PROJECT VERTICON

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP63-00313A000600150042-4
• Release Decision: RIFPUB
• Original Classification: S
• Document Page Count: 45
• Document Creation Date: December 12, 2016
• Document Release Date: July 30, 2002
• Sequence Number: 42
• Publication Date: February 1, 1959
• Content Type: REPORT

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DEFENSE PRODUCTS DIVISION
Fairchild. Camera and Instrument Corporation
Robbins Lane, Syosset, New York
PROJECT VERT ICON
PROPOSAL NO. SNE-CA-80
1 February 1959
PHONGRAPHIC RECONNAISSANCE
from
VERTICAL FIRING ROCKETS
This document contains information affecting
the National Defense of .the United States
within the meaning of the espionage Laws,
Title 18, U.S.C. Sections 793 and 794, the
transmission or revelation of which in any
manner to an unauthorized. person is prohibited
by law.
NRO REVIEW CW/Iiitii?freTcMr Release 2002/
I.
Copy No. /
XRGW-RDP63-00313A000600150042-4
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"ftir Nair
DEFENSE PRODUCTS DIVISION
Fairchild Camera and Instrument Corporation
TABLE OF CONTENTS
Title Page
Table of Contents
Summary
General Discussion
Technical Discussion
Ground Support Equipment
Appendix
List of Illustrations
1. Vertical Rocket Reconnaissance
2. Reconnaissance System for Ballistic
Rocket.
3. 100" Rotary Panoramic Camera
4. Basic Rotary Panoramic Camera
5. Radius of Coverage vs. Altitude
6. 12" Rotary Panoramic for Rocket
7, Photographic Ground Coverage of
Panoramic Camera
8. 12" Rotary Panoramic with Wobble
9. Multiple Camera Installation
10. Photographic Coverage from 100
11. Photographic Coverage from 600
120 Fairchild Four Lens Camera
13. Four Lens Camera Mockup
14. Four Lens Camera Mockup
15. Four Lens Camera Mockup
16. Four Lens Camera (Cut-away View)
17. Single Camera Installation.
Proposal No. SHE-CA-80
1 February 1959
Page No,
Unnumbered
ii
1
3
10
Trajectory
12" Rotary
Control
Miles Altitude
Mile Altitude
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-80
Fairchild Camera and Instrument Corporation 1 February 1959
PROPOSED
An adaptation of a simple and reliable scanning
camera for use in small or intermediate size
vertical firing rockets.
APPLICATIONS
Rapid and large area surveillance.
Rapid meteorological surveys.
Reconnaissance for geodetic control surveys.
ADVANTAGES
High information yield.
Flexibility of usage.
Low equipment cost and short delivery schedule.
CAMERA DESCRIPTION
The basic camera is a scanning rotary pan-
oramic for use with spinning rockets and
a compact array of miniature cameras for
non-spinning rockets. Wide lateral angular
coverage with 3600 azimuthal coverage.
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-80
Fairchild Camera and Instrument Corporation 1 February 1959
VERTICAL FIRING ROCKET RECONNAISSANCE SYSTEM
This proposal presents PROJECT VERTICON, a system for
photographic reconnaissance from vertical firing rockets.
Vertical firing rockets will be an ideal vehicle for
relatively low cost, rapid reconnaissance for meteorological
data, large area surveillance, and extremely accurate geodetic
control surveys. Depending upon the nature of the mission and
rocket selected as the vehicle, the camera installation can
run from an extremely simple low cost unit using 16mm, 35mm,
or 70mm film to more elaborate and sophisticated installations
using special optics for extremely high information content
in the case of long range surveillance or precisely calibrated
mapping lenses and cameras for geodetic control.
GENERAL DISCUSSION
In the gathering of intelligence information utilizing
photographic sensors for reconnaissance purposes in a high
altitude vertical firing rocket two primary factors come under
consideration - Scale of Photography and Ground Coverage. Dur-
ing the determination of a suitable reconnaissance sensor from
the vertical firing rocket two types of cameras have been con-
sidered which in general are suitable to the two types of rockets,
i.e., spinning rockets and non-spinning rockets.
The scale of the photography is determined by the focal
length of the camera selected (regardless of its type) and the
altitude of the rocket at the time of exposure. Ideally, the
scale would be solved by providing the longest focal length
possible in the limitations set by the vehicle.
The ground coverage of the reconnaissance system is deter-
mined by the focal length of the camera, the size of the film
platen (format) and the altitude of the rocket at the time
of exposure. Ideally, the coverage would be horizon to horizon
and 360? in azimuth providing complete ground coverage. The
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-80
Fairchild Camera and Instrument Corporation 1 February 1959
same "ideal" coverage applies to the consideration of photographic
sensors for meteorological or geodetic control surveys with a
reduced emphasis on scale of the photography for meteorological
purposes and an increased emphasis on system distortion for
geodetic control surveys.
Figure 1 illustrates the general application of the photo-
graphic reconnaissance sensor to a mission utilizing a vertically
fired rocket and whose usage may include general reconnaissance
or "looking over the fence", weather reconnaissance, or geodetic
mapping.
In the past, the combination of long focal length and wide
or large coverage has been impractical since it means a large
and bulky installation of a multiplicity of long focal length
cameras. Today, however, the combination can be obtained by
the use of a single camera installation which by its technique
of operation can provide wide angular coverage. As applied to
a spinning rocket, this single camera installation is a SIMPLE
ROTARY PANORAMIC CAMERA
The restriction placed on the installation to obtain this
large information level is that the rocket itself or some part
of it must spin about its longitudinal axis while rising in its
trajectory before and/or after burn-out of the final stage. In
the case of rockets which are designed to "Spin" this presents
no problem.
In the case of the frame by frame camera (or square format
camera) applied to a spinning vertical firing rocket installation
the large angular coverage which is required makes it mandatory
to have either a multiplicity of cameras or fast cycling rate
for a single camera with an extremely fast shutter speed required
in either case to prevent photographic blur due to rocket rotation.
Such an installation can be made using the shorter focal length
lenses with the smaller format sizes.
Considering the non-spinning rockets such as "ARCAS",
"ARCON" and "IRIS" the photographic reconnaissance mission can
be accomplished by a cluster of miniature cameras utilizing
existing wide angle lenses such as the 1-1/2" Biogon and a
2-1/4 x 2-1/4" format. The decision as to the camera design
to be used actually rests with the rocket design selected to
carry out the mission and the type of reconnaissance mission.
For a rocket with a 15" diameter such as the Aerobee-Hi a single
camera housing utilizing four lenses can be mounted at the extreme
lower portion of the rocket. Such an installation is discussed in
the next section of this report. It should be noted here that
this type of installation will provide reconnaissance from alti-
2
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DEFENSE PRODUCTS DIVISION Proposal No, SME-CA-80
Fairchild Camera and Instrument Corporation 1 February 1959
tudes between the time of sustainer drop off and the peak of the
trajectory. During this portion of the flight it can provide
photography of the entire area visiblelhorizon to horizon through
a full 3600. Based on the estimated performance data of the
Aerobee-Hi this would be from altitudes of 26 miles to 168 miles.
For a rocket of smaller diameter the "cluster" of cameras
may be spread out along the longitudinal axis - making five
individual miniature cameras and a single miniature to photo-
graph from the bottom portion of the rocket. Where the par-
ticular mission requirements permit, a delay in the operation
of the vertical camera will permit oblique photography before
sustainer drop off and, therefore, provide larger scale oblique
photography with a minimum blind spot.
The film footage required in any installation is dependent
upon the length of time of the coasting phase and the duplication
of photography desired. It is considered appropriate in the case
of a "cluster" of cameras that several francs be exposed of the
same (full coverage at each exposure station) area since the
scale will be different at each exposure station and multiple
observations will aid in the interpretation of data.
It must be pointed out that although the specific applica-
tion presented here is for the vertical firing rocket, the basic
approaches may be used in other ballistic trajectory rockets
as illustrated in Figure 2.
In the accompanying discussions it is realized that the
vehicle payload includes other equipments such as parachute and
recovery beacon in addition to the photographic sensor.
Characteristics of typical vertical firing rockets are
appended hereto to provide the necessary technical data to
aid in system selection and specification,
TECHNICAL DISCUSSION
This section is devoted to a technical discussion of the types
of cameras and their application to a vertical firing rocket recon-
naissance system.
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DEFENSE PRODUCTS DIVISION Proposal No, SME-CA-80
Fairchild Camera and Instrument Corporation 1 February 1959
a. Panoramic
b. Frame by frame cluster of cameras
c. Frame by frame single lens camera
d. Frame by frame four lens camera
A. Panoramic Cameras
The use of a panoramic camera permits the use of lens design
techniques which result in a higher performance in terms of imgge
quality than a lens design for a square format (frame by frame)
camera within a given weight and cost. This advantage is attrib-
utable primarily to the reduction in the 1/2 angle field of view
of the lens since the panoramic camera format is a slit (a few
thousandths of an inch the width of the film being used) as opposed
to the diagonal of a square format camera (usually 1.414 times
the width of the film).
Using this advantage of design it is possible to increase
the speed of the lens (within the same weight and cost) which
permits faster shutter speeds. With modern large aperture lenses
(together with improved transmission factors) and the high speed
emulsions, very fast shutter speeds can be used to obtain accept-
able exposures. In the panoramic camera where the exposure time
is obtained as a junction of film transport velocity and slit
width speeds upwards of 1/4000 to 1/5000 second are practical.
Such exposure times go a long way towards reducing the amount
of "smear" normally resulting from image motion.
The determination of the correct film transport velocity
across the exposure slit as a function of the rocket spin rate
can be accomplished in at least three different ways as follows:
1. A small rate gyro can be installed within the rocket,
the spin axis of the gyro being perpendicular to the spin axis
of the rocket. An electrical signal can be derived which is pro-
portional to the spin rate and thus becomes the input to a servo
drive for film transport,
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-80
Fairchild Camera and Instrument Corporation 1 February 1959
2. Depending upon the operational concept of the rocket
reconnaissance the spin rate may be obtained by photo-electric
means such as an input to a photo-electric sensitive surface
from the sun.
3.
launch.
The spin rate of the rocket may be preset before
Combinations of these may also be used, for instance, the
determination of preselected spin rate just prior to the last
stage burn out by photo-electric means after which the spin
rate would have a minimum of change in the absence of atmos-
phere to retard it.
Figure 3 represents embodiment of a SINGLE ROTARY PANORAMIC
.CAMERA in a 100 inch focal length showing an extremely long
focal length lens in a minimum package and. serves to emphasize
the major advantage of this type of camera: LARGE SCATg WIDE
ANGULAR COVERAGE IN A SINGLE CAMERA. In this camera type the
lateral angle is a matter of designer's choice. It is shown
in its usual orientation; that is, with its optical axis para-
llel to the ground plane, with a single reflecting surface in
front of the lens to direct the optical axis vertically down-
ward. The instantaneous field of view of the lens is limited
to a rectangular area determined by the film width in one direc-
tion and the width of an exposing slit in the other.
The feature of flexibility of lateral angular coverage is
accomplished as illustrated. in Figure 4. Exposure is made by
drawing film past the slit as the entire camera including the
magazine, rotates about its optical axis. This rotation is
continuous in one direction, the angular -velocity normally
being a function of V/H and. overlap requirements. Thus, it is
possible to scan continuously, 360? around the longitudinal axis
with all parts of the camera moving uniformly without inter-
mittencies of any kind. Film velocity from. supply, through the
exposing slit to take-up spool in this case would be constant.
However, since scan angles greater than 180? (horizon to hori-
zon) are seldom required in a vehicle with its axis horizontal
it is necessary to move film across the slit during only part
of the rotation. The spools, themselves, however, continue to
turn, feeding and taking up film at an average rate which
furnishes the amount required for the portion of the rotation
during which photography occurs. Chambers for the slack film
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DEFENSE PRODUCTS DIVISION
Proposal No. SME-CA-80
Fairchild Camera and Instrument Corporation 1 February 1959
are provided on each side of the slit. Referring to Figure 4,
the transport cycle proceeds as follows:
Film is drawn from the supply spool by a pair of pinch
rollers turning at a speed which is integrally tied to the
rotational speed of the camera, which in turn is proportional
to V/H. The film then passes under a roller attached to the
scan stop switch, thence through the pressure plate assembly
around. the metering drive roller, and idler roller, and onto
the take-up spool. The metering roller is mounted on a rock-
ing member in such a way that it does not contact the film
except during the scan period. This roller is continuously
driven at a speed proportional to the camera rotation. It is
brought into contact with the film by the solenoid (shown sche-
matically) when the camera reaches the point selected for start-
ing the scan. The film previously accumulated. in the supply
chamber is then drawn. past the exposing slit at a speed which
is synchronous with the image being swept across the slit by
the rotating mirror. As the film runs out of the supply chamber
it actuates the scan stop switch, which de-energizes the sole-
noid, causing the rocker arm to tilt counter-clockwise, disen-
gaging the driving roller and engaging a fixed. roller on the
opposite side of the gate, which serves as a brake to hold the
film from coasting or being fed across to the take-up spool
when the latter takes out tle slack loop which has been trans-
ferred into the take-up chamber.
The take-up spool is simply overdriven sufficiently to take
out all the slack film before the next scan. occurs. In a more
refined version or where the mass of film is great, a second pair
of pinch rollers would be used at the take-up side to meter the
film to the spool at a rate which would. keep the spool turning
continuously.
Control of the supply loop by the above method prevents
accumulative build-up, or loss by virtue of the fact that all
the film (whether too much or too little) is withdrawn each cycle.
The effect of a slight over or under supply is merely to add or
subtract proportionately from the angle scanned-
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DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-80
Fairchild Camera and Instrument Corporation 1 February 1959
Figure 4 indicates one way in which the entire camera can
be rotated by a single drive motor. In this case a fixed sleeve
which would be mounted to the aircraft structure or a mount as
the case might be, supplies bearing support for the camera.
A belt is used to couple the motor to the camera through a
cut-out in the fixed. sleeve. Driving of the various rotating
members in. the magazine is effected by a pinion which rolls
on an internal ring gear fastened to the fixed sleeve.
In order to maintain the shutter speed through variations
in V/H the adjustable slit mechanism will, contain an overriding
control, which will be actuated as a function of the rotational
speed.
Other functions such as remote exposure control involving
iris and/or the slit width are readily adaptable by usual servo
methods. The only difference here is that all these items will
be rotating continuously about the optical axis.
As used i:o a vertical firing spinning rocket the basic
camera described above would, be oriented with its optical axis
perpendicular to the ground plane with a single reflecting sur-
face mounted so as to have a field view downward and outward,
Although the camera housing is shown separate from the rocket
shell it is pointed out that the camera and. shell rotate together
at the rocket spin rate. If final installation considerations
show it to be advantageous the camera housing and rocket shell
can be combined, as one unit.
Depending upon the vertical velocity and spinning rate of
the rocket the field, of view of a continuously operating camera
may result in a spiral coverage with a discontinuity of coverage
in the radial direction. To prevent such an occurrence the reflect-
ing surface may be programmed. to pivot about its midpoint as a
function of the vertical, velocity and spin. rate.
In order to determine the optimum exposure altitude for each
panoramic sweep it is necessary to determine the coverage which
can be made from a specific altitude.
'-7
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DEFENSE PRODUCTS DIVISION Proposal No, SME-CA-80
Fairchild Camera and instrument Corporation. 1 February 1959
Figure 5 is a plot of the ground. coverage (arc distance
on the earth's surface) as a function of altitude for two
angles off the vertical. In this case 64? and. 74? were selected
since a panoramic camera of 12" focal, length using 5" wide film
is under consideration- The optical axis is positioned. at 74?,
therefore, providing a field of view from 63-1/2? to 84-1/2?,
(Only a nominal angular value (64?) has been used. in the plot),
Also shown is the radius (arc distance) to the horizon as a
function of altitude.
This plot provides a way of selecting the altitudes for
exposures to be made Thus, if the first exposure is made at
25 miles, coverage is provided from a radius of 50 miles out to
the horizon at 425 miles. Since the high oblique contains inform-
ation which is not extremely useful for certain intelligence
purposes, it may be necessary to provide overlap in. the radial
direction.
For purposes of illustration, consider 50% radial overlap
or the next exposure at such time as the blind spot becomes
approximately 100 miles (see 25 mile altitude at 74? curve on
plot). Such an exposure will extend from approximately 100
miles to the horizon at 625 miles.
By following this sequence, the exposure stations can be
determined. Figure 7 with the overlays illustrates the coverage
of this type of operational technique with the following conditions:
Exposure No.
Altitude
Extent of 360? Coverage
I (red)
25 miles
104 to 886 miles
2 (green)
40
"
170 to 1120
3 (black)
75
i,
344 to 1530 "
4 (blue)
140
"
624 to 2076 "
5 (yellow)
275
"
1380 to 2870 "
6 (orange)
345
"
1894 to 3194 "
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DEFENSE PRODUCTS DIVISION Proposal No. SNE-CA-80
Fairchild Camera and Instrument Corporation 1 February 1959
The coverage as shown is predicated on the use of a 12" focal
length lens and 5" film configured into a Fairchild Rotary Panor-
amic Camera as shown in Figure 6.
To make full consideration of the rocket performance, Figure
8 illustrates the application of a 12" panoramic camera with a
rotatable mirror used to overcome wobble which is experienced
in the rocket during sustainer firing and after sustainer fall
off.
The foregoing descriptions of specific panoramic cameras
and coverage also applies to panoramic cameras using 35mm or
70mm film. These smaller sizes are quite ideal for weather
reconnaissance using the smaller diameter rockets.
B. Frame by Frame Cameras
For application to non-spinning rockets the same coverage as
indicated above can be obtained utilizing 5 cameras set in an
oblique position as indicated in Figure 9. As can be seen the
five oblique cameras have been "stacked" along the longitudinal
axis of the rocket to fit into a 6 inch rocket such as the ARC0N0
Similar installations using other cameresand film sizes can be
made for the 12 inch diameter IRIS, the 4-1/2" diameter ARCAS,
the 8" diameter instrumentation chamber of the AEROBEE-300
(SPAEROBEE) or in the case of weather reconnaissance even smaller
rockets. Specifically consideration has been made for a 16mm
rotary panoramic camera using a 25mm lens to provide 360? cover-
age from up to 38 different altitudes in a two inch diameter
rocket.
Figures 10 and 11 indicates the coverage obtainable from such
an array of cameras from altitudes of 100 miles and 600 miles
respectively.
Fairchild Camera and Instrument Corporation has recently
completed a preliminary design of a four lens camera for use as
a reconnaissance camera from high altitude. The application of
this camera to a vertically fired rocket is shown in Figure 12.
This camera provides an angular coverage of 156? "lateral" or
78? from vertical in all directions (360? coverage in azimuth).
As illustrated in Figure 12, it is obvious that such an instal-
lation is applicable to rockets of 15" diameter and larger,
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Fairchild Camera and Instrument Corporation 1 February 1959
whose sustainer is ejected. It is not impossible in the larger
rockets to make provisions for retracting the camera (or take-up
spools) to allow for recovery techniques required such as seal-
ing the end of the nose cone. This installation will photograph
the entire earth's surface (horizon to horizon - 3600 in azimuth)
from altitudes of 110 miles and above.
Figures 13, 14 and 15 are photographs of the mockup made
of this camera. Figure 16 is an artist cutaway view of the
four lens camera showing the relationships of formats, film
supplies, drive package and the automatic exposure control
sensing element.
GROUND SUPPORT EQUIPMENT
The intelligence obtained from the photographic record
will depend to some extent upon the ground support equipment
furnished. This equipment falls into two major categories,
each identified with the type of camera; panoramic and frame
by frame.
For general reconnaissance each category must provide a
rectification of the photographic record to a useable datum.
In the case of the panoramic camera, this rectification may
be done in several ways. The most direct approach would be
an autofocusing enlarger which would rotate to cause an ex-
posure of a narrow field of view and simultaneously increase
its height above the datum to compensate for the rocket
increase in altitude during a single panoramic exposure. The
relationship between the rate of rotation and translation will
depend On the vehicle selection (rate of spin and velocity at
the time of exposure).
Other types of rectification may be possible for certain types
of intelligence to be obtained such as point location, contin-
uous charting of a single feature such as river, coast line
or transportation network. In this type of intelligence, point
by point rectification may be considered adequate.
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DEFENSE PRODUCTS DIVISION Proposal No, SME-CA-80
Fairchild Camera and Instrument Corporation 1 February 1959
In the case of a frame by frame camera where each frame
of a cluster of cameras may be considered as a single recti-
fication the problem is simple. The overall picture, however,
that of transferring from detail in one frame to detail in
another frame taken from the same exposure station becomes
somewhat more involved. Here it is presently considered
appropriate that the ground support equipment would be based
on an analytical solution relating each frame to the vertical
as a "zenith angle" and "azimuth angle". From such analytical
data) adjustments may be made as multiple observations are made
of the same points in subsequent exposures.
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Approved For Release 2002/0593ENCIA-RDp63gp313A000600150042-4
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DEFENSE PRODUCTS DIVISION
Fairchild Camera aid Instrumet Corporation
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Proposal No. SME-CA-,j)
1 February 1959
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Approved For Release 2002/08/23 : CIA-RDP63-00313A000600150042-4
SECRET
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Approved For Release 2002/08/23 : CIA-RDP63-00313A000600150042-4
Approved For Release 2002/08/23 : CIA-RDP63-00313A000600150042-4
Approved_
For Release 2002/0?THR.1q1A-RDP63-14013A000600150042-4
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DEFENSE PRODUCTS, DIVISION Proposal No. SME-CA-80
Fairchild Camera and. Instrument Corporation 1 February 1959
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DEFENSE PRODUCTS JflrISION Proposal No. SM-CA-i0?
Fairc hi ld , Came ::.a ildfr In:St I brAt Cokp . 1 Felyimalv. 1959
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P-Zi70091.009000VCI?C00-?9dati-VI3 MBOMOU aseeieu JOd 130A0iddV
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Approved For Release 2002/08/23 : CIA-RDP63-00313A000600150042-4
Approved For Release 2002/08/23 : CIA-RDP63-00313A000600150042-4
SECRET
Approved For Release 2002/08/23: CIA-RDP63-00313A000600150042-4
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DEFENSE PRODUCTS DIVISION
Fairchild Camera and Instrument Corporation 1 February 1959
Proposal No. SME -CA -80
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Approved For Release 2002/08/23 : CIA-RDP63-00313A000600150042-4
SECRET 8 0
Approved For Release 2002/08/23 : CIA-RDP63-00313A000600150042-4
Approved For Release 2002/08/23 : CIA-RDP63-00313A000600150042-4
Approved.For Release 2002/08/23 : CIA-RDP63-0e313A000600150042-4
Approved For Release 2002/08/23 : CIA-RDP63-00313A000600150042-4
FIGURE 14
Approved-For Release 2002/08/23 : CIA-RDP63-0'0313A000600150042-4
Approved For Release 2002/08/23 : CIA-RDP63-00313A000600150042-4
FIGURE 15
Approved For Release 2002/08/23 : CIA-RDP63-00313A000600150042-4
Approved For Release 2002/08/23 : CIA-RDP63-00313A000600150042-4
FIGURE 16
Masa'
Approved,for Release 2002/08/23 : CIA-RDP63-0.013A000600150042-4
DEFENSE PRODUCTS DIVISION Proposal No. SME-CA-80
Fairchild Camera and Instrument Corporation 1 February 1959
1 . 1
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Approved For Release 2002/08/23 : CIA-RDP63-00313A00060015G0412-4,
SECRET
Approved For Release 2002/ONC:RWRDP63-00313A000600150042-4
A EMET UPPER ATMOSPI/ERE
SOUND/Na ocitErs
AERO BEE
75
AERO BEE
100
AEROBEE
150
AERO BEE
300
NO BOOSTER
DUAL-THRUST SOLID
100 LB
75 MILES
SOLID BOOSTER
RFNA JP-"4
40 LES
100 MILES
SOLID BOOSTER
RFNA-ANFA
120 LB
190 MILES
SOLID BOOSTER
RFNA-ANFA (151 5T4 &E)
rt e"rA
SOLID 11, 2 14 r-t
65 LB
FIN STABIL/ZED -
NO 011/017NCE
300 MILES
17-Z1700 91.009000W I?n0-C9dCla763110/ZOOZ eseeieu Jag PeAoiddv
P-Zi70091.009000VCI?C00-?9dati-VI3 : MBOMOU aseeieu JOd 130A0iddV
Weights, lb
Inert
Propellants
Launching weight (excluding payload)
Dimensions
Length, overall, in.
Body diameter, in.
Available payload volume, ft3
Sounding-Rocket Performance, 100-lb Payload
UNCLASSIFIED
SPECIFICATIONS AND PERFORMANCE PARAMETERS
515
628
943
205
14.0
up to 4.0
Zenith altitude, ft
Zenith altitude, 1111
Sustainer burnout altitude, ft
Sustainer burnout velocity, ft/sec
Stability Calibers, 100-lb Payload
Launching
Booster burnout
Sustainer burnout
Launching
Sea Level
358,500
68
77,130
4,327
Elevation
11..000 ft
3.7
3.5
1.5
423,000
80
86, !too
4,670
Ca AT SUSTAINER BURNOUT
OPTIONAL NOSE CONVIGER AT ION
ASSUMED PAYLOAD 100 LBS.
Ca. AT BOOSTER BURNOuT
72 00
92.58
123.:
27.4
175.13
198.98
AEROBEE - 75
til4C LASS! FIED
AEROBEE - 75
Approved For Release 2002/08/23 : CIANRINM-00313A000600150042-4
Name
90
r.?
4 Bo
70
6o
Burnout Altitude vs Payload
for Sea-Level and 4000-ft Launching Altitudes
ft
Sea
Level 7
100 120 140 160 180 200
Payload, lb
Burnout Altitude vs Payload
m for Sea-Level End 4000-ft Launching Altitudes
Zenkth Altitude vs Payload
for Sea-Level and 4000-ft Launching Altitudes
14000-ft Launch
5e-Level Launch
120 140 160 180 200
Payload, lb
Zanith Altitude vs Payload
For Sea Level and 4000-Et Launching Altitudes
,9 100
90
80
14000
ft
90
70
AEROBEE - 100
Sea
Level
60
A 50
60
A 1L4
AEROBEE - 150
AEROBEE - 300
130
Payload;.16
So 60 Bo 100
Burnout hit, lb 326 346 366 386
Burnout Altitude vs Payload
for See-Level and 4000-ft Launching Altitudes
4
-ft lat
ch
Sea-Level Lau
ch
.r?
120
140 160 180 200 220
Payload, lb
Burnout Altitude vs Payload
? 130
^ 120
11D
100
10 20 30 40
50 60 70 go 90 100 110 120
Payload, lb
180
170
140
480
500
? 350
300
250
200
I--
COO-ft launch
Sea Level Launch
Payload, lb
40
60
80
100
Burnout wt, lb
326
346
366
386
Zenith Altitude va Payload
for Sea-Leval and 4000-ft Launching Altitudes
4000-Pt Launch
Sea-Level Launch
-7
120 140 160 180 200 220
Payload, lb
Zenith Altitude vs Payload
--E?i 20
30 40 50 60 70 eo 90
laylead, lb
Approved For Release 2002/08/23 : 07-M1515613-00313A000600150042-4
110 110 120 130
Approvec, jeFor Release 2002/08/23 : CIA-RDP634p313A000600150042-4
ATLANTIC RESEARCH CORPORATION
ALEXANDRIA,VIRGINIA
C ONFIDENTIAL
Preliminary Dcaip Characteristics tot: iris RocKet
CalulpAt9d
I,.
Dimensions
A. 'Lengths (inches)
1. Oyer-all
2. Components
a. Motor
b. Nozzle (extension)
c. Nose Cone
3. Grain Length
Mod 2
Cylindrical
225.3
137.5
6.3
80.0
136.0
Mud 3
Tapered
225.8
137.5
d.3
80.0
136.0
NozIc
Head
B. Diameters (inches)
I. Motor OD
12.128
12.128
12.128
2. Motor ID
12.000
12.000
12.000
3. Insulation OD
11.995
11.995
11.995
4. Insulation.ID
11.600
11.600
13.900
5. Grain OD, inhibited
11.585
11.585
11.385
6. Grain OD, uninhibited
11.500
11.500
21.800
C. Thicknesses (inches)
1. Motor
0.064
0.064
0.064
2., Insulation
0.200
0.200
0.050
3. Inhibitor
0.050
0.050
0.050
D. Volume (cubic feet)
L. Nose Cone
4.14
4.14
II.atighps
(pounds)
A. Motor
1. Motor Case and Head
113.73
113.78
2. Nozzle
29.91
29.91
Ami
3. Insulation
59.69
30.25
B. Components
1. Fin Assembly
34.75
34.75
2. Nose Cone
12.10
12.10
C. Propellant
1. Propellant Grain
867.91
897.35
41,1
2. Inhibitor
10.44
10.58
0. Payload
1. Payload Weight
100,_00
100.00
Total
1228.58
1223.72
Mass Ratio (Motor)
0.1:"1
0.829
Mass Ratio (total)
0.707
0.730
NFIDEFITIAL
Approved For Release 2002/08/23 : CIA-RDP63-00313A000600150042-4
I.
tool
Approvad,or Release 2002/08/23: CIA-RDP6341,0613A000600150042-4
mid
ATLANTIC RICISiCAPICH
ALCKANORIA,VIRGINIA
ILL
CORPORATION CWIDEN'TIAL
.lud
Mod 3-
Tatered
Oneratine, Parameters
1200
46.6
1200 13Tj
45.9
A. Pressure psi.
B. &Amiga:lime sec
C. Thrust lbs
i 160
41W 4510
D. Mass DLscharge Rates lbs/scc
18.7
18.7 20.2
E. ProRellarkt
1. Type
Arcite 368
Arcito 368
2. Density lbs/ft3
0.062
0.062
3. Specific Impulse lb-sec/lb
223
4. Burning Rate in/sec
2.92
2.92 3.0C
5. Number of Wires
37
37
4110
F. Nozz4
1. Throat Area in2
2.19
2.1'4
2. Exit Area Ln2
22.06
22.06
3. Expansion Rats
10
10
4. Expansion To psi
14.7
14.7 15.9
IV.
Performance
A. Maximum Altitude
1. Miles
161.49
188.6
2. Feet
852,667
995,808
B. 2...s.2.11.1xiimpl_AWS.0.9. sac
274.53
289.2
C. Altitude at Burnout ft
113,491
120,663
ant
D. Maximum VO.ocity ft/sec
6,791
7,286
E. Initial Acceleration
2.38
2.38 '
F. Final Acceleration
11.45
12.82
C ONF.IDENTI-A L
4-23-58
Approved For Release 2002/08/23 : CIA-RDP63-00313A000600150042-4
Approved For Release 2002/Mbket-RDP6W313A000600150042-4
fris Sounding Rocket Outline Dimensions
45"
18.8'
SECRET
Approved For Release 2002/08/23 : CIA-RDP63-00313A000600150042-4
ago
ApprovvjeFor Release 2002/08/23 : CIA-RDP6329313A000600150042-4
ATI.ANTIC RESEARCH CORPORATICIN
ALEXANDRIA VIRGINIA
CONFIDENTIAL
Design Characteristics of Arcon Rocket
igtilagylpAA 40-lb Payload
I. Dimensions
(inches)
Over-all
Components
134
134
A. Lengths
1.
2.
it. Motor
99
99
b.
Nozzle (Extension)
5
5
c.
Nose Cons
30
30
3.
Grain Length
96.5
96.5
B.
Diameters (inches)
1.
Motor OD
6.094
6.094
2.
Motor ID
6.000
6.000
3.
Insulation OD
5.975
5.975
4.
Insulation ID
5.685
5.685
5.
Grain OD, inhibited
5.665
5.665
6.
Grain OD, uninhibited
5.500
5.500
C.
Thicknesses (inches)
1.
Motor
0.047
0.047
2.
Insulation
0.145
0.145
3.
Inhibitor
0.082
0.082
D.
Volume (cubic feet)
1.
II.Weights
Nose Cone
(*Measured)
450
450
A.
Motor
1.
Motor Case (integral head)
30.34*
30.34*
2.
Nozzle
8.40*
8.40*
3.
Motor Insulation
13.97*
13.97*
B.
Components
1. Fin Assembly (total)
11.50
11.50
2.
Boattail
1.50*
1.50*
3.
Nose Cone
1.85*
1.85*
C.
Propellant
1.
Propellant Grain
139.25*
139.25*
2.
Inhibitor
6.25*
6.25*
D.
Payload
1.
Payload Weight
10,00
40.00
Total (lbs)
223.06
253.06
Mass Ratio (Motor)
0.702
0.702
Mass Ratio (total)
0.595
0.552
CONFIDENTIAL
Approved For Release 2002/08/23: CIA-RDP63-00313A000600150042-4
ApproverofForRelease 2002/08/23 : CIA-RDP6340313A000600150042-4
ATLANTIC RESEARCH
ALEXANURIA,VIRGINIA
III.
CORPORATION
CONFIDENTIAL
9.U.S.P....4118..Mala..e..t.9.Ls
10-21LID2122i
40-lb Payload
A. Pressure Psi
1200
1200
B.
Burning Time sec
33.0
33.0
C.
Thrust lbs
945
945
D.
Mass Discharge Rates lbs/sec
4.24
4.24
E.
Propellant
1. Type
Arcite 368
Arcite 308
2. Density lbs/ft3
0.062
0.062
3. Specific Impulse lb-sec/lb
223
223
4. Burning Rate in/sec
2.92
2.92
5. Number of Wires
19
19
F.
Nozzle
1. Throat Area in2
0.545
0.545
2. Exit Area in2
5.45
5.45
3, Expansion Ratio
10
10
4. Expansion To psi
14.7
14.7
.1V.
Ferformance
A. Maximum Altitude
1. Miles
100.1
61.1
.
2. Feet
528,565
322,384
B.
Time to Maximum Altitude sec
203.9
162.5
C.
Altitude at Burnout ft
71,682
57,900
D.
Maximum Velocity ft/sec
5,426
4,194
E.
Initial Acceleration g
3.26
2.75
F.
Final Acceleration
10.51
7.30
CONFIDENTIAL
Approved For Release 2002/08/23: CIA-RDP63-00313A000600150042-4
Approv,w1 For Release 2002/Mt3RElp-RDP630313A000600150042-4
Arcon Sounding Rocket Outline Dimensions
' nominal
102.88"
14-0.9"
5.2"
133.81"
SECRET
Approved For Release 2002/08/23 : CIA-RDP63-00313A000600150042-4
tad
soil
aro
Approve*For Release 2002/f8KREIRDP631t4313A000600150042-4
ATLANTIC RESEARCH CORPORATION
ALEXANDRIA,VIRGINIA
Preliminary Design Characteristics
For Areas Rocket
I. Payload
A. Total (pounds)
1. Sonde
2. Parachute
3. Nose Cone and Parachute Housing
12
6.5
3.5
2.0
II. Dimensions
A. Lengths (inches)
1. Overall
73
2. Components
a. Motor
46
b. Nozzle
4
c. Parachute Housing
14
d. Nose Cone
9
3. Grain
44
B. Diameters (inches)
1. Motor OD 4.5
2. Motor ID 4.4
3. Insulation OD 4.4
4. Insulation ID 4.1
5. Grain OD, inhibited 4.1
6. Grain OD, Uninhibited 4.0
7. Parachute ilylar (ft) 24
C. Thicknesses (inehed)
1. Motor Wall
2. Insulation
3. Inhibitor
D. Volume (cubic inches)
1. Parachute Container 200
2. Nose Cone
0.05
0.15
0.05
112
Weights (pounds)
A. Metal Parts
1. Motor Case -10.0
2. Nozzle, 3.2
B. Insulation 5.6
C. Propellant 35
D. Inhibitor 1.2
E. Fins 1
F. Nose Cone and Payload (incl Parachute) 12
Total 68
SECRET
Approved For Release 2002/08/23 : CIA-RDP63-00313A000600150042-4
ApprovsfleFor Release 2002/SEEREIE-RDP63110313A000600150042-4
ATLANTIC RESEARCH CORPORATION
ALEXANDRIA,VIRGINIA
owl
- 2 -
Iv. Operating Parameters
A. Pressure (psi) Boo
B. Burning Time (secs) 25
C. Thrust (lbs) 375
D. Propellant Type rcite 373
E. Nozzle
1. Throat Area (in2) 0.255
Exit Area (in2) 2.55
3. expansion Ratio 10
V. Performance
A. Maximum Altitude
1. Miles 38
2. Feet 200,000
B. Time to Max Altitude (secs) 100
C. Altitude at Burnout (ft) 20
F. Typo of Launch Closed Breech
SECRET
Approved For Release 2002/08/23 : CIA-RDP63-00313A000600150042-4