HIGH ACUITY RECONNAISSANCE

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP74B00752R000100090001-6
• Release Decision: RIPPUB
• Original Classification: K
• Document Page Count: 75
• Document Creation Date: December 22, 2016
• Document Release Date: December 13, 2010
• Sequence Number: 1
• Publication Date: March 2, 1959
• Content Type: REPORT

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D.MANSE PRODUCTS DIVISION
Fairchild Camera and Instrument Corporation
Robbins Lane, Syosset, New York
HIGH ACUITY RECONNAISSANCE
SME -CA-81B
2 March 1959
COPY 14- OF 5---
G-U
eon/ 44.
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
ABSTRACT
Presentation of a maximum information content reconnaissance
system for use at an altitude of and a vehicle velocity
of Mach 4.
The system works in both the visual and far infra-red portions
of the electramegnetic spectrum. The system is limited only by the
vehicle characteristics, space and weight considerations. Use is
made of the most advanced techniques and designs. Recommendations
are made for a complete system including the primary camera,
auxiliary cameras, infra-red sensor, and ground support equipment.
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
TABLE OF CONTENTS
Page No.
Title Page Unnumbered
Abstract
Table of Contents II thru III
Section I Introduction I-1 thru 1-2
Section II Basic Design Configuration II-1 thru II-11
Primary Camera II-1
Secondary Camera 11-3
Alternate Secondary Camera II-4
Camera Coverage 11-5
General Design Discussion 11-5
Rejected Configurations II-10
Section III Lens Selection III-1 thru III-4
Primary Lens III-1
Mapping Lens 111-3
Lenses for 6" & 12" Cameras 111-4
Section IV Film Emulsion IV-1 thru IV-2
Section V Image Motion V-1 thru V-3
f Section VI Exposure V1-1 thru VI-2
Section VII Film Capacity VII-1 thru VII-2
Section VIII Effects of Shockwave, Boundary
Layer and Window.Design
Section IX Environmental Considerations
Section X
Auxiliary Airborne Equipment
Velocity 8c Altitude Consideration X-1
Automatic Exposure Control X-2
Data .Recording X-2
Camera Control System X-3
ii
VIII-1 thru VIII-2
IX-1
X-1 thru X-3
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DEFENSE PRODUCTS DIVISION Pi?oposal No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
Section XI
Section XII
TABLE OF CONTENTS (Cont'd)
Ground Support Equipment
Test .Equipment XI-1
Film Processing XI-1
Obtaining QuantitativeInformation XI-1
Panoramic Photo Restitutor XI-5
Dual Mapping Camera XI-6
Page No.
XI-1 thru XI-6
Infrared Sensors 'XII-1 thru XII-7
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
SECTION I
INTRODUCTION
This proposal presents design data and recommendations for a
photo reconnaissance system for a manned aircraft to operate at an
altitude of
and velocity of Mach 4. The data presented
describes a system which will give the maximum information content
compatible with the space and weight limitations of the vehicle.
The philosophical approach has been directed toward a system which
will satisfy the three basic reconnaissancecquestions:
1. Is there anything there?
2. What is it?
3. Where is it?
and toward a system which follows good reconnaissance practice,
is reliable, and which will take advantage of all the latest develop-
ments in the state of the art.
This proposal follows and supersedes the preliminary technical
notes submitted by. Fairchild in Reports No. SME-CA-81 and SME-CA-81A,
dated 1 February 1959 and 18 February 1959, respectively.
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
.Fairchild Camera and Instrument -Corporation 2 March 1959
The system presented is the result of much detailed study
on both camera design potentials and possible application to the
vehicle configuration.
The basic system comprising a primary camera and seconridry
camera is described and discussed in detail in the following
sections.
As a possible adjunct for augmentation of information, the
inclusion of an infra-red reconnaissance sensor is presented and
discussed briefly in the final section..
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
.Fairchild Camera and Instrument Corporation 2 March 1959
SECTION II
BASIC DESIGN CONFIGURATION
The two major requirements of this system, maximum information
capacity and maximum reliability, Fairchild is of the opinion will
be best satisfied by providing a dual photographic capability. In
.Figure 1 is shown a simplified sketch of how this may be attained
within the space limitations imposed by present thinking with
regard to the vehicle design. To the right in this figure is seen
a high acuity long focal length, panoramic camera of the chimney
type; while to the left, a short focal length dual mapping camera.
While Fairchild feels this combination is to be preferred, alternative
arrangements are also presented which may be more desirable when
the primary sensor in the system is other than photographic in nature.
Primary Camera
That the high acuity element should be a panoramic camera is
reasonably obvious when one considers the angular field of coverage
that is required. Any attempt to utilize a conventional single frame
camera to achieve the same level of performance would require lens
characteristics which the optical art cannot provide. The panoramic
approach overcomes this difficulty by effectively operating only in
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
the vicinity of the optical axis of the lens where superlative
imagery can be attained. Of the many types of panoramic systems
which have been devised, the chimney type will inherently permit the
highest degree of photographic acuity. The most significant reason
for this lies in the fact that there is no synchronizing requirement.
between lens and film motions during .scan other than that required
for forward movement compensation. As the lens rotates about its
nodal point, the image is stationary and there is no image motion
relative to the stationary film located in the focal plane arc. In
all other types of scanning panoramic cameras, there is a synchronized
motion required either between certain optical elements or between
the image motion and the film motion. The chimney type panoramic
proposed is quite similar to. that of a current development by
Fairchild. The film handling reliability is extremely high and
many of the detailed problems relative to performance capability
have been worked out. For the abovereaSons, together with wide
associated experience in this field, Fairchild considers maximum
information capacity over large angular fields can be attained
only with a chimney type panoramic. A camera of this type with a
lens made to the Baker high acuity design, currently being built
for Fairchild as part of the Air Force High Acuity Camera System,
offers the maximum potential in intelligence gathering capacity.
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DUkNSE PRODUCTS DIVISION Proposal No. SCA-8IB
Fairchild Camera and Instrument Corporation. 2 March 1959
Secondary Camera
In conjunction with the panoramic unit, it is proposed to
include a dual mapping camera arrangement in a split vertical
installation. The purpose of this part of the system is to provide
information for accurate topographic analysis which cannot easily
be obtained from a panoramic view considering that the system
platform can never be perfectly stable. As all elements in the
field of a panoramic camera are not exposed simultaneously, there
will be of necessity some angular shift of the selected control
points which will be generally an unknown function of the position
of the control points in the field. In a single frame camera, such
motion will affect all points equally. As a result, the inclusion
of the supplementary mapping camera is essential to insure maximum
acCuracy in the precise location of ground points. In addition,
of course, this part of the system will provide a certain amount of
redundancy in information which is desirable from the standpoint
of reliability. The statements made previously, with regard to the
use of a single-frame camera to obtain high level of performance
over a wide angle, still apply. As a result, it is felt that the
use of two such cameras, each covering half the angular field, is
the best compromise with due regard to space limitations imposed
by the vehicle.- This dual arrangement will permit accurate wide
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-8Th
Fairchild Camera and Instrument Corporation 2 March 1959
angle coverage mapping capability utilizing existing ground sup-
port equipment for photogrammetric analysis.
Alternate Secondary Cameras
While Fairchild feels that for cartographic and geodetic reasons
the supplementary camera system should take the form of a dual map-
ping camera, it is recognized that for installations in which the
primary sensor is not the 18-inch high acuity panoramic, higher in-
formation capacity may be desired of this secondary camera than is
possible with the dual mapping cameras. Consequently, there is
illustrated, in Figure 2A, a configuration employing a 6-inch
focal length chimney type panoramic camera, in place of the dual
mapping unit. This camera will utilize 70MM film and scan through
an angle oe 1100 with film capacity sufficient for complete photo-
graphic coverage of the misSion. The lens will be of the same
degree of optical excellence as that in the primary 18-inch sensor
and will provide the same information gathering capacity, except as
limited by the shorter focal length. In Figure 2B is shown a fur-
ther alternative arrangement employing a I2-inch auxillary chimney
type panoramic for installations in which the volume occupied by the
primary sensor permits. This camera will use 70MM thin base film
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
and cover a scan angle of 900. The, performance of this unit
will be similar to the 6 inch discussed above with the exception
of increased acuity resulting from the longer focal length.
Camera Coverage
The proposed camera system provides a capability of
stereoscopic photographic coverage in a single mission of about
146,000 square miles with the primary camera, about 186,000
square miles with the alternate 6" panoramic, about 134,000
square miles with the 12" panoramic and about :05,000 square
miles with the dual mapping camera installation. Since no
specific mission or flight plan is considered, these values are
given for a continuously operating unit in a condition of straight
and level flight.
The coverage of a single exposute made by each of the
cameras is shown in Figure 3 with ground distances indicated
in statute miles.
General Design Discussion
Additional details of the preferred photographic subsystem
of Figure 1 are shown in Figure 2. Because of the compartment
space and size, it has been found necessary in this configuration
to make certain compromises. For example, an initial attempt was
made to provide a 24 inch focal length chimney type panoramic
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
camera using the Baker 24 inch f4.0 Apochromat High Acuity
Lens. This lens is fully developed and in the final phases
of fabrication. It was determined, however, that even with
5 inch thin base film, the compartment could not permit in-
stallation of 26 inch diameter spools required for the total
operating time of one hour and forty minutes. It should be
pointed out that, while the acuity of the system may be
slightly decreased with the shorter focal length, there are
some concommitant advantages. The most important of these
is that, with the same percentage overlap of successive
frames, the photographic base line is larger thus enabling
more accurate determination of heights by stereo techniques.
After some disucssion with Dr. Baker with respect to his
lens, it was decided that an 18 inch focal length chimney type
panoramic camera was the best compromise. The proposed camera,
therefore, incorporates a scaled down version of the 24 inch
f4.0 Baker lens and provides the same high acuity characteristics
as presently exist. This is true because the coverage capability
of the 24 inch lens is the diagonal of a 4-1/2" by 4-1/2" format
whereas the requirement for the 18 inch lens will be an approximate
4-1/2" slit length. Hence, the configuration dhows an 18 inch
focal length chimney type panoramic camera with 90' total field
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
.Fairchild Camera and Instrument Corporation 2 March 1959
coverage on 5 inch thin base film. This camera is installed
in a htrizontal position in the compartment with a fixed 45?
mirror in front of the lens. Again, because of space limita-
tions, the film spools cannot be oriented in the same plane
as the focal plane arc of the camera. However, recent exper-
ience with film handling in a similar application utilizing
skewed rollers to provide necessary film plane transition has
been highly successful. Another reliable way of changing film
plane direction is to provide loose loop transition by metering
the film, with a loop sensor, at both ends of the loop.
It can .be seen from the configuration that the supply and
take-up spools use the space-sharing technique in order to provide
the required capacity for the entire operating time specified.
This technique also has been successfully implemented by Fairchild
on previous panoramica camera development programs. It is possible
to avoid .the space sharing if the spool axes are rotated to
arbitrary angles compatible with the configuration. This as well
as other possibilities would be investigated during the initial
phase of the program and discussion with the vehicle designers.
Forward Motion Compensation for a chimney type panoramic
camera can be readily accomplished by moving the lens perpendicular
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
to the scan direction. A follower on the lens, at some radius from
the nodal point of rotation, drives the lens in conjunction with a
fixed flat plate tilted at the appropriate angle. For variations
in forward motion compensation the scan rate can be proportionate,
thereby permitting forward motion compensation in its simplest.and
most accurate form. To cope with any yaw compensation, the flat
plate need only be rotated through the required angle in conjunction
with the 45? mirror. This will provide theoretically perfect for-
ward motion compensation for the yaw angle and cause only a slight
amount of unbalanced ground coverage from the ground track nadir
line.
Illustrative of the need for analyzing proposed configuration
in intimate detail, one can consider the question of how the -film
should be positioned in the oscillating lens, stationary film
panoramic camera. The film may either be located on a cylindrical
surface concentric with the axis of rotation, or may be positioned
by locating rollers so as to be normal to the lens axis during ex-
posure. If the exposing slit were infinitely narrow, there would be
no difference in these two arrangements. However, as the slit must
have finite width and the camera lens is designed with a flat focal
plane because of the practical difficulty of warping film to fit a
spherical surface, the pros and cons of each mist be considered. In the
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
cylindrical.film approach, there is no image motion but the
image does not remain in exact focus during exposure. In the
second, the image remains in focus but there exists some
relative motion between lens and image.durip.g exposure.
Analysis of the two configurations shows that the out-of-focus
effect of the first varies as the square of angular width of
the slit while the relative motion in the second varies as the
cube of this angle. Since the angular width of the slit is small,
it is found that there is approximately 4 times more potential
image degradation in the cylindrical film approach than in the flat
film arrangement. It should be pointed out that the acutal amount
of degradation is so small for either case as to be insignificant
except for high acuity systems.
The dual mapping camera system will use the Baker 3" focal
length lens on a 4-1/2" by 4-1/2" format with synchronized between-
the-lens type shutters, the synchronization of exposure being a
basic requirement of modern photogrammetric analysis to be made on
the resulting pictures. Because of the basic mission required of
these cameras and their relatively short focal length, these cameras
will not be provided with forward motion compensation. The same 5"
thin base film that is used. in the main camera system will also be
used. Fairchild has developed dual mapping cameras recently that
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
have proven to be excellent for mapping and charting purposes.
Since the configuration is limited in space, use of this dual
camera arrangement is an excellent solution which provides wide
angular coverage with no compromise of conventional mapping
techniques.
The performance of the proposed basic system under optimum
atmospheric conditions using Eastman SO-1213 (or equivalent)
emulsion on a thin base will be 2 foot ground resolution for the
panoramic camera and 20 seconds angular accuracy for the mapping
component.
Rejected Configurttions
During preliminary consideration of other possible approaches
particular attention was given to panoramic systems utilizing a
double-dove prism. It was determined that, aside from severe synch-
ronization problems, this type of camera would necessitate an
impossibly close control of the ambient temperature in order to
deliver high acuity performance. Assuming an 18" 04 lens, the
acutal glass path through which the light must travel in a double-
dove scanning prism will be approximately seven inches, if the
aperture is not restricted. Consider the case where the camera
is looking straight down and both halves of the prism are being
used equally. If a temperature difference exists between the two
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
halves, the original wave front will be divided into two parts
between which there will be a phase difference caused by the dif-
ference in optical path. For this to be negligible, the Rayleigh
criterion states that the difference should be less than one-quarter
wave,
Optical path difference = 7An
or n tr. 10-6
where An is the change in index caused by temperature. A
reasonable value for the coefficient of index of refraction change
with temperature is 10-5 per degree C, with the result that the
temperature of the two halves should not vary by more than 0.10C.
To maintain the temperature of the prism to such a degree would
appear to be a practical impossibility. As a result, the double-dove
configuration was dropped from further consideration.
Other types of panoramic cameras, such as nodding lens, nodding
mirror and traveling lens with mirror or prism were investigated to
determine if there were system advantages. These types were dropped,
however, primarily due to lower dynamic information content resulting
from practical limitations or synchronization.
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IN /A/ 49 0 VV _
-? a --a_
--
!
--
900
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.1.-ote: Approximately
_3"_allowed all around
for will thickness_
71. _5? C A/ / V R
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Ul'IT
? Panoramic C'mera (:ncl. mirror)
Film (Panoramic Camera)
Dual Mapping Camera 30c, each
Film (Dual :lapping Camera) 5#
Junction rex
Timer (Crystal Oscillator)
ER Ecanter aidPecurder
!asc. (Wiring etc.
Gyro
Gyro Power Supply
Horizontal Scan System
PRIMARY CAMERA
format size 4-1/2 x 28-1/4" Ict
Film Footage 6,000 feet
spool Diameter 20 inches.
Lateral Coverage 90?
fore & Aft Coverage 1)4-1/4?
Window Size 11 x 44 incl.cs
?,?
2;'(//9Z 4-7/9/','//1/ G C/9/3e7e-A7/9
?
WEIGHT
6j
63
x2 60
each x 2 10
0
60
10
2D3 lbs.
Sub Total
15
It
Total 318 lbs.
DUAL MAPPING CAMERA
Format size 4-1/2" x
Film 200 feet (each camera)
Lateral coverage 12)4?
Fore aft coverae 74?
Window size 16 x 17 inches.
74 "
0 7.I
./4"./.. 6 v.? E 2
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GROUND COVERAGE OF CAMERAS
All dimensions given in statute miles
1. Primary Camera
18" rook' length
5" film width
90* lateral x 14-1/4? fore & aft
4-1/2" x 28-1/4" format
2. Dual Mapping Camera
3" focal length
5" film width
124" lateral x 74? fore & aft
x 4-1/2" format (each camera
r - ?
3. 6" Alternate Camera
6" focal length
70mm film width 11.1i
110" lateral x 21? fore I
& aft I
2-1/4" x 11-3/4"
format
4. 12" Alternate Camera
12" focal length
70ma film width
90? lateral x 10-3/4'fore & aft
2-1/4" x 19" format
4.25
34
-
1
120.81
I I
6.4
1,2
48.6
3.2
34
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
SECTION III
_LENS SELECTION
Primary Lens
The choice of lens for any optical system must be based
on consideration of the fact that the lens is but one element
in a cascaded system. The mathematical analysisiof cascaded
optical systems is well developed at the present time and may
be used to select the lens for a particular application. The
exact formulation of the analysis simply requires knowledge
of the equivalent line spread functions of the various elements
which are then convoluted and a Fourier transform made. The
resulting Fourier transform has physical significance in that
it is the actual frequency response curve of the overall system.
Utilizing this approach to determine the characteristics
desired of the lens in a maximum acuity system, one finds that
the ultimate in aerial image resolving power is not so impor-
tant as the contrast with which images of larger dimensions are
produced. In order that the lens exhibit the maximum values of
response., it is necessary that image defects caused by aberrations
be eliminated to the greatest degree possible so that the undulatory
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
nature of light will alone limit the perfection of imagery.
Until recently this goal was attainable with lenses of
significant aperture only over extremely small angular fields.
However, utilizing the latest techniques in optical design and
the aspherizing of surfaces, Dr. James G. Baker has succeeded
in designing an f/4, 24 inch focal length lens which is
diffraction limited over a 4-1/2 inch by 4-1/2 inch field.
Consequently, it is proposed for this system of which the
maximum in information capacity is required. This lens in an
18 inch f/4 version will resolve in excess of 200 lines/mm
high contrast and over 100 lines/mm, low contrast, 2:1 ratio,
on Kodak emulsion SO-1213.
Relevant to the use of such a lens is Fairchild's solution
to the problem of maintaining high acuity cameras in focus even
though the ambient pressure and temperature change. As is well
known, the focal setting of a camera is a function of temperature
and air pressure because of the variation of the relative index
of refraction of glass and air and the thremal expansion and
contraction of the metal components of the lens assembly and
camera. The functional relationship must be found experiment-
ally with considerable difficulty and may vary between cameras of
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DEFENSE PRODUCTS DIWSION Proposal No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959 ?
identical de4gn and construction. As a result Fairchild has
developed for high acuity cameras an automatic focusing
technique basecloon auto collimation through the camera lens.
An illuminated grid of alternate opaque and transparent lines
in the focal plane, but outside the format, of the camera is
imaged by the camera lens and dichroic mirror so as to fall
on a similar grid also in the focal plane. Behind this second
grid there is a photocell which produces an output signal when
either grid is moved in the focal plane. The focal plane of
the lens is automatically shifted, either by translating the
lens along its axis or by changing the optical path by moveable
wedges, until the phototube signal is a maximum indicating correct
focus. The dichroic mirror permits the automatic focusing to be
usable with infra-red so as not to affect the photographic trans-
mission of the camera.
Mapping Lens
For the dual mapping cameras the proposed lens is a newly
designed 3" f5.5 Precision Mapping lens of exceptionally low
distortion characteristics and extremely high photographic per-
formance. On the proposed film emulsion (S0-1215). This lens
will have resolution capabilities of the order of 60 lines/mm
AWAR with image quality very much superior to existing mapping
lens designs.
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DEFENSE PRODUCTS DIVISION Proposal No., SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
Lenses for 6" and 12" Auxiliary Cameras
The proposed lens for the 12" auxiliary camera will be
a further miniaturization of the High Acuity lens used in
the primary camera or slight modifications of this design
retaining the same performance. In the case of the 6"
auxiliary camera a :mew lens design is anticipated to
utilize the latest state-of-the-art towards making this a
high acuity system consistent with the mission to be performed.
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
SECTION IV
FILM EMULSION
As the film is but another element in the overall system,
the comments made concerning the selection of the lens in the
previous selection will apply. In this matter one must seek
the solution which will provide maximum acutance within the
exposure limitations imposed by the lens aperture, target
luminance and imperfections in compensation for image motinn.
Analyzing the problem from this point of view, Fairchild has
decided that the film emulsion, currently available, providing
the optimum solution is Eastman Kodak S0-1213 or equivalent.
Emulsions of this type have resolution capabilities in excess
of 200 lines/mm at an ASA Exposure Index of approximately 12.
This exposure index value will be considered in greater detail
in Section VT.; where exposure factors are discussed. Certainly,
in view of advances which have been made in recent years in the
quality of aerial emulsions, one can expect that further improve-
ment will occur in the near future. The actual magnitude of
improvement cannot be specified but it will no doubt be in the
direction of increasing acutance without significant loss in
emulsion sensitivity. Considering the elapsed time before any
IV-1
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DEFENSE PRODUCTS DIVISION . Propesal No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
system becomes operational, it is almost a certainty that an
improved emulsion will become available for this system.
This is greatly to be desired as the emulsion is one of the
poorer elements in the system with regard to its effect on
performance and any increase in its performance will immediately
result in increased system capability.
IV-2
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r
_
1
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
Fairchild Camera and Instrquent Corporation 2 March 1959
SECTION V
IMAGE MOTION
Any relative motion between the image and the photo-
graphic emulsion during exposure will result in degradation of
system performance because of the resulting blur. In general,
the relative motion can be divided into three parts. The first
arises from improper synchronization with the scan motion; the
second, from platform angular instability; and the third, from
the forward motion of the vehicle. The first source of error
has been shown to be eliminated by the choice of the chimney-
type panoramic design. With regard to the second, it is under-
stood that the inherent steadiness of the vehicle is such that
the obtainable ground resolution can be preserved for a satis-
factorily high percentage of the time of flight without a
stabilization mount. This is highly desirable as compensation
for vehicle instability usually is one of the most significant
design factors. Figure 4 shows the critical dependency of obtain-
able ground resolution on angular rates of motion of the vehicle
about horizontal axes. The "starting resolution" values, shown
at the lowest angular rates, are considered obtainable from
the system proposed in these notes. As a result, forward motion
of the vehicle remains as the sole significant source of image
motion.
V - 1
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81R
Fairchild Camera and Instrument Corporation 18 February 1959
In order to track an image (Image Motion Compensation)
with a fixed direction of translation of the lens or film, it
is necessary for the image also to be in translation with an es-
sentially uniform velocity over the format. Coincidence of the
image velocity vector with the image velocity resulting from
lens translation is assured by setting the IMC,direction, shown
in Figure 5, into the plane passing through the ground track.
This can be done by means of rotating the mirror and the lens
translation cam through the "crab" angle as described later
in these notes. It is, however, necessary to provide the camera
with two kinds of information, namely (1) the "crab" angle and
(2) the ratio of vehicle velocity to altitude.
In the case where the vehicle has a self contained navi-
gation system (for navigation over the earth's surface), or
where it can have this information telemetered to it, a simple
computer will serve to convert the relative ground velocity and
altitude to the ratio required as on electrical signal to control
the image motion compensation mechanisms. Further, if the "crab"
angle (i.e. the angle between the relative ground velocity and the
vehicle symmetry axis projected onto the horizontal plane) is
available it can be transformed through the use of a servo to the
combined mirror and cam angular position. If altitude informa-
V - 2
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
Fairchild-Camera and Instrument Corporation 18 February 1959
tion is not available horizon sensors can be used to determine
the earth's included angle with computation to establish altitude.
This is a new and useful technique for high altitude vehicles which
is incorporated in other developments in which Fairchild is engaged.
In the event that the craft flies an accurately known course
then it would be possible to program the angle and the lens scan
rates prior to takeoff or launch. This would be the lightest and
simplest means of establishing the vector velocity to altitude
ratio. Its use is dependent upon the known accuracy of the flight
path, altitude and velocity.
The geometrical formulae which evaluate the blur, in terms
of the pertinent stabilization and steadiness accuracies are
presented in Figures 6 and 7. The mathematical analysis shows
that for the longest exposure time (1/500 sec.) a resolution per-
formance of 100 lines/mm low contrast requires that the rates of
roll, pitch, yaw of the camera should be held to the limits indi-
cated below.
Roll, Pitch, Yaw Rates 5 Minutes of arc/second
Roll, Pitch, Azimuth Angles 1.4 Degrees
Image Motion Compensation Accuracy 2%
V -3
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EFFECT OF VEHICLE ,STABILITY
for 18" focal length .1/500 & 1/1000 sec. exposure
t1/44;
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Sanitized Copy Approved for Release 2010/12/13: CIA-RDP74B00752R000100090001-6
ef.e. "rAit:s.9 k
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6CjIWEIR:c: RELATiON
AZIMUTH
q-opric,
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FIGURE
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OPTIC
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Sanitized Copy Approved for Release 2010/12/13: CIA-RDP74B00752R000100090001-6
BLit?, F.
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Sanitized Copy Approved for Release 2010/12/13: CIA-RDP74B00752R000100090001-6
DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
SECTION VI
EXPOSURE
In general exposure depends upon the major factors of
scene brightness and brightness ratio at the camera, the
spectral distribution of the image-forming light, film
sensitivity, shutter speed, aperture, film processing, time
of day, month of year and cloud cover.
An investigation has been made into the limitations
which would be placed on the operational use of the system
as a function of the anticipated shutter speeds. The results
are shown in Figure 8 which indicates that with certain other
conditions stated (as in the figure) photography is improbable
only at the higher latitudes during the winter months.
It is to be noted that the curves of Figure 8 are based
on an Exposure Index of approximately 12, which is correct for
optimum conditions of atmospheric haze. However, at high
altitudes, One is often apt to be faced with conditions somewhat
less than optimum. This increased haze will often result in a
compression of the range of ground luminance to be recorded.
As the exposure is determined by the minimum scene luninance,
the exposure under such conditions can be reduced, resulting in
VI-1
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Sanitized Copy Approved for Release 2010/12/13: CIA-RDP74B00752R000100090001-6
DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
an effective increase in the Exposure Index. Increases of
two to five are not uncommon. As a result, the 1/200,. second
curve is probably more representative than the 1/500 second
curve in assessing the exposure capabilities of the system.
VI-2
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Sanitized Copy Approved for Release 2010/12/13
L
70
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Sanitized Copy Approved for Release 2010/12/13: CIA-RDP74B00752R000100090001-6
DEFENSE PRODUCTS DIVISON
Fairchild Camera and Instrument Corporatiqn
SECTION VII
FILM CAPACITY
Proposal No. SME-CA-81B
2 March 1959
The required film capacity for the proposed system is
based on the following conditions:
V . Vehicle Velocity = 3880 feet/second
H = Vehicle Altitude = 90,000 feet.
L = Film format in flight direction (inches)
% = 1 - % overlap (60% overlap).
T . Time of photographic mission . 6,000 seconds
f = Focal length of camera (inches)
G = Lateral angle of scan of panoramic camera (radians)
K = Conversion factor (inches/foot).
For these conditions the film footage required may be
derived as follows:
. Film Footage = Vxf2xTx9 (1)
HxKxLx%
This equation may be plotted with Film Footage, focal length,
format size, and lateral angular coverage as a variable as shown
in Figure 9.
For the particular values assumed above the plot indicates
the solution for the following selection of focal length film
width and scan angle.
VII-1
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
18" focal length
5" film (4-1/2" format)
90? lateral scan angle.
As indicated this requires 6,100 feet of film. For
configuration planning, the spool diameter is of immediate
concern and the second reference line on Figure 9 may be
used to determine this value (20 inches in this solution).
Other values of focal length, film width, and lateral
scan angles may be selected and the resulting film footage
obtained.
As will be noted in Equation 1 and Figure 9 the film
footage increases as the square of the focal length. For
some of the extremes of focal length and film widths shown
the resulting spool diameters become intolerable in the
space allotted.
For the purpose of estimating the effect on system
weight of different coverage requirements, figure 10 gives
film weight as a function of film length for thin base film.
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4
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Sanitized Copy Approved for Release 2010/12/13: CIA-RDP74B00752R000100090001-6
DEFENSE .PRODUCTS DIVISION Proposal No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
SECTION VIII
EFFECTS OF SHOCKWAVE, BOUNDARY ?AYER
AND WINDOW DESIGN
In view of the fact that any aerial photographic system
must look through the shock wave and boundary layer attendant
upon high Mach number of the carrying vehicle, it is necessary
to consider what optical distortion might result.
.With regard to the shock wave, analysis shows that, while
the ratio of Air densities across the shock is large, the actual
change in density is small at high altitudes. Since the index of
refraction of air is a function of the air density, the change in
index across the shock is so small that its effect on system dis-
tortion will be negligible. Because of the small value of air den-
sity at high altitudes, similar comments apply with respectto the
effect of the boundary layer on distortion.
Of greater importance in system performance is the heating
of the system window because of heat transfer from the boundary
layer. At the Mach numbers and altitudes under consideration, the
surface-temperature of the window together with the bending effect
of aerodynamic loads may also be the cause of index of refraction
gradients throughout the window. Both .of the above will have an
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
adverse effect on system performance and must be guarded against.
One method of accomplishing this result is to fabricate the photo-
graphic window of two pieces of glass with a vented airspace. By
;
! this means there will be no pressure differential across the heated
outer window to cause distortion. Because there is no pressure
differential this outer window can be relatively thin, thus mini-
mizing the effect of index gradients.
The actual design detail of the optical windows can only be
done after discussion with the vehicle designers. It is improbable
that large single windows can be used. However, this is not an
unusual design limitation and has been studied in detail by Fairchild.
For example, the long window for the primary camera can be in sec-
tions, separated by narrow longerons or mullion strips so positioned
that one of these dividing strips is always in the field of view
of the lens. This arrangement gives even exposure and has minimal
effect on system resolution.
Methods of coverage for window protection on take off and
landing have also been worked out in general design. Here again,
the actual detail will have to be worked out with the vehicle manu-
facturer.
The material for the photographic windows will be either fuzed
quartz or one of the newer optical window materials currently under
development at Corning Glass.
VIII - 2
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
SECTION IX
ENVIRONMENTAL CONSIDERATIONS
One of the initially postulated ground rules for this recon-
naissance system was that the camera compartment would be pressurized
and temperature controlled. Since that time, however, questions have
been raised as to what would be the camera performance without such
controlled environment.
Insofar as electrical and mechanical operations are concerned,
the cameras can operate over a temperature range of 50?F to I20?F.
The cameras can also operate in the external ambient pressure con-
ditions. From an acuity standpoint, however, changes in tempera-
ture and pressure during the flight will materially affect the acuity
of the cameras despite best design practice for such conditions.
IX-1
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
SECTION X
AUXILIARY AIRBORNE EQUIPMENT
Velocity and Altitude Consideration (V/H Signals)
The attainment of a high acuity photographic record from a
supersonic vehicle flying at a finite distance above the earth's
surface requires that provision be made for compensation of relative
ground motion.
If altitude and ground speed can be programmed in advance of
the mission for the duration of the reconnaissance portion of the
flight profile, this programmed data can be used to command a
forward motion compensation mechanism. If this is not the case,
however, then continuous determination of altitude and ground
speed should be provided.
Commonly, these variables are derived from the aircraft
navigation subsystem and from radar altimetry, and combined in a
simple computer to provide the Vg/H command signal to the forward
motion compensation mechanism.
A Doppler Radar which is representative of advanced state-of-
the-art, which may be extended in capability sufficient for the
present purpose, is the AN/APN-115. Present design specifications
X-1
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DEFENSE PRODUCTS DIVISION Proposal No SME-CA.,-8IB
Fairchild Camera and Instrument Corporation 2 March 1959
for this equipment which is now under development indicate an opera-
tional capability of measurement of ground speed to +0.005% (which
is in excess.of.the accuracy required) at the present maximum design
velocity of 1800Dknots. This equipment can also provide measurement
of drift angle to within +1.5 minutes of arc. This latter measure-
ment can be used to position the aiming mirror in front of the camera
to compensate for "crab" as described elsewhere in this proposal.
With respect to determination of altitude present radar altimetry
capabilities appear to be limited to 60,000 feet altitude (AN/APNA:).
Here, however, advantage might be taken of the high altitude of the
vehicle wherein determination of altitude may be accomplished by
measurement of the angle between the apparent earth horizon and the
true horizontal plane. This might be accomplished by use of the
horizon scan package shown in Figure 2.
Automatic Exposure Control
Automatic exposure control will be provided for all cameras
and will be of standard proven design.
Data Recording
In the proposed system both panoramic cameras and dual mapping
cameras will be supplied with auxiliary data recording.
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DEFENSE PRODUCTS-DIVISION. Proposal NO..SME-CA-81B
Fairchild Camera and Instrument Corporation ? 2 March 1959
In the case Of thepanoramiccameraa, provision can be made
for horizon'camera recordings similar to techniques used on another
program with Fairchilth In addition, recordingcan be provided for:
(1) timing marks along the film; (2) film shrinkage marks; (3) time ,
furnished by auxiliary timer; (4) vertical or. nadir recording and
(5) camera identification.
In the case of the dual mapping camera recording of the follow-
ing information can be made: (1) camera identification; (2) latitude;.
(3) longitude; (4) time; (5) altitude; (6) camera attitudes at
exposure.
Camera Control System
It is assumed that the vehicle will be occupied by a single man
and hence the assumption that he will have little time to apply to
camera. control problems. Therefore, the cockpit part of the control
Will be limited to an on-off switch, operating signal indicators, film
capatity remaining, and supplementary over-riding controls for con-
tingency use.
The major portion of the camera control system will be automatic
in providing warm-up, cycling signals, signal, data recording
signals and control, and cut-off.
X-3
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DEFENSE PRODUCTS DIVISION Proposal Na... SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959.
SECTION XI
GROUND SUPPORT EQUIPMENT
Test Equipment
Ground test equipment will be provided for pre-flight
check-out. This test gear will he in mobile form so that it
can be used on the flight line, in the hangar, or equipment
laboratory. It will provide all the necessary go-ho-go informa-
tion as well as confirmation of electronic control circuitry
performance in terms of voltage and current consumption.
Film Processing
.Film processing equipment can be provided for field use.
This equipment will be of proven reliable design,. This gear
can .be of either standard large colume water consumption types
or special designs using a limited amount of water.
Obtaining Quantitative InfOrmation from Panoramic Aerial Photographs
Several papers and reports have been written on the general
subject of obtaining quantitative information from panoramic photo-
graphy. In general, these have been limited to a theoretical
analysis with little concern for the hardware to accomplish the
tasks involved. It has been considered to. the point of a realiza-
tion that certain equipments, such as a precision screw comparator,
XI-1
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Sanitized Copy Approved for Release 2010/12/13: CIA-RDP74B00752R000100090001-6
DEFENSE PRODUCTS DIVISION Proposal No, SME-CA-871
Fairchild Camera and Instrument Corporation 2 March 1959
are impractical for efficient use except on photographed objects of
exceptional importance.
In the concept of functional ground support equipment for the
proposed system, Fairchild has considered various types of equipment
which vary in 'complexityand accuracy from a single frame panoramic
measuring device for target location to a stereoscopic plotter for
continuous-plotting from panoramic photography.
Equations (1) and (2) completely define the geometric relation-
ship between the plane tangent to the earth's surface at the nadir
point and the panoramic photo coordinates. Symbols are given in
Figure 11.
When requirements for the greatest possible accuracy of ground
location exist, equations (1) and (2) must be satisfied either 'by com-
putational or precise instrumental means, such as the Optical.Angulator
proposed by Fairchild in SME-CG-9 dated November 1958 previously sub-
mitted.
In situations in which extreme accuracy is not important, assump-
tions may be made resulting in simplified instruments and procedures.
For instance, if it is assumed or determined that the camera was
vertical during the exposure period, which may be possible in
the proposed installation, equations (l) and (2) may be simplified
considerably as indicated .by equations (3) and (4). These
XI-2
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(1)
CD
C)
8
CD
6,
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CD
0
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r,
?
Ef- cos(i9.7. 41ole?cos0).51174-[f ? 1- sin(tag tan R. cos Os in0+[14'sec Y4. cos6
(1-1-11) v?cos(i-ao44-an 2,evsOco5 --Pan)/ frsin tan *cos 01-114 'sec
h) Ef.sin(fcvi.'fanle.cosketan Yf .cos(1atij.ia4 e. cas 0)3
L-f.c os (fan4ii9 e?cosOcos 01.141-a4 )4...sin(km".1494,e,cos021-LX,,secY 'sin 0]
where (1-1-h) = terrain clearance of point in question
JC . focal length of camera
Y ' = photo coordinates - origin at center of span
R = Angle of roll about flight axis
45 = Angle of pitch about horizontal transverse axis
X,Y
= Ground coordinates with nadir origin andX axis parallel to flight line
(3)
(4)
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:DEFENSE PRODUCTS DIVISION PINTosalNo. SME .-CA-81B
:Fairchild Camera and InOtrument,Corporatign .2 March 1959
rk.10
SYMBOLS USED IN PANORAMIC PHOTOGRAPHS
,FIGURE .11
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Sanitized Copy Approved for Release 2010/12/13: CIA-RDP74B00752R000100090001-6
WENSE PRODUCTS .DIVISION Proposal No. SME-CA-811
.Fairchild-Camera and Instrument Corporation 2 March 1959
expressions may be handled in a comparatively simple mechanical
measuring device to read out in terms of ground coordinates or
in terms that require only multiplication by the altitude above
terrain for ground coordinate values.
Panoramic Photo Restituter
As a direct result of Fairchild's design and construction of
an electronic rectifier for Rome Air. Development Center, we have
now worked out a basic invention for restitution of high acuity
panoramic photographs.
This proposed restituter satisfies the mathematics of the
requirement that the two dimensions of the photograph be distorted
according to a transformation function. Its.output is a restituted
positive print or transparency with or without enlArgement.
The restituter is strip or sheet fed with the transformation
from negative to positive being a continuous photo-optical process.
The machine operation is controlled by a relatively simple computer.
The device will also remove the "S" curve effect inherent in panoramic
photography from .a moving vehicle.
This proposed equipment will have the advantage of high resolution
XI-5
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DEFENSE PRODUCTS DIVISION ? Proposal No.. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
high photographic speed, high versatility and inherent high relia-
bility.. Inasmuch as this is a very recent invention, a separate
detailed proposalis being prepared .on the device and will be avail-
able for Government consideration in the latter part of March 1959.
Dual Mapping Camera Ground Support Equipment
The extraction of intelligence information from the dual mapping
camera installation will use conventional photogrammetric and photo
interpretation techniques currently used for twinplex stereoscopic
mapping. Existing stereoscopic plotters, such as the Balplex, Kelsh
or Twinplex used with these techniques utilizing lateral twinplex
coverage can be used with only slight modification, if any, depend-
ing on the model of the particular plotter being considered. Con-
version fram the three inch focal length to that which is used in
the standard?go ter can be accomplished by a precision ratio
printer.
xi-6
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DEFENSE PRODUCTS DIVISION Proposal. No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
SECTION XII
INFRARED SENSORS
In order to achieve a maximum of useful information, the
inclusion of an infrared ground scanning system is highly
desirable even though the IR system may be capable of only
limited resolution. The correlation of the IR data with that
obtained from the photographic sensor improves interpretability
and provides information not otherwise obtainable. The great
advantage of such a two-color system is that the photographic
channel supplies an easily recognizable terrain picttre, within
which the infrared "hot" target can be accurately located and
its significance ascertained. Two and three color electro-
optical systems have been advocated by Fairchild for over six
years, e.g. the Scan-A-Con System; and large amounts of company
research and investigation have gone into such systems.
Although much of the sensor compartment is filled with the
primary and secondary cameras, there is still adequate space for
an IR scanner, recorder and the associated electronic components.
The only major question yet unresolved is that of background
radiation originating in the IR window of the system. This
problem arises because of aerodynamic heating of the outer surface
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'
(
(
L-1
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
of he vehicle. It is understood that for this particular
application, the window temperature may be approximately
700?F. From black-body calculations it is found that the
wavelength at which peak emission occurs for this temper-
ature is 4.5 microns. This unfortunately falls within the
3 to 5 micron atmospheric window and requires consideration.
However, this problem which is common to many IR systems has
been discussed with two companies highly experienced in this
field, with whom Fairchild has been working on unsolicited
IR proposals, and they feel that the problem is soluble.
Part of the solution depends upon the fact that the actual
power emitted from the window as background is a function not
only of temperature but also of emissivity. As the sum of
emissivity, reflectivity and transmissivity is unity for all
materials, the selection of a window material of maximum
transmissivity for the wavelength interval in which the detector
is responsive will insure minimum background radiation. The
responsivity of the detector will be limited to the 3-5 micron
atmospheric window by appropriate bandpass filters. The ex-
traneous window radiation can be further reduced by loweijmg the
temperature of the window by internal cooling and by altering
the aerodynamic flow pattern in the vicinity of the window so as
XII-2
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
to decrease heat transfer from the boundary layer. The extent
to which the latter may be employed depends on whether or not
the vehicle designer will be able to stand the slight increase
in aerodynamic drag attendant to the alteration in shock wave
and boundary layer characteristics. The cited opinion with
regard to the feasibility of overcoming this difficulty is
based in large part on fundamental studies for IR sensing from
Dynasoar. In any event, there is -aore than sufficient probability
of success to warrant inclusion of detailed study of IR as a
portion of the system capability in Phase I of the program.
The IR spnSor would be designed to work in the 3-5 micron
region. It is considered that the thermal problems discussed
above will preclude any possibility of working in the 8-13 micron
region as this would require an extremely cool window,- The
scanner would be of the line scan type covering a lateral angle
of 900. Recording would be on film using either a cathode ray
tube recorder or the ultrasonio light modulator. The choice of
recording technique would depend on the resolution, bandwidth and
dynamic range required.
XII-3
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Sanitized Copy Approved for Release 2010/12/13: CIA-RDP74B00752R000100090001-6
DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
The resolution of the IR scanner will be at least one
milliradian resulting in-a 90 by 90 feet ground resolution
element at operating altitude.
In view of the fact that the IR information will be
correlated with that obtained photographically, an increase
in IR resolution would not cause confusion in interpretability
as is sometimes the case with independent IR systems. However,
because of the limited space available in the vehicle, the
present state of infrared technology with regard to detector
sensitivity, time constant and other factors restricts the
angular resoiution to a value of approximately 1 milliradian.
Further improvements in the performance of detectors such as
indium antimonide or gold-doped germanium would result in
reducing this system limit and would be incorporated should
they become available in sufficient time. At the present time
improved resolation can be obtained only by the use of multiple
detector arrays with the attendant increase in system size and
weight.
At a resolution of 1 milliradian the scan rate becomes
approximately 39 scans per second (velocity of 388)-i- feet per
second) a figure which is low as regards the capability of
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DEFENSE PRODUCTS DIVISION Proposal No, SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
mechanical scanning techniques. For a 900 scan at 1 milli-
radian resolution, the number of picture elements per scan
line is approximately 1600. At 39 scans per second a band-
width of 31 kilocycles is required. This bandwidth, with
proper gamma control circuitry, is well within the recording
capability of the Fairchild cathode ray tube recording system.
The required film capacity for a 90? scan system of 1
angular mil resolution will be approximately 32 feet if
70mm film is utilized.
Referring now to other details, the use of indium anti-
monide in the photoconductive mode for operation in the 3-5
micron spectral region will require liquid nitrogen cooling.
The cell itself will be mounted in the now customary miniature
Dewar flask. The amount of liquid nitrogen required will be
minimal. Because of the extended operation time study will
be required to ascertain the feasibility of utilizing a small
cryostat for this cooling which would be very convenient.
However, recent developments in indium antimonide detectors
based on the photo-electric-magnetic or Hall effect may permit
the use of an uncooled cell in a system of limited resolution.
XII-5
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
The opto-mechanical design of the scanner can take
many forms considering the scan rates involved. Preferred
forms are oscillating mirror types with low drive power
requirements for large apertures. One arrangement is
positively driven at a controlled rate; the other is based
on a resonant frequency drive. Both are of extremely light
weight construction and are capable of compact configuration.
The two drives are illustrated in Figures 12 and 13. The
resonant frequency drive is thenmore compact and is therefore
particularly desirable because of the smaller external window.
The electronic circuitry will include a power supply,
preamplifier, gamma control and probably a quantizing network
for enhanding contrast as an aid to interpretability and to
reduce bandwidth requirements. All of the above can be highly
transistorized for reliability, compactness and weight redUction.
Dependent upon the inherent stability of the vehicle, it
may be required to record instaneous altitude data (roll, pitch
and yaw). These data will be used in ground support equipment
for automatically rectifying the IR information for correlation
with the photographic record. Proyiding the required correction
xii-6
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-81B
Fairchild Camera and Instrument Corporation 2 March 1959
on the ground will reduce the complexity of the airborne
recorder.
A 1 to 1/2 mil 900 system will weigh approximately
4o to 60 pounds and require a volume of about 1-1/2 cubic
feet. This cubage is made up of the scanner, recorder and
associated electronic components.
XII-7
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.).
3.
i
_i
?I
W
0
7.-
ll.
(.1
Z
? cr
z 0
z cc
a ct
0 ?
v) 2
FIGURE 1 2
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DIAGRAM OF CRANK SCANNER OPERATION
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-
?"1.1-? 4-7/ ' C
L.
"5-C We:71-X -)Z .7/
;
. t?
-
- -7/_?-',-7./e7. 0 C /C:
4-2C
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,}"*. ? ? .?-? .? ?
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, .
Pear GeOrget
? ? . Enclosed-is a 'proposal, ? in a very Preliminary form, for
7*.itt Camera; .or rather, a .family of catheras each basically like the' other
; in most respects.. 'You ? indicated little tiMe could be allowed to. us
.ozettin this th yeui;, therefore, ? it is at best more fravnentazy ?
than' we normally' like:-to4eifleive -our ?handsd :
? ?
; We ,believe the design we hAve in mind will, give the
9f:reeilts ,and in the . long run. be..more reliable than almost' anylou ?
? ,
Oau_isiaiine. It ii flekible enough'to be used at low altitudes right
?
On Up to the range- of satellites with only -minor changes. With some ?.
4414flight:-.procOsslng and scanning are possible. Thus, - it
? Vecoales a-very flexible tool to go with various ;vehicles ? they are
? evolved. .It also .can abcept improvements. in the elements of the
sYstertt,a.s? they cane with :little design rei.arrangement. fle3dbilit
? coupled with. highest reSolution pictures and reliability, deserves...,
your very careful. attention because we doubt it 'Can be surpassed
reagly now. : ? ? ' ? , ? ?
? ,
?
?:-.,tire believe yOu:?ahonld have .first usage ?of'this :deei
,bave
,
7
,444Adtie;li#64'.'460
? e *ia
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Yj ? ?
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Th9 ricitittflon?df.the operating. tonditacns or the aircat
,
ndnd
. is beint-itted .intentionaily here though the goneral ima
, ? 1
specifications are assumed from which those appl..yinz to any: particular
?-7,4; ? - .V,Ad.
`e. Or Aka, .xtA. .0 0.,;4?? ??? t'A
.i.1.71'9414.144tiltkeer't, .04-, 4 ? e !???? ? ,?.? ? $1141V4!:. ?44 '????irr ??? ? y ?
,opari can be e.xtrapoi. ? ?
Aircraft. alii..tude
Photograjihic rIcording tima 1,5spOO second? or
Desired- groutri resolution, ? 2 feet- (in phOic0
? temp)
..ortii)"up.u?
-to:5os000 ,tet
. , 0164!i4.1013441;'( ,
ailditioan';a40.1001
,s4d ?lit' .(1?64)1"
?ZrrretattOlV4th
q- radar racirdinge
4 corret14,14.th
tik
?":.
? ?
. " 7 it*
ad :weight
, 1**$12;
. . .
illifw?he desired troutd- **sole
h if1,40.044)dien used to'covp.t *
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r?
film And II :C properties, the -.17.14.13.1 cesCfl shoulri be realistie for
shorts term develr)pments but sholaii allow for ?inictividual elemental
lasproventents as' they becane vaileb1e.
? With Imo/ledge of al most all conditions, the follow:4g .table ?
,?
;
??
ificaticnio Apcogt404.1:4 ;P02;44144.1:
? ? ,......
2-r De8in
? -1,yr 'Design
plAtIC(fpr'2 stripe Ade by aide
0041.44 0imerptil2 x:e844t1oil .
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??.
The largest factors 'Contributing to the . loss of resltit
? .
?
4ign-41titude. reconnaissance pictures are.: (1) hilure to obtainndto .
use 'the Correct .1141C; (2) vibrations which result from shutter0
?film advance Mechanisms; and other .intermittently moving !lasses; .
*,?(3) lens 'flare,1 (4) incorrect 614losUre; (5) Use of mirrors, moving
optiCe? ? or the like; (6) .incorrect.selection of most suitable films.
By making Marbill.Z.1?sge of the arid?leni.'eariabilities more - alpha till
? .
can be ''given to INC 'measuring devices and correction.. This problemezis1s in ;
all types of ? oak-eras, but its solution in a slit cameraEinr....
achicea fewer comeiitibs. with ? the better resolution prdpO
. ? ? .
it
May ?be:.necessarge to deliver a -higher order of accuracy:4
-? ? '
pected, The .ateral slit
camera' minimizes .1l camera iibrati
, . . ? . -. .
It: it _the purpose here -i,.6 recommend a-' slit type cam
. .: . ...???
h.io the slit it transverse to ..the direction. of flight ',and
,.?
, ? . ,
44tive to the lens and "tainers' ineuntirig. ? INC. and f
.? phot,dgraph .Wit..h ?
yeti( high 'resolution .a.-two.-iiimensionafp
4
I.):. Howeverj# stereoscopic images are not z'eadilX
though sOme optical maitipniation. could be used to place ster
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" t4
recordinf, ts f 1"44 two
: ? ? .
in positn, v70'113 -be st14.%tab,?,,
. .4
for s. tereo,s7.--.7.7 A.F; in II. '!"--,r! 'slits eall.
?
bo ? located ,,yr,reni.ently vion g the le:Alz-th . the filr:?, '11:r;
ci1c5:?10, fa?ctor;.; ns rr!rmx..,rat':,?,y.-,,, ease 'of martufaptUra`,
. .
'of tH.,.(mr.5..n.g.equipment, curvat-,-2 c)f erir.3 e1ci. etc.? ? Other rariatidhit,.:`"
4,
,& this sarie desigr wOul.d laeimit partial" .6teree oover..aE,4e ornbj
fringe covur.age ae 53holn in Figure. ItI;i4-7.
. ,
- ..,
coYerage (10' miles. ) without stereo, as shoiin in:Fi
gu
..
)1,,, 1, ?. ? . ? .:.-
.. at'her poSsibilitieF, ns , eue,h as .one long le for heat.?.
.., , . .
. .
' etail aecompanied by f. short lenst for large area coverage, co u3
..,..14,,t,
04. if 'two strips af f D.= and ? different IMC ......--,,4 slit widths ,?,r
...
444154
1 (See Figure V.) In another variatiop, by: 'the u.re 9
. , . .
,,, .r,,f ? .
eiOne.Or filters,- orie'fil*'cOuld.be Used for.sone.v,O.velene0
4th/3:green region and tho.other.in the 'tar red region:
?
.4iika;b* A:14 Irdi,42i0Ord the ksible
i.aient or. irron a tomb1rfai1ata*Of.V1 and 4re,4er; ?
uiege of the scheme of Figture, I/ and "
S Ejtt '
..atereoeicopy;.difletent ?elpo.skir'es be
. ,
gifning th0.eby in ehed,mi or highiight information.
? in 'usage is possitA?by it 'eking One 1.exis slightly d11iei7,
local length than 'the other, tiring Slightly different scales
,?.;,?"?? ? ,
elight1y::.4.1.1Terent'erfective INP.,whiph
? -
Irmr-
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, Sanitized Copy Approved for Release 2010/12/13: CIA-RDP74B00752R000100090001-6
.Up to;this
? ? -
irk given nortly''..- 6-ran! i7a!:c9 th
d additions.th provion a r-table riatform may .be necessir
. as a result of the vehicle chnrater:F-_1.7.s not known t present..
?
,a part of th I system if the F.:: anz;les art large.
Uniform time siznals and inforrnAtiOn to establish nadir
,
WOUld-tevo to be nhotographed along the edos of the Ma to tet*
*asiirements knl 000rlination with othc,r ins*,rul'Ientatin, The
lusion of the elefients of inertial zuldnee system would be:-
? ..
as:rable'advantage for navigaticm, photogrammatri1 .nadir det
' .
or raeOnnaissanO.intelligence.
, .
This Part of the vstem is probably the same for
ri mechanism, and, therefore, only the recognition pi',
, . .
lems ie ih4nded here at.this time. .
It:ls'nndirstooethat a nuniber of viewirg.ind Print
avalready exist..for?the "two strip"'sterio'recOrding,On)f
. . .
, . ?
dela here.,.: With the.muth higher reaolutiOaobtainable%
-?
csYsteMs.it mar be necessary to increase magnifications
. , .
t an0 enia;Xing Printers tg'takerni.1:41
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?
.?
hoped the,.
near future 4. f you express an i further expl,
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?
?
?
,
"
?
r
?,??
144'
*.;?;)';',
e",..
?
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?
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11./spe,
1 ..-1*^..- . -1.:-..s...-...:.-...sutsZilaiasZatir.414.....A61....- .0.0??????????INIMMAIX. .1.......
? _re' , ?
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