COPY NO. _

0 TECHNICAL REPORT 4885IITRI FINAL REPORT J6342-Z

TNT EQUIVALENCY OF M1 PROPELLANT (BULK)

J. J. SWATOSH. JR.

J. COOK

IITRI

PAUL PRICE

PICATINNY PROJECT COORDINATOR

DECEMBER 1975

APPROVED FOR PUBLIC RELEASE: DISTRIBUTION UNLIMITED.

PICATINNY ARSENAL

DOVER. NEW JERSEY

The findings in this report are not to be construedas an official Department of the Army Position.

DISPOSITION

Destroy this report when no longer needed. Do notreturn to the originator.

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UNCLASSIFIEDPISECURITY CLASSIFICATION OF THIS PAGE (When Dad. Entered)REPORT DOCUMENTIATION PAGE REAsD INSTR'UCTIONS•/

EO DORMPATO PAGE BEFORE COMPLETING FORM. REPORT NUMBER .2. GOVT ACCESSION NO. 3. RECIPIENT'S CATALOG NUMBER

Technical Report 4885 COVEREDTIT.. . ....... ... . .. .

i1iLIITRI J6342-2 JR UME~ L-~4Oa.9--------

1 i~j a. CONTRACT OR GRANT NUMBER(*)

J.i J.Awatosh, Jr. •hok ((IITRI)Paulftricer((Project Coordinator) (Picatin AAA21'73-C-b73

___________Ar senaln L9. PERFORMING ORGANIZATION NAME AND ADDRESS 10. PROGRAM ELEMENT. PROJECT. TASK

Illinois Institute of Technology AREA WORK UNIT NUMBERSResearch Institute

10 W. 35th StreetChicago, IL 60616

II. CONTROLLING OFICE NAME AND ADDRESS

Manufacturing Technology Directorate DPicatinny ArsenalDover, NJ 07801 96______________

,,W .:_-i; RINTT NCY NAME & ADDRESS(/f different from Controllng Office) IS. SECURITY CLASS. (of thie report)

Pi? UnclassifiedSSCHEDULE t

16. DISTRIBUTION STATEMENT (of this Report)

Approved for public release, distribution unlimited.

17. DISTRIBUTION STATEMENT (of the abstract enteted In Block 20, I ditfterent from Report)

IS. SUPPLEMENTARY NOTES

IS. KEY WORDS (Conlinue on reverse side It necessary and Identity by block number)

Ml propellant Critical diameterTNT equivalency Geometrical configurationBlast pressure & impulsesWeb size

20. A"TRACT (Continue an rever oda If neceeary and Identify by block nmtber)-- TNT equivalency tests were performed with Ml, single and multi-perforated,

propellant. Peak pressure and positive impulsd was measured as a function of Idistance from the charges. Configurations tested were sealed shipping drumcontainers and scaled open top and closed top feed hoppers. The TNT equiva-lency for these propellants was computed from the test blast output measure-

, ments. It was determined that the single-perforated (0.013 inch web) MIpropellant yielded a higher blast output in all cbnfigurations tested, thanthe multi-perforated (0.025 inch web) Ml propellant. The highest TNT , I

O 13 UNCLASSIFIEDSECURITY CLASSIFICATION OF THIS PAGE (When Data entered)

~equivalencies computed were at small sealed distances,'ýVft/lbl/3, for the

seldshpig rmcnfgrtin I-SP propellant). They were 240 and 170

percent for peak pressure and positive impulse respectively. In general, themeasured blast output from the closed top feed hoppers was greater than thatmeasured from the open top hoppers.

UNCLASSIFIE

SECUITYCLASIFIATIN OFTHI PAG(Whn Dte I-Itred

FOREWORD

IIT Research Institute (IITRI) has conducted an experimentalprogram to determine the TNT equivalency of two Ml propellant gran-ulatio,:s. The work was conducted for the Manufacturing TechnologyDirectorate, Picatinny Arsenal, Dover, New Jersey as a section ofContract DAAA21-73-C-0737. It is part of the overall program en-titled "Safety Engineering in Support of Ammunition Plants."

The purpose of this report is to provide engineering data that

can be used in facility siting and structure layouts developed inconnection with the Army's Modernization and Expansion program forinstallations and activities.

Technical guidance was provided by Mr. L. Jablansky, P. Price,and D. Westover of the Manufacturing Technology Directorate,Picatinny Arsenal, Dover, New Jersey. The experiments were conduct-ed at IITRI's explosive test facility in La Porte, Indiana. Inaddition to the authors, IITRI personnel who made contributions tothis proiram are R. Joyce, D. Hrdina, J. Daley and H. Napadensky.

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TABLE OF CONTENTS

Page No.

Introduction 1

Background 1Objective 2

Description of Experiments 2

Test Site 2Test Configurations 2Calibration Tests 8

Test Results 8

M1 Single-Perforated Propellant Tests 8M1 Multiperforated Propellant Tests 16TNT Equivalency Calculations 20

Conclusion 28

Appendixes

A Test Data and Computed TNT Equivalency Data 37

B TNT Equivalency Calculation Procedure 77

Distribution List 87

Tables

1 Scaled shipping container dimensions 4

2 Scaled hopper dimensions

3 Ml single-perforated propellant tests 10AA

4 Ml multiperforated propellant tests 185 Maximum TNT equivalency profile of Ml propellant 35i

-Mx6 TNT equivalency profile of M1 propellant 36 4

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Figures

1 Test area 3

k 2 Cylindrical shipping drum configuration 5

3 Full-size hopper configurations 6

4 MI-SP shipping drum configuration 11

5 MI-SP open-hopper configuration 12[ 6 Ml-SP closed-hopper configuration, 50 lb 13

7 Ml-SP closed-hopper configuration, 25 lb 14

8 Ml-SP closed-hopper configuration, 6 and 12 lb 15

9 Ml-SP closed-hopper configuration scaling 17

10 Ml-MP shipping drum configuration 19

11 MI-MP open-hopper configuration, 50 lb 21

12 Ml-MP closed-hopper configuration 22

13 TNT peak pressure and positive impulse 23

14 Ml-SP/MP TNT equivalency, shipping drum 25configuration

15 Ml-SP TNT equivalency, hopper configurations 26

16 MI-MP TNT equivalency, hopper configurations 27

17 Maximum TNT equivalency, Ml-SP shipping 29drum configuration, 43 lb

18 Maximum TNT equivalency, Ml-MP shipping 30drum configuration, 55 lb

19 Maximi. TNT equivalency, Ml-SP open-hopper 31configuration, 50 lb i

20 Maximum TNT equivalency, Ml-MP open-hopper 32configuration, 50 lb

21 Maximum TNT equivalency, MI-SP closed-hopper 33

configuration, 50 lb

22 Maximum TNT equivalency, Ml-MP closed-hopper 34configuration, SO lb

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INTRODUCTION

Backgrounc(

Past methods used for the system design and siting of manufac-turing facilities of explosive materials have been based solely ongross quantities of material handled. Present day technology, how-ever, has shown that in order to produce cost effective and safefacilities, design criteria should be based upon the requirementsof the explosive material involved. With the new approach, specifichazards can be :liminateo or reduced if the unique nature and blastoutput of the material xre known. A

In 1"no with the new interest and philosophy, modernization andlrtde.;ign L currentl> being undertaken for equipment at variousstagces o-, the M1 propellant load and pack (LAP) operation and in-crem,.-iatU net-weigh operation for ammunition charges using Ml pro-pellant. Although all the equipment designs have not been finalized,it is known that bulk quantities of propellant will be well over100 pounds at various stages of these operations. The largest con-centrations of propellant occur in the feed hoppers associated withthe weigh-scale and pack-out equipment. The hoppers planned atIndiana AAP, which are open on top, are to be used in bag loadingoperations. Those used at Radford AAP are in a closed system asso-ciated with the can (shipping drums) pack-out facility.

Considerable work has been performed in establishing air blastparameters of TNT. For facility designs involving other explosivematerials, therefore, the required design information should be ex-pressed in terms of "TNT Equivalency," i.e., the equivalent weight• ~of TNT which will produce the same airblast environment As that

,, produced by a quantity of detonable material involved.

Therefore, at the request of the U.S. Army Armament Command(AR•COM), the Manufacturing Technology Directorate of PicatinnyArsenal has undertaken a study, in connection with its overall ex-plosive safety program entitled "Safety Engineering in Support ofAmmunition Plants," to determine the TNT equivalency of Ml propel..lant.

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Objective

The objective of this work was to experimentally determine themaximum output from the detonation of two Ml propellant granulations(single-perforated, 0.013-inch web size, and multiperforated,0.025-inch web size) in terms of their airblast overpressure andimpulse. The measured pressure and impulse values are to be com-pared with those produced by a hemispherical surface burst of TNTin order to determine the TNT equivalency of the Ml propellant.

DESCRIPTION OF EXPERIMENTS

Test Site

A series of tests were conducted on Ml propellant at the iITResearch Institute (IITRI) explosives research laboratory nearLaPorte, Indiana, under the technical supervision of the Manufac-turing Technology Directorate of Picatinny Arsenal.

A schematic diagram of the test area physical arrangement is Hshown in Figure 1. It consists of two concrete slabs 75 feet long Aby 10 feet wide in which 12 pressure transducers were installed.The pressure transducers were mounted flush with the top surface ofthe concrete slab in mechanically isolated steel plates. The gaugeswere located at intervals on radial lines from ground zero (GZ).The gauge positions ranged from 8 to 80 feet from GZ.

Test Configurations

Three basic configurations were tested. The first simulationconsisted of scaled cardboard drums which dimensionally representedthe actual shipping drum containers. In the second configuration,the geometry included a truncated pyramid appropriately scaled torepresent the typical open feedhopper. The last configuration wasthe closed feedhopper system. A combined cylinder-cone shape geo-metry was used to represent the closed feedhopper simulation.

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Two sizes of scaled shipping drums were used for the shippingcontainer tests as follows:

Table 1

Scaled shipping container dimensions

Diameter Height Propellant weight AP(inches) (inches) (pounds)

11.00 19.00 43(SP) or 55(MP)

9.50 15.25 27(SP) or 35(MP)

Thus, the aspect ratio of the cylindrical drums was approxi-mately the same as the aspect ratio of a full-scale cylindrical card-board shipping drum (i.e., L/D '- 1.69). Figure 2 illustrates therelative placement and spatial arrangement of the C4 explosiveboosters with respect to the Ml propellant. These boosters wereshaped to provide the aspect ratio of 1:1. A cardboard cap wasplaced over the cover so that the blasting cap could be insertedinto the system.

The full-size hoppers to be used at Indiana and Radford ArmyAmmunition Plants are illustrated in Figure 3. Indiana AAP will beusing two different size open hoppers for multiperforated (MP) andsingle-perforated (SP) Ml propellant. Normal operating loads are130 pounds of SP and 190 pounds of MP in the open-feedhopper arrange-rment. The closed feedhopper system will be utilized at Radford AAP•" for both the SP and MP M1 propellant materials. Normal operatingloads are 250 pounds for the SP material process and 303 pounds for

the MP conditions.

Both Indiana and Radford hoppers were scaled down in size to"accommodate the test site weight requirements. Scaling down the *

"hoppers included preserving the ratios of the mass of Ml propellant/mass of hopper, and the aspect ratio of the hopper. The mass of thescaled hopper is changed by varying the thickness of the metal con- '.

tainer, and the volume is changed by varying the physical dimensionsof the hoppers, yet preserving their relative aspect ratios. Table 2gives the dimensions of the scaled hoppers used during these tests.Materials used to construct the hoppers were 1/8-inch mild steel for

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Nominal Depth x Top OpeningLoad

Normal Load Full Scale Size130 lb SP 12 x 42 Square Depth

50 lb SP 8.7 x 30.5 Square

Normal Load Full Scale Size190 lb MP 16 x 34 Square Indiana AAP

Open Top Hopper :<50 lb MP 10.2 x 34.5 Square

Nominal D L H 1 -D.Diameter

LoadI

Normal Load Full Scale Size250 lb SP 60.0 19.5 26.0 L

50 lb SP 35.1 11.4 15.2

25 lb SP 27.9 9.1 12.1

12 lb SP 21.8 7.1 9.5 H

6 lb SP 17.3 5.6 7.5

Normal Load Full Scale Size 4

303 lbs MP 60.0 19.5 26.0Radford AAP

50 Ibs MP 35.1 11.4 15.2 Closed Top Hopper

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the open hoppers and 5052-M32 aluminum for the closed hoppers, rang-rK ing in thickness from 1/8 inch to less than 1/10 inch, depending on

the charge weight.

Charge weights in the open hoppers were 50 pounds for both pro-pellant granulations. In the closed hoppers, 6, 12, 25 and 50 poundsof SP were tested; however, only 50 pounds of MP was tested.

The hoppers were positioned upright on the ground (at groundzero) over a steel witness plate. The propellant was poured intothe hoppers and allowed to mound. Cylindrical C4 explosive boosters,with 1:1 aspect ratios, were buried in the propellant near the topof the mound.

Calibration Tests

During the course of this test program, several calibrationtests were performed to confirm the recording accuracy of the pres-sure and impulse measuring systems. The calibration tests consistedof measuring the peak pressure and positive impulse from the detona-tion of a 5-pound hemispherical block of C4 explosive. The chargewas set on a steel witness plate at ground level. Pressure and im- 2pulse data obtained from the C4 calibration shots was compared toestablished TNT hemispherical surface burst data. (The increasedenergetics of C4 are accounted for.)

TEST RESULTS

MI Single-Perforated Propellant TestsV Shipping Drum Configurations

The tests performed in simulated shipping drum containers aresummarized in Table 3. The tests are grouped according to nominalcharge weights. Two charge weights were tested, 43 and 27 pounds.The results of these tests are plotted on Figure 4. The graphicalrepresentation of the data is extremely concentrated such that anyvisible distinction in peak pressure and positive impulse betweenthE. two different charge weights is not possible. Single curvesfor peak pressure and impulse were fitted to the data.

848 I•

Analysis of the curves (Fig 4) for peak pressure and impulse asa function of scaled distance indicates that for the two chargeweights an asymptotic approach to the maximum output level has beenattained. Therefore, because of the data agreement, it can be gene-ralized that an equivalent response for the full size shipping con-tainer weight (105 lb) can be expected.

The scaled distance and scaled impulse values presented in thisreport are based on the total charge weight. That is, the weightof the booster, in equivalent pounds of propellant, has been addedto the propellant weight.

Open-Hopper Configuration

The three open-hopper (Indiana AAP hopper design) tests arelisted in Table 3 for single-perforated Ml propellant. In each test,50 pounds of propellant material was used and 2.5 pounds of C4 ex-plosive boosters were used for ignition. The peak pressure andimpulse relationships, as L function of scaled distance are illus-trated in Figure 5. At small scaled distances, 4 ft/lbi/3, twocurves are shown. Although the hoppers were symmetrical with respectto each gage line, different peak pressures and impulses were re-corded along the two gage lines for the same test. These resultsindicate that the detonation phenomena in the configuration was notsymmetrical. Secondly, the pressure-time wave shapes were multi-peaked. The peak pressures recorded in Figure 5 are the maximumsand are not necessarily the first peak. This would also explain thescatter in the data. The highest pressure and scaled impulse valueswill be used to compute TNT equivalency. Note that at scaled dis-tances of less than approximately 8 ft/lbI/3 the peak pressures andscaled positive impulses are substantially lower than those obtainedfrom the shipping drum configuration tests.

Closed-Hopper Configuration

The closed-hopper configuratior. tests (Radford AAP hopper de-sign) included charge weights of 6, 12, 25, and 50 pounds. The size

of each hopper reflected the difference in the respective chargeweights such that the corresponding aspect ratios were maintainedat a constant magnitude. The characteristic pressure and impulseversus scaled distance relationships are illustrated in Figures 6,sin7, and 8. At small scaled distances the configurations producedconsiderable scatter in the data, indicating nonuniform or unsym-

metrical explosion phenomena. In addition, the pressure-time waves

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maximum values of peak pressure and impulse are used to compute TNTequivalency.

Figure 9 illustrates the peak pressure and impulse variationas a function of charge weight for a number of scaled distances(X = 3, 9, 18). For small magnitudes of charge weight (6 and 12 lb),the respective pressure-impulse characteristic curves are practic-ally equivalent. Figure 8 represents the scaled blast cutputs forthe two different weights as a function of scaled distance. A mini-mal distinction in the blast output records is observed. In con-trast, increases in scaled blast output versus scaled distance wereobserved for the 25- and 50-pound charges (Fig 6 and 7). With in-creasing scaled distances, both peak pressure and scaled impulseare observed to level off for increases of charge weight (Fig 9).A contrasting trend is also illustrated for small scalar distances.That is, the blast output retord (pressure and scaled impulse) ap-pears to continuously increase as the charge weight is increased,and an asymptotic limit is not apparent.

In summary, for the SP-Ml type propellant, the closed configu-ration yielded larger blast outputs in comparison to the open-hopperconfiguration.

Ml Multiperforated Propellant Tests

Shipping Drum Configuration

The tests conducted with MI multiperforated propellant are pre-sented in Table 4. The first series of tests were performed withsealed shipping drum containers for charge weights of 35 and 55pounds. The results of these tests are illustrated in Figure !0.The larger drums and corresponding weight charges yielded greaterblast outputs at all scaled distances. One can only conclude thatfor full-size shipping drums of multiperforated Ml propellant, anequal or greater scaled blast output than that for the 55-poundcharge would be observed. For similar configurations and chargeweights, a noteworthy observation is that the blast outputs of theSP-Ml and MP-Ml propellant types are substantially different forequal magnitudes of scaled distance. The performance of the multi-perforated propellant is substantially lower than that of thesingle-perforated type (Fig 4 vs Fig 10).

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Open-Hopper Configuration

Three open-hopper configuration tests were conducted, each with

So pounds of multiperforated Ml propellant. The blast output resultsare illustrated in Figure 11. In analyzing the results from Figure 11,a considerable scatter of data points is observed. A consistent de-viation from the mean (for pressure and impulse) is observed for allscaled distances. For the peak pressure, the mean deviation is ap- 1proximately ± 17 percent to ± 16 percent for X = 2 to 20 ft/lbl/3.In the impulse measurement mode, the mean deviation varies from

21 percent to ± 9 percent for respective scaled distances,X = 2 to 20 ft/lbl/3.

In comparing the blast output levels of multiperforated propel-lant (MP-Ml) and that of the single-perforated (SP-M1) type, one ob-serves that for equal charge weights (50 lb), the characteristicblast output attained by the latter is larger than the level of theformer.

Closed-Hopper Configuration

Three closed-hopper configuration tests were conducted with

multiperforated type propellant. The blast output results are illus-trated in Figure 12. As in the open hopper configuration, a similarperformance trend is apparent. That is, the single-perforated MIpropellant yielded a higher blast output than the multiperforatedMl type. A considerable amount of scatter appears in the data re-presentation (Fig 12); specifically, for the small scaled distances I(2 ft/1bI/ 3 ) the deviation is large. This trend is evident for allof the hopper configuration tests.

TNT Equivalency Calculations

TNT equivalency calculations were performed for the nominal ISO-pound scaled drum configuration and for the open- and closed-hopper tests for each Ml propellant granulation. The TNT equivalencycurves for each test configuration were computed from the best fitcurves for pressure and impulse as a function of scaled distance.The TNT equivalency is defined as the ratio of the weight of TNT tothe weight of the test propellant that would produce the same over-pressure (or impulse) at the same distance. The TNT peak pressureand scaled impulse curves used to make the TNT equivalency calcula-tions for this report are illustrated in Figure 13. These curvesmust be used when converting TNT equivalency numbers back into pres-sure and positive impulse values.

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Figure 14 illustrates the difference in the TNT equivalencyresults for SP and MP Ml propellants. Although the charge weights(SP=43, MP=55) are relatively the same, the single-perforated pro-pellant produced a larger blast output (peak pressure and impulse)than the multiperforated type. In addition, because of the identic-al blast output behavior of single-perforated propellant for the27- and 43 pound charge weight (scaled drum configuration), the TNTequivalency curves for the two charge weights are identical. Ifone deduces that the identical peak pressure and impulse behavior ofthe two charge weights are an indication that the maximum outputlevel has been reached, then a logical conclusion would be that anyfurther increase of charge weight (aspect ratios being constant)would result in similar blast responses. That is, the present SPdata could be used for predicting the blast outputs for full-sizedshipping containers (for SP-Ml propellant).

In contrast to the above statement that was made for the single-perforated propellant, the results obtained for the 35- and 5S-poundMP-Ml charge weights (drum configuration) do not define an identicalblast output trend. Because of the difference in the peak pressureand impulse measurements for the two charge weights, any speculationthat the blast output of the larger charge weight is an upper bound iis inconclusive. A justifiable projection of the full-scaled drum/lconfiguration based on the blast output of the 55-pound chargeweight (MP) is not directly possible. An indirect approach, how-ever, is feasible. For any particular configuration and charge"weight, the blast output for the MP propellant is always smaller thanthat for the SP propellant. The SP characteristic blast output canbe utilized as an upper bound for the blast output of MP propellant.

TNT equivalencies for the hopper configuration tests are illus-trated in Figures 15 and 16 for both the SP and MP propellants. Theclosed-hopper configuration (RAAP) gave higher blast outputs thanthe open-hopper configuration (IAAP) and consequently higher TNTequivalencies.

In the single-perforated closed-hopper test mode, the scaledblast output increases with charge weight of propellants at scaleddistances less than 9 ft/lbl/3. Indications are that the maximumoutput or limit has not been attained.

With this observation, expectations are that for the full-sizeclosed hopper, a TNT equivalency equal to or greater than that forthe 50-pound test would be attained. An equivalent generalizationcan also be made for the full-size open-hopper configuration loadedwith SP or MP propellant.

24

I II f111 l IIH M 1 11 1 1:':

41 .it it

.. 1- -~ I'- I A

( 1 ) U ) (

If *-4 Ill -11 - -I4 .I *1 S + I 4 -8

11-1 Ill: IN

. I.H )

r-4 fl*- 1 ;;"T- iIcIn cn

C.-L

44

r4J

r~t= dz1IOiTMH 1-rt7--- L

0'U 4

p

'-44

4 M

II

"-44

44 '4D~~T..b c

2644a

0i

4< 41-4.4

1__._____.114

:~-r ,---771-7I oo

414$~~~ ; l. .

r-4 V74

~44 0-1 0

To -C..,.

7. --- co -)

-A.

Co) 0.

': 0

0 03 C

rr- -4 00 -

Fnm-M 4 pý

Maximum TNT equivalency curves are illustrated in Figures 17through 22 for the three geometric configurations and the two MlTNT equivalency profile at scaled distances of 3, 9, and 18 ft/lbl/3.

CONCLUSION

The average TNT equivalencies computed for Ml propellant, single-perforated (.013 inch web size) and multiperforated (.025 inch websize) tested in three geometrical configurations, are summarized inTable 6. In all of the scaled configurations the volumes and rela-tive charge weights were manipulated to provide equivalent aspectratios relative to the full-size configuration.

Tests with single-perforated Ml propellant in scaled drum con-tainers indicated that the results could be used to project the blastoutput level from full-size shipping drums.

The multiperforated Ml propellant always yielded lower blastoutputs than the single-perforated propellant in similar configura- 4tions and charge weights. Although the test with multiperforatedMl propellant indicated that the data could not be scaled upward tothe full-size shipping drum container, the results from the testswith single-perforated propellant can be used as an upper bound for

*" TNT equivalency determination for full-size multiperforated propel-lant.

Tests with single-perforated Ml propellant in the closed-hopperconfiguration showed that scaling or projecting the data obtainedto full-size hopper units was not feasible at scaled distances lessthan 9 ft/lb1 /!.

28

TI

I Sm

. 0 7 ."4'-4-

C1 +. + Z-ý

tT !- ir I-

J-i .44T +44-+

. 1-111 1 , i ~ CV 0

'4: + I t1. v-I r-. -

cnezw '4-UTA~la~I r4~T r14 li1i -

r4 ail

V9

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U) -I, TT 7 1

I- .51 II -~ -

InI

r4E

41 -1 4J $44 LW "a

S XCL

W- CA_ .1

o o CL

~u~od 'Aua~A~nb n~iLaT

30

titi

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I+

4~r4

9-I mw r E-

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I.Zi4T 1 + ff.,1 fi -FP11 R I II

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7- =1 .7!4~~~ :7 ý UN:

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_ 44'-44

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04

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=44:V

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m 400J1

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k I 4 -36 4) C t

ri -.

Al

V

APPENDIX A

TEST DATA AND COMPUTED TNT -

EQUIVALENCY DATA

.2

37I

C3 a Ln . 0 if$ I,-.

km. N .W 4 -Z 4

c a

CL

I-~~r I-- tr I-6 (tege

IL a

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ix, L- -C LP--f

r cc cc 0- M -if

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40 t-- & >

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t" Cci

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39 1 .C D NPI B PP -O I E

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IP* ~c I -a -, nLrtl'

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C K. *~ C C a C

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tLj

fn c M, M 1W

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a-~~a V)N~L 0 0005CL (PI

r- rn f-W

im CUf.W C C'

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cc a.

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CL go P

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t; in - -C x - on - -t r- CI

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to 4C 4- N

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f- zaf- e

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LL Cc CUAW 01 CD~~~~~U te, f:O C xC O

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ix t C. .... Wa ~*m >4

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a wN~~U

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N af fl- 0 U M W T t .

U,% ml r-. W.r ,a w W

C)45(0 m m. Cl).10 mj i v

Lo w

S ~ ~ ~ ~ e tft"Un-O O

IL6n 0 - -

a. -

m~~~~~ tny. r 4t 01t

-x ýr X -I-

CC. CC S0 m TO x

z 4-

Vk -3--

(V -- ZI

to 0 0' N c

c <L

- rcU ' 0't Lt I,-

a ia

%-, oOlM%

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a. C7 rz c .A; a

x- t -~ r. C rrý. 4 ku *os Xý

cr (r C -712 .O JPI.z -0'.Z ' - .~

o ~ 1 Iz r: *k 0- 9* 5 f5 5 5* **

- L c N

ic JA

X U.

LL trZ Czx-'71 r cr 16!CLli lC-F -f

ar C- >kar rZI Ctr -f rC C ý

7. W- r*5

Cr - j

s-a c 4.1 ::7 in t - T- r- k LPu'u .c Qt

CL a..

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2- - MM M U -- - WM

CL 0.

ira

- -N~fGP-I1O .- N &fO-62to

I' r ftmM t.X

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RE

Ilk

uia z

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U. ) ..J fu M M -

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4 ~63

7P ST I

ST~ (PSI rl (P STIMS

Y;t~ 2 LRS 1. 14 CvY I'JI IOI ID 1 7

15M 353.0 f 1 7 0~

S11 .77 165900 P1.7)It'97 175,0n 91.30•,1 1 , 7 :; 1 2 t• "1 •

ht 510 a6'10C

•:26.98 10.00 23,60

,27 ,0p I13 5 ?IS 2 1,7039.53 5. 7h ?f.v3Q,67 7o2Q 19.60

th i 2,11 1 1.10 -

Ap• 72. 2100 1(,6()

S.IM 'P-?. 55 L 1.5 LP) CYLIINI)r P LID 1,7

ftSO 3 7.00 ,o(0 •7 0

A,8 67a05.3k 0 C,0

11.77 111,0 *.

1 1 97 176a,10 I's 9( lO(

106.q7 16A90 ug.70

169.8 11.90 23obO 027,*02 1 P. ,30n 2.739.53 6,14 ??,to39v67 69hO 20,90

A()0 )5 2.07 1 n,, 40

m I 'Po3k 35 LBS ('*00GM) CVI TNDFR L/n 1.7 J

AO8) 307.00 69,30

11:977 44,70 22:10

16.97 1995n 29.9016.98 19.90 20.'J0

26,98 9034 17.9027.02 9.01 15.a00C19.53 3,35 10.50:139.67 3 092; 10*2(080.65 1.3t 5.26ft0.97 2 1 .30 5.33

2 64

TEST r'ATA

PT

"t 'ApeUp 35 LI5 (,-(O4;M) CT TYL T'PNO /[. 1.7

ARO 6.30 S."O5 I

11.77 31;0130 30 ,t()* 9!, 7 57,q") IJ30, {.l

P0,65 22,6n ?470

I .Q 8 16,an 20,20• '

070412 , Al )"49. e7217n 10,Tn0

Wn,72 1 0 1 A 5 ,2 m

0 ISP= P 1 4 LMS (IS. Lf) rYt.Ti',Fk• /. • 1.7

AM0 4121.on 132.00• ."1 325 .00 1 12 10" I :

1 1.77 1313,0 n 6t'J.00

16.Q7 69.70 14 £A2 o1 .98' s• '4 n 3n 5 ý41

?7,02 15.50 27,3039,93 6096 19.50

21 o.Q 10,3)

MI.SF-2R 13 L MS (1.5 1.4 CYt I l.E I 1 167

A I .i 1 41 1000 1 lQ (I o .1 1,77 1•,00O 51 01"•:•.

I t ,97 12690n 779, q016,97 35,6n 4I3,3U•1h,9p 68,9n .6,90

26,98 1 #3n 30.50.7702 l"46A 26,,7039,53 7.66 20.7039.67 6,04 19,,5080.65 2,2A 1 n10 080,72 1.83 9o99

65

TEST D•ATA

(Fl) ( PSfl) (PS1- IU S 1 1

1:• "1 P,,3P P7 L HS ( o oGm r (Yt.!,I.; I . IfF R L /fl I I

'Q ii1 2 ? A n 7Q q6S11.77 is,*n 0 OA0

:' "I1Pa.,• ?7 L.IS (llOrM) CYLI•tEO• Lif 1.7

1' 1 *97 283100 3A,76.1869" 191,on 77P9(

211.7 119.In 59.3()

1: 6.97 ?9.3r' 30o4J(•)16oOF' 32,30 ?22,60

•. ;. , ;29.5g 1!8,3f39.,53 3,9• 13,70l3Qoh7 L4,?1 12I1()

FaA72 I ,JAQ 6,63

))~o4 66 tlon 7,(

1 1 77 5997t)*- - - - - - - - --n

E ES 1 )A T A

P T

FT) (PS I~ (.I PST mfS I

MSPW I!'1 5 0 Lt~ H ?S LR) iii e7 2 a 3M1,0

S11.72 53,70 35.10

16o95 39210 33a7 (l•.,q o 3P10

).97 11950 P8,8p7.01 1t5,7n 2641039 e,7 7,7? 2,100

50.o6 31.5P Q*o10

M ISP0H3) 50 LIAS (2@5 I.A)

A 1.76 53,70 ?Q.10

8.81 q;7 *u ,12.0

11.99 51,30 32,0S•

16.95 3'4.80 36,110

26.97 2 18 1 6

29%,97 It15 0-1)27,01 14,a0 26;,0

39 .75 6077 .1,41R 8.,69 2,07 Q,3080.72 1.91 9,20

MI 1SP-OH3 So L AS (2,6; LR)

6 11.99 q490• 29,4p

11,72 NO w 33,30

Slb'95 34 0 80 3 6 0 L.

2701 14gb- 2692000'

S39,7S 7021 2n.3080,69 = 12,80

S "80,72 1,91 9120

67

Vo I

TEST O)aTA

FK PSIG CI(PST-HSIUj4'Pw0IH 1 50 Li~S (2.5 h

•.M1 7•.5n ai.50

~1~'~r7 50LP0.5

1 s7 5 a 5 n 33p.20

16.95 23.10 - IP1,,fW 7 13 L °1 n (25 0?7,01 1297n pil30

39*75 5,03 17,60

eiv, a72 l q/1 7,17

41 8-H25 PS 7b?95 L P I

,817 55920 •q

A1. 5790.LO 31

11,72 35930 33,20

111.97 . - 33,00

ie,qs So, 30,130

26097 1 2*qo 22.00

27,01 129.0 23.608

39,4S7 7.2 o 6% 1,4

39.75 60o7 17.00Io 6q 2.26 10.30

0o,72 I,7L A "

mjt4Pw0H3 SO LBS (2*5 LR)

8976 S31,03 "

8,F1 7ts,2n 3;,0;011,s72 50,40 34,30•I1t,99 3q•8n 2Q,20•16997 "= 33,00

AA

16,99 •550 30,4026,97 til,0n 25,50A

f27,01 13,10 ?4,8n"A39j47 7,2S I1o90•39,75 6,6O 17,00

S80,69 2,32 10oan80o72 260a 9,66

68

TESI DATA

F (T) (PSflI (PS T.MS)

*'ilPaC' H1 50 I~hS (P.5 L94)

f%, 1h 193bo 00 1500

5~,70 70300

11,99 6~.013.60o 33.10

27,01 15 , 9n 311,0()394 ,3A 214030

3c) s75 6,80 2'J,9(80,b9 2.7P 14,2()I80.72 2,795 12,50

MI1SPaCH2 5O LRS (2.5 LPI

A,6 137.00 37,00F4.81 156.00 95.5

11,72 9 A7 0 7A.00I1I.g9 139.00 6,9

2 97 19.1 8 5A0 29,S

3q,~c~4 7 8 ::? 1~ 1L.0

1A.72 2*0 . u;q0o

11.99 9500 72,11016.95 63.o7 t

16.99 65.70 4:L,;0

?6997 1903n 2q,80P7,01 250 32.20

r39*447 * *b

39.7S 6086 ?3*60

SO 7 12.20

69

;~41

TEq7 r)ATA

F T ~P SIC T-s

mISP-C'Hu 50 LdiS (2*5 LR)

A a7t, I h, On 5.3 0fi ,8 1 1?U.00,() LJQ.490

J11.72 1 a3,nn 63020I I q9 Q2.Qo ?.9

1.6 , q30I~$1 107.0n 116 ,30

3q,15 3'4.1 19fl

80,72 23.90i 14,60

F7.1 12.75,0 n 96119.72 6792 137170

39*75 ~ U .0 1 £1.3

F";.? 1L9 7.31

27.01 129.00 '21Q C) ,

26.79799 13.50

39',Iq 6.70u 12.00

A0.69 1.8 619 .31

110.72 gi.50 7.683'p

It,,qq780n

TEST PArA

(FT) (PSIG) (PSTeMS)

$IS P- C7 25IS t I2s 2i 1 )j

16,95 27*70) =16.99 29.10 26. 10

?7fl 1.0 0050 k39,47 s,13/1 12,3039.15 7.12 13.10

8,76 2 5020p.81 * - 45,60

11,72 87IA 35.,6011.499 a2,1 I 0.o 60I h S 24.5016.99 26.60 P5.00iŽ6,97 8,4A 2n 4()

27,01 1ijo2O 22,30

3c)7 0 is 13.90I80.69 1 qc91,890072 1o79 ,3

MISP-Ct49 12 LIRS (o6 LR~)

(ts76 5010 3 ,6 0fk 4 aI a a 1.90

1117? 18,50 17,70I 1 o9 24040 21060)16.05 15.30 13.9016o99 9,56st 1203026.97 6.14 1142027,01 7,06 11,3039,47 3,8A 7,10

39*75 2o94 5.16

71

TE:S T P A 7A

(FT) (PSIU,) (PSTIMS)

s Pe r H( i o LFS f 94LA)

23.20 .1

11.72 1201o 10.3011.99q 1 40110 1 4,00

lb.95 ~ 3.51 8,0216.99 7.*9q -

Pb.97 14,0c 5.9627013.8R 7*42

3q,'47 2.29 a3q,4.7 1,93 3s65

(90072 .70 2.,06

M P'"P-CHI 50 LRS r2s5 LP)

8,76 91,70 '48,90 K8.81 102.00 '47.30

11. 72 RA4,70 50,3011,99 91.20 55.1016.95 '42.00 '41.60

26,97 15,140 27,9027.01 15.50 30.,1039,147 6,.72 20,0039.75 7.70 19.60

#40 6q 1.79 10.8080972 2,13 q,78

91'IP-CH? 50 LHS (2.5 LA)

8.76 137.00 30,908.81 179.00 63,6011.72 86.60 '45.2011.99 814.4n 5i7,1016.95 36.20 -*

A lb.99 '43o6026.97 10.96A 30.104 27.01 10.1 a39,157 5408 27.9039*75 5.52 a80.69 2.2080.72 2o33 9.20

72

TEST PATA

CF'r (PSIG) (PSI ?AS)

I1' P C H3 50 LHS (2*5 LP)

11.7? kR'4( 17.10

ib'.7 47.10 32,60

A0969 9.8180s72 2927 9.75 -

1 73

niip

fl to Ai * a o* N a-7* O @

r- :x ' U) ( rf-GA, ftv,&r Pn x a w

- z~ LO C-l P, CC

- - C

ii. C. c

a o

CjC ) C c cc c ~ i o Ce

a -z P: Cra7CI*l

CL b- >' a

fn a c nuc~ 0 ~ ='

a.I c a~ In x r'rccp

*~ .4

in c- CO LC.O0 m 0 U4 c.C Lin

-LLC O~a.

74

-M-

CL -0 C P xc --

M, :3Lo LI C.L L. L x

D. c r '

L. ' C %CC ~ X.fuctZcc c cT

r"-

0 .- COC O_ 4j~ CCý c Ci rc c ccf.

LL LA.

LIJ u'

Q u.Jr ,C>c

* *.a -.3 * * ) ,rf.. .

Q Ai

75

*l o rl - xzta a e

nan 'C--A. ý L 4X

LL)

;E C_ c c Cc c ru c a C, Ur

aZL CV; -Lr nw1

LA.S LL

2 ~ L >

ch ce~o~ AD lei wuce ma

;z . L Vl) aS D

v*. 2i C C V N ~ o o

u tS ) Clc C> m * uac 0 a 0 *SOCSSC I

CL- M 0 -I-- LCN - lr

I-. 4 U~CC-0OCC :1- ( C0% C I

c C c* * se s. If. 0C .; c

*-.& M M a, 0nM -a

76

APPENDIX B

TNT EQUIVALENCY CALCULATION PROCEDURE

77

: -- .. w -

4;7.

Computational Procedure

The computational procedure used to obtain TNT equivalencies isillustrated in this appendix. TNT equivalency for pressure is de-fined as the ratio of charge weight (i.e., TNT weight/test explosiveweight) that will give the same peak pressure at the same radialdistance from each charge. Similarly, the TNT equivalency for im-pulse is defined as the ratio of charge weights that will give thesame positive impulse at the same radial distances. Since the boost-er used to detonate the test explosive, propellant, or pyrotechnicmay be of the order of 10 percent of the test material weight it isnecessary to account for its contribution to the explosive output(i.e., peak pressure and impulse).

The symbols used in this discussion are:

W Weight, lb

k Radial distance from charge, ftA=R/Wl/3 Scaled distance, ft/lbl/3P Peak overpressure, psig

I Positive impulse, psi-msecE TNT equivalency, percent

These subscripts and superscripts are self-explanatory whenapplied to the above symbols:

S Test sampleB BoosterTNT TNT explosiveI ImpulseP Pressure• Quantity is not adjusted for booster weightTOT Total charge weight, booster plus sample

Pressure equivalency is determined by first measuring thequantities WS, R, and PSB- Where PSB is the peak pressure measuredwhen the sample was detonated with a C4 booster, it includes anenergy contribution from both C4 and sample.

One must first approximate an equivalent booster weight, interms of the charge sample weight, so that its weight can be includedin the total charge weight. The approximation is found by obtainingATNT, from Figure BI, for PSB PTNT"

79

FJC•DIDr P.f3 BUL-NM..OT FIU,'D "1

i 02 1o3A

Hemispherical TNTSurface Blast

ii '

v4

2-4.

6t 10 Prssre

S45° 1/3

100 TNTýal

N " S... •

U)

Impurse - '

002

10 10 10

Scaled Distance, TW

XTNT TNT

.Fig B TNT pressure and impulse

80o

The first approximation for TNT pressure equivalency is then:

P- WTNT/WS (AS/ATNT)

where

AS R/WS1/3

and

XTNT R/ TN/

Since the pressures are to be equal at the same radial distance, theR's cancel in the above equation. One applies this approximatedequivalency, Ep, to the weight of the booster to obtain the totalcharge weight

WTOT WS + (I/Ep) WB(I.25) VV

A factor of 1.25 is applied to the C4 booster weight to obtain itsequivalent TNT weight.

A new X is now computed from

XTOT = R/WTOTI/3 Ai

and a corrected pressure TNT equivalency is computed.

P= WTNT/WTOT= (XTOT/'TNT) 3

The P subscript indicates a scale distance for pressure an~d is com-puted from the revised sample weight. This iterative process canbe repeated using the revised value of Ep to recompute the weightof the booster in terms of the sample weight, etc. However, thesecond iteration has a small effect on equivalency.

Impulse equivalency is determined first by measuring WS, R, andIS., where IS is the impulse measured when the sample charge wasdetonated witR a C4 booster. One must first approximate an equiva- _9lent booster weight, in terms of the charge sample weight. Theapproximation is found by locating the data point IB/WB"3: XS onFigure Bl. A 45-degree line is drawn through this data point tointersect with the TNT impulse curve. Values of XTNT and ITNT/WTNT1 / 3

81

W-~~~~-- 777 M-7fl''

are read at the intersection of the two straight lines. These values

give the equivalent TNT weight for equal .mpulses and radial distances.

At the data point ISB/WSl' 3 and XS let

aS- ISB/WS1/ 3 or ISB - aSWS1/3

and

Rs= 1/ 3 or R = XSwS1/3.

For equal impulses

ISB = ITNT

or

asWs 1/3 W 1/3

and for equal radial distances

xdistances1/3AsWs1/3 = XTNTWTNT1

Divide these two equations and get

as - saTNT TNT

Take the log of the above equation

logaS - logaTNT = log XS - log .TNT.

32

This equation shows that a 45-degree' construction line on a log-log plot will intersect the impulse curve and data point in such away as to satisfy the conditions of equal positive impulses at thesame radial distance.

The first approximation for TNT impulse equivalency is

I= WTNT/WS

11WE* (I/Ws1/3)3/ 1/3_3 SS SB S (ITNT/WTNT) 3

Since I = ITNT they cancel in the above equation.SBIR

One applies this approximated equivalency, E1, to the weight ofthe booster to obtain the total charge weight

WTT =W + (I/EI) WB (1.25).

A new scaled distance

1/3TOT = RIWToT

and scaled impulse is then computed as

TSB TOT

1/3This data point is now located on Figure BI and new ITNT/WTNT andXTNT values are determined from the 45-degree line intersectionmethod described.

The correct impulse equivalency then becomes

E = WT/WTOT

1= IsB/WTOT) II WTNT)3

83

4-A.

Computerized Calculations

The TNT equivalencies of the explosive material are determinedby use of a computer program. The first step in the program is tofit a curve to the test data utilizing a manual curve fit method.That is, a curve is drawn through the data points that are mostrepresentative of the characteristic trend. To do this, the pres-sures with their corresponding gage distances (and, similarly, im-pulses with their distances) are entered into the program as inputdata. Scaled distances are then obtained by dividing the gage dis-tances by the cube root of the charge weight. Where the input con-sists of experimental data from more than one test conducted underidentical conditions, the pressure and impulse values are averagedbefore the curve fit is performed. Impulse input is converted toscaled impulse by dividing by the cube root of the charge weight.This is performed before averaging or curve fitting is done. Poly-nomial fits of the first and second order were attempted; however,inadequate results were obtained.

Having chosen the curve which best describes the test data,pressure and impulse values with their corresponding gage distancesare entered into the program along with the appropriate curve co-efficient. The TNT equivalence is determined twice, once usingpoints from the fitted curve at scaled distances corresponding tothe gage locations, and once using the actual data point. This isdone for both pressure and impulse data.

In the program, the TNT pressure and impulse curves versusscaled distance appear as polynomial expressions. To determine thepressure equivalency, the TNT scaled distance at a pressure equalto the test pressure is determined from this equation. The TNTequivalency at each pressure data point is computed as the curve ofthe ratio of the scaled distance of the test data to the TNT scaledM

distance.

A correction is made to the equivalency calculation to includethe weight of the booster in the total weight. The TNT equivalencyis then recoanputed on the basis of the corrected weight. This isan iterative process and continued until the change in the ratio ofthe scaled distance to the TNT scaled distance is negligible.

A similar procedure is followed for impulse data. Since scaledimpulse is used rather than actual impulse, a correction in the totalweight of the explosive to account for the booster weight involvedmaking corrections to the scaled impulse as well as the scaled dis-tance.

84

".2'

. . ..%.~ ~ -

'%tin

The computer output for the pressure tests includes, for theaveraged and curve fitted data, scaled distance, corrected scaleddistance, pressure, total weight, and TNT equivalency at each gagelocation. Output based on raw data includes scaled distance, cor-rected scaled distance, input pressure, TNT equivalency, and gage

distance at each data point. The output for the impulse tests issimilar except that scaled impulse and corrected impulse are included.

S.

45

AN

1 85

"- NIk

DISTRIBUTION LIST

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SARPA- NT- C 2SARPA-MT- F 3-17SARPA-S 18SARPA-TS-S 19-23

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AdministratorDefense Documentation CenterATTN: Accessions Division 26-37Cameron StationAlexandria, VA 22314

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CommanderU.S. Army Materiel CommandATTN: AMCSF 40

AMCRD 41AMCRP 42

AMCIS 435001 E~isenhower Avenue

Alexandria, VA 22333Commander

USAMC Installations and Services AgencyATTN: AMCIS-RI 44

Rock Island, IL 61201

87

CommanderU.S. Army Procurement Equipment AgencyATTN: AMX-PE-MT 45Rock Island, IL 61201

Project Manager for Munition Production BaseModernization and Expansion-USAMCATTN: AMCPM- PBM 46

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ATTN: AMSAR-SF S2-54AMSAR-SC 55AMSAR-EN 56AMSAR-PPI-C, Mr. G. Cowan 57AMSAR-RD 58AIMSAR- IS 59AMSAR-ASF 60

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88 1

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Corps of Engineers, 6014 US PO and Courthouse215 N 17th StreetOmaha, NE 68102

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89

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'44

90

I,_s o• •