WESTINGHOUSE PROGRESS REPORT -1 JULY 1963-30 JULY 1963

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP67B00657R000200210037-3
• Release Decision: RIPPUB
• Original Classification: S
• Document Page Count: 25
• Document Creation Date: December 22, 2016
• Document Release Date: December 9, 2010
• Sequence Number: 37
• Publication Date: September 29, 1963
• Content Type: MF

ILLEGIB
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OXC-5723
Copy k of 3
27 September 1963
MEMORANDUM FOR: Deputy for Technology, OSA
SUBJECT Westinghouse Progress Report -
1 July 1963 - 30 July 1963
Attached for your information and file are two (2)
copies of Subject report.
Chief, Contract
CD/OSA-DD/S&T:J sjj
Dist: 1 - D/Tech w/2 cpys rpt/OXC-5715
2 - CD/OSA-WE-1000 T&P w/1 cpy rpt/OXC-5715
3 - RB/OSA
viskon, OSA
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25X1
25X1
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SECRET
Advanced Vlans & Programs Division
Deputy for Systems )agement
Ng. Aeronautical Systems Division
Wright-Patterson Air Force Base, Ohio
Westinghouse Electric Corporation
HI,,,WITimIL:m;Irl:mil An-purr
ft11,111,
21203
Sptember 11., 196
8848T
i3UBJEC1J!: Contract AF 33(600)40280; Sub-
misst:?n of Progress Report for
July 1963; Westinghouse Refer-
ence MD-45196.
1;ncloeure (1): Three (3) copies of Progress Report for the period of
July 1, 193 to July 30, 1963.
Gentlemen:
In accordance with the subject contract, we are enclosing the
Tionthly Progress Report for July.
Very truly yours,
WESTINGHOUSE ELECTRIC CORPORATION
NWE:sk
Encl.
IF ENCLOSURES ARE WITHDRAWN (OR NOT ATTACHED), THE
CLASSIFICATION OF THIS CORRESPONDENCE WILL DE CAN.
. CELLED IN ACCORDANCE WITH PAR 25F AF REGULATION 205-1
OR NAVY REGULATION ARTICLE 76 (5) (11).
25X1
Marketing Specialist
Marketing Department
(with one copy of Enclosure) 25X1
SECRET
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,
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PROGRESS REPORT
Period of July 1 to July 30, 1963
Contract No. AF33(600)40280
TABLE OF CONTENTS
PROGRAMS
A Flight Test
B Environmental Test
C Design Evaluation 11
EQUIPMENT
D Antenna 14
E Recorder 15
F Switch Tubes 18
G Synchronizer 18
H Transmitter 19
I Field Test Equipment 20
J Motion Compensation 20
K Radome 22
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cir,t "-IT) rim
A FLIGHT TEST PROGRAM
GENERAL
Specific targets recorded during the three flights
(70 to 72) made this month are city parks, railroad yards, portions
of Fort Meade, Maryland, storage sheds and buildings at the Army
Ordnance Depot in Baltimore, and structures of the Bethlehem Steel
Mills at Sparrows Point, Maryland and of Fairless Steel Mills near
Trenton, N. J. Other general targets resolved are highways
housing groups, railroads, and harbor facilities.
Azimuth resolution is improved over recent flights due
to operating the system with an unusually high offset frequency,
275 to 330 cps. Many dots with 5 mil (20 - 25 feet) azimuth
dimension are registered and many instances of only 3 mil (12-15 feet)
dot separation are recorded. The range of equivalent ground
distance depends on the scale factor used when preparing the
correlated film.
The aircraft doppler navigation system which supplies
drift angle information to the pilot and ground speed information
to the automatic film speed control failed on all three flights.
However, by setting the system VFO for "leakage zero beat" and
flying the aircraft on a heading which maintained the antenna pod
at zero degrees the pilot was able to determine his course for a
zero drift flight. The pilot then maintained a true airspeed re-
quired to achieve a ground speed of 830 knots. A constant 830
knot signal to the film speed control established a recorder film
speed of 1.224 inches per second.
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SEr'h 71"
PRIMARY FILM
The focus of the projection of the CRT trace onto
the film was improved by adjusting the CRT in its mount. However,
the first 3/4 inches of each range sector is slightly defocused.
This may be due to poor dynamic focusing,fUrther misalignment of
the Cr or a combination of both of these items.
Striping due to vibration is very bad. This striping
of 200 cps has higher amplitude in the near range sector than the
far range. The far range sector has an additional frequency com-
ponent too high to be measured with handviewers which is probably
the 480 cycle measured on the optical correlator. Frequency com-
ponents up to 300 cps can be detected during function generator
tests by using a 12X magnifier. Higher frequencies than this may
be recorded, but are masked by the striping.
The primary video (oatmeal) recording is very high in
frequency and low in amplitude because of the higher offset
frequency used on flights 70 to 72. The doppler frequency tracker
was set to track between 330 and 275 cps on the last three flights
while previous flights utilized an offset frequency of 225 to 250 cps.
Despite these higher offset frequencies, many zero and near zero
holograms were produced, caused by targets which are illuminated
by the antenna skirts and side lobes.
As an aircraft approaches a point target the doppler
shift in frequency due to the target is F?h6) where V is
d 3r5.
aircraft velocity, ?) is radiated wavelength, and 9 is the angle
in azimuth of the target from a line normal to the aircraft flight
path.
?2?
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Figure 1 represents the azimuth radiation pattern of
the system antenna, and the following is a tabulation of approximate
doppler frequencies at points along the antenna pattern.
db
0
Doppler Frequency
Leading Trailing
0 0
74 120
3
134
220
6
195
316
10
243
414
10.5
245
420
With an operating offset frequency of 250 cps above the
reference frequency, any target giving return below 10 db would
produce "oatmeal" or holograms starting low and increasing in
frequency. However, very large targets exceeding this 10 db
point would produce doppler frequencies beyond the offset thus
producing holograms going from high to zero to high. The higher
the offset frequency, the fewer zero holograms and the higher the
oatmeal frequency.
While a high offset frequency reduces holograms passing
through zero, a desirable advantage, it also accounts for weak
oatmeal registration on the primary film. As noted, the primary
recording is one of a frequency inversion process. Targets which
produce low frequency (happier (such as ground return) also produce
high frequency "oatmeal" A high offset frequency produces oatmeal
frequencies which approach or exceed the recorder band-pass and thus
produces weak film exposure.
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Figure 1 represents the azimuth radiation pattern of
the system antenna, and the following is a tabulation of approximate
doppler frequencies at points along the antenna pattern.
db
0
Doppler Frequency
Leading Trailing
0 0
74 120
3
134
220
6
195
316
10
243
414
10.5
245
420
With an operating offset frequency of 250 cps above the
reference frequency, any target giving return below 10 db would
produce "oatmeal" or holograms starting low and increasing in
frequency. However, very large targets exceeding this 10 db
point would produce doppler frequencies beyond the offset thus
producing holograms going from high to zero to high. The higher
the offset frequency, the fewer zero holograms and the higher the
oatmeal frequency.
While a high offset frequency reduces holograms passing
through zero, a desirable advantage, it also accounts for weak
oatmeal registration on the primary film. As noted, the primary
recording is one of a frequency inversion process. Targets which
produce low frequency (happier (such as ground return) also produce
high frequency "oatmeal" A high offset frequency produces oatmeal
frequencies which approach or exceed the recorder band-pass and thus
produces weak film exposure.
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CORRELATED FILM
FILM
A radar map was produced from each of the three primary
films corded this month. In general, video is weak but strong
enough to allow comparison of the aircraft flight path with maps.
Unfortunately, the heavy vibration striping on the primary film is
also on the correlated film and detracts from the map quality.
A time marker is needed on the correlated film to permit
easier interpretation between the primary and secondary films. When
the primary recordings are weak or if land-water contours are not
visible, it is difficult to identify land-marks" to establish
correlation.
Many dots registered on the secondary film have range
"feathers" caused by excessive pedestal amplitude in the trans-
mitted pulse. These feathers are bright lines ahead of and behind
the main dot representing a target and vary with target size.
Typical target dimensions are 5-10 mil actual dot size, 10-20 mil
leading feather, and 5 mil trailing feather. Holograms producing
reathers are approximately twice as wide as holograms without
range feathers.
No azimuth distortion or azimuth feathers were noted
on 5-70 and S-71 film. Typical azimuth dot sizes measured on
these films are 5 to 10 mils (20 to 40 feet) and many instances
of 3 mil (12 to 15 feet) separation were detected.
On 5-71 film, there are several instances where dots
appear to be stretched diagonally. However, close examination
with a 12X magnifier reveals adjacent dots are running together
due to what looks like film over-exposure. Spacings of 3-10 mils
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C
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SECRET
can be measured between the range feathers of these specific
targets.
The majority of dots on 5-72 film are slanted. However,
this slanting is a function of the correlator range filter. Dots
above thehorizontal line produced by the junction of the correlator
range filters are vertical - those below this line are slanted.
Also, the area above the range line is defocused - striping as well
as video.
Specific examples of azimuth feathers caused by zero
holograms on 5-72 film are described by the following tabulation.
Target
Azimuth Dot
Width (mils)
Leading Feather
Length (in.)
Hologram Frequencies
Leading Trailing
1
15
0.135
95
220
5
20
0.435
220
220
6
18
0.175
95
280
7
5
No azimuth
feather
0
180
8
7
No azimuth
feather
0
200
It may be concluded from this month's data that improved
azimuth resolution is realized by operating with a high offset
frequency. However, this procedure produces weak background video
which must be overcome by increased RF power or, better still, in-
creased RF bandpass of the recorder.
INSTRUMENTATION
An analysis of data from this monthts flights indicates
there is good correlation between antenna position, VFO position,
and drift angle 75% of the time, indicative of good tracking.
Instrumentation modifications are being made concurrent
with APQ-93 modifications. They will provide performance and
envirmIT
ental data on the new transmitter, and will double the
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"quick look" capabilities of the magnetic tape instrumentation.
An additional 7 channel capability is being added to the magnetic
tape recorder. The following signals will
netic tape:
Audio Comments
Time code
DPT Frequency pulse
Vibration (3 channel
Drift Angle
VFO Position
DFT Signal Level (received)
Several new temperature channels are being added to
record temperatures in and around the new transmitter. These new
circuits will monitor the following:
form)
be monitored on mag-
Ground Speed
Pitch
Roll
Antenna Acceleration
Antenna Velocity
Antenna Position
Ambient
Ambient
Surface
Surface
Surface
Surface
air in missile bay area
air in pressure vessel
temperature of pressure vessel (inside)
temperature of CFA chassis
temperature of TWT collector
temperature of CFA tube
The CFA current pulse and CFA high voltage will also
be monitored.
Fabrication of these mods is 75% completed but calibration
has not been started.
SYSTEM
Flight testing was discontinued this month and system
modifications were started. Modifications incorporated during
this period include:
1. Production type printed circuit boards replace the
original Doppler Frequency Tracker breadboard unit.
2. The power supply has been modified electrically to
provide regulated 28 volts do as a primary power source for the
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1T:
recorder high voltage power supply.
3. The synchronizer has been modified to provide
range marks on the system primary film as an aid to film correlation.
4. Mounting for recorder number 6 has been modified to
reduce vibration effects. (Recorder number 6 includes modifications
incorporated in recorder 4 to reduce vibration).
5. The motion compensation mode selector panel has been
modified to simplify the radar operator's switching tasks during a
data run.
Figure 2 is a sketch of the physical arrangement of
system components on the rotary armament door, and Figure 3 is a
diagram of the modes of motion compensation available and the
switching requirements.
During the down time for radar modification, the aircraft
doppler-navigator system and auto-pilot are being overhauled. Also,
an aircraft 50 hour inspection is being performed, and minor air-
ft skin cracks are being repaired.
B ENVIRONMENTAL TEST
Vibration tests were performed on Recorder #6 with various
vibration isolators. In order to use the magnetic vibrator, the
cathode ray tube was replaced with a light source. Best results to
date were obtained with eight Lord JA 8350-7 isolators. The most
range degradation was 3 line widtli; of a half mil line over a
narrow vibration frequency band centered at 140 cps. This frequency
caused bad track degradation as well. Vibration in the pitch axis
caused the worst film degradation, vibration in the roll axis the
least.
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WESTINGHOUSE ELECTRIC CORPORATION
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Temperature-altitude tests were performed on the
modified receiver. Maximum frequency deviation as measured on
the LFE Stability Tester was 170 cps during 170 minutes of operation.
Maximum drift was 7,5 KC in ten minutes at the stabilized condition
of 1310F and 27,000 feet altitude. There was no significant
power change during this test.
C DESIGN EVALUATION
The following studies, described in the previous period,
were reproduced in this reporting period:
1. Effect of Relative Phase on the Range Resolution
of Two Point Targets (STM-126).
2. Feed-Forward (Logetronic) AGC Performance (STM-127).
Other studies underway, but not completed during this
period are:
1. Radar Range Equation and Signal oise Theo STM-129)
This study was partly described in the last report, and
is a summary of those factors which affect the system signal/noise
ratio. This includes the idealized range equation, plus all the
system processing losses due to Imperfect mechanization. These
effects involve not only the radar, but the recorder and correlator
as well.
The second phase of the study performed in this period,
is a theoretical study of the S/N required for a good map. This
was found to be a very complex subjectsdue largely to the effect
of the human observer. Three approaches were studied, and included
in thenemo, based on:
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(a) Data reported in the literature on the sensitivity of
the eye in detecting intensity changes.
(b) Detection probability, based on a false alarm
probability.
(c) An experiment on target detectability.
Orthese, the third appears to best represent the actual
case. It differs from the reported experiments in two important
ways: the two observed regions of different intensity were noise
modulated, and they were physically separated. Both effects were
found to drastically increase the required intensity change before
It became noticeable to the eye. For no noise modulation and
adjacent targets approximately -13 db S/N would suffice. With
noise modulation and adjacent targets, -7 db would be marginally
adequate. For separated regions with noise modulation, about -2
db is required. To get a really "good-looking" map, it appears
that the latter is required.
This study will be issued as a memo in the next period.
2. System Signal/Noise Performance Calculations (STM-132)
The calculations of the expected system S/N, based on the
theory of item 1, were completed in this period. A memo will be
issued in the next period describing the conclusions and results.
Curves of the S/N across the strip were calculated for both area
and point targets. Also curves were made for the extreme conditions
of offset frequency, corresponding to uncompensated antenna angular
motion. All calculations were done for four different altitudes,
corresponding to possible modes of operation.
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The S/N was found to vary drastically across the strip,
due largely to gain-ripple in the antenna pattern and the offset
frequency errors due to antenna motion. For example, the peak-
to-peak change due to the antenna is about 5 db, and the "average"
SAT is -6 db at the highest altitude considered. (This assumes
G3l db, Ppk=1 mw, and a TWT receiver.)
Two spatial filter methods were considered for the
correlator:
(a) A wide one consisting of 2 knife edges, wide
enough to always pass the signal, even with maximum offset variations.
(b) A narrow one, with a Taylor weighting transparent mask
at the Fourier plane. (The weighting is necessary to prevent excess-
ive side-lobes when the narrow filter is used). The narrow filter
was found to be greatly superior in minimizing the S/M variation
across the strip due to offset frequency changes, and was the
approach assumed in the S/M curves.
3 Fourier-plane Weighting Mask
As a direct result of the above study of the effect of
a weighting mask on system signal/noise, many advantages of such
a mask became apparent. First, the S/N is improved at all ranges,
because the filtering approaches the 'tmatohed-filter" optimum.
Second, the variations in S/N across the strip caused by offset
frequency changes are reduced because the effective offset variation
Is greatly reduced. Third, the correlation clutter of strong
point targets is greatly reduced, since the minimum offset frequency
is increased. Lastly, the system resolution should be improved,
as discussed under the next report.
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Quantitative figures for all the effects have not yet
been completed, and will be the subject of a continuing study.
It does appear clear that a Fourier-plane frequency weighting
mask is extremely important, and it is recommended that the
procurement of one be expedited.
4. System Resolution
The effect of correlating only a fraction of the signal
history on resolution was considered. It was found that most of
the degrading factors on resolution become less, ae the fraction
is made smaller. The only factor getting worse is the inherent
focussed spot size of the hologram. Combining all the contributing
factors gave a curve of resolution versus fraction - processed,
which had a minimum value at about 1/5 to 1/2 of the signal.
That is, the resolution should actually Improve, as less signal
is processed. For the resolution to equal that for the full
signal, only about 20% need be correlated.
These conclusions support the desirability for a spatial
filter mask discussed above, and perhaps also help explain a
similar effect noted experimentally.
Based on processing one-half the signal a rough revised
resolution budget was made, updating the one made last January.
Further work is required to include second-order effects.
D ANTENNA
All major design work is complete. The work remaining
is the final report, R.F. testing of No. 2 and No. 3 antennas
R.F. evaluation of a radome sample and completion of the six
spares modules. Some "clean up" work on the drawings is also
necessary.
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A fixture is being fabricated to enable the bonding of
a new laminate on an array stick without removing the array stick
from the module. If tests are successful, this fixture will pro-
vide a repair technique for the most probable failure.
PARTS STATUS
Antenna No. 2 -,Complete. MOre range testing is desirable
for this antenna.
Antenna No. 3 - Complete except for R.F. range testing.
This antenna wil,1 be available for environmental testing on 5
August 1963.
Spares Modules - All six modules bonded and assembled.
Three modules have been soldered, pressure tested and R.F. tested.
E RECORDER
VIBRATION
During July, attempts were made to reduce vibration
resonances within the recorder and noise generated by rotating
components.
Excitation was introduced by a speaker attached directly
to the bearing plate with varying frequency and amplitude of the
driving cone. Signals from accelerometers placed at suspect
locations were observed on an oscilloscope. This technique allowed
faster evaluation of a comtemplated design change, and photographs
were taken for comparison of results. Highest responses were found
at 218 and 285 cps on the plates and anything spanning the plates
such as the lens board or tie-bars. Several layers of cork rubber
composition isolating the lens mounting and M3 mirrors from the lens
board proved ineffective below 300 cps.
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A layer of cork rubber between the motors and the plates
and the use of nylon screws reduced noise by approximately 50%. The
residual noise was reflected through the plates onto the lens
board and the lens and the M3 mirror. After isolating the drive
system, an accelerometer placed on the side plate indicating motion
along the optical path showed 10 micro-inch motion at the predominant
frequency of 485 cps. The predominant frequency was determined by
feeding the accelerometer signal through a band pass filter to a
spectrum analyzer. The amount of noise or vibration is still
excessive and effort is continuing to reduce it.
ELECTRICAL
Packaging of the modified focus modulation circuit has
been started.
The variable speed inverter for film drive does not
bottom at 350 cps when the output of the navigational potentiometer
moves below the control voltage for this frequency. An additional
circuit, now in fabrication, provides a "stop" for the low frequency
excursion at approximately 350 cps.
The neutral density wedge method of measuring frequency
is being used in the study of the vibration and noise problems with
some success. More intensive work on this will be conducted in
the next month.
A circuit to provide a xhster sweep has been breadboarded
to observe hum, jitter, and other disturbances when used in con-
junction with a dot generator and the viewing microscope. This
circuit drives one of the 500 ohm centering coils on the yoke with
a back-to-back sawtooth to produce a raster. Intensity modulating
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the CRT grid with a dot generator produces a time pattern
which can be used for adjusting focus and viewing disturbing
hum fields.
KAISER HIGH VOLTAGE SUPPLIES
The first Kaiser high voltage supply has been
installed in Recorder #6 at Westinghouse. Regulation of output
voltage with temperature variations is satisfactory, but line
regulation does not meet specification. The power supply will
eventually be returned for repair.
The second and third supplies have been received at
Itek and are undergoing Phase II of the Acceptance Tests. The
second supply, on which the Phase II tests are 90% complete, can hold
the ratio of ultor to focus voltage better than + 0.1% for a period
of 1 1/2 hours after a 30 minute warm-up. During this interval in
a 24?C ambient, the transistor heat sink temperature increased from
29? to 60?C. Line and load regulation is better than + 0.02% as the
baseplate temperature changed from 37? to 33?C. Ripple on the ultor
and focus voltages is less than + 0.1% and locked to the input
synchronizing square wave.
A maximum external magnetic field of 7.5 x i0 gauss
is radiated 3 inches from the top of the supply next to the low
voltage plug. A step function from no load to full load on the
focus supply produced a 2 volt overshoot.
Further dynamic testing in the recorder is required to
complete the Acceptance Test. In addition, vibration tests and a
temperature check will be made, when sufficient operational power
supplies are available.
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F SWITCH TUBES
One of the two new WX-3846 tail bite tubes, was returned
for retest because of the inability to control the firing point with
respect to the rf pulse. Internal pressure apparently dropped due
to a leaky valve. The tube was refilled to 8 PSIG pressure, tested
and returned to the system, where it is now operating satisfactorily.
The second WX-3846 has been tested and packaged.
Four new WX-4554 dump tubes have been fabricated to
date. The flattening of the electrodes to reduce erosion proved to
be ineffective. One tube had rhodium tips on the domes WiiiC the
other tubes had tungsten tips. The rhodium tips did not form burrs
in the erosion process like the tungsten tips, but eroded evenly over
the surface. The rhodium tips autotriggered at 4o KW peak whereas the
tungsten tips showed no autotriggering up to 60 KW peak.
The above tubes were tested on the traveling wave
resonator ring. The data has been compiled and is now being analyzed.
The breakdown time of the above tubes was measured to be less than
or equal to 5 nanoseconds to the 3 db point. Isolation was between
10 and 13 db.
o SYNCHRONIZER
SYNCHRONIZER BOX
Change orders have been written to change both wiring
diagram and schematic diagram to conform to latest configuration.
A Range Mark Generator has been readied for the flight test system.
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FREQUENCY GENERATOR
90% of circuitry has been designed and breadboarded.
These breadboarded units will be mounted in the Environmental
frequency generator chassis and checked out for use in the F101
flight test program. The present flight test unit and the
Evaluation unit will then be reworked by Model Shop for shipment
with systems.
An entirely new center chassis has been laid out to
replace the original. Drafting has started detailing. Printed
circuit boards are about 30% completed by drafting.
H TRANSMITTER
FLYING BREADBOARD
Additional cooling was added to the CFA chassis.
Specification checks and measurements of power output, phase
stability and jitter were performed.
The charging choke failed after 10 minutes. It was
round to have a manufacturing defect. The second delivered unit
has operated satisfactory for about 20 hours.
Three 30 KV power transformers have failed by arcing
across the winding. A new epoxy molded design has operated but
the results are still inconclusive.
PROTOTYPES
CFA chassis position was changed to increase distance
between ground plane and thyratron tube.
Electrical changes found necessary from the breadboard
were incorporated into the units. Wiring was completed as far as
mechanical conditions would allow. Unit was circuit checked.
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I FIELD TEST EQUIPMENT
The modifications of Stability Analyzer are completed
and Preliminary checkout indicates that the problems have been
satisfactorily solved. The residual instabilities of the Test
Equipment have been reduced across the entire frequency spectrum
of interest (0 - 200 cps) and the linearity is now within 1% over
a frequency range of 1800 cps. See Figure 4.
Composite tests are now in progress. However, the
phase lock problem of the VFO and intermediate Test Set Frequencies
has not yet been eliminated. Changing of the Grounding System has
reduced the problem somewhat but further investigations are required.
It is felt that the problem is still severe enough to cause some
nonlinearities in the Doppler sweeps.
No tests have been performed with the system.
All of the Standard Test Equipment has now been
received. The Jitter Tester and Sub-sonic Analyzer are still in
calibration.
J MOTION COMPENSATION
The final mechanization for the motion compensation as
completed by Honeywell has a resonant response. The resonant
frequency and damping are such as to give the required integration
accuracy but result in a long settling time. This problem is
solved by decreasing the settling time by about 5 at turn on, and
then switching to high gain, high accuracy, for mapping. The theory
of this design has been checked and considered good.
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_
,
......
.... ?
q-,- ? ... ? ?
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FIGURE 4
,?1 I
't4C0 :i1.1.010t X Ot
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3.74i
K RADONIS
A sample of the new silicone glass radome was received
In a panel large enough to test one module of the antenna. The
loss at most was .5 db, occurring at a depression angle corresponding
to maximum range. From this it was determined that the thickness
could be increased from .300" to .306" giving a predicted loss of
.2 db maximum. From electrical considerations the tolerance
should be + .002" but this may be tighter than can be conveniently
maintained.
This radome performance is considered good. It is much
better than originally assumed and rather negligible compared with
the loss due to antenna blocking by metal support structure for the
radome itself.
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