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

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP67B00657R000200210017-5
• Release Decision: RIPPUB
• Original Classification: K
• Document Page Count: 6
• Document Creation Date: December 22, 2016
• Document Release Date: December 9, 2010
• Sequence Number: 17
• Publication Date: February 12, 1965
• Content Type: LETTER

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Westinghouse Electric Corporation
Defense and Space Center Friendship International Airport
Box 746, Baltimore, Md. 212-03
Telephone: (301) 761-xooo
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PROGRESS REPORT
Period of August 1, 1964 to August 31, 196+
Contract Number AF33(600)40280
BY
WESTINGHOUSE ELECTRIC CORPORATION
AEROSPACE DIVISION
P.O. Box 746, Baltimore 3, Md . , 21203
1- SPECIAL HANDLING
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TABLE OF CONTENTS
PROGRAMS
F-101 FLIGHT TEST
LIGHT TEST.
EQUIPMENT
C ANTENNA . . . % .
B SPARES . . . . . .
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5PEC ALHATING
A. P-lOl FLIGHT TEST
The 300 hour periodic inspection on the F-101 aircraft pre
vented any system flights this month. With the inspection 95%
complete, all structural repairs have been completed. All T.O.
and TWX's have been completed, except a few which cannot be
cmplfished because of the modified aircraft configuration.
Receiver tests continued through this period. Outcome of the
tests has been the recommendation to increase the video amplifier
bandwidth.
modification reduces the number of overshoots
following a pulse. The accompanying reduced video gain causes no
difficulty in driving the CRT's now available.
The video amp breadboard was also modified to test a range
boost system. This range boost extends the high frequency respons
of the video amp to compensate for recorder high frequency roll-off.
The proper amount of boost will be determined in flight test.
anamitter pulse forming network was changed to narrow the
pulse and improve range resolution. Output power is decreased but
sufficient for this flight test program. Reducing the transmitted
pulse from 30 to 20 nanoseconds decreases
he received pulse
cathode ray tube grid from 30 to 29 nanoseconds. The response of
the IF amplifiers limits the minimum received pulse width.
The variable ground speed inverter and control oircu;
oved from the recorder to minimize ac pickup on the CRT display.
These units were mounted external to the recorder.
To accommodate flight tests at two different altitudes, the
Doppler Frequency Tracker was mod if ied to allow the gate to be
positioned in flight at either 90 or 180 microseconds range. The
switching for recorder blanking has not yet been incorporated.
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The preflight checklis
as updated to agree with the
modified system to be flown the following month.
Two signals--antenna accelerometer output and accelerometer
network output--were reinstated to the instrumentation magnetic
tape recorder to facilitate analysis of the linear motion compen-
sation system.
Operational checks on the instrumentation were begun late
in this period. Complete signal calibrations will be conducted
early next month.
B.. PHASE II FLIGHT TEST
The antenna servo was tested with the INS. Trouble was en-
countered with the INS. It appears that the drift, roll, and
pitch outputs of the INS are affected when the navigation system
is switched from one mode to another, independent of the radar.
Further investigation is required.
Testing continued on the first delivered system. A wide
variation in film density was encountered on Recorder 006. After
exchanging cathode ray tubes with Recorder 007, the first film
density tests were unsatisfactory because of developing. Recorder
007 was returned to Westinghouse to be modified.
The cause for the transmitter overload relay to trip has not
yet been determined.
Minor modifications included new lifting eyes installed on
the frame, test relay added in the Hav Tie-in, and a diode added
to Programmer to prevent relay chattering.
The second delivered system, 003, was received in the field
on August 12 Power supply voltages, stale :lockup, and receiver
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noise figure were normal. The pulsed 120 no signal from the
frequency generator was unreliable and prevented proper transmitter
operation.
The spherical and corner reflectors were installed at the
Phase II testing site to check resolution and detestability.
Following a request by Westinghouse concerning vibration
near the Single Axi_a Platform location, instrumentation people of
the prime contractor concluded there were no significant resonances
in the critical 200 and 400 cps region.
Major items delivered to the Phase II testing area were:
(1) antenna test stand and dummy antenna for testing
antenna servo
(2) lifting fixture.
ANTENNA
Tests continued on the antenna pressure sealing problem. 'o
samples of IS fabric, cured at different times and temperature
were bonded and tested. Best cure was the highest temperature.
Larger supplies of i :brio have been ordered from the supplier.
The new supply of Doryl varnish was not acceptable. The supplier
has suggested the addition of a small amount of Ferric Acetel Acetonate
be added to speed up the reactions and provide a stronger bond. The
catalyst and a new supply of Doryl. were . ordered .
D. SPARES
About 96 per sent of the system spares have been delivered.
g August, 25 items were added to the spares list.
Ground Support Spares are about 95% complete; no items were
added to the GSE spares this month..
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