PHOTOGRAPHIC EVALUATION REPORT MISSION 4018 28 MAY - 1 JUNE 1965

• Document Type: CREST
• Collection: NGA Records (Formerly NIMA)
• Document Number (FOIA) /ESDN (CREST): CIA-RDP99T01396R000300250001-3
• Release Decision: RIPPUB
• Original Classification: T
• Document Page Count: 117
• Document Creation Date: December 28, 2016
• Document Release Date: March 14, 2012
• Sequence Number: 1
• Publication Date: October 1, 1965
• Content Type: REPORT

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TECHNICAL PUB TION
PHOTOGRAPH IC
EVALUATION REPORT
MISSION 4018
28 MAY - I JUNE 1965
OCTOBER 1965
COPY
125 PAGES
GROUP I EXCLUDED FROM
AU TOMA TIC DOWNGRADING
AND DECLASSIFICATION
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WARNING
This document contains information affecting the national security of the United States within the meaning
of the espionage laws U. S. Code Title 18, Sections 793 and 794. The law prohibits its transmission or
the revelation of its contents in any manner to an unauthorized person, as well as its use in any manner
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to receive Information in the designated control channels. Its security must be maintained in accordance
with regulations pertaining to TALENT-KEYHOLE Control System.
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PHOTOGRAPHIC INTERPRETATION REPORT
PHOTOGRAPHIC EVALUATION REPORT
MISSION 4018
28 MAY - I JUNE 1965
OCTOBER 1965
NATIONAL PHOTOGRAPHIC INTERPRETATION CENTER
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SYNOPSIS
GENERAL FLIGHT DATA
TABLE OF CONTENTS
Page
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PART I. CAMERA OPERATIONS 3
1. Main Camera No FM-20 3
2. Stellar Camera No s-13 5
3. Index Camera No S-13 5
4. Associated Equipment 6
PART II. FILM 7
1. Film Footage
2. Film Processing
3. Physical Film Degradations
4. Density Readings, Stellar and Index Material
PART III. IMAGE QUALITY
1. Definition of Photographic Interpretation (PI)
Suitability
2. PI Suitability for Mission 4018
3. Analysis of Resolution Targets on Mission 4018
APPENDIX A. MENSURATION
APPENDIX B. EXPERIMENTAL OPERATIONS
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TABLE OF CONTENTS (CONTINUED)
Page
APPENDIX C. SYSTEM SPECIFICATIONS
39
1. Main Camera Data
39
2. Expanded Schematic of Optical Components
40
3. Main Camera Format Dimensions
41
4. Time-Track Format
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APPENDIX D. MICRODENSITOMETRY
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1. Edge Spread Function
43
2. Edge Traces, Mission 4018
45'
3. Isodensitracer
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4. Isodensitrace, Mission 4018
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APPENDIX E. MISSION COVERAGE STATISTICS
55
1. Summary of Plottable Photographic Coverage, Mission 4018
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2. Mission Coverage Tracks
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LIST OF ILLUSTRATIONS
Figure 11 Definition of Photographic Data
Figure 2 Camera Slit Images at Rest Pgaition .
1 ? ? ?
Figure 3. Banding, Early in the Misaion .
Figure 4. Banding, Late in the Mission
Pigure 5. Stellar Camera Flare Pattern
Figure 6. 144PX Pamera Photography ? ? ? ? ? . ? ? 6c.
Figure 7. Oblique Index Camera Frame . ? ? ? ?
Figure 8. Forward Half of Stereo Pair Processed at the
Intermediate Level of Development ? 8a
Figure 9. Aft Half of Stereo Pair Processed at the Full Level
of Development
Figure 10. Result of Underdevelopment ? ? ? ? ? ? ? Sc
Page
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4p
4e
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6a.
6e
8a
Figure 1.1? Same Target, Proper Level of Development . . . . . . 8c
Figure 12. Resolution Target 20a
Figure 13. Photograph of Stereo Pair, Exposed Through Camera Slit
# ? ? ? ? . 38a
Number 1
Figure 14. Photograph of Stereo Pair, Exposed Through Camera Slit
Number 2 ? ? ? ? ? ? 38a
Figure 15. Good Quality, High Resolution Photography 1
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tISTIF IllerniktIONS (CONTINUED)
Figure 16. Imagery Degraded by Thermal Changes of the Stereo
Mirror
Figure 17.
Figure 18.
Imagery Degraded by Thermal Changes bf the Stereo
Mirror -., , .
Imagery Degraded by Thermal Changes of. the Stereo
Mirror
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Figure 19. Imagery Degraded by Thermal Changes of the Stereo
, . . ? . Mirror.and?Looper Loading Vibrations 38k
Figure 20. .38m
Figure 21.
Image Quality Example
Image Quality EXample
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SYNOPSIS
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Mission 4018, a satellite photographic reconnaissance mission,
retrograde polar orbit on 27 May 1965 at 2048Z.
a 77-inch focal length main camera and a
The mission was an overall success, accomplishing
a 5-day period. Good quality photography was
of the 3 cameras aboard. Recovery of the
made in an air catch on pass 83D.
was launched into a
The system included
stellar/index unit.
83 revolutions over
recovered from each
payload capsule was
Some frames of photography from the main camera are equal
to the best quality ever gained from this system. Experiments
involving the main camera were made intermittently throughout
the mission. Among the experiments were: exposure tests, slit
comparisons in the stereo mode, and a test designed to calculate
the influence of the ionisphere on the camera system optical
elements. The results of the mission and the experiments are
included in the text of tilj_s report.
The stellar and index cameras each recorded 2,044 frames.
A variety of anomalies resulted in problems of considerable
magnitude in the reduction of data recorded by the stellar camera.
In addition, the roll angles of the vehicle at times made it
impossible to use the stellar field for mensuration.
1
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Launch and Recovery Dates
Launch Date
Recovery Date
GENERAL FLIGHT DATA
27 May .1965/2048Z
1 June. 1965/2237Z
Orbital Parameters (Planned)
Period
Perigee
Apogee
Eccentricity
Inclination Angle
Photographic Operations
Operational
88.44 min
84.01 nm
153.36 nm
0.0086 ,
134.148- ?
44 Passes 727 Frames
5 Partial Passes* -- 19 Frames
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1. Main Camera No FM-20
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PART L CAMERA OPERATIONS
The main camera was operational throughout the mission, recording
good quality photography in each mode of camera operation. Three
operational exposure slits and a fourth slit designed for testing were
used during the mission. The slit widths are 0.0085 inches, 0.0169
inches, 0.0337 inches, and 0.1600 inches.
Image smear at the beginning and end of each frame is less than on
previous missions. The smearing at the beginning of a frame represents
the imagery exposed before the camera system overcomes inertia. The
smeared imagery at the end of a frame is caused by the camera slowing
down in preparation for stopping.
Image degradation caused by the looper loading action is present
for 4-9 inches after each 26 inches of continuous camera operation.
The image degradation resulting from the looper loading action is less
pronounced and extends over a shorter length of film on the first 50
percent of this mission than on most previous missions. However, as
the mission progressed the result of the looper loading action became
more pronounced and by the end of the mission was more severe than on
most recent missions. By pass 65D the film is severely degraded by
bands of varying density and image motion is apparent on approximately
9 inches of film following each continuous camera operation of 26 inches.
In addition to the image degradation described in the preceding
paragraph, all imagery on passes 64D and 65D is out of focus. Also, the
imagery acquired after pass 65D is variable in quality and is generally
not as acute as that which was acquired prior to pass 64D. The image
degradation is apparently the result of thermal distortion of the primary
mirror caused by the camera door being programmed to open following frame
6 of pass 63D and remain open through pass 65D. The purpose of the
"open door experiment" was to calculate the effect of the orbital
environment over an extended period of time on the camera optical system.
In addition, de-focusing experiments conducted intermittently after pass
65D introduced some intentional degradations. Imagery equal to the best
ever attained by a satellite system appears on frame 6, pass 63D; but
weather degrades the following frames of the pass. The first 11 frames
of pass 64D are also cloud covered to a large extent. However, frame
3
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12, pass 64D, is relatively clear and is highly degraded by an out-of-
focus condition. All imagery of pass 65D contains a similar degradation.
The quality of the remainder of the mission is variable. While it is
consistently better than the imagery on passes 64D and 65D, it does not
appear to be as consistently good as the photography prior to pass 64D.
There are from 3 to 5 distinct slit images at each frame line. It
appears that the camera start-up is interrupted by pronounced hesitations
in the film advance system. These slit images are more pronounced on
this mission than on most previous missions. An example of the images
is present on frame 7, pass 27D. In addition to the slit images, there
is a rectangular pattern of fog near the supply end of several frames.
It Appears near the center of the format and is approximately 0.5
inches long and 0.25 inches wide. The density of the fog is such that
it can only be detected in the absence of high contrast or heavy density
imagery. It is probably the result of a light leak in the vicinity of
the aperture plate. Frame 6, pass 36D, contains an example of the fog.
The presence of the fog does not constitute a serious degradation be-
cause it occurs at the end of a frame in the area normally degraded by
image smearing associated with the slowing of the film in preparation
for stopping.
Slit number 1 appears to have consistently provided Image quality
superior to that exposed through slits 2 or 3. The imagery exposed
through slit 4 cannot be considered in this regard because it was
used as a research experiment and was not employed in areas benefiting
from .a favorable Solar elevation. Most imagery exposed through It Was
underexposed. On the stereo pairs where one-half of the pair was
exposed through slit 1 and the other half through slit2 the frame
exposed through slit 1 was invariably better; however, this observation
does not single out the slit aperture as the cause, since it is generally
felt that the interval between the mirror position change and the exposure
of the-second half of a stereo pair is not sufficient to allow settling
of the mirror vibrations. In the experiments conducted on this mission,
the second frame of the stereo pair was always exposed through slit 2.
The effects of the slit aperture and the suspected mirror vibrations are
subtle.
Minus density streaks parallel to the major axis of the film are
continuous in conjunction with the slit being used. These streaks are
caused by foreign matter in the slit aperture. The streaks are most
pronounced and numerous on the photography exposed through slit 1.
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FIGURE 1. DisilINITION OF PHOTOGRAPHIC DATA
The data pertaining to the photographic illustrations contained
in this publication are defined as follows:
PASS: A pass is the operational portion of an orbital revolution. A
suffix D indicates that the photography was acquired during the
descending portion; a suffix A indicates that the photography was
acquired during the ascending portion; and a suffix M indicates that
the photography was acquired during a pass that includes both
ascending and descending portions. An additional suffix E indicates
that the pass was an engineering operation (no imagery detectable)
or that a portion of the photography has been edited.
DALE OF PHOTOGRAPHY: The date of photography indicates the day, month,
and year (GMT) that the photography was acquired.
UNIVERSAL GRID COORDINATES: These coordinates are included to locate the
illustrated photography within the format.
INDEX: A mark placed along the titled edge, numbered consecutively within
a pass and spaced approximately every 18 inches. It is used to
orient the Universal Grid on the photography.
ENLARGEMENT FACTOR: The enlargement factor is included to indicate the
number of diameters the original material has been enlarged in the
photographic illustration.
GEOGRAPHIC COORDINATES: These coordinates are included to indicate the
latitude and longitude of the photographic illustration.
ALLLTUDE: This measurement is the vertical distance from the vehicle to
the reference ellipsoid at the time of the acquisition of the photo-
graphy.
VEHICLE ROLL: This is the roll programmed for the acquisition of the
target.
CONE ANGLE: The angle between the principal axis of the camera optical
system and the vehicle gravity gradient vector.
TYPE OF COVERAGE: This indicates whether the photography was acquired
in the stereo or monoscopic mode.
MIRROR POSITION: The stereo mirror may be pitched to one of three positions
to produce forward, vertical, or aft looking photographs.
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SLIT NUMBER: Three operational slits were used and a fourth slit was
designed for testing. The slit widths are: (1) 0.0085 inches,
(2) 0.0169 inches, (3) 0.0337 inches, and (4) 0.1600 inches. The
slit number designates which slit was used for the exposure of the
photograph.
EXPOSURE: This is the duration of the photographic exposure expressed
in fractions of a second and is computed from the slit width and
film speed.
DEVELOPMENT LEVEL: This indicates whether the original material re-
ceived primary, intermediate, or full development.
LOCAL SUN TIME: This time is included to present to the viewer a
realistic time of the acquisition of the photography illustrated.
SOLAR ETRVATION: The angular height of the sun above a plane tangent
to the surface of the earth at the center of the photographic
format. A negative solar elevation indicates that the sun is
below the plane.
SOLAR AZIMUTH: The solar azimuth is the angular measurement of the rays
of the sun measured from true north Clockwise.
AZIMUTH OF THE REINCIPAL RAY: The angular distance of the principal ray
measured clockwise from true north.
SOLAR BEARING FROM THE PRINCIPAL RAY: The angular distance of the solar
azimuth measured clockwise from the azimuth of the principal ray.
PHOTO ORIENTATION: All photographs in this report with the exception of
Figure 3 are oriented with the title edge at the top. Figure 3 is
oriented with top toward the film supply.
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FIGURE 2. CAMERA SLIT IMAGES AT REST POSITION
This pattern of slit images appears between most
frames of the mission. The photograph also shows the
rectangular pattern of fog which appears near the supply
end of several frames.
NPIC K-5136 (10/65)
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Pass 27D
Frame 7
Date of Photography ...... . 29 May 1965
Universal Grid Coordinates . . . 55.5 - 12.0
Index. . ......... . 15
Enlargement Factor ...... . Contact
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FIGURE 3. BANDING, EARLY IN THE MISSION
Banding associated with the looper
loading action was less apparent through
the first half of the mission than the
last. See Figure 4.
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Pass 34D
Frame 1
Date of Photography 29 May 1965
Universal Grid Coordinates . . 67.0 - 12.0
Index .3
Enlargement Factor Contact
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FIGURE 4. BANDING, LATE IN THE MISSION
This photograph illustrates the image
degradation introduced by the looper loading
action late in the mission. See Figure 3.
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Pass 80D
Frame 1
Date of Photography ...... 1 June 1965
Universal Grid Coordinates . . 47.5 - 12.0
Index ..... ...... . 3
Enlargement Factor Contact
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2. Stellar Camera No S-13
This is the first mission utilizing the new stellar camera .
capable of being operated independent of the main camera and
providing a capacity of 2,500 frames.
The first frame of the mission was double exposed. Several
subsequent frames were grossly overexposed and unusable for
mensuration because the vehicle roll angle during exposure was such
that the camera lens was at an angle which allowed earth flare
to enter the lens. In addition, most stellar images are smeared
and on 8 frames are double imaged. The smearing is believed to be
caused by vehicle instability during exposure. The double images
probably are the result of a shutter bounce (shutter opening/closing
after the prescribed interval and partially opening again as a
bouncing action). The double stellar images and the image smearing
cause complications that delay the stellar reduction process; however,
these problems do not render the film useless. The minimum flare
pattern engrossed approximately 10 percent of a frame. The final
analysis of the stellar camera film revealed 833 frames with stellar
images adequate for attitude determination and 1,211 frames that
were unsuitable for attitude determination because of earth flare.
3. Index Camera No S-13
This camera is half of the stellar/index unit as described in
paragraph 2 above (providing the ability to acquire photography
either in conjunction with or independent of the main camera). This
camera also has a capacity of 2,500 frames. On this mission, as with
the stellar cameral 2,044 frames were exposed. Each frame of the
index camera correlates with (was exposed at the same time as) a
stellar frame.
The first frame is a double exposure. All subsequent frames
received relatively good exposure. The image acuity near the
center of the frames is good, but there is a distinct fall-off
toward all corners.
Newton rings are numerous throughout the mission. They
apparently occurred during exposure.
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Obstructions caused by foreign particles on the reseau plate
are present throughout the mission and increase in number as the
mission progresses. The extremely small scale of this photography
makes the presence of these obstructions particularly undesirable.
Edge fog is present at both film edges at intervals of 4o inches.
Each occurrence of the fog extends from 2 to 6 inches along the
edge and varies in width up to 0.2 inches. The presence of the
fog alternates from one edge to the other, but appears
consistently, beginning in the pre-flight, at intervals of 40
inches at each edge. The pattern of this fog suggests a film
tracking problem.
Each frame is vignetted at the camera number edge and
take-up end. The vignetting is minor and obscures only the
camera number, rendering it unreadable.
There is an emulsion scratch, approximately 0.5 inches long,
0.05 inches from and parallel to the format edge opposite the camera
number side at the supply end of each frame through frame 38. The
position of the scratch relative to the format edge is
approximately identical on each frame, suggesting that it was camera induce(
The metering is erratic through the first 25 percent of the mission.
The space between frames varies from 0.15 to 0.85 inches. There
were no instances of overlapping exposures. The metering on the
last 75 percent of the mission is reasonable and consistent.
4. Associated Equipment
The time track is distinct and readable throughout the mission.
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FIGURE 5. STELLAR CAMERA FLARE PATTERN
This photograph was made from a negative
not degraded by roll angle. The flare pattern
here is typical throughout the mission.
NPIC K-5139 (10/65)
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Frame. . . 163
Date of Photography. . . 28 May 1965
Enlargement Factor . . . 6x
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Declassified in Part - Sanitized Copy Approved for
? Trin errnrT ni irr
Release 2012/03/14:
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CIA-RDP99T01396R000300250001-3 5X1
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CIA-RDP99T01396R000300250001-3
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!Ur StLKt1 Kat'
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FIGURE 6. INDEX CAMERA PHOTOGRAPHY
This is a typical index camera frame
of this mission. Note the vignetting.
NPIC K-5140 (10/65)
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Frame 270
Date of Photography 28 May 1965
Enlargement Factor 2.5X
I ?
1
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Declassified
111
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Tnn crrnrT ni irr
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541,411.,:cr,
0270
4018 28 MAY 65
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101' StLKLI KUIt
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FIGURE 7. OBLIQUE INDEX CAMERA FRAME
The quality of this frame is typical
of the index photography of this mission
in a roll attitude.
NPIC K-5141 (10/65) '
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Frame 448
Date of Photography 28 May 1965
Enlargement Factor 2.5X 11_
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1. Film Footage
for Release 2012/03/14: CIA-RDP99T01396R000300250001-3
Z5X1
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PART fl. FILM.
Main Stellar Index
Camera Camera Camera
Total Footage Processed 2,965 258 504
Total Frames 841 2,044 2,044
Of the main camera film recovered, 213 feet is pre-flight,
2,589 feet operational, and 163 feet runout.
2. Film Processing
The film of the main camera was processed in the Yardleigh
processor. The processor functioned well according to its
design and the density of the negatives with respect to the level
of process was good. On 12 frames the infrared densitometer of
the Yardleigh dictated a change in process within the format.
This is not an anomaly but rather a design characteristic of the
machine. Frame 1, pass 34D, is an example of a frame which
received all 3 possible levels of development.
A major processing error is apparent in frame 8, pass 58D.
It is one-half of a stereo pair and was processed at the primary
level. The other half of the stereo pair (frame 9) was processed at
the full level of development. Frame 8 is grossly underdeveloped,
while frame 9 received the proper development.
Most processing changes are within 0.7 inches of ?the frame
division, resulting in no degradation to the imagery.
Following are the number of frames processed at each level
of development: ,
Primary
226
Intermediate
72
Full
531
-7-
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11
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Twelve frames received more than one level of development.
A splice used to attach the stellar camera thread-up to the
mission film was not detected in the inspection procedure prior to
development and subsequently separated in the processing machine,
necessitating a processor cut between frames 725/726. As a
result, 21 frames are degraded by static fog, abrasions and
chemical fog.
3. Physical Film Degradations
a. Main Camera Film - The film of the main camera is severely
scratched and abraded intermittently from head to tail. A great
majority of this damage has been inflicted since processing. The
film was inspected immediately after processing and only minor
random emulsion abrasions were detected. It is obvious from the
physical condition of the film that it is being improperly handled.
In addition to the scratches and abrasions, there is foreign
matter adhering to the surface of the film on several frames. The
magnitude of the foreign particles is such that valuable terrain
imagery is obscured. Frame 15, pass 56D, is an example of a frame
containing foreign particles imbedded in the emulsion. Chemical
stains appear randomly throughout the mission. The stains are
pink and are probably associated with film handling rather than
processing. For instance, the stains on frames 8 and 10, pass 10D,
have the configuration of fingerprints.
b. Stellar Camera Film - In the vicinity of frames 725/726
where a processing cut was made because a splice separated in
processing, there is a variety of physical degradations as
described in the processing section of this report. Frames 1290
through 1299 contain heavy fog induced by dendritic static
discharges. Minor fog due to dendritic static discharges appears
at the camera number edge of frames 704/705.
c. Index Camera - Edge fog, which is suspected to have been
caused by mistracking in the camera, appears at intervals of 40
inches along both edges throughout the mission (refer to Part I.
Camera Operation). An emulsion scratch on each of the first
38 frames of the mission is also thought to be camera induced and
is described in the aforementioned section. The physical condition
of the film is good.
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2 5X 1
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11
FIGURE 8. FORWARD HALF OF STEREO PAIR PROCESSED AT THE INTERMEDIATE
LEVEL OF DEVELOPMENT
FIGURE 9. AFT HALF OF STEREO PAIR PROCESSED AT TEE FULL LEVEL OF
DEVELOPMENT
The following 2 photographs were made from negatives
of a stereo pair which were processed at different levels
of development.
NPIC K-5142 (10/65) NP1C K-5143 (10/65)
1
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FIGURE 8
CIA-RDP99T01396R000300250001-3 RY1
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?
Pass 75D
Frame 21
Date of Photography 1 June 1965
Universal Grid Coordinates 52.2 - 11.3
Index 48
Enlargement Factor 40X
Geographic Coordinates 12-13N 013-07E
Altitude (nm) 88 1
Vehicle Roll (Planned) -9 2?
Cone Angle (Planned) 16 00
Type of Coverage Stereo
Mirror Position 1IIATD
Slit Number 1
Exposure 1/398 sec
Development Level Intermediate
Local Sun Time 1121
Solar Elevation 77 3?
Solar Azimuth . . . . . 38.1?
Azimuth of Principal Ray 26 2?
Solar Bearing from Principal Ray. . . . 348.1?
Pitch 14.9567?
Yaw 3.4626?
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- 8h
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Sanitized Copy Approved for Release 2012/03/14:
FIGURE 9
75D
22
1 June 1965
51.3 - 5.6
50
4ox
12-06N o13-04E
88.3
9.2?
15.7?
Stereo
1 AFT
1
1/398 sec
Full
1121
77.2?
38.2?
164.9?
126.7?
-14:663205?
-3460
CIA-RDP99T01396R000300250001-3
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?
-rnn crrnr-r ni irr
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1
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1
Declassified
I
Trm crrnr-r ni irr
in Part - Sanitized Copy Approved for Release 2012/03/14: CIA-RDP99T01396R000300250001-3 5X1
25X1
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Declassified in Part- Sanitized Copy Approved forRelease2012/03/14 :
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1
1
FIGURE 10. RESULT OF UNDERDEVELOPMENT
CIA-RDP99T01396R000300250001-3sil
from
the
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FIGURE 11. SAME TARGET PROPER LEVEL OF DEVELOPMENT
Figure 10, the first half of the stereo pair, was made
a negative processed at the primary level of development. Figure
11, displaying much better image quality, is the other half of
stereo pair and was made from a negative processed at the full
level of development. The cause of this processing anomaly is not
apparent.
NPIC K-5144 (10/65) NPIC K-5145 (10/65)
- 8c -
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TOP SECRET RUFF
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FIGURE 10
1
FIGURE 11
Pass
Frame
Date of Photography
Universal Grid Coordinates
Index
Enlargement Factor
56D
8
31 May 1965
55 5 - 13.0
12
Contact
56D
9
31 May 1965
50.5 - 11.0
14
Contact
Geographic Coordinates
57-13N 085-45E
57-17N o85-44E
Altitude (nm)
85 6
85.4
Vehicle Roll (Planned)
24 10
24.1?
Cone Angle (Planned)
29 8?
29.7?
Type of Coverage
Stereo
Stereo
Mirror Position
1 FWD
1 AFT
Slit Number
1
1
Exposure
1/371 sec
1/367 sec
Development Level
Primary
Full
Local Sun Time
1201
1202
Solar Elevation
54 70
54.6?
Solar Azimuth
181.49
181.5?
Azimuth of Principal Ray
312.5?
250.8?
Solar Bearing from Principal Ray.
228.9?
69.3?
Pitch
14 9567?
-14.63050
Yaw
-2 009419
-2.0094?
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Sanitized Copy Approved for Release 2012/03/14:
CIA-RDP99T01396R000300250001-3
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Trin crrnrT ni in-
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2
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Tnn crrnrT ri trr
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with an ET 20 attachment and 0.5 millimeter aperture and are
presented here in the interest of further analysis.
4. Density Readings, Stellar/Index Material
They were made with a McBeth QuantaLog Densitometer model EP1000
last frame of each operational pass of the stellar/index camera.
The following density readings were made from the first and
IUP St(.1