INVESTIGATION OF THE DETERMINANTS OF THE MODULUS OF RUPTURE OF FUSED SILICA PART I

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP67B00944R000100050001-2
• Release Decision: RIPPUB
• Original Classification: K
• Document Page Count: 35
• Document Creation Date: December 12, 2016
• Document Release Date: July 9, 2002
• Sequence Number: 1
• Publication Date: February 1, 1961
• Content Type: REPORT

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INVESTIGATION OF THE DETERMINANTS
OF THE MODULUS OF RUPTURE OF
FUSEDSILICA
ATINTL
Contributors to tLi:: work:
PART I
'17obruary I, 1961
Documer.t 301
rtOe- -140g
PY 1 OF
STATI NTL
Nk.r.:ber of Pi.s
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I. INTRODUCTION
Te roolrt re ,:err a SUI-r1Z-.17y that r;ceh Jo t date
on the proram pro r,!-: in prore':;s to determine the offoeto
"
method, and surface gunlity on the modulus of rupture c Case,:! silica.
The motivation for such a study as well the overall objectives are
discussed in detail in the document titled "A Proposed Program Eor Investi-
gating the Determinants of Modulus of Rupture of Fused Silica", July 1960.
Figure No. 1 presents in pictorial form the overall procedural flow. This
report concerns itself with the results of breaking the group labeled
"Set. e.
PROCEDURES
A. Grinding and Polishing
Sixty fused silica disks, 4" in diameter and 1/4" thick, were
numbered for identific,a,tion and cloth polished on one surface. They
were then cemented to blocks in groups of six ahd-thc, other surface
ground and polished in a conventional manner using the following
abrasives,:
Blahhz'.rd - 150 grit diamond (100 micron particle)
line irfrid - 2F aluminum c7,ide (.30 micron particle)
flee cind - 3i' aluminkrm (20 micron particle)
line rind - Kll aluminum oxide (1:4 micron particle)
Fine rind - KO aluminum oxide (12 mir.n particle)
PolHh Baruesi:_e
The abrasive ,equence was detevmined fr.,r1 the fine .(?rind dad
polish schedule followed on other fused silica structural pieces made
recently. The overall grinding procedure was uncontrolled in the
sense that the amount of material to be removed with cLen abrasive
was left entiriily to the discretion of the operator.
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A history of ;Thrive c, .1ater rcmove;,1 i;; cc
operation, tL:c of reowl, wa: kmL Lr eL.c. ample. All
fine grindirve, and polihirw wLs done by 1.:x. ame (Ttician on t
machine to remove the poscibi lityof operator ski 11 or machine c;arac-
teristics as an influence on resultant strength.
B. Inspection and Classification
Upon completion of the polishing operation, the samples were.
cleaned and sent to Quality Control for' inspection. The surface area
of interest was found to be free from inspectable defects -in almost all
cases. ? Controlled surface scratches, therefore, were purposely
.introduced to approximately. 2/3 of the sample pieces, selected at
--_,random, and the samples were returned for further inspection. All
samples were inspected a minimum of two times by each of two inspectors
making a total of four inspections. Samples whose final classification
was still in doubt were inspected aim by each of the inspectors
for a total of six inspections.
Each sample was then placed in one of three groups according
to its surface qurility within the surface area of interest, The groups
are defined as tdlows:
Crou,)
Sccntch
0-60
60-100
100-160
Scratch specic.ications described in U. S. Government Specifiation
MIL-0-13830 are defined by an arbitrary master at Frankford Arsenal,
Pennsylvania and refer to the appearance of all defects which are
of a long nature. Duplicates of this master are used for visual side
by side comparison with the optical element being tested under the
light from a standard 40 watt incandescent lamp.
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In C7,1- ;)Crr.
in doubt hec:IL 'he variation in Q. C. (:.1:tIch d.5lL;natiuns,
was placed in t,:e roup f6hr which it by vir'fie
of Lle controlled scratch :,reviously introduce.:.
C. Test Equipment
Figure 2 is a photograph of the equipment used for breaking the
test pieces. Load is applied to the sample by the extension of the
spring attached to the end of the lever. arm. Loading rate can be
_adjusted to any desired value by varying the voltage to the drive
-1flotor. Motor speed is indicated .by a tachometer mounted on the MOEOC
shaft, and may be kept constant as load increases by fine adjustment
of, motor voltage.
Load measurement is accomplished by means of an Emery hydraulic
load cell which transmits a pressure signal to a Honewell pressure
transducer. The crLnsducer in turn cnverth this to an electrical
signal which 1:;-1 to a pen recorder. Thus a permanent record is made
of load verms time f,11: each sample.
CLlibr[tion of load cell-tr;:nisducr asnembly was hy moan:; of
applicaz:i,-n of km.;1,-r) loads mer..2;urc2 Morehour.e. ria. Accur!:...cy
was found to he 27. in the test load range.
III. ANALYSIS
A. Breaking Stren
.1,ure 3 is a photograph of a test sample being broken between
the upper and ic:;er rings of the test apparatus.
loads the sample as foll)ws:
The apparatus
a = 1.75"
r, b = 0.625"
2.09"
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Within the concentric area of radius' r , radial an,_1 tangential
stresses are e,;n,il is magnitude, and 1-.1y be expressed by the cquation:
=
1
where K and KI are coefficients based on material properties (Poisson's
ratio, modulus of elasticity) and test apparatus dimensions (a and r0).
W is total load (lb.).
For the tests under discussion, K= .0.77 and K 2 0.32, the
equation may be reduced to:
.700W
Q-r
The. double ring test is used, rather than the conventional knife-
edge method with rectangular samples, because the -former produces
maximum stresses of equal magnitude throughout the concentric area
of radius ro' while leaving the edges relatively stress free. The
use of the knife-edge method would have resulted in large stresses
at the edges of each sample and necessitated the grinding and polish-
ing of the edges of the test samples F:0 the same igtec of perfoction
as the center. Moreover, stress at reratch would be depenTh:lt on
exact ::7cratc I :a,:ion and orient.tin. In the double ring t:st,
however, so i.su. the .::-Itatch is wit the concentric nr,m
radius the reult:Int stress at t(,e craten is independent of
scratch boor tunor ,,rientation.
B. Long Time Stress
Figure 4 is a representative curve for the breaking stress of
2
glass at room temperature as 'a function of time duration. Shand
1
Roark, "Formulas for Stress and Strain", McGraw-Hill, 1954, Pg. 194
2 Shand, "Fracture Velocity of claBs in Fatigue Rane" J. Am Cer. Soc.
-ary roved For Rerease 2002/0700 : CIX-RDP67`500944R000 ,
Janu100050001-2"
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state:: that Fur a particular lart7pe,4he L ross concentr,atiDn
factor at Lie crack rip varies the one-haif power of toe cracl,
depth. he further states that wiri she same initial crack tip stress,
the time duration fc)r fracture (stress durtin) will vary directly
with the initial depth of the crack.
Thus:
where al and a2 = initial crack depths
In and 0-2 =. nominal appliedtensile stresses
t1 and t2 = time durations to fracture, or stress duration.
- Therefore, by selecting any point (q-L, t1) on the stress-time curve,
Cr
'and any other point (q7"2, t2.) such that a line
drawn through these two points will represent the locus of equal values
of crack tip stress for different magnitudes of initial crnck depth.
Line A-B on Figure 4 is such a line.
Thus, by shifting the representative curve along line A-B so
that it passes through the test point of interest, this single curve
may be made applicable to samples having any initial crack depth.
The eff,:ctive load duration was taken as that required for tne
final 107 ircrehse before fracture. This relationship is based on
3
actual computations by Shand from tests conducted by him.
IV. TABULATION OF TEST RESULTS
Table 1 is a tabulation of surface quality inspection results for
the test sample::. The last column indicates the group in which the sample
3
Shand: Verbal communication, June 1960
?
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was placed
1..,111S It he t. t
in almost:core scrat:Th pre?-67,r, ther7_ Ibte
variation betlen te vicious Q.C. C1i i ctior1 for
illustrating the Lled for a more consistent =Iner of establiching
surface quality.
Table 2 is a tabulation of breaking stress for the test samples
arranged by groups. Column 1 shows the actual breaking stress. column 2
indicates the time in seconds. for the load to rise from zero to the break-
ing load. Column 3 shows the calculated long time stress-. '
DISCUSSION OF DATA
. Significance of Results
4
An analysis of variance performed on the breaking stress data
resulted in the conclusion that there was no significant difference
between the results of group II and group III. .There was, however,
definite significance between the ce.dts of group I and each of the
other groups, ond between group I and the .::omposite of groups II and III,
Groups It and III., therefore, are treated as a combined sample hence-
forth in this report.
B. Breaking Stret.
'igure 5 is a chart of m_,,h11;:s of rnl.ture versus Eceuency of
occurrence for the test groups.
The data for these distributions are uhimodc11 with averages of
8600 psi for Group I and 7040 psi for Groups II and III and a range
of values on either side of the averages of 2000 psi for Group 1 and
3000 psi for Groups II and III. The distributions were tested to
determine their fit with the normal distribution. The plot of the
4
Waugh, A.E., "Elements of Statistical Variance", McGraw-Hill, 1943; P236-252
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data on prob?Ibility paper a-cpeared Lo bc4repre[entative r.t. a nrsrmal
distribution. Therefore, roe normai H_striuti,.'n parametric pt--
diction techniciues were used to determine the lower modules of rupture
values.
C. Long Time Stress
Figure 6 shows the frequency of occurrence of calculated long
time stress. Introductions of time as a parameter in the calculations
of the long time stress has tended to weight the, values. When plotted
on probability. paper, the data appears to be normally distributed,
Croup I shows a mean value. of 3000 psi while the mean for the composite
of groupsII and III is. 2250 psi.
Lower Limit Stress Valdes
We may compute lower limit stress values with varying degrees
of reliability according to the formula
LV = tS
where LV = lower limit stress value, psi
_
X - sample mean stress, psi
= a device for computing the lower limit
S :tandard deviation
5
Valuer of t were obtained from tables prepared by Lieberman for
various reliabilities and percentages of the distribution below the
lower limit value. Reliability is the assurance afforded by the
formula that the lower limit value computed will be exceeded that
percentage of the time. The t values are shown in Table 3 and the
lower limit values for breaking stress and long time stress
are shown in Tables 4 and 5 respectively. The datizof the tables
5G. J. Lieberman, ,"Tables for One-Sided Statistical Tolerance Limits",
Ind. Qual. Control, April 1958
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are pr, lnted i,1:1!;hcal for, fa 1,'fires* 7 nnd 8. i oth
the lower It j tfl for he strf:s aie shvon L col iv.a:L!7,on. L'ith
the similar values to the long time strss.
or cxanr,le, there. is
951 assurance that a valut. or. 1.8.C) psi or 1L-cn cause rwture 1/,
of the time in quart with a 60 scratch or less. This is equivalent
to a 1225 psi long time stress. In quartz with greater than a 60
scratch, the breaking stress is 3370 psi and Crle long time stress
psi for the same reliability and percent of the distribution
below the _lower limit.
SUMMARY
YthemodUluS of rupture for quartz ground and polish,id according to
,
dtur.present technique was colaputed for .samples of different surface. quality.
The effect of fatigue on the 1.odu1us of re:,ture calculated. It was
?
found that the data fro l: sanples haviri a surface quality equal to or
better than a 60 scratch f:as si;:,ntficantly dIfforent from those with a
surface quality of 30 scratch or wore.
With 99% rel Lability
fouud tnat only once In a hue(1red timcs
could yr. CNT,i2.CC fai:ule Ln LI, c,u,,rtz to OCCUT be Low 4650 p;)l. lt its sur-
.faCe qua) Lty was !)L!"..1..el a ',() Cl low 2
quality was all
z1fect of fnti n?f in to
reduce these v,)lw's to 30 psi :d ,si rc!:41occively.
noted L%ain thas :f3i:s,?. are ,,alcallt,,d f)alue:i, dad :_ftr_tto Hit-ICI: of
- fatigue on 7770(Inlu:; Of ruptL7A-L 11.is Jot eea deco.tnLoQd expori:lent3Lly
thus far in this :,roo_am.
Future plans call foi7 d testin,; of another set of. 5amples, this
time ground and poli3hcd accoidin4f, to controlled procedures designed to
minimize residual crack3 rmaiaing beneath the surface of the quartz as a
r. suit
4i411KabSPOr fszeielEe
. : CIA-KUP67E300944R000100050001-2
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In
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START
20 SAMPLES
SET A
60 SAMPLES
gd.rmassmal
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P01 ISHING
SAMPLES POLISHED
IN CONVENTIONAL
MANNER
GRINDING
SAMPLES GROUND
IN CONVENTIONAL
MANNER
? SELECTION
20 SAMPLES CHOSEN TO
FITTED INTO EACH OF 3
SURFACE GROUPS
400060001-2
-
QUALITY CONTROL
SAMPLES CLASSFIED
INTO 3 SURFAcE
GROUPS
BE
FITTING
SAMPLES FITTED INTO APPROPRIATE
GROUPS BY SCRATCHING OR POLISHING
000nfl
0 0
SAMPLES GROUND
ACCORDING TO CON-
TROLLED PROCEDURES
SET
60 SAMPLES
0 0
00
C
?
0
00
000
?
BREAKING
LOAD
troe?kull
,
L
T PWRI
I SUPPL
T,
PRESS
VOLT
XDCR
000 LOAD CELL
120 SAMPLES
PEN
ANALYSI
I. SIATISTICAL DISTRIBUTION OF MODUL(
OF RUPTURE FOR FUSED SILICA.
2 EFFECT OF CONTROLLED \iS CONVE
TIONAL GRINDING PROCEDURES
3. DEPENDENCE OF MODULUS OF PUPIL
ON SURFACE SCRATCHES & DIGS
4 ESTABLISHMENT OF CONSISTANT SUR
FACE CODE
5 REPRESENTATIVE SAMPLES OF EACH
QUALITY GROUP STORED AS STAN-
DA RDS.
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Approved For Release 2002/07/30 : CIA-RDP67600944R000100050001-2
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Available ?
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Approved For Release72002/0-7/311: GIA-RDR67B00944R000100050001-2-,
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SUMMARY OF SURFACE QUALITY INSPECTION RESULTS
DATE 10/3/60 10/5/60 10/13/60 10/14/60 10/18/60 10/18/60
INSPECTOR' A B A B A B
PIECE NO. GROUP
,
1 160 100 100 100 80 80 It
0
0
0
0
0
80 80
80
100 II
III
III
III
It
II
II
III
III
III
II
II
13
100
100
160
120
160
120
14
80
100
100
100
15
80
100
100
160
160
160
16
160
120
100
100
160
160
17/
80
100
80
100
18
100
100
80
100
19
80
100
100
100
20
80
160
100
120
?
160
140
21'
160
100
120
120
160
160
22
100
120
100
100
23
80
120
80
80
80
80
24
80
80
80
80
0
0
DATE
INSPECTOR,
PIECE NO.
ID/3/60 Foil-1'4%e 2069/0109 CIAA110094414(CIP0500CIP-91/60
GROUP
27
28
29
30
31
0
0
0
0
0
0
0
0
0
0
0
40
60
40
60
0
0
0
0
32 ' 60 100 80
80
.
120
80
40 160 120 120 120
41
80
100
80
100
42
160
160
80
120
160
160
43
160
80
80
120
120
120
44
160
120
160
160
45
80
100
80
100
46
160
100
160
80
80
80
47
80
80
100
80
48
80
100
80
80
49
80
100
100
160
160
120
50
100
80
80
80
51
0
0
0
0
52
60
120
80
100
80
80
53
80
100
160
160
100
120
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III
II
III
II
III
II
II
III
Ii
II
III
DATE
INSPECTDR
PIECE NO.
10/3/60 10/5/60 10/13L60 10/1410 1.9./18/60 .110/18/60
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54
80
100
100
55
30
120
80
56
0
0
0
57
80
120
160
58
80
160
160
GROUP
?100 II
120
100
100
40
0I
160
160
160
120
160
160
160
160
140
II
III
III
III
GROUP I
Tiece Breaking Time, Long Tine
Number Stress, PSI Sec Stress, PSI
Fititii4
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2
7050
3 . 8500
-11150
8625
8900
7700
8000
9650
8675
9900
8650
9100
8425
7750
9200
'8850,
7300
8075
10150
6900
8125
11
-25
26
27
28
qo
. 33 -
,34,
36
-51 .
56
8
8600
1047
21
26.5
28.6
38.1
28.6
20.5
24.0
29.2
32.9
29.4
34.8
29.5
30.4
24.1
23.8
28.7
27.7
22.3
27.0
29.3
26.0
30.4
2250
2900
4500
3000
2900
2500
2650
3500
3000
3800
3000
3300
2800
2500
3300
3100
2300
2750
3800
2250
2800
3000
- 543
21
Appro
Summary of Modulus of Rupture' Cilculaticas-
GROUP Ii
Piece - Breaking Time
Number Stress, PSI Seb
1 6600
9 8125
10 8425
12 7650
14 8040
17 7200
18 5675
19 6850
23 8850
24
32 5125 13.2
37 9450 31.4
39 5950 19.6
41 7875 23.8
45 6375 18.9
47 5750 17.8
48 6175 18.9
50 7325 25.8
52 10125 32.5
54 7075 18.8
55 6275 19.4
46 6225 19.4
-- 'GROUP III
'Piece "Breaking Time,
Number 'Stress, PSI Sec
23.6 2000
30.5 2800
31.0 .285O..'
24.3 2500
26.4 2750
25.8 2400
18.6 1600
21.4 2150
23.4 3050
7200
1263
21
R =. Mean
S Standard Deviation
N = Semple Size
1450'
3300
1700
2650
1900":,
1650 -
1800--;
2450..
3800
2150'
- 18507,
1825
'6875
7100
6950
? :7950
6150
7200
7850
.7125
7550
4250
8850
5050
8100
7375
3400
5325
-6830
1180
16
GROUP II AND III
Breakit*
Stress. PSI
'68310
S 1233
N. 37
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23.2
? 22.3
17.6
26.4
21.6
22.6
24.8
22.9
23.0
12.7
26.4
16.2
31.5
29.5
19.9
14.7
Long Time
Stress, PSI
2200
2350
2100
2650
1800
2350
2600
2300
2450
1050
3100
1375
????IM,
2950
2450
1500
1400
2160
572
16
COXPOSITE
Long Time
Stress, PSI
0
562
37
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