PROGRESS REPORT PERIOD OF 1 JUNE 1965 TO 30 JUNE 1965 CONTRACT NUMBER AF33(600)40280

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP67B00657R000200210012-0
• Release Decision: RIFPUB
• Original Classification: K
• Document Page Count: 11
• Document Creation Date: December 22, 2016
• Document Release Date: December 9, 2010
• Sequence Number: 12
• Content Type: REPORT

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7
SPECIAL HANHLIN
Copy 2 of 5.
PROGRESS REPORT
Period of I June 1965 to 30 June 1965
CONTRACT NUMBER AF33(600) 0280
BY
WESTINGHOUSE ELECTRIC CORPORATION
AEROSPACE DIVISION
Box 746, Baltimore, Maryland 21203.
SPECIAL HANDLING
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TABLE OF CONTENTS
F-WI Flight Test .
Flight Teets . . r .
Modifications and Ground Tests
i
Low Noise Receiver Pre-Amplifier
Motion Compensation
s ? . s r
Antenna
C. spares . r ?
D. Correlator Operation, .
E. Gcrrelator Design Review
Appendix A - : n ary of Flights
SrWAL H.AN LING
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A. F-l0l FLIGHT TEST
ht Tests
Five radar missions were accomplished during June, as indicated
n the program summary in Table I. Primary prpo
the f 1 igh'
were linear receiver evaluation and radar interpretation data from
a ship anchored in Baltimore Harbor and army vehicles at Aberdeen
Proving Ground.
Flight 169 was the last in the series using the linear receiv
h a corner
tor pattern at Boiling Field as the primary target.
Difficulties on the next flight prevented direct comparison of the
limiting amplifier with the linear receiver.
Ten radar passes were made against the "Ciudad de la Habana"
a freighter anchored in Baltimore Harbor, at 0O0 450, 900, 31;50, and
2700 headings relative to the ship and for down-look angles of 240
and 38?.
TALE I
F-l01 PROGRAM SUMMARY
June 1965
Scheduled
.14
hts Accomplished
Radar
5
Flights Cancelled
Recorder
I
Receiver
1
Power supply
1
Weather
3
Aircraft
3
In-flight Failures
Power suppi
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Radar returns have not been constant over the full range for
the flights at 22,,500 feet altitude. Near range returns were less
than normal, indicating incorrect positioning of the antenna elevation
pattern relative to the recorded range sweep. Range mark timing and
transmitter delay (l uses) were measured relative to the same
synchronizing pulse and found satisfactory. A map with more uniform
was obtained by flying at 21,000 feet altitude to effectively
shift the antenna pattern.
Appendix A summarized the individual flights in June.
All radar data was recorded at low altitude. However, the
aircraft was flown to 40,000 feet on three flights to perform after-
burner engine tests. A Pratt and Whitney representative has
visited Westinghouse as a consultant and recommended further engine
work. to correct the deficiency and permit high altitude, super-
sonic missions. Failures of the radar operator's oxygen regulator
and aircraft altitude indicator and a skin fracture that occurred
during flight 172 have been corrected.
Personnel fry Hill AFB in Ogden, Andrews AFB, and Wright-
Patterson AFB met at Westinghouse to review the IRAN and Tech
Order status on the F-l0l. Four T.O.'s, were considered critica
T.O. 847 Wing Skin Doubler
T.O. 859 Speed Brake and High Q Fence
T.O. 921 Rivets in Wing Rear Spar
(4) T.O. 951 Heat and Vent Ducts
In order to maintain maximum aircraft availability for the contract
AFB people will fabricate ducting; and supply a crew to perform
these depot level T.b.'ss at Westinghouse in July.
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V LI.IML 11H1@? iV )
Modifications and Ground Tests
Receiver
After completing the linear receiver tests with flight
169, the second IF amplifier was reconverted to the normal limitin
c onf igura
During, the flight 171 pre-f light, a change in noise level
and receiver oscillations were noted when the transmitter was on
Retuning the Par-Amp and changing the Par-Amp bias fU
corrected the trouble.
Tunnel Diode Amplifier failure was reported in the May
progress report. The TR tube was replaced at the same time as the
TDA module and returned to the manufacturer for testing. The TR
tube was found to have a cracked window which increased the trans-
mitter leakage per into the TDA, causing the TDA failure.
Transmitter
An intermittent overload developed during the 174 pre-
flight.. To expedite flying, transmitter 001 was replaced by the
breadboard transmitter, which provided a 32 nano-second pulse and
40 watts average power.
Recorder
The improved electronics package with higher reliability
and faster switching in the flip-flop circuits has been flown for
the last four flights with satisfactory results. The C blanking
uitry was modified at the same time to shorten the cathode
urn lead.
Post-flight tests following 169 indicated a decrease in
CRS' light output and a change in the recorder transfer eharacte:
~(WAL HANULING
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Recorder 006 replaced 005 In the F-10l. The recorder bias vs.
film transmission curve for this CRT is very steep over the desired
linear operating region, causing the bias adjustment to be quite
critical, as evidenced by the maps of flights 171 and 172 against
the ship.
The high voltage power supply was unsynchronized Into
mittently during flight 169 causing a change of focus, in addition,
a $u8 failed in the dynamic focus circuit.
Recorder 006 now in the P-101 has satisfactory C
but the trace focus on the capstan is out of adjustment. Becau
of this maladjustment and the greater vibration noise in recorder
006, recorder 005 will be ,returned to the F--101 prior to the next
ht.
Power Supply
An arcing fuse--holder and a shorted Zener diode were re-
placed in one of the +150 volt power supplies during the pre-flight
for 171. The shorted Zener caused a voltage overload and damage
to a transistor in the film drive inverter.
Forward Look System
Data from the forward look system was recorded for the
second time on flight 173. Receiver gain was inadequate for proper
operation.
B.
Low Noise Receiver Pre-Amplifier
The Par-Amp installation for the two deliverable units has
been delayed another six weeks. The delay imposes no problem,; since
the Phase 11 flight test is inactive until October.
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Motion Compensation
Tests on the modified integrator unit were completed. Results
showed the gain and phase shift to be the same as the original
design, while the resonant period of the ringing was increased less
than 10 per cent. However, the overshoot in response to a step
function was reduced eignif cantly t
ad Unit Unmodified Unit
shoot in High Gain, First Maximum 5.2 volts
7.5 volts
Second Maximum. 0.83 volts 3.3 volts
This improvement will be added to all units, including the integrator
used in the F--10:
Antenna
Investigation into possible solutions to the antenna sealin
problem is continuing along several paths.
inghouse Research Labe have achieved excellent bonds of
fabric on nickel strips with heat, pressure and no adhesive.
However, bonding to the waveguide sticks has been more difficult
because of non-uniform pressure along the bonding surface. Two
successful bonds have been made and are being tested.
Research Labe are also working on a wet overlay bond, in which
a glass fabric saturated with resin is laid on the waveguide sticks
and cured and then overcoated with successive layers of resin, which
are cured in sequence. This has been unsuccessful to date because
of the formation of bubbles in the bond line and air leakage through
the fabric at room temperatures.
In tests at Aerospace, IkO and 166 resin was used to bond the
fabric to waveguide as Doryl had been used. One sample out of
three for each type of resin survived 6 hours at heat and pressure;
one of these
later held 70 psi pressure at roan temperature.
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The remaining sticks developed leaks in the bond line during
heat-pressure teats. Except for a few local spots, adhesion was
exceptionally strong, indicating a problem in cleaning the sticks.
Tests showed that the vapor degreasing and ultrasonic cleaning
hot tri-clorethylene did not leave the surface clean. Electro-
chemical etch should replace the ultrasonic cleaning.
No additional testing of the Doryl resin is planned because
of non-uniformity and lack of control on. the resin.
Vacuums of 10-4 gun of mercury were attained on. an antenna
module (16 sticks). Because of the encouraging results with the
1140 and 166 resin bonding techniques, this technique will be
discontinued for now.
C.; SPARES
One Item - TR tube - was added to Amendment 11 of the system
spares exhibit.. Status of spares is as f ollowss :
Items
Ite
Cent
Shipped
Open
plete
Sys
1
99
Basic list plus first 10
amendments
1
9
99
Amendment 11 (remains open
Ground Support Equipment
1
99
D. CORRELATOR OPERATION
The beat correlated map to date was obtained from flight
168 in the Washington, D. C. area.,
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Jr Ll,IP L 1 If ?JL'".v
'WW
A series of test correlations was run to determine if the
narrow alit above the wedge interference filter could be located
to eliminate extra images caused by inter-reflections. As a
the alit has been relocated.
Work with the Detail Correiator continued. Two plane-convex
cylinders were added to the enlarging system which normally 'provides
a 4.4 to 1 aspect ratio. The added lens enlarged the range
dimension approximately 1 times, while relaying the azimuth infor-
mation, to provide a 1 to I aspect. Since they are simple lenses,
field curvature is still a problem. Achromatic doublets have been
ordered to improve this.
Several targets from many flights have been correlated on the
Detailer for interpretation work and study.
E. CCRRELATOR DESIGN REVIEW
Further delays have been encountered with the information for
design review report.
Srt U AL HAN0UUNG
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APPENDIX A
Flight No.
169
170 J
i
Date
6-2-65
6-14-65
6-22-65
Altitude
22500
21000
21000
Area
Washington, D.C.
Washington, D.C.
Baltimore- Harbor
Purposes
After-burner checks;
After-burner L herkss
.~ultiple runs against
receiver Linearity
Iii lI rrmiting es `?4th,
an arch red sh p0
ests with corner re-
corner refleib for ear-
P
flector targe,s
gets; Altitude change
i or antenna pat tern
test..
Significant stern ~
11.14 db less FT gair.
L it:L--gig receiver; re-
if l
d
6
YTone
Changes
than flight I66
; ,od
e
corder 00
recordder electronics
1
package.
{
Results a
4 r vi i at
were
Antenna servo
6
~1^ix~'v~ z ~~'- ~a~ on ?...?~~
and 20 ab. Run 2
15
corder not turned on,.
ecor~ela ion a
,
fail
No o 7 d d J tamed
I ore de ail, sit con-
rast s ~