PROGRESS REPORT PERIOD OF 1 SEPTEMBER 1965 TO 30 SEPTEMBER 1965 CONTRACT NUMBER AF33(600)40280 10 NOVEMBER 1965

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP67B00657R000200210008-5
• Release Decision: RIFPUB
• Original Classification: K
• Document Page Count: 13
• Document Creation Date: December 22, 2016
• Document Release Date: December 9, 2010
• Sequence Number: 8
• Publication Date: November 10, 1965
• Content Type: REPORT

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Copy 2 of 5.
PROGRESS REPORT
PERIOD OF 1 SEPTEMBER 1965 TO 30 SEPTEMBE
CONTRACT NUMBER AF33 (6003) 4280
10 November 1965
DOC.Q.--
COPY- OF
PAGES
.__--...._..
1965
BY
WESTINGHOUSE ELECTRIC CORPORATION
AEROSPACE D SION
0. Box 746, Baltimore, Maryland 21203
S -1E !AI HANDLING
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TABLE OF CONTENT
A P_10l Flight Test
ht Tests
ations and Ground Tests
B Field Flight Test
C System
Recorder r r a . . r .
Automatic Gain Control
Transmitter
s rr . N
Low Noise Receiver Pre-Amplifier .
Antenna r
Spares
Correlator Operation
relator Mechanical Review
Appendix A - Summary of Flights
4
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A F-101 FLIGHT TEST
FLIGHT TESTS
Four missions were flown in September, producing data of
the Wallops Island, Philadelphia, and Washington-Baltimore areas.
Specific information on all four flights is tabulated in Appendix
A.
Flight 184 was planned as the first of a series of flights
ng altitude and radar conditions of the Field Flight Test,
ever, after the F-101 was airborne, ground control would allow
a maximum altitude of only 35,000 feet and the flight was of no use
for altitude comparison. The second flight of this series, flown
the same day over the same path at 20,000 feet, was unsuccessful
because of a transmitter TWT failure.
The target area for the repeat flights for high altitude
simulation was shifted from Philadelphia to Washington-Baltimore
on flight 186 because of sonic noise considerations.
TAME
F-101 Program Summary
September 1965
Flights Scheduled
Flights Accomplished
Productive Radar Flights
No Results-Transmitter
Tt+ T Failure
Flights Cancelled
Weather
3
Target Area Clearance
1
Aircraft Problems
1
Recorder
i
Transmitter
1
Receiver
1
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n intermittent random striping or fading of video recorded on
primary film was mated, similar to the problem experienced
ate spring of 1964. Since the deliverable receiver used on
this one flight is suspected of being the cause, the breadboard
receiver will be installed for the next flight.
Shortly after the end of the radar run on flight 186, a
engine fire warning indication was observed. Post-flight
checks revealed an insulating blanket located between the engine
and fire warning sensors, had been punctured and insulating material
displaced. The aircraft has been grounded since the flight,
awaiting replacement of the blanket.-
DP? operation was checked on flight 183. Up to. 15 db
attenuation was inserted in the D IF amplifier with no noticeable
racker operation. The improvement in M?T operation is
due to replacement of a defective transistor In the Prequency
fenerator as described in the August progress report.
MODIFICATIONS AND GROUND TESTS
;Titter
The transmitter failure of flight 185 was caused by a grid-t
cathode short within the 7'. This tube was replaced.
Internal arcing of the new TWT caused an overload of diodes
.n the WT filament voltage switching circuit ., This circuit was
modified to switch the diodes out of the circuit prior to th
application of the TWT high voltage.
Voltage can now be applied to the vac-ion pump of the TW
during periods of transmitter inactivity to maintain its vacuum
ithout applying full high voltage.
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Transmitter servo lookup has been improved by molding n
external control into a pigmy connector and eliminating the
connector cable. The deliverable transmitters have always had
this Improvement.
Receiver
A defective stab in the breadboard receiver was discovered
prior to flight 186. Receiver 003 was. installed in the aircraft.
Although ground checks were satisfactory, the striping noted on
flight 1.6 may have been caused by this receiver. After replacing
a defective tube and relay, the breadboard receiver was re-installed
in the F-101 for the next flight.
Recorder
is normally free to slide from side to side over the
film take-up roller. However, several days exposure to high
humidity caused film to stick to rubber rollers and eventually
creep over the roller flanges. This problem was corrected by
replacing the rubber take-up roller with an aluminum roller.
After performing the 10-flight recorder adjustment and in-
spection procedure per T-Spec 787137, the electronics package was
led for 14 ke sweep operation in preparation for the fligh
simulating field conditions.
KA-45A Camera
The A.-15A was returned to the manufacturer for investigation
of the shutter malfunction. No difficulty was noted. Since being
returned to Westinghouse, the camera has not operated properly and
is still being checked in the laboratory.
Instrumentation
chile the aircraft is grounded for the fire warning problem
several instrumentation channels are being calibrated.
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FIELD FIGHT TEST
A proposal was submitted in anticipation of the reactivation
of the Field Flight Test. Supplementing this proposa
request for replenishment of spares as they are used and for
additional test equipment to test the parametric amplifier now
being added to the systems.
the completion of the extensive modifications to the
electronic package, all three recorders are now operational.
However, the first package used vector boards for initial testing.
These will be replaced with. printed circuit boards as used on the
later two units after Recorder 005 is removed from the F-101 next
month.
An Automatic Bias Control (ABC) was included in each
recorders when delivered by Itek.. Because the circuit has be
extremely noisy, erratic, and narrow in dynamic range, the ABC has
never been operated closed loop to control the average light output
of the cathode ray tube, but used only as a CRT light monitor for
the failure circui,
Several months ago, the film gamma was Increased to improve
overall recorder signal linearity. This reduced the required grid
drive to only 10-20 volts peak-to-peak,, causing two conditions which
dictated improvements to the ABC:
all variations in grid bias or CRT char?acteri.stics now
cause a signif leant change In light output and the operating
point on the bias-transmission curve.
-6-
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The more critical recorder set-up makes pre-flight
checks all the more Important. The present cheek is a
three-point bias check of film density, which requires
developing and analyzing the film before correcting set-up.
This undesirable time lag should be reduced.
Several changes have been tried on one recorder to improve the
BC performance
1. The light sensor increased in area by a factor of 7 and
placed more advantageously, making a large improvement
in the circuit signal/noise ratio
2. Input impedance to the ABC amplifier reduced from 10K to
I K ohms providing the proper impedance match for the
light sensor with improved stability and reduced noise.
Input circuit tuned to the system PRF giving somewhat
greater gain.
Circuitry changed to allow switching from open loop (light
meter operation) to closed loop (ABC) operation without
requiring a change in the bias adjustment.
Preliminary tests show the circuit to work well in closed loop.
A means of adjusting the C1 light output operating point is being
developed. Eventually these improvements will be incorporated in
all three recorders.
AUTOMATIC GAIN CONTROL
A flyable breadboard of the AGC was built and installed but not
connected in the F-101. Flight testing is delayed until sufficient
time is available to cheek out the AGC performance in the receiver.
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TRANSMITTER
Based on the experience with the F-101 teats, three modifications
have been designed for the transmitter and are to be incorporated in
units. These are t
Redesign of the TWT filament voltage switching circuit to
improve reliability. TWT t s are subject to internal area
under normal operation because of manufacturing imperfections
and outgassing. In the past, this arcing has caused some
lures in the filament switching c
Simplification
of this circuitry, with one component change, has eliminated
the failures due to arcing with no change in function.
21 Addition of an external method of applying voltage to the
TWT vac-ion pump when the transmitter is charged with
Adding two high voltage diodes and using a spare ENC
connector on the transmitter shell allow the TWT- to be
vacuum pumped without applying high voltage to the CPA.
The vac-ion pump is normally operated full-time when. the
transmitter is in
64
Addition of a TiT overload circuit to prevent loss of
suit components in the T'AT power supply and modulator
when an overload occurs. With this change, either a TWT
or CPA overload will shut off the transmitter and be in-
dicated by the CPA failure light on the Control Panel.
This overload circuit was deemed necessary because
a T failure in the P-101 transmitter caused the Phase' C
power supply fuse to blow, which in turn caused the two
transmitter heat exchanger blowers, running on only
phases, to overheat and fail.
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OW NOISE RECEIVER PRE-AMPLI
The parametric amplifiers for the two deliverable units
are being assembled now. ANTENNA
The heat-pressure life test on three array sticks bonded with
i-40 resin was discontinued after 604 hours at 550?F and 30 psig
internal pressure. The three sticks were then packed in dry ice
for three periods of 8 hours each. No leakage was detected from
any of the sticks either during or after the test.
During the continuous heat pressure test, large bubbles
developed on one stick and small bubbles on another.
ation
of the bond area showed that a residue of resin remained on both
the fabric and the metal stick surface, thus indicating a resin
deterioration. Based on these tests, life expectancy of the seal
500 to 600 hours at 5500F and 30 prig with no degradation at
_65?F
Bonding of the array sticks for Antenna 002 is complete on
five of the six modules. All sticks will undergo a heat-pressure
check at 550
or 8 hours before assembly to the module, Completion
of Antenna 002 is planned for 1 November 1965.
The feasibility of electron beam welding the joint between the
array stick and the manifolds was discussed at Westinghouse Atomic
Power Division. The complexity of the job evidently prevents the
of welding in this application, No further Investigation is
planned.
LcAL HANDLING
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The report on the bonding study at Westinghouse Research
Labs was released as technical. memorandum STM-172 ' Polyimide
Impregnated Glass Cloth Bonded to Nickel Surfaces for High
Temperature, Oas Tight Seals".
D SPARES
After adding four transmitter spares items (two blo
one motor, and an "C" ring), Amendment 11 to the system spar
exhibit has been closed and prepared for submission for negotiation.
The last of the spares for Ground Support Equipment was delivered
in September. Status of spares is suzmmari ed t
Items Shipped Items Per Cent
in September open Complete
System
Basic list plus first 10 amendments 0
Amendment 11 0
Ground Support Equipment 1
E CORRELATOR OPERATION
In addition to the regular flight support, some flight film
was recorrelated to give optimum focus at particular areas of interes
Flight 182 was rerun to obtain the optimum position of the output
slit system.
On the Detail Correlator, the tank platen assembly was Inter-
changed with the unit located at Itek, which includes a pump and
fluid filter system. The film now used In the Linhof camera back
for making exposures on the Detail Correlator is Type 247 5,, the same
used In the Correlator except for the 70 mm width.
17 99
99
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CORRELA'FOR MECHANICAL R. ''IE
As a result of the Correlator design investigation, five
ations, are being proposed to improve the Correlator
Performance. These are
a new input alit mount to reduce stray light at the
output film plane
installation of a liquid filter to reduce scattering
of light due to dirt in the liquid gate
polishing of scratched lenses to eliminate stray light
due to scratched surfaces
procuring new platen glasses to allow repolishing the
platens on a rotation basis
new rainbow filters with the proper slope to reduce
azimuth resolution errors when processing film from
22,500 foot altitude flights.
In addition, a film cleaner to reduce scattering of light
due to dust on the Input film was Justified by the study. This
eaner was quoted as part of the normal maintenance costs of
e correlator.
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 APP'17Y A
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SIGNIFICANT
S ti T a CHANGES
a-a
FLIGHT NO.
183 18k 185
DATE
9-3- 9-8-65 9--8
ALTITUDE
20000 35000 20000
AREA
PURPOSES
To evaluate W' opa rati
High altitude simu- nigh altitude
slm t-
l and obtain radar map of
j lation flight over lation flight
over
Wallops Island missile
Philadelphia, Pa. Philadelphia,
Pa.
launching site.
Repaired circuitry
None None
for video and D YT.
a
g
1 ES~MTS
a Is a rc~m I'~m a
7
- i ~'
1
range. Contrast &
map is best f ra m. near l No data.
{ resolution are good.
S
t
t
edge to 3A range .
5
ome
arge
s less than.
Resolution is not tie
1 20 ft. ShadM3 are fair
beat contrast is f a
clean. Low density bands
corres
o
d t
IW
Elementary dote are
p
n
o
T track-
in
error
I
t
elongated as much as
g
s.
ns
r nt-
3 to 1 and change in I
ation Information for
direction from verti-
deters .ng offset freq-
cal to 2 o' clock. nr
uency in error.
was tole 't . Antenna W46
pulled around by acceler-
ometer integrator.
Suspect roll table,
sity bands not as eonasty;
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 rsrrsurv. n,
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186
FLIGHT No.
DATE
9-21-65
ALTITUDE
1
AREA
PURPOSES
over Washington, D.C.
and Baltimore: .
?S FF ICANT
C
NOW transmitter TWT;,
receiver package changed
S O- ~M t
.tH~i ? E
i
j
C9
RE&SSIM.S.S
Stripes on pr or
# 04 to .12 see, duration
not always uniform over
range.- My be caused by
Stale instability. In be
t
areas resolution and con
mast
is . jqap Is faced
good
ram
gedge
to 1/3
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