SOVIET HEAVY-LIFT LAUNCH VEHICLE AND SPACE SHUTTLE ORBITER FACILTIEIS, TYURATAM MISSILE AND SPACE TEST CENTER

• Document Type: CREST
• Collection: NGA Records (Formerly NIMA)
• Document Number (FOIA) /ESDN (CREST): CIA-RDP91T01115R000100140002-8
• Release Decision: RIPPUB
• Original Classification: S
• Document Page Count: 33
• Document Creation Date: December 28, 2016
• Document Release Date: September 9, 2010
• Sequence Number: 2
• Publication Date: March 1, 1984
• Content Type: REPORT

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secret
Soviet Heavy-Lift Launch
vehicle and Space Shuttle
Orbiter Facilities,
Tyuratam Missile and
Space Test Center (S)
secret
IA 84-10017
March 1984
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Summary
Information available
through 31 October
1983 was used in this
report. (U)
Soviet Heavy-Lift Launch Vehicle and Space
Shuttle Orbiter Facilities, Tyuratam Missile
and Space Test Center (S)
A large-scale, integrated facilities construction and modification pro-
gram is nearing completion at Tyuratam Missile and Space Test Center
for the offloading, receipt, assembly, checkout, transport, and launch of
a new Soviet heavy-lift-capability space launch vehicle. Several variants
of this heavy-lift vehicle probably are being developed, one of which
will be used to launch the Soviet space shuttle orbiter. Shuttle orbiter
landing and processing facilities also are being built at Tyuratam.
Construction of new facilities and modification of existing ones for the
heavy-lift vehicle began in 1978. New booster facilities include a single-
pad launch site, two launch control centers, a high-bay vehicle process-
ing building, and miscellaneous support areas. Facilities under modifi-
cation include a twin-pad launch site, a vehicle assembly and checkout
area, a payload and upper stage assembly and checkout area, and sev-
eral support and housing areas.
Facilities for the space shuttle orbiter include a large airfield, begun in
1979, and a twin-bay orbiter maintenance and checkout building, begun
in 1981. Several other facilities, including the new high-bay vehicle
processing building, will support both shuttle orbiter and heavy-lift
vehicle processing activities.
Initial heavy-lift vehicle/launch pad compatibility testing occurred in
October 1983. Completion of the first launch site and most of the
launch vehicle and shuttle orbiter support facilities is expected in 1984
or 1985, with nonshuttle launch operations possibly beginning about
mid-1985. The first launch with the shuttle orbiter is expected no earlier
than late 1985.
The basic heavy-lift vehicle consists of a core booster and four strap-on,
thrust-augmentation boosters. The core booster has two or three main
propulsion engines and will use high-energy liquid oxygen and liquid
hydrogen propellants. The strap-on boosters will use liquid oxygen and
probably a hydrocarbon-based fuel such as kerosene. Large payloads,
such as the shuttle orbiter, and possibly payloads with attached upper
stages will be mounted to the side of the core booster. Future variants
of the heavy-lift vehicle may have differing numbers of strap-on boost-
ers, use high-energy-propellant upper stages, and be able to accommo-
date either side- or top-mounted payloads.
iii Secret
IA 84-10017
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Successful development of the heavy-lift launch vehicle and its variants
will enable the Soviets to orbit up to 150 metric tons. With this launch
vehicle, the Soviets will be able to conduct shuttle orbiter missions simi-
lar to those flown by the US; launch large payloads such as space sta-
tion modules; and, with the development of upper stages, conduct
flights to the moon and planets.
Secret
IA 84-10017
This information is Secret
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Secret
Summary
Introduction 1
Space Launch Site W
Propellant-Related Facilities 6
Support Facilities
Space Launch Site J
Propellant-Related Facilities 16
Support Facilities
Support Facility 31
Vehicle Assembly and Checkout Building
Orbiter Maintenance and Checkout Building 22
Spacecraft/ Upper Stage Propulsion Facility 25
Support Facility 1
Appendix 31
V Secret
IA 84-10017
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Soviet Heavy-Lift Launch Vehicle and Space
Shuttle Orbiter Facilities, Tyuratam Missile
and Space Test Center (S)
The Soviets are in the late stages of a large-scale,
high-priority construction project at Tyuratam Mis-
sile and Space Test Center to provide support and
launch facilities for a new heavy-lift launch vehicle
(HLLV). Variants of the HLLV will be used for
launching the Soviet space shuttle orbiter and prob-
ably numerous other payloads. The facilities under
development at Tyuratam include those required
for the offloading, receipt, assembly, checkout,
transport, and launch of the HLLV and its vari-
ants. Landing and processing facilities for the shut-
tle orbiter and assembly/checkout facilities for
other HLLV payloads are also being built or modi-
fied. Most of the facilities at Tyuratam for the
HLLV have been under construction or modifica-
tion since 1978 and are expected to be operational
in 1985 or 1986. (s
The HLLV under development is the successor to
the SL-X-15 (formerly the TT-5) booster, which
was to have been used in the Soviet manned lunar
landing program. After three successive launch
failures between 1969 and 1972, the SL-X-15
program was cancelled in early 1974. Most, if
not all, of the facilities at Tyuratam originally built
for the SL-X-15 booster and payload programs are
being extensively modified for the new HLLV pro-
gram since
at least 1976 a new three-stage space launch vehicle
has been under development by the V. P. Glushko
design bureau, which also designed the SL-X-15.
The new booster be-
ing smaller than the SL-X-15 and employing high-
energy liquid oxygen (LOX) and liquid hydrogen
(LH) propellants. We believe this launch vehicle
is the new HLLV. (s
The new HLLV is composed of several large com-
ponents which are mated together to form the
launch vehicle. The basic vehicle consists of a 59-
meter-lon core booster and 25X1
four strap-on thrust-augmentation boosters, each
about 40 meters in length and 4.0 meters in diame-
ter (see appendix). The core booster has two or
three main propulsion engines and will use LOX
and LH propellants. The strap-on boosters are de-
rived from the first stage of the SL-Y, a medium-
lift space launch vehicle also under development at
Tyuratam, and will use LOX and probably a hy-
drocarbon-based fuel such as kerosene. (s F7-r)X1
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The payload-lift capability to low earth orbit for
the HLLV and its variants will probably range
from 100 to 150 metric tons. The basic HLLV
probably will be able to orbit about 100 metric 25X1
tons. An HLLV variant employing a high-energy-
propellant upper stage should be able to place
about 150 metric tons into low earth orbit. These
launch capabilities will enable the Soviets to pursue
a wide variety of space missions. The launch of
their space shuttle orbiter on the basic HLLV will
allow them to conduct missions similar to those
flown in the US shuttle program. In addition, other
heavy, earth-orbital payloads such as large space
station modules; heavy, unmanned interplanetary
spacecraft; and, eventually, manned missions to the
moon and Mars probably will be launched using
the HLLV and its variants. (s
Secret
IA 84-10017
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Space Launch Site W
Space Launch Site W, one of two launch areas for
the HLLV at Tyuratam, is under construction
about midway between Launch Site J and Airfield
3 (figure 1). The launch site is configured to sup-
port the launch of an HLLV (designated SL-W by
the Intelligence Community) with four strap-on
boosters and a side-mounted payload, such as the
space shuttle orbiter. This site may also be capable
of accommodating side-mounted payloads with up-
per stages. (S
Ground breaking for Launch Site W occurred in
May 1978 and actual launch pad construction be-
gan in August 1979. In October 1983, the site was
in a late stage of construction and a prototype
HLLV (without payload) was brought to the pad
for the initial series of launch pad compatibility
checkout tests. Based on the current pace of con-
Figure 1
Tyuratam Missile and Space Test Center
struction, completion of the launch site may occur
by late 1984 or early 1985 and initial nonshuttle
launches may begin in mid-1985. The first launch
of the space shuttle orbiter is expected no earlier
than late 1985. (s
The major features of the launch site include the
launch pad and its associated booster and payload
service structures, flame pit, exhaust chute, light-
ning arresters, and illumination towers; bunkered
propellant-related facilities; propellant storage facil-
ities using spherical tanks; and miscellaneous pro-
pellant-related facilities (figure 2). Support facilities
constructed in the vicinity of the launch site include
a construction worker housing area, a launch con-
trol center with two associated probable support
buildings, two materials receiving areas, a steam
heating plant, and an unidentified building which
will provide some form of support. (S
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Launch Area
The launch area consists of a single launch pad and
launch vehicle support and service structures lo-
cated near the launch pad (figure 3). The launch
pad and its C-shaped pad substructure, as well as
the flame pit, are located at the base of a triangular
excavation which was 525 meters long, 220 meters
wide, and 45 meters deep at the start of pad con-
struction. Construction of the pad substructure be-
gan in August 1979 and the substructure now sup-
ports the 84-meter-long by 62-meter-wide steel-
reinforced-concrete launch pad. A 30-meter-wide by
40-meter-high curved flame deflector is enclosed on
three sides by the pad substructure and is water
cooled. An underground building, about 58 meters
long and 40 meters wide, was built adjacent to and
level with the west side of the launch pad. Pro-
pellant, propellant-support, and utility lines run
into this building and probably are distributed to
facilities at the launch pad for servicing the HLLV.
A 14-meter-long, 30-meter-wide,
launch vehicle support pedestal is located on t e
launch pad, above the flame deflector. The pedestal
is configured for an HLLV with four strap-on
boosters, each 4.0 meters in diameter. Besides struc-
tural support for the HLLV, the pedestal probably
will provide electrical, mechanical, and hydraulic
connections to the HLLV. Engine exhaust from the
launch vehicle will be directed downward through
the pedestal and then deflected into the flame pit
and exhaust chute during lift-off, Water spray
nozzles for cooling the pedestal and flame deflector
and for suppressing launch noise vibrations proba-
bly are located in or on the launch pedestal, but
they have not yet been identified, (s
Once the HLLV has been erected on the pad, it will
be serviced by both fixed and mobile service struc-
tures (figure 3). The fixed service structure (FSS) is
a 10-meter-square by 69-meter-high open steel
framework which is located adjacent to the launch
vehicle support pedestal and will be used for load-
ing the cryogenic propellants onto the core booster
of the HLLV. Two probable propellant-loading
umbilicals, one for LH and one for LOX, have
been identified on the FSS and each has been seen
in extended and retracted positions. The two umbil-
icals, which are swung into or out of osition, are
mounted on the FSS at about~46 meters
above the pad surface. The position of each umbili-
cal relative to that of the erected HLLV's core
booster indicates that the lower propellant umbili-
cal probably will be used for LH and the upper
umbilical probably will be used for LOX. (S F_
The mobile service structure (MSS) is a large
gantrylike structure mounted on a 34-meter-gauge
rail line which will provide access to and around an
erected HLLV and payload. The MSS is about 77
meters tall and has a clear span between its side
support towers Ten service
platforms are attached to the MSS support towers
at elevations from about 64 meters above
the pad surface. The platforms are hinged and can
be swung into and out of position around an
erected HLLV and its side-mounted payload. Fur-
thermore, the platforms are mounted to the MSS in
a manner that indicates that the space shuttle orbit-
er is one of the intended payloads for the HLLV.
When hinged in the open position, the lowest four
MSS platforms will allow about
ance for each shuttle wing when the MSS is being
moved into or out of position. No platforms for
orbiter payload bay or cosmonaut access have been
identified on the MSS. (S
Two lightning arresters and four illumination tow-
ers are positioned around the launch pad (figure 2).
The lightning arresters, each 222 meters tall, are lo-
cated about 135 meters north and south of the
launch point. In addition to the four illumination
towers, banks of lights are mounted on the light-
ning arresters. (S
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Two bunkered possible compressed-air facilities are
located about 245 and 208 meters north and south,
respectively, of the launch point (figure 2). Both fa-
cilities consist of six adjoining arched-roof build-
ings, each about 14 meters long and 14 meters
wide, and are connected by underground conduit to
the launch pad area. Small, upright, cylindrical ob-
jects, possibly tanks, were observed on palletlike
platforms adjacent to the facilities during construc-
tion. These possible tanks were subsequently in-
stalled in the facilities and may be used for the
storage of compressed air, which will be required
for the control of pneumatic equipment at the
launch pad. (S
Propellant-Related Facilities
Storage, conditioning, and pumping facilities for
liquid propellants are under construction west of
the launch pad area and are connected to the
launch pad by underground conduits or elevated
pipe galleries. These facilities include four major
bunkered facilities, probable LH and LOX storage
facilities, and several miscellaneous facilities (figure
2). (s
Bunkered Facility A. This possible propellant- or
utilities-related facility is located about 220 meters
west of the launch point and consists of five adjoin-
ing arched-roof buildings, each about 119 meters
long and 14 meters wide. The buildings are individ-
ually vented and are connected by conduits to the
underground launch pad support building. No stor-
age tanks have been associated with the buildings,
suggesting that the facility may be used for pro-
pellant-related purposes, such as temperature condi-
tioning and pumping, or for utilities, such as hous-
ing electrical equipment. (S
Bunkered Facility B. This possible propellant tem-
perature-conditioning or pumping facility is adja-
cent to the south side of Facility A and consists of
an 88-meter-long by 14-meter-wide arched-roof
building and eight adjoining arched-roof buildings,
each about 44 meters long and 14 meters wide. Al-
though the facility layout is similar to that of a
bunkered LOX storage facility at site J used during
the SL-X-15 program, no storage tanks have been
associated with these buildings. The facility is con-
nected by conduits to Bunkered Facility D, which
probably is used for kerosene propellant storage,
and to the launch pad, suggesting that it may be
used for propellant temperature conditioning or
pumping. (S
Bunkered Facility C. This water storage and possi-
ble air conditioning equipment facility is on the
south side of Facility B and consists of two arched-
roof equipment buildings, both about 121 meters
long and 14 meters wide; a third arched-roof equip-
ment building about 80 meters long and 14 meters
wide; and three concrete water storage vaults, each
about 36 meters square and 6 meters high. The fa-
cility is connected by conduits to the launch pad
and is similar to a facility at the former SL-X-15
launch site that was used for water storage and to
house air conditioning equipment. Water stored
here probably will be used to cool the flame deflec-
tor and launch pad surface during launch of the
HLLV. (s
Bunkered Facility D. This probable kerosene pro-
pellant storage facility is located south of Facility C
and consists of three arched-roof buildings, two of
which are about 63 meters long and 14 meters
wide, and a third which is about 98 meters long
and 14 meters wide. This facility houses at least six
and probably eight 3.0-meter-
diameter propellant storage tanks, each with a ca-
pacity of about 170,000 liters, and is connected by
conduits to Facility B and the launch pad. (SF-
Probable LH Storage Facility. A probable LH stor-
age facility is located about 850 meters northwest
of the launch point and contains four double-
walled spherical tanks, each with a capacity of
about 1.43 million liters (figures 2 and 4). The
tanks are storage dewars; each consists of a 16-
meter outer tank and a 14-meter inner tank and
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provides an insulated environment for prolonged
storage of the cryogenic fuel.' The four tanks are
interconnected and have a common rail-served off-
loading area. Fuel apparently can be transferred
from one tank to another by means of an extensive
intertank piping system. The tanks are also con-
nected by pipeline to adjacent banks of upright cyl-
inders,
These cylinders-a total of
32-possibly are refrigeration units for cooling the
stored LH and for recovery of condensed hydrogen
vapor, thus minimizing cryogenic liquid losses from
boil-off. Two bunkered arched-roof buildings have
been built in the vicinity of the spherical tanks,
possibly for housing special environmental-control
and pumping equipment for the fuel. A hydrogen
burn area is located immediately north of the prob-
able LH storage facility and contains several flare
stacks. (S
the new
HLLV may use a combination of liquid and solid
hydrogen, also known as slush hydrogen, for its
high-energy fuel. The higher density of slush hy-
drogen versus liquid hydrogen would allow the
Soviets to store a greater amount of LH in a given
volume, thereby reducing the size and weight of the
LH tanks required for the launch vehicle. The
lower temperature of the slush hydrogen also would
result in less hydrogen loss due to venting. (s
The LH capacity of this storage facility (about 5.7
million liters) is much greater than the quantity of
LH required for tanking a single HLLV (estimated
at between-1.5 and 1.8 million liters).' Therefore, if
slush hydrogen is used in the HLLV, two of the
four LH storage tanks may be used primarily for
receipt and storage of LH, while the other two
could be used for conditioning the LH into a slush
state and for maintaining such a condition by
means of recirculation. (S
'A dewar is a twin-walled container which functions as a vacuum bottle.
The space between the walls is evacuated of air and usually filled with
insulation in order to prevent heat transfer to stored liquids, especially
liquified gases. (U)
2Estimate based on a calculated approximate volume of LH contained in
the H LLV (1.5 million liters) plus up to an additional 300,000 liters for
Probable LOX Storage Facility. A probable LOX
storage facility is located about 700 meters north-
west of the launch point and consists of two groups
of three double-walled spherical storage tank
dewars, for a total of six tanks (figures 2 and 4).
The tanks are identical in size and capacity to those
in the LH storage area. LOX apparently can be
transferred by pipeline between spherical tanks
within a group or between the two groups by an
extensive piping system. Connected to both groups
of tanks are 16 cylindrical possible refrigeration
which may be used for cooling the stored
LOX and for recovery of condensed oxygen vapor,
thus minimizing cryogenic liquid losses from boil-
off. Colocated with the piping system of the south-
ernmost group are two cylindrical probable cryogen
storage tanks, possibly used for storing liquid nitro-
gen for pressurization or purging of pipelines and
tanks. In addition, two bunkered arched-roof build-
ings have been built between the two groups of
spherical tanks, possibly for housing environmen-
tal-control and pumping equipment for the oxi-
dizer. (s
the new
HLLV may use LOX which has been subcooled
from 25 to 30 degrees Celsius below the boiling
point.' Since the LOX capacity of this storage
facility (about 8.6 million liters) is much greater
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than the quantity of LOX required for tanking a 20A]
single HLLV (estimated at between 1.4 and 1.8 mil-
lion liters), several of the spherical tanks could be
used for LOX storage while others could be used
for subcooling LOX and for maintaining such a
condition by means of recirculation.a (S
An elevated pipe gallery has been built for the
transfer of cryogenic propellants between the tanks
at the probable LH and LOX storage facilities and
the fixed service structure at the launch pad. Two
For LOX, subcooling involves cooling the liquid to a temperature below
that of its boiling point (-183?C) but above that of its freezing point
(-220?C). (U)
'Estimate based on a calculated minimum volume of LOX contained in
the H LLV (1.4 million liters) plus up to an additional 400,000 liters for
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arched-roof bunkers are located along and con-
nected to the pipe gallery by underground conduits
and may house equipment designed for temperature
conditioning and monitoring of the transfer pipe-
lines during propellant loading and unloading oper-
ations. The larger of the two bunkers is about 122
meters long and 14 meters wide and also houses
two cylindrical cryogen storage tanks,
and
associated equipment. No tankage has been associ-
ated with the second bunker, which is about 47 me-
ters long and 14 meters wide. (S
Other Propellant-Related Facilities. Several other
propellant-related facilities support Launch Site W.
A probable POL storage facility is situated between
the probable LH and LOX storage facilities and
consists of four dark-toned cylindrical storage
tanks,
and a 39-meter-long by 14-meter-wide
arched-roof building (figure 2). This facility is
bunkered and may store fuel to run on-site genera-
tors, compressors, and pumps. (S
A probable LOX drainage area is located about
240 meters south of the launch point and contains
a probable drainage pond and three possible collec-
tion tanks (figure 2). This area is connected to the
launch pad fixed service structure by an elevated
pipeline and is similar to, but larger than, an area
at Tyuratam Space Launch Site Y where probable
LOX drainage/venting has been identified. (S F
A high-pressure gaseous helium storage facility is
located about 500 meters west of the launch point
and contains 44 cylindrical tanks, each about 25
meters long
An adjacent, 119-meter-long by 14-meter-wide,
arched-roof building probably will regulate the
pressurized gas. (S
A facility consisting of an induced-draft water cool-
ing building and two support buildings is under
construction about 725 meters west of the launch
point (figure 2). The induced-draft cooling building
is about 78 meters long, 18 meters wide, and 9 me-
ters high and will house six eight-meter-diameter
fans. The building is connected by underground
pipelines to the bunkered facilities. Two support
buildings are located adjacent to the induced-draft
cooling building. One of these is about 92 meters
long, 12 meters wide, and 9 meters high and the
other is about 21 meters long, 12 meters wide, and
8 meters high. (S
An extensive underground conduit network is un-
der construction throughout Launch Site W for
propellants, pressurized gases, utilities, and cabling.
In addition, an underground conduit, which trans-
itions to an aboveground cable and utilities gallery,
has been installed between the launch pad and a
support area south of the launch area. (S
Support Facilities
A large housing area for construction workers and
a launch site control, storage, and services area are
also located at Launch Site W. (S
1983. (s
Construction Worker Housing Area. The housing
area is about 1 kilometer (km) west of the launch
area and extends southward for about 3 km (figure
2). Construction of this area began in 1978, and
since 1980 the number of single-story barracks has
more than doubled-from about 80 to about 170.
The last of the barracks were completed and ap-
peared to be occupied in mid-to-late 1983, indica-
ting that construction manpower probably was at
or near peak levels during the second half of
Launch Site Control, Storage, and Services Area.
The second Launch Site W support area is located
about 3.4 km southwest of the launch area and
consists of a bunkered launch control center (LCC),
two probable LCC-support buildings, a probable
liquid nitrogen (LN) storage building, a materials/
components receiving and storage area, and a
steam heating plant (figure 5). The LCC is about 68
meters long, 43 meters wide, and 18 meters high.
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Secret
This facility will support the prelaunch checkout,
launch countdown, and launch of the HLLV and
payload. The LCC is constructed of reinforced-
concrete sections, has three levels, and is connected
by an underground conduit to an aboveground
cable and utilities gallery that runs to the launch
pad area. The two buildings that are adjacent to
the LCC probably will provide personnel and tech-
nical services, including computer-related support
for launch operations. At least one, and probably
both, of the buildings are connected by conduit to
the LCC. (s
A probable LN storage building is under construc-
tion near the LCC and is connected by pipeline to
the launch site area. The building, about 140 meters
long and 60 meters wide, is the largest in this sup-
port area and consists of six rectangular sections.
The LN is probably stored in four cylindrical
tanks, each about 23.0 meters long
which are housed in one section of the
building. Probable cryogenic rail tank cars have
been observed on a rail siding adjacent to this sec-
tion. (s
A large materials/components receiving and storage
area with a single gantry crane and large concrete
aprons is located southwest of the LCC. The facil-
ity is rail and road served and has been used to
store launch site equipment, including large pro-
pellant and pressurized-gas storage tanks. A large,
high-bay probable component warehousing facility
is under construction along the southwest side of
the receiving area. The warehouse is about 96 me-
ters long, 53 meters wide,
bays. (S
A steam heating plant housing four boilers is under
construction west of the LCC. A steamline from
the plant runs along an overhead gallery to Launch
Site W. A rail-served fuel offloading area and a
vaulted fuel storage facility have been built adjacent
to the plant. (S
Other support facilities located in the Launch Site
W vicinity include an electric substation and a large
construction materials receiving area. The substa-
tion is located north of the steam heating plant and
serves the launch area and the construction housing
area. The construction materials receiving area is
located about 4 km south of the launch area and
has multiple rail sidings. Five gantry cranes and at
least two traveling cranes have been identified in
this area. (S
Space Launch Site J
Space Launch Site J was built in the mid-to-late
1960s and was used for launching the SL-X-15
booster. The site consists of two launch pads and
support/servicing facilities which are being exten-
sively modified for the launch of the new HLLV.
Launch Site J is about 5 km southeast of Launch
Site W and about 4 km north of Support Facility
31 -the HLLV assembly and checkout area (figure
1). Major alterations to the two launch pads-Jl
and J2-include modifications of the rotating ser-
vice structure (RSS) and launch pad aperture and
the construction of new underground support
buildings. In addition, new propellant and utilities
facilities are being built and others are being modi-
fied in the launch area (figure 6). The similarities
between the new facilities at Launch Site J and
those at Launch Site W indicate that the sites will
be capable of supporting launches of the basic
HLLV. Is
Modification of Launch Site J began in 1978 and is
continuing. Debris from the site was first noted in
August 1978 and was associated with the removal
of propellant-related equipment. Dismantlement
and alteration of the RSS and aperture components
of each launch pad and construction of new pro-
pellant-related facilities began in 1979. Although
work at launch pad J2 is proceeding ahead of that
at pad J1, the sequence of activities at both pads
appears to be identical. Based on the current pace
of construction, pad J2 may be completed in 1986
or 1987 and launch pad J I in the late 1980s or ear-
ly 1990s. (S
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Launch Area
Launch pads J I and J2 both have an RSS, a pad
aperture, three exhaust flumes, and ancillary equip-
ment such as lightning arresters and illumination
towers. In addition, three adjoining underground
probable propellant and utilities distribution build-
ings for support of HLLV servicing operations are
being built at launch pad J2 (figure 7). (s
The RSS at each launch pad, formerly 145 meters
high, has been partially dismantled and both struc-
tures are currently about 100 meters high. In addi-
tion, all SL-X-15-associated service platforms, pip-
ing, and support equipment were removed from the
service structures. Reconfiguration of the RSS at
launch pad J2 began in 1983 when a service plat-
form mounting framework was installed on the ser-
vice structure between 33 and 48 meters above the
pad surface. Assembly of at least two booster ser-
vicing arms for this framework began in early 1983
at the base of the J2 RSS (figure 7). Both arms
have servicing platforms with cutouts for two
HLLV strap-on boosters, indicating that an HLLV
with at least four strap-ons can be accommodated.
The assembly and installation of additional service
platforms, as well as propellant-loading umbilicals,
is expected. Reconfiguration of the J I RSS had not
begun by late 1983, but it probably will be identical
to the one at pad J2. (s
Each launch pad has a 20-meter-diameter aperture
which is being reconfigured to accommodate the
new HLLV. Former SL-X-15 booster-related struc-
tures, including a cylindrical
booster support pedestal, have been removed from
the pad aperture. This pedestal was mounted inside
the aperture and provided structural support for
the launch vehicle; electrical, mechanical, and hy-
draulic connections to the first stage of the SL-X-
15; and engine exhaust channeling during lift-off. A
new HLLV support pedestal will have to be con-
structed over each pad aperture, and these may be
similar to the one at Launch Site W. (S
has a 30-meter outer diameter and a 20-meter inner
diameter and it appears to be constructed of rein-
forced-steel segments (figure 7). It probably will be
installed around the pad aperture to provide sup-
port for an HLLV support pedestal. (S
The basic Y-shaped layout of each launch pad's ex-
haust flumes will be retained for the HLLV. How-
ever, the pyramidal flame-splitter in the base of the
pad J2 aperture appears to have been refurbished
and modified to accommodate the HLLV strap-
ons. The area around the three sides of the flame-
splitter has been deepened and, on at least one of
these sides, a wall is being built from the base of
the splitter into the exhaust flume, dividing that
section of the flume in two. This modification will
enable exhaust from two HLLV strap-ons to be ef-
fectively channeled through each of the three
flumes, suggesting a potential capability for launch-
ing not only a four strap-on HLLV from this pad,
but also a six strap-on variant of the HLLV. Simi-
lar modifications in the pad aperture are expected
to take place at pad J 1. (S
Construction of three underground buildings
around the J2 launch pad aperture has been under
way since late 1982. The buildings are being built
up to pad level and probably will be used for the
distribution, control, and monitoring of pro-
pellants, high-pressure gases, electricity, and other
utilities for the pad-functions probably like those
performed by the underground support building ad-
jacent to the pad at Launch Site W. (s
New or modified lightning arresters and illumina-
tion towers will be used at both launch pads. The
illumination towers around launch pad J2 have
been removed and probably will be replaced. In ad-
dition, reinforced-concrete hardstands are being
built near pad J2 and may be used to support new
illumination towers or lightning arresters. (S F
In late 1982, assembly of components for a circular
probable pad reinforcement structure began on the
rail approach to pad J2. The washerlike structure
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Propellant-Related Facilities
Existing propellant-related facilities are being reno-
vated and new facilities are being built at Launch
Site J for the HLLV. Also, an extensive network of
interpad conduits for propellant transfer operations
is under construction. The completed propellant fa-
cilities will probably be similar, if not identical, in
layout and function to the propellant facilities at
double-walled, spherical tank dewars, each with a
16-meter-diameter outer tank and a 14-meter-diam-
eter inner tank, and bunkers and support equip-
ment. The LH will be pumped through an elevated
pipe gallery and underground conduits to the
launch area. The layout of the tanks and the associ-
ated cylindrical possible refrigeration units is al-
most identical to that at Launch Site W. (s
Launch Site W. (S
Extensive renovation is under way on the interpad
bunkers which housed LOX storage tanks, water
tanks and air conditioning equipment, compressed
air tanks, and a site control center for the SL-X-15.
By late October 1983, all but the fuel storage and
fuel temperature control bunkers had been at least
partially unearthed. Six 34-meter-long
LOX storage tanks were removed from
their bunkers, probably in preparation for bunker
modification and the installation of new tanks. Old
propellant-related piping and debris have also been
seen around the interpad bunkers. We have not ob-
served any major modifications other than new
conduit connections to several of these bunkers.
However, new propellant tanks have been delivered
to the site. (S
Major new propellant storage and support facilities
are under construction both on- and off-site. These
include a group of five arched-roof propellant- or
utilities-related buildings, probable LH and LOX
storage facilities, a probable POL storage facility, a
high-pressure gaseous helium storage facility, and
an extensive interpad conduit network (figure 6).
The five arched-roof buildings are under construc-
tion on site between the two transporter/erector
rail approaches. Each building is about 14 meters
wide and 106 to 113 meters long and will possibly
house utility equipment or serve a propellant-sup-
port function other than storage, since no tank in-
stallation has yet been identified. This group of
buildings is similar in design and layout to Bun-
kered Facility A at Launch Site W, which may be
used for propellant- or utilities-related purposes.
A probable LOX storage facility is located about
750 meters north of the launch pads at site J. The
facility consists of two groups of three intercon-
nected, double-walled, spherical tank dewars, each
identical in size and capacity to those at the proba-
ble LH storage facility. The LOX will be pumped
through an elevated pipe gallery and underground
conduits to the launch area. The layout of the
tanks and the associated cylindrical possible refrig-
eration units is similar to that at Launch Site W.
A probable POL storage facility is under construc-
tion between the probable LH and LOX storage fa-
cilities. Four dark-toned cylindrical storage tanks,
armed-roof building probably will be used for stor-
ing fuel to run on-site equipment such as compres-
sors, motors, and generators. A nearly identical fa-
cility is located at Launch Site W. (s F_
Other propellant-related facilities under construc-
tion at Launch Site J include a high-pressure gase-
ous helium storage facility which is nearly identical
to its counterpart at Launch Site W. The completed
storage facility will contain 44 cylindrical gas stor-
age tanks, each about 25 meters long
DAn extensive network of interpad and off-site
conduits also is being built. The conduits will ac-
commodate propellant, pressurized gas, utility, and
cabling lines and will connect with underground
support buildings adjacent to the pad aperture.
Conduits for probable instrumentation cabling and
utility lines also are under construction from the
launch area to Support Facilities 31 and I (figure
A probable LH storage facility is under construc-
tion about 750 meters north of the launch pads at
site J. The facility consists of four interconnected,
6). (s
and a 39-meter-long by 14-meter-wide,
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Support Facilities
Two materials receiving areas and a construction
worker housing area are associated with Launch
Site J. A rail- and road-served materials/compo-
nents receiving and storage area with 11 buildings,
a gantry crane, and concrete aprons has been built
on site, west of launch pad J2 (figure 6). Another
rail- and road-served construction materials receiv-
ing and storage facility with three gantry cranes is
located between sites J and W and may be associ-
ated with site W also. A large construction worker
housing area south of Launch Site J was started in
mid-1978 and, although occupied, is still being ex-
panded. (s
A new landing facility, designated Airfield 3, has
been built about 5 km northwest of Launch Site W
to support shuttle orbiter landings and to receive
air-ferried booster components and orbiters (figure
1). This facility includes a concrete runway-the
third at Tyuratam and one of the largest in the
Soviet Union; a transloading facility; and a large
operations control building (figure 8). The runway
is 4,500 meters long and 84 meters wide and was
constructed along
= The first survey line for the runway was laid
between October and December 1977, and in No-
vember 1978 housing for construction workers was
started about 2 km west of the survey line. Grading
for the runway began in March 1979 and concrete
paving probably started in May 1979. Paving of the
runway was partially completed and the transload-
ing facility was completed in 1982. In late Decem-
ber 1982, a modified Bison carrier aircraft and two
support aircraft were parked at Airfield 3, indicat-
ing that the runway was capable of supporting
booster component deliveries. Runway paving and
turnaround apron construction were completed by
mid-1983. Runway grooving was under way in 1983
and 400-meter-long unpaved runway overruns were
being added in late 1983. Numerous landing aids
facilities have been or are being built to the south,
north, and adjacent to the runway to provide final
approach data to returning orbiters or transport
aircraft. Wide-radius-turn roadways have been con-
structed for the transport of orbiters and booster
components between Airfield 3 and Support Facil-
ity 31. (s
The runway was constructed using the continuous-
strip method, which involved pouring probable
high-grade concrete in two layers of overlapping
strips over a prepared subsurface. Each strip is 7
meters wide indicating
that the runway has a total thickness of at least 1.0
meter. By comparison, the US shuttle runway at
Kennedy Space Center he top
layer of the Soviet runway was reinforced with
square steel grids, giving the runway a very high
load-bearing capability. This high strength will per-
mit the Soviets to land or take off reusable space-
craft and transport aircraft which are much heavier
than the shuttle orbiter or modified Bison aircraft.
The transloading facility at Airfield 3 is used for
the delivery or shipment of the large, air-ferried
HLLV core booster components and will be used
for the delivery or shipment of space shuttle orbit-
ers. The facility is adjacent to the north side of the
runway and consists primarily of two offset, rail-
mounted gantry cranes that are about 60 meters
wide and 20 meters above the ground. The cranes
are mounted on a 270-meter by 90-meter concrete
apron and are built for lifting the booster compo-
nents and shuttle orbiter off of or onto the top of a
modified Bison carrier aircraft when it is positioned
beneath them. A similar transloading facility is lo-
cated at Ramenskoye Flight Test Center, where
mated testing of core booster components and the
shuttle orbiter with modified Bison aircraft has
been conducted. A transloading facility also is lo-
cated at Kuybyshev Aerospace Production Plant 1,
where production and direct air shipment of core
booster components originate. (S
A large probable operations control building is on
the north side of the runway, east of the transload-
ing facility. The building consists of a main five-
story section about 126 meters long, 19 meters
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secret
wide, and 27 meters high and an attached multi-
story wing
and faces the runway. Atop the
roof of the main section are five probable antenna
mounting platforms, each about six meters square.
The presence of these platforms indicates that the
building will probably provide telemetry receipt,
tracking, and computer support during shuttle mis-
sions and landing operations, The attached wing
eventually may house a control tower. (S
Other construction at Airfield 3 includes a 380-
meter by 141-meter concrete hardstand apron, sev-
eral buildings to garage runway support vehicles, a
steam heating plant, and miscellaneous small sup-
port buildings. Road, rail, and utility lines connect
Airfield 3 facilities with Launch Sites W and J and
Support Facility 31. (s
Support Facility 31
Support Facility 31 is 4 km south of Launch Site J
and was originally designed to support the SL-X-15
booster, Existing buildings at the facility are being
modified for the receipt, assembly, checkout, and
transport of the new HLLV and its variants. New
buildings for the maintenance and checkout of the
shuttle orbiter and for payload propellant loading
and mating to the HLLV are under construction.
Also, an LCC for Launch Site J is under construc-
tion adjacent to the launch control bunker used for
the SL-X-15 program, Other areas within Support
Facility 31, such as the construction worker and ci-
vilian housing complexes, have been refurbished
and reoccupied (figure 9). New worker housing,
motor pool areas, electric substations, materials re-
ceiving areas, a concrete batch plant, and a steam
heating plant have been or are being added in the
support facility.
Vehicle Assembly and Checkout Building
A large vehicle assembly and checkout building
(VACB) was constructed in the mid-1960s to sup-
port SL-X-15 booster processing-component re-
ceipt, assembly, integration, and checkout prior to
transfer to the launch pad. The building has since
been renovated and modified to support similar
tasks for the HLLV. The renovation and modifica-
tion work probably began shortly after the SL-X-15
program was cancelled. Between 1974 and 1977, we
observed railcar movements into and out of the
VACB and vicinity which were probably related to
the removal of tooling and components for the SL-
X-15 booster, Six of nine roof-mounted telemetry
checkout antennas were removed between early and
mid-1974 and the remaining three were removed in
mid-1979. Only a small latticework tower has since
been installed and it may be intended for short-
range communications. In April 1978, derelict SL-
X-15 propellant tank hemispheres were removed
from the VACB. Large tooling, jigs, frameworks,
and crates formerly used for the SL-X-15 program
also were removed from the building beginning in
1978. Three additions to the VACB have been built
since mid-1978 and two of these probably were
mandated by differences in vehicle design and proc-
essing flow between the SL-X-15 and the HLLV
(figure 10). (See the appendix for a description of
vehicle design and processing flow.) The third addi-
tion probably will provide technical support or per-
sonnel services. (S
A clear-span addition has been built on the east
side of the VACB and probably is used for the re-
ceipt and inspection of the HLLV core booster
components. The addition is 78 meters long, 36 me-
ters wide, and 32 meters high and has a craneway
with a usable height of about 16 meters. The size
and features of the addition, which is accessed by
wide-radius-turn roadways, indicate that it proba-
bly is intended for receipt and inspection of the two
large components for the HLLV core booster. A
road-served door about 13 meters wide and 13 me-
ters high has been installed on the east end of the
wing and a rail-served door
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is present on the addition's 2bAl
south wall. The addition is adjoined on its south
side by a 54-meter-long, 12-meter-wide,
administrative-service annex,
The second addition, a probable core booster trans-
fer air lock, is located on the north side of the
VACB. It is about 81 meters long, 18 meters wide,
and 19 meters high. The addition is rail served and
has an access door on the north end which is about
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Based on its
size and features, this addition probably is used as
an air lock for the transfer of the assembled HLLV
core booster from its environmentally controlled,
final-assembly section to an area in the VACB for
integration with the strap-on boosters. An assem-
bled core booster on a rail transporte
bn the north side of the
VACB in probable preparation for movement into
one of the two HLLV final assembly and checkout
high-bays for strap-on attachment. (s
A probable technical support or administrative-
service annex is located on the south side of the
VACB and is about 42 meters long, 10 meters wide,
and 10 meters high. The annex probably is an ex-
tension of a similar internal annex between the two
HLLV final assembly and checkout high-bays (fig-
ure 10). (s
The strap-on boosters for the HLLV are delivered
by railcar to a large subassembly building, original-
ly built in the late 1960s and early 1970s for the
SL-X-15 program, which is connected by a covered
rail line to the south side of the VACB (figure 10).
Delivery of a strap-on booster to this building was
first observed in September 1983 and has subse-
quently been observed several times. The building
probably is used for receipt and inspection of the
strap-on boosters and their components, as well as
other subassembly component storage for the new
HLLV. After inspection, the strap-ons probably are
transferred to the VACB low-bay section for final
assembly and checkout prior to mating with the
core booster in one of the two VACB high-bays.
Once assembled and checked out, the HLLV will
be transported horizontally on one of two rail
transporter/erectors (TEs) directly to the launch
pad or to a new building at the nearby Spacecraft/
Upper-Stage Propulsion Facility for probable pay-
load mating. The two former SL-X-15 TEs have
been totally reconfigured to transport the HLLV
and its payload. The TEs, which are normally
parked outside the VACB, are each about 55 me-
ters long, 24 meters wide, and 19 meters high and
travel on a 20-meter-gauge rail network (figure 11).
One TE was observed undergoing an HLLV
weight-simulation test in late December 1982 and
was later used to transport the prototype HLLV to
site W in October 1983. (S
Orbiter Maintenance and Checkout Building
Soviet space shuttle orbiters will be processed be-
tween missions in a large orbiter maintenance and
checkout building (OMCB) under construction
about 400 meters east of the VACB (figure 12). The
building, which is about 232 meters long, 122 me-
ters wide, and 39 meters high, consists of two 34-
meter-high high-bay sections, each with a usable
space about 193 meters long and 45 meters wide,
and 19-meter-high, four-story technical support an-
nexes which have been built along three of the
high-bays' four exterior walls. A 41-meter-wide by
22-meter-high doorway is located on the fourth side
of the high-bay area and can accommodate the
Soviet space shuttle orbiter, which is about 38.0
meters long Groundbreaking
for the building occurred in November 1981, but
actual building construction did not begin until
March 1982. The building probably will be com-
pleted in 1985. (s
The size of the building's high-bay sections indi-
cates that it probably is designed to perform main-
tenance and checkout work on several shuttle orbit-
ers simultaneously. Each bay has underground con-
duits probably for utility and servicing equipment
that will be required for the refurbishment, mainte-
nance, and checkout of the orbiters between mis-
sions. One of the high-bay sections has 24 vent
openings in the roof, while no vent openings have
yet been observed in the other high-bay section.
Other probable support and utilities buildings are
under construction adjacent to the OMCB and the
building is accessed by wide-radius-turn roadways
for probable shuttle orbiter ground transport.
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Spacecraft/Upper-Stage Propulsion Facility
A large, high-bay building (HBB) is under con-
struction in the former SL-X-15 Spacecraft/ Upper-
Stage Propulsion Facility at Support Facility 31
(figure 13). This facility was built in the mid-to-late
1960s for the loading of storable propellants and
installation of ordnance devices onto the payloads
of the SL-X-15 and possibly for the installation of
ordnance devices onto the upper stage of the
launch vehicle. After propellant loading and ord-
nance installation were completed, the payload and
upper stage were transported to the VACB for inte-
gration with the SL-X-15 booster. The HBB proba-
bly will be used for loading storable propellants
onto the space shuttle orbiter and other HLLV-
related payloads. Installation of ordnance devices
onto HLLV payloads and possibly onto upper
stages of the launch vehicle may also be conducted
here. The features and layout of the HBB indicate
that the shuttle orbiter probably will be mated to
the HLLV in the horizontal position and then
transported in that position to the launch pad.
Groundbreaking for the HBB, which is about 146
meters long, 78 meters wide, and 62 meters high,
occurred in April 1981, but actual building con-
struction did not begin until April 1982. The build-
ing is constructed of three-meter-wide structural
steel support columns which form a 132-meter-long
by 42-meter-wide usable high-bay section. A crane-
way with a usable height of about 45 meters is in
the high-bay section and, as indicated by the heavy-
duty building construction, it probably is designed
to lift very heavy loads, such as the shuttle orbiter.
Four-story support annexes, each about 12 meters
wide and 17 meters high, flank both long sides of
the high-bay. As indicated by floor spacings, the
lower two floors of each annex will be used for
technical support and the upper two floors will be
used for administrative-service functions. Two
large, rail-served doorways, one on each end of the
high-bay section, are being built. The doorway fac-
ing the HLLV launch areas is about 30 meters wide
and 42 meters high and will allow passage of a hor-
izontally transported HLLV with payload. The
doorway at the opposite end of the buildin is
about 30 meters wide The
building probably will be completed in 1985.
The transporter/erector rail line has been extended
from the existing TE rail network to just outside
the larger of the two doorways in the HBB and
probably will terminate inside the high-bay section.
In addition, a single reinforced-rail spur is being
built which probably will allow movement of stand-
ard-gauge, heavy-duty payload rail transporters
into the center of the HBB for payload propellant-
loading or mating to the HLLV. A single standard-
gauge rail line accesses the smaller doorway of the
HBB (figure 13). (S
The propulsion-related buildings within the facility
do not appear to have been altered, suggesting that
they may continue to be used for relatively small
payloads. A 20-meter-long by 13-meter-wide proba-
ble propellant-related support building and a
steamline are being constructed within the facility.
An underground conduit for probable propellant
and utility lines is being built inside the facility to
connect the HBB with an existing probable pro-
pellant storage building. (s
Launch Control Center
A new LCC is under construction about 600 meters
west of the VACB and just north of the former SL-
X-15 launch control bunker which supported SL-X-
15 launches from site J (figure 14). The LCC ap-
pears to be identical to that at Launch Site W and
will be used to support the prelaunch checkout,
countdown, and launch of the HLLV from Launch
Site J. The new LCC is about 3.1 km from the
nearest launch pad at site J and is connected by
conduits which probably will carry monitoring and
control cabling to the site and to a tracking facility
located adjacent to the east side of Tyuratam Sup-
port Facility 1. The LCC is constructed of rein-
forced-concrete sections and is about 68 meters
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long, 43 meters wide, and 18 meters high and has
three levels with a personnel accessway located on
the south side of the middle level. Like at Site W,
the LCC probably will be bunkered. (s
The LCC will be connected by conduits to the old
launch control bunker, and at least two support
buildings are under construction adjacent to the
LCC. One of the support buildings is on the west
side of the LCC and probably will provide person-
nel and technical services, including computer-re-
lated support for launch operations. The layout of
the building appears identical to that of its counter-
part adjacent to the site W LCC. Early construc-
tion features of the second support building, lo-
cated south of the LCC, indicate that it will be sim-
ilar to the probable LN storage building located
near the site W LCC. (s
Support Facility 1
Support Facility 1, located east of Support Facility
31, was expanded in the mid-to-late 1960s for the
final assembly, integration, and checkout of the
fourth stage and payload for the SL-X-15 (figure
15). Most, if not all, of the former SL-X-15 pro-
gram-associated buildings are being renovated and
construction of several small support buildings is
under way adjacent to the SL-3/4/6 booster and
payload assembly/checkout area. The renovation
and construction activities, under way since 1978,
indicate that this facility will be used for similar
purposes for the new HLLV and probably also for
spacecraft to be launched on the shuttle orbiter.
Refurbishment of the former SL-X-15-associated
assembly/checkout building in Support Facility 1
began in January 1978. At that time, what was
probably SL-X-15 upper stage/payload-associated
debris was seen outside the building. In mid-1978,
two derelict SL-X-15 upper stages were moved out-
side the building and later disassembled. Two_
parabolic dish antennas were in-
stalled atop pedestals on the roof of the western
side of the building in late 1979. These antennas
may be used to receive and transmit on-pad pay-
load checkout telemetry during prelaunch opera-
tions. (S
Five support buildings, one of which is connected
to a new induced-draft water cooling tower, have
been or are being built near the assembly/checkout
building. In addition, an underground conduit
about 2 meters wide has been
constructed between the largest of the new support
buildings and the SL-3/4/6 booster and payload as-
sembly/checkout area. The conduit may be used as
a personnel passageway or for cable and utility
lines. (s
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Secret
Appendix
Soviet Heavy-Lift Launch
Vehicle
A prototype of the Soviets' new heavy-lift launch
vehicle (without payload) was seen for the first time
at Launch Site W, Tyuratam
Missile and Space Test Center. The HLLV con-
sisted of a core booster and four strap-on, thrust-
augmentation boosters. The launch vehicle was
erected on the pad and probably was undergoing
the initial series of compatibility checks with the
pad facilities. The HLLV was removed from the
pad by a trans orter erector and returned to the
VACS (S
Vehicle Components
The HLLV core booster is about 59 meters long
and has two or three
main propulsion engines that will use LOX and LH
propellants (figure 16). The core booster serves as
the structural backbone of the HLLV configura-
tion, in that the strap-on boosters and payloads are
mounted to it for launch. (s
The core booster consists of two major components
which are manufactured at Kuybyshev Aerospace
Plant I and are individually air-transported atop
modified Bison aircraft to Tyuratam. The larger
component
The strap-on, thrust-augmentation boosters are as-
sembled at Dnepropetrovsk Missile Development
Production Center and are shipped to Tyuratam by
flatbed railcar. Each strap-on booster is about 40
meters long and 4.0 meters in diameter and is de-
rived from the 4.0-meter-diame-
ter first stage of the SL-Y, a medium-lift space
launch vehicle also under development at Tyuratam
(figure 17). The additional length of the strap-on is
for an asymmetric nosecone which is attached to
the intertank of the core booster and which could
house a recovery parachute system if the strap-on is
to be reused. The liquid-propellant strap-on boost-
ers will use LOX and probably a hydrocarbon-
based fuel such as kerosene. Analysis of the base of
the first stage of the SL-Y suggests that its propul-
sion system will use a single nozzle. Also, a ring
appears to encircle the end of the nozzle and appar-
ently is connected to three or four possible actua-
tors on the booster. The ring could be pivoted into
the exhaust flow from the nozzle and provide thrust
vector control for the booster during launch.
Vehicle Configuration
The prototype HLLV observed at Launch Site W
in October 1983 was about 59 meters long
and its strap-on boosters were
mounted offset on the core booster. The position-
ing of these strap-ons toward one side is designed
to accommodate the attachment of large payloads,
such as the shuttle orbiter, on the opposite side of
the core and to counter the center-of-gravity shift
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krontains the LOX tank and intertank
section. Upon delivery to the VACB, aerodynamic
covers are removed from the two components and
they probably are checked out before being mated.
At some point during core booster processing, two
or thre "podded" engines are at-
tached to the base of the LH tank and constitute
the propulsion system for the core booster. The
pods could also house a recovery system for the en-
gines if they are reusable. (S
caused by side-mounted payloads. The Soviet shut-
tle orbiter will be attached to the core booster in a
manner similar to that used in the US shuttle 25X1
launch system (figure 18). Variants of the HLLV
may be developed which will use differing numbers
of strap-ons, high-energy-propellant upper stages,
and be capable of launching either side- or top-
mounted payloads. Although up to eight strap-ons
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could physically be accommodated around the core,
it is unlikely such an HLLV variant will be devel-
oped. Based on launch pad configurations, HLLVs
launched from site W apparently will be limited to
four strap-ons. Those launched from site J will
have at least four and possibly six strap-ons, de-
pending on the final pad configuration, the capabil-
ities of the TE, and the mounting position for the
payload. (s
Vehicle Final Assembly and Processing
The final assembly and processing procedures for
the HLLV components at Tyuratam are signifi-
cantly different from those employed during the
SL-X-15 program. During the SL-X-15 program,
the thousands of pieces and subassemblies required
for each booster were shipped by rail to the VACB
at Support Facility 31, where both the final fabrica-
tion and assembly of the booster occurred
indicated that poor design and
quality control of the SL-X-15 booster were major
contributors to the launch failures and ultimately
the cancellation of the program. In contrast, the
major components of the HLLV are fabricated,
assembled, and tested at the manufacturing plant
before shipment to Tyuratam, thus ensuring better
factory control over component quality. Little, if
any, final fabrication of the HLLV at Tyuratam is
necessary. The final assembly of the HLLV essen-
tially involves the checkout of a few large compo-
nents and their integration into one unit. Total ve-
hicle processing time has thereby been significantly
reduced from that of the SL-X-15 booster. Thus,
the HLLV processing facilities at Tyuratam should
be able to support a much higher launch rate than
that believed attainable during the SL-X-15 pro-
gram. (S
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