CORONA PROGRAM HISTORY VOLUME V SYSTEM INTEGRATION

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP89B00980R000500110001-7
• Release Decision: RIPPUB
• Original Classification: T
• Document Page Count: 98
• Document Creation Date: December 19, 2016
• Document Release Date: January 12, 2006
• Sequence Number: 1
• Publication Date: May 19, 1976
• Content Type: RP

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CORONA HISTORY
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CORONA Project Officer
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Central Intelligence Agency
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PUBLICATION REVIEW ............................................
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TABLE OF CONTENTS ............................................
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DISTRIBUTION ................................................
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SECTION I - INTEGRATING CONTRACTOR AND DEVELOPMENT OF THE SYSTEM ...
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SECTION II - EVOLUTION OF THE CAMERA SYSTEMS ....................
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SECTION III - SECURITY AND FACILITIES ............................
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SECTION IV - THE AGENA VEHICLE AND THE THOR BOOSTER ...............
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SECTION V - CORONA OPERATIONS ...............................
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SAFSP Gen Kulpa
CIA/S&T C. Duckett
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CIA/Project Officer
NPIC J. Hicks
ITEK J. Wolfe
M. Morton
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In the early 1950s the Rand Corporation published a series of studies covering the feasibility and utility
of satellite vehicles. In 1955, as a result of these studies, the WS-117L Program Office was established,
and a one year competitive study for the preliminary design of an earth orbiting satellite was initiated.
Lockheed was the winner of this study. Starting in October 1956, Lockheed continued investigation and
research efforts on the development of space systems. This work was labeled "Project 97" and was funded at
a low level. However, with the Russian launching of their first Sputnik satellite in October 1957, the funding
emphasis changed. By early 1958, funding became available for a concentrated effort to develop a US military
space capability. As a result and as early as December 1958, the AGENA satellite became a reality.
When the decision was made to place one of the WS-117L photographic subsystems under covert manage-
ment, the Lockheed Missile and Space Company (LMSC), then a division of Lockheed Aircraft Corporation,
was selected as a prime contractor. This company was selected by the Advanced Research Projects Agency
(ARPA) and the CIA. The subcontractors to LMSC were Itek for the camera and the Space Re-entry Program
Division of General Electric for the recovery system. Lockheed was to supply the satellite vehicle (AGENA)
and the photographic payload system and was responsible for the command and control of the satellite during
launch and orbital operations. The early Lockheed contracts also included responsibilities for the launch and
tracking selection, test hardware, and vehicle integration. In addition to the THOR booster and the develop-
ment of the AGENA, the launch facilities, tracking stations, and communications were identified, the sites
constructed, and equipment installed in a period of 10 months. These achievements allowed for a launch
attempt in December 1958.
It was determined by the Program Office that all reconnaissance operations were to be developed in a
At that
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the program grew to a peak of over 251
time the scheduled life of the program was to be one year. This program was named CORONA. It became the
longest continuous space program ever conducted by the United States. The CORONA contract also included
provisions for tools, manufacturing space, and support personnel. In addition to the personnel assigned by
II
Lockheed provided management and technical specialists to the facility to set up an integrated and
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1 963 when the MURAL, LANYARD, ARGON, and J-1 payloads were in production. The number of
left assigned to the last designator for Project CORONA).
The AP Facility started in 1958 with approximately 3, 100 square feet of leased space, grew to nearly
78,000 square feet by 1965, and ultimately became the central point for the photographic payload system
technical direction, final assembly, and test and software preparation for command and control. There was
also a period when the orbital timer for the AGENA was received and prepared for launch at this building
because of the covert nature of the vehicle commands being punched into the memory tape.
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The CORONA Program was unique among space programs within Lockheed in that the full integration of
the space vehicle and its many payloads were the responsibility of the Program Office. This included technical
(mechanical, electrical, environmental, etc.), mission planning, launch, and orbital support.
Ito Willis Hawkins, then Assistant General Manager. Assisting
Research and Electrical Design;
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mi
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from 1967 - 1971; and
The AGENA satellite vehicle was produced in the Lockheed plant at Sunnyvale, California. In addition,
the well publicized biomedical recovery system was controlled in Sunnyvale since this capsule was part of
the cover story for the photographic capsule. Administratively, the Advanced Engineering Test (AET)
organization at the I (plant reported to the AGENA office in Sunnyvale. Some years later, the AET title
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I Mechanical Design and Fabrication.
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Program managers from Lockheed.
The success of any program depends upon the people employed and the atmosphere/conditions surrounding
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rom 1971 - 1972. Figure 1-1
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J. W. Plummer
(1958 - 1961)
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J. W. Plummer
(1958 - 1961)
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it. The CORONA Program was no exception. The covert environment of the program required that access be
rigidly limited for all organizations, Government as well as contractors. The added advantages of this closed
environment were highly motivated personnel, rapid and direct communications, and less unproductive
interference. Although the facility was managed by Lockheed, its organization included permanent Government
Iork force, and the Itek, Fairchild, and General Electric field crews.
In addition, the location of management and technical support was conveniently situated. The DISCOVERER
Program Office in Sunnyvale, Lockheed Palo Alto Research Laboratories, Itek West Coast Office, and other
subcontractors were for the most part close by.
Communication links to Itek in Boston, Fairchild in New York, General Electric in Philadelphia, Eastman
Kodak in Rochester, and to Government agencies in Washington DC and Los Angeles were available 24 hours
a day through special telephones and TWX lines. The problems which arose varied in magnitude over the
years and existed from the start of the program to the final launch; however, in each case the lines of
communication established early in the program were maintained and utilized to the final recovery. Rapid
and direct communication was a major contributor to the success of the CORONA Program.
In the beginning, no one was exactly sure how the task of reconnaissance from a satellite was to be
accomplished. Since this was one of the pioneer efforts there were no "experts" in this field. However,
as the result of the many achievements of CORONA, other programs that followed drew heavily upon the
experience and knowledge in designing, launching, and recovering satellite vehicles gained through the
development of the CORONA Program.
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integrated organization. In 1960, Lockheed divided its management personnel by project and the first
Program Engineering Manager (PEM) was assigned. The PEMs, in order, were
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Number 2. Figure 1-3 presents a picture of the last CORONA vehicle (CR-8) on the launch pad. So after
13 years and 3 months (145 AGENA satellite vehicles and 141 CORONA reconnaissance payloads), the era of
the first earth satellite photographic reconnaissance system came to an end.
Throughout its history the CORONA Program had several cover identifiers. Known for some time as the
"DISCOVERER" Program, it also had a series of numerical designators assigned by the Air Force; i.e. ,
WS-117L, 162, 241, and 846; and a number of internal Lockheed designators; i.e., WS-117L, DISCOVERER,
162, 241, andl
Lockheed, as prime contractor and integrator, was involved in all phases of the payload system from
camera and recovery system development to on-orbit command and control, and thermal control. Structures
for the payload system were fabricated in Sunnyvale which were similar to those structures being fabricated
for the biomedical payloads. The photographic payload structures were then diverted undercover to the AP
Facility for modifications. These modifications consisted of camera mounts, blow off doors that covered
the camera lens through ascent, and associated features required for the camera subsystems. Electrical
design and fabrication were accomplished either at the br under subcontract.
Engineering, Manufacturing, Logistics, and Associate and Subcontractor Offices within close proximity so
that the responsible engineers could be quickly available when problems arose in any of the manufacturing/
test cycles. Test data and mission analysis, with its supporting computer for command and control, were
also located in the AP Facility.
No formal quality assurance (QA) program existed during the early days "however each person was
constantly briefed on the importance of his individual responsibility toward QA. The first formal QA program
was established in 1961, and as the systems developed, the procedures for quality controlling operations
were formalized into standard specifications.
shaped office building ith an area of approximately 3, 100 square feet. The program continued
room facilities were moved into this new building which was located directly adjacent to IThe
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I was a "U"-
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well as procurement personnel, were located in these new buildings. The J-1 manufacturing facilities were
was terminated and the organizations
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realigned. In October 1964, the engineering, procurement, and manufacturing organizations were located in 25X1
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The test, integration, reproduction, and associate offices were located in
program, customer, finance, security offices, and the flight readiness clean rooms were located in
In parallel with the I I a building at the old Army tank overhaul facility at Vandenberg Air Force
Base (VAFB) was rehabilitated for final load and assembly of the payload system before launch. This building
was one of several occupied by Lockheed personnel at VAFB in support of AGENA launches. It was modified to
include a dark room for loading the system with flight film, a movable collimator, a small processing facility,
machines for weight and balance of the recovery capsule, and a sandbagged area for final gyro loading. A
small crew of cleared VAFB personnel manned the building to assistDPeople in readying the payload for
flight.
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Final checkout of the AGENA was accomplished in the Missile Assembly building adjacent to the AP
building. Since the AGENA was the on-orbit stable platform for the payload, as well as the second-stage
boost vehicle, many of the functions necessary to make the photographic system work were available.
The AGENA carried the batteries, command control system, and telemetry, as well as the guidance.
Because of the many wires crossing the interfaces, a compatibility test of the two systems was required before
each launch. These tests were conducted in the Missile Assembly building with the payload enclosed in a
small structure or "doghouse" to keep its true purpose covert. Some of the AGENA personnel were cleared to
work on payload function testing, and in fact many problems arising from these tests were solved by AGENA
and payload personnel working together as a team. It turned out that because of their knowledge that these
VAFB launch crews had as much to say about how things were accomplished during the flight preparations as
the designers at Sunnyvale and AP.
Because of the unknowns of space environment in the 1958 - 1959 era, a comprehensive test program was
acilities were completely equipped with a modern manufacturing setup and
engineering laboratory to support component and subassembly fabrication/testing and environmental testing
equipment and optical collimation facilities for system level testing. Th u Ifacilities were designed
to handle all but a few exceptional situations. These were the thermal/altitude testing chamber for the
complete system and the manufacturing of major structures. These operations were performed at Lockheed's
Sunnyvale plant.
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The evaluation/analysis data from tests and early flights resulted in many design and manufacturing
changes as the systems were being produced. The environment of the covert facility allowed scientists,
engineers, and technicians the freedom to develop new ideas, new methods of production, and to incorporate
rapid modifications not possible in large manufacturing plants. Ideas from technicians, bench assemblers,
or mechanics came as frequently as from the designers. This spirit motivated true teamwork rather than
individual effort.
The history and records of the first actual launch were deleted a long time ago as the attempt ended in
failure. A timer malfunctioned and the separation rockets, which at that time were attached to the aft rack
of the AGENA, ignited before the THOR-AGENA lifted off the pad. An approximate "six inch apogee" was
achieved and although still on the pad, the AGENA required major repairs and considerable redesign before
again becoming operational. Officially, the first CORONA/AGENA launch occurred on 28 February 1959 when
it was announced that the United States Air Force launched Vehicle 1022, the first of a new series of space-
craft intended to provide an orbiting vehicle with three-axis stability (earth-oriented) and the capability of
ejecting a recovery capsule and returning it to earth.
Systematic testing, which today is routine on most space programs, originated with CORONA. Since
high reliability components were not available early in the program, the philosophy was to test/debug at the
component level, then test/debug again at the black box level, once more at the subsystem level, and
finally at the system level. There were many problems of a major nature at the system level even after
resolving minor component problems. With these phase testing operations, the system level testing was
greatly simplified. The overall system reliability was significantly improved as experience was gained
through the years as evidenced by the spiraling success of system performance. The efficacy of this
philosophy can further be substantiated by a review of the thermal/altitude testing in 1968. Of the reruns/
retests required due to thermal/altitude problems on the system, less than five percent of the failures were
attributed to small components such as diodes, transistors, etc.
Itek, the camera contractor, maintained a field crew of camera experts at the n support of the 25X1
system. This group rapidly became part of the Lockheed team. Fairchild personnel attached to AP 25X1
also joined the team. During the early years, General Electric also had a field crew assigned but on NRO
1 July 1961 the recovery system test and checkout were assigned to Lockheed engineers and technicians.
Because of early design constraints and operational problems imposed by limitations of the boosters,
the designers were forced to eliminate as much weight as possible from the payload. The weight limit was
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a major design constraint. Qualification testing was limited to small margins over the predicted operational
conditions because of these restrictions. Light weight materials such as magnesium and its alloys were
utilized wherever possible. Even as the booster capability grew, these weight limitations continued to exist
since every pound that could be saved in structural construction meant more film could be flown. In the very
early days there were times when filing, chipping, and sawing away the excess were the only solutions.
The camera system design began with a major operational problem as a result of the space environment.
The film used in the first C cameras had a triacetate base and became brittle and disintegrated when driven
over rollers in vacuum. Numerous tests in thermal/altitude chambers at Itek and Lockheed were conducted
in an attempt to solve this problem. Roller adjustments were made, bobber rollers were designed and
installed, and many other ideas were attempted, but the problem persisted. What was even more frustrating
was that a system that passed the test on the ground would fail in flight. Itek and Lockheed both advised
the Government that this problem must be solved by the film manufacturer before successful camera operation
on-orbit could be guaranteed.
In 1960, Eastman Kodak was able to produce a polyester base film which they felt would hold the emulsion NRO
under vacuum conditions. Two spools of film were shipped On 15 April 1960, the eighth camera systerr25X1
(Camera C-14) was orbited, and successful operation of the camera was achieved utilizing one of these
spools. However, the film was not recovered due to spin rocket failures on the recovery vehicles.
As a result of this failure to recover Mission 9008, the Program Office directed that the program should
standdown until the recovery system was made operable. During this period it was discovered that the
Mark(MK) IIA Recovery System then in use had deficiencies. Hot gas rockets were used to spin and despin
the recovery vehicle but ground testing confirmed that the operational reliability of these rockets was low.
The internal batteries of the SRV were also unreliable (small mercury batteries soldered together), and the
event timing sequencer which was controlled by a mechanical timer was questionable from the standpoint of
both reliability and repeatability. Veiled by these negative elements, the Mark II system was discontinued.
General Electric next produced the MK II/MK IV satellite recovery vehicle which was equipped with
electronic event timing and more reliable batteries; however, it retained the hot gas spin rockets. In parallel
with the MK IV modifications, Lockheed engineers designed and produced a cold gas spin/despin system which
appeared would assure the true ballistic attitude necessary for recovery. Together, the two companies
engaged in an around-the-clock qualification program on this new subsystem. Lockheed also developed a
diagnostic event telemetry system for failure analysis which was also incorporated with the cold gas spin 25X1
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In June 1960, the first SRV with the cold gas system was launched but it failed to achieve orbit. A
backup system was readied and launched on 10 August 1960 and after 17 revolutions, was recovered from the
Pacific Ocean on 11 August 1960. This was the DISCOVERER XIII diagnostic package that became famous all
over the world as the first recovered object from outer space. On 19 August 1960 another milestone was reached
as the first successful air recovery/film package combination was achieved from Mission 9009. The CORONA
Program had successfully demonstrated that aerial reconnaissance on any desired area could be performed
from a satellite.
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Missions 9038 - 9041 (Cm-7 through Cm-10) nearly 50 percent of the recovered film was seriously degraded.
Extensive studies were made by the Lockheed Research Division on the types of materials/designs to be used
for shielding to protect the payload. As a result some of these designs were fabricated and used on a number
of systems. At the same time, testing in vacuum chambers isolated the rubber metering rollers as a medium
which was acting as a generator and discharging static electricity causing exposure markings on the film.
These electrostatic dendritic-shaped markings were aptly named "corona" discharge markings. Application
of an antistatic coating used on the rollers temporarily allowed flights to continue while experiments on more
conductive rollers were performed by Itek. Simultaneously, tests by Itek and Lockheed determined that the
discharges occurred predominantly in the pressure range of 10 - 100 microns. Ion gauges developed by
Lockheed were flown in each mission to correlate and substantiate the actual pressure on-orbit. Final
solution to the problem was achieved when Lockheed developed a pressure makeup system (PMU) from which
the system pressure on-orbit could be adjusted to a noncritical level depending upon the type of film flown.
On later J-3 flights, the PMU option was successfully utilized on the DISIC camera, as well as the panoramic
cameras.
With the pressure of meeting launch schedules, early test plans and procedures were mostly hand
written or "red-lined" as systems progressed. Team testing with system test personnel, camera and
recovery experts, and data analysts was utilized to assure continuity of testing. These teams picked up the
subsystems upon receipt at AP and conducted acceptance testing; assembled and tested the system;
transported the system to VAFB; launched it; controlled it on-orbit; removed the film after recovery; and
shipped it to its designated processing and duplication facility. In 1962, with the issuance of3tandard
Operating Procedures, the first standard and more formalized test procedures were produced. In 1964,
these test procedures were computerized.
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have the time and funds to build a qualification vehicle (QR-2). In fact, later in the program the QR-2 system
was refurbished and flown. Each system was subjected to environmental acceptance testing in vibration,
shock, and thermal/altitude simulation. Of all the testing, the thermal/altitude simulation became the most
valuable measure because it provided the best environment from which the overall system performance could
be effectively evaluated and predicted. When the factory to launch concept was instituted, this test became
the final acceptance test of the system prior to shipment to the VAFB launch site.
Meetings were held in the spring of 1965 between Lockheed, GE, Itek, SAFSP, and the CIA to examine
the feasibility of a CORONA improvement program. Failure modes and operational deficiencies of the existing
J system were studied as were coverage requirements, weather data, and overall system reliability data.
From these studies, a matrix of feasible system designs was developed along with all recommended designs
incorporating advanced panoramic and Stellar/Index camera systems and an improved command system. This
work led to the development of the J-3 system.
A "go-ahead" was issued in July 1965 to Douglas (THORAD), Fairchild (DISIC camera), and Itek for
manufacturing its Constant Rotator (CR) camera. However, delayed issuance of an approval to Lockheed and
GE until April 1966 resulted in a six month delay in the originally scheduled first launch of the J-3 system.
The first launch (Mission 1101) was rescheduled for 25 July 1967.
Schedules of critical design reviews, a qualifying test program, hardware deliveries, and system test
activities were established to meet this date. Final design reviews for the camera, SRV, electrical system,
structural aspects, and total payload were set for 23 August 1966, 7 September 1966, 7 October 1966,
17 February 1967, and 14 April 1967, respectively. All were conducted according to plan. Deliveries of the
camera systems and SRVs to AP were several weeks behind the target schedule; however, these time slippages
were made up during system testing. The J-3 qualifying program proceeded smoothly throughout the test cycle.
In early July 1967, it appeared as though the target launch date would be met; however, a corona marking
problem was uncovered on both the panoramic and DISIC cameras during thermal/altitude testing, and two High
Vacuum Orbital Simulation Chamber (HIVOS) test reruns were required. This delayed the first J-3 launch to
15 September 1967, approximately seven weeks behind the target date of 25 July 1967.
Any effort to name even those who made major contributions would result in a lengthy list. However,
in behalf, and representative, of all of the people who made CORONA the great success it was, photographs
are included as Figures 1-4 and 1-5 showing some of the personnel who worked on this program.
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C AND C PRIME (C') CAMERA SYSTEMS (1958-1959)
The original C camera was a scanning panoramic instrument with an oscillating lens cell. Seventy
millimeter film was fed from a supply spool through special drive mechanisms to a curved platen area where
it was exposed. The exposed film was then transported into a takeup spool in the recovery system. Before
ejection of the recovery system from the satellite, a cut and seal device closed/sealed the cover of the
recovery capsule to protect the film. The in-flight programmable camera and V/h ratio were fixed and
preselected prior to launch. The image motion control was fixed mechanically to the V/h ratio. Two Horizon
cameras were used for attitude determination. System time was recorded on the film by imaging the numbers
displayed on a system clock known as a Digitote.
The structure was a thermally shielded conical fairing with three pyro activated electable photographic
doors, light tight boots around the lens, and electrical harnesses as required. The recovery system was a
MARK IIA satellite recovery vehicle equipped with a single parachute, hot gas spin/de spin rockets, chaff for
radar detection, and a seawater dye marker for water recovery. The re-entry vehicle had a design goal
capacity for handling 20 pounds of film.
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compatible with launch and space environments. Weight limitations caused by booster structure/capabilities
were of prime concern. Light weight materials such as magnesium alloy, aluminum, and titanium were
utilized wherever possible. In 1959, load/stress testing in Sunnyvale, using early predictions of ascent
heating on a fairing, weakened the structure causing it to collapse. Further analysis led to design changes
which solved the problem. A major effort was put forth in developing a passive on-orbit thermal control
system to protect the camera and recovery systems. This effort became a controversial subject for years
between contractors and even between Government agencies.
A requirement to have an on-orbit command and control system with readout instrumentation for prelaunch
and in-flight status led to a subcontract with Fairchild. This contract was for the production of an orbital
programmer to control the events of the AGENA and the photographic payload. Checkout of this programmer
was originally accomplished at the but was later transferred to Sunnyvale and finally to VAFB.
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Early in the development of the system, many technical experts lacked confidence in the camera subsystem
through the boost/ascent phases. To counteract this lack of confidence, a research payload (named GRD)
was counted down in parallel with the first CORONA system in case a decision was reached to delay the
CORONA launch. Originally, the philosophy of flying the camera subsystem consisted of mating the photo-
graphic system, launching, and starting the camera on-orbit when desired. However, as failures continually
occurred, this philosophy changed. The camera was operated on the pad after mating to the vehicle to assure
proper tracking operation before launch. This method of certification remained an operational procedure
throughout the life of the CORONA Program.
The use of polyester film and the changes in the recovery system have been discussed in earlier volumes
and will not be repeated here. With the successful operation of the first system accomplished, it was
realized that many modifications were needed. Some of these changes included a V/h programmer to achieve
better forward motion compensation to improve resolution, and changes in the recovery system to increase
film capacity to 40 pounds. Lockheed continued to manufacture the cold gas spin system, the cutter/sealer
device, and to furnish the parachute. A schematic drawing of the C and C' payload is presented in Figure
2-1. Figure 2-2 photographically illustrates some of the final assembly phases of the payload subsystem
II
The C contract was awarded to Lockheed on 25 April 1958 for 12 systems. Figure 2-3 shows the
organizational structure that handled this contract from March 1958 to April 1961. Ten systems were launched
and two were delivered to the Government for storage. The first system was launched on 25 Tune 1959 and the
last on 13 September 1960. For those launched the status was: four failed to achieve orbit; four failed
on-orbit and no separation was accomplished; one separated but was not recovered (DISCOVERER V); and one
was successfully recovered.
The C' contract was awarded to Lockheed on 26 July 1959 for eight systems (later changed to eleven) .
Mission duration went up to two days. Ten systems were launched and one was delivered to the Government
for storage. The mission duration for C' was increased to two days. The first system was launched on
26 October 1960 and the last on 15 November 1961. Of these, four failed to achieve orbit; one separated but
was not recovered; and five were recovered.
Predicted performance of the C and C' systems at 125 nautical miles altitude was:
Coverage - 6,800,000 square nautical miles per mission
Resolution - SO-102 Film - 55 lines per millimeter
25 feet ground resolved distance
25X1
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Recovery
Capsule
Supply Spool -
(capacity 40lbs)
Rear Light Shield
Platen
Air Vent
Horizon Camera
Panoramic
Camera
24" Focal Length
f/5.0 Lens
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AFBMD
DISCOVERER Program
25X1
Payload Systems
Structures, and
Flight Support
Lockheed
Advanced Engineering
Testing
Itek
(Camera)
Douglas
(THOR)
General Electric
(SRV)
LMSD DISCOVERER
Program - AGENA
Launch, Tracking,
and Recovery
Support
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CORONA HISTORY
Volume V
ARGON SYSTEM (1959-1960)
In August 1959, a satellite mapping camera program called ARGON (CORONA-A) was started. ARGON
was primarily funded by the Army for the purpose of obtaining cartographic coverage. Lockheed was selected
as prime contractor and Fairchild Camera & Instrument Company and the General Electric Company as
subcontractors. Figure 2-4 outlines the contractual relationships involved in this program. The system
consisted of a pressurized mapping camera composed of a Geocon 3 inch focal length f/2.5 lens for the
terrain mission and a 3 inch focal length f/2.0 for the stellar mission. The two exposure times were
synchronized to one millisecond.
exposure by opening the back side of the platen to vacuum. Film was fed from the supply spool through drive
mechanisms to the terrain and stellar platens where it was exposed. It was then driven through a pressurized
film chute to the recovery vehicle takeup spool. Forty pounds of 3.0 mil mylar based, 5 inch wide film was
used on the system. Data recorded on the film included pitch and roll attitude (fed from the AGENA telemetry),
direction of flight indicator, shrinkage markers, optical fiducials, camera number, clock word, and vacuum
to platen status.
For geodetic purposes an accurate clock was required which was able to record simultaneous system and
telemetry time. Fairchild, under a subcontract to Lockheed, developed and produced the Digital Time
Interval Recording Clock for this purpose. Because of its accuracy and reliability this recording clock was
used during the CORONA Program from 1960 to 1972.
The MARK V recovery system was also pressurized. It had a capacity for a 5 inch takeup instead of the
70mm takeup used in the C system. Figure 2-5 is a schematic drawing of the ARGON payload subsystem.
The payload system was designed to operate at 165 miles altitude for six days, which was a significant
improvement from the C system that had a one day operation as its original design goal. The first ARGON
system was launched in February 1961; however, numerous anomalies occurred causing its failure. The
problems that surfaced with this program were the operation of the camera shutters and timers were inconsistent
and the booster unreliable. In addition, there was a problem from the pressurized system that had not been
anticipated and that was the residual gas left in the system prior to the recovery operation. In the operational
sequencing, separation of the bellows that connected the camera chute to the recovery vehicle was timed to
occur at the same instant that the recovery vehicle was separated for de-orbit. However, entrapped gas
pushed the recovery vehicle into a new orbit before spin-up, thus causing a perplexing situation for the
design engineers. Needless to say, on the next launch the system was depressurized before ejecting the 25X1
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Fairchild
(Camera)
General Electric
(SRV)
Douglas
(THOR)
LMSC
(AGENA)
LMSC General Electric Douglas
(Payload) (SRV) (THOR)
LMSC
(AGENA)
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Fairchild
(Camera)
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ARGON PAYLOAD SUBSYSTEM
1 Millisecond
Synchronization Clock
`Ablative Shield
W Recovery Capsule
!~1 (pressurized)
M Cassette
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CORONA HISTORY
Volume V
recovery system. After these problems finally were resolved or suppressed, an ARGON system was launched
and recovered successfully in May 1962. The first ARGON system was launched on 17 February 1961 and
the last of this block of systems on 29 October 1963. Ten systems were launched of which three failed to
achieve orbit; two failed to separate; one separated but was not recovered; and four were recovered.
A follow-on ARGON contract was awarded on 23 September 1963, retroactively effective 15 July 1963, for
four systems. Under this contract the camera systems were furnished by Fairchild and the SRVs by GE, while
E1urnished electrical boxes and structures and acted as integrating contractor. The first of these follow-on
systems was launched on 19 June 1964, and the second on 21 August 1964. Both capsules were successfully
recovered. The other two systems were sold to the Government in an "as is" condition, the first on
4 September 1964 and the second on 22 September 1964. Both of these systems were returned =and were 25X1
packed and shipped to Government storage.
The predicted performance of the ARGON system at 165 nautical miles altitude over the prime mapping
objective area (80?N to 55?S latitude) was:
Terrain Resolution - 330 feet ground resolved distance
Stellar Resolution - 515 magnitude stars
Locational Accuracy - 700 feet
C TRIPLE PRIME (C"') System (1960-1961)
It was soon realized that there was little potential for future improvement of the C' Program and as a
result an Improvement Program Committee was established. This committee consisted of representatives from
the Government, Lockheed, General Electric, and Itek. Meetings were held and design goals established
centering around increasing the operational reliability and improving the photographic quality through changes
in the panoramic camera system. Two proposals, referred to as C-61 or the C" (Double Prime) system, were
forwarded to the CORONA Program Office for consideration in early 1961. These two designs were proposed
by Itek and Fairchild Camera and Instrument Company. After many negotiations, decisions, and even a
cautious start on Fairchild's concept, Itek's proposal was selected and became known as the C"' (Triple
Prime) system. At that point all references to C" were cancelled. The C"' contract was awarded on
27 June 1960 for six flight systems. The first launch was on 30 August 1961 and the last on 13 January 1962
with the following results: one failed to achieve orbit; one failed on-orbit; and four capsules were recovered.
It should be noted that the camera subsystems utilized under the C, C', C"', and ARGON Programs were
single camera subsystems which furnished only monoscopic photography. However, starting with the MURAL
and J Programs a dual camera subsystem was utilized which was capable of obtaining stereoscopic photography.
TOP SECRET 25X1
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CORONA HISTORY
Volume V
The C"' camera was a single scanning panoramic instrument with an oscillating element in the optical
system. It was designed to operate at 100 - 110 nautical miles altitude and to achieve resolutions of
80 - 110 lines per millimeter. The supply consisted of 40 pounds of unperforated thin base 3.5 mil mylar
70mm film. The film was fed from a lightweight supply spool through drive and metering mechanisms to a
curved "rail" structure where it remained stationary during exposure. The lens cell scanned past the rail to
image the coverage on the film. The film was then fed to a takeup cassette in the recovery subsystem. Image
motion compensation (IMC) was accomplished by a mechanical cam which caused the lens system to move
opposite the direction of flight during scan and then return for the next cycle. Two Horizon cameras with a
90mm focal length and a shutter speed of 1/200 second were used for attitude determination.
The main camera lens was a 24 inch focal length f/3.5 Petzval type system designed for a 70mm slit
format. A preset slit width and a Wratten 21 Filter were used. Exposure time was determined by the motor
speed which was controlled by the V/h input derived from one of the ten selectable levels programmable by
a real time command.
Time was recorded on the film by registering the binary numbers displayed from the system clock. Time
marks of 200 cps, fiducial marks, the camera serial number, a center of format marker, and shrinkage
markers were recorded on the edge of the film.
The preset tape-stored commands included camera on-off, V/h stepping, and recovery. The real time
commands were V/h starting and recovery commands. Telemetry data reported status for V/h readout, voltage,
film footage, light leak sensors, temperature, and other operational and diagnostic information.
The payload structure consisted of a passive, thermally shielded conic fairing housing for the camera,
film supply, light tight boots around the lenses, electrical harnesses, and instrumentation, see Figure 2-6.
There were three optical doors which were designed to blow off during ascent. The SRV was attached to the
fairing. A single recovery system, MARK IV, with a dual parachute and a cold gas spin/despin system was
used. An AGENA served as the second-stage and orbital stable platform, while the THOR was the booster stage.
MURAL SYSTEM (1961-1962)
MURAL (M) was the first stereo camera system in the CORONA Program. Two 24 inch focal length
panoramic cameras were mounted in a 30 degree convergent stereo angle. The 70mm film was fed from a
double spool film supply cassette with one of the two film webs going to each panoramic instrument through a
twisting system of drives, rollers, and clamps. The film was exposed through 70 degrees of lens cell angular
rotation and then fed to a double spool takeup cassette in the SRV. Simultaneous operation of both instruments
was required for stereo photography. Figure 2-7 presents an illustrated profile of the M payload subsystem.
25X1
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Platen
Horizon Camera
Supply Spool
25X1
Re-entry Body
Capsule Cover
Thermal Cover
Pin Pullers -'
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MURAL PAYLOAD SUBSYSTEM
Camera Mount
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Panoramic
Cameras
24" Focal Length
f/3.5 Lens 11
700 Scan Angle
Vertical
Framing Camera
Clock
1 Millisecond 1! i
System Time Correlation I I
(accuracy 1 x 10-8)
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CORONA HISTORY
Volume V
Prime attitude information was provided by one Stellar/Index camera utilizing 70mm film with a 1.5 inch
focal length f/4.5 lens for index (terrain) information and 35mm film with an 85mm focal length f/1.8 lens for
attitude (stellar) information. Backup attitude information was provided by the Horizon cameras with a 90mm
focal length f/6.8 lens.
The system was designed for nominal altitudes of 110 nautical miles with a mission duration of up to four
days. Dynamic resolution was designed to be 80 to 110 lines per millimeter.
With the incorporation of a stereo system, modifications were required on the command/control,
instrumentation, and telemetry systems. Incorporation of the Stellar/Index camera subsystem created real
problems on the MURAL Program because it was continuously plagued with failures and breakdowns.
The MK VA recovery system utilized was nonpressurized and capable of handling up to 80 pounds of film.
Basically, this recovery system was utilized throughout the balance of the CORONA Program.
On Mission 9051 (Cm 18) the orbiting vehicle did not pitch down properly for separation. As a result the
recovery capsule landed in the ocean approximately 1, 000 miles from its predicted impact point. Both the
beacon and telemetry antennas burned in half due to very high re-entry heating, but the recovery aircraft were
able to maintain tracking. The capsule was actually sited in the evening, but it was felt that it was too late
to attempt a recovery from the water at that time. A decision was made to monitor the drift of the capsule by
the beacon signal and make the pickup the next day. Some time during the night the beacon signal disappeared,
and it was assumed that the battery had reached its limit. Luckily, searching aircraft located the vehicle the
next morning floating upside down by means of seeing the reflections of the sun off the gold thermal covering
of the capsule. The capsule was retrieved and all 78 pounds of film saved. However, a new problem had
emerged and that was the instability of the capsule while in the ocean. Lockheed designed a swing down
ballast to keep the capsule upright even in heavy seas. This swing down ballast was utilized throughout the
T-1 Program.
The first M flight system was launched on 27 February 1962 and the last on 21 December 1963. There
were 26 systems launched with the following results: two failed to achieve orbit; four capsules separated but
were not recovered; and 20 capsules were recovered. Performance of the MURAL system exceeded design
specifications. When operating at 125 nautical miles altitude, stereo coverage totaled 6,800,000 square
nautical miles, and the system achieved a resolution with SO-132 Film of approximately 125 lines per millimeter
and ten feet ground resolved distance. 25X1
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TOP SECRET
CORONA HISTORY
Volume V
25X1
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CORONA HISTORY
Volume V
LANYARD SYSTEM (1962-1963)
The LANYARD (L) camera system contract was awarded on 2 August 1962 for five satellite reconnaissance
systems with stereoscopic photographic capabilities. The camera subsystems were furnished as GFE by Itek,
an associate contractor, and the SRVs by GE, another associate contractor. The contract also stipulated that
Advanced Projects should furnish systems engineering for the Government through August 1963. The number
of flight systems was later contractually increased from five to eight, and the systems engineering period of
performance amended to cover the period of 22 February 1962 through 31 October 1962. Figure 2-10 shows
the contractual relationships for LANYARD. The system design goal was to achieve ground resolution of four
to five feet at an altitude of 112 nautical miles for a duration of four days.
Both stored and real time commands were utilized for system decoder and recovery operations. The
decoder selected operate programs and controls a roll joint. Telemetry provided channels which were con-
tinuously transmitting diagnostic and operational data.
The L system was a panoramic spotting camera with an oscillating lens cell viewing a large mirror which
was pointed at a 450 angle toward the earth. Movement of the mirror enabled the system to produce stereo or
mono photography. The 5 inch film was fed from a supply spool (capacity 8,000 feet or 80 pounds) to the
V0 platen for exposure and then to a takeup cassette in the recovery system. The effective focal length of the
optical system was 66 inches.
The time word (from a data head driven by the digital recording clock generator) and other data on attitude,
roll steering, and rate were imaged on the film. The system included a Stellar/Index camera which provided
pitch and roll information and tracking correlation for the panoramic camera. The payload structure consisted
of a 60 inch barrel and a fairing. On the aft end of the barrel was a counter-balanced roll joint enabling the
entire payload to rotate by command to the various pointing angles. All structures were thermally shielded.
A modified MK VA recovery system was used with a double parachute and cold gas spin system. The AGENA D
served as the second-stage and orbital stable platform, and the Thrust Augmented THOR (TAT) was the booster.
A schematic drawing of the L system payload appears as Figure 2-11.
On 23 October 1963, the contract was curtailed, and the number of flight systems was reduced from eight
to the three which had already been launched. The results of those missions were: the first (18 March 1963)
failed to achieve orbit, but the second and third (18 May 1963 and 30 July 1963) were both successfully
recovered.
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25X1
 { Approved Fat Release 2006/41/30 : CIA-RDP$9.B0098bR0005t01100(t'1-7
25X1
LM SC
Integration,
Structures,
Flight Support
Itek
(Camera)
General Electric
(SRV)
Douglas
(T HO R)
LMSC
(AGENA)
Launch,
Tracking, and
Recovery Support
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 I i I
r ------ i--
~
LM SC
25X1
Itek
Integration,
(Camera)
Structures,
Flight Support
I Approved Fot Relea* 2006/(1/30 : CIA-RDP$9B0099OR0005601100011-7
LANYARD AND JANUS CONTRACTS' ORGANIZATIONAL STRUCTURE (Nov 62-Aug 64)
General Electric
(SRV)
Douglas
(T HO R)
LMSC
(AGENA)
Launch,
Tracking, and
Recovery Support
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LANYARD PAYLOAD SUBSYSTEM
Stellar/Index Instrument Top View ~- o. Side View
Roll Joint J
(00 + 15? + 30?)
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CORONA HISTORY
Volume V
The L system was operated on the second and third flights at approximately 90 nautical miles altitude and
produced best ground resolved distances of 5.5 feet on SO-132 Film. The ground coverage varied from
660,000 to 1,320,000 square nautical miles dependent on the relationship between the monoscopic and stereo-
scopic operations.
With the stereo capability of the MURAL Program proven and the longer life of components and subsystems
now possible, the next goal for the reconnaissance satellites was to increase film capacity. With this in
mind, the JANUS (J) Program was conceived. The first system in the JANUS series was called the J-1, which
was designed with a dual re-entry payload. Research had been going on since late 1962 at AP on this type
system. Finally in March 1963 approval was given to have the same organizations that worked on LANYARD
develop the J-1 system. Figure 2-10 shows the contractual structure. This system became the work horse of
CORONA. Fifty-two systems were launched, with the first in August 1963 and the last in September 1969.
The mission duration grew from five to a fifteen day life cycle. Design also included a deactivate period
mode (Zombie) so that the system could be stored on-orbit for up to 20 days between recoveries if desired.
Major redesign of the command and control subsystems, the pyro subsystems, and telemetry was required
to accommodate the expanded operational requirements. For some period the decision on how to transfer one
recovery capsule to the other was unresolved, with technical experts backing both the cut/splice and cut/
wrap techniques. It was finally proven on the J-1 and J-3 systems that the cut/wrap technique was best.
The cut/wrap technique was used on the follow-on programs.
Two major problems emerged during the initial assembly stages of T-1. One was a film tracking
problem through the system and the second was the cut/wrap sequence. The fourth model of this system was
taken off the line and utilized as a test bed to solve these problems. The combined effect of redesigning the
rollers, making critical adjustments, changing the "B" takeup electronics, and the dedicated skill and
knowledge of the test personnel resulted in the successful solution of these problems.
With the increased on-orbit life of the system, the success of recovering the "B" (second mission
segment) capsule became jeopardized due to the limited life of the pre-activated recovery battery. A new,
longer capacity battery was developed to overcome the long idle time encountered, this battery was named
"Dreamboat. "
With the intelligence community continuing to request more information, the J systems were launched at a
rate of better than one a month during 1964 and 1965. In 1966, the number of launches were reduced to nine. 25X1
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CORONA HISTORY
Volume V
In April 1965, Itek was awarded a contract to provide a pan-geometry (PG) capability for the J-1 cameras.
This would allow the mapping and charting community a means to more accurately determine the geographic
location of targets on CORONA photography. PG consisted of providing "rail holes" with an appropriate light
source (lamps) so that a reseau could be determined and an IMC trace imaged on the panoramic camera film.
Using calibrated data from the cameras, the cartographic community would then be able to reconstruct the
internal geometry of the camera system. A design goal was to have the accuracy of producing maps in the
1:50,000 scale range.
In September 1966, the first CORONA pan-geometry mission was flown. The results were generally
favorable but insufficient to allow the user community to conduct a statistical evaluation. However, the
second flight in November 1966 gave sufficient data for a user evaluation, the results were a mixed lot of
pros and cons; but the decision was to keep flying the PG subsystem.
The success of the J-1 Program can be measured by its results. Of the 52 systems launched, two systems
failed to achieve orbit (four capsules); six capsules were not recovered; while the remaining 94 capsules were
recovered. The 1-1 system, at 125 nautical miles altitude, produced 13,600,000 square nautical miles of
stereo coverage per mission and achieved ground resolved distances of 10 feet and resolutions of 125 lines
per millimeter.
A schematic drawing of the 1-1 system is presented in Figure 2-12. Figure 2-13 is a photograph of the
J-1 system in the process of going through a portion of the "vertical" testing.
The next operational phase of the TANUS series was the J-3 system which was designed to acquire
improved stereoscopic photographic reconnaissance for intelligence information; provide a base for
establishing a means to evaluate the correlation between cartographic and geodetic sources; and to
photograph special items of interest. These special requirements might include different types of
films (high resolution, color, camouflage detection) for use in determining the geologic, economical, as
well as military potential of a given area of interest. Another system was being designed during the same
time period as the J-3 research/proposal stage. This system, designated as J-2, consisted of a J-1
panoramic camera, a Dual Improved Stellar Index Camera (DISIC), and an improved THORAD booster.
However when approval was given for complete development and implementation of the 1-3, all work and
reference to the J-2 configuration was terminated.
25X1
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Segment-2
Recovery supply spools
System i- Film Path --. (capacity 180 lbs of SO-132)
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(X)I:ONI\ 111STUkY
Volume V
25X1
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CORONA HISTORY
Volume V
The J-3 (Constant Rotator) camera system consisted of two panoramic instruments, each with a constant
rotating lens cell, mounted at a 30 degree convergent stereo angle. The 70mm film was fed from a double spool
film supply (capacity 16,000 feet or 160 pounds) with one of two film webs going to each instrument through a
system of drives, rollers, and clamps. The film was panoramically exposed through 70 degrees of lens cell
angular rotation and then fed to a double spool takeup cassette in one of two SRVs. Simultaneous operation
of both instruments was required for stereo photography. IMC was provided by a "nodding" cam proportional
to the scan rate. The scan period was proportional to V/h, and a V/h programmer provided an in-flight
adjustable sinusoidal voltage to assure the correct scan period. The J-3 camera subsystems contained the
capability of panoramic geometry for mapping and charting.
The design goal for film utilization included the capability to accommodate infrared, high speed black
and white, color, and ultra thin base (UTB) films. Although the film normally used was 3404 black and white,
UTB was planned for use effective with the fifth system.
The main lens was a Petzval 24 inch focal length f/3.5 optical system. The exposure time could be varied
in-flight by selecting one of four slit widths, plus a "failsafe" capability. The DISIC employed 35 mm film
and dual side-looking 3 inch focal length, f/2.8 lenses. Index (cartographic) coverage was provided on
5 inch film with a 3 inch focal length, f/4.5 lens. Backup attitude information was provided by the horizon
cameras with a 55mm focal length, f/6.8 lens system.
Time data was recorded by a silicon light pulser (solid state) driven by an electronic digital recording
clock generator. Additional flight data was recorded by the conditioning of conventional pulsing or switching
circuits. A recoverable tape recorder was used to provide the "center of format" times for each frame.
The command and control consisted of stored commands for on-off and recovery operations, and real time
commands for system conditioning. Later 1-3 configurations were equipped with a new command system
utilizing a digital shift register for increased operational capability and flexibility. Telemetry consisted of
commutated, multiplexed, and continuous data transmitted via the AGENA TM system. The J-3 system was
designed to operate at 80 - 100 nautical miles and to produce ground resolutions of 5 - 6 feet.
The major improvements of the J-3 system were:
A. Constant Rotator Panoramic Camera
1. Removal of camera system oscillating members and reduction of error budget vibration
2. Improvement of V/h match from 5 percent to 1 percent.
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CORONA HISTORY
Volume V
the uncertainties of being able to consistently operate on-orbit with UTB
6. Exposure control through variable slit selection.
7. On-orbit filter selection capability.
8. Capability of handling alternate film types and split film loads
9. Improved lens performance.
3. Proper camera cycling rates at altitudes down to 80 nautical miles (minimum J-1 altitude was
100 nautical miles).
4. Elimination of camera failure caused by film pulling out of rails (two such J-1 failures were
experienced on-orbit).
5. Capability of handling ultra thin base (UTB) film. An increase of 50 percent in coverage at
no increase in weight. Partial UTB loads were flown experimentally during early J-3 flights, and one complete
flight (Mission 1105) was flown. However, this goal was never fully achieved because of film handling and
10. Pan-geometry without effect on imagery (J-1 systems required IMC traces in the format area).
B. DISIC
1. Improved Terrain camera performance (increased focal length 1.5 inch to 3 inches) .
2. Independent mapping capability.
3. Improved shutter reliability.
4. Removal of Stellar launch window restrictions (J-1 launch windows were governed by Stellar
C. All Systems
1. Removal of limited shelf life items.
2. Removal of items affecting R-1 readiness capabilities.
3. Reduced power requirements.
The payload structure consisted of a 60 inch diameter instrument barrel, DISIC conic section, fairing,
pyro actuated doors, light tight boots, and miscellaneous operationally linked items. Both recovery systems
were the General Electric MK V SRVs with sink valves, water seals, parachute, beacon, flashing light, and
other standard equipment. The recovery battery was changed from a prelaunch activated battery to a pyro
operated battery activated just prior to recovery. Storage characteristics of this battery allowed it to remain
on the shelf up to three years before being utilized. The management organizational structure for the T-3
system contract is illustrated in Figure 2-14. Figure 2-15 presents a photograph of views of the camera
system and the payload.
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LM SC
Integration,
Structures,
Flight Support
Itek
(Pan Camera
General Electric
(SRV)
Fairchild
(DISIC)
Douglas
[THORAD (TAT)]
LMSC
(AGENA)
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Launch,
Tracking, and
ecovery Suppo
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CORONA HISTORY
Volume V
25X1
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CORONA HISTORY
Volume V
Seventeen J-3 systems were purchased. Within these 17 was the first system in the CORONA
Program to be built and dedicated for qualification testing. This system, QR-2, was later refurbished and
flown. Of these 34 capsules, all were recovered except two (one system) which were lost when the THOR
booster failed during the launch. Figure 2-16 is a schematic drawing of the J-3 payload.
These systems with lens improvements, better thermal and focus control, and a digital command system
significantly improved the performance of the CORONA systems. This was substantiated by the Mission
Information Potential (MIP) ratings derived by the National Photographic Intelligence Center (NPIC) which
increased from 100 to 125.
The J-3 Program was scheduled for completion in 1970, but its replacement encountered many development
problems and the Government had to resort to continuous "stretchouts" to provide the required reconnaissance
coverage until the new program was fully operational. As a result, much of the hardware fabricated in 1967,
1968, and 1969 was "stretched" beyond its specified operational life. It was only through continuous testing
and refurbishing that the hardware was made acceptable for flight. The final system (Mission 1117) performed
on-orbit without an anomaly.
DUAL IMPROVED STELLAR INDEX CAMERA (DISIC) SUBSYSTEM (1964-1972)
The DISIC subsystem was designed to provide exposed film for use in precision geodetics and cartography
and, in conjunction with the J-3 cameras, to aid in establishing vehicle attitude and precise location of
reconnaissance points of interest. Figure 2-17 illustrates the configuration of the DISIC system. Figure 2-18
presents a photograph of the cross-section of a DISIC Conic with the RV installed. Table 2-1 lists the physical
characteristics of the DISIC subsystem.
Lens
Lens Aperture
Film Format
Angular Coverage
Lens Distortion
Terrain Camera
3 inch Ikogon
f/4.5
4.5 by 4.5 inches
74 by 74 degrees
30 microns (R)
5 microns (T)
By glass plate
Stellar Camera
3 inch Ikotar
f/2. 8
1.25 diameter with flats
232 degrees
15 microns (R)
5 microns (T)
By glass plate
25X1
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CORONA HISTORY
Volume V
2.5mm spacing
2.5mm spacing
10 microns maximum width
10 microns maximum width
Reseau Illumination
Natural
Artificial
Natural Fiducials
1 set of four
1 set of four
Shutter Type
Rotary
Rotary
Selective Exposure Time
1/250 second
1.5 seconds
1/500 second
Cycle Period
9.375, 12.50, 15.675 and
3.125 seconds (Mode I)
18.75 seconds (last two
same as Terrain (Mode II)
not on CR-1 through CR-6)
Dual Stellar Operation
Simultaneous or by selection
Knee Angle
100 degrees
Data Recording
Time and serial number
Time and serial number
Film Type (normal)
3400
3401
Width
5 inch
35mm
Total Capacity
2,000 feet
2,000 feet
Metered Length
5 inches
3 inches
25X1
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Main Intermediate Roller Assembly
Film Path Fairing Pan Cameras
Pan Takeup Cassettes T r- DISIC Conic Pressure Diaphragm
25X1
"A" SRV L "B" SRV I DISIC Camera I "Pan Boots
Delta Structure
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DISIC SYSTEM CONFIGURATION
DISIC Water Seal
Roller Box
Film Chute
Separation
Cut & Splice / r- DISIC Camera
-} EARTH
Stellar Baffle
Film Supply Cassette
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 Approved For Release 2Q ?l c f RDP89B00980R000500110001-7
(( )[ (DNA IIIS'CC~RY
Vollllne V
I . ;,i Ib r~ c [,'I
7. .. I'vro I 3c,~ wlu, i, 1'ran" fr,r; "A" ,~egmcnt tc? "13" ,;c~~ ncn~
L I'i,ansl 'r
,I I'an C in, i Iii ['aL}is to take ip Cassette
5 ',vo k Ltl irc NI1 cup System
[i it ai i . )tic-,, ,cha iism (TUNA)
ILLEGIB
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CORONA HISTORY
Volume V
25X1
NRO
in April 1958, a 25X1
strict security control was established to keep the numbers of individuals to the absolute minimum necessary NRO
to produce and operate the CORONA Program. Figure 3-1 presents a diagram of the interior and exterior
security of the complex. Various cover stories were initiated to keep the personnel who were working on
the WS-117L Program from knowing that such a project as CORONA even existed.
Initially, it was believed that the biomedical launching and recoveries would provide an adequate cover
story. One operational plan that was tried was when a reconnaissance mission was scheduled then the camera
subsystem would be substituted for the biomedical equipment just before launch. The technical problems of
integrating the CORONA payload and the AGENA, however, required that system tests be conducted with the
two electrically mated, and thus this plan was not feasible.
Since the system test between the payload and AGENA was conducted in an atmosphere of both cleared
and uncleared people in the Missile Assembly building at Vandenberg Air Force Base, several methods were
employed to cover the true purpose of the payload.
A small portable building called the "doghouse" was constructed to cover the payload during the test,
with CORONA cleared personnel always present when the payload was in this building. Since the operation
of the payload created heat in this small building, a vent fan was installed. To cover up the noise of the
payload operating under test, one blade of the vent fan was bent so that it ticked against the guard as it
turned, thus creating enough noise to cover the camera operation. VAFB maintenance personnel could never
understand why the payload people did not want the fan fixed.
counter down to the launch pad when the mating of the payload to the vehicle was being accomplished. This
caused consternation among the launch crews and especially the safety personnel, but it did serve the
purpose of cover.
One of the major security concerns was the fear that one of the recovery capsules might be recovered
from the ocean by some other country and the contents publicized. Therefore, a device called a sink valve
was designed and fabricated This valve would slowly dissolve causing the capsule to sink if it had
not been recovered after a time period varying from 48 to 90 hours in the ocean.
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25X'1'NRO
CORONA HISTORY
Volume V
0
not to talk and they honored and followed this direction. Questions and speculations by uncleared people
were usually met with "no comment" and this response seemed to close the subject. After 12 years of covert
hardware was moved out for safety and security reasons in case the plant was broken into. At this time, it
was feared that the true mission of the personnel employed there might become revealed to the news media,
but it was not.
25X1NR0 When the
o
25X1
NRO
iad a strike called by the union representing their people, the cleared ieople 25X1
25X1 N RO manned the picket line in front of the I
25X1NR0 continue. When the strike was over and the
25X1NRO what had been accomplished at while the main)
25X1N R0
nd allowed free access to Lockheed people so work could N RO
Fairchild personnel did not show up when these "flare-ups" occurred as it was feared that someone might
recognize them and identify their company affiliation.
A security problem that arose in shipping hardware to VAFB was the transportation of explosives. VAFB
rules stated that any truck transporting explosives and requiring access to the base must be escorted by the
Provost Marshal and the necessary red lights and sirens. When the factory-to-launch sequence was started
retrorockets and their ignitors and door ejection gyros were installed; therefore, to comply with VAFB
rules, access to the base could not be accomplished without an undesired escort. The following was the
solution of this problem: to conform to the State Safety Code, a permit to transport explosives was obtained
from the California Highway Patrol; and to circumvent the VAFB restrictions, a set of removable explosive
signs were fabricated for the truck. The payload system was loaded onto the truck at D Without signs.
The truck would then be driven to another building in Sunnyvale where the explosive signs were installed.
The truck, with escort, would then be driven legally down the highway until it was near VAFB when it was
diverted to a side road and had the signs removed. The "clean" truck would then be driven onto VAFB to the
"L" building as a common carrier delivering freight. Figure 3-2 shows photographs of some of the phases and
the transportation permit involved in shipping hardware from AP to VAFB.
guard force provided protection against penetration. These fences were expanded and strengthened in
25X1
NRO
NRO1
between Government agencies and contractors. A covert TWX facility and telephone lines provided rapid
communication. All purchasing, procurement, and shipping were conducted under security cognizance in order
that the location of the facility or its functions were not revealed. Fences around the facility and a 24 hour
25X1
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CORONA HISTORY
Volume V
25X1
NRO
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CORONA HISTORY
Volume V
25X1NRO security of this program. Photographs of the
- Figures 3-3 and 3-4.
25X1N RO
1NRO
w
25X1NRO
25X1 NRO
NRO
25X1
In 12 years, there were 139 flight systems engineered, manufactured, tested, and flown from the 25X1
facilities. In July 1970, the CORONA Program was relocated fro
The actual movement of the company went smoothly. The success
of this transfer can be attributed to extensive preplanning and coordination. One of the major concerns during
this move was personnel. This concern included maintaining trained personnel for the final launches and
placement of the dedicated
(work force. After the transfer of I
as the only group of ~ersonnel remaining in the complex.
Pperations to
the move, essentially all of the 1::Jersonnel were placed in positions where their CORONA training could
~ad trained and experienced manufacturing personnel and the facilities and equipment to perform
NRO
25X1
25X1
NRO
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A. Precision machining of detail parts including lathe turning, milling, drilling, grinding,
polishing, etc.
B. Fabrication of sheet metal parts including sawing, cutting, braking, rolling, bending, drilling,
etc. Such items include various detail small parts, mounting brackets, doublers, stiffeners, shims, gussets,
etc., and many mockup and special test parts.
C. Molding and vacuum or hot forming rubber and plastic parts such as gaskets, seals, O-rings, etc.
D. Bonding with various adhesives and epoxies many different types of materials including metal,
wood, fiberglass, plastics, and rubber.
E. Assembly and installation of parts into subassemblies and final assembly including such
operations as fitting, riveting, bolting, match-drilling, etc.
F. Assembly, maintenance, and repair of various types of tooling and AGE including dollies,
console frames and enclosures, slings, handling fixtures, shop tooling, jigs, and fixtures.
NRO
25X1
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CORONA HISTORY
Volume V
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.1 NRO
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CORONA HISTORY
Volume V
G. Sanding, polishing, sand-blasting, and other methods of preparation of material surfaces for
application of finishes. Preparation, mixing, application, and curing of various finishing compounds including
primers, paints, epoxies, alodyne, etc.
H. Fabrication of electrical junction boxes including all details such as terminal boards, modules,
and internal cables.
1. Fabrication of cable harnesses to meet all flight, test, and AGE requirements using either solder 25X1
type or taper pin connectors.
Figure 3-5 presents a series of photographs showing certain phases of these manufacturing capabilities
test laboratories were equipped and staffed to perform the necessary functional and environmental
tests on parts, components, subsystems, and systems.
All tests required to qualify equipment for satellite
application were performed xcept for the System Thermal Vacuum Tests which were conducted in the
large vacuum chambers at Lockheed's main plant in Sunnyvale. Thermal vacuum testing was first introduced
into the Space Industry by the CORONA Program. This method has now become a standard in the testing
procedures used for all satellite reconnaissance payload subsystems. Figure 3-6 shows a series of photographs
which depict: (1) the first vacuum chamber in Boston which was used to conduct early tests on the dry
leaves and CORONA electrostatic marking problems; (2) the High Altitude Thermal Simulation (HATS) Chamber
which was used for testing "C," "A," and "M" systems; (3) the Thermal Altitude Simulation Chamber
(TASC) which was moved from Boston to Sunnyvale and used for system level testing of the "M, " "L, " and
extensively on the J-1 Programs; and (4) the High Vacuum Orbital Simulation (HIVOS) Chamber which was used
for testing J-1 and J-3 systems. Figures 3-7 and 3-8 present photographs of different phases of some of the
early developmental testing. Figure 3-9 shows photographs of some of the clean room areas with associated
equipment used to perform photographic tests. Figure 3-10 shows a series of film tension tests checking
from the spool to the film to the splices. Figure 3-11 is a photograph of a J-3 system going through collimation
testing. The following is a list of the major test equipment and facilities utilized at AP:
A. Electrodynamic Shaker
MB Electronics, New. Haven, Connecticut
Force Output: 21,500 pounds maximum
Frequency Range: 5 - 2,000 cps
Maximum Stroke: .8 inch peak-to-peak
B. Slip Table
Wyle Laboratories, El Segundo, California
Size: 68 inches by 68 inches
Oil Feed: Pressurized with filter and 2 gallon reservoir
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CORONA HISTORY
Volume V
25X1N RO
Figure 3-5 I I 25X1
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CORONA HISTORY
Volume V
"M" System Going into High Altitude
Thermal Simulation Chamber at Sunnyvale
"C" System in Vacuum Chamber
at Boston
J-3 System Going into High Incited
Orbital Simulation Chamber at > !nnyvale
Thermal Altitude Simulation
Chamber at Sunnyva I c,
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CORONA HISTORY
Volume V
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CORONA HISTORY
Volume V
Clean Room Collimator and Theodolites
Used to Test "C" Systems
Clean Room and isolation Block Used
in Collimation Testing c [ J-3 ,Systcrn
Clean Room and Block Used to lest
"M" and J-1 Systems
PR ES S U/ P f M A A'f 00 ON r r
SRC/iDES a ~'