

00

0 0n

4,1

MI 1 0

(lJn

zc

a))

1-4

CD Cinm

(VdX)- allS(-daA

67-

IMPULSE (kPa sec)

o 00 00 0 0 0o o a a a 000 0 0o a0 0 0 0o 0 0 a 0

Qnj

Eto 0

" 0L

co CP (1

x /uZ) 0

E VI' /

10

in W

C- rrj

4Ji

C

cn

m a)

C2-

0

0 0 0

0 0dlU-,

68

00

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o o

Mi

- a0

0 CD

U -1

C Z)

- a-FJ

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c i-02

o E Ea

02o

ci.

044

020,-

4-I

In C, U

(sn~~slao 020p)adrvada

>49

0.0-~

0 0

0 C

* -4

0 -:

cu ai

4, 4, 0

- = 41

4, 4,X-.

D.

*o LL

(J U

0 00

0 C0

00

on 0>to o Qi

G LL

4-

co >

41 04"

x

4) 0)

CU C-

4,4

CD 0

o G

XnqA IVM3H

71D

APPENDIX A2

KA-III, PHASE C

TEST C-2


DATA-TIME HISTORIES

72

CL Q.

2i -

a ai

F--

D E

* CD

2:3

4J4

< wj0))

mI-I cloC

4 EnC L

0 (

0 ~

a:)

zra(

0 0

ceam amnsaucma0

730

0

0 0.0

o 0 0

0 0

0 0

0 010 0O00

go~

100

0

> CO

(In

C :DL (U

0 3J

* 4 1x

a)>1 L

0 L2

aa

nL

0 0 C<D 0 0z0 02

74L

IMPULSE (kPa *see)

o 0 C

o 0 0in00

o 0 0 0 0o 0 07

1EE3j Ixa

Ln-

240.

>0 CO-

C DL ro

x - I

xLLJ

aaIL

0 U)

>4w <

0

cu c r0m

I-I ci

(Vdm)aunssadsaI

/5

IMPULSE (kPa sec)

0 0 0 0 3 000o000 0 0 0

o 0 0 0 0 0 00oo Wu CU

0(f

0 0

r- -O

0 in

f1 u/

~> C O

CO

!-41- di

OD C4cJ

S x n

LnL

m

0L

0In Ln

(Rd~) alnS~ad~aA

o70

IMPULSE (kPa sec)

o 0 0000

o00 0 0

.1

in in/I

10

LU <

C D- S p

aa

41 L

cnco

LU

00

In4

C.3)

CeJX)a~n9SHJ~aA

77 Z

IMPULSE (kPa sec)

o 0 0 0

o 00 0

0

0-0

0 inE

to Im

Ua

10x n1

E

4.'Cc

(3 LL

>m_on LU .

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N4.Jx

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0 0 a

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flJ40

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(D3

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(vdaf) aunssauduaO

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ar

C:

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C.

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CD 0U3 0

to 0

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41j

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44

co ::

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aJ 4

00

(ram)~- amsa]~~

____I 87

Li Ui W

Li LLIL)a

0 .J~

01 (

101

(D c F

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L E~

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x r

fu

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(snTSTOD ~ ~ ~ ~ Eg5P uiada

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C2 aC0

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U3 co

x cu

K K

in 4.

- -.-

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2) E

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I I C) L

ru,

Xf00I r013

890

tna-0

o inN

r, 0

0 6OE fu

_in

* (a

o ao

N ID D

I.~ N

P1I_-

CA"0 0

0 0

903

APPENDIX A3

K%-IlI, PHASE C

TEST C-3


DATA-TIME HISTORIES

91

IMPULSE (kPa x* sec)o 0 00

oCo 0 0 0 3 C 0o~C 0

0 40a

o ~ c 0 000O

0 0 0 at

%n IN

C:(D 0. L> M

C'

J aj

cu

% mjVCL

z

uu

m

__ _ _ __ _ _ 0

0 (

0VX ac-n9dHA

______________ L92

IMPULSE (kPa sec)

o to.4-'-------

1 Cu

I'.In

41

41 L

ann

0

:93

0 a00. 0

00

4-)

MII

(0 I

-4 1

U C-

1 -. L

1<

toW

C3C

InI-

94J

IMPULSE (kPa sec)

0 C3

000(f

E -

U3U

CL (-

M4-)

> CD

C-

L m

L CL

04~

(no -1 (

0

0 000000

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(ledN) a1IQSSa~1dHaAO

95

(nV

cn wto0

>0 (3

00

'Ti

C-)

uj

00

L m

tot~

_ _ _ _ _ _96

IMPULSE (kPa *sec)

o 0 0 000 0 000

o 0 0 000

o Zn 0

C w 0

a) L

-- I 0 sFC

Z ( 0

w>- w

0(

4 w0Cu(n

0(

(Vdx)aunssaaaao

970

IMPULSE (kPa * see)

o L 0L 01 0

tl a )

InItoon IAU3

fn'i

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10 0

n co

1 4Jx

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%~ 0-

C-

m00

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00

00

('RdX 2=SH~d rVJAX

98)

IMPULSE (kpa .sec)

o0 0 0

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0 I0

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40040 0

10Wx c l

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> Co

L ra

a (Ii

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cu

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00

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00

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IMPULSE (kPa *sec)

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0 CL

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w w

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100

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> C.0

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1024

IMPULSE (kPa sec)

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4-)

> M

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Cr)

k- 00

z100

IMPULSE (kPa *sec)

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104

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InI-xnqa vW~aw

108u

APPENDIX A4

KA-Ill, PHASE C

TEST C-4


DATA-TIME HISTORIES

109

00-~

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w 0

enI

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x

(1)

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x

< ai

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110-

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0 0 00

0n 0

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1

11

(-

Cu

Lo

(u C .1

Cu

L

)

oo U)

0 LL

U41

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-.4

rnz

mss~mdua0

oi l l

IMPULSE (kPa )Esec)

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In v - 4-)L

efn

a E

0

C

'S x

Ld a'

uL

0 co fc

m L-

0 A

(led) R~S9Z~l~aA

112

IMPULSE (kPa sec)

o 0 0 a 0a 0 000o 0 00 00 0! 000

in 0 0i 0 0W irig Mi -u - -ug

of! 0 a,7

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(u olu0' 0

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114

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11

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in in In 00 0 0 0u

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(vdx) Zaflss3adwIaA

117

IMPULSE (kPa ~*sec)

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S~ 0

c CO

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CO

L- C_

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z la)ansuu~11

IMPULSE (kPa ~*sec 1000)

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119u

IMPULSE (kPa sec)

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o 0o 0 ni

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fm -4

120

IMPUL -E (kPa Sec)

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m,

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100

z0 a'f

12

IMPULSE (kPa *sec)

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a. m.-

to

Cu' I

t CC

41 L

tn 0

((u

0(

innCu W .q

In I0

(12d%)~C MSS,(A

1224

IMPULSE (kPa it sec)

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o 0 0 0 1

, --- , {-

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g . , . 0

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in_

( sn) _s saum lAo123

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IMPULSE (kPa sec)

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~ 0 2

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0

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-0

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2E L

0

C"0iInc

127

*U.S GOVRNMW MNG OMCE~ 9 91 s31 - 1 # o o L

Documents

DEFLAGRATiON IN PARTIAL CONFINEMENT · KA-Ill, Phase C, M-1 Propellant Tests: Defiagration in Partial Confinement 6. AUTHOR(S) Charles E. Joachim 7. PERFORMING ORGANIZATION NAME(S)