PROGRESS REPORT PERIOD OF 1 MAY 1965 TO 31 MAY 1965 CONTRACT NUMBER AF 33(600)40280

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP67B00657R000200210014-8
• Release Decision: RIFPUB
• Original Classification: K
• Document Page Count: 11
• Document Creation Date: December 22, 2016
• Document Release Date: December 9, 2010
• Sequence Number: 14
• Publication Date: January 1, 1965
• Content Type: REPORT

?/ AV P Ae
Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8 r.
1 +n- `ter,
Copy of 5.
PROGRESS REPORT
PERIOD OF 1 MAY 1965 TO 31 MAY 1965
CONTRACT KMER AF 33(600)k0280
BY
WESTINGHOUSE ELECTRIC CORPORATION
AEROSPACE DIVISION
BOX 746, BALTIMORE, MARYLAND 21203
SPECIAL HANDLING
Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8
 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8
TABLE OF CONTENTS
A F-101 FLIGHT TEST
FLIGHT TESTS
MODIFICATIONS AND ORO
SYSTEM
REC ORDER
QISE RpZEWER PRE-AMPLIFIER
OTION COMPENSATION
ANTENNA . . . . .
ENVIRON
TEST
SPARES ? _ r < s r a
GROUND SUPPORT EQUIPMENT ? a
F CORRELATOR OPERATION
CORR.ELATQR DESIGN RMEW , . . . .
APPENDIX A - SCARY OF FLIGHTS
TESTS . . r
a ? s ? e
? 6
10
Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8
 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8
F-101 PLIG
ht Tests
Five fIigh
flown during May, as Indicated in the program
summary in Table I. Radar tests were devoted to evaluating the low
noire pre-amplifier performance and obtaining data for linear
receiver evaluation. The linear receiver data was acquired by
varying receiver gain on repeated fly-'rya against a corner reflector
pattern located at Soiling Field.
An after-burner problem In the airoraf
hta to allow engine tests at high altitude. None of the attempted
have been effective in correcting the
'd mapping,
burner misfi
which occurs only above 30,000 feet.
A summary of the individual flights appears in Appendix A.
ht 165 was aborted due to a failure in the transmitter; flight
167 was unsuccessful because of a recorder fa lur
TABLE I
101 PROGRAM SUMMARY
may 1965
Flights Scheduled
Radar
hts Cancelled
Weather
Aircraft
Transmitter
aircraft
hts Accomplished
In-flight Failures
mitter
ecorder
Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8
flights to low altitude and reduced fligh
 r-. . , II? &If11 ILI f'
5F
Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8
Transmitter
ranamitt-er T developed a grid--to-cathode s hor
during flight 165. Since the replacement tube was longer than the
der defective tube, waveguide fittings and mounting braoketry had
at ions and Ground Tests
Bence. 't'ransm'itter 002 was then replaced by ? 1. Initial
~ts of drive, causing poor pulse shape and transmitter servo
modified. The replacement tube would not saturate, even with
power measurements were 26 watts average power. Changing the CPA
high voltage increased power outpu
of
69 watts with a pulse width
oseconds.
elver
During preflight for 166, a noise figure o
measured. Replacing a defective module in the Tunnel Di
Amplifier restored the system noise figure to 6.5 db.
After flight 166, the Tunnel Diode Amplifier was replaced
by the Westinghouse Parametric Amplifier to complete the flight
tests of this modification which were begun in January 1965. Inter-
mittent gain variation and oscillations were noted during Flight
ing WT in its normal configuration. Apparently the high
The Par-Amp was retuned, this time while operating into the
input VSWR of the TWT caused instabilities until compensated for by
uni,ng Performance during flight 168 was excellent. System noise
figure in 5.2 db; amplifier gain is 17 db. Bandwidth at the 1 db
level is 157 mc, at the 3 db level, 233 me.
owing flight 1.6h, the limiting IF ampi
video channel was converted to a linear amplifier in order to demon-
strate in-flight the effect of receiver non-linearity. Measurements
SPECIAL HANDLING
Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8
 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8
rifled the received linearity. Sufficient flight data has not
been gathered for complete evaluation of non-linearity effects.
Failures
During preflight for 168, the -(-60 volt power supply lost
regulation. The breadboard power supply was installed on the mis
door.
The pressure window between the transmitter and antenna
burned open during flight 164. The pressure system checked out and
VSWR measurements of the system wavegu de and antenna did not indicate
any existing conditions which could cause this failure.. The problem
has not been encountered again; however, transmitter power output is
now less than at the time of failure.
SYSTEM
Forward Look System
No flights were made with the forward look system because
abilities in their circuitry.
Recorder
roved flip-, l op circuitry has been wired into the
electronics package from recorder 007. Tests have been encouraging.
Following one more flight, this electronic package will be substituted
Order 005 f 6r flight testing.
Receiver Pre-Ampli.f
etor supplies, pump tube, waveguide components, control
mitry, and frame wiring are available and complete for the
deliverable Par-Amp installation. Since circulator delivery has
been delayed until mid-June, the system installation Is not expected
to be complete until late July.
Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8
 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8
Notices. Co npensation
Aft
ceiving the parts to reduce the peak transient
resporaa of the integrator, one unit was mod if ied . Results of the
transient response tests were as predicted. Frequency response
measurements remain to be performed.
Antenna
Several investigations were started following the failure last
;h of the spare module at 275?C .
A second module was temperature - pressu:
ed to determine
a different batch of Daryl adhesive would be satisfactory. This
:odule failed at 200?C and 10 psig pressure in the same way as the
first module.
(2) special batch of Doryl without a wetting agent additive
was obtained and applied to several sticks. Three test sticks held
psig at 288?C., but all failed when the pressure was increased to 20
psig. Bonding with Doryl will be further tested,. with a chemical
leaning process added to the procedure.
Dupont states that no changes have been made to their ML
fabric, the original material used on the antenna. Since it .s.,'
expected to delaminate as before, no further tests are planned.with
the ML.
nghouse Research Labs proposed two new techniques.
One involved bonding of a fiberglass film to a metal foil,, etching
the foil to
pond to the slot area.,., of an array stick, and
the foil. to the array stick. The second procedure bonds the
abric to the array sticks through heat and pressure without an
adhesive. Since the second technique appears more feasible, experl-
work has been authorized. Preliminary experiments will be
-6-
Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8
 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8
performed on 12 waveguidea; if successful, 16 array stinks for
one module will be bonded.
(5) Vacuum will be inve
d as a d ff erenll.
of pre
venting breakdown. Four test eticks were bonded conventionally
the Dory l. Leakage rates will be checked on these sticks and coating
applied to the fabric to reduce the leakage so that vacuums of
approximately 10 mm. of mercury can be attained. Electrical tests
allow.
C EW RONM NT A-L TEST
Recorder 006 passed a full explosion test. Since torque motors
own to are in use, they were specially tested to prove that
they would not cause an explosion. Details are reported in report
ST14-169.
D SPARES
No items were added to either system or Ground Support Equipment
spares this month. Status of spares is as follows:
Items Items Per Cent'
Shipped Open Complete
2 15
list plus first 10 amendments 2
Amendment 11 (remains open) 0
Ground Support Equipment 0 4
OTM SW'PPORT E QUIT
After preliminary tests indicated the Film Evaluat
c patible with the now optical bench components
ral
fabricated and the optical axis of the scanner changed to
make the bench a practical test tool to measure azimuth resolution.
Several plots of
and multiple targets show -20 db sidelobes
with a 4ynamic range greater than 30 db at low light levels. The
_7
99
99
Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8
 .UFf'IAI IaANfll INf;
Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8
-up is still being evaluated.
CORRELATOR OPERATION
in addition to processing the `-1011 flight film, one minor
cation was made to the Correlator. The wedge interference filter
holders were shortened to allow more motion to compensate for changes
in the focal length across the field. Twice the range is now avail--
able, permitting compensations of + 5 per cent in focal length or
approximately + 2 per cent in aircraft Velocity/film speed ratio.
Royal X Pan Recording Film 5475 used, as the final film is no
longer available. The replacement film type 2475 has similar speed
but less dynamic range. When chemically processed as the 5)475, It
has a higher gamma. By processing at 800 temperature rather
than 900, a lower gamma and better dynamic range were obtained. All
output films will now be processed in this manner.
Much effort was spent on the Detail Correlator this month. A
a of photographs were made using the designed 4,/ to I aspect
tics, the 1.4 to 1 ratio obtained by inverting the cylinder conjugate
and the 1.2 to 1 obtained by adding a small meniscus cylinder near
the primary output plane. Both 4x and 18x magnifications were made.
While the 1.2 and 1.4 aspect ratio were more pleasing;, the output
d with these two set-ups was curved approximately 3 inches across
inches. The field was flat for the 4.4 to 1 arrangement.
Photographs of various targets on seven flights were teen on
Polaroid Type 55 Positive/Negative film. This film allows fast resu
for analysis and repetitive work, and gives a relatively high reso-
lution negative for further enlargement. Because of the high gamma
of the Type 55, it is not suitable for comparison of low return areas.
I L HANDLING
Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8
 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8
SPECIAL HAKLING
a CORRELATOR DESIGN VI1
The design review report is delayed because of
information from Itek on their evrrelator noise and f'i
and insufficient experimental time on the corre
d ies
nghousea
SPECIAL HANDLING
plete
Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8
 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8
"light w4V e
4 06 4
165
6 i
l~
Date
5-3-65
5-11-65
5--10-65
Altitude
s 22,500
22,500
22,500
Area
!Washington,
Washington, D. C.
Washington, D. C.
Purposes
_
!Aircraft after-burner
Aircraft afterburner and
Receiver linearity test
test, data acquisition.
I receiver linearity tesus.
Significant
IF limiting eliminated Transmitter 001 in
System
stalled -26 watts
Changes
Resul Us
APN- 102 Doppler Navigator
d
No data due to trans- Re- ,eiver gain switch left
intermittent. Nest cart
muter- failure =
n
in 0 db oo itio n on all
Ii: e Etweer ha-If and full
d
r
s a ;.sow level targets
range . ontrast is good
su 'i as grass or
trees
resolution is sligt-.Ulu be
i-
pp
P
}? conger t-`nar _,z, sal 'be-
s'vs.
!l
ib
a;
-
s L s
low average, age, -Divergent
gg
k
'g ?
e?3'1~.s
of
ri
e
receiver
pclutter of bridges etc
.
'
'
, a in Detail like air-
,
!is strong
Also strong
.
, lights, show up
por
targets blank out back-
I
ett
ber than usual. .eso
ground in az mutt . Some
l~ ~t i on of road map is
smearing over full range,
good -15 were gt i-
light d
may be due to motion.
mens~ons. Corner reflect
Second and third runs are
ors v' apart were separ-
below average in both
able. Cloud effects were
contrast and resolution.
checked; no discernible
Dens ity variations ma-,- bel
attenuation or scattering
or scattering
due to motion,
Contrast at low levels
very good. Strong target
divergent clutter and az
moth background blanking
by strong targets was
present
APPENDIX A - SUMMARY OF FLIGWP
S
i
Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8
 Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8
5-26-65
22,500
Purposes Aircraft after.-burner
and receiver 1 inearit-
tests
Washington, D.C.
ignif scant 63 watts average power 16.14 db less P gain
ystem Far-Aro in glace of - 4 than fl t 16 _
hanges in receiver (5.db less
receiver gain)
6 runs were made at -5, k
10, and -15 db IF (,:,rain.
On most runs, low level
contrast was verT good.
Water and shadowed areas
were cleaner than usual
unless near a strong
target which had some
divergent clutter ;slight
on Run #5, -15 db gain
setting). Resolution
was good over best areas
Strong target halo did
affect immediate
surroundings.
Approved For Release 2010/12/09: CIA-RDP67B00657R000200210014-8