KAPUSTIN YAR CRUISE TEST COMPLEX D, SITE 1

• Document Type: CREST
• Collection: NGA Records (Formerly NIMA)
• Document Number (FOIA) /ESDN (CREST): CIA-RDP83T00574R000103060001-6
• Release Decision: RIPPUB
• Original Classification: S
• Document Page Count: 29
• Document Creation Date: December 28, 2016
• Document Release Date: February 1, 2010
• Sequence Number: 1
• Publication Date: December 1, 1982
• Content Type: REPORT

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PICA-15/0606/82
DECEMBER 1982'
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Kapustin Yar Crui
se Test Complex D, Site 1
CATEGORY BE NO. COMIREX NO.
USATC. Series 200, Sheet 0235-22, scale 1:200,000 (UNCLASSIFIED)
ABSTRACT
1. (S/WN) Kapustin Yar Cruise Test Complex D, Site 1, referred to in this report as Complex D, is a
major Soviet facility supporting the development and testing of ground-launched, air-breathing cruise
vehicles. This includes vehicles with reconnaissance, target, and probable land-attack missions. This re-
port discusses all construction activity observed at Complex D and all cruise vehicle programs related to
this facility.
2. (S/WN) This is the first NPIC basic report on Complex D and it satisfies the basic reporting
requirement for that installation. A location map, 44 annotated photographs, two conceptual drawings,
and three inset tables of mensural data are included in this report. The information cutoff date is
3. (S/WN) Kapustin Yar Cruise Test Complex D, Site 1, (Figure 1) is in the southwestern USSR
approximately 140 kilometers (km) southeast of Volgograd and 19 km north of Akhtubinsk Flight Test
25X1
25X1
4. (S/WN) Complex D is a component of the Vladimirovka Advanced Weapons and Research
Complex (VAWARC) and is a major test and development center for ground-launched cruise vehicles.
This facility also serves as the major target drone launch facility supporting air-to-air missile (AAM) testing
at the VAWARC. Cruise vehicle/drone programs that have been associated with Complex D include
probable large surface-launched aerodynamic missiles,' the DR-1 (LA-17) target and reconnaissance
drones, the DR-2 (Luggage) long-range reconnaissance drone, the DR-3 (ADV-1) battlefield reconnais-
sance drone, the ADV-2 probable long-range reconnaissance drone, the ADV-4 probable battlefield
reconnaissance drone, and a probable long-range, ground-launched cruise missile (GLCM).
5. (S/WN) Support for the cruise vehicle development programs at Complex D is primarily provided
by three installations: Akhtubinsk FTC, Ramenskoye FTC and Kapustin Yar Complex D 25X1
Center
SSM Support Facility
BASIC DESCRIPTION
6. (S/WN) Complex D (Figure 2) is a rectan-
gular, triple-fence-secured facility with dimensions
of approximately 3,500 by 650 meters. The long
axis of the Complex is oriented north/south. Com-
plex D consists of four areas: Site 1 (the southern-
most area), Site 2, Site 3, and Site 4 (the northern-
most area). When first identified in September
1957, only Site 1 and Site 2 were under construc-
tion (Figure 3). By December 1959, construction
was well underway at Sites 3 and 4. (A detailed
construction history for each site is presented in
paragraphs seven through 20.)
Construction History
7. (S/WN) Site 1 (Figure 4) was probably ini-
tially constructed to support a large, surface-
launched aerodynamic missile program. Most of
the permanent structures had been completed by
September 1957. These included the main con-
crete launch pad, the rail-served launch structure
and an associated rail-mounted tower crane, the
launch control bunker (item 5), a small personnel
bunker (item 6), three support buildings (items 2,
3, and 8), a probable pumphouse (item 9), a par-
tially buried water/POL storage tank, and a large
catch basin. In addition, Kapustin Yar Complex D
SSM Support facility, which is connected by rail to
Site 1, was under construction at this time.
8. (S/WN) Between September 1957 and De-
cember 1959, the Site 1 launch pad was being
expanded to accommodate a fixed erector/laun-
cher device and launch rail probably used by
another large, surface-launched aerodynamic mis-
sile. Other additions to Site 1 included an opera-
tions support building (item 1), a probable track-
ing support building (item 10), two general sup-
port buildings (items 4 and 7), four optical trackin-
WNINTEL
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g/recording positions, and a second partially un-
?derground water/POL tank.
9. (S/WN) By February 1962, a large concrete
support apron and loop road had been added to
the Site 1 launch pad. A large light tower was
erected in the middle of the support apron. A
drive-down entrance extending under the apron is
on the northwest side of the apron. In addition,
this apron is flanked by two tall lightning arresters.
10. (S/WN) By April 1965, some of the struc-
tures built to support the probable large, surface-
launched aerodynamic missile programs had been
dismantled. Both the fixed erector/launcher and
the large traveling tower crane which support the
rail-served launch structure had been removed.
11. (S/WN) Only a few changes to the facili-
ties at Site 1 have been noted since 1965. These
included the dismantlement of the entrance to the
personnel bunker (item 6), the removal of a part of
the pumphouse roof (item 9), and the addition of
several optical tracking/recording positions.
12. (S/WN) Site 2 (Figure 5) was initially iden-
tified under construction in September 1957. All
major construction in this area had been halted by
December 1959 with the site still largely incom-
plete. The cruise vehicle which Site 2 was intended
to support has never been identified. It is likely
KAPUSTIN YAR CRUISE
TEST COMPLEX D, SITE 1
AKHTUBINSK/VLADIMIROVKA
that this program was cancelled prior to the start
of its flight testing which led to the cessation of
construction at Site 2. Since 1959, Site 2 has prima-
rily served as a storage/support area for Sites 1 and
3. Structures completed in this area include two
small, irregularly shaped concrete pads, a large
control bunker (item 3), a small control bunker
(item 4, dismantled in 1976), a large storage/park-
ing apron, and two support buildings (items 1 and
2). The base of a partially underground water/POL
tank was in place by December 1959; however,
this tank was never completed.
13. (S/WN) The construction of Site 3 (Figure
6) began after September 1957. By December 1959,
most of the major facilities in this area were either
complete or under construction and testing had
already begun on the DR-2. The completed facili-
ties included the main concrete launch pad and
loop road, a small partially underground control
building, a large U-shaped revetment with a cen-
tral support building, several general support
buildings (items 4, 5, and 8), and five probable
optical tracking/recording positions. In addition, a
large, drive-through checkout building (item 1)
and a large operations/administration building
(item 2) were in the midstages of construction.
14. (S/WN) By April 1962, both the checkout
building and the large operations/administration
(Continued p. 8)
AKHTUBINSK
FLIGHT TEST CENTER
AKHTUBI NSK/VLADI MIROVKA
AREA AIRFIELD
FIGURE 1. LOCATION OF KAPUSTIN YAR CRUISE TEST COMPLEX D, SITE 1, USSR
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KAPUSTIN YAR COMPLEX D
SSM SUPPORT FACILITY
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building had been completed. A heating plant
(item 3) was also constructed. The previously iden-
tified small control building was also removed.
15. ' (S/WN) Since April 1962, construction ac-
tivity at Site 3 has mainly been limited to small
structures built to support specific cruise vehicle
programs. A small concrete launch ring had been
completed by June 1964. This construction has
been used as a launch position for the DR-2, the
DR-3, the ADV-2, and the ADV-4. A large control
building (iterrr.9), replacing the original small con-
trol building, was identified in April 1971. A large
checkout tent has been present at Site 3 since
January 1973. This tent originally supported the
early -testing of the DR-3 and later supported the
ADV-2 program. A small vehicle storage building
(item 6) had also been completed by 1973. A
Quonset-type storage/support building (item 7),
started in September 1978, was completed during
June 1979. A small checkout tent supporting the
ADV-4 program was first observed in September
1979.
16. (S/WN) Site 4 (Figures 7 and 8) was first
identified under construction in December 1959.
As Site 2, this area was never completed. However,
Site 4 has been used for field-testing/training exer-
cises of both the DR-2 and DR-3. In December
1959, grading for the launch pad was underway. A
large excavation, probably for a control bunker,
was immediately north of the launch area. One
onsite support building and two general support
buildings were also under construction.
17. (S/WN) By April 1962, the launch pad had
been partially finished with concrete and the pre-
viously identified onsite support building and gen-
eral support buildings had been completed. An
additional support building had also been con-
structed.
18. (S/WN) A probable optical tracking/re-
cording position had been added to Site 4 by April
1965 (Figure 7).
19. (S/WN) Between April 1965 and April
1971, several significant changes to Site 4 were
identified. The onsite support building was dis-
mantled/destroyed (Figure 8) and all the other
general support buildings were razed. A graded-
earth launch ring, similar to the concrete launch
ring at Site 3, was added northeast of the incom-
plete Site 1 launch pad. This ring was later finished
with concrete.
20. (S/WN) A second graded-earth launch
ring was identified approximately 800 meters north
of Site 4 in August 1973.
Cruise Vehicle Test Programs
21. (S/WN) This section of the report deals
with the cruise vehicle systems that have been
associated with Complex D. Each system will be
discussed separately and will include the follow-
ing: a description of equipment associated with
the system, a general summary of the test pro-
gram, and a detailed analysis of the significant
events observed during the test program.
Early Surface-to-Surface Cruise Missile Programs
22. (S/WN) The first test programs con-
ducted at Complex D probably involved large sur-
face-launched aerodynamic missiles with a land-
attack mission. Although these missiles were never
observed, it is possible that their design was influ-
enced by two US surface-to-surface cruise missiles
(SSCMs), the SNARK and the NAVAHO, which
were under development in the 1950s.2 The Soviet
SSCMs were probably `launched from two large
devices observed at Site 1.
23. (S/WN) The first of these devices, proba-
bly completed in 1957, was the rail-served launch
structure (Figure 9). The launcher is at the end of a
railspur connecting Site 1 with the SSM support
complex. This launcher is comprised of two major
components, the erecting/launching mechanism
and a large curved section. The erecting/launch-
ing mechanism is
wide. This mechanism pivots, with the aft portion
traveling along a single rail mounted atop the
launcher's curved section. Two probable blast ar-
eas are behind the curved section. The location of
the blast areas indicates that the erecting/launch-
ing mechanism was inclined at least 45 degrees for
launches. The blast areas also indicate that the
main launch orientations from this launcher were
90 degrees and 20 degrees. A large rail-mounted
tower crane (Figure 10) was probably used to ser-
vice the vehicle on the launcher.
24. (S/WN) The second device identified at
Site 1, the fixed erector/launcher (Figure 10), was
constructed between 1957 and 1959. An irregularly
shaped probable erecting mechanism is situated at
the western end of the fixed launcher. A 33-meter-
long, probable, dual-launch rail extends eastward
from the erecting mechanism. The probable
launch orientation from the fixed erector/laun-
cher was approximately 90 degrees.
25. (S/WN) The US SSCMs SNARK and NA-
VAHO proved to be heavy, inaccurate, and vul-
nerable to interception and were abandoned in
favor of ICBMs. It is likely that similar problems
were encountered with the Soviet SSCM pro-
grams, as none were ever deployed. By 1965, the
rail-mounted tower crane which supported the
rail-served launch structure had been removed.
Also removed was the erecting mechanism for the
fixed erector/launcher. No further activity relating
to these launch devices has been identified.
Probable Target/Reconnaissance Drones
26. (S/WN) DR-1. The DR-1 (LA-17) is a
straight-wing subsonic drone powered by a turbo-
jet engine mounted under the fuselage. Designed
in the early 1950s by the Lavochkin Experimental
Design Bureau (OKB), the DR-1 has been used in
both the target and reconnaissance roles.3
27. (S/WN) The DR-1 (Figure 11) is0 25X1
long with afuselage diameter. The wing 25X1
span of this vehicle is The ventral- 25X1
mounted engine nacelle is 4 meters long with a
diameter.
28. (S/WN) The DR-1 launcher (Figure 11) is
a two-axle towed carriage. A small launch rail is
mounted atop the carriage. The overall length of
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OPTICAL TRACKING/
RECORDING POSITION
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FIGURE 10. RAIL-MOUNTED TOWER CRANE AND FIXED ERECTOR/LAUNCHER, SITE 1
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29. (S/WN) The ground-launched version of
the DR-1 (LA-17) is assisted at launch by two strap-
on boosters (Figure 12). These boosters are ap-
proximately~long with a diameter oc--]
meter.
30. (S/WN) The DR-1 has been present at
Complex D, Site 1, since at least April 1965. The
number of deployed DR-1 launchers at Site 1 in-
creased from two in the 1960s to as many as five by
1978. Since late 1980, four DR-1 launchers have
normally been observed.
31. (S/WN) Akhtubinsk/Vladimirovka ASM
and AAM Storage Facility a com-
ponent of Akhtubinsk FTC, has served as t e main
receiving/storage/checkout facility for the DR-1
since the 1960s. When required for launches, the
DR-1s are shipped by road from the storage facility
to Complex D (Figure 13).
32. (S/WN) The DR-1 has been used at the
VAWARC primarily as a target for AAM testing.
However, reconnaissance variants of this drone
have probably also been flight tested at Complex
D. Evidence of a probable DR-1 reconnaissance
drone field-testing/training exercise was obtained
in June 1978. On 7 June, two DR-1 launchers, one
with a DR-1 (Figure 14), were deployed approxi-
mately 500 meters south of Site 1. Several support
trucks, trailers, and tents were also observed. This
equipment was not from Site 1, which still had five
previously identified DR-1 launchers. All of the
field-deployed equipment had been removed by 4
July. This field deployment of the DR-1 may have
been related to a similar DR-2 deployment and a
possible DR-3 deployment which occurred in the
VAWARC area during the summer of 1978.
33. (S/WN) DR-2. The DR-2 (Luggage; RAM-
A) is a large, delta-wing, turbojet-powered rec-
onnaissance drone associated with the Tupolev
OKB. This vehicle is designed for high-altitude,
supersonic flight with a maximum range of over
3,000 km.4
34. (S/WN) The DR-2 (Figure 15) has a 26-
meter fuselage with a maximum diameter ofC 25X1
meters. The forward end of the fuselage tapers to
a point. The large delta wings are mid-mounted on
the fuselage and have a span of 8 meters. Large,
triangular, horizontal stabilizers, with a span ofL
meters, are at the rear of the fuselage and a single
vertical stabilizer is mounted atop the aft fuselage
section.
25X1
25X1
35. (S/WN) The original flight testing of the
DR-2 involved the use of a probable fixed inclined
launcher at Site 3 (Figure 16). This launcher was
approximately 21 b 2 meters. The launcher was
approximately high at the aft end and 25X1
high at the forward end. Launches con- 25X1
ducted from this device had a heading of approxi-
mately 90 degrees. This launcher was only ob-
served in December 1959.
36. (S/WN) Since at least 1964, the DR-2 has
used a towed semitrailer transporter/launcher
(Figure 15). This semitrailer is Ometers. 25X1
When set up in its firing position, the front end of
the launcher is slightly raised while the aft end is at
ground level.
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37. (S/WN) A large, chamfer-roofed van
trailer probably serves as the main checkout vehi-
cle for the DR-2. This checkout van trailer (Figure
15) is Several fuel/oxidizer and
cargo trucks also support DR-2 launch operations.
38. (S/WN) Flight testing of the DR-2 began
between 1957 and 1959. In December 1959, the
probable fixed inclined launcher was present,
along with several support vehicles, at Site 3. Blast
marks behind this device confirmed its use as a
launcher. This fixed inclined launcher was proba-
bly used primarily for the initial aerodynamic and
propulsion testing of the DR-2.
39. (S/WN) In June 1964, a DR-2 was first
observed on the towed transporter/launcher.
Launches were being conducted from the newly
constructed launch ring at Site 3. In July 1966, two
DR-2s were identified for the first time at Complex
D (Figure 17). Testing of this system at Site 3
continued throughout the remainder of the 1960s.
It was also during this time that DR-2-associated
equipment was identified in the Tupolev area of
Ramenskoye FTC, firmly linking that OKB with the
DR-2 program.
40. (S/WN) The DR-2 had been deployed in
limited numbers by the early 1970s and DR-2-
related activity observed within the VAWARC area
during this time was probably indicative of field-
training exercises and not developmental testing.
At Complex D, these exercises were conducted
within Site 4 where two launch rings had been
constructed by 1973 (Figure 18). Exercises within
this area were detected in August and September
1973, February and March 1976, September 1976,
and August 1978.
41. (S/WN) DR-3. The DR-3 (ADV-1) is a
small, subsonic, low-altitude, battlefield reconnais-
sance drone developed by the Tupolev OKB. The
DR-3 is propelled by a solid-propellant booster
and a turbojet sustainer engine.5
42. (S/WN) The DR-3 (Figure 19) is 7 meters
long with a maximum fuselage diameter ofC
meter. It has an aft-mounted, clipped delta wing
with a span of A single vertical stabil-
izer is mounte atop the aft section of the fuse-
lage. The air intake for the turbojet sustainer en-
gine is mounted atop the fuselage approximately
aft of the nose.
43. (S/WN) The original prototype launcher
for the DR-3 (Figure 20), used prior to 1975, is a 16-
meter-long flatbed trailer. The aft end of this
launcher is wide. A box-like structure is
mounted atop the trailer approximately 6 meters
aft of the launcher's front end. This structure isC
meters long, wide, and 0 high.
The box-like structure probably simulated a por-
tion of the launch canister seen on the operational
DR-3 transporter-erector-launcher (TEL).
44. (S/WN) The DR-3 TEL (Figure 20), used to
launch the DR-3 since 1975, is a variant of the ZIL-
135 8x8 wheeled vehicle. The TEL has an overall
length of and a width of
Mounted on the back portion of the TEL is the
launch canister which is 8 meters long and E
meters in diameter. A large end cap covers each
end of the canister. The front end of the canister is
elevated approximately 20 degrees for launch pur-
poses. A probable sliding tray/rail (Figure 21) is
contained within the launch canister.
45. (S/WN) The DR-3 resupply vehicle (Fig-
ure 22) is also a variant of the ZIL-135. This vehicle
is 13 meters long overall with a maximum width of
3 meters. The aft portion of the resupply vehicle is
a 9-meter-long cargo area covered by ribbed can-
vas.9
46. (S/WN) The DR-3 is shipped in a unique
container (Figure 22) which is
Two distinct ribs/handling bands extend longitudi-
nally atop the container.
47. (S/WN) Testing of the DR-3 probably be-
gan at Complex D during the early 1970s. These
tests were accomplished using the prototype laun-
cher which was first observed at Site 3 in January
1972. This launcher (Figure 23) was used until the
DR-3 TEL became available in 1975. During this
time period, DR-3-associated equipment was re-
peatedly observed in the Tupolev area of Ramen-
skoye FTC and at Akhtubinsk FTC. Testing of the
DR-3 at Complex D was confined to Site 3 until
August and September 1977. During this time, a
large-scale field-testing/training exercise was con-
ducted at Site 4 (Figures 24 and 25). The DR-3 was
probably first deployed to operational units during
1977 or 1978. Testing of the DR-3 continued at Site
3 through April 1979. revealed 25X1
an open TEL with a probable DR-3 (Figure 26). DR-
3 testing was moved to Site 1 in June 1979 probably
to make room for increased ADV-2 testing at Site
3. With an apparent standdown in ADV-2 activity,
the DR-3 resumed testing at Site 3 in July 1982.
48. (S/WN) ADV-2. The ADV-2 is a large
aerodynamic cruise vehicle which has been under-
going flight testing at Complex D since at least
1976.6 This vehicle, which was probably designed
by the Tupolev OKB, utilizes a probable solid
rocket booster and a turbojet/turbofan sustainer
engine.? The intended function of the ADV-2 has
yet to be confirmed. The association of the ADV-2
with the Tupolev OKB, which developed the DR-2
and DR-3 systems, suggests a reconnaissance mis-
sion. However, the use of the ADV-2 in a land-
attack role is also possible.
49. (S/WN) The ADV-2 is similar in appear-
ance to the smaller DR-3. It is likely that the design
of the ADV-2 was greatly influenced by the success
of the earlier Tupolev reconnaissance drone.
Three versions of the ADV-2 have been identified.
The three vehicles differ from each other primarily
in the design and location of the various control/
lifting surfaces. All three variants, designated ADV-
2a, ADV-2b, and ADV-2c (Figure 27), have aC
meter fuselage with a diameter. As the
DR-3, all variants of the ADV-2 have a dorsal-
mounted air intake on the aft portion of the fuse-
lage. A single vertical stabilizer is mounted atop
the rear of the vehicle.
50. (S/WN) The ADV-2a (Figure 28), first ob-
25X1
25X1
25X1
25X1
served on has aft-mounted, 25X1
clipped delta wings with a s an of and a 25X1
root chord of Two sets of rounded 25X1
foreplanes are on the forward section of the fuse- 25X1
lage.
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I)cv-I
25X1
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51. (S/WN) The ADV-2b (Figure 28), first ob-
served on has clipped delta
wings with a span of and a chord of
meters: A single set of clipped foreplanes is
mounted forward on the fuselage. ,
52. (S/WN) The ADV-2c (Figure 29), first
identified on also has a single set of
foreplanes similar to those on the ADV-2b. The
wings of the ADV-2c, however, are of simple delta
design (not clipped) with a span of
a chord of
53. (S/WN) The ADV-2 prototype launcher
(Figure 30), of which two have been identified, is a
double-axle towed trailer. A raised
cradle used to support the ADV-2, is centerline
mounted on the trailer and is
The prototype launchers are towed from the for-
ward end.
54. (S/WN) The new-type ADV-2 launcher
(Figure 31) is also a towed trailer but is towed from
the aft end. The new-type launcher is equipped
with a hinged platform which supports the for-
ward section of the ADV-2. When this platform is
lowered, the launcher is long. When
raised, the launcher is long. The
launch cradle on the new-type launcher is re-
cessed and is long. Two of the new-type
ADV-2 launchers have been observed to date.
55. (S/WN) The ADV-2 transporter (Figure
32) is also a towed Olong, double-axle
trailer which is normally canvas covered. The can-
vas is draped over a light framework which gives
this vehicle a ribbed appearance.
56. (S/WN) The ADV-2 checkout van trailer
(Figure 28) is a long, chamfer-roofed
vehicle. Eight vents, four along each side of the 2 Al
chamfered roof, and two box-like protrusions
have been identified on the van body. This van
trailer is probably used for electronics/guidance
system checkout of the ADV-2.
57. (S/WN) All of the ADV-2-associated
towed trailers have been observed attached to
KRAZ-214/255 or ZIL-131 prime movers.
58. (S/WN) The ADV-2 special-purpose vehi-
cle set (Figure 33), first observed in June 1979, is,
comprised of two tracked vehicles and one van-
bodied truck. The tracked vehicles are
meters. The van-bodied truck is a probable URAL-
375 workshop. These vehicles are normally ob-
served at the Site 3 launch pad when the ADV-2 is
being prepared for flight (Figure 28). It is likely
that the special-purpose vehicle set serves some
checkout/calibration function for the ADV-2.
59. (S/WN) The ADV-2 booster (Figure 31) is
a probable solid rocket motor used to assist the
launch of the cruise vehicle. The identification of
spent boosters downrange from Complex D (Fig-
ure 12) indicates that the booster is jettisoned
immediately after launch. The ADV-2 booster is
shipped in a rectangular container (Figure 31)
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which is wide, and 25X1
meter high.
60. (S/WN) AD airframe (Figure 34)
which has been observed mounted under the port
wing of a BACKFIRE B may also be associated with
the ADV-2 program." An ADV-2 checkout van
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(Continued p. 26)
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trailer was observed adjacent to the BACKFIRE-
mounted airframe during May 1980 at Akhtubinsk
FTC. The use of the ADV-2-associated van trailer
suggests that the airframe contains an
electronics/guidance system similar to that of the
ADV-2. No control/lifting surface has ever been
observed on the airframe.
61. (S/WN) The development of the ADV-2
appears to have incorporated three phases of test-
ing. The first phase was probably for basic aerody-
namic, control, and propulsion evaluation. The
second phase of testing produced aerodynamic
changes to the ADV-2 and probably developed the
ADV-2 electronics/guidance systems. The third
phase was characterized by a significant increase
in ADV-2 launch activity and may be a precursor
to an operational deployment of this system.
62. (S/WN) ADV-2-associated equipment was
first identified in the Tupolev area of Ramenskoye
FTC during 1974. Testing of this system at Complex
D had begun by 1975 where an ADV-2 transporter
was observed in May. This first phase of testing
involved the ADV-2a and the first prototype
launcher, both of which were originally observed
at Site 3 on (Figure 20). This
testing continued through at least April 1977.
None of the support equipment tentatively associ-
ated with the ADV-2 electronics/guidance system
was observed during this period. These initial tests
were probably to evaluate the aerodynamic, con-
trol, and propulsion characteristics of the ADV-2.
63. (S/WN) The testing of the ADV-2 elec-
tronics/guidance system components probably be-
gan in 1978 and continued into 1981. During this
period, several significant events, probably related
to the electronics/guidance testing, were ob-
served.. In May 1978, an ADV-2 checkout van
trailer and RSBN-4N short-range navigational aids
(Figure 35) were deployed to Site 3. By December
1978, the second prototype launcher was at Com-
plex D. ADV-2b testing from this launcher began
in February 1979. Testing of the BACKFIRE-
mounted airframe began in May 1979
at Ramens oye FTC. The ADV-2-associated spe-
cial-purpose vehicle set was deployed to Complex
D in June 1979. The airframe and an
ADV-2 checkout van trailer were observed at
Akhtubinsk FTC during May 1980. Aerodynamic
refinement of the ADV-2 led to the ADV-2c which
began testing on the second prototype launcher in
May 1980. In June 1980, an ADV-2, two ADV-2
checkout van trailers, and the airframe
were transferred from Complex D and Akhtubinsk
FTC to Ramenskoye FTC. In December 1980, ADV-
2c testing from the first new-type launcher began
at Complex D (Figure 36). The identification of
spent ADV-2 boosters downrange from Site 3 indi-
cated that at least two, southeast-oriented
launches had been conducted from the new-type
launcher by June 1981. All previous ADV-2s had
been launched in an easterly direction.
64. (S/WN) The third and possibly final pre-
deployment phase of ADV-2 testing was con-
ducted at Complex D from August 1981 through
May 1982. At least 15 ADV-2c launches occurred
during this period. All of these launches were
conducted from the new-type ADV-2 launchers,
the second of which arrived at Site 3 in April 1982.
Three launch orientations were used for these
tests: east, southeast, and south-southeast. No
sightings of either the ADV-2 checkout van trailer
at Complex D or the airframe at Ram- 25X1
enskoye FTC were made during this time. It is 25X1
likely that the guidance system and possibly a
reconnaissance package for the ADV-2 had been
fully developed by August 1981 and that subse-
quent testing was of the complete ADV-2 system.
65. (S/WN) No ADV-2 or ADV-2-associated
launch activity has been observed at Complex D
since May 1982. This apparent hiatus in launch
activity was accompanied by the removal of ADV-2
equipment from Site 3 (Figure 37). During June
and July, the missile checkout tent was dismantled.
One of the new-type ADV-2 launchers and the
associated special-purpose vehicle set were re-
moved. All of the solid rocket booster shipping
containers were also removed.
66. (S/WN) The significant decrease1in ADV-
2-associated activity and equipment at Complex D
may indicate that the test program of this probable
reconnaissance drone has been completed. If the
Soviets intend to operationally deploy the ADV-2,
field-training exercises, similar to those observed
for the DR-2 and DR-3, may be conducted in the 25X1
near future.
67. (S/WN) ADV-4. The ADV-4 is a small,
TEL-launched cruise vehicle on which testing be-
gan at Complex D during 1978. This vehicle is
probably intended to be used as a highly mobile,
short-range battlefield reconnaissance drone.
68. (S/WN) The ADV-4 (Figure 38) is 3 meters
long with afuselage diameter. The vehi- 25X1
cle has a tapered straight wing with a span of 0 25X1
meters, a wing root chord of and a 25X1
wing-tip chord of The horizontal stabil- 25X1
izer has a span of A small vertical 25X1
stabilizer is mounted atop the rear the fuselage.
The configuration of the ADV-4 engine has not yet
been identified on imagery.
69. (S/WN) The ADV-4 TEL (Figure 38) is a
tracked vehicle similar in appearance to the M- 25X1
1974 122mm self- ropelled gun chassis. The chassis
is Mounted atop the chassis is a 25X1
probable launch rail and erecting mechanism. The 25X1
rail is mounted offset to the right. A unique cham-
fered cover has often been observed on the TEL
(Figure 39). The cover, with an overall length of= 25X1
meters, overhangs the rear of the chassis by ap-
proximately 2 meters. As many as two TELs have
been observed at Complex D.
70. (S/WN) An ADV-4 TEL was first identified
at Site 3 in May 1978. A small checkout tent which
has been associated with the ADV-4 program had
been erected by June. In April 1979, the second
ADV-4 TEL was first identified at Site 3.
71. (S/WN) By April 1981, three sightings of
the ADV-4 had been made at Site 3. Twice, on 25X1
and on (Figure 40), this 25X1
vehicle was observed on a TEL. Ono a 25X1
probable canvas-covered ADV-4 airframe was
identified in the cargo bed of a ZIL-131 truck
(Figure 41).
72. (S/WN) Testing of the ADV-4 continued
until April 1981. From late April 1981 until March
1982, no ADV-4 launch-related activity was de-
tected at Complex D. The reason for this 12-month
(Continued p. 30)
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halt in launch activity has not been determined.
This may have been an evaluation period prior to
the start of a new test phase. This hiatus could also
have been necessitated by some problem that may
have developed during the first three years of
ADV-4 testing.
73. (S/WN) Testing of the ADV-4 resumed at
Complex D during March 1982 and is expected to
continue for some time. This testing will probably
be required to fully develop the vehicle's propul-
sion, guidance, and possibly a reconnaissance pay-
load before it is operationally deployed.
74. (S/WN) In 1981, the Soviets began testing
a probable, long-range, GLCM at Complex D.9
Equipment at Site 1 indicates that the GLCM may
be related to the SS-NX-21 long-range, sea-
launched cruise missile (SLCM) currently being
tested at Nenoksa Naval Missile Test Center (BE
75. (S/WN) The probable GLCM launch ve-
hicle is a tracked TEL (Figure 42).
Atop the TEL is a centerline-mounted launch tube
(Figure 43) which is long and
in diameter. To date, only one probable GLCM
TEL has been identified.
76. (S/WN) The probable GLCM
container (Figure 42) is an
shipping
meter-diameter cylinder. This container is identi-
cal in size and configuration to those associated
with the SS-NX-21 SLCM.10
77. (S/WN) Several probable GLCM launch
canisters have also been observed (Fi ure 44). The
canisters are 8 meters long and in diame-
ter and are normally observed inline with and
downrange from the TEL. These canisters might be
sealed capsules, each containing a cruise missile,
which are inserted into the launch tube and
ejected either during or just after launch. If so, the
identification of new canisters downrange from
the TEL would indicate a recent GLCM launch.
However, this has never been confirmed and the
exact function of the canisters still has not been
determined.
78. (S/WN) The tracked TEL, minus the
launch tube, was first observed with two adjacent
probable GLCM shipping containers at the Site 1
support apron in October 1980. By
the launch tube had been placed on the TEL and
the entire assembly was moved to the launch pad.
The TEL has also been cable connected to the Site
1 launch control facility.
79. (S/WN) During September and October
1981, preparations for the first probable GLCM
launch were observed. By the launch
tube had been removed from the TEL and two 8-
meter-long cylindrical objects were by the Site 1
operations building. On a KRAZ-
214 cargo truck was observed adjacent to the TEL.
The launch tube had again been placed on the TEL
and the two cylindrical objects were no longer
present. On Oa probable launch canister
was observed adjacent to the launch pad. This
canister was not inline with the TEL and was prob-
ably not used for a GLCM launch. The KRAZ-214
and a support bus were also present on the launch
pad. By I both the KRAZ-214 and the
support bus were gone and the TEL had been
canvas covered. The canvas had been removed by
80. (S/WN) The first probable GLCM launch
occurred between
On the TEL was canvas covered and a
second probable launch canister was observed ap-
proximately 170 meters downrange. The second
probable GLCM launch was probably conducted
in early December and a third probable launch
canister was subsequently observed approximately
210 meters downrange from the TEL. A Modified
CANDID B with a
long tail extension was observed at Akhtubinsk
FTC on This aircraft,
previously associated with the SS-NX-21 SLCM
program," probably supported the GLCM test ac-
tivity observed in 1981.
81. (S/WN) A third probable GLCM launch
occurred between Ima-
gery ofl revealed a fourth probable GLCM
launch canister approximately 160 meters down-
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range from the TEL. The first two launch canisters 25X1
were not present and vehicle tracks in the Site 1
area indicated that they had been recovered byF-] 25X1
I 25X1
82. (S/WN) The GLCM currently being de-
veloped at Complex D is most likely a variant of
the SS-NX-21. Testing of the GLCM will probably 25X1
continue for some time and the operational de-
ployment of this system is not expected before late
1983 or 1984.
Helicopter Sightings
83. (S/WN) On three occassions since 1975, a
helicopter has been observed on the large stor-
age/parking apron at Site 2. The first two sightings
were of new attack/assault helicopters which were
probably undergoing weapons testing at the
VAWARC. The third sighting was of a helicopter
probably being used to support a cruise vehicle
test at Complex D.
84. (S/WN) A HIND D combat assault heli-
copter was at Site 2 on (Figure 45).
The HIND D at the VAWARC was probably related
to the helicopter's weapons test program. HIND D
was first operationally deployed in 1976.92
85. (S/WN) A camouflage-painted HELIX B
amphibious assault/fire support helicopter13 was at
Site 2 on (Figure 46). This
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helicopter was probably involved in some prelimi- LOAM
nary weapons testing at the VAWARC. To date, the
HELIX B has not been operationally deployed.
86. (S/WN) A HIP C probable range-support
helicopter was at Site 2 on (Figure 47).
Activity at Site 3 indicated that an ADV-2 test was
in progress on that date. It is likely that the HIP C
at Complex D or[:=was used to support the
ADV-2 test.
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the preparation of this report.
(S/WN) All applicable satellite imagery acquired through) Ithe information cutoff date, was used in 25X1
MAP OR CHART
US Air Target Chart. Series 200, Sheet 0235-22, scale 1:200,000 (UNCLASSIFIED)
DOCUMENTS
1. CIA/NPIC. PIC/JR-1015/61, Probable Aerodynamic Missile Facilities, Kapustin Yar/Vladimirovka Missile Test
2. Salamander Books Ltd. "Rockets and Missiles, Surface-to-Surface Land Strategic," 1979, pp 58 and 59
(UNCLASSIFIED)
Center, USSR, (S), Apr 61
3. FTD.
FTD-1330W-107-75-SAO, Soviet Remotely Piloted Vehicles (U), 16 Jun 75 (TOP SECRET
-Extracted information is classified SECRET.
4. DIA. DST 2660P-107-81 SAO, Trends and Developments Foreign Technology Weapons and
Systems, Aerodynamic Systems, Soviet Drones (U), 16 Mar 81 (TOP SECRET
-Extracted information is classified SECRETI
IIAR-0176/80. Development of Soviet Aerodynamic Cruise Vehicle-ADV-2 (S), Nov 80
(TOP SECRET
-Extracted information is classified SECRET
7. NPIC. Z-15239/82, Aerodynamic Vehicle Activity, Kapustin Yar Cruise Test Complex D Site 1, USSR, 11 Jun 82
(SECRET
8. NPIC.F I IAR-A111/80, ADV-2-Associated Probable Checkout Van/Trailer Identified at Akhtu-
binsk Flight Test Center, USSR (S), Jun 80 (TOP SECRET
Extracted information is classified SECRET
9. NPIC. Z-14519/82, IAR-0007/82, Cruise Vehicle-Related Activity at Kapustin Yar Cruise Test Complex D, USSR,
August 1981-9 February 1982 (S), Feb 82 (SECRET
81 (TOP SECRET
-Extracted information is classified SECRET/WNINTEL.
11. NPIC. RCA-16/0001/81, Akhtubinsk Flight Test Center (5), Dec 81 (TOP SECRET
-Extracted information is classified SECRET/WNINTEL.
12. DIA. DST-1340S-224-81, HIND Helicopter System (U), 12 Jun 81 (SECRET
-Extracted information is classified CONFIDENTIAL.
13. DOD/Department of the Army, PIM17-82, ATC-11-1340-049-82, HELIX Helicopter (U), Jan 82 (SECRET
COMIREX P02
Project 542060P
(S) Comments and queries regarding this report are welcome. They may be directed tol I Warsaw Pact
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