REPORT OF CURRENT ACTIVITIES

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP89B00487R000300510001-6
• Release Decision: RIPPUB
• Original Classification: K
• Document Page Count: 52
• Document Creation Date: December 22, 2016
• Document Release Date: August 9, 2011
• Sequence Number: 1
• Publication Date: January 3, 1958
• Content Type: MEMO

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1. Three Configurations (B #13, A-2 #12, A-2 #13) are ready for
ABSTRACT
shipment to Del Rio.
2. A second Shutter HS-732 ran 170, 000 cycles without malfunction in a
durability test.
in Configuration C.
3. Simple additions to the radio noise filters provided adequate suppression
,missions with satisfactory electrical and mechanical oper.atioon.
4. Reliability of Configuration B has.been established in 15 successive
35 1/mm in the later flights. Further work may improve this in January.
5. The quality of Configuration B photo results has consistently been
LIST OF ENCLOSURES
Manning,Chart, Field Service Department
Preliminary Engineering Report on Resolving Power of some aerial film
Location of Configurations
1. Configuration B Rework
2. Durability Test HS-732
3. Progress Report on the 73-B Vibration Problem
4. . Radio Interference Tests on HR-73C Configuration
.'Optical System
.55. Interim Report, Cold Temperature Tests, Configuration 73-C
SAPC ,2g2ey
COPY 7 OF
3 January 1958
25X1
LJ/\ I
Report of Current Activities
6. Flight Test. Schedule
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'fi ' e f pr e a the ? ewc>
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arnd bea ..1 g groove v erm t ess backlash. Slight shutter b# de
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HYCON MODEL 73-C CAMERA SYSTEM
RADIO INTERFERENCE SUPPRESSION
WORK PLAN
25 October 1957
Subject, The subject with which this work plan is concerned is the
radio noise interference which is created by the 73-C Configuration.
1..2 Purpose. It is intended that this work plan be a systematic and logical
approach to the problem of radio interference in the 73-C. It is not
meant to be a rigid plan, but one which presents a framework for the
sycternatic solution of each problem.
1. 3 Scope. Basically, the intention is to detail a procedure of testing,
correction, performance testing, and evaluation, An appendix is at.-
tacked which outlines briefly the general problem of radio interference.
2. 1 Radio interference. Specifically, the 73-C Configuration generates
noise which interferes with the aircrafts radio and ADF equipment..
2,2 Mode of Propogation. Two modes eNist: conduction and radiation.
It is, expected that both modes will be encountered.
2. 3 Frequency Range. The frequency range of interference with which we
are concerned extends from 150 KC to 400 MC.
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2.4 Permissible .Levels. The level to which the radio interference. is
to be reduced shall be defined. as the level which permits the aircraft's
radio equipment to perform satisfactorily. This shall be determined by
Hycon engineers. in cooperation with the aircraft personnel, concerned.
3.0 PROCEDURES.
3. 1 Testing.
3. 1. 1 All units of the 73-C Configuration which are suspected of being
interference sources are to.be tested. by either the radio noise
facilities of Cornel-Dubilier (or similar facilities) or by our own
RF (G. F. E.) receiver.
3. 1.2 It shall be the function of the above test to determine the. sources
of radio interference, the interference level. associated with each
source, and to find filter devices and/or develop techniques which
will reduce the level of interference.
3.2 Correction.
3. 2. 1 The results of the testing described in 3. 1 will indicate the
correct means of reducing the interference.
3.2..2 Units which, are prime offenders will be modified first and
tested as outlined in 3. 3.
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3. 2. 3 It is anticipated that in the majority cases, the radio inter-
ference will be reduced adequately by the use of:
1) Filters.
2) Arc suppression devices.
3) Shielding.
4) Improved Bonding.
3.2.4 All corrective work shall be accomplished at Hycon Plant 99
under the supervision of the engineers responsible for the
particular units.
3. 3 Performance Testing
3.
3. 1
3.
3.2
3.
3. 3
Each modified unit will be taken to the Test Site and installed
in the 73-C Configuration.
The Configuration will be installed in the aircraft and operated
in conjunction with the radio equipment.
A qualitative comparison of the interference levels and an
evaluation of the improvement of the levels by the modification
of each unit will be made at this time.
3. 3.4 Further testing and improvement will depend upon the performance
of the modified units as determined by a flight test.
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Progress Report No. 1
RADIO INTERFERENCE SUPPRESSION
WORK PLAN
24 October 1957
1. TESTS PERFORMED.
1. 1 Units Tested As of this date, the following units have been tested
by the radio noise facilities at Cornel-Dubilier Electric Corp. ,
Venice, California.
1.
Gyro Sensor Assembly
Part No.
7338915
2.
Film Take-Up Motor
Part No.
734360
3.
Aperture Motor
Part No.
733273
4.
Tension Regulator Motor
Part No.
734181
5.
Film Drive Motor
Part No.
733646
6.
Oblique Drive Motor
Part No.
733676
7.
Main Junction Box
Part No,
734120
8.
Film Drive Servo
Part No.
733640
9.
Oblique Drive Servo
Part No.
733670
10.
Stabilizer Servo
Part No.
7.33870
11.
Programmer
Part No.
733600
12,.
Stabilizer Power Supply
Part No.
733885
Items 7, 8, 9, and 10 above comprise the Electrical Rock.
1.2 Conditions of Testing The radio interference testing facilities at
Cornell-Dubilier Electric Corp. , are designed and equipped to conform
with the environmental requirements of Mil-1-6181B. In brief, this
means the tests were performed in a screened room with no detectable
interference "present; the equipment being tested was mounted on a
ground plane of specified minimum dimensions and properly bonded to*
the screen room; the equipment was bonded properly to the ground
plane; line stabilization networks were utilized on the power lines; and
AN-type radio interference measuring sets were used for quanitative
results.
2.0 TEST RESULTS.
2. 1 The units which were determined to be prime sources of radio inter-
ference were:
1. Film Take-Up Motor
2. Aperture Motor
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2. 1 (cont'd)
3. Tension Regulator Motor
4. Film Drive Motor
5. Oblique Drive Motor
6. Programmer
7. Gyro Sensor Assembly
The order of the above list is not intended to indicate the magnitude
of the radio interference emitted by each unit.
2.2 Recommendations. With the exception of the Gyro Sensor Assembly,
which did not receive further testing, filter devices were tested and
techniques recommended by Cornell-Dubilier for all other units listed
above.
2. 3 Levels After Filtering. Although Mil-I-6181B specifications are intended
to be used only as a guide, tests performed by Cornell -Dubilier indicate
that all the motors can easily be modified to be well below the specified
maximun levels of Mil -I-6181B. Tests on the Programmer (after filter-
ing) indicate a substantially reduced level which should be adequate.
3, 1.. Motors The motors tested (i. e. , the Film Drive, Film Take- Up,
Aperture, Tension regulator).. Have been modified as follows:
a. A filter, of the type -recommended by Cornell-Dubilier,
has been installed.
h. The units have been reworked to obtain better shielding.
This has mainly been accomplished by use of shielded wire.
c. Great care has been taken to insure good bonding between
surfaces to improve the electrical ground. Insulating
layers, such as anodize,. have been removed at the points
of contact and the surface cleaned.
The direct purpose of the above modifications is to contain the radio
interference within each unit and thereby prevent conduction and /or
radiation to occur.
3. 2 ., Programmer. A shielded box has been constructed upon which has
been mounted twenty five filters. This filter assembly has been taken
to the Test Site, mounted adjacent to the Programmer, and the filters
inserted into the appropriate leads. The filters used were recommended
by Cornell-Dubilier.
3. 3 Gyro Sensor Assembly. The prime sources of radio interference in
unit are the heater circuits of the gyros. A. double RC network of,our
own design has been installed across the relay contacts in each circuit
of the unit in the 73-C Configuration at the Test Site.
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4. 1 Testing . The above modified parts were removed to the Test Site
and installed in the 73-C Configuration there. Test procedures were
carried out as outlined in the Work Plan, Section 3, 3.
4. 2 Test Result. After the. configuration was installed the article was
towed to a remote section of the flight line.,. The unit was operated
in different Modes for half an hour while Mr. Joe Falcon, aircraft
radioman listened on various receiver channels for radio noise. His
opinion was that the noise had been reduced to an aniount that was
barely noticiable and would present no receiving problem.
4. 3 Flight Test The 31 October 1957, Test Flight, of the 73-C will he
used for a 'pilot's evaluation.
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2. 4 Flight Test Schedule (See Enclosure (6 . )
The proposed flight test schedule for January through April 1958 requires
a high frequency of test flights in latter part of January and in February. The
number of articles available and weather may be limiting factors. Two flights
will be made with each B Configuration. After results have been analyzed and
determined to be satisfactory, the configuration will be returned to M & O :for
preparation for deployment.
3. PERSONNEL (See Enclosure (4).)
The rotation of field personnel is proceeding in accordance with the schedule
enclosed. This schedule differs from the one reviously submitted in that it
indicates a change in the rotation -of In addition we are 25X1
proceeding to assign) ~ to maintain hand controls and drift sight at 25XI
the0 Instruction of ersonnel rotating is proceeding. We have sent all our 25X1
processing personnel to facility for a week's training. We also sent 25X1
two of our field men to Rod Scott's for refresher instruction in the maintenance of
the Mark II tracker prior to our running the Red Dot Tracker series.
reported to C Detachment on Tdy for the purpose of re-collimating all 25X1
of C's A-2 configurations.
The two FOG instructor-type trainees reported on 9 December and their in-
struction is proceeding.
reported to Del Rio on 9 December as our second tech rep in
accordance with the terms of our FOG field service contract.
4. STAGING
A number of commentary reports on staging operations have been prepared by
our field. service engineers from all detachments. is analyzing 25X1
this information and preparing a final consolidated report and recommendations.
Other than providing adequate shelter, and better portable 70 mm processing
.equipment at the staging area, there are only minor changes in or additions to
ground equipment required. Recommendations are mainly concerned with pro-
cedures and pre-staging requirements.
5. OTHER COMMENTS
5. 1 Film Resolving Power (See Enclosure (8). )
A film resolving power test was made by our optical lab. It indicates the
resolving power of thin base film, 0-3, is considerably better than that of Aero xx.
The Red Dot film, 0-8, had a resolving power beyond the limit of our reticle,
114 lines /mm,
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5. 2 Configuration A-1 Overhaul
A preliminary check indicates the cartographic characteristics of the
HC-730 cameras have been unaffected in their tour of duty. Further checks are
being made. A review of HC-730 spares was made and a recommended re-
distribution submitted.
5. 3 Shutter HS-731 Leaf Assemblies
200 spare leaf assemblies are being obtained out of shutters at Mobile by
Bob Welch. None have been received but 25 are expected this week. Ed Green
obtained a quotation of $112. 92 each with five months delivery from Fairchild for
100 spare leaf assemblies. They can be ordered if the spares from Mobile are not
satisfactory. Detail drawings of leaf assembly parts were sent to us by Sid Brewer
in order to permit us to salvage some leaf assemblies by manufacturing replacement
links.
Installation of the Rolit at EAFB is ready to proceed pending approval by
Headquarters.
5. 5 Wires Survey
Completion of the C spares deliveries in January and February will provide
satisfactory lead time for the coming photo season. Hycon is planning to take a
physical inventory of the photo areas at all locations on 31 January 1958. This
-'will reveal any discrepancies between the records and the physical assets in time
to take action prior to the start of the photo season.
5. 6 B Film Boxes
Ten new steel B film boxes were shipped to us by Ed Green on 24 December.
We have manufactured ten sets of B spool shipping spiders to a new, more rugged
design. When the steel boxes arrive, we will make some trial packaging arrange-
ments.
5. 7 Location of Configurations (See Enclosure (.9 ). )
The latest information on the physical location of configurations is tabulated
in Enclosure 9 .
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Enclosure (1)
2 December 1957
Page 1 of 5
CONFIGURATION B, REWORK
1. Added stiffness to camera members to control film tracking. Design in final
approved stage. Production began week of 1 December.
1. 1 New Stiffener bar to cross panel to maintain roller parallelism under
overload conditions.
1. 2 New cassette shafts to limit load deflections to 0. 005.
1. 3 New clamp type cassette shaft supports to provide positive clamping of
shafts during camera operation. The design also offers adjustable lateral
positioning and securing of the spools to aid in film tracking.
. 1. 4 New 6-inch spool cores to add stiffness to flanges.
1. 5 New sheet metal stiffener beams added to structure side panels. Beams are
secured f camera main torsion bar and extend to two corner points of
structure that support the film spool shafts. Design in layout stage; pro-
duction to begin week of 80becember.
2. Added strength to driving members. Design in final approval stage; production
began week of 1 December.
2. 1. 1 Adaption of more ball bearings throughout to replace bronze type to
allow smoother operation with decreased demands on motor.
2. 1. 2 New stronger drive shafts.
2. 1. 3 New pressure and idler rollers.
2. 1. 4 New supporting brackets for cantilevered bearing shafts.
2. 1. 5Internal changes to gear box to use brazed gear and shaft assemblies to
replace pins and screws.
2. 2 Oblique Drive
2. 2. 1 Improved security of pulley on gear box output shaft.
2. 2. 2 Internal changes to gear box to use braized gear and shaft assemblies
to replace pins and screws.
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Enclosure (1)
2 December 1957
Page 2 of 5
2. 3 Take-up Drives
2. 3. 1 All Motordyne type motors have been replaced with Western Gear
type motors. Experience indicates the Western type is more reliable,
quieter operating, and better matched to the load demands, especially
the 6, 000 ft. load.
3. General Design Improvement
3. 1 Adjustable oblique brake device now in production as an aid in postflight
maintenance to insure positive positioning of-lens assembly.
3. 2 Cassette centering device improvement in design phase for correct position-
ing of cassette for film spool alignment.
3. 3 Investigation is in progress to provide stronger film tension limit stops
and a system of less critical adjustment. Production expected to start
week of 8 December.
Environmental tests have been conducted on the shutter operating in a vacuum
under both-hot and cold conditions. No adverse affects upon material or operation
were noted.
Examination of all parts returned to the factory show corrosive action in some
.external parts on unit from C Detachment only, but no evidence of corrosion was
found as a deterrent to camera operational reliability. C Detachment unit shop
ran four complete missions during tests before disassembly for major maintenance
and current rework.
Complete system environmental test in cold chamber will.be conducted upon
completion of rework program.
A series of tests have been made to study the feasibility of eliminating the
tension sensor and servo system as an aid to reliability. The tests indicated that
under normal conditions the film would transport properly without the aid of the
sensor system. However, when the take -up -spool diameter reached a point approxi-
mately halfway through a film roll, any increase in drag due to a worn bearing;
voltage drop, or spool flange pressure, the motor could stall and stop taking up
the metered film. It was decided that the factor of safety and reliability by having
the demand power response capability of the sensor system on the camera was
worthwhile and steps then taken to improve the design where possible. (See 3. 3)
Life cycle tests Ore complete on the film drive, improved oblique drive motor,
take-up motors and the tension sensor systems. Approximately 80, 000 feet of
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Enclosure (1)
2 December 1957
Page 3 of 5
film or over 13 (6, 000 ft.) mis sions have been successful with no malfunctions or
replacements of these components. Sixty percent of the missions were actual test
flights.
Evaluation tests are complete on the take-up motor demand versus capability to
reaffirm initial motor specifications. Results show Western Gear type motor
adequate for application with good. safety margin capability.
Analysis of test flight results show that vacuum failures will not occur due to
the camera vacuum system providing the vacuum valve is periodically inspected
and adjusted per the post maintenance procedures. A spring-loaded plunger de-
sign is being tested to minimize possibilities of improper adjustment which is
critical at present. Aircraft instrumentation to record bay differential vacuum
pressures will be performed on a near future test flight at EAFB. Report to follow.
MAXIMIZE PHOTO QUALITY
1. Vibration (See Encl. 3)
1.1 Shutter
Design for shock mounting the shutter is complete and in production. The
design calls for the addition of six soft spherical rubber buttons, set deep into the
shutter castings that isolate the shutter assembly from the lens housing. Shutter
castings must be machined to provide additional clearance for free movement within
the lens housing. Light sealing is accomplished by addition of nylon velvet ribbon,
set into shutter at mating surfaces around "drawer" opening.
1 Motors
Design for shock mounting the film drive, take-up and oblique motors is
complete and in production. All motors will be mounted on rubber grommets.
Vibration and noise level has been greatly reduced.
1. 3 - Mirror and Platen
Design changes pending accelerometer studies.
1.4 In-flight aircraft three-axis motion rate recordings. (See Encl. 3)
2. Design improvement affecting photo quality. Production to begin week of 1 Dec.
2. 1 New improved IMC direct drive system utilizing one-piece cycle shaft,
silent chain drive, and simplified clutch-gear housing to eliminate all backlash in
driving train.
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Enclosure (1)
2 December 1957
Page 4 of 5
2. 2 New cassette light seal to camera body. Sponge rubber removed from
light seal channel frame on cassette and lip frame on camera increased in height
to provide a non-contact light-'tight baffle.
2. 3 New adjustable focus posts to provide ready means to perform corrective
focus changes if necessary and as .an aid to factory collimation procedures. Posts
will be locked and safety wired after factory collimation.
2. 4 Improved data image by tests using a masking aperture in the housing and
altering the black and white painted surfaces to obtain constant diffused light over
the entire data card.
2. 5 - New oblique cyclic drive to minimize operational shock vibrations on the
optical structure will bq tested week of 1 December. Report to follow.
2. 6 Mirrors currently being inspected for -necessary recoating. std.
INCORPORATE ADDITIONAL NECESSARY FEATURES
1. Remote Control
Complete pilot capability to. select and operate the camera from the cockpit in
all Patterns and modes of operation, both horizon to horizon full terrain coverage,
and selected areas vertical, left and right concentrated targets.
1, 1 Programmer Model HP8191. In production starting week of 24 November.
Final design to production week of 1 December.
1.2 New two-speed film drive motor.
1.3 New camera wire harnesses.
1.. 4 Engineering investigation is near completion on necessary changes to add
two additional selective positions to band controls Marks I and II. Rework includes
replacement of selector switch in Mirk I and. Mark II units with additional wires.
Mark III unit to be reworked to add two additional wires. Minor electrical changes
are necessary on the A/C Junction Box, A luminous decal nameplate will be pro-
vided to indicate additional. switch positions. A luminous switch pointer knob will
be provided as an added feature to the hand controls. A field service bulletin is
being prepared delineating necessary changes 'to each type,of equipmep.t although it
is recommended that rework be performed at the maxi iirer's factory. Engineer-
ing has placed orders for all .parts as switches are a term procurement item,
Service bulletin to be complete week of 8 December. All lights to be green.
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Enclosure (1)
2 December 1957
Page 5 of 5
2. Improved B material shipping assembly.
Production in process for ten experimental ruggedized shipping flange assemblies.
Evaluation continuing for simpler design.
3. Radio noise suppression (See Encl. (4-),)
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-A Stroh:
PASADENA
HYCON MFG, COMPANY
. :DURABILITY. TEST HS-732
Serial #39
PAGE.
Jo..
of. 12
REPORT:
PURPOSE To conduct a durability test of Shutter HS-732, Serial #39
TEST :CONDITIONS
Shutter was operated on the begch in. Maintenance & Overhaul shop by
Field Engineer, Gordon von Stroh,
.In the initial part of the test, the shutter was operated at runaway, Which
;s obtained by applying a continuous trip voltage to the shutter; the
interval
i
between shutter firings is 1. 1 to 1. 4 secs, depending upon the sp,6.edi of the
rewind motor. When the rewind motor has recocked, the drive springs
and latches Ore in place, arrt the shutter is immediately fired.. This; is a
more severe test than operating the shutter by intervalometer, of in. the
camera with the normal 4-1/2 sec interval between shutter firings. The.
shutter was operated at runaway at the start in order to shorten the total
elapsed time of the test. During the latter part of the test it was operated
by, Inter valometer at 28 cycles per minute.
A 1.0:, 000 cycle interval between inspections was selected as a moire rigid
test. of the shutter. Field instructions require 5, 000 cycle inspection,
lubrication and adjustment. The shutter was run continuously ford at
least 4, 000 cycles before stopping for any reason other than inspections
or end of work period in order to simulate the required minimum duty.
period as closely as possible.
A check of. the shutter speed, with test set (light source, oscilloscope,
photocell) was made periodically during the test. The measured speed
must be multiplied by 1. 2 to obtain. actual effective shutter speed. Speeds
.quoted in this report are the actual effective shutter speeds.
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r'Str
ASADENA
.HYCON MFG. COMPANY
`.-DURABILITY- TEST HS-732
Serial # 39
PACE T of 12
PURPOS TQ conduct a durability test of Shutter HS-732, Serial #39..
TE S'1'' 'CONDITIONS:
Shutter was operated on the bench in Maintenance & Overhaul shop by
Field Engineer, Gordon von Stroh.
In the initial part of the.test, the shutter was operated at runaway, which
is obtained by applying a continuous. trip voltage to the shutter; the interval
between shutter firings is 1. 1 to 1.4 secs, depending upon the speed of the
rewind motor. When the rewind motor has recocked, the drive springs
'and latches ire in place., a^t the shutter is immediately fired. This is a%
more severe test than operating the shutter by intervalometer, or in. the
camera with the normal 4-1 / 2 sec interval between shutter firings. The.:..
shutter was operated at runaway at the. start in order to shorten the total
elapsed time of the test. During the latter part of the test it was operated
by.,intervalometer at 28 cycles, per minute.
A 1.0, 000 cycle interval between inspections was selected as a more rigid
test. of the shutter. Field instructions require 5, 000 cycle inspection,
lubrication and adjustment. The shutter was run continuously for at
least 4, 000 cycles before stopping for any reason other than inspections
or end' of work period in order to simulate the required minimum duty.
period as closely as possible, .
'A check of the shutter speed, with test set (light source, oscilloscope,
photocell)' was made " periodically during the test. The measured speed
must be multiplied by 1. 2 to obtain actual effective shutter speed. Speeds
quoted in this report: are the actual effective shutter speeds.
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 I ,I I
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vacs `utroh
PREPARED $Y-
..1'214157
HYCON MFG. COMPANY
DURABILITY TEST HS-732
Serial X39
I I;
!Aaal;2.of 12
I .i.l'
I li.
REPORT
Pli'or" to the durability t ot, the shutter was operated 2, 500 cycles during
'routine quality control checking,' inspection and adjustment.
After 140, 000. cycles of testing, the, shutter was subjected to lows tempera-
turn, high altitude. operating conditions for 20, 000 cycles. i!
t
At' the st
t
f * ? te
ar
o
s
:
Runaway Rate: 52 cycles per minute
Shutter Speed: 11220 sec
Worm Gear in #2 position
TEST DATA:
"Nov. 1, 1957 Friday.
At 1:05 pm the unit was
connected to electrical test equipment containingi the
necessary switches. and cables. The trip. switch of the tester was placedi in' the
"on" position, This produces a runaway condition in the shutter. Power was,
applied.
Running time: 1:05 pm to 3:50 pm
8, 360 cycles - from 2:05 pm to 3:50 pm. Runaway rate was 50 cycles
per minute.. No malfunctions Test off for weekend. Total Cycle' 360
Nov. 4, 1957 - Monday
Test continued at $;15 am to 9:10 am
Operated at runaway at,.50'?cycles ? per minute,'
1, 640, cycles, to complete 10, 000 cYele run. `'Stopped to perform
10,.000' cycle maintenance check. At . this time the unit was again ( I!
timed, using the.photocell and oscilloscope camera., Time, 1/240 sec. ?j
r
PASADENA:
i ,II
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,tE l 2' 4-1-5.7.
PASADENA
HYCON MFG. COMPANY
DURABILITY TEST HS-732
Serial #39
CALIFORNIA
PAGI 3 of 12
A readjustment of the worm gear was made and items on the standard
maintenance and inspection list for 10, 000 cycles were checked.
Worm gear remained in #2 position. Total Cycles: 10, 000:
Nov. 4, 1957 - Monday
The unit was placed back on test at ;;:30 am
-Running time: 11:30 am to 2:35 pm
Operated at runaway rate of 54 cycles per minute.
10, 000 cycles Total Cycles: 20, 000
Nov.. 4, 1957 - Monday
The unit was subjected to a timing test, using the photocell and
equipment noted previously. Time, 1 / 240 sec. The unit was then
given a 10, 000 cycle periodic maintenance check. The unit was
placed back on test.
Running time: 3:05 pm to 5:05 pm
Operated at runaway rate of 54 cycles per minute.
6, 380.cycles. Test stopped overnight. Total Cycles: 26, 380
Nov. 5, 1957 - Tuesday
Test continued at 8:10 am
Running time: 8:10 am to 9:10 am
Operated at runaway rate of 54 cycles per minute.
3, 070 cycles to complete 10, 000 cycle run. Unit timed and sub-
jected to a 10, 000 cycle maintenance check. Time, 1/238 sec.
Total Cycles: 30, 000
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.n
closure 2
vci Stroh
PWARI I _
HYCON. MFG. COMPANY
PASADENA CALIFORNIA
PAGE .4 of 12
DA?E 1 4 ., ?
DURABILITY- TEST HS-732
Serial 039
Nov. 5, 19571 - Tuesday
:.Test continued at 10c,Z5 am
Running time: 10:25 am to 1:35 pm
Operated at runaway rate of 54 cycles per minute.
1.0,000 cycles; speed and maintenance check. Time, 1/240 sec.
Total Cycles: 40,000
Nov. 5, 1957 - Tuesday
Test continued at 2:10 pm
Running.time: 2:10 pm to 5:00 pm
Operated at runaway rate of 54 cycles per minute.
9,400 cycles. Test stopped for the night. Total Cycles 49, 400
Nov. 6, 1957 - Wednesday
Test continued at 8:05 am .
Running time: 8:05 am to 8:20 am
Operated at runaway rate of 54 cycles per minute.
600 cycles to 10, 000 check. Time, I/ 240 sec.
The ring gear carrier bearings required slight adjustment to
take up wear. Total Cycles: 50, 000
Nov. 6, 1957 - Wednesday
At 50, 000 cycles, the rewind motor was due for overhaul. The
test was deliberately continued without overhaul of the motor to
determine the 'safety factor in specific overhaul period.
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VOW ? troxi
PREPARED.iY_
CHECK BY
nT 214/ 5.7 .
PASADENA
HYCON MFG. 'COMPANY
DURABII,,ITY TEST HS- 732.
Serial #31
.Test continued at 1:25 pm
PAGE
5 of 12
(REPORT=
Running time: 1:25 pm to. 4:35 pm
Operated at runaway rate of 54 cycles per minute.
10,000 cycles; time and maintenance check. Time, i/235 sec.
Nov. 7, 1957 - Thursday
Test continued at 8:35 am
Running time: 8:35.am to 10:00 am
Operated at runaway rate of 54 cycles per minute.
i..
Total Cycles,
4, 500 cycles. Stopped test at 10:00 am due to motor dropping in
speed to, 36 cycles per. minute and overheating. Motor had. not been
overhauled at 50, 000 cycles per maintenance check list in order to
verify. this requirement. Motor M & 0 overhaul was done at this
time and worm gear changed to Position #3. Total cycles on worm
gear Position #2, 649-500.
Total Cycles:
Nov. 8, 1957 - Friday
Test continued at 9:00 am
Running time: 9:00 am to 11:00 am
Operated at runaway rate of 46 cycles per minute and at completion
of 10, 000 cycle period, had slowed to 43 cycles per minute. Removed;
unit from test and subjected it to a photographic timing test, then a
10, 000 cycle maintenance check. Minor worm gear adjustments were
made to improve motor speed. Exposure speed, 1 /240 sec:,
5.,500.cycles
Total Cycles: (70,1000
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 19.57 Friday
byc?H NRFV. COGAPANy:
Operated at runaway rate of 46 cycles per minute. Speed, 1/235 sec;
101, 000 cycles Total Cycles:
Nov. 8, 1957 - Friday
Test continued at 4:10 pm
.Running time: 4:10 pm to 4:30 pm
Operated at runaway rate of 46 cycles per minute.
'900: cycles, Test off for weekend.
cALWWO
Total Cycles:
Operated at runaway. rate of 46 cycles per minute;.slowed to 45 cycles
per. minute.
4,.200 cycles to 10, 000 cycle check. Changed worm gear; to position;
Total Cycles':
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von Stroh
PREPARED BY
C
CHECKED BY
DATE 12/4/57
PASADENA
HYCON MFG. COMPANY
DURABI~ITY TEST HS-732
Serial #39
.Nov. 12, 1957 - Tuesday
Test continued at 1:15 pm
Running time: 1:15 pm to 4:30 pm
Operated at runaway rate of 46 cycles per minute.
10, 000 cycles. Test stopped for the night and 10, 000 cycle check.
PAGE 7' of 12
' Total Cycles: 100, 000
Nov. 13, 1957 - Wednesday
Unit given 10, 000 cycle maintenance check and photographic timing
test. Speed, 1/240 sec.
Test continued at 8:30 am
Running time: 8:30 am to 9:30 am
Operated at runaway rate of 51 cycles per minute. K-2 relay contacts
began sticking, causing m1$-latching at. runaway oper.ation.,:: This con-
dition was anticipated, so unit was changed from runaway to intervalo-
meter operation, set to pulse 28 cycles per minute, and shutter con-
tinued to operate properly on intervalometer. Sticky relay was
retained to determine margin of safety and ultimate life under normal
conditons.
3, 060 cycles Total Cycles: 103, 060
Nov. 13, 1957 - Wednesday
Test continued at 10:00 am, continuing shutter on intervalometer at
28 cycles per minute.
Running time: 10:00 am to 1:30 pm
6, 940 cycles to 10, 000 cycle check and 50, 000 cycle M & 0 motor
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HYCON MFG. COMPANY
PAO' 8 of 12
DAT' 12/4/57
DURABILITY TEST HS-732
Serial #39
overhaul and worm gear adjustment. Speed, 1/235 sec.
Total Cycles: 110, 000
Nov. 13, 1957 - Wednesday
Test continued at 3:30 pm after motor overhaul.
Running time: 3:30 pmfto 4:30 pm
Shutter ran on intervalometer at 28 cycles per minute. Runaway
rate, 50 cycles per minute.
1, 680 cycles. Stopped test for the night. Total Cycles: 111,680
Nov. 14, 1957 - Thursday
Test continued at 7:50 am
Running time: 7:50 am to 12:50 pm
Shutter ran on intervalometer at 28 cycles per minute. Unit removed
from test and subjected to a timing test and 10, 000 cycle inspection.
Runaway cycling rate, 50 cycles per minute. Speed, 1/245 sec.
8,400 cycles Total Cycles: 120, 000
Nov. 14, 1957 - Thursday
Test continued at 2:00 pm
Running time: 2:00 pm to 5:00 pm
Shutter ran on intervalometer at 28 cycles per minute. Runaway
cycling rate, 50 cycles per minute. Test off for the night.
5, 060 cycles Total Cycles: 125, 060
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von Stroh
PREPARED RY
CHECKED. BY,
DATE 12/4157
DURABILITY TEST HS-732
Serial #39
PAGE 9 of 12
REPORT.
Nov. 15, 1957 - Friday
Test continued at 8:00 am
Running time: 8:00 am to 10:55 am to 10, 000 cycle check.
Shutter ran on intervalometer at 28 cycles per minute. Runaway rate,
50 cycles per minute. Speed, 1/240 sec.
4, 860 cycles Total Cycles: 130, 000
Nov.- 15, 1957 - Friday .
Teat continued at 11:30 am
Running time: 11:30 am to 4:30 pm
Shutter ran on intervalometer at 28 cycles per minute. Runaway rate,
50 cycles per minute. Test off for weekend.
8, 500 cycles Total Cycles: 138, 500
Nov. 18, 1957 - Monday
Adjusted limit switches before resuming testa
Test continued at 8:45 am
Running time: 8:45 am to 9:45 am
Stopped test to make a 10, 000 cycle check and photographic timing
test. Speed, .1/240 sec. Runaway cycling rate, 50 cycles per minute,
1, 500 cycles
Total Cycles: 140, 000
Nov. 19, 1957 - Tuesday
Conducted low temperature test in cold box.
At 8:00 am, placed unit in a cold chamber at +35?F and allowed to
stabilize for one hour. Circulating fan in dry ice chamber turned on
HYCON MFG. COMPANY
PASADENA CALIFORNIA
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L.nciosure. (2)
'von Stroh
PREPARED RY_
HYCON MFG. COMPANY
PACE 10 of 12
DATE 12/4/57
DURABILITY TEST HS-732
Serial #39
at 9:00 am and temperature dropped momentarily to -65?F. Shutter
would not operate at this temperature. Turned off fan and tempera-
ture gradually returned to +35?F. Tested shutter during warm-up
period and normal operation began at -20?F. Cold chamber stabi-
lized at +35?F and operating test started at 9:15 am.
Running time: 9:13 am to 3:15 pm continuous.
Shutter operated on intervalometer at 28 cycles per minute, at +35?F.
Runaway rate, 48 cycles per minute. Stopped test to make a 10, 000
cycle maintenance check and photographic timing test. Speed, 1/240 sec. Test off overnight.
10, 080 cycles Total Cycles: 150,080
Nov. 22, 1957 - Friday
Conducted altitude test in combination with low temperature. Packed
bell jar with dry ice and applied vacuum to simulate 40, 000 ft. altitude
at +32?F. Test continued in low pressure and cold at 9:30 am.
Running time: 9:30 am to 3:30 pm continuous.
Shutter ran on intervalometer at 28 cycles per minute, simulated
40, 000 ft. altitude and +32?F, Runaway rate, 48 cycles per minute.
Test off at 3:30 pm and unit subjected to photographic test. Speed,
1/240 sec,
9, 920 cycles Total Cycles: 160, 000
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Y. Strad '.
CHECKED ar
ATOV. 25, 1.957 Monday
CILIEORNIA
Rewind motor given 50 000 cycle overha l and worm, gear adjusted
.
PAfi~~~l Oaf" 1 ~.:
.Test continued at 3:30 pm- at ambient room .temperature and pressure..
Running time: .3:30 pm to. 4:30 piin
Shutter operated onintervaiometer. at 28 cycles per, minute Runaway
rate, 46' cycles per minute.
1, 680 cycles
Nov. 26,. 1957 - Tuesday
Test .continued at .8:00 am
Running time: 8:00. am.:to 10:30 am
PASADENA.
HYCON
DUR BILYTY "TEST RS-732
Serial; #39
Total- Cycles:, 161, 680
Shutter operated onintervalorneter at 28. cycles per minute Runaway
rate,
45
cycles. per minute. Room..ambient... At 9:00- am, 165, 860
cycles, motor slowed down, approaching 30 cycles per minute.
Stopped test at 10:30
am as unit,. required motor and gear adjustment.
4, 200 cycles Total Cycles: 165, 880,
Nov 26, 1951, - Tuesday
Test continued at.1100 am at cycling, rate of 45 cycles. per .minute
Running time: .l l :?00 am to 1:30. prri, 4, 2?Q". cycles to 10, 000 cycle
check. Shutter . operated on intervalometer at 28` cycles per, mminute.,.
.Runaway rate at end of period, 3.5 cycles per minute. Unit removed
from test and subjected to a 10, 000 cycle photographic timing test
and maintenance check. Speed, J,'/210. sec. Test . shows shutter
bounce of I M/S duration and approximately" 10% amplitude 'Wear.
Test: off for the night.
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HYCON MFG. COMPANY
DURABILITY TEST HS-732
Serial #39
REPORT
gear teeth and bearing grooves permits excess backlash. (1 /4")
ade: overlap.. No. ecdentric adjustments left :tjo compensate for
wear., Worm gear worn beyond satisfactory service, no re-adjustment
Total Cycles: 170, 000
Test ' discontinued and shutter assigned to Engineering for detailed wear
'Shutter #39' operated 170, 000 cycles without malfunction.
at least 100% safety factor.
The field instructions. to inspect and adjust every 5, 000 cycles has
The field instructions to replace the rewind motor at 50, 000 cycles
a; 30% safety factor.
The field instructions to rotate worm gear to new operating position
every 20, 000 cycles has safety factor of 20% 101011111111M ?r+rri in v
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CALIFORNIA ''WE 12 of 12
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Enclosure (3)
TO: W. A. Stewart Date: 3 December 1957
FROM: Don Moors
SUBJECT: Progress Report on the 73-B Vibration Problem
A vibration study of Configuration 73-B has been undertaken to determine
to wha extent vibration was causing image degradation, to find the source
of ima e degrading vibrations, and to investigate methods of isolation.
Vibration measuring equipment has been purchased and used. This
equipment consists of an piezo-electric type accelerometer and an
amplifier with a double integrating network incorporated in it. The output
of this equipment is displayed on an oscilloscope.
A multi-channel pickup and amplifier system is now being made up. This
system will have the capability of in-flight recording using a Century
Recorder.
Preliminary tests showed a sever-,4 transient on the lens housing due to the
shutter. Subsequently a shutter was shock mounted by relieving the shutter
housing approximately 1/32 inchM and supporting the shutter on rubber
.pads, It was found that with proper installation of this mount, the displace-
ment of the lens housing could be reduced to . 0005 of an inch during the
exposure. A subsequent flight (PTF 216) with the oblique drive locked in
vertical, position showed a definite improvement. To date, the same quality
has not been obtained with the oblique drive operating, however, ground
tests with the configuration in the airframe have shown that all transient vibrations
excited by oblique positioning are damped out before the subsequent exposure
in all modes of operation.
Measurements made on the mirror with all components operating including
the shocjc mount shutter show movements ranging from .0003 to . 0001
inches during the exposure. Measurements with the shutter disconnected
indicate no more than.00015 inch of movement. No significant change was
observed with the oblique drive disconnected. Displacement of the mirror..
appears to be slightly less at the top than at midpoint, though no conclusions
can be made as to the amount of rotation until measurements can be made
.with the multichannel recording system.
Readings taken on the structure adjacent to the take-up motors indicate
that rubber mounting of motors effectively isolates a 600 cps ripple that
seems to be responsible for much of the audio noise though there is no
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 Sanitized Copy Approved for Release 2011/08/09: CIA-RDP89B00487R000300510001-6
indication that this component is present on the optical assembly. The
accompanying table briefly summarizes the data to date.
1. The present method of shutter shock mounting is a definite
improvement, however, it is probable that more improve-
ment could be realized with a mounting system with greater
side to side compliance.
2. Rubber mounting the take-up.motor will probably not make a
significant improvement in image quality at this time. Rubber
mounting will reduce audio noise.
3. The shutter is the major displacer of the mirror.
4. Transient vibrations. excited by oblique positioning are damped out
in sufficient time.
Recommendations
1. More work on the shutter mounting:
a. Modify one lens housing to accommodate a more compliant
mounting system.
b. Ground test and flight test the modified shutter mounting.
c. Make tests to determine how the shutter transient is trans-
mitted to .the mirror and evaluate methods of isolation.
2. Make in-flight recordings to determine the frequency and amplitude
of A/C vibration.
3. Determine the resonate frequencies and modes of vibration of all optical
components.
4. Continue to investigate other causes of image degradation such as A/C,
motion.
DM/pe
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 HYCON MFG. COMPANY
PAO
FtEPARM 11Y
PASADENA
CALIFORNIA.
s
-
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CHECKED RY
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 Sanitized Copy Approved for Release 2011/08/09: CIA-RDP89B00487R000300510001-6
Enclosure (4)
Interference Tests on HR-73C Configuration
Introduction. Modifications to eliminate radio interference from
the 73C Camera have been installed in Unit #2 at the Test Site.
`rwo.flights have been made since the installation. Prior to each
'flight the pilot was briefed to. test all previously. affected equipment.
The results. indicate that radio interference was not detectable.
Purpose, of Tests. Previous operation of the 73 C Camera in flight
ntiterferre*d with the aircraft radio equipment.
Interference Sourrces. All suspected sources of radio interference
ere tested by the radio noise facilities at Cornell-Dubilier Electric
Corp., Venice- California. The frequency range was 150 KG to
X000! rneg:acycle, s. The following units were found to be prime sources;
Aperture Motor
Film Drive Motor
Fi'in Take-Up Motor
Obkfque Drive Motor
Tension Regulator Motors
?6,; Gyro Sensor.Assernbly
Switches
-,: Programmer
Mpdifications Required. The following modifications were made on
.above equipment.
Motors. Filters, shielded housings and shielded-
wire were installed. Bonding was improved.
Programmeeer., Feed-through capacitors were installed
installed in noisy lines. A shielded compartment for
the. filters and shielded wire was used.
theater relay contacts.
Gyro Sensor Assembly. R-C filters were installed across
y
R=C_;filters were installed.
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Radio Interference Tests: on HR-73.C Configuration
7?e,0 Resulte. The following tuts have been performed:
megacycles. The radio interference present was negligible.
* Cos 11~I)ubilier over the frequency range of 150 KC to 1.000
Laboratory Tests.After modification the motors were tested
b,. Ground' Systems Tests. After the modified units were installed
in Unit #2 at:the=Te Site, .the Configuration was :installed in the
article. The article 'was towed to a .remote section. of the flight
line. The Configuration was operated, for :one -half hour while
Mr. Joe Falcon, aircraft radioman, operated the radio equipment.
All radio channels . and :frequencies were checked. M.r. Falcon
reported the 'interference. was negligible.
,c. Flight~Tests. PTF 215 and?PTF 218 were used as tests. The.
pilot vas briefed to. test all radio equipment over all frequency
ranges. Glenn Pulkerson and the pilot have notified us that
.radio interference during.flight operation of the Configuration
ways :dundete stable-.
Enclosure (4)
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 Sanitized Copy Approved for Release 2011/08/09: CIA-RDP89B00487R000300510001-6
Enclosure (5)
T 0,
Ihtetim' Report '.:old.
i lk i1 i` ~ > 9 0 le ~a 2 Cs' ? x Fwi a d *i;Y e
'' - ,. .$ ~' :_ c t # i.:,, f; k' l v i ::t?.i 5., . .!"
w} it was LC3 s1iN