Каталог - Оружие России 2000 c82-795
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362
PART 2 2
CARRIER-BASED
FIGHTERS
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GROUP 15 AIRCRAFT AND AIRFRAME
STRUCTURAL COMPONENTS
Class 1510 Aircraft, Fixed Wing
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The aircraft is equip-
ped with an in-flight
refueling system.
The cockpit is fitted
out with a sophisti-
cated multifunction
display system to
represent naviga-
tional, tactical and
aiming information,
as well as onboard
systems monitoring
data.
The Su-33 is equip-
ped with a powerful
jamproof pulse-
Doppler radar able
to search for, track
while scanning up to
ten aerial targets against earth (sea) background and
simultaneously engage several targets by missiles. An
optronic aiming system, consisting of an infrared radar
and a laser rangefinder and operating in conjunction
with the pulse-Doppler radar, is integrated with a hel-
met-mounted target designator.
The onboard electronic intelligence system warns the
pilot about illuminating radar threat. To set active jam-
ming, the aircraft carries electronic countermeasures
equipment housed in pods mounted at wing tips.
The flight control and navigation system ensures over-
water and overland flights in any geographic conditions
with aircraft position updating from satellite and long-
range radio navigation systems, return to the aircraft
carrier and approach for landing in the automatic con-
trol mode at weather minima of 30 x 400 m.
The Su-33 weaponry comprises a built-in 30mm gun,
up to 12 RVV-AE, R-27R1, R-27T1, R-27ER1 and R-
27ET1 medium-range air-to-air missiles, R-73E short-
range missiles, Moskit supersonic antiship missiles, as
well as guided and unguided weapons to defeat sur-
face and ground targets.
A multirole version of the Su-33 is available to cus-
tomers. It features enhanced capabilities to engage
aerial targets, effectively operate in the air-to-surface
mode using a wide range of modern high-precision
weapons, conduct reconnaissance and designate tar-
gets for ship-based and airborne weapon systems of a
naval task force.
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Basic Characteristics
Crew 1
Maximum weight, kg:
takeoff 33,000
combat load with takeoff from deck/airfield 6,500/8,000
Speed, km/h:
maximum flight 2,300
carrier-approach 240
Service ceiling, m 17,000
Operating range, km 3,000
Maximum operational g-load, g 8
Engine type, number x thrust, kgf AL-31F(K), 2 x 12,500 (13,300)
363
PART 2 2
SEARCH-AND-RESCUE
HELICOPTER
-
Ka-27PS SEARCH-AND-RESCUE
HELICOPTER
The Ka-27PS helicopter is intended to search for and
rescue flying vehicles on land and at sea and carry out
emergency rescue operations at any time of the day
and year, in VFR and IFR weather conditions, in sea
state up to 5.
The helicopter is equipped with inflatable ballonets to
perform emergency water landing, a winch with a cargo-
lifting capacity of 300 kg, and an external suspension
system to carry cargoes weighing up to 3,000 kg.
Its flight control and navigation complex ensures sta-
bilization of flight modes, automatic flight on a pre-
programmed route, as well as radar-assisted direct-
ing of the helicopter onto a preset waypoint and hov-
ering over it with a high accuracy in the automatic
mode.
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Basic Characteristics
Crew 3
Maximum takeoff weight, kg 11,000
Flight speed, km/h:
maximum 270
cruising 250
eiling, m:
hovering 3,700
service 6,000
Operational range, km 800
Maximum flight duration, h 5
Overall dimensions (length x height x width), m:
helicopter 12.25 x 5.4 x 3.8
cargo cabin 4.52 x 1.32 x 1.3
Main rotor diameter, m 15.9
Engine type, number x power, hp TV3-117VMA, 2 x 2,200
GROUP 15 AIRCRAFT AND AIRFRAME
STRUCTURAL COMPONENTS
Class 1520 Aircraft, Rotary Wing
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364
PART 2 2
ANTISUBMARINE
HELICOPTERS
GROUP 15 AIRCRAFT AND AIRFRAME
STRUCTURAL COMPONENTS
Class 1520 Aircraft, Rotary Wing
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Basic Characteristics
Crew 3
Weight, kg:
maximum takeoff 12,000
combat load 800
Flight speed, km/h:
maximum 270
cruising 250
Service ceiling, m: 6,000
Flight range, km:
in search and attack mode 900
in search mode 1,160
Flight duration in search mode 2 h 15 min
Overall dimensions (length x height x width), m 12.25 x 5.4 x 3.8
Main rotor diameter, m 15.9
Engine type, number x power, hp TV3-117VMA, 2 x 2,200
Ka-28 ANTISUBMARINE HELICOPTER
The Ka-28 antisubmarine helicopter is intended to
search for, detect, track and defeat submerged sub-
marines at a depth of up to 500 m and at a speed of
up to 75 km/h. It can perform search operations in var-
ious climatic conditions, at any time of the day and
year, in VFR and IFR weather conditions, at ranges of
up to 200 km from a takeoff pad, and in sea state of
up to 5.
The helicopter is provided with inflatable ballonets to
perform emergency water landing. The folding blades
of main rotors enable the Ka-28 to stow in shipboard
and airfield hangars.
Its flight control and navigation complex ensures stabi-
lization of flight modes, automatic flight on a prepro-
grammed route, and radar-assisted directing of the
helicopter onto a preset waypoint.
The Ka-28’s armament system comprises:
- APR-3V antisubmarine torpedoes;
- S-3V antisubmarine bombs;
- OMAB-12D, OMAB-25-8N marker bombs;
- RGB-16-1 radar hydroacoustic buoys.
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365
PART 2 2
COMBAT-TRANSPORT
HELICOPTERS
-
GROUP 15 AIRCRAFT AND AIRFRAME
STRUCTURAL COMPONENTS
Class 1520 Aircraft, Rotary Wing
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Basic Characteristics
Crew 2
Normal takeoff weight, kg 11,000
Service range, km 750
Ceiling, m:
hovering 3,700
service 6,000
Flight speed, km/h:
maximum 280
cruising 235
Overall dimensions (length x height x width), m:
helicopter 12.25 x 5.4 x 3.8
cargo cabin 4.52 x 1.32 x 1.3
Main rotor diameter, m 15.9
Engine type, number x power, hp TV3-117VMA, 2 x 2,200
Ka-29 COMBAT-TRANSPORT HELICOPTER
The Ka-29 is intended for use in transport and combat
versions in all latitudes, by day and at night, in VFR and
IFR weather conditions.
In the transport version, the helicopter can carry a
cargo of up to 4,000 kg or 16 troopers with individual
weapons. It is capable of carrying a cargo of up to
4,000 kg by its external suspension gear.
In the combat version, its surveillance and fire control
equipment and four external store racks ensure the use
of various weapons weighing up to 2,000 kg, including:
- guided missiles;
- 80mm unguided rockets;
- versatile gun pods with the 23mm GSh-23L guns;
- incendiary tanks.
The helicopter is provided with a 7.62mm flexibly
mounted machine gun.
Armoring of the crew cabin and vital powerplant acces-
sories enhances the helicopter’s combat survivability.
Its flight control and navigation complex ensures stabi-
lization of flight parameters and automatic flight on a
preprogrammed route.
The folding blades of main rotors enable the Ka-29 to
stow in shipboard and airfield hangars.
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366
PART 2 2
RADAR
PICKET HELICOPTERS
GROUP 15 AIRCRAFT AND AIRFRAME
STRUCTURAL COMPONENTS
Class 1520 Aircraft, Rotary Wing
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Ka-31 RADAR PICKET
HELICOPTER
The Ka-31 is designed for early radar detection of aer-
ial targets (aircraft, helicopters), including those flying
at extreme low altitudes, as well as surface ships, their
tracking and automatic data transmission to command
and control posts. The helicopter may be used to time-
ly inform the Navy and the Ground Forces of enemy’s
ships, aircraft and strike helicopters. The Ka-31 is
developed from the Ka-27 and Ka-29 ship-based heli-
copters.
The avionics complex is based on a powerful solid-
state radar with a 6-m span antenna. The heliborne
radio/radar complex serves for detection of targets,
their identification and transmission of information to
shipborne and ground-based command posts.
Operation of the complex jointly with the integrated
flight control and navigation system makes it possible
to perform automated preprogrammed-route flights in
any weather and climatic conditions.
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Basic Characteristics
Crew 2
Takeoff weight, kg 12,500
Flight speed, km/h:
maximum 220
patrolling 100
Maximum patrolling altitude, m 3,500
Patrolling duration, h 2.5
Scanned area, deg 360
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367
PART 2 2
AIRBORNE ENGINES
GROUP 15 AIRCRAFT AND AIRFRAME
STRUCTURAL COMPONENTS
15 ! !
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AL-31F AIRBORNE
AFTERBURNING BYPASS
TURBOJET ENGINE
The AL-31F is designed
to power the Su-27
aircraft and its modifi-
cations (Su-27SK,
Su-30MK, Su-32MF).
It is a two-shaft bypass
turbojet engine with
main/bypass exhaust
mixing, with a common
afterburner and a fully-
variable supersonic
exhaust nozzle.
The AL-31F distinguish-
ing features are: modu-
lar design, high com-
pressor gas-dynamic
stability, low specific fuel consumption, as well as high
monitoring capability, maintainability and reliability. The
AL-31F is provided with electronic (main) and hydraulic
(backup) engine control systems.
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ULTGK SGMMG EPRVGNDJK, QV 1530
Basic Characteristics
Maximum afterburning thrust (H = 0, V = 0, ISA), kgf 12,500
Specific fuel consumption at low-consumption engine rating, kg/kgf
.
h0.68
Bypass ratio 0.571
Overall dimensions, mm:
length from front flange to nozzle end 4,950
maximum diameter 1,240
Engine dry weight, kg 1,530
$"+"# ! .$""
AIRBORNE ENGINES
368
PART 2 2
AIRBORNE ENGINES
GROUP 15 AIRCRAFT AND AIRFRAME
STRUCTURAL COMPONENTS
15 ! !
" #$ ! " %##$
RD-33 AFTERBURNING
TURBOFAN ENGINE
The RD-33 engine is
intended to power the
MiG-29 fighter and its
modifications.
The RD-33 is a double-flow
two-shaft turbofan engine
with flow mixing in a com-
mon afterburner. The
engine is equipped with a
fully-variable supersonic
exhaust nozzle.
Structurally, the engine
comprises a four-stage
low-pressure axial flow
compressor, a nine-stage
high-pressure axial flow
compressor, a short annu-
lar combustion chamber, single-stage low- and high-
pressure turbines, an afterburner bypass air duct, and
an adjustable exhaust nozzle. The engine is provided
with an electronic/hydromechanical control and moni-
toring system.
The RD-33 is designed around a modular configuration.
Owing to its high gasdynamic stability, the engine sets
no limits on aircraft piloting and features a high rate of
thrust buildup versus flight speed.
The following modifications were developed from the
RD-33 engine: RD-33N to modernize foreign second-
and third-generation single-engine fighters; RD-93 to
power the latest FC-1 Chinese fighter.
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VFPLQVFISE[\ DQFVCMB 1040
TFLLF, PU 1055
Basic Characteristics
Full reheat power setting (H = 0, V = 0, ISA), kgf 8,300
Maximum nonreheat power setting (H = 0, V = 0, ISA), kgf 5,040
Specific fuel consumpton, kg/kgf
.
h0.77
Bypass ratio 0.46
Maximum turbine inlet temperature, °K 1,680
Overall dimensions, mm:
length 4,230
maximum diameter 1,040
Weight, kg 1,055
369
PART 2 2
AIRBORNE ENGINES
GROUP 15 AIRCRAFT AND AIRFRAME
STRUCTURAL COMPONENTS
15 ! !
" #$ ! " %##$
$"&"# !'
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<(#!. !%&+ 4000
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Basic Characteristics
Maximum thrust, kgf 1,700
Specific fuel consumption, kg/kgf
.
h0.7
Bypass ratio 0.78
Service life, h:
total 6,000
hot portion 4,000
Dry weight, kg 297.5
#-./0.12 345467258-7868
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6("(/ ](%;(/ ;+/ ( = 0, V = 0, 0?) 9000
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0a*%+/"8# &/6&$ < () 6 &$,+(., °c 1720
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"+ 4230
/*%+/"8-. +/& 1040
0%%, *< 1055
Basic Characteristics
Full reheat power setting (H = 0, V = 0, ISA), kgf 9,000
Maximum nonreheat power setting
(H = 0, V = 0, ISA), kgf 5,600
Specific fuel consumpton, kg/kgf
.
h0.78
Bypass ratio 0.437
Maximum turbine inlet temperature, °K 1,720
Overall dimensions, mm
length 4,230
maximum diameter 1,040
Weight, kg 1,055
RD-1700
AIRBORNE TURBOJET
ENGINE
The RD-1700 turbojet
engine is intended to
power the MiG-AT trainer
aircraft. The engine is
designed around a two-
shaft configuration and
has a two-stage fan, a
four-stage compressor, a
two-stage turbine with
cooled blades, and a
fixed-exit nozzle.
RD-133
AFTERBURNING
TURBOFAN
TVC ENGINE
The RD-133 afterburning turbofan thrust-vector control (TVC)
engine is designed to power the MiG-29 aircraft modifications
(MiG-29K, MiG-29SMT, MiG-29UBT and others).
The engine is devel-
oped from the RD-33
and RD-33K afterburn-
ing turbofan engines.
It differs structurally
from the RD-33 by the
all-aspect adjustable
nozzle with thrust vec-
tor control and a new
electronic/hydrome-
chanical control and
monitoring system.
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370
PART 2 2
AIRORNE ENGINES
GROUP 15 AIRCRAFT AND AIRFRAME
STRUCTURAL COMPONENTS
15 ! !
" #$ ! " %##$
TV7-117S AIRBORNE
TURBOPROP ENGINE
The TV7-117S turboprop engine is intended to
power Il-114-type airplanes. The TV7-117S is
a modular turboprop engine with a variable-
stator axial/centrifugal compressor and a free
turbine. The engine is equipped with an elec-
tronic engine control system provided with a
hydromechanical backup subsystem.
#*+,-+./ 012134/25*4535
89:;9<=> ;? @ABC=;9D ECFGDC (H=0, V=0, MCA), O= (B.<.) 1840 (2500)
STCB>;UV E?<W9T =9XBG@? ;? OECV<CE<O9D ECFGDC
(=6 OD, V=500 OD/Z, 8[), \/(O=
.
Z) 245
8?<<? (<]W?^), O\ 520
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_ECT;?A;?ZC; TB^ ]<=?;9@OG ;? <?D9BC-
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@9V T@G\?=CB> D9T]B>;9V O9;<=E]OaGG <
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XEC<<9E9D G <@9`9T;9V =]E`G;9V. DCC=
bBCO=E9;;]c <G<=CD] ]XE?@BC;G^ < EC-
ACE@;9V \GTE9DCW?;GZC<O9V Z?<=>c.
Basic Characteristics
Takeoff power (H = 0, V = 0, ISA), kW (hp) 1,840 (2,500)
Specific fuel consumption at cruise rating
(H = 6 km, V = 500 km/h, ISA), g/kW
.
h 245
Dry weight, kg 520
TV3-117 AIRBORNE
TURBOSHAFT ENGINE
The TV3-117 turboshaft engine is
designed to power Mi-8MT, Mi-14,
Mi-24, Mi-28, Ka-27, Ka-28, Ka-29,
Ka-31, Ka-32, Ka-50, Ka-52 helicopters.
Structurally, the engine consists of a
variable stator 12-stage axial flow com-
pressor with guide vanes of the first four stages, a direct-flow
annular combustion chamber, a two-stage axial flow compressor
turbine, a two-stage axial flow free turbine, an exhaust duct with
flow deflection through 60°, a new electronic control and monitor-
ing system. A dust-proof device may be installed at the compres-
sor inlet.
The TV3-117 is one of the world’s best engines in its class in
terms of efficiency achieved due to high performance of its basic
components. The engine features a long service life and high
reliability. It is simple in operation and features high repairability.
Over 15 modifications were developed from the TV3-117. The
TV3-117VM/VMA (Series No. 02) versions have been certified in
Russia, CIS countries, Canada, China and India. The latest
TV3-117VMA-SB3 (VK-2500) modification boasts upgraded per-
formance characteristics.
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=9BC=U 8G-88, 8G-14, 8G-24,
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n9<<GG, <=E?;?W [, k?;?TC, kG=?C G ;TGG. 9@CVl?^ D9-
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#*+,-+./ 012134/25*4535
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[=CXC;> X9@UlC;G^ T?@BC;G^
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8?O<GD?B>;?^ =CDXCE?=]E? \?A9@
XCECT =]E`G;9V, °k 1263 1293
89:;9<=> ( = 0, V = 0, t
H
= +30 °C), B. <.:
;? ZECA@UZ?V;9D ECFGDC 2400 2700
;? @ABC=;9D ECFGDC 2200 2400
;? OECV<CE<O9D ECFGDC 1500 1750
STCB>;UV E?<W9T =9XBG@?, \/B.<. Z:
;? @ABC=;9D ECFGDC 210
+10
210
;? OECV<CE<O9D ECFGDC 250
+10
230
?`?EG=;UC E?ADCEU, DD:
TBG;? 2055 2055
lGEG;? 660 660
@U<9=? 728 728
8?<<?, O\ 293 300
Basic Characteristics
TV3-117VMA TV3-117VMA-SB3
(Series No. 02)
Compressor air pressure ratio 9.4 9.9
Maximum turbine
inlet temperature,
o
K 1,263 1,293
Power (H = 0, V = 0, t
H
= +30
o
C), hp:
at emergency rating 2,400 2,700
at takeoff rating 2,200 2,400
at cruise rating 1,500 1,750
Specific fuel consumption, g/hp
.
h:
at takeoff rating 210
+10
210
at cruise rating 250
+10
230
Overall dimensions, mm:
length 2,055 2,055
width 660 660
height 728 728
Weight, kg 293 300
GROUP 58 COMMUNICATIONS,
DETECTION AND COHERENT
RADAR EQUIPMENT
58 !"#, $%&",
'$(()* +$'$)$$
$%$+$!
371
PART 2 - . 2
AIRBORNE
RADARS
ZHUK FAMILY AIRBORNE RADARS
The Zhuk family airborne radars are designed for
equipping the MiG-23, Su-27, F-8-IIM and MiG-29 air-
craft.
The Zhuk family multifunction radars ensure:
- in the air-to-air operating mode: detection of colli-
sion/pursuit critical aerial targets; single collision/pur-
suit target tracking; multitarget tracking with/without
airspace scanning; close maneuvering combat by ver-
tical and windshield scanning, targeting by the use of
the helmet-mounted target designator, and large zone
scanning; detection and engagement of hovering heli-
copters; estimation of massive target complex
strength;
- in the air-to-surface operating mode: ground map-
ping by the use of a scanning beam, Doppler beam
narrowing, synthesized focusing aperture, map scale
coarsening, and map freezing; surface ranging; sea
surface surveillance; detection and tracking of moving
ground/surface targets; ground proximity warning; car-
rier speed measurement.
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bK EfHXODO ±90 ±70 ±90 ±85 ±85
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jELLE, Zg 220 300 260 240 180
KLHDQIH jHk-23 O-27 O-27 F-8-IIj jHk-29
Basic Characteristics
Radar type Zhuk Zhuk-F Zhuk-27 Zhuk-8-II Zhuk-M
Target detection range
(ERA = 5 m
2
), km 90 130-200 130 90 120
Number of targets:
detected 10-12 24 10 10 10
tracked 2-4 6-8 2-4 2 2-4
Scanned area, deg:
azimuth ±90 ±70 ±90 ±85 ±85
elevation +55 - -40 +70 +55 - -40 +55 - -40 +55 - -40
Weight, kg 220 300 260 240 180
Carriers MiG-23 Su-27 Su-27 F-8-IIM MiG-29
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AIRBORNE RADARS
«oOZ-j»
Zhuk-M airborne radar