ADDITIONAL MISSILE AND SPACE RELATED SUPPORT PROGRAMS IDENTIFIED AT ZAGORSK, USSR

• Document Type: CREST
• Collection: NGA Records (Formerly NIMA)
• Document Number (FOIA) /ESDN (CREST): CIA-RDP91T01115R000100320003-7
• Release Decision: RIPPUB
• Original Classification: S
• Document Page Count: 18
• Document Creation Date: December 28, 2016
• Document Release Date: October 19, 2010
• Sequence Number: 3
• Publication Date: September 1, 1984
• Content Type: REPORT

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Additional Missile and Space
Related Support Programs
Identified at Zagorsk, USSR (S)
A Research Paper
Secret
IA 84-10072
September 1984
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Summary
Information available as
of June 1984 was used
in this report.
Additional Missile and Space
Related Support Programs
Identified at Zagorsk, USSR (s)
The Zagorsk Missile and Space Development Center was established in
the early 1960s to support emerging Soviet missile and space programs.
Since then the center has been involved in developing and testing
missile transporters, propellant/oxidizer transporters, silo shock isola-
tion systems, some spacecraft systems, and space launch vehicles and
their respective launch sites. Intensive analysis of new and modified
facilities at the center, using information through June 1984, has
resulted in the identification of additional missile- and space-related
support programs at Zagorsk. Maintaining a good understanding of the
types of activity being conducted at Zagorsk is important because of
the potential tipoff it might provide to the direction and status of
important Soviet missile and space programs.
Previous analysis of satellite imagery had revealed a scale model of a
launch pad for a space launch vehicle at Zagorsk. More recent analysis
of modifications to the model and of associated activity patterns
indicates that exhaust gas flow experiments have occurred there over an
extended period to aid in developing several space launch vehicles-the
SL-X-15, the SL-X-16, and the SL-W-and their associated launch
sites.
Another facility currently under construction at the center will replicate
part of the propellant loading system at one of the launch sites for the
heavy-lift launch vehicle at Tyuratam. This facility will most likely be
used for checking connections between the umbilical and the booster,
duplicating the flow of pressurized gas and cryogenic liquids through
the umbilical, and developing operating procedures for use at the
launch site.
A probable impact test facility, constructed at the Zagorsk center
between 1979 and 1982, may test either surface penetrators for
interplanetary exploration or spacecraft soft landing systems. Surface
penetrators for interplanetary applications are sophisticated devices that
impact and penetrate the surface of a planet or asteroid in order to
measure various conditions on, as well as beneath, the surface. The
data is then transmitted to an orbiting satellite for relay to Earth.
Extensive testing of such devices is required to ensure that they function
after impacting the surface and experiencing force loads of up to 20,000
Gs or more.
Secret
IA 84-10072
September 1984
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Two other facilities at the Zagorsk center, heretofore unidentified, are
probably involved in treating and disposing of toxic liquid wastes
resulting from experiments with propellant-related chemicals and possi-
bly toxic metals. Construction of these facilities at Zagorsk was
probably prompted by increasing Soviet concerns about the disposal of
highly toxic effluents related to the development and handling of missile
and space launch vehicle propellants. Such facilities may also be built at
other missile propellant-related installations if these two prove success-
ful.
Secret
IA 84-10072
September 1984
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Summary
Probable Exhaust Gas Flow Experiments
1
Heavy-Lift Launch Vehicle Service Equipment Test Facility
5
Probable Impact Test Facility
5
Facility Description
5
Test Activity
8
Probable Toxic Liquid Waste Treatment-Disposal Facilities
12
Facility 1
12
Facility 2
14
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IA 84-10072
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Additional Missile and Space
Related Support Programs
Identified at Zagorsk, USSR (s)
The Zagorsk Missile and Space Development Cen-
ter (ZMSDC), located 15 kilometers north of
Zagorsk, was established in the early 1960s to
support the Soviet Union's then-fledgling missile
and space programs (figure 1). Primarily through
analysis of imagery-the main source of informa-
tion available on the Zagorsk center-a variety of
tasks related to these programs have been discov-
ered. These activities have included developing and
testing strategic missile transporters, silo shock
isolation systems, and propellant/oxidizer trans-
porters; testing shroud separation systems; and
testing soft landing systems on at least one series of
interplanetary probes-the Venera. Testing involv-
ing scale models of launch sites for space launch
vehicles is also an ongoing part of programs at
the center. (S
Closely monitoring activity at Zagorsk is important
because of the potential tipoff it might provide to
the direction and status of key Soviet missile and
space programs. A number of new facilities have
been constructed and existing ones modified since
1970 at the ZMSDC. The facilities examined during
the preparation of this report include a scale model
of a space launch pad, which has been modified
and used for testing in at least three separate
phases; a facility for testing certain ground support
equipment for the new heavy-lift. launch vehicle
(HLLV); a probable impact test facility for surface
penetrators or spacecraft soft landing systems; and
two previously unidentified structures most likely
for treating and disposing of toxic liquid wastes.
Probable Exhaust Gas Flow Experiments
A scale model of a launch pad was built at Zagorsk
in 1967. The facility is referred to in the Intelligence
Community as the J minipad, because it was
modelled after a launch pad at Space Launch Site
Some spacecraft have multi-section shrouds around
portions of them to protect certain external compo-
nents during the launch phase. The shroud sections
must separate and be jettisoned after launch-usually
during the powered portion of the flight-in order for
the components to function in space. To ensure an
operable spacecraft, the sequence of events related to
shroud separation is usually tested at some point in
the development program of a spacecraft. (U)
Spacecraft soft landing systems are either passive or
active. Passive systems, including parachutes and air
foils, make use of the existing atmosphere to slow the
spacecraft to a safe velocity for landing on a body. In
the absence of'an atmosphere, however, active sys-
tems must be used. These systems utilize retrorockets
that are fired in the direction of descent to slow the
spacecraft for landing. (u)
J, Tyuratam Missile and Space Test Center
(TTMSTC). The TTMSTC is the major Soviet
flight test center for space launch vehicles; Launch
Site J was built there in the mid-1960s for the SL-
X-l5, the first Soviet HLLV. The SL-X-15 was to
have been comparable to the US Saturn V, but
after several unsuccessful launch attempts the SL-
X-15 program was cancelled in 1974. Launch Site J,
including its exhaust flumes, is currently being
modified for the new Soviet HLLV, the SL-W.
At least three distinct phases of modification and
related test activity have occurred in the J minipad
area since 1967: from 1972 through mid-1979; from
mid-1979 through early 1982; and from early 1982
to the present. These phases are probably related to
exhaust gas flow experiments for the new space
launch vehicles (SLVs) and launch sites currently in
Secret
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development.' Similar experiments, also using mod-
els, were conducted in the mid-1970s and again in
1981 at the Marshall Space Flight Center,a Na-
tional Aeronautics and Space Administration test
facility in Huntsville, Alabama, to aid in developing
the US Space Shuttle and its launch facilities. (S
Initial modification and associated test activity at
the J minipad area involved installing two narrowly
spaced rails in early 1972 just west of the site,
removing the existing tripod tower, and erecting a
larger framework tripod tower between March 1973
and January 1974 (figure 2). Exhaust gas flow
Two new SLVs are currently in development at the TTMSTC.
The SL-X-16 is a medium-lift launch vehicle that will be
launched from Space Launch Site Y, and its flight testing could
begin before the end of 1984. The SL-W, a new HLLV, will be
launched from Space Launch Site W as well as from Space
Launch Site J. The HLLV will be used to launch a space shuttle
orbiter from Site W, and other large payloads from both Sites
W and J. Flight testing of the HLLV from Site W could begin in
1985, but flight testing from Site J, where construction has not
nroeressed as far, is not expected before 1986 or 1987. (SD
experiments were probably conducted using this
new tower and the existing model exhaust flumes
until mid-1979. The function of the rails is not
clear, but they could have been used to mount
movable instrumentation equipment for tests at the
site. (S
By August 1979, as part of a second phase of
modifications and testing, skirts had been erected
around at least part of the tower base. Guide
blocks or tracks for positioning a device to be
delivered later were also being placed in front of
the tower (figure 2). Construction materials for the
probable impact test facility under construction
nearby were being stored temporarily on the apron
adjacent to the large new tower. In May 1980, what
was later identified as a scale model of an exhaust
flume was observed in front of Building 9, which is
near the ZMSDC entrance (figures 1, 3). The
exhaust flume model was I I meters long, 3 meters
wide, and had internal panels or support spars. One
end of the flume had a flat, boat-nosed shape, with
a step located about 6 meters away. The model
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exhaust flume was moved to the J minipad area
, where it was
positioned on the guide blocks or tracks. (s
The flume model was observed with its deepest end
under the base of the tower several times between
February 1981 and early 1982, when it was last
seen. The configuration and scaled size of this
model suggest that it was probably used for exhaust
gas-flow simulation experiments for the exhaust
trough design at Launch Site Y, TTMSTC. At that
time the trough at Site Y was in a mid-to-late stage
of construction. Alternatively, the mockup could
have been used to investigate changes that have
since been made to the flame splitter and trough
area of Launch Site J, TTMSTC. (A flame splitter
is a structure, positioned beneath the launch vehi-
cle, that is used to deflect hot exhaust gasses into
an exhaust trough where they are channelled away
from the pad during a launch.) The changes at Site
J are intended to accommodate the complex gas
flow pattern resulting from the launch of the new
HLLV at this site. (s
A third testing phase at the J minipad was first
noted in April 1982, when a completely different
model was seen in front of the tower on satellite
imagery. The new model consists of a combination
launch stand and flame trough (figure 4). The
configuration indicates that the model will be used
to simulate the deflection and channeling of HLLV
exhaust during launch from Launch Site W at the
TTMSTC. An exact 1:10 scale model of the unique
launch vehicle support pedestal at Launch Site W is
present on the launch stand portion of the model.
Also related to the test activity in this phase are
two vans that are probably used for instrumenta-
tion and office space; an unidentified short frame-
work structure adjacent to the model; a small
arched-roof object 5 meters long, 3 meters wide,
and approximately 1 meter high; and a crane for
moving objects onto the model. The small arched-
roof object, which has been observed in the flame
trough area, probably houses sensors during a test.
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Heavy-Lift Launch Vehicle Service Equipment
Test Facility
A facility being built adjacent to the shroud separa-
tion test facility at Zagorsk will be used to test the
operation of ground umbilical servicing equipment
for the new HLLV (figure 5). Construction of the
servicing equipment test facility began in early
1983, was nearly complete by mid-1984, and could
be finished by late 1984 or early 1985. (s F_
The facility contains test fixtures which, when
completed, will replicate a portion of the propellant
loading system which has been installed at
TTMSTC Space Launch Site W. The only apparent
difference between the two fixtures is the presence
of a blast shield over the umbilical at Tyuratam,
which will help prevent damage to the umbilical
during an HLLV launch. The test fixture at the
ZMSDC will probably also replicate a structure at
Space Launch Site J, which is currently being
modified for the HLLV. In addition, hardware for
mounting a test article that will simulate a section
of the HLLV core booster has also been installed at
the facility. (s
The primary test fixture at the facility is an
approximately 10-meter-square by 9-meter-high
open framework structure which has a 20-meter-
long, triangular
appendage attached to it. When completed, this
fixture will nearly duplicate that part of the fixed
service structure at Tyuratam Space Launch Site W
which houses an umbilical for the transfer of liquid
oxygen (LOX) to or from the HLLV. The appen-
dage on the square, framework structure probably
will be used for mounting a replica of the LOX
umbilical used at both HLLV launch sites. An
array of nine small mounting points that will
probably support a section of th
core booster of the HLLV is approximately 10
meters from the test fixture. The umbilical and a
test section of core booster tankage will most likely
be used for checking mechanical and pneumatic
connections between the umbilical and booster,
duplicating the flow of pressurized gas, cryogenic
liquids, or both through umbilical/booster lines,
and developing operating procedures for use at the
launch sites. (s
This test facility may also be used for testing other
ground servicing and possibly booster checkout
equipment. With some minor alterations, for exam-
ple, the test fixture could be used for mounting a
liquid hydrogen (LH) umbilical like those at the
HLLV launch sites. A series of tests similar to 25X1
those that will apparently be conducted with the
LOX umbilical could then be done with the LH
umbilical. (s
Probable Impact Test Facility
The probable impact test facility, situated at the
extreme west end of the Center, consists of a test
site structure that encloses a basin, a rail-mounted
service tower, and a traveling crane that can lift
heavy objects into and out of the test site (figure 6).
Also related to the test facility are a control
building connected to the area by an underground
utilities conduit, a test preparation building, and a
buried drainage collection basin. These facilities
were built concurrently with the test site enclosure.
Testing of surface penetrators for interplanetary
exploration or spacecraft soft landing systems may
occur at this site. (s
Facility Description
Construction at the impact test facility was first
noted on satellite imagery in March 1979, when
ground scarring was seen at the control building
site. Tree clearing preparatory to erecting the test
site enclosure and service tower was first observed
in July 1979, and the enclosure and tower were
completed in early 1981. All other facility construc-
tion, except the drainage collection basin, was
completed by early 1982. Work on the basin began
in May 1980 and was finished in 1983. (s
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The test facility consists primarily of an unusually
configured, sloped-wall enclosure containing an
open basin (figure 7). The enclosure, basically a
The upper 10 meters of the walls slope inward at a
45 degree angle, and along at least the eastern side
of the structure an internal wall slopes approxi-
mately 45 degrees inward from the 5-meter level to
the ground level, Angled supports for the internal
wall were seen along this side of the enclosure
during construction. Although we believe similar
walls are on the other sides of the enclosure, the
sides were not observed at a stage of construction
which would have revealed their existence. (SF-
The basin in the enclosure is 18 meters long, 12
meters wide, and 7 meters deep. The basin's walls
are 2 meters thick, and were built by erecting two
parallel rows of prefabricated concrete panels and
filling the area between the panels with some sort
of loose material. A removable, three-section cover
protects material in the basin against the environ-
ment. The traveling crane adjacent to the enclosure
is used to remove and replace the cover sections.
The service tower, which can be moved into and
out of the test site enclosure on rails, is a steel
framework structure about 44 meters high (figure
7). The lower of the two sections is 15 meters
square and 20 meters high. At the 14-meter level of
this section is a floor with an approximately 3-
meter-square opening in its center. When the tower
is positioned over the basin, this floor acts as a
kind of roof for the enclosure, and together with
the sloped walls almost completely covers the area
above the basin. (s
The upper section of the service tower is 30 meters
high and 6 meters square. This section extends
down 6 meters into the center of the lower section,
resulting in a height of 44 meters. The upper
portion has what may be launch or guide rails
attached to two of its sides. The rails probably
guide a test device as it is dropped or propelled
into the basin (figure 8). (s
The test preparation building is 33 meters long, 30
meters wide, and two stories high. The western half
of the building is an open bay section probably
used for work on the test devices. The eastern half
of the building consists of two floors of small
rooms that provide administrative and workshop
spaces. The control building is 50 meters long, 18
meters wide, and one story high. Site operations
during testing are probably directed from this
building. The 20-meter-long by 12-meter-wide L-
shaped drainage basin is divided into small
cells. This buried basin serves as a temporary
retention basin for water runoff emanating from
the test facility area. Drainage pipes buried
throughout the area during construction connect
into the basin, Steamlines serve the site enclosure,
control building and the test preparations building.
An unidentified pipeline also leads to the test site
enclosure (Figure 6). (S
'Test Activity
Activity that could be testing, facility checkout,
or both, was first noted in early 1982 at the impact
test facility. In March of that year a probable
telescoping arm, which may be an extension of the
upper section of the service tower's launch or guide
rails, protruded from the tower's center to an
object on the concrete apron adjacent to the
enclosure (figure 8). The fixture-seen on later,
better quality imagery-probably holds a test de-
vice for Final checkout and attachment to the arm
before a test occurs within the enclosure. The
fixture is an open, thick-walled cylinder approxi-
mately 2 meters high, with an outside diameter of
about 3 meters and an inside diameter of about 1
meter; it stands upright on four feet. (s
the service tower
was seen within the test site enclosure, and the
three sections of the basin cover were on the
adjacent concrete apron under and near the travel-
ing crane, indicating that a test was underway
(figure 8). This test was apparently completed by
when the service tower was seen outside
the enclosure and the basin was again covered.
Another test was noted in July 1982. At that time,
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the test device handling fixture and a small prob-
able trailer were present outside the enclosure at
the usual pre-test position of the service tower.
Function
While the specific type of testing being conducted
at the facility is not clear, the facility's configura-
tion, together with activity observed there since
early 1982, provides some insight about the test
program. We believe that the basin is a key test
feature, and that it probably contains some speci-
ally prepared material-whether solid or liquid we
are not sure-into which test devices are dropped
or propelled from the service tower. The facility's
test sequence can also be postulated. First, the
device to be tested is probably checked out and
instrumented in the test preparation building just
before moving to the test facility. The device is then
transported to the test site, where it is placed into
the handling fixture for attachment to the telescop-
ing arm. After final checkout, the device is raised
into the tower by the arm and the cover sections
for the basin are removed. Next, the tower is
moved over the basin, where the test device is
dropped or propelled into the specially prepared
material. The tower is removed from the enclosure
after the test, and the device is recovered from the
basin and returned to the test preparation building
for inspection and evaluation. The cover sections
are then replaced over the basin, thus completing a
test cycle. (s
Two systems that might use such testing procedures
are surface penetrator systems or spacecraft soft
landing systems for. either land or water recovery.
Of these possibilities, the testing of surface penetra-
tors seems the more likely. In a surface penetrator
scenario for the Zagorsk facility, the basin would
contain the specially prepared soil and rock media.
The penetrator would be launched downward into
the basin from the service tower using a high
pressure gas, or a small rocket motor. The sloping
walls of the enclosure would deflect any throwout
material resulting from impact back into the basin
or floor area of the enclosure. (S
Studies related to the use of surface penetrators for
planetary and asteroid exploration have been under
way in the US since the mid-1970s. As developed and
tested in the US, surface penetrators consist of
slender, ogival-nosed cylindrical projectiles that carry
sensors and other instruments to a depth of'a few
meters in soil or rock so that various natural
phenomena can be measured in situ. The penetrators
typically impact the surface at high velocity-nearly
150 meters per second-and separate into fore and
aft sections. The aft section remains on the surface
and the fore section, while remaining connected to
the aft section by cable, penetrates the surface to the
desired depth. The aft section acts primarily as the
communications link between the penetrator and an
orbiting satellite, but can also house meterological
and imaging sensors as well. The fore section con-
tains sensors to measure conditions in the soil or rock
such as seismicity, chemical composition, heat flow,
and magnetism. Surface penetrator systems, despite
their .seemingly apparent simplicity, are sophisticated
devices that must survive extreme conditions of de-
ployment (e.g. force loads of 20,000 Gs and more)
and still perform their intended mission.2 Extensive
development and testing programs, therefore, are re-
quired to perfect these devices. ((,)
Experiments involving the high velocity impact of
instrumented penetrators of'various shapes and con-
figurations have been conducted in a wide range of
earth types. Many of the tests were conducted at test
sites using a transportable air gun where the target
media, various combinations of soil and rock, were
specially prepared and where the experiments could
be closely controlled and monitored. Other tests were
carried out at unprepared sites using the transporta-
ble air gun or by air-dropping to propel the penetra-
tor into the natural soil and rock media environment.
(U)
-One G is the gravitational force acting on a body at sea level,
and equals 9.78039 meters/second at 0 degrees latitude. Astro-
nauts typically experience 3 Gs-essentially 3 times their weight
at sea level-or less during a normal launch and recovery. An
emergency ballistic reentry might result in 8 Gs or so. (U)
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In a scenario for testing spacecraft soft landing
systems, the basin would contain earth or water.
The spacecraft, probably a model, would be pro-
pelled or simply dropped from the tower at the
desired velocity into the basin. (s
Probable Toxic Liquid Waste Treatment-Disposal
Facilities
The function of two previously unidentified facili-
ties at the ZMSDC is probably the treatment and
disposal of toxic liquid wastes (figure 1). The
features of these facilities strongly suggest that they
were designed for the treatment and disposal of
liquid wastes generated within the ZMSDC, proba-
bly during experiments with small quantities of
propellant-related chemicals and possibly toxic met-
als. Furthermore, we believe that the first toxic
waste facility (Facility 1) was a functional model
for the second (Facility 2) and that the Soviets,
after evaluating the performance of Facility 1,
decided to build the much more elaborate Facility
2. If these facilities prove successful, they may serve
as models for the construction of additional toxic
waste treatment and disposal facilities at other
missile propellant-related installations. Figures 9-1 1
compare the construction chronologies of Facilities
I and 2. (S
Facility 1
Facility I was built in the south-central portion of
the ZMSDC. Construction was apparently accom-
plished in two phases, the first from April to
August 1978, and the second from March to May
1979. (s
Toxic liquid wastes could be delivered to Facility 1
in several ways: directly to the central structure by
road vehicles; by rail car via what may be an
unloading rack on a new rail spur; or from the
terminus of a possible pipeline 200 meters north of
the facility adjacent to a tank farm. (s
The first phase of construction at Facility 1 in-
volved excavating three straight 60-meter-long
trenches that radiated at 90 degrees from each
other from a central circular excavation. Short
trenches were also excavated perpendicular to the
ends of the trenches. These 60-meter-long trenches
are probably drainage outlets for liquid effluent
after it has been treated in a structure in the central
excavation. By May 1978, a circular concrete basin
was being built below grade at the facility's center,
and dark-toned probable drainage tiles were being
emplaced in one of the trenches (figure 9). (sLI
On August 1978 satellite imagery, the facility ap-
peared essentially complete; the trenches had been
back-filled with earth and a rectangular structure
had been built over the circular basin (figure 10). By
March 1979, however, the rectangular structure
above the basin had been removed. A trench had
been excavated from the center of the facility to the
north under a newly established rail spur to a point
about 200 meters away. The trench's terminus was
adjacent to an existing tank farm and parking area
for propellant transporters. By April 1979, an
unidentified structure was visible at the center of
the facility, and a radial pattern of alternating light
and dark material was present around the structure
(figure 11). The pattern and its relationship to the
three known radial drainage outlets suggests that a
fourth drainage outlet had been built on the
easternmost side of the facility. By May 1979, the
radial pattern of light and dark material was still
present but not as apparent, and an octagonal shed
had been erected around the unidentified structure
at the center of the site. The facility appeared to be
finished at that time. (S
A possible drain field, an area where a liquid
effluent is allowed to seep into the ground, was
constructed adjacent to the toxic liquid waste
facility, most likely for operational support. Rows
of what may be flexible hoses or cables could be
seen laying on the field's specially graded surface
during this area's construction. Later the hoses or
cables were apparently buried. Access to the drain
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field is gained through a small road-served struc-
ture near the south side of the facility. The con-
struction timing of this area and its proximity to
what is probably the toxic liquid waste facility lead
us to suspect that the two areas are related,
although we have not detected a direct connection
between them. (s
Facility 2
A second, more elaborate site that is probably a
toxic liquid waste treatment facility has been built
next to the north side of the ZMSDC. Facility 2 is
similar to Facility I in both appearance and con-
struction technique. It consists of what is probably
a central waste treatment building connected to an
array of eight radial drainage outlets. (S
Early activity related to the facility was noted in
February 1981. At that time, a road was being built
to its construction site from near the entrance to
the ZMSDC along the outside of the northern
perimeter fence. By March 1982, most of the radial
trenches had been excavated and dark-toned proba-
ble drainage tiles were present in several of the
trenches. Short trenches perpendicular to the ends
of some of the arms were also present. Addition-
ally, a circular concrete basin was being built below
grade at the center of the array, a control and
monitoring building was under construction at the
southwest corner, and pipeline trenches were being
excavated within the ZMSDC proper adjacent to
the treatment facility (figure 9). A conduit had also
been emplaced between the control and monitoring
building and the central area of the facility.
By May 1982, some of the trenches had been back-
filled and a rectangular structure was being erected
around and over the circular concrete basin (figure
10). What were probably dark-toned drainage tiles
could be seen in some of the trenches, and a
disruption in the earth and solid perimeter fence
next to the control and monitoring building indi-
cated that a connection had been made to the
pipeline trenches seen within the facility two
months earlier. (s
The facility was externally complete by early 1983.
By June, a radial pattern of alternating light-and
dark-toned material similar to that at the first
facility could be seen (figure 11). The only connec-
tions between Facility 2 and the ZMSDC are the
buried probable pipeline and a steamline leading to
the control and monitoring building. No direct
vehicular or personnel access is provided to the
facility from the ZMSDC. A temporary housing
area built for construction workers has deteriorated
since Facility 2's completion, and no additional
construction is expected in this area. (s
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