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AD-A105 905
UNCLASSIFIED
BULOVA SYSTEMS AND INSTRUMENTS CORP VALLEY STREAM N Y F/6 19/1 DEVELOPMENT PROGRAM OF DUAL MODE IMPACT DELAY MODULE FOR ARTILL—ETC(U) DEC 79 G THOMAS DAAK10-78-C-0269
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fEND t>«TI Fll«D
II-.81 OTIC
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\0 ©
10
LEVEl/ 2
DEVELOPMENT PROGRAM
OF
DUAL MODE IMPACT DELAY MODULE
FOR
ARTILLERY FUZES OTlC
r FINAL TECHNICAL REPORT
Prepared for: US Army Armament R&D Command
Dover, New Jersey 07801
Prepared by: Bui ova Systems & Instruments Corporation
P.O. Box 189 Valley Stream, N.Y. 11582
Contract No. DAAK10-78^0269
OCT 2 1 1981
H
>QD[L©W/Ä\ SYSTEMS & INSTRUMENTS CORPORATION
81 8 18 066 ^•^-*_... "-"- - --'.." "'—W*
BULOVA SYSTEMS A INSTRUMENTS CORPORATION
DEVELOPMENT PROGRAM
OF
DUAL MODE IMPACT DELAY MODULE
FOR
ARTILLERY FUZES.
JFTNAL TECHNICAL REPORT
/ / I /• " . i! I J
Prepared for: US Army Armament R&D Command
Dover, New Jersey 07801 Y*
l/J Prepared by:
Bulova Systems & Instruments Corporation P.O. Box 189
Valley Stream, N. Y. 11582 ' • /
Contract No. DAAK10-78-C-0269
Submitted by:
£v ̂Vtv^k!':
G.y Thomas roject Engineer
Approved by
J. J. \Jlsi Manager, Productiorf^Engineering
/ ,
•~MMH
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BULOVA SYSTEMS & INSTRUMENTS CORPORATION
TABLE OF CONTENTS
I
Section
1. 0
2.0
3. 0
3. 1
3.2
3. 3
3.4
3. 5
3.6
3.6.1
3. 7
3.8
Title
INTRODUCTION
BACKGROUND
SCOPE
Stresau Report
Phase I - Environmental Tests
Phase I - Ballistic Tests
Phase II - Environmental Tests
Phase II - Ballistic Tests
Phase III - Environmental Tests
Phase III - Environmental Tests
Updated Design
Phase III - Ballistic Tests
Conclusion
Page
1
3
4
5
19
26
30
33
39
47
52
86
I
I
Figure 1
ILLUSTRATIONS
Section View
Dual Mode Assembly
"itÜf G*AM DtlC TAB
justification-
By—— DW**i*«»' - ; YvaU^iUt? Co*«»
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BULOVA SYSTEMS A INSTRUMENTS CORPORATION
1.0 INTRODUCTION
This Final Technical Report is prepared to summarize the progress on
Contract DAAK10-78-C-0269 covering the period from 27 July 1978 thru
31 December 1979. The objective of this effort was to improve the develop-
ment of a Dual Mode Impact Delay Device (previously developed on Contract
DAAA21-77-C-0080) thru a hardware analysis phase to demonstrate design
confidence and reliability of performance in the artillery firing environment.
See Figure I for drawing of the latest configuration.
.
I I I I
•
I I
Retainer, Slider Spring KB-89604
Spring,Firing Pin KB-88096
Spring, Slider KB-89177
Ball, Firing Pin (2} MS19060-405
Pin, Restraining (Assy only)
Housing KC-87901
Spring,Plunger KB-87910
Holder, Firing Pin KC-89493
Plunger KD-87903
Slider KC-87904
Ball, Slider (2) MS-19060-4807
Lock,Detent KC-89183
Pin, Pivot KB-88587
Cover, Housing KC-87902
Firing Pin KD- 88579
Retainer, Detent (2) KB-88589
Spring, Detent (2) KB-89176
Detent, Spin (2) KB-88580
SECTION ROTATED 90°
DMID CUTAWAY VIEW Figure I
2
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BULOVA SYSTEMS A INSTRUMENTS CORPORATION
•2.0 BACKGROUND v The Ml Plunger Delay Element currently in use on artillery fuzes is limited in
usefulness due to the fixed pyrotechnic delay time employed. The effect against
thin targets is that the round can pass thru the wall of a typical thin target, go
thru an empty space and enter the opposite wall before detonation. The effect
against thick targets is that the round will detonate prior to penetration of the
wall into the occupied space. Both cases illustrate less than optimum effective-
ness against all possible target thickness.
I The Dual Mode Impact Delay provides a delay proportional to target thickness
so that detonation occurs as a function of target penetration regardless of thickness.
This is accomplished by sensing the deceleration on impact. Upon reduction of
deceleration force to a level corresponding to target penetration, the unit senses
this and detonation occurs. This mode of operation therefore provides optimum
projectile effectiveness regardless of target thickness.
. , - • - - ÜI
*•
I BULOVA SYSTEMS t INSTRUMENTS CORPORATION
3. 0 SCOPE
The Scope of Work for this contract was divided into 3 phases with each phase
having specific improvements incorporated and tested for sensitivity, environ-
ment and ballistics. Each are discussed below.
J In addition, as part of Phase I, a study was conducted/by R. Stresau Laboratory to'
A- Evaluate sensitivy of the M55 Detonator by means of a flying plate test
and compare with the sensitivity of a less sensitive material (lead oxide)
B- Evaluate the ability of a reduced output M99 to initiate the acceptor
M55 Detonator
Results of the above study follow.
I I I I
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1 R. fTRESAU LABORATORY, Inc. MKAftCM — KVCLOMMffT — IVALUAnONI
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Bulova Systens & Instruments 7 December 197<S Post Office Pox lr.q ^'allcy Streams, New York 115C2
Subject: M739 Fuze, Dual Mode Initiation Device P/N KF8S590 Initiation of M5S Detonator by M99 Detonator
Ke: P. 0. 5822
(;en t lernen:
1. Reported herein are efforts to analyze factors involved in the initiation of the M55 Detonator by the M99 Detonator of the M739 Fuze as affected by the Dual Mode Initiation Device P/N KF88590 as proposed by us. This analysis will be based on results of penalty test« in which the test variables will include loading and other dt-sign variables of both detonators and dimensions ol inert components of the system, especially the paths through the DnID with the
>'.,'3Ci set f>r point detonation, as directed in the referenced purchase order.
2. Although, >r t\\Q basis of qualitative cons derations, it seems quit«, obvious that the subject transfer should tu highly fli-tble, quantative assessment of the reliability •a difficult because of the inherent randomness of some of the controlling factors in the transfer process. An exami- nntion of thp design, in the light of experience with explo- sive initiation systens, leads to the conclusion that the agency oi th-s transfer is rapidly moving fragments either of the "retainer" of the M99 detonator or of the point of the firing pin which mijjht be torn loose. When fuze hard- ware, including detonators, became available for testing, it was loe.nd that the point of tin- firing pin was torn loose Csec Photo ViP-l). It is reasonable to assume that the tip of the fi'ing pir is the principal agency of detonation transfer.
3. The angular attitude of the tip of the pin at impact can . be expected to greatly affect its effectiveness in this function. The point of the firing pin is, of course, of the standard design and dimensions prescribed foi firing pins for M55 detonator», which, when initiated as prescribed must fiie reliably on a one inch-ounce impact. it can be expected that those firing pin tips which strike point end first will result in h*>»hly reliable initiation. The two back corners may he near'y as effective, edge on impact less so, and flat normal impvel nay require many times the energy required lor in:fiat ion by < top hitting point fiist. As a result, a very Lar»'< random variation in the tip velocity required for initiation is to be expected.
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I I I
R. STRISAU LABORATORY, toe. — STAR ROUTI — IPOONIR, WISCONSIN
RSLR 78-44 (E-0548-8)
Similar copsidcv.it iun of the comple of factors which nuist affect energy the 1590 detonator to the firing pin doubt that the realized velocity of •V35 detonator also varies over a wi of kinetic energy anong the fragmen tories are necessarily largely rand affect the kinetic energy and momen penetrate the central hole of the f they can contribute to the breaking firing pin tip. The momentum and k are those remaining after deducting impact and the energy required for the firing pin.
xity of the interaction and momentum transfer from tip leaves no room tor impact of the tip or. the
de range. The distributions ts as well as tneir trajec- or.i, particularly as they turn of the fragments which iring pin to fl point where and acceleration of the inetic energy of the tip the losses of inelastic
fracture of the tip from
The reliability with which the M55 detonator will by the M90 Detonator in the subject fuze is th« pr that the velocity with which the tip of the 1!ring exceed that necessary for initiation. It, thus d the comparison ol two quantities each of which, as shown in foregoing paragraphs, is subject to large variation. The extreme sensitivity of the M55 Det combination with observation of substantial damage or insenstivt components wrought by the tiriPi: pin r<4.°.--2) lead to intuitive confidence that the lowes tip velocity exceeds the highest velocity required an M55 detonator. Experimental data in support of fidence seemed elusive from the start and was, ind difficult to attain. A variant of the "Varicomp" used to obtain data which was extrapolated statisti •mtain estimates of reliability.
be fired obab i1i t y pin will
ependf upon has teen random
onator in to inert tip (Photo
t rea1i/ab1< to init i ati this con-
eed, rather approach w.;s
callv to
The "Varicomp" method in of detonation transfer pr the substitution, for an ol another material of di have been calibrated, usi relationship between init of the initiating stimuli! judiciously chosen, it is of initiation of the desi with the surrogate. The in Enclose!-«- A. As i s po is essential to the valid the Varicomp method that closely as practical (in detonation transfer mocha system being considered, by methods <ltich. in effe system as designed.
its broadest definition is a method obability assessment which involves explosive specified in the design, ffering sensitivity. If both mater.al ng the same test, in terms of the iation probability and the nagnitudi s, and if the surrogate has been possible to predict the probability
gr, explosive from results obtained approach is discussed in more detail mted out in References I and 2, it ity of reliability estimates made by the calibration test simulate as particular with respect to the nism) that which applies to the or alternately that data be obtained ct, "bracket" conditions in the
9. ITftHAU LABORATORY, Inc — STAR ROUTt — SPOONER. WKCONfM
I I
I I I
RSLR 78-44 (E-054fi-8)
The choice of a suitable Varicomp surrogate for the M55 was based on a combination of consideration including availability, sensitivity relative to that of the NOL 130 priming nix useo as the prining charge of the M55, and unambiguous response character istics. Of course, any surrogate snould be sensitive enough to be at least reasonably consistently initiated when substituted in the system to be evaluated. However, since efforts to select and calibrate the surrogate (and calibrate the M53 Detonators) were started before receipt of the M9'J detonators, some of the other factors were the subject of experimental effort before experimental determination of per- formance of surrogates in the syscen as designs could be made. The M55 Detonator must (per specification) be initiated by a one inch-ounce impact using its standard firing pin. None of the surrogates which were considered can be initiated by any impact which can be-^administered by a dropped weight on the standard firing pin . Assuming such data to be applicable, almost any currently used pure explosive (including lead azidc and lead styphnate) would be quite appropriate as a surrogate. However, the combination of low velocity and relatively lar^i mass with the nearly pointed firing pin {i1 has a 0.007 flat) rei.ovcs this test so far from simulation * of the subject interface us to destroy the credibility of any prediction made on. this basis. A Proportional Gap Test, with 50 uil diameter donors and M55 detonators as acccplors was pcrtormeu with the expectation that it, with existing stab sensitivity data night be shown to "straddle" conditions at the subject interface. The results of this test, which when compared with existing data*, indicates that even PETN is too senstive for use as a surrogate for the M35, made any effort to realize this expectation academic. It was decided, at this point, to try to simulate the conditions of the system as closely as possible in the calibration tests. All subsequent calibration tests were determinations of the velocity of an aluminum disc 0.01ft thin by 0.075 diameter necessary tor threshold initial iot- ol the M55 detonator or a Varicomp surrogate.
In the calibration tests, the acceptors were M55 detonators m M^S deton.itor cups loaded with candidate Varicomp surrogates. The candidates snrrogates were:
rxp1os ive
Dextrinateit Lead A/.ide PETTI Rarium Styphnate
Lead Styphnate
Source Load ing Pressure
DuPont 30 Kpsi Trojan Powder Co. 30 Kpsi P.. Stresau Lab., 10 Kpsi
Inc. Olim Industrial 10 Kpsi
Preliminary to the calibration tests, each of the candidates was tried as a surrogate in the subject fuze, with the UMID in place ana" set for point detonator.
7
- • - • M^
—.
R. mUAU LABORATORY, Inc. — STAR ROUTE — SPOON ER, WISCONSIN
RSLR 78-44 (E-0548-8)
Pt \io in re T.i/I
Oi Cll 0 7. i r. (!' as da 11)
) n po of i 11
TN t i pa
act nif "1
:i ra idr- Lh
hot a^
ta" i 11 • ti int Lh
i t i
and bai i n i t iated ragraph ion , i n es t at i on ow order ctetizat , loaded e s vs t <'ir. o 348-A) Var icortp , ii won ate itext a t > r uf ed out, v differ .it i or .
urn styphnate were eliminated becaus by the M99 Detonator in the interfa
I. Lead styplinafe was eliminated b the subject interface,was relativel s (see Photo 54P-3) usually refercd detonation" requiring subjective j ion as "fire" or "failure". bextri in !i55 cups and substituted lor M5 ras cons istently and unmistakably
Dextrinated lead azide was, tent surrogate. On the basis of stab s
Id be predicted that any system whi r mated lead azide would be a higlil the NUL 130 priming charge. Howeve such predictions are probably mi sie ence in mechanisms involved in stab
e they were ce as descr1 bed dause its y mild, with to as those udgr.tent for nated lead 5 detonators detonated at ively,chosen ensit ivi ty ch would y reliable r, as has been ading because and fragment
10.
11
1 I
12
In a thirty-trial Bruceton calibration test (as described at lie end ot paragraph 7, Bruceton 54F-4) of M35 detonators tin mean velocity threshold velocity (501 point) for initiation was found to be 1S5 meters per second with a standard devia- tion of 0.0605 log units. By statistical extrapolation as illustrated :n SK 78-4-1 (Enclosure A) the velocity required tor 99.975 (minimum at 95°o confidence) reli.i1 le initiation would be 430 meters per second (see enclosed calculation she« t for Bruceton Test 54R-1).
It was lound that lead azide was initiated test, by a flyer plate impacting at 214 me Thus, a less sensitive acceptor was necess surrogate. However, as mentioned above, a candidates had been eliminated. A few eff desensitize lead azide with «dditives but that the development of a desensitized lea factory characteristics would be a separat rntudo beyond the scope of the referenced The interposition of an aluminum barrier i input surface of the acceptor was used as A series ot experiments were performed to priate thickness of this barrier. In the 430 meters per second served as the criter that the "cut-oft" barrier thickness is be mils and, in five trials with 8.8 mil barr acceptors were initiated. On the basis of it has been shown that, at 95% confidence, velocity (that for 50% initiation), for in ilrxtrinated lead azide with a 8.8 mil cove meters per «econd.
, in the cal ibrat ion ters per second, ary as a Varicomp 11 other aval lab 1e orts were made to it became apparent d azide of satis- e project of a mag- purchase order, n contact with the an additional penally choose an appro- calibration test, ion. It was found tween six and seven lers none of the this last finding, that the mean itiation of the r is at least 430
In tests of Cite subject interface using dextrinated lead azide acceptors with 10.6 mil barriers, the acceptors detonated in four of live trials. In a repeat test, using R.H mil barriers the score was, again, four in five. Combining these data, in
8
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I I
ft. fTUSAU LABORATORY. IM. —STAt ROUT1 — SPOONIR, WtSCOMSM
RSLR 78-44 (E-0548-8)
1 eight of ten trials with aluminum barriers at least 8.8 mils thick, dextrinnted lead azide detonators were initiated by the M99 detonator at the subject interface defined in paragraph 1, above. By binomial statistics, eight successes in ten trials indicate a minimum reliability (at 95% con- fidence) of 4°. 3";, which, for purposes of the analysis such as this, is not significantly different from 50*.. Taken with the results cited in paragraph 11, the foregoing demonstrates that the stimulus transferred from the M99 detonator to the M55 detonator at the subject interface is equivalent to that delivered by the calibration test at 430 lu^Lers per second as the results, given in paragraph 10, of the calibration test of the M55 detonator indicate, the minimum reliability, predicted at 95° confidence when initiated in the calibration ••st at 430 meters per second is 99.975".. It can be predicted, lrom the foregoing,, that the reliability of detonation transfer between the N99 detonator and the M55 detonator at the subject interface should be at least 99.975% at 95°. confidence.
This pred t ions, po tion of h from pena vations a view of t to the MS support o and 548-6 Variconp hear impr impact of
iction, of course, is subject to the mted out in Enclosure A, which apply igh degrees of safety or reliability lty tests performed with small sample re particularly applicable to the pre he probable variability of the stimtt 5 detonator, pointed out in Paragraph f the rationale of paragraph 3, note , which are of the acceptors which fa tests of the actual interface, that bo ints which could have resulted only f the firing pin tips.
usual rescrva- to the predic-
by extrapolation s. These reser- sent case in us transmitted 3, hereof. In in Photoe 548-5 iled in the th acceptors rom flat side-on
Respectfully submitted,
R. N. Stresau
RIN/r.irb
Enclosure A
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.v R- STRBSAU LABORATORY. Inc. — STAR ROUTE — SPOONER, WISCONSIN
I
RSLR 7P-46 (E-0548-8)
T*FFFMi r:cs
Ayv.F, J. K., Unrip ton, L. D. , Kabik, I., Solcm, A. D. , "Vnri- corp, A Method lor I »ete minting Detonation Transfer Probabilities" Nnv'.vcps Report /411, H. S. Navnl Ordnance Laboratory, Wl.it. Oak, .Ml), .latvi.ii y 19«.I .
Ftr"S.iu. It. II., "Development of the Varicomp Method, Expansion of Ap-p i 11 ah • ; ' ty (To Determine Detonation IransCei Prohahi 1; tit*» Willi Redntv d Dependence Upon System Variables) I'art b Analysis >f Data and Presentation in Forms Adapted to Safety and Reli- ability Estimation for Explosive Trains", RSLR 74-4 for thr P.S. '.'.ivil V,-a pins Center, China Lake, California, 5 April 1974.
Hampton, L. D. Savitt, J. Starr, L. E. and Stresau, k. 11. , "Priming F.xplor.ive Evaluation Tests", DavOrd 2P24 I». S. Navord ordnance Laboratory, White Oak, Silver Spring, MD, 19 March 1" ..
ENCLOSURE A
Stie*nn, K. II., I>. II. Chamberlain, M. J. Peslin, "Vuety and Reli- ability Testir.;; oi Fiiz<- Explosive Trains", FSLR /S-4, 10 March 1'»,
I 10
r~ *•
R. STRESAU LABORATORY, Inc. — STAR ROUTE — SPOONER, WISCONSIN
Date
BRUCETOH DATA SHEET No. 548-4
M55 Type of Test Flyinc Disc Item Deton
11/27/78
ator Dv»g He«
Variable Velocity Step Size .02S LOP Units
Criterion of Fire
Disc Materie
Explosives Flash Charge I
Shattered Rotor
il Aluminum Di. . .075 Thickness .018
Lead Azide Base
JOL 130 Int.Charge (PVA) Charce RDX Ace.
Charge Dia or Other Size Flash Charge Base Charge Donor Ace.
Leading Pressure or Density Flash Charge Base Charge Dcnor Ace.
m s \ I 1
j i 11 i : !
Ü .2 i 1
1
1 N i i
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'T1 X 1 1
1 1 i K \ K 0 Ji
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Kf 1 1 i c X 0 i 0 :i :? X A I
'#'7 rfi \
1 .'/ Q 0 . D 0 s d
W<Q< ') o !x i 0 i . 0 i
•*. 7
i
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\g?2 i 1 0 i j
• 1 1 1 i
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11
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R. STRESAU LABORATORY, Inc. — STAR ROUTE — SPOONER, WISCONSIN
BRUCETON CALCULATIONS
'
I
PROJECT jsm. BRUCETON NUMBER S^f-*/
BRUCETCN DATE //A7.'?g
tb&%
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1 n m ni •4 +3 + 2 / A V + 1
0 5 V t
-1 3 -5 \ -2 / -3 y -3 • -3 9 -4
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N '* A -5 B atv X = Xo + d ($ 2 .5)
-./cos **'£ <*$ -V -• /55. oVfa f"/5
» - I - (*> * /33
s a G
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^ 4r STEP
( S ) (step sizeV Ob£
f/S o
MS
CALCULATION DATE J_^_ N/vr CALCULATIONS BY / , •••/ 5
CHECKED ( ? ) ///- I t
T = /.7&
Cx < - ( T ) (ox )-.OJ7*> at 95$ ^>c <^yu^
o- ( cr) ( H I ^j>&t *«%"**- u cr VN *•
o-ff<= ( T ) ( c c ) ~0.057<v at 95^ ^«S u/rUXi
°d
D < , Xs - X - C% « at 95#) •= 3. H$ 7
at 959S 0 + CT « at 9595) (-/**• ^ 3°
Maximum JKCVBy Failure
Rate at 95# Confidence 7 0-0 V3Ö ^ -Ö-ÖDO^
12
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R. STOSAU LAMtATOtY. Inc _ STAR ROUTI - SFOONER, WISCONSIN
RSLR 78-44 (E-0548-8)
Firing Pin (KBR8579) of D::iD KF?.>;r>9() with tip blovn oft by M«»Q Detonator in H73S Fuze
13
WM." WJ m i
IL STRRSAU LABORATORY, Im. — fTAR ROUTE - SPOONER, WISCONSIN
PS LP. 78-44 (E-0548-8)
NT*?' Fustc Rotor, showing dana^c to detonator cup 'which hod been load<<! v»th PF.TT') by output. of r(,r? IVtuniiror filtered through DMIfc iKWWOJ
1 I 14
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it rrmtsAu LABORATORY, inc. — STAR ROUTE — SPOONE*. WISCONSIN
RSLR T*-4'i
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''ii-Ms fjDtT! M73lJ Fny.i s ii whicli {) iX'tonators
I.: <i •i) lirvd with DMUJ 8i*t i"r, pu!nt i> I'tiTfll i-.»n. l.otor at I'll ('.»'rviTS" s:dt-- ol Mill .sh.-.vn in Fhotu 54'-2) had CO«it a i ii"ri Jin ' '• K'UP lond.'d Willi PKTi\ Rotui .it Lit had . »r,| i'n'd all !i'j^ cup loaded with Lr.id SLyphnali
1 5
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It rnttSAU LABORATORY, Inc. — STAR ROUTE — SPOONER, WISCONSIN
RSLR 7fi-4^ (E-054S-R)
Shfl Module of f!7/»y Fuze in which ihr MS!) Ih'fon.lfor h.ld öern replaced with .in }irt5 Detonator (.'up loaded wit!) riix I r i n.ited lead nsiide. The MO'l Detonator had been ii red wiUi the DlilD Jet tor point de tonnt ion.
I I I
16
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ft. ITIUAU LA10JUTORY, Inc — STAR ftOUTf — SPOON ER. WISCONSIN
RSLK 7P-4A (K-0548-S)
I I I I
V-'.tT.t ol Rotor of 11)V) tujsc with Miü •up loaded vith dextrinated lend (acceptor) .')/'. :!•• and covered w: L11 alnr.umii.i lüiiricr. .Vcrpior had failed when Mr.f.' detonator was i i r<-d with DlilU S"t for po'iit. detonation. I'i'tr iiiipviiit of firing pfr point Striking Li.it side or..
I 17
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K. STMSAU LABORATORY. IM. — fTAft ROUTE — SPOONER. WISCONSIN
RSLR 7R-44 (E-0548-P)
I
Barrirr disc from tri;il similar (in both arrangenent and result) to that described in cant ion of Photo 54S--5
16
mmm •"".""
3.2
PHASE I
BULOVA TESTS
I 300 Units Made
100 For Ballistic Tests
100 For Environmental and Sensitivity Tests
All Above Assemblies contained the following:
1. Brass Plungers slotted for ball clearance.
2. Housings and covers modified using government furnished Mi Delay
assembly parts.
3. Aluminum (machined) firing Pin Holders.
4. Other parts used were the same as previous contract (dvvg. no. KF-88590).
METHOD OF TESTING:
All Plunger sub-assemblies were tested for non-arming (11 00 RPM) and
arming (2000 RPM) before final assembly and then repeated after final assembly,
After environmental tests each unit was checked for non-arm position and then
armed. The units were then dropped on a steel plate at a specified height to
simulate ground impact and then examined for function.
19
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tm/mmmm^F -mr-mm^i^^m
PHASE I
ENVIRONMENTAL & SENSITIVITY TESTS
A. Sensitivity Tests - Quantity 20 Units
1. All units passed Arming (2000 RPM & Non-Arming (1100) Tests.
2. After Arming Test, all units were checked for Plunger Freedom.
It was found that 10 of 20 units witnessed an interference between
the spin detents (2) and the shoulder of the Firing Pin Holder when
the Plunger was depressed.
This interference was caused by the accumulation of tolerances on
affected parts plus the inconsistant shape (although within draining
tolerance) of the detent lock (soft tooling and 2 piece spot-welded
construction).
10 of 20 Units were not tested due to above defect.
Unit No. FUNCTION DROP HEIGHT (IN.)
2 3/4 3 3/4 4 3/4 5 3/4
2 No Yes
4 No Yes
7 No No No No '•<
8 No No Yes
10 No Yes
12 No Yes
14 No Yes
15 No Yes Yes
17 No Yes
20 No Yes
20
• !•••»•
^"1 ' W ' • •»—i^^^^^W»^
i I
* FAILURE ANALYSIS ON UNIT NO. 7
Failure was due to plunger spring interference (solid height) with plunger
which did not allow sufficient travel to release the firing pin balls. (2)
To prove this failure mode, the plunger and spring was reassembled into the
housing and the depth of plunger travel was gaged to check functioning distance.
Gage measured . 1 98 travel. A min. of . Zl 5 travel is needed for function.
To correct this condition, the spring lead in diameter on the plunger was
chamfered to allow spring to seat properly.
B. Unit configuration: Brass plunger had taper cut on spring guide end
for proper spring seating. All other parts same as previous test.
Bl. JOLT & JUMBLE TEST 6 UNITS
1. After test all units examined to verify safe position - All OK
2. Verify plunger freedom - All OK
3. Performed Arm/Non-Arm Spin Test - All OK
4. Perform Sensitivity Tests
Unit. No. Test Function Drop Height (IN. ) Remarks
2 3/4 3 3/4 4 3/4
1 ^ No Yes
2 Jolt & Jumble No Yes
3 No No No 1 Slider Ball Released
5 1 No No No Plunger jammed in down pos. approx. .125
4 Jolt Only No Broken Detent Lock - No Test
6 No No Yes
21
<• -, -" -- "- •- —
^mmm 1
FAILURE ANALYSIS
Unit No. 3 Detent protrusion caused interference with outside diameter on
Firing Pin Holder. Holder O. D. to be reduced . 020 dia.
Unit. No. 5 Plunger jamming due to burr on edge of Plunger. Edges to be
radiused on future lots.
Unit No. 4 Broken detent lock was caused by poor spot welding. Parts are
to be 1 pc. construction on future lots.
B2. AMBIENT SENSITIVITY TEST 9 UNITS
ALL UNITS SPIN TESTED FOR ARM/NON-ARM - ALL OK
ALL UNITS CHECKED FOR PLUNGER FREEDOM - ALL OK
UNIT NO.
7 No
8 No
9 No
10 No
11 No
12 No
13 No
14 No
15 No
FUNCTION DROP HEIGHT (IN.)
2 3/4 3 3/4 4 3/4
Yes
Yes
No
No
Yes
No
Yes
Yes
Ves
Yes
Yes
Yes
C. Unit configuration: DMID Units A thru L (11 Units)
1 Firing Pin holder O. D. was reduced .020 Dia.
2. Plunger Chamfered for Spring Clearance.
3. Plunger Spring modified (ends turned outward)
Dmid units 1 t'iru 7 - Same as above except item 1 was not modified.
22
—T-*- "'"' m%!**»
I I I
Cl. Jolt k Jumble Tests - 11 Units
Units A thru L were subjected to Jolt Test. After test all were checked fo*
safe position - All OK.
Verify plunger freedom - All OK
Arm/Non-Arm Spin Test - All OK
Units E, F, G, H k J were reassembled to M739 fuzes and subjected to Jumble
Tests.
After Test, All checks were performed (same as above) All OK except
Unit No. J which became loose during test was considered an overtest.
C2. Transportation Vibration Test - 7 Units
Units 1 thru 7 were subjected to transportation vibration test (Ambient)
All above checks after test were OK.
All dmid units were then armed and tested for Sensitivity as follows:
I 23
«u.
mmm^
I I I !
Unit No.
Cl A
B
C
D
E
F
G
H
J
K
L
Test
Jolt
Function Drop Height (In.
4 3/4 5 3/4 6 3/4
Remarks
Jolt & Jumble
Jolt
No Yes
No Yes
No Yes
No Yes
No Yes
No Yes
No Yes
No No
No No
NO TEST
No Yes
No
One ball released
Overtest
C2 1 TV
2
3
4
5
6
7
FAILURE ANALYSIS:
Yes
No
Yes
No
Yes
Yes
No *
Yes
Yes
Yes ^Plunger jammed Down-No ball Release
H - One ball released during drop test. Firing pin did not release no cause found.
J - Locking screw loosened during test.
K - Unit could not be disassembled - (thread stripped)
I 24
D. Unit Configuration: 15 Dmid units with stainless steel firing pin holders.
Chamfered and radiused brass plungers modified plunger springs (ends
turned out) New detent locks (1 pc. construction)
All Arm/Non-Arm and plunger freedom tests were acceptable.
SENSITIVITY TESTS - 15 Units
Unit No. Test
1 Ambient
2 ii
3 ii
4 II
5 II
6 Jolt
7 II
8 II
9 II
10 n
11 Jolt & Jt
12 II
13 II
14 II
15 II
Function Drop Height (In. )
4 3/4 5 3/4
Yes
Yes
Yes
Yes
Yes
No Yes
Yes
Yes
Yes
Yes
No
Yes
Yes
Yes
Yes
I 1 1
FAILURE ANALYSIS:
Unit No. 11 - Slider Ball came out but did not function. Firing Pin was
depressed slightly and released. Small burr was found on I. D. of firing pin
holder.
25
3.3 BALLISTIC TEST RESULTS
YUMA PROVING GROUND
PHASE I
70 Dmid Units with Brass Plungers (Modified with Exit Channels for Ball
Relief) were assembled to Inert M739 Fuzes and fired for recovery using
the following:
Units 1 thru 35 - 155mm, Zone 2, HQE Set SQ
1 thru 7, 1100 Mils elevation,
8 thru 22 1050 Mils 23 thru 35 1075 Mils
Units 36 thru 70 - 155mm, Zone 7 LQE, Set Delay 315 Mils Elevation.
I I I I
26
I • FUZE DMID SfcA
ÄOUND NO. FUZE NO SETTING FUNCTION FUNCTION REMARKS
• 943
•
1 Super Quick
Yes Yes Plunger Stuck in Down Position
1 944 2 i - - Not Recovered
945
1 946
3 - - Not Recovered
4 Yes Yes Firing Pin in Start Position
947 5 4 k 948 6 Firing Pin in
Start Position 1 949 7 1
1 1 1 950 8
1 !
1 951 9 1 1
1
1 952 10 i 953 11
| 954 12 j
955 13 i
956 14
957 15
958 16 1
959 17
1 960 18
961 19
1 962
963
20
21
1 964
965
22
23
1 966
967
24
25
• 968
969
26
27 I 1 f \
• 970 28 Super Q uick Y 5S Y( SS
I 27
FUZE
ROUND NO. FUZE NO. SETTING
971 29 Super
972 30 Quick
1 973 31 i
• 974 32
* 975 33
• 976 34 1
• 977 35 Super Quick
• 978 36 Delay
1 979 37
• 980 38
" 981 39
1 982 40
' 983 41
1 984
985
42
43
I 986
987
44
45
1 988 46
989 47
990 48
991 49
992 50
993 51
994 52
995 53
996
997
54
55
j 998
999
56
57 Dela V
DMID
FUNCTION
Yes
Yes
Yes
Yes
Yes
Yes
Yes
Si A
FUNCTION
Yes
I
REMARKS
Yes
Yes
Yes
Yes
Yes
Yes Yes
Yes Yes
- -
Yes Yes
Yes Yes
Yes
Not Recovered
Not Recovered
Not Recovered
Not Recovered
Not Recovered
Not Recovered
Not Recovered
Yes Yes
Yes Yes
— - Not Recovered
- V Not Recovered
- - Not Recovered
• a Not Recovered
I 28
HI \ amuamtmMmMä
1 FUZE
ROUND NO. FUZE NO. SETTING
I 1000 58 Delay
1001
\ 1002
59
60
1003
| 1004
61
62
1005
\ 1006
63
64
1007 1 65
1008 66
1009 1
67
1010 68
1011 69 •
1
1012 70 Delay
DMID S&A
FUNCTION FUNCTION REMARKS
Yes Yes Not Recovered
- - Not Recovered
Yes Yes
Yes Yes
Yes Yes
Yes Yes
Yes Yes
Yes Yes
Yes Yes
Yes Yes
No Fuze Heavilv
Yes Yes
Damaged
Not Recovered
I I I
29
•••-
***v9**m*r mmmm
PHASE II
I I I
3.4 ENRIRONMENTAL TESTS
Parts Ordered for 1000 Units
100 Units made for Ballistic Tests
32 Units made for Environmental & Sensitivity Tests.
Assemblies contained the following:
Zinc Die Cast Plungers with Minor Design Changes.
New Design Housing & Cover.
Modified Slider & Firing Pin Holder to Accomodate New Housing.
New Springs for Arming Level of 1700 RPM and
Non Arming Level of 1100 RPM.
One (1) Piece Construction Detent Lock
All Assemblies were Tested in the Same Manner as Phase I.
I 30
i M i
——
PHASE II
ENVIRONMENTAL TESTS
a) JOLT TEST - QTY 5 UNITS
Arming & Non- • Arming Test - Acceptable
Sensitivity
Unit No. Function Drop Height (in. )
4 1/2 5 1/2 6 1/2 1 Yes - - 2 Yes - - 3 Yes - - 4 No No No 5 No Yes -
Failure Analysis: Unit No. 4 when Plunger was Fully Depressed
would not fire, no cause found.
b) JOLT fc JUMBLE TEST - QTY 5 UNITS Arming & Non-Arming After Test,
Units 8, 9 & 10 would not Arm
Sensitivity
Did not Function After 3 Drops
9 I Did not Arm After Test
10 \ Spin Detents were Jammed.
I I
c) TRANSPORTATION VIBRATION - QTY. 5 UNITS ARMING & NON ARMING
Function Height (in. )
5 1/2 6 1/2
TESTS - ACCEPTABLE
Sensitivity
Unit No. Func
4 1/2
11 Yes
12 Yes
13 Yes
14 No
15 Yes
No Yes
31
• i..«—
I I I
1
D) COLD TEST (-45T) 2 UNITS, TESTED IN ARMED POSITION
Sensitivity
Unit No. Function Height (in)
4 1/2 5 1/2
16 No Yes
17 Yes
E) SENSITIVITY TEST (AMBIENT CONDITION) 15 UNITS
Unit No.
18
19
20
21
22
23
24
25
26
27
28 *
29 *
30 *
31 *
32 *
Function Drop Height (in. )
4 1/2 5 1/2 6 1/2 7 1/2
Yes
Yes
Yes
Yes
Yes
Yes
Yes
Yes
Yes
81/2
Yes
No No No Yea
Yes
Yes
No
Yes
Yes
* These Units were Dropped using new M739 Fuze Bodies. The Soft Nose Caps
Cushioned the Drop Force & therefore needed a Higher Drop Distance. All other
Unite Utilizaed Previously Used M739 Fuzes.
32
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33
tMtktm • n ii i •Mi IMM
wn^iP IMPMH
I I 8" PLYWOOD IMPACT TEST
155MM, M109A1, Zone 2, T2 Charge, Target-500 Feet, Fuze Set-Delay, Velocity -780 ft./sec.Quantity - 10 Units.
Round No. 1
Fuze No. 70
2 66
3 63
4 17
5 61
6 10
7 69
8 5
9 68
10 67
Function Behind Target (3 to 5 feet)
8" PLYWOOD IMPACT TEST
105MM, M102, Zone 5, T2 Charge, Target - 500 Feet, Fuze Set Delay, Velocity - 1000 ft/sec.
Round No. Fuze No. Function 1 4 Behind T;
2 16 ii
3 29 ii
4 30 ti
5 2 n
6 9 n
7 22 II
8 21 ii
9 1 it
10 62 n
34
JE*. - ^tmtam
wmmmm m • — '•
PRE-RELEASE TEST
I I
155MM, M109A1, Zone 2, HE Charge, QE-1050MILS, Ground Impact, Fuze Set-SQ, Velocity - 780 ft/sec, Qty, 15 Units.
Function Round No. Fuze No.
1 46
2 88
3 73
4 39
5 89
6 87
7 86
8 34
9 2o
10 77
11 72
12 37
13 23
14 25
15 75
High Order on Impact
I I 35
mmmm "WV ^p
I I I I I
I
I I I
PRE-RELEASE TEST
155MM, M109A1, Zone 2, Inert, QE-1050MILS, Ground Impact for Recovery, Fuze Set-Delay, Velocity -780 ft/sec, Quantity - 2 5 Units.
Recovered Round No. Fuze No.
1 11
2 12
3 13
4 6
5 14
6 15
7 8
8 5
9 29
10 10
11 16
12 4
13 17
14 3
15 45
16 7
17 19
18 20
19 32
20 31
21 30
22 22
23 2 24 26
25 27
Not Recovered
Functioned (S&A Armed, Det Pierced)
Not Recovered
Functioned (S&A Armed, Det. Pierced)
n
ii
Not Recovered
n
Functioned (S&A Armed, Det. Pierced)
Did not function (S&A Armed, Det. not Pierced)
Not Recovered II
Functioned (S&A Armed, Det. Pierced)
II
it
Not Recovered
36
****** •••
BROACHING TEST
155MM, M109A1, Zone 7, HE Loaded, QE-310 MILS, Ground Impact, Fu Set-Delay, Velocity- 1850 ft/sec, Quantity 15 Units.
ze
Round No. Fuze No.
1 27
2 37
3 38
4 31
5 35
6 39
7 33
8 64
9 74
10 36
11 48
12 32
13 40
14 28
15 41
Function
High Order on Initial Impact
37
— -***•!
wmmmm^*
I I I I I
BROACHING TEST
155MM, M109A1, Zone 7, Inert, QE-310MILS, Ground Impact for Recovery, Fuze Set-Delay, Velocity - 1850 ft/sec Quantity - 25 Units.
Round No. Fuze No. 1 2 3 4 5 6 7 8 9
10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25
28 47 46 49 41 42 21 50 32 39 31 38 27 40 48 44 43 25 23 24 34 33 37 36 35
Recovered Functioned (S&A Armed, Det. Pierced)
Not Recovered S&A Armed-DMID Firing Pin did not Release Functioned (S&A Armed, Det. Pierced)
II
it
II
II
ri
ii
II
II
II
Functioned (S/A Armed, Det. Pierced)
'
38
mmm
3.6 PHASE III
ENVIORNMENTAL TESTS
Quantity 116 DMID units of current design (Assembly No. KF-87906) and
Quantity 67DMID units of updated design (some parts modified to incorper-
ate a change in assembly procedure) Assembly No KF-87906 REV A were
assembled into M739 Fuzes and tested per MIL-STD-331. For Jolt &
Jumble, Transportation vibration, 40 foot dropiThermal Shock and
temperature tests,.
At the completion of tests, all units were spin tested for non-arming at
1100 RPM and then armed at 1700 RPM.
A sensitivity test was then performed for function by dropping each unit at
a controlled height (approx. 6 1/2 inches) to simulate impact.
A summary sheet & details of each test are as follows:
I I I 39
im
I
I TEST
JOLT & JUMBLE
JOLT & JUMBLE
TV
TV
TV
40 FT. DROP
40 FT. DROP
40 FT. DROP
5 FT. DROP
5 FT. DROP
5 FT. DROP
THERMAL SHOCK
SUMMARY SHEET
PHASE III
CURRENT DESIGN
CONDITION QTY.
COLD TEMP. 65°F 18
HOT TEMP. +160°F 18
AMBIENT 5
COLD - 65°F 10
HOT +160F 10
COLD - 65°F 10
HOT 10
AMBIENT 5
COLD - 65°F 5
HOT +160°F 5
AMBIENT 10
10
FUNCTION REMARKS
16 2 units did not arm
18
5
10
6 4 units did not arm
9 1 unit did not function
10
5
5
5
10
8 1 Firing pin did not release
1 did not arm
TOTA LS 116 107
I I 40
mw WLMI1IM
PHASE III
TEST UNITS
CURRENT DESIGN
I I
UNIT NO.
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
J & J - COLD (-65T)
Did not arm
Did not arm
J & J - HOT (+160°F) 18 UNITS
FUNCTION HEIGHT (INCHES)
18 UNITS
6 1/2
6 1/2
7 1/2
6 1/2
6 1/2
15
6 1/2
6 1/2
7 1/2
8 1/2
7 1/2
6 1/2
7 1/2
8 1/2
6 1/2
15
6 1/2
« 1/2
6 1/2
6 1/2
REMARKS
41
1 I I
UNIT NO.
23
24
25
26
27
28
29
30
31
32
33
34
35
36
37
38
39
40
41
42
43
44
45
46
TV
TV
FUNCTION HEIGHT REMARKS (INCHES)
6 1/2
6 1/2
7 Ml
6 1/2
6 1/2
7 1/2
6 1/2
6 1/2
7 1/2
6 1/2
6 1/2
6 1/2
6 111
6 1/2
AMBIENT 5 UNITS
6 1/2
6 1/2
6 1/2
6 1/2
6 1/2
COLD (-650F) 10 UNITS
6 1/2
8 1/2
6 1/2
8 1/2
6 1/2
42
mww m mm
UNIT NO.
47
48
49
50
51
NCTION HEIGHT REMARKS (INCHES)
6 1/2
6 1/2
6 1/2
6 1/2
6 1/2
TV
52
53
54
55
56
57
58
59
60
61
Did not arm
Did not arm
Did not arm
Did not arm
HOT ( + 160T) 10 UNITS
6 1/2
6 1/2
6 1/2
6 1/2
6 1/2
6 1/2
!
I I I
62 Nose down
63 Nose down
64 Nose up
65 Nose up
66 Horiz.
67 Horiz.
68 45° Nose down
69 45° Nose down
40* DROP - COLD (-65°F) 10 UNITS
6 1/2
6 1/2
6 1/2
6 1/2
6 1/2
6 1/2
6 1/2
6 1/2
43
mil I'I» mH
UNIT NO. FUNCTION HEIGHT (INCHES)
REMARKS
70 45° Nose up 6 1/2
71 45° Nose Up
40' DROP - HOT +160' F
6 1/2
10 UNITS
72 6 1/2
73 6 1/2
74 6 1/2
75 6 1/2
76 6 1/2
77 6 1/2
78 6 1/2
79 6 1/2
80 6 1/2
81 8 1/2
1 82
40' DROP - • AMBIENT 5 UNITS
6 1/2
[ 1 84
6 1/2
6 1/2
1 86
6 1/2
6 1/2
51 DROP - COLD (- 65° F) 5 UNITS
87 Nose Down 6 1/2
88 Nose up 6 1/2
89 Horiz. 6 1/2
i 90 45° Nose down 6 1/2
91 45° Nose up 6 1/2
44
mmmmw^m
I
I I I I
•UNIT NO. *T 'NOTION HEIGHT (INCHES)
REMARKS
5' DROP - HOT (160° F) 5 UNITS
92 Nose Down 6 1/2
93 Nose up 6 1/2
94 Horiz. 6 1/2
95 45" Nose down 6 1/2
96 45" Nose up 6 1/2
5' DROP - AMBIENT 10 UNITS
97 Nose up 6 1/2
93 ii 6 1/2
99 Nose down 6 1/2
100 it 6 1/2
101 Horiz. 6 1/2
102 II 6 1/2
103 45° Nose down 6 1/2
104 II II 6 1/2
105 45° Nose up 6 III
106 II II 6 1/2
THERMAL SHOCK 10 UNITS
107 6 1/2
108 6 1/2
109 Balls released (f: Lring pin did not release)
110 Did not arm 6 1/2
111 6 1/2
112 6 1/2
113 6 1/2
114 5 1/2
45
h ••—••-
UNIT NO.
115
116
FUNCTION HEIGHT (INCHES)
5 1/2
5 1/2
REMARKS
I
• - - - -T -"
I I I
3.6. 1
t
TEST
TV
ENVIRONMENTAL TESTS
PHASE HI
UPDATED DESIGN
SUMMARY SHEET
CONDITION QTY FUNCTION REMARKS
Ambient
TV Cold -658F 5 5
TV Hot + 160°F 5 4
Jolt k Jumble Cold -65*F 5 3
Jolt & Jumble Hot
Jolt & Jumble Hot
Jolt & Jumble
40Ft. Drop
40Ft. Drop
40Ft. Drop
5Ft.Drop
5Ft.Drop
5Ft.Drop
Thermal Shock
SPECIAL UNITS
Jolt & Jumble Cold
TV Cold
+ 160°F
(Retest)
Ambient (Retest)
Cold -65°F 5 5
Hot + 160°F 5 5
Ambient 2 2
Cold -65°F 2 2
Hot + 160°F 2 2
Ambient 5 5
_ 5 5
1 Did not arm (Spin lock jammed)
1 Did not arm
1 Did not arm 1 Assembled in armed position
Units assembled in armed position No Test
1 Did not fire Unit set safe
1 Unit did not arm Spin locks jammed
_—•
5 5
-65°F 3 2 IDid not arm
-65°F 4 4
Total 67 55
47
'i .-• PP. mmmm~im*W
I I I I
I I I
UNIT NO.
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
PHASE III
TEST UNITS
UPDATED DESIGN
TEST
TV-HOT +160°F
Did not arm - (Spin Detent)
FUNCTION HEIGHT (INCHES)
TV-AMBIENT
8 1/2"
Did not arm - Spin Detent Jammed
TV-COLD - 65°F
6 1/2
6 1/2
8 1/2
8 1/2
8 1/2
6 1/2
8 1/2
6 1/2
6 1/2
J&J - COLD -65°F
Did not arm (Spin detents jammed 2)
8 1/2
8 1/2
Unit - fired during test - was assembled in armed position
8 1/2
J&J - HOT 160°F
Unit was assembled in armed position - retest
Same as Item 18
Same as Item 18
Did not arm
Same as Item 18 48
w *m**m*
I I
I I I
UNIT NO.
23
24
25
26
27
28
29
30
31
32
33
34
35
36
37
38
39
40
41
42
43
PHASE HI
TEST UNITS
UPDATED DESIGN
TEST FUNCTION HEIGHT
(INCHES)
40'DROP - COLD - 65°F
Nose Down
Nose Up
Horiz.
4 5° Nose Up
45" Nose Down
Nose Down
Nose Up
Horiz.
45° Nose Down
45° Nose Up
Nose Down
Nose Down
Nose Down
Nose Down
Nose Down
Nose Down
Nose Down
Nose Up
Horiz
45* Nose Up
45° Nose Down
40' DROP - HOT -165°F
40' DROP - AMBIENT
5' DROP - COLD -65°F
5' DROP - HOT +165°F
5' DROP - AMBIENT
49
6 1/2
6 1/2
6 1/2
8 1/2
8 1/2
6 1/2
6 1/2
8 1/2
8 1/2
8 1/2
8 1/2
8 1/2
6 1/2
8 1/2
6 1/2
8 1/2
6 1/2
8 1/2
6 1/2
8 1/2
6 1/2
.
•P mmm '•--1
I I I
UNIT NO.
44
45
46
47
48
A
B
C
D
E
F
G
H
18
19
20
22
PHASE III
TEST UNITS
UPDATED DESIGN
TEST FUNCTION HEIGHT (INCHES)
THERMAL SHOCK -65°F & 160°F
J&J - RERUN - AMBIENT
Did Not Arm - Spin Detents Jammed
J&J - HOT + 160°F (RETEST)
Did not fire - Unit set safe at 7" after 4 Drops
6 1/2
8 1/2
6 1/2
6 1/2
8 1/2
8 1/2
8 1/2
8 1/2
6 1/2
8 1/2
8 1/2
8 1/2
6
5 1/2
6
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The following tests were made on updated units (modified for improved assembly)
with Zinc Die Cast Firing Pin Holder P/N KC-89493.
Jolt & Jumble Test - 8 Units 4 Hot &.• 4 Cold.
All Units did not function.
It was determined after this test that the Firing Pin Balls did not Release the
Firing Pin. This was due to excessive force used while staking the retainer
onto the firing pin holder which closed up the Firing Pin Ball Holes.
New Units were assembled and The Test Rerun as follows;
Unit No.
5
6
7
J&J, COLD TEMP. (-65°F)
Function Height (in. )
Did not arm (cent. Lock sticky)
7 1/2
6 1/2
12
13
14
15
TV CONDITIONED, COLD TEMP. (-65°F)
6 1/2
6 1/2
7 1/2
6 1/2
I 51
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I I
BALLISTIC TESTS
PHASE UI
The following ballistic tests were conducted to evaluate the Final Prototype
Design (Dwg. KD87906 Rev. A) under this contract.
All tests were conducted at Yuma Proving Ground using M739 Fuzes and T-2
explosive charges.
A summary and detail sheets follow.
A- Diagnostic These ground impact tests were conducted to determine
unit performance at zones and elevations where previous designs
experienced operational problems. (Broaching and Pre-release)
B- Sensitivity These tests were conducted to determine unit sensitivity
against plywood targets using min. and max. charges and various plywood
thicknesses.
C- Reliability
D- Graze
E- Penetration
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DIAGNOSTIC
A-l 175mm, Zone 1 - 15 inert rounds - to be recovered.
Cancelled
A-Z 175mm, Zone 1, Set Delay - 10 rounds fired H. E., ground impact
Round Fuze Velocity No. No. Ft. /Sec.
271 358 1780 Z72 360 1794 273 356 1787 274 355 1784 275 457 1781 276 451 1784 277 452 1786 278 453 1766 279 455 1780 280 456 1781
Function
Yes ti
ti
ii
ii
II
ti
IT
II
II
Remarks
75 - 80 sec. flight time
Elevation 900 mils
B SENSITIVITY Langlie type test using plywood targets at 500 feet distance and fired horizontal.
B-l Weapon - 105mm. Zone 1, Set Delay
Function Remarks Fuze Plywood No. Thickness
193 5 194 3 1/2 195 2 1/2 196 2 197 1/2 198 1/2 199 1 1/2 200 3 1/2 41 2 1/2 42 1 1/2 43 2 44 2 1/2 45 3 1/2 46 3 47 1 1/2
Yes II
II
it
No II
II
Yes it
No n
II
Yes II
No
56
11-in .ip.... •^
B-2 105mm, Zone 5, Velocity approx. 1068 ft/sec
I I
Round Fuze Plywood No. No^ Thickness Function
3 5 Yes 4 3 1/2 ti
5 2 1/2 No 6 2 1/2 Yes 7 1/2 No 8 1 1/2 M
9 3 Yes 10 2 No 11 2 No Test 12 2 No 13 2 1/2 1 I
14 3 1/2 Yes 15 3 M
16 2 1/2 No
Remarks
I B-3 105mm, Zone 7
Round Fuze Plywood No No. Thickness Function
31 5 Yes 32 3 1/2 ii
33 2 1/2 No 34 3 II
35 4 Yes
36 3 1/2 it
37 3 No 38 3 1/2 Yes
39 3 No 40 3 1/2 Yes
113 3 No 114 3 1/2 No Test 115 3 1/2 Yes 116 3 No Test 117 3 Yes 118 2 1/2 No Test 119 2 1/2 No 120 3 n
Remarks
Hit top of frame on target
I 1
57
—
B-4 155mm, Zone 2, Velocity approx. 750 ft/sec
I I I
Round Fuze Plywood No. No. Thickness Function
65 4 No 66 6 Yes 67 5 ii
68 3 1/2 ti
69 2 1/2 No 70 3 Yes 71 2 1/2 No 72 3 II
49 5 1/2 Yes 50 4 No 51 5 Yes 52 4 1/2 n
53 3 No 54 3 1/2 n
55 5 1/2 Yes
Remarks
B-5 155mm, Zone 7, Qty. 17, Velocity 1857 ft/sec
Round Fuze Plywood No. No. Thickness Function Remarks
56 4 No 57 6 it
58 8 Yes 59 7 it
60 4 1/2 n
61 3 No 62 4 II
63 5 1/2 Yes 64 4 1/2 No Test Hit frame 73 4 1/2 No 74 5 II
75 6 1/2 Yes 76 6 it
77 4 II
78 3 1/2 No Test Missed target 79 3 1/2 Yes 80 2 1/2 No
58
-r=- -mmi. mm ""•
B-6 175mm, Zone 1, Qty. 16, Velocity 1675 ft/sec
Round Fuze Plywood No. No. Thickness Function
193 194 266 7 in. Yes 195 267 4 1/2 No 196 268 6 Yes 197 269 5 No 198 270 5 1/2 1 1
199 271 8 1/2 Yes 200 272 7 it
201 251 4 1/2 No 202 252 6 n
203 253 9 Yes 204 254 7 1/2 it
205 177 5 No 206 178 6 Yes 207 179 5 1/2 No 208 180 6 Yes
Remarks
B-7 175mm, Zone 3, Qty. 15, Velocity 3000 ft/sec
Round Fuze Plywood No. No. Thickness Function
90 8 Yes 95 8 No 97 11 Yes 98 9 1/2 ii
99 6 ii
100 4 II
101 2 No 102 3 Yes 103 2 1/2 ti
104 2 it
89 1/2 ti
94 1/2 No
Remarks
59
*mmm')rr-r "• •- • •- -» •-•-'•- -
mmmmmrn.
B-8 8-inch Gun, Zone 1. Qty. 15
Round Fuze Plywood No. No. Thickness Function
17 5 No 18 6 1/2 Yes 19 6 tt
20 4 No 21 5 ii
22 6 Yes 23 5 1/2 No 24 6 Yes
121 5 1/2 No 122 6 Yes 123 5 1/2 No 124 6 Yes
• 125 5 1/2 No
1 126 6 Yes 127 5 1/2 No
Remarks
B-9 8-inch Gun, Zone 7, Qty. 15
I I I I
Round Fuze Plywood No. No. Thickness Function
128 7 Yes 161 5 n
162 3 1/2 No 163 4 n
164 6 II
165 8 1/2 Yes 166 5 1/2 No 167 6 Yes 168 5 1/2 No 169 6 II
170 7 Yes 171 6 1/2 n
172 6 No 173 6 1/2 Yes 174 6 No
60
Remarks
B-10 105mm, Zone 1, -65°. Qty. 15
Round Fuze Plywood No. No. Thickness Function
420 5 Yes 421 3 1/2 Yes 419 2 1/2 No 422 3 Yes 423 2 1/2 No 424 3 Yes 425 2 1/2 No 426 3 No 427 5 1/2 Yes 432 4 Yes 428 3 Yes 429 2 1/2 No 433 3 No 434 5 1/2 Yes 430 4 Yes
B-ll 105mm, Zone 7, +155°F, Qty. 15
Round Fuze Plywood No. No. Thickness
431 5 396 6 397 6 399 4 400 3 401 2 402 2 459 5 461 4 462 3 463 2 464 2 465 3 466 5 460 3
1/2
1/2
1/2
1/2-
Function
No Yes Yes Yes Yes No No Yes Yes Yes No No No Yes Yes
I [I
6 1
Remarks
Remarks
- • i a-*——- •-— *—•**— • • Mfl
B-12
I I I
1 75mm, Zone 3, Ambient, Qty. 15
Round Fuze Plywood No. No. Thickness Function
435 3 Yes 436 1 1/2 No 437 2 No 438 4 No 439 5 Yes 440 4 1/2 Yes 441 2 1/2 No 442 3 1/2 Yes 432 3 Yes 398 1 1/2 No 412 2 Yes 413 1 1/2 No 414 2 No 395 4 Yes 416 3 No
-
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74
I I
C RELIABILITY TESTS
Ground impact and plywood tests at ambient, temperature conditioned, and TV conditioned.
All fuzes set delay except where noted and T-2 charges used.
C-l 155mm, Zone 7, LQE 83-5° azimuth, 500 mils elevation,
'
cold temperature condition
Round Fuze Velocity No. No. Ft. /Sec.
1108 512 1865 1109 508 1859 1110 514 1865 1111 513 1863 1112 510 1864 1113 260 1867 1114 262 1868 1115 259 1866 1116 261 1863 1117 257 1865 1118 258 1867 1119 264 1859 1120 263 1870 1121 314 1867 1122 315 1861 1123 313 1864 1124 317 1862 1125 316 1864 1126 318 1868 1127 319 1861 1128 320 1864 1129 338 1862 1130 343 1865 1131 342 1868 1132 339 1872 1133 340 1867 1134 344 1862 1135 341 1880 1136 337 1865 1137 273 1869
Function
Yes
Remarks
* * * * #
(No) Yes
• Updated Units Some parts were modified to incorporate a change in assembly procedure.
I! D 75
m ^m^
C-2 175mm, Zone 3
92° aiimuth (round weight 146 lbs. average) Cold temperature conditioned at -50°F 2 min. 8 sec. flight time, Qty. 10 rounds
Round Fuze Velocity No. No. Ft. /Sec. Function
249 Spotter Round 250 386 3026 Yes 251 385 3074 252 369 3042 253 370 3015 254 371 3024 255 372 3019 256 373 3019 257 374 3010 258 375 3079 259 376 3017
Remarks
C-3 175mm, Zone 3
Same as C-2 except hot tempe ratu re conditi
Round Fuze Velocity No. No. Ft. /Sec. Function
260 Spotter Round Yes 261 454 3011 262 458 Lost 263 443 3009 264 447 3019 265 444 3016 266 448 3020 267 445 3017 268 446 3023 269 449 3024 270 450 3017
Remarks
;
i 76
_•- -~ - -•
—— •^w»
C-4 105mm, Zone 7
84° azimuth, 500 mils elevation, cold temperature conditioned at -50°F, qty. 1 5 rounds
I Round Fuze Velocity No. No. Ft. /Sec. Function Remarks
1434 278 1627 No 1435 277 1625 Yes 1436 274 1626 1437 280 1635 1438 275 1629 Reverse function 1439 276 1633 1440 326 1619 1441 329 1621 1442 327 1622 1443 323 1622 1444 328 1624 1445 325 1622 1446 321 1619 1447 322 1621 1448 324 1622
C-5 105mm , Zone 7
TV con ditioned, 85° azimuth, 500 mils elevation, qty. 15 rounds
Round Fuze Velocity No. No. Ft. /Sec. Function Remarks
79 211 — Yes 80 212 -- 81 213 1621 82 215 1623 83 216 1617 84 249 1615 85 250 1614 86 233 1613 87 234 1615 88 235 1612 89 236 1633 90 237 1618 91 238 1615 92 239 1609 93 240 1618
i 77
/• • m.
- , ...
mmmm ^^mmm • '
C-6 1 55mm, Zone 2
6 inch thick plywood target at 45° angle to gun Distance 500 ft. Qty. 1 5 rounds
Round Fuze Velocity No. No. Ft ./Sec. Function Remarks
133 Yes Long delay 134 698 135 723 136 742 131 130 129
81 No Functioned on groi approx. 800 ft.
82 Yes 83 84 85 86 87 88
C-7 105mm, Zone 5
4 inch thick plywood target at 45° angle to gun Distance - 500 ft. , 7. 6 mils elevation Qty. 15 rounds
I I I
Round No.
Fuze No.
190 189 184 182 181 191 188 192 157
93 158
91 92 96
132
Velocity Ft. /Sec. Function
1070 No Test 1064 Yes 1053 ii
1057 it
1058 II
1056 No 1061 Yes 1063 II
1060 II
1065 II
1070 II
1068 II
1066 II
1068 II
1067 n
Remarks
Missed target
Functioned on ground impact
78
wmm wmmm
C-8 155mm, Zone 2 HQE, Ground impact, ambient, 84' 900 mil ä elevation, qty. 30 rounds
Round Fuze Velocity No. No. Ft. /Sec. Function
1053 494 764 Lost 1054 495 758 Yes 1055 496 755 1056 515 743 1057 516 748 1058 175 744 1059 106 747 " 1060 108 744 " 1061 109 752 1062 105 741 " 1063 107 747 1064 110 751 1065 111 749 " 1066 112 749 " 1067 137 752 1068 138 752 1069 139 756 1070 140 754 1071 141 753 1072 142 754 " 1073 143 751 " 1074 144 751 1075 289 758 " 1076 290 759 1077 291 761 » 1078 292 756 1079 293 758 1080 294 756 1081 295 753 1082 296 759 "
azimuth,
Remarks
*
*
*Some parts were modified to incorporate a change in assembly procedure.
1 I 79
.. . . M
m^^m •
I I I
C-9 155mm, Zone 2, HQE
Ground impact, TV conditioned, qty. 25 rounds
Round Fuze No. No.
1083 217 1084 218 1085 219 1086 220 1087 221 1088 222 1089 223 1090 224 1091 225 1092 226 1093 227 1094 228 1095 229 1096 230 1097 231 1098 232 1099 241 1100 242 1101 243 1102 244 1103 245 1104 246 1105 247 1106 248 1107 214
Velocity Ft. /Sec.
755 757 760 754 756 762
765 761 756 758 764 765 766 763 765 760 761 768 762 761 763 759 764 766
Function
Yes
Remarks
C-10 105mm, Zone 7 LQE
Ground impact, ambient, fuzes set S. Q. , 500 mils elevation, qty. 40 rounds
Round Fuze No. No.
1394 492 1395 493 1396 498 1397 497 1398 491 1399 141 1400 145
Velocity Ft. /Sec.
1611 1630 1626 1618 1615 1626 1614
Function
Yes
Remarks
* * *
"»—
I I I I
Round Fuze Velocity No. No. Ft. /Sec. Function
1401 146 1619 Yes 1402 147 1630 it
1403 149 1617 n
1404 305 1617 ii
1405 307 1614 ii
1406 153 1619 II
1407 154 1615 II
1408 155 1614 II
1409 156 1623 n
1410 160 1617 II
1411 176 1617 H
1412 159 1619 n
1413 308 1619 II
1414 306 1618 II
1415 312 1621 II
1416 297 1619 II
1417 300 1615 II
1418 299 1619 II
1419 304 1617 II
1420 303 1619 n
1421 302 1619 II
1422 298 1617 n
1423 301 1614 II
1424 311 1617 ii
1425 309 1614 " 1426 329 1619 II
1427 332 1616 II
1428 336 1620 n
1429 335 1616 II
1430 331 1617 II
1431 330 1619 II
1432 334 1622 II
1433 333 1618 n
Remarks
[ L
*^"
C-ll 105mm Zone 1
4 inch thick plywood target, distance 500 ft. Hot temperature conditioned +145°F 16.8 mils elevation, qty. 10 rounds
Round Fuze Velocity No. No. Ft. /Sec. Function
1349 467 Yes 1350 403 II
1351 407 780 M
1352 405 Ft. /Sec. 11
1353 404 Average No 1354 486 Yes 1355 485 ii
1356 487 ti
1357 483 n
1358 484 ii
Remarks
Functioned on ground impact
I
C-12 105mm, Zone 1
4 inch thick plywood target, distance 500 ft. Cold temperature conditioned -50° F 16.8 elevation, qty. 10 rounds
I
Round Fuze Ve locity No. No. Ft ./Sec. Function
1369 408 No Test 1370 409 780 Yes
• 1371 501 Ft ./Sec. No * 1372 500 Average No * 1373 502 Yes * 1374 506 No * 1375 503 Yes • 1376 505 No * 1377 499 Yes * 1378 504 No
Remarks
Missed target
Functioned on ground impact
Functioned on ground impact
Functioned on ground impact Long delay Functioned on ground impact
* These fuzes were modified to incorporate a change in assembly procedure. They were mistakenly used on this test.
,
1 C-13 105mm, Zone 1
4 inch thick plywood target, d
Round Fuze Velocity No. No. Ft. /Sec.
210 669 209 678 205 676 201 673 206 678 202 207
681 683
203 683 208 683 204 681
Function Remarks
No Test Missed target Yes
u
II
II
II
II
II
II
No Functioned on ground impact
C-14 105mm, Zone 7
4 1/2 inch thick plywood target, distance 500 ft. Hot temperature conditioned 145°F, qty. 10 rounds
Round Fuze No. No.
1359 471 1360 468 1361 488 1362 489 1363 490 1364 472 1365 469 1366 473 1367 470 1368 474
Function Remarks
No Test Missed target IT n II n
No Yes
No Test Missed target ii ii ii n
Yes No Function on im
5 1/2" Plywood No it it
5 1/2" Plywood Yes
I I
HM
GRAZE FUNCTIONING TESTS
All rounds were fired ground impact at distances of 325 to 850 feet. All fuzes set delay - T2 charges used.
D-l 105mm, Zone 1, Graze
Qty. 25 rounds
Round Fuze Velocity Elevation Distance No. No. Ft. /Sec. (mil 3) (feet) Function Remarks
1474 255 609 10 600 No 1475 253 646 10 600 Yes 1476 152 660 10 600 ii
1477 310 672 10 600 tt
1478 345 673 12 650 n
1479 346 676 12 650 n
1480 347 680 13 650 II
1481 348 681 14 700 II
1482 349 683 15 700 II
1483 350 685 16 750 Approx. 1 ° 1484 351 682 9 550 II
1485 352 685 9 550 it
1486 381 683 6 500 No 1487 382 686 6 500 Yes 1488 383 687 6 500 n
1489 384 683 6 500 n
1490 380 685 10 600 it
1491 379 688 10 600 II
1492 378 685 15. 8 750 it
1493 377 685 15. 8 750 n
1494 511 684 15. 8 750 II *
1495 507 685 15. 8 750 " *
1496 509 681 15. 8 750 " * 1497 357 688 20 800 n
1498 354 687 25 850 II
*These fuzes were modified to incorporate a change in assembly procedure.
mmmmmwmm
D-2 105mm,
Qty. 25
Zone 7,
rounds
Graze
Round Fuze Velocity Elevation Distance No.
49
No. Ft. /Sec.
1625
(mils)
36
(feet)
400
Function Remarks
517 No 50 518 1614 3° 300 No 51 519 1613 3 1/2° 550 Yes 52 520 1618 3 1/2° 550 53 521 1615 3 1/2° 550 54 281 1617 4° 500 55 282 1614 4° 500 56 283 1615 5° 500 57 284 Lost 5° 500 58 285 1616 2° 400 59 286 1616 2° 400 60 287 1620 2° 400 " Long delay
61 288 1618 2° 400 62 361 1616 2° 400 63 362 1622 2° 400 64 363 1622 1 1/Z° 350 65 364 1623 1 1/2° 325 66 365 1621 1 1/2° 325 67 366 1623 1 1/2° 325 68 367 1618 7 (1°) 600 No 69 368 1618 7 (1°) 600 No 70 148 1618 7 600 Yes 71 256 1622 7 600 No 7^ 183 1620 5 550 Yes 73 150 5 550 Yes
PENETRATION TESTS
These tests will be conducted at a later date.
85
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I I I I
3. 8 Conclusion
Phase I included specific changes to eliminate a broaching and pre-release
problem which existed on previous contracts. Results of these tests i. :ate
that the problem has been eliminated.
As part of this phase a study was made by R. Stresau Labs to determine the
reliability of the M55 Detonator's propagation through the path of the DMD unit
and the results were favorable.
Phase II was a feasibility study conducted to test the use of zinc die casting in
place of machined brass on the plunger. Tests have indicated that the properties
of zinc are adequate to the performance of the device and the part cost will be
lowered.
Phase III was a qualification study conducted to establish and improve the final
design of all parts including changing the Firing Pin Holder from machined
aluminum to die cast zinc.
Although approximately 900 units were tested for environment and ballistics with
satisfactory results, a follow-on task should follow to finalize the unit's design
and tooling for future production.
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