CONTRACT AF33(600)40280 WESTINGHOUSE REFERENCE: DYD-45196

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP67B00657R000200210016-6
• Release Decision: RIPPUB
• Original Classification: K
• Document Page Count: 32
• Document Creation Date: December 22, 2016
• Document Release Date: December 9, 2010
• Sequence Number: 16
• Publication Date: March 23, 1965
• Content Type: MEMO

Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
Westinghouse Electric Corporation
Air Arm Division Friendship International Airport
Box 746, Baltimore 3, Md.
Telephone: 761-iooo
23 h1
-Of
ntft0b, We
STAT
STAT
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 &' osm-w
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
V1 L-W.F,L- of 110w
"Nor %OOF gr
Copy 2 of 6.
PROGRESS REPORT
FOR
PERIOD OF SEPTEMBER 1, 1964 TO JANUARY 31, 1965
CONTRACT NUMBER AF33 (600 )40280
BY
WESTINGHOUSE ELECTRIC CORPORATION
AEROSPACE DIVISION
BOX 746, BALTIMORE 3, MARYLAND 21203
S'' .CIA.L HANDLING
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
TABLE OF CONTENTS
PROGRAM
A F-1O1 FLIGHT TEST . . . .
Modification & Ground Test
In-Flight Tests
.
Instrumentation . . .
PHASE
II
FLIGHT
TEST . . . . . . . .
B
~y
~}~{
DYNAMIC ~~
C I NAMIC CORRELATO
ONMENTAL TEST .
9
10
EQUIPMENT
MODIFICATION . . .
Low Noise RV Pre-Amplifier
14
ange Boost . .
15
Increased Power output .
16
SYSTEM .
16
Receiver Phase Shift
16
Recorder . .
19
Reliability . .
19
H GROUND SUPPORT EQUIP?
I SPARES .
APPENDIX
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
A F-i0l FLIGHT TEST
The 300 hour periodic inspection of the F-101 aircraft was
completed with the functional test flight on 9 September 1964.
The first radar flight followed on 14 September. A summary of
the flight program is given in Table
Radar flights flown in this period from September 1964
through January 1965 are summarized in Appendix A. A defective
aircraft cooling system prevented flights between IT December and
28 December.
Modifications and Ground Tests
Receiver
Three receiver modifications have been performed and tested.
First,, the Tunnel Diode Pre-amplifier was replaced with a parametric
amplifier built by Micro-Mega, repeating a test started on fligh
114 prior to the aircraft inspection. This amplifier has gain of
16 db and produced a system noise figure of 5,6 db, an improvement
of 0.9 db over the Tunnel Diode Amplifier. After flight testing on 127,
the TDA was re-installed.
Prior to flight 130, a second lim
amplifier was in-
stalled to allow cockpit variations in the signal level to the video
amplifier without changing the limited signal to the DST. This permits
changing the signal return power at which limiting occurs. This
second limiting TF has remained a part of the F-10l installation.
The third receiver modification consisted of replacing the
Tunnel Diode pre-amplifier with the final configuration of the
parametric amplifier, one designed and built by Westinghouse.
Installing this component required constructing a 400 volt power supply,
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
TABL
P-101 PROGRAM SUMMARY
September 1964 through January 1965
Flights Scheduled
Flights Accomplished
Aircraft
Functional Feet Flight
Pilot's Proficiency
Radar
Productive Flights
Productive Flights Prior to a Failure
Film drive and diode switch failure
Transmitter overload
Transmitter failure
Transmitter servo failure
No Results
Film drive failure
Military Operations over target area 1
Cancelled
Weather
Motion Compensation System
Transmitter
Transmitter Servo
Aircraft Compass Problems
Aircraft Oxygen Supply Inadequate
Aircraft Turbine Failure
Inspection Scheduling
24
19
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
,J7 `v.. .r -- --
fabricating and mounting bracketry, and modifying wave-guide runs.
This par-amp produced a system noise figure of 5.1 db, and
is now installed and ready for flight test. Because of the improved
noise figure and apparent stability of this unit, units of this type
planned for the two deliverable systems as well as the F-1O1.
Receiver tests performed on the P-101. system were reported
STAB 164.
Transmitter
Flights
~hrough 123 used a transmitter having a narrow
pulse forming network in the CPA discharge circuit. Pulse width
was 28 nanoseconds and average power 22.5 watts. The remainder
of the flights used the original PFN, which produced 37 nanosecond
pulse width at 29.5 watts. The narrow transmitted pulse generated
by reducing T WT NP drive pulse width (as described in section Z
this report) has not been flight tested.
Prior to flight 132, the thyratron was replaced in the CPA
modulator and average power increased to 58 watts.
TWT and CFA pulse coincidence was lost on flights 120 and
121, caused by a defective tunnel diode in the transmitter servo.
Checking to determine if temperature was a problem, a thermistor
measured the highest temperature on the servo chassis in-flight to
be 39?C, which is not excessive.
Doppler Frequency Tracker
Six flights, were made off -shore from Charleston, South Caroline
o savannah, Georgia. For the last four of these flights, the DFT
gate was moved from its normal 180 use o range to 235 uses to reduce
the lose of DFT operation when the gate is over water.
_5_
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
Motion Compensation
Tests on the motion compensation system were started on
ight 117. In-flight the integrator output would not return to
zero. This condition was corrected by changing tube and wire
shield grounds and by adding decoupling to the power supplies.
In addition, a transient occurs when the accelerometer is
connected in-flight to the integrator network,, pausing the network
to accumulate an excessive charge. Investigations into this network
charging are still underway.
During the course of these tests, an integrator of deliverable
configuration (built by Minneapolis-Honeywell) was installed in
the F-1O1. After correction of initial drift problems, satisfactory
operation was obtained. System gain was checked by causing the
aircraft to pitch sinusoidally approximately 4.3g and evaluating
instrumentation data. Results were obtained on the film of flight
131 with the forced aircraft pitching both with and without motion
compensation.
An incorrect accelerometer scale factor (volts per g) caused
the gain at the integrator input to be set too high on flight 136.
Recorder
The film speed inverter and CRT filament power supply have
been installed external to the recorder to minimize 400 cps pick-up.
Following flight 126, a general tightening of the recorder was
performed, which improved the reliability of film transport and
vibration striping on the film. This procedure is required to be
repeated periodically.
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
Several different film emulsions of the Eastman 5401
have been used during this 30 flight period. Prior to the use of
a new emulsion, sensitometric measurements and CRT bias-density
curves are plotted to determine optimum CRS' operating voltages.
This procedure along with a bias only film sample on each pre-
flight test has enabled determination of C: performance for each
flight. A defective CRT bias pot was located through these tee
Recorder 007 was modified to the final altitude ( ke sweep rate)
configuration and tested on flights 142, 143, and 144 to simulate
final altitude results. Recorder operation was satisfactory.
A study of CRT bias tests resulted in adjusting the CRT closer
to out-off for all flights after 133. This theoretically
(1) operates the CRT in a more linear region of the video-
transmission curve, causing fewer images
(2) gives greater contrast for small targets
gives brighter image on the correlation,, or allows
operation of the correlator at a faster speed.
Results on the correlated film are signifioantlyr improved with the
lower bias voltage. Nominal density on the primary film
averaging about 0 3.
poor correlation of flights 128 and 129 flown at the extreme
lower limit of ground speed triggered ground tests of ground speed-
film speed tracking. Tracking was found to be 3 per can
at the lower limit of 750 knots ground speed. After ad justment, less
than ,3 per cent error in film speed was found over the full range
780 to 900 knots ground speed.
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
The field flattener in recorder 007 for the far range sector
eked. Since useful video occurs only on far range in 4 ko
ep rate operation from 45,000 feet altitude, the recorder
as modified to interchange the near and far range traces
on the CRT and satisfactory operation was obtained.
Dual Altitude Operation
Flight 132, planned for 45,000 feet altitude over Norfolk, was
aborted due to military operations taking place in the flight area.
Following this flight, a switch was installed in the cockpit to
permit the radar operator to select D FT gate position and record
blanking for either high or low altitude operation. This flight
has been used twice to date to fly both high and low altitude
flights the sane day.
'light Tests
Repeated runs over the same target area with various second
amplifier bias levels were made to determine the extent of
images caused by IF limiting. Flight path was not consistent
enough to check data; the series will be repeated.
Several flights were flown to test the range boost circu
in both the 8 ke and 4 kc sweep rate configurations, as noted in
Appendix A,
Four flights were made over the Philadelphia area to show
results under simulated altitude conditions. A comparison of the
results of flights 137 and the first run of flight 138 showed the
simulation to be logical when extended to 90,000 feet, in fligh
1P2 and 143.
:L H 111 U 6
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 WKIAL HANULIiyu
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
Altitude Recorder RF
fight Simulated Sweep Rate Attenuation
142, 14'3
22,000 45,000
145,.000 45,000
145,000 90,000
4 kc
4 kc
10 db
0 db
instrumentation
The CEC oscillograph was removed from the aircraft in preparation
for installing a KA-45 aerial camera in that location. Some of the
signals formerly recorded on the CEC were added to the magnetic tape
ording. The signals now recorded during each flight are:
Variable Frequency oscillator Potentiometer Position
Antenna Accelerometer Output
Antenna Accelerometer integrator Output
Antenna Position Error
Aircraft Pitch Angle
DFT Meter
Aircraft Drift Angle
Aircraft Roll Angle
Antenna Roll Table Position
Aircraft Ground Speed
Sine of Aircraft Heading
Recordings of the aoceleratlons at the location of the aerial
camera were taken.
-9_
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
PHASE II FLIGHT TEST
The unsolved problems listed in the August report have been
corrected during this period. The errors in the INS output
signals of drift and pitch were caused by loading of the INS output
signal due to a wiring error in the aircraft magnetic recorder. A
defective charging choke caused the transmitter overloading problem
and was replaced. The erratic pulsed 120 me from the frequency
generator was due to a malfunction in the crystal gate driver.
Because of the lull In the Phase II activity, the following
was returned to Baltimore in October to increase the assistance
to the F-201 Flight Test Program and provide a back-up system:
(1) three of the four field engineers
adar system 002, not including the antenna and
single axis platform
Radar Test Set
valuator
few pieces of standard test equipmen
The second radar system, test set and the test equipment were
up in a new laboratory in the hangar, adjacent to the F-101.
Maintained in a ready status, this system has been able to supply
replacement assemblies for the F-101 system. In addition it has
been used for check-out of modified and repaired sub-assemblies.
Special system tests have been performed on system 002, such' as
phase-shift measurement of the receiving chain and modification
of the recorder to the 4 ke sweep configuration.
of the one system, activity on system 003 at the
Phase II
ing site has been limited to the installation of
modifications on the inverter, torque motor, and focus power supply.
aye~+r a. oo ai asLB~si3
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
A pressure test of the antenna indicated leakage to be about the
same as it was when shipped a year ago.
A fourth field engineer, normally located at the Phase II
returned to Baltimore for the month of December to ass
in the correlator set-up and become more familiar with the
ations and testing procedures.
Minor modifications to all three systems have been progressing
satisfactorily. Status is as follows:
Modification
'Video Amp, Increased Bandwidth
Control Panel, Second Failure
Determination
Frequency Generator, Temperature
Stability, etc.
Frequency Generatorr Oscillator
Transmitter, TWT Filament Supply 2
Range Mark Selector
:'der, inverter
Recorder, Focus Power Supply
Recorder, Torque Motor
Recorder, Inverter Low Frequency
Cut Out
C DYNAMIC CORRELATC)R
1 N/A
N/A
N/A
N/A
N/
N/A
The dynamic correlator was transported from the Phase II testing
area to Westinghouse. After arrival in Baltimore on November 23, th
correlator was set up in a special laboratory space, with the first
correlation processed on December 11. Operation of the equipment
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
by the same two Itek representatives as previously, with
results that are equal to those attained previously.
Initial installation was with a makeshift exhaust blower.
After installation of the proper blower and correction to the
conditioning in the room, a positive pressure in the room was
attained. Dust studies under various conditions are being conducted
reduce the level as much as practical.
In January a Contact Printer was received as OFE and set up in
the same laboratory as the correlator. Itek personnel
0 most
of the operation with this printer. Dupes of both the primary
correlated films can be exposed with this printer and developed
with the Veers mat provided by Westinghouse.
The consolidation of the radar and correlator work at
Westinghouse has reduced the time to process flight films. However,
erplay between the personnel of the two equipments is of much
more significance. Several instances have occurred in the two months
of operation where both radar and correlator problems have been
engaged more productively with the close coordination now possible.
First example came with the processing of flight 136 film.
First correlations were out of focus. However, a refocusing of the
correlator produced good results and pointed out the eexceseit
of change of the Variable Frequency Oscillator by the accelerometer
integrator. Further checking isolated the difficulty to the wrong
scale factor used for the accelerometer.
More recently, ground speed and imaging problems have been
eked more imaginatively through short recorrelationa of certain
;ht or test data film. As both the radar and correlator
engineers become more familiar with both equipments, even more
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
ive use of the equipment can be made.
Advantages to the Radar Interpretation program of this
correlator location are just as great.
D ENVIRQNM N'AL TEST
The results of the temperature and altitude tests on the
Frequency Generator were released In January as STM 161
environmental tests in addition to this were performed durini
period.
ICATION
duced Transmitter Pulse Width
ahoratorr work on reduced transmitter pulse width was
completed, using the rack breadboard traner
urned from
S FD. Transmitter results were encouraging, while receiver response
revealed an inability to reproduce the narrowed pulse.
Changing the CPA pulse forming network from 30 to 20 nano-
ends did not narrow the output pulse because of stray
capacitance of the charging choke and filament transformer. A
20 nanosecond output pulse was obtained by narrowing the TWT RP
pulse driving the CPA to 20 nanoseconds
a normal anode pulse.
pulsing the CFA with
A CFA tube which delivered 146 watts average, 1. MW peak,
30 nanoseconds, generated 90 watts average, 1.1 MW peak, when
operated with a 20mnoses and TWT pulse, Modulator efficiency
dropped 26 per cent due to the increased effect of stray capacitance
at the narrower pulse width.
Receiver response tests showed that the video output pulse
owed only slightly (approximately 3 per cent) for the 33 per
cent pulse width reduction from 30 to 20 nanoseconds. At the same
-13-
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
the amplitude decreases by 1.8 db. Thus, the present receiver
prevents taking full advantage of the narrow pulse widths attainable
with the transmitter.
Low Noise RF Pre-Amplifier
A wideband non-degenerate parametric amplifier was designed
J:GL L.L.Lgm, Tr e' a-u:Lng in to F-iO"1.
This Parametric amplifier uses two matched varaotor diodes in a
novel circuit design to achieve improved temperature stability.
cult configuration permits easy tuning of the idler resonant
frequency,
eliminating the idler frequency from the signal
Stringent phase requirements between pump and signal frequent
are eliminated.
The delivered parametric amplifier, to be Installed in the
F_101, has the following characteristics:
Noise Figure
Gain
Bandwidth, 3 db
1 db
Flat
Insertion Lose with no pump power
Pump Power
Pump Frequency
Beam Supply
Reflector Supply
Bias Supply
3.6 db
16 db
270 me
0 me
3 db
135 milliwatte
25,01 gig xycles
-1039 volts at 28.5
milliamps
769 volts
0.545 vol
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
System noise figure should be improved 1.0 to 1.5 db over
that attained with the Tunnel Diode Amplifier. Further Improve-
ment (about 0.3 db) could be attained by using a low noise second
stage in place of the present TWT. Parts are on order for the two
deliverable pre-amplifiers,
geBoost
Range boost extends the high frequency response of the video
amplifier to compensate for the recorder high frequency response.
Test films were generated using a single pulse in range of 20 to 40
nanoseconds duration. Four degrees of high frequency boost were
run for each pulse width. Evaluation of the resulting
was accomplished by scanning the recorded signal on the primary
film with a micro-densitcmeter. Rise time of the recorded pulse
was improved with range boost, but it was accompanied by ringing of the
range pulse. Effective range resolution was not Improved with any
of the four amounts of boost.
The preceding ground tests were performed on recorders of both
the 45,000 (8 kc sweep rate) and 90,000 (4 kc sweep rate) foot
configuration. Little difference was noted in the results
of the two recorders as predicted theoretically. The work is complete
except for the detailed evaluation of the 4 kc microdensitome
scans.
Data flights were made in the F-101 using the range boost of
our degrees with both the 8 ko and 4 ice recorders.
prove
meat of range resolution was noted on the secondary film. As a
result of these tests, the two deliverable systems will not be
ed for range boost.
-15_
SPECIAL H AN OLIN G
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
Increased Power Output
has been recommended that the proposed modification of
increasing power output by using improved cross field amplifier
tubes be deleted. The expected improvement of 1.5 db in signal-
to-noise ratio by this high power modification is about the same
Improvement attained through the change from a tunnel diode to a
parametric pre-amplifier. The cost of the high power components
alone would be more than the cost of the complete parametric
amplifier installation. In addition, it is expected that normal
tube development will make higher power CFA tubes available in
the future.
Receiver Phase Shift
Phase linearity measurements were performed on the system
receiver. Tests were performed using both the regular video
of the tests are shown on the graph of Figure 1.
Referring to the test equipment arrangement in Figure 2$ the
signal source was an X-band klystron, whose output was fed to
TWT. This TWT was serrodyned to add 1 ko to the test signal, and
its output passed through the receiver. The klystron test frequency
also passed through a phase shifter and double mixed in order
to beat the video amplifier output frequencies down to a difference
1 ko, containing the system phase information.
The serrodyning process produced some discontinuity pips at the
1 ko rate. These pips were reproduced at the output of the balanced
and served as phase change markers on the scope presentation.
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
TESTJAJC7
LLVSTI UN
r t I ~ }
9b /Sc ~7? 3bo
DE4'REE i
7b Ifw AWN.
W.
SC' L 14 e$'E,/IATio#/
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
VZCZ . PRK/S/cx/
PN49g SH/r7Ei2
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
A low pass filter removed the pipe on the scope sync input,
allowing the scope to sync on the sinewave only. Thus the pips
were caused to move across the scope face in response to the
system phase function.
Results with the wideband video are a smooth linear curve
with a one cycle superimposed ripple. Origin of the ripple was not
determined. Deviation in the phase shift of the receiver with
-band video amplifier was within acceptable
quenc lea s up to 20 me.
Recorder
video
Analysis and some laboratory effort was performed to determine
techniques of speed-up and linearization of the recorder sweep.
Both are required to match the correlator characteristics and im-
prove the output resolution. No changes are planned for this
generation of equipment, since the improvement In resolution is
rather small considering the cost Involved.
lability,
Failures have been reported through procedures established
in February 1964 which allow calculation of mean times between
es for these systems. All improper system operations are
classified as failures, including film Jams, broken wires, and
operator errors. Failures in which more than one component fails
are considered only a single failure. The I" SF calculations are
weighted to reflect actual ratio of standby to transmit time.
A summary of the failures and ? BF calculations is given below
for the system in the F-101 and system 002, just recently returned
to Baltimore. Operating time on system 003 in the field has been
too low to make valid calculations
-19-
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
Period
P-101 system
2/4/64 to
Operating Time, Standby 566.
Transmit 140.5
Average Standby 48.2
s, Receiver 2
Recorder
power Supply
Synchronizer
Transmitter
Nav Tie
Miscellaneous
but there was excessive flow into the slots during the pressure cure
and a losses of strength of the bond. Various batches of Doryl from
the two available sources were tried with varying results.
Acetonate to the Doryl adhesive caused a brittle bond with little
adhesion. Aerosol OT was added to the adhesive as a wetting agent
System 002
1/25/65 4/3/614 to 1/21/65
23T-7
32.1
24.4
0
7.2
Although all tests on antenna pressure sealing have not been
successful, the latest results are encouraging. Adding Ferric Acetel
Mean Time Between Failures
4 ANTENNA
these months of experimentation, best results were obtained
when using production Dory?. Power bubbles resulted when the cure
cycle started with a cold oven. Acceptable adhesion can be achieved
only when the array sticks are post cured for three hours at 315?C.
Since the solder sealing the module assembly ments at 310?C, the
modules must be disassembled, bonded and reassembled.
-20-
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
Rework of Antenna 3 was started. During this rework, it was
found that the bubbles generated in the bonding operation could be
reduced significantly by perforating a row of .030 diameter ho
along each edge of the 18 fabric and in areas not covering the slots
on 40 sticks indicate 75 per cent of the sticks have pressure
within acceptable limits on the first bonding attempt. Those
sticks out of tolerance have been reworked successfully by cv
coating with 16 resin.
e end of January, three modules of 16 sticks each have
been dismantled,
aned, vapor blasted, and ultra-sonically cleaned.
Bonding is complete on two modules and their reassembly started.
H GROUND SUPPORT EQUIPMFM
At the completion of the recorder development, Itek supplied
a rack used to test recorders. Changes were designed to allow
this rack, when used with the standard test equipment, to perform
the functional tests independent of the system on all radar system
assemblies, except the transmitter and single axis platform and its
electronics. A few power supplies, control circuits, and cables
ation approximately 85 per cent complete
quired. Design of the changes are complete, and the actual
The recorder cart is complete and now in use with System 002
in the hangar.
A review of the Film Evaluator suggested several improvements
in the azimuth evaluation portion to improve the usefulness in
the examination of test targets. The following modifications were
undertaken t
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
(1) add
enter to source slit to allow setting repeatability
trengthen mechanically the track for the scanning
(3) modify projector section, using better lenses in an
arrangement which allows easier and more stable alignment
4) modify phototube circuitry to provide logarithmic display
(5) modify the light source to improve alignment and stability.
All the items have been completed, axe
The Radar Test Set has been used extensively to provide
is to both the System in the F-101 and the back-up system.
Particularly useful is the dual azimuth target simulation, as used
in the tests to determine the effects of receiver non-lineariti
I SPARE
During this five month period, 68 items of system spares have
been shipped, leaving 54 open items. Of 8
added to spares
during this period 33 were transferred from the cu
sser
supplied list to be Westinghouse supplied and 11 were increased
quantities.
Completion of spares work by amendment is as follows:
ems PerCent Complete
list plus first 7 amendments
Amendment 8
Amendment 9
Amendment 10
18
2
98.5%
56 %
0 %
On the spares for Ground Support Equipment, 14 items were shipped
during this period, no items were added, leaving 15 items remaining
to be shipped. This amounts to 97% completion of the OSE spares.
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67BOO657ROO0200210016-6
APPXNDIX A
SIC OF FLIGHTS
Flight Number
115
116
117
Date
9/14/64
9/16/64
9/23/64
Altitude
22, 500
22,500
22, 500
Area
Philadelphia, Pa.
Norfolk,. Va.
Washington, D.O.
Purposes
System checkout and data
Data acquisition and range
Test range boost with 3 IF
-acquisition.
boost tests.
gains and linear motion
compensation system.
Significant
30 V P-P limited video.
30 V P-P limited video.
System Changes
Results
Presentation good from 1/2
Presentation fair in best
Presentation on a 50 sec.
to 3/4 range. Resolution
areas. Imaging and clutter
length of WF2 is fair. WF1
in best areas about 15 ft.
detract significantly. Vege-
is too dense and lacks con-
in azimuth and 20 ft. in
tation clutter extends into
trast. Imaging of a bridge
range. Clutter present on
water. Contrast and resolu-
is present. There was an
all strong targets. Images
tion in best areas fair. No
apparent reduction of trans-
present on same. Contrast
discernible effect of range
mitten-receiver isolation
irly good.
boost. Focus poor over
during flight. Film failure
near range.
during Run #2.
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67BOO657ROO0200210016-6
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
Flight Number
118
119
120
Date
10/l/64
10/6/61+
10/9/64
Altitude
22.500
220500
1+5,000
Area
Washington, D.C.
Washington, D.C. &
Philadelphia, Pa.
Baltimore., Md.
Purposes
Test range boost with 3 IF
Test range boost with 3 IF
Test linear motion ccmSpensa-
gains and linear motion
gains and linear motion
tion system and range boost 5.
compensation system.
compensation system.
Significant
12.5 V P-P video noise.
System Changes
Results
Presentation is good from
Presentation is good from
For about 8 clocks the
1/2 to 3/1+ range except
1/3 to 3/4 range (on Run
presentation was fair over
some empty gaps in azimuth
-11 at 10 volt level)o
a strip from 1/2 to 3/4
due to transmitter failure.
Best azimuth resolution
range. During part of the
5 Volt signal level appeared
is approximately 15 ft.
flight transmitter was out
better in contrast than 10
Low level contrast is
of coincidence. 400 cps
or 20 volt level. No dis-
good over best areas.
images were strong during
cernible map differences
Imaging and clutter is
this time.
in range boost changes.
seen by strong targets
as bridges., particularly
from clocks 62 to 64.
Good detail on most of map.
No correlated film at 5
volt level. Transmitter
failed during flight.
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
Flight Number
121
122
123
Date
10/13/64
10/16/64
10/21/64
Altitude
459000
22,500
229500
Area
Norfolk, Va.
Western Maryland
Boiling
~T
Washington., D.C.
Purposes
Test range boost 5 with
Test range boost against
Test range boost against
variable receiver gain.
corner reflectors.
corner reflectors.
Significant
Selected video noise
Reduced recorder bias from
System Changes
levels of 20 Vp 17 V,
38 V to 30 V.
and 12 V.
Results
Map is fair for first
Weather prevented flying
Map fair over strip from 1/2
3-1/2 minutes over a strip
by corner reflector area.
to 3/4 range. Corner re-
from 1/2 to 3/4 range.
Map is poor over the best
flectors appeared on poor
Remainder of roan has too
regions. Contrast and
part of map on all runs.
low density and poor con-
density are too low. Over
Azimuth resolution from de=
trast. imaging at 400
part of the film the
tailed correlation of red
cps was strong. Even
density is so low that
flector areas was 3 to 4 ft.
shore extends into water
strong targets are hardly
No range boost effects dis-
rather strongly.
identifiable.
cernible.
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
-4-
Flight Number
124
125
126
Date
10/28/64
11/4/64
11/10/64
Altitude
459000
459000
229500
Area
Norfolk,, Va..
Philadelphia,, Pa.
Purposes
Data acquisition with re-
Test new linear motion
Test linear motion compensa-
flectors at Norfolk Air-
compensation system.
tion system.
port.
Significant
PFN change resulted in
Minneapolis Honeyvell
System Changes
pulse width of 37 usec.
Integrator installed
and 29.5 watts pop.
prior to flight.
Results
Far range strip is good
On far range strip map is
Film jam in recorder pre-
over most of the range.
good from 1/3 to 7/8 range
vented acquiring data.
Contrast is fair. Near
over most of the flight.
range is good from 1/3
On near range strip map
to 3/4 range. Imaging
was good from 1/2 to 2/3
at 400 cps not as strong
range. Lox level con-
as in some previous
trast is only fair.
flights. Resolution in
Imaging of bridges is
azimuth is approximately
quite noticeable at
25 ft.
spacings of 400 cps, and
120 to 150 cps. Compen-
sating effect of ac-
celerometer is not ob-
vious.
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
-5-
Flight Number
127
128
129
Date
11/13/64
11/17/6+
11/17/64
Altitude
45,000
45,000
45,000
Area
Norfolk, Va.
Charleston, S.C.
Charleston, S.C.
Purposes
Test micro-megs parametric
Data acquisition.
Data acquisition.
amplifier.
Significant
Parametric amplifier in-
TDkre-installed prior
System Changes
stalled for this flight.
to this flight. Noise
Noise figure 5.6 from
figure 6.5 db.
6.3 db.
Results
tap was smeared in azimuth
Map out of focus entire fl
ight. Inconsistent drift data
and contrast poor over whole
from doppler navigator over
smooth water causes doubt in
flight. Flight was rough.
ground speed data. Many b
ank spaces occurred because of
Since accelerometer was
IFT unlocking. Water was i
maddy. Resolution poor.
not used in motion compen-
sation, film was badly
degraded.
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
Flight Number
130
131
132
Date
11/20/64
11/24/64
12/7/64
Altitude
22,500
22,500
45,000
Area
Washington, D.C.
Washington, D.C.
Norfolk, Va.
Purposes
Test effects of IF limiting
Data acquisition and test
High altitude test of in-
and IF gain.
integrator calibration.
tegrator and data acquisition.
Significant
30 V P-P limited video; 5,
Auto-correlator installed
Integrator re-calibrated
System Changes
10, 15, & 20 db IF attenu-
for this flight.
prior to flight. Transmitter
ation steps. Installed sepa-
repair produced 58 watts pwr.
rate limiting IF for signal
yeah V. bias reduced
Results
M p is good over the range
First 22 clocks taken over
Military operations over
strip usually in focus for
rural area with only fair
target area prevented super-
Runs #1 and #+. For at-
contrast and boundary
sonic flight. Integrator in-
tenuations of 10 db or
resolution. Where aircraft
strumentation run made at
more, the density level
was forced into sinusoidal
low altitude.
was too low and contrast
motion, the map appeared
was not as good as in the
good (azimuth resolution
other runs.
20 ft. or less) when ac-
celerometer was engaged.
When accelerometer was dis-
engaged, periodic smears
were obvious. This effect
was much greater on strong
distinct targets than on
vegetation areas.
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
Flight Number
133
134
135
Date
12/9/64
12/15/64
12/15/64
Altitude
45,000
45,000
45,000
Area
Philadelphia, Pa.
Charleston,.S.C.
Charleston, S.O.
Purposes
Integrator test and data
Data acquisition.
Data acquisition.
acquisition.
Significant
Increased CRT bias to
System Changes
37.5 V with 25 V P-P
limiting video. IPT
gate at 235 Usee.
Results
General appearance of map
Strong headwind kept groun
L speed 10% below nominal. In-
was poor. Low level targets
correct speed ratio-caused
nap to be out of focus on entire
hardly discernible to clock
flight. Results s3mil
flights 128-129, except signal
#19. From clocks f25 to
level more consistent.
#30 astigmatism (or rota-
tion) was bad and range
resolution was poor. Cross
track velocity was over-
compensated.
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
Flight Number
136
137
138
Date
12/31/61
1/6/65
1/6/65
Altitude
45,E
45,E
22950?
Area
Philadelphia., Pa.
Philadelphia., Pa.
Philadelphia, Pa.
Purposes
Data acquisition.
Reference for altitude com-
Run #1 - Simulated 1+5,000
parison.
flight flown at 22,500.
Run #2 - Effect of 10 db
SIN improvement.
Significant
Calibrated film speed
Recalibrated integrator for
Ferrite attenuator installed
System Changes
prior to flight. Video
5 V.G input. D]'T gate at
in receiver line, controlled
limit level of 30 V P-P.
235 uses.
from cockpit.
Results
Contrast was fair and
Nap improved in contrast
Map is best from 1/2 to ex-
resolution was between 20
and greater areas of well
treme far range for Run #l.
and 30 ft. in best areas.
resolved targets. Some
Contrast and resolution are
From clocks #26 to #30
fading occurred between
good. Some fading from
map faded because of
clocks #12 and #30 during
clock #35 to #40 when antenna
extreme position of an-
which antenna was in ex-
was in extreme position.
tenna due to acceler-
treme position. From
Some imaging and clutter of
ometer overe. sation
clock #12 to #15 slope
strong targets are noticeable
and excessive ringing
of accelerometer inte-
on Run #2.
of accelerometer in-
grator output was ex-
tegrator. Strong targets
cessive.
were poorly resolved in
this region.
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
-9-
r
C;
Flight Number
139
i10
141
Date
1/12/65
1/12/65
1/12/65
Altitude
459000
45 9 000
229 500
Area
Charleston, S.C.
Charleston, S.C.
Targets of opportunity be-
tween Charleston & Baltimore.
Purposes
Data acquisition.
Data acquisition.
Data acquisition.
Significant
IPT gate set at 230 usec
I gate set at 230 usec
System Changes
for this flight.
for this flight.
Results
First correlations were a
of focus, similar to flights
From clocks #15 to #20 map
128-129 and. 134-125. Rec
elated with a 20% shorter
is good and resolution is
focal length gave very goo
- map. No explanation for
good from 1/2 to 3/4+ range.
error; speed ratio checked
within limits from films.
Average density is high and
Resolution about 15 ft.
azimuth and 20-25 ft. in
contrast is marginal in low
range in last part of 140.
Contrast is good over
level areas. Shore s=eared
entire film. Occasional 4
DO cps and other images.
into water at about 400 cps
at clocks #24 and #+k.
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
 Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6
Flight Number
142
14+3
144
Bate
1/19/65
1/21/65
1/25/65
Altitude
15,,000
45F000
45,ooo
Area
Philadelphia,, Pa.
Philadelphia,, Pa.
Philadelphia., Pa.
Purposes
Simulated 90,,000 flight;
Simulated 90,,000 flight
Range boost test on 4 KC
from 1+5,,000a
from 45,,000.
recorder (007).
Significant
Recorder 007 modified for
Replaced CRY' bias pot and
System Changes
4 KC operation.
set for 60 V bias.
Results
Defective CR1 bias pot
Primary film density satis-
Mip is best from 1/4 to 1/2
caused primary film
factory. Best part of the
range. Azimuth resolution is
density to be high. Best
map is from i/4 range to
below average over all the
part of map is near mid-
mid-range due to filter
map. From clocks #10 to #15
range. Average density
slope mismatch. I&Lp of
some azimuth degradation oc-
is low,, thus contrast
small tanks at clock #27
curs while integrator output
is not adequate. Azimuth
is good. 'lank size scales
slope is greater than 25 cps/
resolution is poor over
from 25 to 30 ft. on radar
see. Contrast is fair for
most of the map.
map compared to actual
first 5 clocks and better
tank size of about 20 ft.
during the remainder of the
Motion disturbances low
flight. Motion disturbances
here during this view
during the flight were
time. Contrast is fair
significantly above average.
in tree-grass regions.
Sidelobes or images appear
at clock #32. Separation
is 75 mils.
Sanitized Copy Approved for Release 2010/12/09: CIA-RDP67B00657R000200210016-6