CONTRACT AF 33(600)-40280; SUBMISSION OF PROGRESS REPORT FOR OCTOBER 1963; WESTINGHOUSE REF. DYD-45196

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP67B00657R000200210030-0
• Release Decision: RIPPUB
• Original Classification: K
• Document Page Count: 23
• Document Creation Date: December 22, 2016
• Document Release Date: December 9, 2010
• Sequence Number: 30
• Publication Date: January 9, 1964
• Content Type: LETTER

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,
Westinghouse Electric Corporation
AdNassed Plans Or Programa Division (ASZ05)
Deputy for aysteme tlAnagenent
Headquarters
Aeronautical 4yetem43 Division
Wrigizto.Patterson Air Force Base, Ohio
2\ht Arm' DJ% \Itpmt
\
January 9, 1964
Al
ClifiaCT: Contract. 314$ 33000-40250;
antraission of Progress Report tor
October 1963; Westinghouse Ref.
V1D.45196
gig 4. OP- QM 00 g. 41. trer *10 g. gag g.
Bnclosure (1): Three (3) copies of Progress Rejport for the period, of
October 1, 1963 through October 31, 19(3.
n:
Th accordance with the subject contract, we are enclosing
the rnoth1r Progress Report for October., 1963.
Very truly yours,
WEERINORWES RUICTR/C CCMPORATION
CC:
WE; N ) , I-- i :ACHED), THEI
';1,:EAl'151PNEFH-HECE.EE--,ER'4E,1'?GEOIELREGAE1-
(:111.i. I) IN ((r -.L V;;:i; i :111 : 5:: Al REGULATION 205-1
/ OR NAVY RLGHLA HON f,1,11REE 75 (',) (11).
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STAT
STAT
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Progrees Report
SECUR:TY HO. 86 ? -2 -
.....
Copy.
Period of October 1 to October 31, 1963
Contract No. AF33(600)40280
This document conta!ns information affecting the
Nahonal of the LL-Ii'led Elees within the
meni, C., Sec-
tion . . : revelation
ot La to an unauthorized
person is prohted by law.
DONVNGRADYD AT 12 YEAR INTER',
V ALS; NJI.'
DECLASSIFIEJ. D31) D1R 5200.10
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TABLE OF CONTENTS
PROGRAMS
A F-101 FLIGHT TEST 1
B AIR FORCE FLIGHT TEST 3
C ENVIRONMENTAL TEST
? ? ? ? 6
D DESIGN EVALUATION . . . ? ? *********** 7
EQUIPMENT
E RECORDER ? 9
F CATHODE RAY TUBE POWER SUPPLY 16
G ANTENNA 16
H TRANSMITTER 18
I SYNCHRONIZER 18
? MOTION COMPENSATION 19
K FIELD TEST EQUIPMENT 20
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SECRET
A F-101 FLIGHT TEST
FILM EVALUATION
Highways railroads, street patterns in Hagerstown, Md.
and Harrisburg, Pa., airport runways and rapids in the Potomac
River were resolved on correlated film from flights of this
month. Also the Charles Town race track and individual buildings
In military depots near Harrisburg and state penal farm near
Hagerstown are resolved.
Except for very strong targets, dots in the near range are
vertical and focused well over the entire sector. Well defined
2-4 mil (8.5 to 17 foot) azimuth separation of dots can be seen.
Density is lower in the far range with reduced contrast, giving
the impression of weak video. Noise as well as video dots change
from an oblique pattern at the beginning and end of the far range
film to be vertical at the center. On far range, poor focus causes
rows of individual dots to blend into long azimuth targets.
Range marks are approximately 2.5 mils in range on primary
film and 9 mils on correlated film. A comparison of holograms and
their correlated dots determined the primary to correlated dot
magnification of 1:3.5. Since the range scale factor is 1:2, this
Indicates range resolution is being degraded by approximately 75%
in the correlation process.
Offset frequency variations were caused by poor DFT operation.
On the primary film, strong low frequency video is recorded for
offset frequencies below 250 cps and weak high frequency video for
offset above 250 cps.
During a portion of flight S-81, the aircraft was in a right
drift attitude and the antenna positioned up, causing doppler
-1- Cr? riliQ ET
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frequency to increase with range. The decrease in video level at
long ranges because of recorder band-pass was apparent on the Mil.
Holograms from flight 5-78 were reversed, indicating reversal
of the VFO relative to the radar reference frequency. Modification
to the DFT corrected the VFO and the holograms on the last three
flight films showed correct polarity.
SYSTEM
Transmitter leakage into the receiver was reduced 25 db by
inserting a waveguide diode switch in the RF input line of the
CFA transmitter and by another 70 db by inserting a solid state
coaxial switch in the 120 me fixed frequency line to the buffer
amplifier.
The doppler frequency tracker was tried on the five flights
male this month. Reasons for the unsatisfactory operation of all
flights are being investigated.
Tracking performance of the DFT-antenna loop was Improved
on the last two flights, locking up for 30 and 90 per cent of the
runs. Failure to lock-up or track continuously was caused by low
loop gain and inability of DFT to track at frequencies higher than
300 cps. This latter problem is caused by saturation of the four
stage amplifier section of the DFT by a large return signal, thus
reducing the frequency of the DFT output. Ten db receiver attenuator
usually increased the DFT output about 35 cps but at times up to
100 cps.
Only one in-flight failure was encountered, this being failure
of the nylon gears on the loop motors in the recorder
film transport. The nylon gears were replaced with steel gears.
-2-
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INSTRUMENTATION
No changes have been made during the past reporting period.
The failure of the magnetic tape recorder to run on flight #19
has been attributed to either brake tension on the recorder or
bad tape and reels (Reeves Soundcraft). The tension was in-
creased on the recorder, although it was not out of specification,
and the "Soundcraft" reels will not be used anymore. This should
eliminate the problem.
Figure 1 is a strip chart of some of the parameters recorded
on flight 030. This shows the DFT tracking for about 1/3 of the
run and having an oscillation of about 0.6 degrees peak to peak.
These oscillations change the offset and cause noticeable striping
on the final film. The effect of adding the acceleromater net-
work caused the pod to unlock since it drove the VFO down in
frequency about 1 KC.
B AIR FORCE FLIGHT TEST
The basic pulse interval for the instrumentation programmer
was increased from, 0.6 to 1.0 seconds to be compatible with the
scan rate of the customer's digital recorder. This change re-
quired rescheduling the test modes of the programmer.
Space for the instrumentation was allocated off the frame,
but located just forward of the recorder. Location of the CEO
recorder was changed to make room for the tracker camera added
in the equipment bay. The government furnished CEO 5-114P3 re-
corder has been received. Electrical design of the instrumentation
and programmer is practically complete, with fabrication of half
the packages underway. Completion is scheduled for January 2, 1964.
3-
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Twenty-three signals are to be recorded on the CEC analog
recorder. These are:
VFO Input
Antenna Position Feedback
Input Current to Actuator
Accelerometer Output
DFT Output (Ahead of smoothing)
PESAP Input
Recorder Automatic Brightness Control
Film Drive Control
Film Drive Output Rate
Transmitted Power Output (temperature compensated
thermistor bridge)
Power Supply Outputs - 7 supplies
Temperatures - 6 locations, including antenna area.
Present programmer schedule calls for normal system operation
55 per cent of a repeating 2000 second cycle. Initial plans are
for normal operation to be modified for a 100 second period in
each of the following modes:
Open Accelerometer
Zero Yaw and Pitch Input
Switched Offset Frequency
Open DFT
No IF Limiting
Increased Receiver Attenuation
Switched Offset Frequency and Open DFT
Switched Offset Frequency and Increased Receiver Attenuation
Swept VFO (Checks recorder azimuth bandpass)
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Recorder Range Band pass (13 me, 26 mc and 39 me
frequencies into video amplifier)
Instrumentation Calibration
Terrain mapping will be accomplished in all modes except
the Swept VFO and Recorder Range Bandpass modes.
V RONMENTAL TEST
Three-Axis vibration tests were performed on the receiver
traveling wave tube, removed from its chassis, to determine existing
resonancalin the tube package itself. Significant resonances were
observed on the input waveguide stub. This vibration may be trans-
ferred to the tube case when the tube is mounted to its chassis.
In preparation for the antenna high temperature test, the oven
was tested to insure proper temperature control. The antenna
electrical test consisted of comparing the azimuth and elevation
antenna patterns and main lobe gain at design and room temperatures.
Patterns showed that the antenna tuned frequency decreased about
50 me. Main lobe gain decreased about 1 db at maximum temperature
relative to room temperature, with proportionately lower losses at
lower temperature.
Calculations explain most of the increased antenna losses at
high temperature, including:
Power divider I2R loss
0.20 db
Stick I2R loss
0.02
Manifold I2R loss
0.02
Phase changes in manifold
0.34
Differential changes in power divider arms
009
db
In addition, a loss is caused by the non uniform temperature
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variations on the antenna structure, particularly front-to-back.
A pressure check following the antenna temperature test
indicated leakage at the waveguide joints. No other mechanical
difficulties were noted during the test. Further pressure-temperature
tests will be performed.
Three axis vibration tests are currently being performed on
the modified lens optics recorder 46, to determine the effectiveness
of the Itek modification. These comparative tests are being per-
formed with several types of vibration isolators.
During this reporting period vibration fixtures for the SAP
and SAP electronics package were designed and fabricated. Reduction
of antenna vibration data from the previous period was completed.
D DESIGN EVALUATION
CORRELATOR SPATIAL FILTERING
The rough draft of a memo (STM-l46) on the effects of correlator
spatial frequency filtering was prepared. This included completing
the computer runs of correlator output patterns with the recorder
filtering present. Plots were made of the various output patterns,
both with and without the recorder, and with and without a tapered
gaussian filter. The recorder non-symmetry did not significantly
degrade the correlation pattern.
Also included in the study was the effect of uncompensated
acceleration on system resolution, as a function of the fraction
of signal processed. As may be anticipated, the resolution de-
gradation was found to decrease as the fraction of signal processed
is reduced. Quantitative results were obtained, and included in
the report.
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FLIGHT FILM ANALYSIS
In an effort to determine all the information possible from
flight films, film 8-78 was studied at length for possible ales
as to system malfunctions. A number of conclusions were made:
(1) The range resolution is much poorer on the correlated
film than on the data film. This would appear to be due to
correlator image motion.
(2) The range marks are tilted on the output film in the
range direction, which would check with the image motion theory.
They are straight on the data film.
(3) The recorder resolution degrades about 2/1 at the edges.
(4) There is no observable pulse pedestal with the new trans-
mitter. This was not true with the ring.
(5) Varying the correlator slit width or filter width affects
the map appearance, but does not seem to affect resolution
appreciably.
(6) Azimuth resolution on weak targets approaches the design
goal. On stronger targets, as expected, it degrades, but the de-
gradation is more than expected (about 3/1 instead of 2/1).
(7) Judging by the width of the range marks and of clutter
due to too low an offset, the range resolution would probably be
about that anticipated if the image motion problem were eliminated.
CORRELATOR LIGHT LEVEL
A study was initiated to verify the exposure available on the
output film with the present light source. The reason for interest
Is to extrapolate the results for a laser source. To date, results
have not been in agreement with the observed exposures, and further
work is indicated.
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E RECORDER
RECORDER #6 TESTS
Tests made on recorder #6 showed that an 18 cycle per second
(approximately 15 cycles per inch) modulation of trace position
was strongly evident. Considerable effort failed to determine the
cause of this flutter before the recorder was shipped. Examination
of the capstan rotation failed to detect any erratic motion. In-
vestigating for modulation of the CRT spot position by magnetic
fields revealed the presence of 60 and 400 cycle components, but
the limited field of the viewing microscope prevented Observing 18
cycle modulation. Use of the stroboscopic effect of pulsed 18 cps
on the grid was not conclusive in isolating the cause of the 18 cps
flutter.
Several other difficulties were discovered. The output stage
of the focus modulation circuit was unable to deliver the required
150 volts of signal without distortion, and requires further work
to obtain the required level. Another difficulty was insufficient
centering current to place the trace at the correct position. The
recorder cannot be adjusted to 12.12 microseconds per inch writing
speed. Since achievement of this writing rate requires the purchase
of a new deflection yoke, the present 14 microsecond per inch
capability will remain.
The Automatic Brightness Control unit operated satisfactorily.
Figure 2 is a plot of the change of light output from the CRT
caused by an independent voltage source varying the bias with the
ABC off and ABC on. The data shows a 100:1 change in brightness
with no feedback, with a change of only 1.71:1 with ABC on.
9
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4-
ti
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At the operating point of -39 volts bias, a 2:1 change in bright-
ness obtained with ABC off is held to 1.1:1 change in. brightness
with ABC an.
LOOP-FORMING MOTOR CIRCUITRY
A check on the feasibility of 1.6 inch per second film speed
resulted in an investigation of the loop motor circuitry. To
change from 1.25 to 2.00 inch per second speed presently requires
changing the two loop control motors, with limited range of control
with rheostats. Replacing the rheostats with zener diodes allows
greatly increased range of control.
Some preliminary tests were conducted on the use of tran-
sistorized speed control circuit for the loop motor controlled
from the dc component of the variable speed inverter so as to
permit the motors to roughly track the film speed. The micro-
switches would still be used to provide correction to the loops
as required, but with this method the transients in film motion
produced by the microswitch operation will be reduced to a
minimum.
FIBER OPTIC TUBE STUDIES
The experimental fiber optic tube WX5321-P11 #1288 has been
installed in a breadboard setup. The first phase of the investi-
gation was to determine the sensitometry requirements of films for
use with this tube. SO-243 (Special High Definition Aerial) film
was found to be unsuitable since its low sensitivity severely
limited the dynamic range of the tube. Tests with 8430 (Fine Grain
Aerial Duplicating) showed this film to match the tube character-
istics to a greater degree, with threshold exposures on film very
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close to visual cutoff. The frequency transfer function of this
film is also superior to Plus-X Aerial (4401) which is used in
the lens recorders.
A reproduction of a swept frequency test on 8430 is shown
in Figure 3. The noise and striations due to the fibers compare
favorably with that obtained from the lens recorder from con-
ventional cathode-ray tubes.
The film transport of the fiber-optics recorder was modified
to reduce the effects of rotating magnetic components on the CRT
trace and uneven belt tension to the capstan roller resulting in
film flutter. The modifications included use of an aluminum
capstan and drag roller instead of 440c stainless steel (at a
sacrifice in concentricity) and the use of a teflon belt-tension
post instead of rollers. The results of these changes were
Indeterminate at this time.
RECORDER #7
Recorder 107 has been completely assembled except for three
items, two of which are limiting the testing. These are:lenses
CRT yoke (returned to vendor for inductance change) and power
supply (Fluke Power Supply can be used instead).
Several Improvements have been installed on #7 and on
this month. These are:
1. A microscope scale and magnifier for trace measurement
and microscope position indicators.
2. A magnetic shield cover for the film motion transducer.
3. A spool shaft bearing guide. This will simplify installing
the cassettes and will prevent incorrect alignment.
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4. A cassette cover lock. This device will prevent light
from entering the cassette through an ill-fitting removable cover.
It will also serve to orient the cover properly so that inter-
ference between the cassettes and adjacent components will be pre-
vented.
The two Wollensak Special Input Raptar lenses were received
and underwent a resolution test on the optical bench. The visual
axial resolution at f/2.8 or smaller aperture was very good well
in excess of 140 1/Mal and axial photographic resolution with
Pan-Atomic X sheet film was slightly greater than 64 1/Mm However
It was discovered in these tests that both lenses had an excessive
amount of field curvature. Targets 1 7/8 inches from the axis
were imaged on a surface which was about0.020" inside the plane of
best axial focus. The off-axis image, where it is in focus, is
quite free from astigmatism and the resolution is very nearly as
good as the central Image. A field flattener should work very
well and one is being. designed.
During the testing it was also observed that there was con-
siderable axial chromatic aberration. This, combined with the
field curvatures indicated that perhaps one or more of the lens
elements was fabricated from glass of the wrong index. One lens
was shipped back to Wollensak for further testing.
HIGH VOLTAGE POWER SUPPLIES
Three Kaiser high voltage power supplies have failed after
20-30 hours of bench operation. Many rectifier stacks from the
voltage tripler and quadrupler sections have had excessive reverse
current.
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One cause of the damage to the series diodes in the stack
was a 4 kilocycle reverseswitching current of 5 milliamperes.
By inserting a 5 ohm 10 watt resistor in series with the primary
of the high voltage transformer, the maximum reverse current
transient was reduced to 0.1 milliamperes. Additional turns had
to be added to the secondary of the high voltage transformer to
provide specified output voltages. The reduction in reverse
current is accomplished by a large reduction of the ringing on the
secondary of the high voltage transformer.
Another source of possible trouble is the turn-on transient
generated by shorting the 100 ohm series resistor in the high
voltage primary. Turn on generates a fast 6 milliamperes pulse
(microseconds duration) of reverse current through the diodes.
The transient can be reduced to 2 milliamperes by inserting a third
series resistance of 20 ohms in the primary of the high voltage
transformer which is recommended to be shorted out 10 seconds
shorting out the 100 ohms. With the new modifications, the power
supply is less efficient but the input current does not exceed 3.0
amperes under worst conditions.
In addition, the diodes in the high voltage rectifier stacks
are now Selected by the manufacturer for their uniformity of
reverse switching characteristics as well as equal forward voltage
drop.
Power supply #9760 has been operated for a total of 42 hours
with four new rectifier stacks manufactured to these tighter toler-
ances. The new rectifier stacks showed no degradation when re-
moved from the supply and tested after this period. Itek plans to
run the power supply an additional 50 hours during the acceptance
test pelod. -15-
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The new high voltage precision divider resistors with a
varnish binder instead of the former glass seal were also tested
during the 42 hour interval. Although all the resistors displayed
a slight change in value caused by temperature and voltage aging,
three resistors showed an increase in resistance rather than the
normal decrease.
CATHODE RAY TUBE POWER SUPPLY
The rash of failures on the high voltage power supplies at
Itek has caused a speed up in work on the new design at Westing-
house. All electrical parts have been received and one unit
should be completed by November 4.
Several problems have been encountered with the subassemblies
and corrected. Excessive stray capacitance in the 15 KV multiplier
circuit caused a complete redesign. The 4 KV circuit design re-
quired a change in the transformer design.
G ANTENNA
All antenna design work is complete. The six spares modules
have been electroformed and are complete except for the final RP
tests and clean-up of the barriers and the overcoating with silicon
rubber.
An antenna pod-radome test was conducted using antenna 3. No
pattern deterioration was noted as caused by the radome or the pod
structure. Losses of gain were .25 db one way for the radome alone
and an additional .45 db for the blocking by the radome support
structure.
Delamination of the varnish on the fabric covering the antenna
sticks is a potential cause of trouble. A cost study is underway
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to determine the costs of heat-pressure treatment of the ML fabric
and the tensile tests needed to determine the improvement in the
bond between adjacent layers of varnish.
Drafting on the interconnecting waveguide will be completed
by 12 November, at which time the drawings will be released for
fabrication. Availability of satisfactory waveguide material is
the most pressing problem of this task.
Waveguide breakdown was calculated for both CW and single
pulse transmission for two conditions:
(1) 689:rand 6.6 pale., corresponding to test conditions.
(2) 550?F and 20 psia (pressure established by lower tolerance
on air bottle pressure regulators).
Repetitive pulse breakdown is an indeterminate function of repetition
rate and pressure but limited by CW and single pulse breakdown.
A breakdown of 445 KW measured under the first ambient conditions
and with normal PRF is a reasonable check on the calculations.
Temperature pressure
68?F
oF
6.6 psia
20 psia
Breakdown Power (KW)
Calculated
CW Single Pu
362 1218 445 (measured)
687 3930 005(extrapoal
Repetitive
Pulse
Assuming that repetitive pulse breakdown occurs at the same
fraction of the difference between CW and single pulse breakdown, it
is predicted that 1 Megawatt is the actual breakdown at the antenna
Input. Taking into account the estimated 1.5 db circulator and
Interconnecting waveguide loss, antenna breakdown would occur at
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1.4 megawatts out of the transmitter.
Both antennas 2 and 3 were power tested, with breakdown
occurring at approximately the same level. Although not providing
much safety factor, the antenna pressure does appear to be adequate.
Both deliverable antennas 2 and 3 were boresighted. The angle
between the peak of the radiated beam and the edge of the honeycomb
is 900 for both antennas. Mounting dimensions for the two antennas
are accurate enough that Interchanging antennas would cause an
azimuth error no greater than 1/8 degree. A boresighting procedure
has been written. One critical area of the antenna installation
is the inclination of the longitudinal axis of the antenna. This
angle shall be adjustable from the predicted flight attitude of
the initial flights to that of the final flight attitude.
H TRANSMITTER
Unit testing on the first developmental model was completed
after correction. of 400 cps jitter on the CFA modulator and Inter-
action between the TWT and CFA pulser. A blower was added to cool
hot spots on the charging choke, charging diode, and the series
transient resistor. After installation of this transmitter in the
F-101, an additional pick-up problem in the TWT servo was solved.
I SYNCHRONIZER
The first deliverable Frequency Generator has been fabricated
and is now undergoing test. A level set pot has been added to limit the
Variable Frequency Output to 3 VRM3 at 10%. Tests with the Flight
Test Equipment are planned next month.
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(MON
OMPENSATION
When the first antenna yaw control actuator became available,
the gain and frequency response were not as predicted by the
supplier. As a result it was necessary to change the servo
amplifiers and feedback in the Honeywell supplied equipment.
This has been accomplished in unit #2 which has been acceptance
tested and is now in Baltimore. Unit #3 is ready for acceptance
test at Honeywell and unit #1 has been returned to Honeywell for
these same servo modifications.
Two parameters of the actuator received from the customer
we less than those given in the original design specification.
The position feedback LVDT gain measures 3.8 volts per inch instead
of 5.0. Gain of the actuator second stage is 40 inches/Sec per
Inch rather than 60. After further testing with the actuator and
electronics, the necessary steps to compensate for these differences
will be determined.
At Aerospace the ant nna has been operated in a closed loop
with the yaw control electronics. It is at least controllable and
stable, but measurements have not yet been made on frequency response
or control accuracy.
Continuing flight test is emphasizing the relative importance
of angular correction of antenna pointing and the cross track
velocity compensation. The angle compensation is a matter of prime
Importance in obtaining a useful picture while the velocity com-
pensation is but a small correction which improves resolution, only
as a second order effect. Fortunately the deliverable system is
arranged to take advantage of this situation.
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K FIELD TEST UIPMENT
Modification of the Field Test Equipment to include circuitry
for three nominal film speeds is completed. This modification
includes changes in counter operation to produce the correct
number of pulses to operate the Nay-Tie-In step motors and
selection of ramp slopes to keep a constant focal length. All
units are functioning properly and the System Test Set is complete
and available for providing test functions.
Preliminary test on the system Frequency Generator indicated
problems of intermodulation. This intermodulation was greatly
reduced and a new series of tests is planned.
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