UNCLASSIFIED

AD NUMBER

AD464450

NEW LIMITATION CHANGE

TOApproved for public release, distributionunlimited

FROMDistribution authorized to U.S. Gov't.agencies and their contractors;Administrative/Operational Use; 13 APR1965. Other requests shall be referred toBureau of Naval Weapons, Washington, DC20350.

AUTHORITY

18 Apr 1967, ST-A per USNOL ltr

THIS PAGE IS UNCLASSIFIED

UNCLASSIFIED

AD_445

DEFENSE DOCUMENTATION CENTERFOA

SCIENTIFIC AND TECHNICAL INFORMATION

CAMERON STATION AlEXANDNIA. VIRGINIA

UNCLASSI FIED

ROTICE: 11en Covemint, or other dravings,, spool-ticatIons or other Sata arm used flor any puarposeotlter than in connectoa vith s. definitely relatedgovettmo't procurmont opezatlon, the U. S.Government thereby incurs no responsibili~ty, nor anyobligtio~n i*uttoever; and the fNot that the Govern-mnt my have foziualted, Aunished, or in any mysupplied the said drawings, specificaticiis, or otherdata Is not to be regarded by iplication or other-wise as in any =mnr licensing the holder or anyother person or corporation, or conveyling any rigtsor pezuissior. to manufacture, use or oell anypatented invention that may In any way be relatedthereto.

NOLTR 65 -3 3

THE EFFECTS OF CONFIGURATION ANDCONFINEMENT ON BOOSTERCHARACTER ISTICS

NO L3 APRIL 1965

UNITED STATES NAVAL ORDNANCE LABORATORY, WITE OAK, MARYLAND

~,A

NOTICE

Requests for additional copies by Agencies of the Department of Defense,their contractors, and other Government agencies should be directed to:

Defense Documentation Center (DDC)Cameron StationAlexandria. Virginia

Department of Defense cor.tractors who have established DDC services orhave their 'need-to-know' certified by the cognizant military agen~cy oftheir project or contract should also request copies from DDC.

I INOLTR 65- 33

The Effects of Configuration and Confinementon Booster Characteristics

I. Jaffe and A. R. Clairmont

ABSTRACT: The purpose of this work was to examine the effectof certain changes In size, shape, and confinement on theeffectiveness of tetryl boosters. Effectiveness was judged intwo ways: by the booster's approximation to a plane-wavegenerator and by its Initiating strength Consequently themeasurements made were of non-planarity jradius of curvature)of the detonation front emerging from the booster and of theshock velocity vs distance curves of the hydrodynamic disturb-ance it caused in Plexiglas.

The changes made In confinement and shape of two-inch-diam boosters caused no significant change in either perfor-mance property. Changes In booster length, however, had amarked effect. Booster effectiveness increases with Increasinglength and is still increasing at A/d of 4 contrary to litera-ture statements that curvature of the detonation front is con-stant at ./d a 3 and that booster strength becomes constant at£/d a 1.5. The validity of using truncated cones in place of,ylindrical boosters in large-scale field tests of detonability

was confirmed. The variation of 5Wj gap thickness with boosterlength (and corresponding invariance of critical Initiatingpressure), for a given test material, was quantitativelymeasured.

PUBLISHED JUNE 1965

APPROVED BY: CrlR a Chief

CI3MiSTRT ISAICH DEPARTMENTU. S. NAVAL OIDHNC IA,1~)RATOqRYWhite Oak, Silver Sprinc, Maryland

i

-!I

NOLTR 65-33 13 April 1965

The work of this rM, is one phase of a continuinginvestigation of the sensit .ty of propellants and explosives.Observations were made on tha effect of certain chanees In size,shape, and confinement on the effectiveness of tetryl boosters.Several conclusions are made regarding the use of truncatedboosters in place of cylindrical boosters, the correlationbetween length and shock planarit , and the relationship betweenlength and booster efficiency, The investigation was carriedout under Task RMWI-22 14 9 /212 1/F009/06-11, Propellant andIrgredlent Sensitivity.

R, E. OENIMCaptain, USNComander

t, . /' .. ', . ;

kLERT LIOMrBODY /By direction

ii

II

NOLTR 65-33

TAKE OF CONTENTS

Introduction ....................... .... 1Ezperiinntal Procedure ............ *........ 2Re suits ......................... 4Discussion *.......... ..... e... .. 6Conclusions ......... ............ 23Acnvlegnt ........... eg~eegeeggg.ee 24Re ferences g.g.g~.eg............. ~.25

ILLUSTRATIONS

Table 1 Shock Front Profile - Unconfined TetrylCylinders (12.06 mm and 25.4 - lOeths).... 26

Table 2 Shock Front Profile - Uncon~fined TetrylCylinders (50 mm lorg) .... ee. 000**0099.000 27

Table 3 Shock Front Profile - U~nconfined TetrylCylinders (101.6 =long) 0*00000*00*0.egeege 28

Table 4 Shock Front Profile - Unconfined TetrylCylinders (203.2 m long) .g eeggg.. 29

Table 5 Shock Front Profile - Confined TetrylCylinders (25.4 mm long and 50.8 w lorg) .... 30

Table 6 Shock Front Profile - Confined TetrylCylinders (76.2 man and 101.6 mmu long) *ee. 31

Table 7 Shock Front Profile - Unconfined Cones(25.4 mm, 50.8 mml and 101.6 umm lone) 32

Table 8 Shock Attenuation in Plexiglas - UnconfinedTetryl Cylinders (50.8 mis lore,) ............. 33

Table 9 Shock Attenuation In Plexiglas - TetrylCylinders - Unconfined (101.6 mmi and203.2 um long) .. e.... ~ geg~~gg~ 34

Table 10 Shock Attenuation In Plexiglas -TetrylCylinders - Confined (50.8 mm long) ......... 35

Table 11 Shock Attenuation in Plexiglas - TetrylCones - Unconfined ........ g. 000000*0.0009000

NOLTR 65-33

TANS OF CoVmm(Cant)

Table 12 Computed Radii for the Shock FrontProfiles .......... Oeee...... 37

Table 13 Shock Velocity in Plexiglas vs Distance ... 38

Table 14# Coarl.%n or 50% Cap VajLues Obtained withDifferent Tetry!. Boosters ................. 39

Figure 1 Experimental Arrangement for Wave PlanarityMeasurements ******...**.**** 3

FIgure 2 Experiwata.1 Arrangement for ShouokAttenuation Masuremeints *..0. 0.. *.... 5

Figure 3 Smear Trace from End of Det;;.izor (;-efiectedLight) T..................

Figure 14 The Influence of the Detonator or. the WaveShape ..................................... 8

Figure 5 Typical Smear Traces for Charges of Various

Figure 6 Smear Trace Along the Periphery of aCylinder .......... .............. ......... 10

Figure 7 Rrdii of the Detonation Front vs langth ofUnconfined Tetryl Cylinder ......... 13

Figure 8 Comparison of the Radii of Curvature .... 15

Figure 9 Compa-ison of 50.8, 101.6 and 203.2 mmUnconft.neA Cylindrical Boosters ,.... 18

Figure 10 Comparison of 50.8 and 101,6 m, cone *... 19

Figure 11 The Attenuation of the bhock Velocity Inthe 50.8 n. Booster ...................... 0 20

Figure 12 The Attenuation of the '"hock Velocity Inthe 101.6 wu Boosters ............ *......... 21

IVI

NOLTh 65- 33

The Effects Of ConiguVration. and Confinementon Booster Characteristics

I. Jaffe and A. R. Clairmont

IMTO WCIOII

For lamce scale, critical dimter tests, replacement~ ofthe cylindrical booster by a truncated con has been recowinded(1); an equivalent stimulus delivered to the test material from~approximately 113 the amount of booster explosive "as desired.For the laboratory scale, gap sensitivity test (2), strongrecommendations hae been made to replace the current booster ofler~th to diameter ratio, L/D - 1, with a cylinder of L/D ;t 3.There i3 general agreement that an L/D of 3 or more Is desirableto assure a build-up to steady state fres a minimal shock initia-tion, but this does not seem relevant to the use of an adequatel.ydetonated booster in masuring the shock sensitivity of anacceptor ..-t material (lID z 3)., In other words, if the boosterexhibits steady state detonation,, the same value of criticalpressure necessary to Initiate the acceptor should be measured,regardless of booster length,

It was the intent, of the present investigatior. to examinethe effects of changes in size, shape and confinement on thebooster effectiveness, The shape of the detonation wae frontemerging from the booster and t,,*- shock it set up in ?lexiglas*were used for this purpose. In addition to metilng these objec-tives, the data acquired serve to correct the followine Inexactstatements in the literature:

1. that the curvature of the detonation front becomesconstant after an L. of about 3 (3);

2, that the 50% gap value for a booster of L/D - 0.6r7will differ from that with an L/D - 1,274 by a constant thick-ness (14); and

3. that increasire the booster length beyond LIE) - .will have no further effect (14).

SManufactured by Rohm, and ILaas

*;MTR 65-33

El? ERIM?rkL PROCEDURE

A, The Wave Shape

Tetryl pellets (p0 = 1.51 + 0.01 g/cc), 50.8 mmi indiameter and 25,4& = lon~e, were stacked and cemented together attheir periphery to form cylinders or various lengths. Thesecylinders were used unconfined or confined In steel pipes (50.3mmn I.D., 76~.2 mm 0.D.), or they were machined down to the shapeof a truncated cone, The two bases of the truncated coniec werektept cordtarat at 9,5 mm diameter and 50.8 mm respectively, Theartle o! inclination of the cones varne with the lervgth of t ri

cone,

Figure 1 is a comiposite drawirM showize. the gen~eralarrar~e-uwnt used to observe the wave planarity of the va'-loscha-ecs, A I.o, r'1-l'stirc cap* was uzed to Initiate t". ?Kozzter,

The canp was lined up ith the axris ort t"e chare, and held ir.place by a cylindrical piece of vood (50.6 cm dia., 25 ..n lorAF),cemented to the bace of the cNharge,

An aluminized 1eilsflazher-, 7-. =- in 14azeter and3. ar thick, uas cem~ented at its periphery to the end of ttw

charge. The thin layer of air- sarndwiched between the charge andthe disc flashes when It iz ht by, the zhock wwve. The intensityof the flash increases the illumination, facilitat-InC the

reodinrcf tl.he wave shape by the smear exr , The carerzi Vievcthe shod.: fron- t'hrouch a srnall transparent area, -. 2 nr. *v-Ide,which divides the disc into fcur eq'ial par'Vs4 (see FIC. l

To alienr the axis of the charg-,e with the optical axis ofrthe camera, a bear of liZht waz proj)ectee ba~ck lth'ou-,h thecamera onto the alum-ini.zed rurfaco of the flasher, rThe .3sseanbywas adjusted until the bean of lirht- was reflected back on itsincident path, placing_ the cha--r', axis in lr~e vith th.- optical

The procedure was ched to observ';e the shape or thuwshock. wave at the end of a hlaztin j cap o , detona--or. The capwas ali~ned in the ranner descrbeij abov-e, Limt since the ilhination produced by the cap wcas toG umak tr. oebtai4n pozzttire smea'record, the wave rhzpe was folowed by olbservirZ tn;" inzerrpttorof reflected lirght' off' an alliminlz, d 1Ic2 1.J :-_.~aj x ~thick at the end or the detonator. lbe 14i'ht f'c~ .r explodiik

M anufactured 1. Ciin-Irathia:-on

aE

0 92

4

166

ioLTR 65-35

wire, was arrarced at an appropriate angle in front of the discwhich reflected the beam alonZ the optical axis irto the camera.The writing speed of the smear came-a was 1.32 r.W/bsec.

. he Shock Velocity

FPiure 2 is a schematic diagram of the arrazvcmentused to reasure the shock veiocity in a Plexiglas rod, ThePlexiglas attenuators were A;achlned froL, 50.6 im flat stock toa cylinuler approximately 52 mm la diameter, containing twoparallel, opposir flats approximately 9-10 mm wide. The flatsprovide an utistorted optical path through the Plexiglas.Thin lrles perpendicular to the axis of the cylinders, were4nscribed on the Plats to mirk off known axial dist _nces. Ashield, conzitin- of ilexi'laS 20e G p&M wA 2.& ce thik,was used to prevent the reaction products from obst='ucting theview of zhe cacra. The center portion of the shield wasmachined to a tt-.Ic,:ne s of T.2 =n (see Figure 2). This addi-tional thickness of 1 4-_.laz, carefully measurud before eachtes., ,.ac con:idered an part of the total attenuation path,

A an.rror, -i-dlar to ;he flasher used above, was fixedte.-F ;-ar!l:- t. a :--linder flt. The mirror was placed concen-

:r -with the n-'.Jpe!nt ta1er. alo.r. the leith of the cylinder.The entire assentily was align-ed, with the aid of the mirror, sothat It= lonritulinal a::= w.-i perpendicular to the optical axisat :..e ridpolnt alorz- the le. -th of the cylinder.

-- ~"..- .;a= s-c.: :,-hv!cd by an exploding, tursten.:ire. 2'oms which XiY) volt- were dischar -..ed, The wire, 0.05.-z.' ter an' 7- r-. )r-, :as :mtru- in a 2.5 -m capillary

7zed -, ce3 .t the focal point of a 15 cm lens. The lenswas uhed to loiiL-a'te:ht bhind the cylinder. The

dr -.- pocitioe "4 m nro%.zate1y 10 c- in front of thelen..

REZU12TSFi. ure: , ., ar e._.roductions of the smear canera

record= r~x-nlfied .. rprc.i..te1.1 - tines. There particularrecord: fotlo t.. .eveor.t of the :-ave becInn-ir at the endof -.he dlet-^tor, .'uzt prior to enteri- the tetr*l charge, tothe endI of an unconfined, 2).3 . o !o-, cylindrical charge.The rrid liner, whih are ..pelcpoed upon the oriCInalrec-.rdz, are equivalent to 1.M. vccr:/dlvislon alornC the tiea;.I: .-Te horizontal ntrea, .n th: center of the record, is arefvrenc- 1!ne which facilltate: r..adI .nj the records, In mostinstances, th-- 4i:tan.e :an be measutr ed to , 3.1 rn wvl. the time

/ ! " I-a

NOLTR 65 -33

(mum OR M)

* * BLAT LAS')

-- w-lIGLAS CYLIN~1

CALIPRATrON LINE

FIGURE -2- PRDETAL ARRAiroawN FRm sW)C ATE!ATION NEASUPMr3~ S

IINOLTR 65-33

to 0.03 Rsec. The results are listed in the Tables 1 - 7.

Figure 6 is a typical record obtained for the attenua-tion of a shock wave in a plexiglas rod. The distance, in thiscase, can be measured to -, 0.2 imm and the time to 0.03 iLsec.The data have been recorded in the Tables C - 11.

DISCUSSION

The '"ivp Profile

Figures 3 - 5 show the progress and development of thewave front from its inception at the end of the detonator cap,to tht. end of a cylinder 50.3 mm in diameter and 20.32 cm long.The incident wave front off the cap is quite irregular andspread over an interval equal to 0.5 4.sec (Fir. 3). The effectof this is to initiate the tetryl charge over a region approxi-mately described by a circle whose diameter is somewhat greaterthan the diameter of the detonator (6 =). The influence of thecap on the wave shape is quite apparent at the end of the 1.6 mmof tetryl and is still evident at the end of 3.2 mm of tetryl(Fig. 4). The irregularity in the front is completely lost,however, at the end of 12.7 mU of tetryl.

As the wave continues down the cylinder it flattens out.The edges of the front draw forward, and in line with thecenter. At the end of 20.3 cm of tetryjl, there is a 0.2 I.secinterval between the arrival of the center and the edgees of theshock wave. The curves for the most part appear smooth andsymmetrical about the center axis, and show no discontinuity atthe boundaries of the cylinder due to lateral rarefactions.

The development of a detonation wave in the solid,tetryl cylinder, appears to be analogous to the expansion of acompression wave in a homogeneous medium such as water.* Thecharge is initiated at numerous points over a circular area ofapproximately 6 mm. Each point of inittation acts as a pointsource activating the material around it, creatine, minute areas(centers) of reactive particles. The result Is determined atany given time by the envelope formed by the spheres expandingfrom the reacting centers. Given enough time and material, I.e.,long enough path of travel, any Irregularity in the detonationfront disappears, and the wave front appears in the cylinder asa segment of a sphere which is expandine, radially at constantvelocity.

Huygen's principle of wave construction

6

,NOLTR (5-3-,

NQLTR(5-33

\OLTR( -3

INOLIR 65-33

I -~-.30

I U

I <

5.4

CA

1.~.

'I

I

NOLTR 65-33

Assuming the shock wave is point initiated, spherical,and moving radially at a constant detonation velocity, it canbe shown (5) that the following relationship holds:

22 2R I R0 2 + Yi (1)

orR2 Y2R - = 1

(2)Ro Ro

a rectangeular hyperbola where

Ro = radius of curvature of the detonation front attime, to

t o = the time that has elapsed fror. moment of initiationto the moment the shock front reaches the surfaceof the charge observed by the slit

R, = radius of curvature of wave front at t

Yi - distance front has traveled along the surface ofthe charCe at time t i

t I - elapsed time as measured from the moment the shockfront reaches the surface observed by the slit,i.e., time as measured on the smear cawera trace

For a constant detonation velocity, equation (1) may be writtenas

(UDto + UDti)2 = (UDto) 2 + Yi 2 (3)

where

UD = experimental detonation velocity

The value of detonation velocity used, UD = 7.2 mm/4sec,had been prev.,ously measured (5). The data Y,, t obtained fromthe experimental records and the detonation velocity (U ) weresupplied to the IM!1 7090 computer. The computer chose ?he bestequation, by a leact squareo method, to rcpre,,ent the data as aspherical front. Since no experimental record (Fitr. 3 - 5)

11

IINOLTR 65-33

showed any departure from the spherical shape at the lateralboundaries (edge effects), data over the entire front were usedto obtai't the best representative sphere. The results arepresented In Table 12. In those instances where more thanthree experiments were made a standard deviation of + 3.2,(25.4 mm lorc. bare cylinder) and + 3.CQ (50.8 mm lone-barecylinder), were calculated. The iean value is eiven in allother cases. In most instances the spread of the data from themean Is about equal to or less than 3.5 with the exception ofthe 203.2 mm lor urconfined cylinder (&), This smallerprecision is probably (lue to the proportionately smaller seg-ment of the sphere used to calculate the radius of curvature Inthis long charge.

Figure 7 Is a plot of the results listed in Table 12:radius of curvature on the axis as a function of the lergth ofthe unconfined cylinder. This curve is compared with a linerepresenting the grot:th from a point initiation, of a spherlialwave whose radius is equal to the length of the cylinde - . Forany given letwth, the radiu -: detqrmined from the experimentalresults appears larger than the geormetric radius (radius =lerrth). The initiation of the charge occurred over an areaapproximately 6 m. in dia (FPg.4)anId 1 ra from the beginning ofthe charge (5) rather than Pt a point at the base of the charge.This has the effect of increasire the apparent length of thecharge. The experimentally derived radius Is 1.09 times greterthan charge length for the 25.4 =m and 50.3 mm charges, and1.07 and 1.14 times larger for the 101.6 mm and 20.2 mr, chargesrespectively. If the initiation for all the charger were thesame, the !agest deviation from the geom.etric radius wouldoccur for the -malle-t length charge. However, the initiationfront is dependent upon the detonator (Firs. 3 and 4). As aresult the Initial wave front In the tetryl is not planar, neednot be synmetrical, nor need it be initiated over ths samecross-sectional area for each charge (See Fig. 4). Thus themode of initiation will. affect the measurements. A conbinaticnof this experimental variation and the )recision of themeasurements can account for the apparent small departure ofthe detonation front curvature from spnerical expansion(FIE. 7).

As the 0n-th o'f the chrr.e Increases, the radii o!curvature continue to Increase. A 'steady state" rd's which

* Continuous sphertc:}- erpanion Is to Le expeoted if thereaction zone of tht; explosive hat :;ero 'Uilcknesz In til.case, no rarc'actionn enn catch up to (and at:'e(t) t.croaction ::one.

12

I INOLTR 65-33

\4

a

C

"\ z

13

! Jlh

NOLTh 65-33

does not Increase witl an increase In chare ler.th was notobtained for the rarm.e of ;haret studied. because no signifcant departure ra.i the curve for spherical expansion could beobserved uip to (L/D) - 4, the ezi.tence of such a rteady stateradius or curvature appears dub-ous. However, such a radius ofcurvature (constant, at an L/D q.reater than 2 to 3.5) has beenreported for a number of "ideal" explosiver (3).

The Effects of Dooster Shape. Sze.and Confinement or theDetonation Front

The ptkyical states of the three boosters are quivedifferent: a bare cylinder, a cylinier confined by a 1/2 Inichthic: steel wall, and a truncated cone whose mass is about 1/3the mass of the c:linder. For a charee length of one radius(25.4 r£..), the curvature of the detonation front should be t"esame for the c::lindrical charges (confined and unconfined). Itis only after the front has traveled 25 ,4 mn or more that theinfluence of the envi,%nment, giving rise to rarefactions forthe unconfined charg-,e and shock reflections for the confiredcharCge, birht become effective. In zhe conical charge, thedetonation reaction Is zubjected to lateral rarefactions almostfrom the inztant of Irtiation. The effects of these parameterson the shape of the detonation fronu are compared in Figure 8,which displays radius of curvature as a function of length foreach of the different charges.

Considerin the.large differences in the boosters, theresultant chazEez in the chape of the detonation front .Pin.. 8)are relatively small and are of the same size as the experimen-tal error. The apparent differences at (L/D) , 2 are, however,generally 'n the direction to be expec ed for rmall effectz ofgrcatcr lateral rar'-faction in the cone and lesser lateral rare-faction In the confOlned cylinder an compared, In both cases, tothe unconfined cylinder.

iffect of Boonter Chaniez on Exnlo-ive LoadiW,

2o observe the effect:; of a variation in booster configur-ations on the pressnure or Ir.ipu. .e loads produced by boosters,the attenuations of non-zeactive shocks caused by the booster!oadiir of ?lexiglas rcy!. (See P '. 2) were -measured andcompared. The eype-.Wental date (Tab~es 5-1l) were numericallycurve fitted, The renult.itne distance-time equations weredifferentiated with respect to time to obtain tPe shock velocityin the Plexi-laz. Cor.ent procedures far te data reductioa arreported in .reater detail In reference ., App. UI.

I II I II I I II I I I I I14

NOLTR 65-33

0 d0

11

NOLTR 65-33

Olven taw Nigoniot relationships for Plexiglas, whichrelat particle velocity,, shock Velocity and shocik pressure,it is possible to compar'e the shock pressures obtai~d in the'leoxftlao cylline as a function of the booster used. JSwever,the accuracy of the available *Verlmental M~onioto relatingshock velocity and particle velocity am' questionable. More-over, because of the caculation required to derive the ahv~*pr'essur'es from the velocities, the errors usA. In readirMthe experimiental data sand obtalnift the shock velocities arethen wagalfied by diffewlz iwnts; throughout the pressureraaW studied, Corsequently, shock velocities rather thanpressunes a&e coand here.

The experlsor-tal. shock volooitler as a (unction of timIn Pieziglas shocked by charges of different lengths sumr givenIn Table 13 said are plotted In FIgures 9 1 2. 2he value atzero time, i.e. at the tetryl-Plexiglas Interfaces in anextrapolated value. Mw first epewliontol aeasuement in theP2@lxglas was nod* at sbout 5 no from the interface. At thispoint Ow precision of the velocity Is believed to be &Icu+ %; however, the error decreases with an Increase In the'Tei'Wth of the rodj, and Is soroxuftely + 0.1 -0,2% W. 100-of Plexiglas. The tloo-dependent shock pressure nWitude Inthe Plexiglas will depend upon the ispedanee mloitch betuwenthe tetryl detonation products and Plexiglas and on the cowplete pressre *time history behind the detonation froat, For agiven booster in which the steady state has been achieved, thepressure. tim profle* behind the detonation front may be dividedinto two time Intervals, The first it a short period of lessthan a microsecond in whch the high shi)ck pressure (von Nournnsplike) at the de;onation front falls to the letonatior pressureat the end of the reacticn zone (ChapmanJouget point), In thesecond Interval, which is much longer than the first, thepressure falls from! the C,3. pressure to an ambient pressure.Theortically,p the first Interval is reproducible,, but thesecond may not be, as It depends upon six*, shae and/or con-f ttnet of the bouster,

When the pressure-tire profileo behind the detonation waveis very st*", the velocity of the shock In the Plexiglas willattenuate extremely fast within a short distance past theInterface, The Initial and steepest portion ^f the atteniuationcurve will le relatively close to the vertical axis ofFigura9 - 12; the most rapid Attenuation occurs before thefirst experimental observation at 5 m, Thus azr extrapolationback to zero length of Plexiglas will not follow the trueatter-asion curve and will Yield a shock velo~ity uhich Islow, than the actual shock velocity at the Interface. As thepressure-distance profile In the booster becomes less steep,

16

momnd~,

i.e, tON booster Is 1me.the attematon rate of the shockin the Pilgft s is rebedamd the relative error in the eztmsp-slee dok W3laety at Wis ft ee is smaller. of course Itnever wrll0010100 tIN P2e6s~6 treaMM5tted 1W the Von sNOMMO

an.-, but It my apposh that camosi by the C-JT pressure IntieoMater.

U ech of Flaw**s 9 3ie 10, the attenuation camue ame.~edfor booer having s p try bet 6ifftt

leat"s. Ia bowh cases, cylinder Wg.9 aed oe (ig. 10),the sMca velocity at 5 M a oFlga Incresed witsh anImereeSe In cMWa lasso. th curves an shinm 22 dashed. linesIn M I laerval 0 to 5 m Ploxlglas. Sw dashes lafioste thatthis portion of the crvem remilts from extrapolation into arqiAM WWI* .340r2sita rmits could not be obtaime. veknow that this Portion of Us cume is fIcttious bdicause the

IbR r V.uesur@ trammats6 ftem the tetW.i boosur mest, Inevewy case, be theNme. am** the attenutionim n W

W tf Sv"l follow t1W qualitative pattern 1016108,106 Obooster lenth of the steepness of the Tayor

folow1eing the deteMUOtl: greatest attenution for theskutest booster.

Vithin the reglos of shock travel greater thena 5 -m IP152-glae, the rates of tt ationan approw.iztel, the sow foran1 thee booster loa~ths. Of course, t tneg averageattesuation over 5 to 70 sm path ise "ete . M oqesI tbhooster. but this results fro o w l the pressure dofire thee Initial pressure vbich is much iowr thenthe actualU m proesre.

Mr the asgion 5 to 100 M Plexiglas, Pigs. 9 sam 10 showshock volocity (and pressure) decreasing with path length utilthe @=ars from different lsuwth boosters becom svermstallycoincident at about 50 m and above. In Pig. 9, the tirwecurves do not ohmw as smooth a tred wi1th variation in boosterleOth as would be Oepefted; In particular, there seems to beno levelling off of the Initial (extrapolated) values With

Inceasngbooster loath, as would be seted. lfw middleCurve (parallelin the lower cuve) bosis to be slightly tippedso that it Is too low at the bomaisry sad too -.A- at 50 M amdmosSO. Us calibration curve for the standard booster (50.8 meleft. 0-10) a 1) a" derived from the greatest ismetr of shots;(five), and has beef checked by Liddlardts wor (7). Nee* the

Moret parallelism between this curve and that for the 101.6sfbooster PrIbably arises from errors In the latter curve; the

affet of the erroro Is to produce too mll a slop. In theinitial Part of the curve.* Additional evidence or teismapearsin the comparison of aalogous curves for cones and cylinders.

Fgure 11 compares the calibration curves for the threeboosters of 50.2 = leungth. The three curve: are, withinexperimental error, coincident for the first 50 = or ah'ocktravel. Plguro 12 makes the corresp o -Aia cor~mr1 eon~ for101.6 am come anyt cylinders. Although there appeara to be a

17

SOLTR 65-)'

4I

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] NOLTR 65-33

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NOLTR 65-33

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NOLTR 65-33

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15

NOLTR 65- 33

a gree'ter difference than In Fig. 11, it is still withinexpe:vimental error. Moreover, the apparent difference (strongershock from cone than from cylinder) Is, In this case, In thewrong direction. Since the curve for the 101.6 m cylinder isalready suspected to be In error by showing an insufficientlysteep, initial slope, it is a reasonable working assumption thathere, as well as In the case of the 50.8 m boosters, the curvesshould be coincident for the first 50 mm, and that the curve forthe cone hapPens to be closer to the true common curve than doesthat for the cylinder. Substitution of the 101.6 nmn curve fromthe conical booster for that of the cylinder in Fig. 9 i. achange within the experimental error which aligns the data to givesuoother experimental trends. The validity of this substitutionis supported by the gap test results shown in Table 14.

Three sets of explosive charges covering a range in shocksensitivity were prepared. Each was tested for gap sensitivitywith the cylindrical tetryl boosters of 50.8 mm and of 101.6 =.length. For the 50.8 nun long boosters, the corresponding shockvelocity at the end of the gap was taken from the standardcalibration curve because, as argued above, this curve shouldbe the more accurate. With this assumption, the 50% gap valuesobtained by use of the 101.6 nm long boosters then give threepoints on a calibration curve, shock velocity vs. gap thickness,for these longer boosters. Comparison can now be made of thecurve indicated by the gap test values (columns 2 and 3 ofTable 14) with those already obtained for the 101.6 m longcone (column 4) and the 101.6 mm long cylinder (column 5). Itis evident that the curve from the gap test values lies closerto that for the cone than to that for the cylinder.

Irrespective of the extent of the error in one of thecurves, Figs. 9 to 12 supply much of the information sought Inthe study. Figs. 9 and 10 show that there will not generallybe a simple relationship between the 5005 gaps measured withdifferent length donors, The trend is longer gap with longerbooster, but the difference is greatest for insensitive materials(small gaps) and decreases to zero for the more .iensitive accept-ors. Substitution of one booster for another in a gap testrequires a calibration for both boosters to explain the twV setsof results, for they can be correlated only in termo of initiat-Ing pressures (or shock velocities), not by measured 505 gapthicknesses.

Figures 9 and 10 show the calibration curve- for differentbooster lengths converging, and this is the expected trend. Itis easy to see, however, that for small changen in L/V (O.6A7 to1.274), tests over a limited range of Cap might give 5CYr rap

22

NOLTR 65-33

values which differ by what appears to be a constant thickness,within experimental error.

Figure 9 shows that the boostering effectivensss increaseswith charge length, and that it is still increasing at('ID) - 4. If the suggested correction is made to the middlecurve, 1.e., substitution of the curve obtained with the101.6 ---m cone, the rate of increase is beginning to fall off at('ID) - 4.

Figures 11 and 12 show that the shock waves produced bythe cylindrical and conical tetryl boosters of equal L/D are,within experimental error, the same for path lengths of up to50 m in Plexiglas. After longer paths through the attenuator,the curves show apparent differences according to the boostertype. The maximum differences at high attenuation are In aregion where conversion of shock velocity (U) to pressure by useof Nugoniot data is inadequate (6). Moreover, the greatestdifference in U is 0.2 wm/isec which is the order of magnitudeof experimental error. More precise measurements of U accom-panied by careful measurements of free surface velocity In thehigh attenuation region might establish whether the apparentdifference is a true one; no further work has been done on itbecause this particular point is irrelevant to the purpose ofthe present investigation.

No experimentally significant differences were detectedbetween the conical and cylindrical boosters of the same lengtheither in the rhape of their detonation front or in the shockpressures their detonation caused in thin layers of Plexiglas.Thus it would appear that in a practical test of explosives andpropellants at zero gap a cylindrical booster may be replacedby a conical booster as lorg as the same L/D ratio is maintained.In the case of the truncated cone, the diameter of the largerbase is used to compute 1I/D.

CONCLUSIONS

Several observations have been made, These are:

1. There is no significant difference between tetrylboosters, in the form of truncated cones or cylinders of thesame length, in either curvature of the emerging detonationfront or axial stimulus delivered to the acceptor at zero gap.Hence for large scale shock tests it is preferable to use acone rather than a cylinder to reduce the weight of therequired explosive charge.

23

I i INOLTR 65-33

2. Boosters of the same length but different geometryshow similar shock attenuation In Plexiglas up to about 50 mmthickness of the attenuator.

3. There is no simple way to correlate gap test resultsobtained with boosters of different lengthe without calibratingthe booster-attenuator systems.

4. Although Increasing booster length increases themeasured 50o gap, the same initiating pressure for a givenacceptor is measured in either case in the range L/D & 1.

5. The booster effectiveness definitely increases withlength. It Is still Increasln at an L/D - 4.

6. The curvature of the detonation front in a finite,approximately point initiated charge shows no sign of attaininga constant value up to L/D - 4. Indeed, it is still following,within experimental precision, a spherical expansion.

ACKIOWLEDGEMENT

We wish to acknowledge the invaluable assistance andguidance given us by Dr. D. Price and Mr. J. W. Enig.

24

I I I II ,I

t " INOL!R 65- 3

(1) i 1os es Hazard Classification Procedure, hWeps Inst81*o.3# Jtly 1962o

(2) D. Price and I. Jaffe, ARS Jourml j, 595-99 (1961).

(3) N. A. Cook, 0. 3. Horsley, R. T. byes, W. S. Partridge,and W. 0. Urenback, J. Appl. Phys. j, 269-277 (1956).

(4) E. H. Xyster, L. C. Smith, ad S. R. Valton, 'heSensitivity of High Ibloslves to Pure Shocks", IOLM10,336, July 19419.

(5 A. R. Clairmont and 1. Jaffe, "Analysis of the OpticalDetemInation or Detonation VWlocity In Short Charge.",NOLTR 6-23, Nay 1964.

(6) I. Jaffe, J. Toscano andt D. Price, "Behavior of PlexiglasUnder Shock Loading by a Tetry1 Donor". NoLo 64-66,July 1964.

(7) T. S. Liddlard, Jr. and D. Price, NOLU 65-4, in press.,

25

mmJ. 65-3

If . 0 & 0 0 0 0 0 0 Ali in 0 0 C4 0 t- 0ten 0 i00

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NOLTS 65-33

TME 2 - Shock front Profile - Unconfied Tetryl Cyll "ers(50 m long),,t A 16 B! _ 24 Expt - t A- 132Disance TIM Distance aI anat -fiIii-e~~L..C_5 -L~a mawe c r *~'~~~o IIO o.., " .o ,., seo e+.

25.0 0.70 25.0 0.76 25.0 0.73 25.0 0.7623.6 .64 22.5 .64 22.5 1.60 22.5 .6421.6 .53 20.0 .51 20.o .50 20.0 .5119.4 .4 I7.5 .38 J 17.5 .39 17.5 .3816.6 .33 15.0 .30 15.0 .29 15.0 .3013.8 .23 12.5 .22 12.5 1 .21 12.5 .22

1.1. .16 10.0 .16 I 0. .13 10.0 .16j9.3 .09 T.5 .09 T.5 .08 7.5 .096.8 .05 0 o 0 0 0: 0,14:4 .o3 7.5 .08 7.5 .07 7.5 .08,1 5 .01 10.0 .15 10.0 .11 .o0 I .15:0 0 12.5 .21 12.5 .17. 12.5 1.211

1.4 .01 15.0 .29 15.0 .25 ' 15.0 .2 j3.0 .01 17.5 .9 17.5 .36 17.5 .39'5.0 .05 0. .50 20.0 .47 20.0 .50:7.9 .09 22.5 1.61; 22.5 i.59 22.5 .110.3 .14 25.0 .76 25.0 .71 25.0 .76'12.8 .21 615.3 .30 117.6 .40 I19.8 .14822.5 .631

27

I I tiNOLTR 65-33

TAMI. 3 - Shook Pront Pzotile - Uncontlned Tetryl Cylinders(101.6 = long)

zipt A-22 Fxpt A-23 Expt A-24m aSOC ILSWO m ILmec

25.0 0.36 25.2 0.41 24.6 0.3521.0 .25 22.0 .34 22.0 .2918.8 .20 20.0 .27 19.1 .2216.0 .13 17.2 .19 17.0 .1613.6 08 15.1 .14 14.4 .1311.1 .05 12.2 .10 12.1 .08

0 0 9.8 .05 8.3 .068.4 .o5 7.3 .04 5.1 .0310.8 .09 3.4 .01 0 0

13.2 .15 0 0 4.6 .0215.7 .20 5.7 .01 7.4 .018.1 .27 8.5 .03 0.6 .0820.7 .313 12.2 .07 13.5 .1423.0 .39 14.8 .11 15.4 .1825.4 .47 17.1 .16 17.4 .22

19.7 .23 19.7 2021.9 .29 22.4 .3725.1 .37 25.1 .45

28

r,/ !I

,I INOLTR 65-33

TABLE 4 Shock Front Profile - Unconfined Tetryl Cylinders(203.2 mm long)

Rt.._No, A- 47 A-48 i A5£xN A-4 A-52

Distance Time Tim Timemr se c jLbOC gsec

25.4 0.20 .19 .21

24.1 .18 .18 .2022.9 .17 .15 .1822.0 .15 .14 .1620.3 .14 .13 .14

19.0 .12 .11 .1417.8 .11 .11 .1216.5 .09 .09 .11

'15.2 .08 .08 .0914.0 .07 .06 .0812. .o5 .06

of.054.011.4 .04 .04 .05

10.2 .03 .03 .04

0 0 0 0

10.2 .03 .03 .0411.4 .05 .05 .0512.7 .06 .06 .0714.0 .07 .08 I .08

15.2 .08 .08 .0916.5 .09 I .10

17.8 .11 .11 i .1219.0 .13 .12 I .12

20.3 . 1 .13.

22.0 .15 .15 .1622.9 .17 .16 .17

24.1 .20 .19 j.oL25.0 ..

29

Now-

NOLTR 65 .53

TABL 5 - Shock Front Profile Confined Tetryl Cyllnderz=.(25.4 mm lonr, and 50.S rm lonr)

Lenth 25 .4 Run 0 mm Expt 1:o. A-125 A-153 T 4 xpt No. A 69 A*71 A.74Distance Time Time Time Distance Time Time TirmeM. . seec .. see e E! Lsec ; sec . isec ___l

250 .'7 1. .3 5.4 0.66 0.82 ~1 f1. 13 .A 22.9 .54 .6H .55

20.0 3.01 ' • .91 20.3 .4 .56 .441175 .: "- •0 17. 32-. 5 .32.51 15.2 .21. . .2

10.0 .22 2 10.2 .11 .t_. .11.: .12 l .!i .12 0 -

0- #10.2 .14 .12 .17" " .5 .11 . .12 12.7 62 2 -, 2

10 00 -X 70II0. "" -"i - ± . 15.2 all .26 .*11a. 7.: zi . !' .2 17.S .40 .3715.0 , .( , 20.5 .52 .415 .5117.5: .:2.90

20.0 . .90 .9, 25.4 .42 .70 .i o

• CorInement consi='z o/" steel tube 12.7 r~i thick

'0

NOLTR 65-33

Ta 6 - Shoec Front Profile - Coaftned Tetryl Cylinders(76.2 m and 101.6 mm long)

I* th -- 76.2 m 101.6

Expt No. A-170 A-171 A-172 p t No. A-127 ,A-129 A-137T. = ... = -- ': -- = .... - .... .Diatza= Tim Tim jTim Distance Timj Ti* JT±mi

isee gasec gaSOC__ I same* jIme * Asc25.4 0.55 0.54 0.45 25.0 0.40 0.39 '0.

22.9 .44 .45 .36 22.5 .33 .32 .3420.3 .34 .36 .26 20.0 .261 .26 .2117.8 .26 .27 .20 17.5 .21 .20 .2215.2 .18 .20 .1041 .15 .15 .1512.7 .13 .l5 .09 12.5 .10 .09 .1110.2 .08 .10 .04 10.0 .07j .07 .077.6 :04 _o6 .02 1 7.5 . 0 31 .02 .045.1 .02 .03 .01! 0 - .0 - 7.5 .03 -!.5.1 .01 .02 V&.O 10.0 .07r .08 .07(

7.6 .0 .08. 125 .09 .11 .1010.2 .07 .08 .12; 15.0 .I .15 .1512.7 .11 .1 1 .17 175 201 .20 .2015.2 1 .17 .191 .24 20.0 .261 .26 .261.8 .2 .251 321 2251 od

17 . .: .32 .40 25.0 .422.9 . 4' .2 .81

25.4 49 -558 2 L J

t5

I0LIR 65-33

TADNS 7 - Shock Fnt Profile - Uncasfined Coiw(25.4 mm, 50.8 t and 101.6 = long)

tamth 25.4 m 50.8 - 101.6 ...

Disanc Time Ti"u Tim Tla* TIUm Time jTim Tim ITim-- m p se ,,, ec I t I uc ilsc I LS@ c s | i ec ILsC ILs-,

25. 1.1111.4 1 04 :7 0o.76 0.39 0.47; 0.37622.9 1.06 1.16 1.18 .61 .31 .3 .2720.3 :8 . 9, &.96 : 49 .. 51 .201 7 .S 6 4 " T 4 ". 3 8 " 3 " 3 1 8 2 3 . 1 15.2a -9 .-58 .i57 .27 .q .3 .14 .18 .101

12.T .35 .44 i .4 .i .19 .19 .0- :13 .081ii -10.2 .16.0 .08 08 , 0

76 .4 .3 z3 .3

7.6 IT .16 IA. .08 .0 . .o10. 30 it -2, .2 .4 .4 . .0i0 1

115.2 , 58 .2 1 .44 -3C .3 .32 .16 1.15 ,.7 15'.142 .42' .145 .22 .21j .2711120.3 1 .95 .3 j76 .53 e5 56 .0.29 3

2. 1.81-7 .98 .6T .68 .6 38 .37 it .84514 __ __1c-4 1.40 1.30 (1.16 .82 .8o _ .83_ AT___.

*APex 9.5 madiameter - Niue 50.8 m diameter

-92

NOLTR -35-33

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B;OLTR 65-33

TANX 9 - Shock Atteruation in Plexiglas - Tetryl Cylinders -Unconflned (101.6 m and 203.2 mm long)

50.8 mm clia x 101.6 ma long 50.8 m dia x 203.4 mm longExpt A-169 Expt A-140 Expt A-177 - Lxpt A-180

Tim1 Distance Tima Distance Tim Distance I Time I Distance'sec m m jsec m 4aec ma ! 4 ±ec =

0.86 5.0 0.60 3.4 0.55 3.2 0.55 3.21.79 10.0 1.83 9.7 i l.12 6:4 1.111 612.77 15.0 M.6 16.o 1 1.67 9 95 1.67 S 5

3.82 20.0 4.-46 22,4 2.28 12.7 2.26 12.74.96 25.0 5.74 28.8 2.90 15.9 2..37 15.96.10 30.0 7.28 35.1 3.51 19.0 3.43 19.07.34 35.0 8.91 41.4 4.13 22.2 4.10 22.28.66 40.0 10.76 47.8 4.74 25.4 4.7 25.4

110.09. 45.0 12.71 54.2 5.44 2S.6 5.40 28.611.50 50.0 16.60 66. -6.07 31.8 6.07 31.8

13.01 55.0 23.61 79.6 6.50 74.9 6.80 3".914.53 60.0 24.71 92.2 7.58 39.1 7.54 3a.116.04 65.0 28.85 105.0 3.34 41.3 8.34 41.3-17.55 70.0 9.20 44.4 9.15 u.4

19.12 75.0 10.04 47.6 10.09 47..20.74 80.0 10.93 50.8 11.00 50.22.39 85.0 11.96 54.0 12.01 54.024.02 90.0 12.89 57.1f 12.98 57.1525,63 95.0 13.90 60.3 13.95 60.3.27.27 100.0 14.83 63,5 14.88 63.528.75 104.L, 15.79 66.7 15.90 66.7

16.76 69.8 16,87 59. I17.72 73.0 17.38 7o.018.68 76.2 18.54 7.219.70 79.4 19.58 79.420.74 82.6 20.89 ,,.t -

21.'14 85.7 21.90 ;5.722.78 M.9 .' _0.9

23.78 , 92.1 ) .95 92.1

21. I 95.2 2'.00 5.02, I .,9 2 o o .

0. 400 5%.42h,.96 ' I01.,, ' 27.CQ 101.

L ] ?2".C? i 10 . [I2 . I ';., ]

NOLTR 65-33

TABLE 10 - Shock Attenuation in Plexiglas - Tetryl Cylinders -Confined (50.8 mmu lor)

50.8 =- dia x 50.8 mm long in 12.7 mm thick steel

E ____t A-173 Expt A-174Time Distance Time Distance

Iec m sec mm

0.92 5.0 0.91 1 5.01.94 1 10.0 1.95 10.02.97 15.0 2.97 15.04.11 20.0 4.12 20.05.30 25.0 5.30 25.06.56 30.0 6.55 30.07.7- 35.0 7.79 35.09.12 40.0 9.16 40.010.55 45.0 10.52 45.011.95 50.0 1>.02 50.013.45 55.0 13.51 55.014.92 60.0 14.92 1 60.016.46 65.0 i 16.48 6 E5.017.95 70.0 I 17.96 70.019.53 75.0 19.52 75.021.02 80.0 2.07 80.022.57 85.0 22.60 85.024.13 90.0 24. 14 90.025.71 95.0 25.72 I 95.027.32 100.0 27.24 I100.028.93 105.0 288 1 101;. 0 o.

NOLTR 65-33

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YOLUR 65-33

D.L EXBONNo. of

CPZA (Distribution List) *............... 132Director, Special Projects OfficeWashirgton 25, D.C.

Code 20 ....................... 4Code 271 ......................... 1Code 2710 ...... 0.000*.*... ..... *...*..*........... 1

Chief, Bureau of Naval WeaponsWashington 25,, D.C.DIS-3 **.*.**. 4

Cowimnding Off icer, Naval Prope.llant PlantIndian Neaad, MarylandLibrary Division I..................Process Development Dlvii.lon I............

Comimanding OfficerNaval Explosive Ordnance Disposal FacilityIndian Head, M~arylandLibrary Division ............ 0...1.....*.

U.S., Army Eneineer Research -id DevelopmentlieFort Delvoir, VirginiaSTINPO Branch *......o* *......*......o..e....*e0*. 1

V.S. Bureau of Mines4800 Forbes Street, Pittsburgh 13, Pennsylvania

Dr. C. M4. Mason o...........o.o.o.................... 1Aerojet-General Corporation, Azusa, California

Aerojet-General Corporation, Downey, CaliforniaDr. N. J. Fisher .................................... 3

Hercules Powder CompanyAllegany Ballistics LaboratoryP.O. Box 210, Cumberland, Ma"land

Mr.* Robert Richardson 090000000000040000000000000*000Dr.* Eyler .... . ......... ............... 0000 1

Director,, Office of the Secretary of DefenseARPA, Washngton 25, D.C.

Dr.* John F. Kincaid .................................Atlantic Research Corporation812 North Fairfax Street, Alexandria, Vir7;iniaDr,* Andrej Vacek ..................

(1)

B INOLTR 65-33

DISTR1 ION(Cont)

1o. *f

University of Cal. Lawrence RadLatLon Lab.P.O. Box 1663, LoS Alamos, New MexicoDr. L. C. Smth I..................

Space Technology LaboratoryP.O. Box 95001, Los Angeles 45, CaliforniaNr. H. A. Taylor ........................ I.... .

Aerojet General CorporationSacramento, CaliforniaD r . W . K i r c h n e r ......... .. .... .... .... .... .... 4

Lockheed Missiles and Space CopanyA Division of Lockheed Aircraft Cerporation1122 Jagels RoadSunnyvale, CaliforniaMr'. J. Lightfoot o...................................0Pureau of Naval Weapons Representative(Special Projects Office)Lockheed Missiles and Space CompanWP.O. Box 504, Sunnyvale, CaliforniaSPL-313 . . .. . . . . . . . . . . . . . . . . . .. 2

Bureau of Haval Weapons Representative(Special Projects Office)Aerojet-General CorporationSacramento, California

SPIA-30Dueau of Naval Weapons Franch RepresentativeAllegany allstics Laboratory3Il30 **000000 ... 0................................... 2AeromnutronicsA Division of the Ford Motor CoManyFord Road, NWport keach, California

lq. V, Wellesr ....................................... 2N . N. kN er *.*. ................. ... . ... *. . . 1

Roha and SniCqaiReda one Arsenal, INntsviile, Alabama

Dr. N. Shuey .......*.....*......................Cosmnder, U.S. Naval Ord~nance Test StationChraLake, Californi a

Aimed Services Explosives Safety Boardaaildirg T-7, Gravelly PointWashington, D.C.Nr. R. C. Newman .......... *.......................

(2)

' I

NO.';R 65 3

DISTIBMXION(Cal 0)

No. of

Stan~ford Research InstituteLiquid Propellant DepartmentPropulsion Services DivisionNenio Park, California

Dr. A. B. mster I.................Defense Documentation CenterCamron StationAlexndia, Virginia ................. 20

Office of Naval ResearchWashiz~ton 25, D.C.

University or Cal, Laurence R1 'nLaboratoryPO. Box 1663, Los Alamos, gt; *-"xlco

(3)

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-22 M9/222 1/M00/0.11____

Owallf led reqesters ww obtain espies or this rawor trre m.

IS aIV ow Tpz'ese of' this Oet No to examin aw effet orGON'taft eSIOO IS 6190, Shps, and 0rSSfiMt 00 00 efteeti100110e

tetryl boosters. Itfoctiuws use j -d% a twouep %u: mebooter's swr0311tiomf to a pu1-mv.6oevvrtor me tv its laitiat-in atu'sgthe Cem0esqu0e6t n ose s ats isd ur or mnnpumo-ity (radius of ev~atm) or me detowstimn tre emrgin "M no

%or md of the ShO V01AoitY T dfutabfe OWM3e Or tbf Nireft-o ditubof it Cowsed In fleziglas.so waft min onfinement Ad *w of two-losk diem

bfsters" earnedw - sgafie e in eitkow perfeumne property.in beostet 1ei~oh, hivr, had a Marined effect. hster

ieosIncreases wt nrsi lewfthsad is still fteseatoontion f~ Is seustaint at A(4 & 3 sad that boseter streath

a cOastant at 1/4 & 1.5. t validity or main~ trueated onomeIn plase of oylieiea bovelers in laure-soa1. field tests of dot..-abiltY Us Osmftimd. Sovariation or 50% sap thickness W.Ahbosoter leIqth (sa cor-seadift lwrarisinoe or critical inatirg

a Sem test neterial, was qusatitatively weinsd.

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