VOLUME TWO PROJECT 9015 FINAL REPORT 1960-1964

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP67B00657R000300150001-1
• Release Decision: RIPPUB
• Original Classification: K
• Document Page Count: 168
• Document Creation Date: November 16, 2016
• Document Release Date: January 3, 2000
• Sequence Number: 1
• Publication Date: June 1, 1965
• Content Type: REPORT

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VOLUME TWO
PROJECT 9015
FINAL REPORT
1960 -1964
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SHC65-9015-314/2
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This volume contains the appendixes to the 9015 Project Final Report
Most of the appendixes are reports written on the project. The reports have
not been updated to include later results or to reflect current thinking, but
they have been reviewed and found to be essentially correct.
The dates of the original work are as follows:
Appendix I
II
III
IV
V
VI
VII
VIII
IX
X
XI
XII
XIII
XIV
XV
March 1961
December 1964
February 1963
December 1964
November 1964
February 1963
May 1963
February 1964
June 1963
September 1964
February 1964
December 1964
Itek Document Number SHC65-9015-314/1, Volume One.
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I. DOCUMENTS
II. INVESTIGATION INTO LIQUIDS SUITABLE FOR IMMERSION PRINTING
III. EFFECTS OF FINITE BANDWIDTH IN THE LIGHT SOURCE
IV. INSTALLATION REQUIREMENTS
V. SPARE PARTS
VI. DETERMINATION OF THE VELOCITIES OF MOVING TARGETS
VII. APERTURE WEIGHTING
VIII. INTERFERENCE PATTERN GENERATOR
IX. STRAY LIGHT IN THE PROCESSOR
X. CYLINDER LENS EFFECTS
XI. FLIGHT TEST REPORT FORMS
XII. EFFECT OF FILM EXPOSURE ON RECORDER / CORRELATOR
PERFORMANCE
XIII. COHERENT SLR RECORDER-CORRELATOR SYSTEM
XIV. TWO DIMENSIONAL HOLOGRAMS
XV. SPECTRUM AND OUTPUT FOR OPTICALLY CORRELATED CHIRP
SYSTEM
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Appendix I
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Appendix I
This is a list of the documents generated at Itek on the 9015 project.
Project Reports
Model 9015 Processor Final Report
May 1964
SHC64-9015-310
9015 Project Final Report, Volume I
June 1965
SHC65-9015-314/1
Appendixes, Volume II
June 1965
SHC65-9015-314/2
9015 Project Report, Jan-June 1965
June 1965
SHC65-9015-315
These four volumes cover all phases of the project up to June 1965. The Pro-
cessor report is often referred to in the Project report as reference 1. The
latest report covering the period January to June 1965 covers specific studies
on noise and stray light.
Progress .Reports
Progress Report
November 1961
SHC61-9015-158G
Progress Report
December 1961
SHC62-9015-08
Progress Report
January 1962
SHC62 -9015- 57
Progress Report
February 1962
SHC62-9015-77
Progress Report
March 1962
SHC62-9015-176
Progress Report
April 1962
SHC62-9015-172
Progress Report
May 1962
SHC62-9015-195
Progress Report
June 1962
SHC62-9015-237
Progress Report
July 1962
SHC62-9015-238
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Progress Reports (continued)
Progress Report
Aug/Sept 1962
SHC62-9015-331
Progress Report
October 1962
SHC62-9015-359
Progress Report
November 1962
SHC62-9015-384
Progress Report
December 1962
SHC63-9015-42
Progress Report
January 1963
SHC63-9015-77
Progress Report
February 1963
SHC63-9015 -103
Progress Report
March 1963
SHC63-9015-159
Progress Report
April 1963
SHC63-9015-190
Progress Report
May 1963
SHC63-9015-250
Progress Report
June 1963
SHC63-9015-312
Progress Report
July 1963
SHC63-9015-342
Progress Report
August 1963
SHC63-9015-385
Progress Report
September 1963
SHC63-9015-433
Progress Report
October 1963
SHC63-9015-478
Progress Report
November 1963
SHC63-9015-535
Progress Report
Dec/Jan 1964
SHC64-9015-81
Progress Report
Feb/March 1964
SHC64-9015-219
Progress Report
April 1964
SHC64-9015-267
Progress Report
May 1964
SHC64-9015-329
Progress Report
June 1964
SHC64-9015-432
Progress Report
July 1964
SHC64-9015-441
Progress Report
August 1964
SHC64-9015-503
Progress Report
September 1964
SHC64-9015-582
Progress Report
October 1964
SHC64-9015-666
Progress Report
November 1964
SHC64-9015-770
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25X1A
Progress Reports (continued)
Progress Report
December 1964
SHC65-9015-30
Progress Report
January 1965
SHC65-9015-120
Progress Report
February 1965
SHC65-9015-138
Progress Report
March/April 1965
SHC65-9015-241
Progress Report
May 1965
SHC64-9015-278
Proposals
Proposal 6B -- Basic proposal submitted by
Proposal 3155 July 1960
Itek proposal to cover work on 6B proposal
25X1A
Added Task Submission June 1962
SHC61-9015-157
Change to processor necessitated by system changes.
Auxiliary facilities and equipment.
Proposal 3320
August 1961
SHC-209-61
Addendum
October 1961
SHC61-9015-271
Test and Simulation Program
Proposal 3334
F101 Flight Test Support
August 1961
SHC61-9015-209
Added Scope Proposal
January 1962
SHC62-9015-04
Revision
January 1962
SHC62-9015-24
New Optical System to accommodate system changes.
Film Drive modifications.
Interface Engineering
Program Recommendations June 1962
SHC62-9015-194
Added Scope Proposal July 1962
SHC62-9015-215
Further Test and Simulation Effort
Special Purpose Optical Bench Processor
Continuation of F101 Flight Test Support
Follow-on Proposal April 1963
SHC63-9015-161
Installation of TV Viewing Station
Continuation of F101 Flight Test Support
Interface Engineering
Experimental Processor
Special Purpose Optical Bench for field use
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Proposals (continued)
9015 Follow-on Proposal March 1964 SHC64-9015-168
Field Service
Test Support
Correlator Modifications and Detail Correlator
System Theory and Experiment
Improved Correlator
In addition, the following proposal was initiated in connection with this pro-
gram; but it covered work concerned primarily with the recorder.
Proposal for Optimum Parameters February 1962 SHC62-9015-38
The following proposals and work statements involved separate projects,
but they are an outgrowth and continuation of the work on the 9015 system.
Statement of Work July 1964
Proposed Study and Experimentation
Efforts to further "Exploitation of Radar
Imagery "
SHC64-3529-388
Detail Correlation Configuration September 1964 SHC64-3529-506
and Performance
Project 9015 Statement of Work January 1964 SHC65-9015-53
Miscellaneous Documents
Preliminary Specification November 1960 SHC9015-60-1R
Instruction Manual Volume I February 1963 not classified
Instruction Manual Volume II February 1963 SHC63-9015-102
Program
(Note: This document is superseded by the
Project Final Report where the entire contents
of SHC63-9015-143 is up dated and reproduced)
Effect of Film Exposure on Re- June 1963
corder/Correlator Performance
(This work is included in this
volume as Appendix XII)
Final Report, Test and Simulation April 1963 SFIC63-9015-143
SHC63-9015-544
Letter to Peter Hall September 1964 SHC64-9015-505
Subject: "Relocation of Correlation Activity"
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Appendix II
INVESTIGATION INTO LIQUIDS SUITABLE FOR IMMERSION PRINTING
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Appendix II
INVESTIGATION INTO LIQUIDS SUITABLE FOR IMMERSION PRINTING
In the selection of liquids to be considered, it was important that the
following be taken into consideration:
(1) Liquid must have an index of refraction close to
1.50, in that the cellulose tri-acetate films will
average close to 1.48, with the estar base types
averaging close to 1.58.
(2) Liquid must be safe to handle, insofar as personnel
are involved, or, non-toxic.
(3) Liquid must not be flammable.
(4) It must not affect the film adversely, neither emul-
sion nor base, during or after the immersion.
(5) It should have sufficient viscosity to maintain the
film in the center of passage.
(6) Liquid must dry quickly and easily, and leave no
residue.
(7) It should be readily obtainable.
(8) Liquid cannot be absorbed into, either base or
emulsion.
In the SMPTE Journal of October 1957 a group of twenty solutions were
listed. Inasmuch as many of these liquids could not be used for various
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reasons, such as. dissolving the film plasticizers, being toxic or flammable,
the following list was compiled. Several other compounds were tried
(1)
Trichlorethane . Index 1.48
(2)
Orthodichlorbenzene
1.55
(3)
Methanol (Methyl Alchohol)
1.33
(4)
Carbon Tetrachloride
1.460
(5)
GE Refractasil
1.46
(6)
Tetrachlorethylene
1.504
(7)
O-xylene
1.505
Preliminary tests consisted of soaking 1" x 10" strips of both the acetate
and mylar films in small containers of the liquid, then drying normally,
(drain and by air) and then also utilizing an improvised pair of rubber
rollers, producing a squeegee effect. Following are the results.
1. 0 Trichlorethane
This solution was discarded immediately, in that it is a solvent for the
film plasticizer, particularly with the Mylar types. It also raised havoc with
the plexiglass breadboards. Produced extreme curl and disfiguration of the
film.
2. 0 Orthodichlorbenzene
Although there was no apparent damage to the films, the liquid is most
unpleasant to use and would require extreme venting. Dried normally in
about 3 minutes, in about 30 seconds when roller squeegee was used. The
film seems to retain the odor for an hour or longer following drying.
Viscosity seems low, and the liquid is flammable. Dries very quickly
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and produced no bad effects other than slight curl following drying with the
roller squeegee.
4. 0 Carbon Tetrachloride
Dried very rapidly, both normally and with roller squeegee. Viscosity
is low and would anticipate problem in complete wetting of the film. This
solution also has property of slightly charging the film, thereby enhancing
its dust gathering capabilities.
5. 0 Refractasil
Dried very slowly by air methods, but quite rapidly by roller squeegee.
However, the rollers do take up a considerable amount of the solution, which
over a long length of film could conceivably affect its ability to remove the
refractasil, a bath of carbon tetrachloride immediately following the refract-
asil bath speeded up drying markedly with the roller squeegee system, and
did not load up the rollers as badly. Printing properties are excellent, with
no adverse affects of any kind.
6. 0 Tetrachlorethylene (Per chlorethylene)
This solution has been used with success by the technicolor corp. , in a
similar application, and results of tests here proved this to be worthy of
serious consideration. No apparent ill effects on the films were noted, its
viscosity is very good, it produces no curl or softening and dries most
rapidly.
7.0 Summary
On the basis of these findings, the refractasil and the tetra, chlorethylene
were selected as the two most outstanding, and the following tests were con-
ducted, now using the breadboard platen.
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Brass shims of .005", . 0075" and . 010" were prepared to be used as
separators in the platen.
The . 005" was quickly discarded as it did not provide adequate spacing,
even with the . 004" Mylar film. With the . 010" shim it appeared that more
bubbles occurred between negative and platen surfaces, so the . 0075" shim
was used for following tests.
92" aerial film was used and it was quickly apparent that the best method
of using this platen is to push the negative through the solution, with the sec-
tions firmly bolted together. Trying to close the platen with either the re-
fractasil or the tetrachlorethylene resulted in definite bubble formations that
are virtually impossible to remove. Air trapped between the faces of the
platen is responsible for this. Either a sliding system or an immersed hinge
affair might solve this, but threading the negative through the slot definitely
eliminates bubbles. Previous experience with this type of printing has proved
that it is most difficult to remove bubbling by a sandwich pressure system.
Apparently too much separation between faces can add to bubble trouble,
while too little will bind. These tests seem to indicate that an approximate
clearance of . 0025" is adequate, for the . 005" films.
This report, originally written early in 1960, was reviewed in May 1965.
No new materials or methods are available and the continued use of tetrachlor-
ethelene is recommended.
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Appendix III
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Appendix III
1. 0 Introduction
The focusing property of a hologram is dependent on the wavelength
of the light, the focal length being inversely proportional to the wave-
length. Thus a diffraction limited image can only be obtained with mono-
chromatic light, such as that from a laser or a low pressure gas discharge
lamp.
An incandescent source such as a carbon arc produces white light
which must be filtered before it can be employed for the correlation of
holograms. For practical reasons light obtained from a filtered "white"
source is never completely monochromatic. The fractional bandwidth
T- may be small (0. 4% in the present system) but is nonetheless an im-
portant factor in the performance of an optical correlator.
1. 1 Resolution Without Compensation
The resolution obtained for a given value of L depends on the highest
hologram frequency.
If O1 = image diameter due to filter bandwidth alone.
S2 = image diameter due to hologram bandwidth alone.
S3 = image diameter due to all other causes, assumed constant.
Then if the image functions are approximately Gaussian in form,
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bz,= 612 +622 +632
We will hold 63 constant, and will determine
filter wavelength A millimicrons
filter bandwidth AX millimicrons
hologram bandwidth W cycles/inch
(half power bandwidth of Gua s s ian pa s s band)
Diffraction angle e = fH . A
where fH = hologram frequency.
Thus, A@ = fH AA
If F is hologram focal length
M is (azimuth) magnification
61 and
62
Then in the absence of any chromatic correction bl and 62 can be
approximated by
F, F. fHL X
Ti . AO=- M
1
62=MW
Figure 1 shows these quantities for
AX= .004 X
fH = (50 + w) i. e. 50 c/inch offset.
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Filter Bandwidth Alone
~a = 0. 4%
A = .640
0 200 300 400 500 0 100 200 300 400 500 0 10 20 00 300 460 500
fH
0
fH
fH
Hologram Aperture Effect.
This is constant once W is fixed.
4 I I + T ++ i i ;
100 200 300 400 500
Max. Hologram Frequency
(W + 50 c/inch)
Figure 1
Ap
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If the aperture is now limited, i. e. fH. is limited, then bl improves
and 62 gets worse. This is shown in Fig. 2, where the best overall
resolution is obtained when the aperture is limited to 300 cycles/inch.
The actual resolution obtained here depends on 63 and is drawn for
63 = 0, but the position of the minima along the frequency axis does
not change if 83 is independent of the hologram aperture and light wave-
length.
2. 0 Prism Compensation
A possible method of compensating for the finite bandwidth of light
is to insert a prism with controlled dispersion in the optical system.
We have seen that the angular spread of light due to finite bandwidth is
Ae = fH . ox.
Thus the angular spread QA varies across the hologram getting
progressively larger toward the high frequency end of the hologram. A
prism inserted in the optical system will necessarily deviate all light of
the same wavelength through the same angle. In this case, the best we
can do is to design the prism to correct the angle exactly in the center
of the hologram, and accept some over-correction at the low frequency
end and an equal amount of under-correction at the high frequency end.
This is equivalent to correcting the "lateral" spread and leaving some
longitudinal spread along the axis through the center of the hologram.
This is shown in Fig. 3.
If fc is the center frequency of the hologram then
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AA= .004 A
Resolution
mils
--- .._.._ _ _ _ .+--_.__..._. _...__.}.. _ .....__...._ .4 _ _ _.._ _...+
0 100 200 300 400 500
Max Hologram Filter
Figure 2
Resolution Versus Aperture No Prism
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Aec = fc ? Q
Prism deviation 6 = a"(n - 1)
where yr = prism angle
n = refractive index
Thus dA do the required dispersion 9c = f and a(. do = f
ate, U-, pa c 41A c
In any specific glass the dispersion Tx is a function of wavelength.
The variation in ?n- can be reduced to a considerable extent by making
a multiple prism using several different glasses.
The actual angular spread at any hologram frequency fH after prism
compensation will be
A91 = L\X I f H - fc
The image diameter after compensation 6 1 = FMX IfH d X
If dn
is constant with wavelength, then the image diameter will be
proportional to 0X, which is generally proportional to the wavelength
X. Thus using an "ideal" prism, 61 will vary both with wavelength and
hologram frequency as shown in Fig. 4(a) which is based on a bandwidth
W of 300 c/inch and offset of 500 c/inch. The uncompensated image size
is shown again for reference at Fig. 4(b). With a practical prism, U7
will decrease with wavelength.
The effect of this on bi is shown in Fig. 4(c) for a single-glass
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prism of Z. 38? angle. The best that can be done here is to arrange the
image size to be equal at the two extremes of 44 ,a, f = 50 cycles/
inch and X = . 64 ,co, f = 350 cycle s / inch.
As discussed in Section 1.1 the overall resolution bT varies with
bandwidth and has a minimum value.
It is to be expected that with the inclusion of a compensating prism,
the usable hologram bandwidth will be increased with a consequent im-
provement in
T'
2. 1 Practical Considerations
The requirements for a prism to minimize the finite waveband are
(1) Constant dispersion of . 01 radians per micron
over . 440 to . 650 micron band.
(2) Prism design must allow insertion in the optical
system without major changes.
(3) Transmission light loss to be minimal.
(4) The prism must not introduce spherical aberra-
tion into the optical system.
After considerable investigation, it was found that these conditions
could not simultaneously be met. Some of the problems encountered
were:
(1)
A 2-element prism of nearly constant dispersion
over the required band would be desired for inser-
tion in the optical system just underneath the liquid
platen, but such a prism would have a deviation of
20 0 which cannot be accommodated. A prism in
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this position will also cause dispersion of the
zero order.
(2) Attempts to eliminate the residual deviation re-
sulted either in causing great changes in disper-
sion or in the use of impossibly large prism
angles. This would lead to a very thick prism
composed of a large number of sections cemented
together which would take a great deal of space,
be heavy, expensive and cause a large light loss.
(3) If the prism were located nearer to the output
plane where more space is available, then a
greater dispersion would be required and spheri-
cal aberration would be introduced because of the
converging beam.
As it was not possible to physically accommodate suitable prisms
without redesigning the correlator mechanically, the possibility of in-
troducing the required dispersion by means of a diffraction grating was
next investigated. The intention was to replace one of the plane mirrors
with a blazed reflectance grating. This idea is treated in the next section.
3. 0 Correction of Filter Bandwidth by Means of a Reflection Grating
3. 1 Deviation Required to Correct Image Spread
The angles of incidence and diffraction in a hologram are related by
the following expression:
sin i + sin w = M. A. f
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where m = order of image
i = incidence angle, to normal
41 = diffraction angle, to normal
A = wavelength of light
f = hologram frequency
In the present case, i and Y are small angles and we are concerned
only with first order images. Thus we can write:
i=A.f. -W
To correct lateral image spread, we require Y/ to be constant.
Thus, the required condition is
X f - i = constant
Differentiating with respect to we get
In other words, the required rate of correction in radians per inch
is equal to the hologram frequency in lines per inch.
A typical hologram contains a range of frequencies, and the correc-
tion can only be perfect at one frequency. If we correct the frequency at
the center of the hologram, then the low frequency edge is overcorrected
and the high frequency edge is undercorrected, by the same amount. The
result is to leave a residual longitudinal image spread. In spite of this,
an improvement of at least 2:1 in image size is obtained this way. The
improvement factor is fH2f H where
#H = highest hologram frequency
fL = lowest hologram frequency
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Thus in a heavily squinted hologram where fL is large, a much greater
improvement factor is possible.
3. 2 Reflection Grating
If i is the incidence angle and /3 is the reflection angle measured to
the normal of the macro surface of the grating, and if 91 'is the groove
angle
Groove angle cac' _ /3
2
Total reflection angle 0 = i +13
In a blazed grating, we require the light to be reflected from the
grooves in the same direction that it is diffracted. Thus:
a(sin 13- sin i) = M~
where a = groove spacing
Angular dispersion d/3 = m
dpi a cos
Combining these equations, we
cot of = tan 0 + 2
~` dA
MA
2 cos sin of
Thus, given the total reflection angle 0, the wavelength A and the re-
quired angular dispersion we can determine the grating frequency and
blaze angle.
The best position for a reflection grating appears to be in place of the
bottom mirror. This is after the zero stop and so avoids any trouble due
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to shifting the zero order image. Also the angular dispersion, here is
greater, which requires a higher grating frequency making the grating
more practical in this case.
The angular dispersion required at any point in the system other
than at the hologram itself will now be determined.
Let the hologram focal length be F0
field lens focal length be Fl
relay lens focal length be F2
cylinder lens focal length be F3
spacing of field and relay lens principle planes be A
spacing of relay and cylinder lens principle planes be B
The image formed by the hologram and field lens will be at a dis-
tance xl given by
Fo Fl
Fo+ F1
The distance of this image from the relay lens F2 is
The virtual image formed by the relay lens will be at a distance
F2 x2
x3 _F 2- x2
Finally, this image will be at a distance x4 from lens F3 where
x 4 = B + x 3
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Then if 90 is the angular deviation of the beam at the field lens F1,
the angular deviation of the beam emerging from F3 will be
6 = X3 . xl . 9
3 x4 x2 0
If the mirror is situated a distance x5 from the lens F3 and the final
image plane is a distance x6 from lens F3 then the deviation required at
the mirror is
e
=e
x6
4
3
x6-x5
xl
x3
x6
E) -
e
.
4 x2
.
x4 x6 - x5
0
3. 3 Calculations
If the frequency at the hologram center f = 250 cycles
the required correction at the hologram is
di 250
d = 2 radians/micron
= .0098 radians/micron
per inch, then
We will round this off to . 01 radians/micron. The angular deviation re-
quired at the lower mirror position will be
.01 . xl . x3 x6 radians/micron
x2 x4 x6 - x5
where xl = 20. 6 inches
x2 = 2.97 inches
x3 = 3. 61 inches
x4 = 12.31 inches
x5 = 5. 5 inches
x6 = 39 inche s
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Angular deviation required = . 01 20.6 3.61 39 0236 radians/
2. 97 2. 31 33.5
micron.
The total reflection angle 0 = 370
= 18.5, tan=
= . 550 micron
dT
.335, cos
d13 _ n.,36
a.---/
;
-
r
cot of = tan 0 + 2
dd
dA
= .335 + 55 x2.0 3 = 154. 3
Then groove angle os' = 0. 37?
Groove spacing = m
2 cos 2 ? sin os
.550
1.89 x . 00647 microns
This is equivalent to 22.3 grooves/mm.
3. 4 Practical Considerations
The effectiveness of a reflection grating in this application depends
on the efficiency of the blazing; with efficient blazing all the incident
energy is directed into a single diffraction order. In the present case,
diffracted energy of the first order only is required: the presence of
appreciable light in the zero and higher order images will cause
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overlapping data.
Data from Bausch & Lomb indicated that it was possible to rule
gratings in which over 90% of the incident energy was directed into a
single order, although they could not guarantee this with a grating of
such low frequency. The main problem is in preserving the flatness
of the reflecting surfaces of the groove.
Test gratings were ordered from B & L on a best effort basis.
It was found on testing these gratings that only about 50% of the
incident energy was actually diffracted into the first order, making
the gratings unusable for the intended purpose. This was apparently
due to the difficulty of holding optical flatness in the reflecting surfaces
of a coarse grating, due to the width of cutting tocl required.
4. 0 Conclusions
The only feasible method of compensating an optical correlator for
finite filter bandwidth appears to be the use of a prism in the collimated
beam adjacent to the input film. This would introduce a bend in the opti-
cal system, and cause dispersion of the zero order, both of which effects
would have to be taken account of in the initial design of the optical system.
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Appendix IV
INSTALLATION REQUIREMENTS
This appendix contains a few selected sections from the Operator's
Manual. These are reproduced here for the convenience of personnel
who may have to provide facilities for the Processor. If possible,
recent log books and/or operating personnel should be consulted for
further details.
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Appendix IV
1. 0 Introduction
1.1 General
This manual contains operation and maintenance instructions for the
Model 9015 Processor manufactured by Itek Corporation. Classified infor-
mation pertaining to Sections III, IV, and V are contained in Volume two.
The Model 9015 Processor (See Fig. 1) is used to enlarge one-half of a
92 inch wide input film and to expose the enlarged area onto a 92 inch wide
output film.
1.2 Description
1.2.1 Physical
The Model 9015 Processor consists of a carbon arc unit and an optical
unit (see Fig. 1). The carbon arc unit contains the carbon arc lamp with
its rectifier power supply and water circulator. The optical unit contains
the optical system, the input and output film drives, and the film drive
controls and power supplies.
1.2.2 Functional
The Model 9015 Processor provides a 92 inch wide output film showing
an image area that is a 2X enlargement of one half of the image area of its
9? inch input film. During this process, the equipment performs the follow-
ing functions:
(1) Drives the film at constant speed.
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Figure 1
Model 9015 Processor
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(2) Maintains the film at the proper tension through-
(3)
out the operation.
Stops the film drive mechanism upon the occur-
rence of the following:
a. Failure of certain mechanical components.
b. End of film.
(4) Provides for automatic operation (once the unit
is started).
(5) Enlarges one-half the input film and exposes the
enlargement on output film having the same width
as the input film.
1.3 Equipment Characteristics
The physical and electrical characteristics of the Model 9015 Processor
are as follows:
(1)
Input power requirements:
a. 120 volts, 15 amperes, 60 cps, 1 phase, 3 wire.
b. 208 volts, 60 amperes, 60 cps, 3 phase, 3 wire.
(2) Temperature limits: 70 + 5?F, relative humidity
at 40 + 10 percent.
(3) Mounting:
a. Arc unit: on frame fitted with jackscrews and
casters. Floor moutning provided by lifting
the frame and casters off the floor by the
jackscrews.
b. Optical unit: self-contained cabinet fitted with
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(5)
operating or servicing the Model 9015 Processor.
jackscrews and casters. Floor mounting
provided by lifting the cabinet and casters
off the floor by the jackscrews.
(4) Overall dimensions (arc unit plus optical unit):
100 inches high, 114 inches wide, 482 inches
deep.
Fuse complement:
a. Two type 3AG, SLO-BLO, 0. 5 ampere.
b. Two type 3AG, SLO-BLO, 0. 6 ampere.
c. One type 3AG, 3 amperes.
d. One type 3AG, 6 amperes.
2. 0 Accessory Test Equipment
2. 1 General
Table 1 lists the accessory test equipment and special tools used when
Table 1
Test Equipment
Manuf. & Model No.
Application
Volt-ohm milliammeter
Simpson Electric Co.
Voltage measurements
Model 260
continuity checks
Theodolite (with auto-
Wild, Model T-2
Alignment of optical unit
collimating eyepiece)
Mirror (7 inches square)
Libbey Owens Ford
Glass Co. (high quality
plate glass)
Centering fixture
Itek Corp. (drawing
Centering Fl & F2 lenses
9015-0523)
Centering fixture
Itek Corp. (drawing
Centering relay lens
9015-0522)
Test film
Itek Corp. (drawing
Focusing of optical unit
9015-0521)
Lamp house draft gage
Strong Electric Corp.
Draft measurements for
(for lamps using 75-
carbon arc exhaust duct
100 amperes)
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3. 0 Installation
3. 1 Site Slection
3. 1. 1 Power Requirements
The Model 9015 Processor requires the following sources of external
power:
(1) 208 volts, 60 amperes, 60 cps, 3 phase, 3 wire
terminating in a fuse box with 60-ampere fuses
in each line.
(2) 120 volts, 5 amperes, 60 cps, 1 phase, 3 wire ter-
minating in a standard grounding type outlet.
(3) 120 volts, 10 amperes, 60 cps, 1 phase, 3 wire
terminating in a standard grounding type outlet.
The power listed in tems (1) and (2) of paragraph 3. 1. 1 is required by
the arc unit that in item (3) by the optical unit.
3. 1. 2 Temperature and Humidity
The Model 9015 Processor is designed to operate at a temperature of
70 + 5?F and a relative humidity of 40 + 10 percent.
3. 1. 3 Intake System Requirement
The arc unit requires an 8-inch diameter intake duct. No blower should
be used.
3. 1. 4 Exhaust System Requirements
The carbon arc lamp of the arc unit requires an 8-inch diameter exhaust
duct. The exhaust blower in the lamp hood removes exhaust gases from the
arc. An additional blower in the upper stack is required to remove the ex-
haust gases from the exhaust system. This blower should have an air
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velocity of approximately 700 linear feet per minute.
If the upper stack blower is inadequate, the
exhaust gases will back up into the Processor
area and into the lamp house.
The optical unit requires an exhaust system capable of exhausting 250
cubic feet of air per minute. A 6 inch diameter duct is required for this
purpose. A 4 inch diameter duct is also required to exahust the condenser
cooling system.
The optical unit exhaust ducts must exhaust
independently into the atmosphere. Their
outlets must not be located near the intakes
of any system, including those of the Model
9015 Processor.
3.1.5 Darkroom
The installation area must include a darkroom for loading and unloading
the output magazine.
3. 1. 6 Dust and Dirt Control
The importance of controlling dust and dirt within the area assigned to
the Model 9015 Processor cannot be overemphasized. Accumulation of dust
and dirt on the internal lens of the equipment causes not only loss of illumi-
nation, but, what is even more important, loss of reproduction resolution
due to the scattering of collimated light rays. Although the ideal area, which
has a sterile, dust-free atmosphere, is impossible in view of personnel
activity and the materials used, areas which approximate the ideal should be
seriously considered in preparing to install the equipment.
The main source of dirt is the outside air, which generally contains dirt
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in the form of dust or cinders. Common types of open-air contamination and
the common methods for the removal of each type are listed in Table 2. Per-
sonnel introduce dirt through their activities or through their clothing.
Equipment also introduces dirt in the form of metal particles from moving
parts, oil deposits from bearings, and dust particles from carbon arcs.
Most dirt can be removed from the air by ordinary commercial air filters.
The best of these, however, only cuts down the amount of cleaning required.
Some electrostatic filters have proven advantageous in photographic practice.
Filters made of bundles or mats of soft crepe or cotton pads give good results
and require less maintenance. Since no filter is perfect, some smoke and dirt
deposits accumulate on the walls and ducts. These deposits are usually dis-
lodged later by vibration or an accidental blow. Dirt from this source is
serious in photographic work. It can be substantially reduced by viscous
filters on the ends of long runs of duct work. Ducts should be made of smooth
material and constructed so that they can be easily and thoroughly cleaned.
The air movement associated with air conditioning causes more dirt to
collect on the films and lenses, thereby increasing the need for air filtration.
However, the ducts and fans of existing air conditioning systems can be uti-
lized for systems which filter dust from the laboratory air.
The preparation of the assigned area for dust and dirt control should be
supplemented by thorough dirt inspection and cleaning routines.
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Scale of Atmospheric Impurities
Particle Type
Heavy industrial dust
Size Range,
microns
100 and up
Method of Removal
Cyclone separators
General dust
1
- 100
Dynamic precipitators
Fly ash
3
- 70
Water spray; air filters
Fog
1
- 40
Air filters
Pollen
20
- 60
Air filters
Plant spores
10
- 30
Air filters
Bacteria
1
- 15
Air filters
Fumes
Air filters and. electrical
Pigments
7
precipitators
Electrical precipitators
Smoke
0.
001
0.
3
Electrical precipitators
Tobacco smoke
0.
01
- 0.
15
Electrical precipitators
Oil smoke
0.
03
- 1
Air filters and electrical
precipitators
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Appendix V
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Appendix V
Qty.
Description
5
AGC 3 Amp
Main power sup-
F203
Fuse
5
AGC 6 Amp
Little Fuse
ply
TV control
Fuse
5
AGC 10 Amp
Little Fuse
TV control
Fuse
5
AGC 4 Amp
Little Fuse
TV control
F9 01
F903
F904
5
AGC Slo Blo
Little Fuse
Loop controller
F302
5
.6 Amp
AGC Slo Blo
Little Fuse
Loop controller
F301
Circuit
1
.5 Amp
AM-12
Heineman
Power input
CB201
Breaker
Lamp
2
No. 1820
General Electric
Panel light
DS405
Lamp
10
T-34 NE-51
Cleveland, Ohio
Dialight Corp.
Panel lights
DS401
Relay
1
MH17D 24 VDC
Brooklyn, N. Y.
Potter & Brum-
Loop controllers
K301
4 PDT
field, Princeton,
K302
Ind.
K304
Relay
1
MH17D 115V
Potter & Brum-
Loop controller
K303
Relay
AC.A
field, Princeton,
Ind.
Potter & Brum-
Loop controller
K101
field, Princeton,
Ind.
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Item
Qom.
Light
1
Light
2
Switch
Relay
1
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Description
25 watt 120 V
frosted
No. 47 mini-
ature
90326
Switch
Switch
Switch
1
1
5
Drive
Wheel
1
Drive
Wheel
1
Motor
1
Motor
1
Motor
1
Motor
1
138866A3L
138867A3L
DTZRVZ-A7
9015-0689
9015-0652
N29GMW
B8194E-120m
ALPJRE
NSH-12R
Where Used
Part No.
General Electric
Cleveland, Ohio
General Electric
Cleveland, Ohio
Strong Electric
Toledo, Ohio
Strong Electric
Toledo, Ohio
Arc Unit 19039
Arc Unit
Arc Unit
Control panel
S401
S403
S101
silo
S114
Ucinite
Control panel
Sill
Ucinite
Control panel
S112
Micro switch
Safety circuit
S209
S212
S215
S219
Haydon Switch
Loop control
(many)
Waterbury, Conn.
switches (inter-
changeable with
No. 5227)
Itek Corp.
Lexington, Mass.
Itek Corp.
Lexington, Mass.
Input film drive
Output film drive
Main drive motor
B201
Bodine Elec. Co.
Condenser cooling
B212
Chicago, Ill.
Electric Indicator
Reel torque motor
B209
Stamford, Conn.
Bodine Elec. Co.
Loop drives #1 & 2
B204
Chicago, Ill.
B205
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 tion
Descri
Manufacturer
Where Used Part No.
R~y,
p
Motor
1
20-02 - IN
Inland Motor
Film torque motor
B202
T1231B
Northampton,
Motor
1
2114C
Inland Motor
Northampton,
Reel torque motor
B210
Motor
1
KC1-23 IN
Bodine Elec. Co.
Loop controller
B206
Chicago, Ill.
B207
Rheostat
1
H500-562 shilo Ohmite
Intensity control
R201
Chicago, Ill.
R203
Resistor
1
lOW 50 ohm
Ohmite
Intensity control
R204
Chicago, Ill.
R202
Capacitor
1
T30ZN 34 -
Aerovox
Input supply motor
C202
400 VDC 3. 0
mfd
Capacitor
1
T30ZN 34 -
Aerovox
Blower motor
C21Z
400 VDC 4. 0
mfd
Capacitor
2
VC 1164B
Aerovox
Loop control
C206
C207
Loop
controller
1
9015-1038
Itek Corp.
Lexington, Mass.
Electronic chassis
9015-1076
Itek Corp.
Lexington, Mass.
Main drive
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Appendix VI
DETERMINATION OF THE VELOCITIES OF MOVING TARGETS
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Appendix VI
DETERMINATION OF THE VELOCITIES OF MOVING TARGETS
1. 0 Introduction
A coherent radar system records the radar return in such a manner that
moving targets can be identified. The signal histroy left by a moving target
will be slightly different from that for a stationary target. These differences
would lead to a slight image blur and/or image displacement in a correlator
such as the one used on the IR & D program 5271. However, a correlator of
the proper calibration could detect the differences and determine the velocity.
The velocity of the target is the geometrical sum of two perpendicular
components: one component parallel to the path of the airplane, and the other
component normal to the path. The former would appear as a change in the
focal plane, and the latter as a lateral displacement, of the correlated image.
Each of these components would be measured separately in the correlator,
and each is treated separately below.
2.0 Analysis
The following analysis considers first-order effects only. It is assumed
furthermore that the velocity of the target is constant while it is in the antenna
beam.
The expression for the focal length of radar data is
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V 2 R r r
F H =
where V = film velocity
Vr = vehicle velocity
R r = range
= radar wavelength
r
= correlator illumination wavelength.
0
In the case of a parallel moving target, only Vr, in effect, will change. Let
subscript m denote a moving target, and let Vmx denote the target velocity
component parallel to the vehicle path. Then the focal length of the data re-
lating to the moving target is
F =F
m H
where positive Vmx is taken to be the same direction as the vehicle's motion.
The change in data focal length is
LF = Fm - FH
F = FH
V
r
V
r 2
- Vmx/
Finally, target speed in terms of iF is given by
FH
Vmx = Vr (1?FH J
Since we assume that the target velocity will be less than the vehicle velocity,
only the minus sign in the above expression need be used.
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It is well to remember that in this expression FH is the focal length of the
data itself; correlator optics have not yet been considered.
2. 2 Perpendicular Motion
Analysis of perpendicular motion requires an understanding of the Doppler
shift. The Doppler return from a stationary target is shown in Fig. 1.
Figure 1
This frequency appears as a modulation of the radar carrier frequency fr.
The carrier is normally heterodyned down to zero so that the modulation
ranges from zero cycles out to its high-frequency limit fD max' as shown
in Fig. 2.
Carrier Highest Doppler return
freq. (fr frequency (f D max + f r
frequency No
(a) Modulated return
,~Z
(b) Return with carrier removed
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Range of Doppler modulations
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Target motion in the normal direction will produce a change in the Doppler
spatial frequencies. Suppose a target is moving at a constant velocity Vmy;
2Vm
the shift in frequency will then be . Let positive Vmy denote motion
away from the vehicle path, and negative Vmy motion towards it. In Fig. 3
the solid line represents the normal spectrum of the data, and the broken line
2Vm
represents the spectrum of moving-target data which has been shifted by
frequency No
Figure 3
The correlation appears relative to where the zero frequency of the Dop-
pler modulation appears on the data film, for the modulation is a hologram,
which acts like a lens: if the optical axis moves, the image moves. Thus a
shift in the Dopper return causes an azimuth offset of the correlation. This
offset can easily be calculated by reference to Fig. 4.
FH
Figure 4
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The axis represents zero frequency, and the frequency at any other point on
the hologram is denoted by the variable fD, the Doppler frequency. From
previous studies we know that
g = FH Xo fD'
where g is the distance from the axis to the point where the frequency fD ap-
pears, and A o is the wavelength of the correlator illumination. The offset
can be denoted by Ag, and the Doppler shift by A fD. We have then
Ag = FH X0 AfD.
2v
We know though that AfD is simply m
, so
r
Og=2V F
my H
This gives the correlation offset distance at the natural focal length of the
data. Finally,
Vmy =
Xr
A g.
ZFH o /
3.0 Measurement
The following discussions assume a correlator without range compensa-
tion. With compensation the need for the range-variable graphs will be
obviated.
3. 1 Parallel Motion
A change in the data focal-length results in a change in the position of
the output plane, which can be readjusted to focus by means of a cylinder
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lens. It is difficult to calculate from system parameters the amount of move-
ment required by the cylinder lens; therefore a means has been devised to
calibrate the correlator.
Test holograms of known focal length can be inserted in the system, and
the position-at-focus of the cylinder lens noted. From these points a curve
of data focal-length vs. cylinder lens position can be constructed, and from
the curve one can convert a change-in-cylinder-position to a change-in-data-
focal-length. Since we have seen that a change in focal length is proportional
to velocity, there must also be a curve by which a change in data focal-length
can be converted to velocity.
3. 2 Perpendicular Motion
In this case the correlator can be calibrated by successively inserting
the test holograms and moving each by a known amount. The resultant off-
set can be noted for each, and a graph constructed. One picks the appropri-
ate value of FH, then reads the corresponding ratio of Qg , where At is
the amount of offset in the correlator output. Since At can be measured,
Ag can be found and substituted in the equation for V m
Y .
There is, however, a problem involved in finding the offset distance,
namely: from where is the correlation offset? Most ground vehicles travel
on predetermined paths: automobiles on highways, trains on tracks, etc.
One simply decides where the target was probably traveling, and measures
the offset distance from that point.
Another class of targets is more difficult: ships at sea, sports cars on
sand flats, etc. There are no predetermined detectable paths for these tar-
gets, so assuming the target is relatively isolated one can measure its
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spectrum and compare it to the spectrum of the complete data. The difference
between the two is then the Doppler shift, as was shown in Fig. 3; and the
appropriate equation is
Vmy = 2r QfD?
This method is, of course, applicable to any type of moving target so long as
the target can be effectively separated from its environment in such a manner
that AfD can be measured.
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Appendix VII
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Appendix VII
1. 0 Introduction
The signal-to-noise ratio and diffraction ring ("side lobe") suppres-
sion of an aperture-limited system can often be improved by use of
aperture weighting. Investigations of the detail correlator were begun
about a year ago. The first finding was that photographic film, on
which filters are normally made, was insufficiently flat, and impaired
the resolution of the relay lens. Obviously optical-quality glass was
required for the filter. Another difficulty arose from the granularity
of the photographic emulsion, which tended to scatter too much light.
Deposited aluminum filters were chosen finally because they offer
much better scattering characteristics, although such filters are more
difficult to fabricate.
The varying transmission is obtained by depositing the aluminum
through a narrow slit which oscillates in front of the surface to be
coated. Gradations in density are controlled by the velocity of the slit,
since the evaporation rate is constant. A cam of a certain profile is
required to drive the slit in the proper manner. The cam operates
through a linkage which can be adjusted for any desired bandwidth.
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2. 0 Determination of Cam Profile
The nomenclature in this section is as follows:
d = rate of evaporation
D = density
V = slit velocity
s = slit width
N = number of revolutions
t = time/revolution
0 = angle of cam revolution
x = distance traveled by the slit
Now we can formulate the basic equations. First,
D = dNt (rate of evaporation x total time)
D=dN(2Vs)
V = D (where k = 2dNs).
And second,
d9 = w (a constant),
at
dx =
at v (a variable).
Substituting and integrating,
do w
ax = v
x
0 = k D dx.
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This last equation means that one must construct a graph of the desired
density-displacement function and integrate, presumably by direct measure-
ment. For each value of displacement x there will be a unique 9, so the
shape of the cam is now completely specified.
3. 0 Designing the D-x Curve
The optical system is represented in Fig. 1.
Figure 1
frequency
plane
relay lens
(magnification of . 646)
g = m AfF,
as shown in Fig. 2, where f and g are the variables. The frequency plane
F
grating of frequency f frequency plane
Figure 2
displays the spectrum of the input material.
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By calculation, in the optical system of Fig. 1,
g = m XfF
_ (. 646) (2. 5 x 10-5) (24) f
f = 3. 88 x 10-4 = . 388 miles per cy./inch
f
g = 2. 58 cy. /in. per mil
By actual measurement on the system itself,
R = 3. 94 mils per cy./in.
f
f
= 2. 54 cy. /in. per mil,
g
which is in excellent agreement with the calculated values.
The spatial frequency spectrum of the input film was measured and found
to be as in Fig. 3. It agrees with values that had been calculated
200 cy. /sec.
r--z- - __ -~-
200 400 600 800
cycles/second
Figure 3
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some time ago. The bandwidth at the half transmission points is 125 cy./sec.
(The cy. /sec. designation incorporated the film speed factor of 1.2 in. /sec. }
Now the D-x curve can be drawn, for we know the bandwidth of the data,
the location of peak data response, and where this frequency appears on the
Fourier plane of the optical system. A model of the curve for 250 cy. band-
width appears in Fig. 4.
0.4 0.8 0.12
Displacement x in inches
Figure 4
One assumption was made in the construction of this curve. If the center
were actually zero density the velocity of the slit would be infinite. This
is clearly impossible so a minimum density of 0. 3 was chosen, which led
to a maximum density of Z. 0. The final specifications for the cam are at-
tached.
4. 0 Cam Profile Tolerance
The controlling factor on film accuracy is the cam-follower velocity,
i. e. the slope of the cam profile. At the filter center let us assume a
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maximum allowable tolerance of +20% of the transmission. The fractional
density variation is then + log10 1. 2 = +. 075. The center density is 0. 3, so
the permissable change in density is + ' 075 5 = +. 25. Because density is in-
versely proportional to velocity the tolerance on velocity is +25%.
The cutting stations on the cam profile are spaced 4 mils in radius. Thus
a 25% error in slope corresponds to an error of one mil between cutting points,
or an error of 0. 5 mil in each cutting point in the worst case.
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Appendix VIII
INTERFERENCE PATTERN GENERATOR
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Appendix VIII
INTERFERENCE PATTERN GENERATOR
1.0 Summary
This report contains an analysis and design information for an optical
device that generates an area interference pattern using a photographic trans-
parency as input. An area containing patterns of any desired length, frequency
and focal length can be generated by this method. The problem of obtaining a
pattern of varying focal length in one dimension to simulate range has not yet
25X1A been solved. The method was first proposed by in memoran-
dum ED-M-510 dated 12 December 1962.
2. 0 Basic Principle
2. 1 Radar Pattern
The pattern we wish to simulate is that due to the phase shift of a radar
signal emitted from a vehicle at A, reflected from a target T and received
back at A as shown in Fig. 1. The vehicle velocity is assumed negligible
compared with the propagation time of the radar signal.
The phase shift is given by
0 __ ZAT 2
R ~ R ~R
where XR = radar wavelength
R0 = offset range
x = distance along vehicle track
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Figure 1
Radar Geometry and Interference Pattern
Figure 2
Simulator Geometry
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The spatial frequency produced by this phase shift is
F = dO 2 x 2 sin 9R
R UT A R o + x2
The pattern frequency gradually drops to zero at the point opposite the
target as shown in Fig. 1.
2. 2 Simulated Patterns
Figure 2 shows the essential geometry of the simulator. Consider a
wave emitted from A in the direction AX, and a second wave coherent with
the first travelling in the direction XB.
The phase difference between wavefronts at point X is
AX+ BX
OS - 0
If the point X lies on the axis and AX = BX then
2AX
=
_
S
Pattern frequency
0
F = 2 x = 2 sin 90
s Xo d2 + x2 Ao
Thus a pattern with similar properties to the radar pattern is generated.
Note that it is essential for the wavefronts to be travelling in the directions
indicated, away from A and toward B, or vice versa, This can be seen from
Fig. 3(a) and (b) which show the interference patterns produced by two
spherical waves centered on focal points a short distance apart. In Fig. 3(a)
both points are radiating coherently to produce an interference pattern at
plant P. This is not the pattern required. If the direction of one of the
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Movement of
wave crest
Figure 3(a)
Figure 3(h)
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Interference Pattern with Both Sources Radiating
Si
P
Movement c
wave cres
S N
Direction ofwavefronts
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wavefronts is reversed as in Fig. 3(b) the required pattern is produced along
the plane P. In practice an opaque film would be placed at P and both waves
would impinge from the same side as indicated in the diagram.
2. 3 Optical System
The optical system necessary to implement this idea is shown in Fig. 4.
The transparency is illuminated with collimated, monochromatic light from
source S. In the range dimension the transparency is imaged directly onto
the film plane by the spherical lens L1.
In the azimuth dimension, in which the interference pattern is required,
the lens L1 would normally image the transparency in the same plane. How-
ever, two addition cylindrical lenses L2 (positive) and L3 (negative) split this
into two images at points A and B. The two wavefronts produced by these
lenses form the desired interference pattern between points C and D as
shown.
The lens stop is vital to operation of the system. It is essential that the
two wavefronts exactly overlap to produce the pattern. Any spillover will re-
sult in the film being fogged.
Exact overlap is achieved when the two sides of the lens have apertures
in proportion to their focal lengths, as shown. The zero stop must be of suf-
ficient width to give the desired pattern offset frequency.
Design formulae for the optical system are developed in the next section.
3. 0 Analysis of Pattern Simulator
The following analysis is based on a single point T on the transparency.
It is equally applicable to an ensemble of points.
Referring to Fig. 5, let the phase angle of the wave reaching Al be 00
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sua-r T'eo
-T.IPUTTAO 4tTds
do3s suaZ
suet Teot.zaqds
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Figure 5
Optical Geometry
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and let the phase of the wave reaching B1 be 0o +
upper wave at D1 is
1 1
0.U = 0o + A D
Phase angle of lower wave at D1 is
OL=0o+0l -
D1B1
01'
Then phase angle of
- l wavelengths.
AO=0U-0 =A1 D1+D1B1 Cb
A1Dl = 1/a2 + (PC1 + x)2
PC1 = a tan ar
.'. A1D1 = a` + (a tanor + x)
Similarly
D1B1
+(btanof-x)2
Qo_ Vd2+(atanoc+x)2 + - \ / b 2
x
,LO
b the spatial frequency F = d
Scx
x + a tan of + x - a tan of
A (x + a tan oc)2 + (a tan oc - x)
= 1 sin (a