Каталог - Оружие России 2000 c82-795

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392

PART 2  2

UNMANNED AIRCRAFT

SYSTEMS

 

 

Basic Characteristics

Weight, kg:

takeoff 280

normal/maximum payload 50/80

Maximum/cruising flight speed, km/h 175/145

Hovering/service ceiling, m 2,900/5,000

Flight range

with normal payload, km 530

Maximum flight duration, h 4

Diameter, m:

fuselage 1.25

main rotor 5.3

Airframe height, m 2.3

Engine type, power, hp Hirth 270GR05, 65

MBVK-137 MULTIPURPOSE UNMANNED

HELICOPTER COMPLEX

The MBVK-137 is intended for air reconnaissance, bor-

der guard, police and ecology patrolling, urgent air

delivery of special-purpose cargoes in emergency situ-

ations, as well as for transmitting information data from

dangerous zones.

Provision is made for three versions of the MBVK-137:

automobile-based, airborne (carried by the Ka-32 heli-

copter), and ship-based.

The complex comprises:

- Ka-137 multipurpose unmanned helicopter;

- ground control station provided with an operator’s

workstation equipped with the helicopter control levers

and console, data display system, TV and radio-control

equipment.

The Ka-137 is a coaxial-rotor helicopter provided with

a spherical tailless fuselage, four-leg leaf-spring land-

ing gear, and a piston engine.

By customer request, TV and thermal imaging cam-

eras, radar, signal repeater and

other equipment with a total

weight of up to 80 kg can be

installed in a special equipment

compartment of the helicopter.

Interacting with a radio altime-

ter, a satellite navigation system

and other systems, the heli-

copter’s automatic control sys-

tem and onboard radio equip-

ment, functionally interfaced

with radio equipment of the

ground control station, ensure

Ka-137’s takeoff, hovering at a

required altitude, en-route flight

and landing in a given area. The

Ka-137 can be controlled by

introducing a flight program or

directly from the ground control

station by the operator. A com-

bined control mode can be

used.

'()*+),- ./0/12-03(2313

QRRQ, ST:

UVWXYZQ[ 280

\]WXVZ]^ ZQT_`VSa Z]_bQWcZQ[/bQSRabQWcZQ[ 50/80

S]_]RYc \]WXYQ bQSRabQWcZQ[/S_X^RX_RSQ[, Sb/d 175/145

]Y]W]S RYQYadXRSa^/eaZQbadXRSa^, b 2900/5000

fQWcZ]RYc \]WXYQ

R Z]_bQWcZ]^ \]WXVZ]^ ZQT_`VS]^, Sb 530

QSRabQWcZQ[ \_]e]WgaYXWcZ]RYc \]WXYQ, d 4

faQbXY_, b:

hiVXW[gQ 1,25

ZXR`jXT] UaZYQ 5,3

kR]YQ \WQZX_Q, b 2,3

Q_SQ eUaTQYXW[, b]jZ]RYc, W. R. «Hirth 270GR05», 65

45'6'7898:'; <8=>9'5?;

:8@'985?; A'4=98A 4<:A-137

_XeZQVZQdXZ eW[ UXeXZa[ U]XZZ]^ _QVUXeSa, \]T_QZad-

Z]T], \]WanX^RS]T], oS]W]TadXRS]T] \QY_`Wa_]UQZa[ a

oSRY_XZZ]^ e]RYQUSa T_`V]U R\XnaQWcZ]T] ZQVZQdXZa[ U

d_XVUkdQ^Zkp RaY`Qna[p, Q YQSgX \X_XeQda aZh]_bQnaa

aV ]\QRZkp V]Z.

qSR\W`QYQna[ -137 \_Xe`RbQY_aUQXYR[ U Y_Xp UQ_a-

QZYQp: QUY]b]raWcZ]b, Qo_]b]raWcZ]b (rQVa_`XYR[ ZQ

UX_Y]WXYX Q-32) a S]_QrXWcZ]b.

 R]RYQU  Up]e[Y:

- bZ]T]nXWXU]^ rXR\aW]YZk^ UX_Y]WXY Q-137;

- ZQVXbZk^ \`ZSY `\_QUWXZa[ (s) R _Qr]dab bXRY]b

]\X_QY]_Q, ]r]_`e]UQZZkb \`WcY]b a _kdQTQba `\_QUWX-

Za[ rXR\aW]YZkb UX_Y]WXY]b, RaRYXb]^ ]Y]r_QgXZa[ aZ-

h]_bQnaa, YXWXUaVa]ZZ]^ Q\\Q_QY`_]^ a _Qea]Q\\Q_QY`-

_]^ `\_QUWXZa[.

Q-137 - UaZY]S_kWQ[ bQtaZQ R]]RZ]^ RpXbk R hiVXW[-

gXb RhX_adXRS]^ h]_bk rXV pU]RY]U]T] ]\X_XZa[, R dX-

Yk_XpRY]XdZkb tQRRa _XRR]_Z]T] Ya\Q a \]_tZXUkb

eUaTQYXWXb.

 ]YRXSX nXWXU]T] ]r]_`e]UQZa[

\] gXWQZai VQSQVdaSQ b]T`Y `R-

YQZQUWaUQYcR[ YXWXUaVa]ZZkX a

YX\W]UaVa]ZZkX SQbX_k, _Qea]-

W]SQY]_, Q\\Q_QY`_Q _XY_QZRW[-

naa RaTZQW]U a e_`T]X

]r]_`e]UQZaX ]rjX^ bQRR]^ e]

80 ST.

aRYXbQ QUY]bQYadXRS]T] `\_QU-

WXZa[ (s) Q-137 U] UVQab]-

eX^RYUaa R _Qea]UkR]Y]bX_]b,

RaRYXb]^ R\`YZaS]U]^ ZQUaTQnaa

a e_`Taba RaRYXbQba a R]UbXRY-

Z] R r]_Y]U]^ _Qea]Q\\Q_QY`-

_]^, h`ZSna]ZQWcZ] R]\_[gXZ-

Z]^ R _Qea]Q\\Q_QY`_]^ s,

]rXR\XdaUQiY UVWXY Q-137, VQ-

UaRQZaX ZQ Y_Xr`Xb]^ UkR]YX,

\]WXY \] bQ_t_`Y` a \]RQeS` U

VQeQZZ]b _Q^]ZX. s\_QUWXZaX

Q-137 b]gXY ]R`jXRYUW[YcR[

\`YXb VQeQZa[ \_]T_Qbbk \]WXYQ

aWa ZX\]R_XeRYUXZZ] R s ]\X-

_QY]_]b. ]Vb]gXZ S]braZa_]-

UQZZk^ R\]R]r `\_QUWXZa[.

GROUP 15 AIRCRAFT AND AIRFRAME

STRUCTURAL COMPONENTS

Class 1550 Drones

6@E== 15 98895?8 ==@?

> ':5?8 > A'@=E':

WQRR 1550 XR\aW]YZkX S]b\WXSRk a WXYQYXWcZkX Q\\Q_QYk

393

PART 2  2

AIR-TO-GROUND

AND AIR-TO-SHIP MISSILES

  « !" - #$»,

« !" - '(»

GROUP 14

GUIDED MISSILES

Class 1410 Guided Missiles

 14    !

! ( !#)

4566 1410 !78594:;<=; 85>;?= @ 85>;?=-AB6@?;4@

Kh-25ML SHORT-RANGE

AIR-TO-SURFACE MISSILE

The missile is designed to engage pinpoint mobile and

stationary ground (waterborne) targets such as radars

and SAM launchers, open and slightly sheltered air-

craft, light bridges and ferries, small displacement ves-

sels, railway trains, and others.

The missile is provided with a semiactive laser homing

system and uses proportinal navigation guidance. The

control parameter is the angular rate of the target sight

line. The follow-up laser target seeker has a field of

view of 2 degrees and a maximum target bearing angle

of 30 degrees.

A container is used to transport and store the missile.

Carriers: Su-17M3 (M4), Su-24M, Su-39,

MiG-27K(M,D), MiG-29SM.

-. / -#/!/  «- 123 -

 -3 » !# 5 2#  3-25!#

Z8;[A5\A5];A5 [4: 7B85^;A@: <54B85\<;8A=_ 7B[-

9@^A=_ @ A;7B[9@^A=_ A5\;<A=_ (A5[9B[A=_) `;4;a:

 @ Z! >B<74;>6B9 !, 65<B4;?B9 A5 B?>8=?=_

6?B:A>5_ @ 9 4;b>@_ c>8=?@:_, 4;b>@_ <B6?B9 @ 7;8;-

7859, <54B?BAA5^A=_ 6c[B9, ^;4;\AB[B8B^A=_ de;-

4BAB9 @ [8cb@_.

f<;;? 7B4c5>?@9Acg 45\;8Acg 6@6?;<c 65<BA59;[;-

A@:. h59;[;A@; 78B9B[@?6: 7B <;?B[c 78B7B8`@BA54i-

ABbB 6j4@^;A@:. Z585<;?8B< c78594;A@: :94:;?6: cb-

4B95: 6>B8B6?i 4@A@@ 9@\@8B95A@: `;4@. !bB4 7B4:

\8;A@: 64;[:k;bB 45\;8ABbB >BB8[@A5?B85 `;4@ - 2

<5>6@<54iA=a cbB4 7;4;Ab5 `;4@ - 30

4: ?85A67B8?@8B9>@ @ _85A;A@: 85>;?= @67B4i\c;?6:

>BA?;aA;8.

hB6@?;4@: c-17#3(#4), c-24#, c-39,

#@l-27(#, ), #@l-29#.

67897:; <=>=?@;>A6@A?A

#5>6@<54iA5: [54iAB6?i 7c6>5, >< 10

#5665, >b:

>BA?;aA;85 6 85>;?Ba 540

6?58?B95: 295

jB;9Ba ]56?@ 86

'B;95: ]56?i pcb56A5:

@6?;<5 A59;[;A@: 7B4c5>?@9A5: 45\;8A5:

B]AB6?i A59;[;A@: (), < 4 - 5

8;[A:: 6>B8B6?i 7B4;?5, </6 400 - 450

@7 ?85;>?B8@@ A5>4BAA5:, 6 «bB8>Ba»

@575\BA, ><:

[54iAB6?;a 7c6>5 2,5 - 10

9=6B? 7c6>5 0,05 - 5

l5j58@?A=; 85\<;8= 85>;?=

([4@A5 _ [@5<;?8 >B87c65 _ 85\<5_ B7;8;A@:), < 3,57 _ 0,275 _ 0,787

Basic Characteristics

Max launch range, km 10

Weight of container with missile, kg 540

Launch weight, kg 295

Warhead weight, kg 86

Warhead type HE

Guidance system semiactive laser

Guidance accuracy (CEP), m 4 - 5

Average flight speed, m/s 400 - 450

Trajectory type slanted with zoom

Limits, km:

launch range 2.5 - 10

launch altitude 0.05 - 5

Overall dimensions of missile

(length x body diameter

x wing span), m 3.57 x 0.275 x 0.787

-#/!  - J

GUIDED AIRCRAFT ARMAMENT

394

PART 2  2

AIR-TO-GROUND

AND AIR-TO-SHIP MISSILES

  « !"# - $%»,

« !"# - ()»

GROUP 14

GUIDED MISSILES

Class 1410 Guided Missiles

 14    !

! ( !#)

4566 1410 "78594:;<=; 85>;?= @ 85>;?=-AB6@?;4@

%&'(&)* +,-,./*-0%/0.0

$5>6@<54CA5: D54CAB6?C 7E6>5, >< 10

$5665, >F:

6?58?B95: 400

HB;9BI J56?@ 155

(B;95: J56?C 78BA@>5LM5:

@6?;<5 A59;D;A@: 7B4E5>?@9A5: 45N;8A5:

BJAB6?C A59;D;A@: (), < 4 - 8

R5H58@?A=; 85N<;8= 85>;?=

(D4@A5 S D@5<;?8 7B HB;9BI J56?@ S 85N<5S B7;8;A@:), < 4,1 S 0,34 S 1,17

Basic Characteristics

Max launch range, km 10

Launch weight, kg 400

Warhead weight, kg 155

Warhead type penetrating

Guidance system semiactive laser

Guidance accuracy (CEP), m 4 - 8

Overall dimensions

(length x warhead diameter

x fin span), m 4.1 x 0.34 x 1.17

S-25LD SHORT-RANGE

GENERAL-PURPOSE MISSILE

The missile is designed to engage hard overland and

waterborne targets in visual meteorological conditions.

The missile features the canard configuration. It con-

sists of the S-250FM rocket and control unit, which

comprises the semiactive laser homing head, electron-

ics unit, roll sensor, and the system of electric power

and air supply, and uses proportinal navigation guid-

ance. The control parameter is the angular rate of the

target sight line, which is measured by the homing

head. The control unit stabilizes the missile in pitch and

yaw. Carriers: Su-24M, Su-25, Su-17M3(M4).

?@ A ?#A!A  !# B

C#  DE FA -25#C

j8;DA5NA5J;A5 D4: 7B85k;A@: 78BJA=S A5N;<A=S, 5 ?5>k;

A5D9BDA=S l;4;I 9 78B6?=S <;?;BE64B9@:S.

=7B4A;A5 7B 5m8BD@A5<@J;6>BI 6S;<; «E?>5».

-25! 6B6?B@? @N D9ES <BDE4;I: n -250o$ @ H4B>5

E78594;A@:.  H4B> E78594;A@: 9SBD:?: 7B4E5>?@9A5: 45N;8-

A5: FB4B9>5 65<BA59;D;A@: (Rn), H4B> m4;>?8BA@>@, D5?J@>

EF45 >8;A5 @ 6@6?;<5 m4;>?8B7A;9<B7@?5A@:. "78594;A@;

85>;?BI B6EM;6?94:;?6: 7B <;?BDE 78B7B8l@BA54CABFB

6H4@k;A@:. j585<;?8B< E78594;A@: :94:;?6: EF4B95: 6>B-

8B6?C 4@A@@ 9@N@8B95A@: l;4@, >B?B85: @N<;8:;?6: Rn.

(4B> E78594;A@: 6?5H@4@N@8E;? 85>;?E 7B ?5AF5kE @ >E86E.

nB6@?;4@: E-24$, E-25, E-17$3($4).

395

PART 2  2

AIR-TO-GROUND

AND AIR-TO-SHIP MISSILES

  « !"# - $%»,

« !"# - ()»

GROUP 14

GUIDED MISSILES

Class 1410 Guided Missiles

 14    !

! ( !#)

5677 1410 "896:5;<=>< 96?<@> A 96?<@>-BC7A@<5A

Kh-29L SHORT-RANGE

GENERAL PURPOSE MISSILE

The missile is designed to engage ground targets such

as hard aircraft shelters, concrete runways, permanent

railroad and highway bridges, industrial facilities and

depots in visual meteorological conditions.

The missile has a semiactive laser homing system and

uses proportional navigation guidance. The control

parameter is the angular rate of the target sight line.

The follow-up laser seeker is similar to that of the

Kh-25ML missile. The system of control in the vertical

plane can operate in two modes. When the missile is

launched from the carrier fitted out with the Prozhektor

type illuminating radar, the two-plane control system

operates in the homing mode. When launched from the

carrier outfitted with Klyon and Kaira illuminating radars

(the illuminating beam can be diverted from the aircraft

axis), the system of missile control in the vertical plane

permits guidance in three stages: the first stage is log-

arithm trajectory motion (independent guidance), at the

second stage the missile is turned toward its target,

while the third stage represents missile homing. This

provides for an increase in the angle of missile

approach to the target during low-altitude launches.

The control system

also stabilizes the

missile in yaw, roll

and pitch.

A container is used

to transport and

store the Kh-29L

missile.

Carriers:

Su-17M2 (M3, M4),

Su-24M, Su-39,

MiG-27K(M,D),

MiG-29SM,

MiG-23-98, Su-32,

Su-35.

+, - +#-!-  !# .

/#  01 2- 3-29#

_9<`B6aB6b<B6 `5; 8C96c<BA; B6a<=B>d e<5<f @A86 89Cb-

B>d g?9>@Af 76=C5<@C:, h<@CBA9C:6BB>d __, 7@6eACB69-

B>d c<5<aBC`C9CcB>d A iC77<fB>d =C7@C:, 89C=>i5<B-

B>d 7CC9gc<BAf A 7?56`C: : 89C7@>d =<@<Cg75C:A;d.

j=<<@ 8C5g6?@A:Bgk 56a<9Bgk 7A7@<=g 76=CB6:<`<BA;.

l6:<`<BA< 89C:C`A@7; 8C =<@C`g 89C8C9eACB65mBCnC

7h5Ac<BA;. _696=<@9C= g896:5<BA; ;:5;<@7; gn5C:6;

7?C9C7@m 5ABAA :AaA9C:6BA; e<5A. 5<`;oAf 56a<9B>f

?CC9`AB6@C9 6B65CnAb<B ?CC9`AB6@C9g #-25$. A7@<=6

g896:5<BA; : :<9@A?65mBCf 85C7?C7@A =Cc<@ 96hC@6@m :

`:gd 9<cA=6d. _9A 8g7?6d 96?<@> 7 BC7A@<5<f, ChC9g`C-

:6BB>d 7@6BeA<f 8C`7:<@6 @A86 «_9Cc<?@C9», 7A7@<=6

g896:5<BA; : `:gd 85C7?C7@;d 96hC@6<@ : 9<cA=< 76=C-

B6:<`<BA;. _9A 8g7?6d 7 BC7A@<5<f, B6 ?C@C9>d g7@6BC:-

5<B> 7@6BeAA 8C`7:<@6 @A86 «5<B» A «6f96» (5gb 8C`-

7:<@6 8C`:Ac<B C@BC7A@<5mBC C7A 76=C5<@6), 7A7@<=6

g896:5<BA; 96?<@> : :<9@A?65mBCf 85C7?C7@A 8Ca:C5;<@

89C:C`A@m B6:<`<BA< : @9A p@686: B6 1-= p@68< - `:Ac<-

BA< 8C 5Cn69Aq=Ab<7?Cf @96<?@C9AA (6:@CBC=BC< B6:<-

`<BA<), B6 2-= - 96a:C9C@ B6 e<5m, B6 3-= - 76=CB6:<`<-

BA<. r@C 8Ca:C5;<@ g:<5AbA@m gnC5 8C`dC`6 96?<@> ? e<-

5A 89A 8g7?6d 7 =65>d :>7C@. (5C? g896:5<BA; @6?c<

7@6hA5AaA9g<@ 96-

?<@g 8C ?g97g, ?9<-

Bg A @6Bn6cg.

!5; @96B78C9@A-

9C:?A A d96B<BA;

96?<@ #-29 A7-

8C5mag<@7; ?CB@<f-

B<9.

lC7A@<5A:

g-17$2 ($3, $4),

g-24$, g-39,

$As-27 ($, !),

$As-29$,

$As-23-98, g-32,

g-35.

4567589 :;<;=>9<?4>?=?

$6?7A=65mB6; `65mBC7@m 8g7?6, ?= 10

$6776, ?n:

?CB@<fB<96 7 96?<@Cf 1000

7@69@C:6; 650

hC<:Cf b67@A 317

(C<:6; b67@m 89CBA?6ko6;

A7@<=6 B6:<`<BA; 8C5g6?@A:B6; 56a<9B6;

CbBC7@m B6:<`<BA; (), = 6

9<`B;; 7?C9C7@m 8C5<@6, =/7 250 - 350

96<?@C9A; B6?5CBB6;, 7 «nC9?Cf»

s6h69A@B>< 96a=<9> 96?<@>

(`5AB6 d `A6=<@9 ?C98g76 d 96a=6d ?9>56), = 3,875 d 0,38 d 1,1

Basic Characteristics

Max launch range, km 10

Weight of container with missile, kg 1,000

Launch weight, kg 650

Warhead weight, kg 317

Warhead type penetrating

Guidance system semiactive laser

Guidance accuracy (CEP), m 6

Average flight speed, m/s 250 - 350

Trajectory type slanted with zoom

Overall dimensions

(length x body diameter

x wing span), m 3.875 x 0.38 x 1.1

396

PART 2  2

AIR-TO-GROUND

AND AIR-TO-SHIP MISSILES

  « !"# - $%»,

« !"# - ()»

GROUP 14

GUIDED MISSILES

Class 1410 Guided Missiles

 14    !

! ( !#)

5677 1410 "896:5;<=>< 96?<@> A 96?<@>-BC7A@<5A

%&'(&)* +,-,./*-0%/0.0

$6?7A=65DB6; E65DBC7@D 8F7?6, ?= 10

$6776, ?G:

?CB@<IB<96 7 96?<@CI 1030

7@69@C:6; 680

KC<:CI L67@A 317

(C<:6; L67@D 89CBA?6NO6;

A7@<=6 B6:<E<BA; 8677A:B6; @<5<:APACBB6;

CLBC7@D B6:<E<BA; (), = 2 - 3

9<EB;; 7?C9C7@D 8C5<@6, =/7 250 - 350

A8 @96<?@C9AA B6?5CBB6;, 7 «GC9?CI»

V6K69A@B>< 96P=<9> 96?<@>

(E5AB6 W EA6=<@9 ?C98F76 W 96P=6W C8<9<BA;), = 3,877 W 0,38 W 1,1

V6K69A@B>< 96P=<9> ?CB@<IB<96

(E5AB6 W :>7C@6 W XA9AB6), = 4,35 W 0,9 W 0,86

Basic Characteristics

Max launch range, km 10

Weight of container with missile, kg 1,030

Launch weight, kg 680

Warhead weight, kg 317

Warhead type penetrating

Guidance system passive TV

Guidance accuracy (CEP), m 2 - 3

Average flight speed, m/s 250 - 350

Trajectory type slanted with zoom

Overall dimensions of missile

(length x body diameter

x fin span), m 3.877 x 0.38 x 1.1

Overall dimensions of container

(length x width x height), m 4.35 x 0.9 x 0.86

Kh-29T SHORT-RANGE

AIR-TO-SURFACE MISSILE

The missile is designed to engage visually discernible

ground and waterborne targets such as reinforced con-

crete shelters, permanent railroad and highway

bridges, industrial facilities, depots, concrete runways,

ships and landing craft.

The Kh-29T missile is provided with a passive TV hom-

ing system, whose field of view is 12 x 16 deg in the

search mode and 2.1 x 2.8 deg in the automatic track-

ing mode. The maximum angular rate of the sight line

is 10 deg/s. The system of control in the vertical plane

operates in two modes: self-contained and homing.

Self-contained control is effected at the initial stage of

flight, while homing at the terminal stage by propor-

tional navigation guidance.

A container is used to transport and store the Kh-29T

missile.

Carriers: Su-17M4, Su-24M, Su-39, Su-27M,

MiG-27K(M, D), MiG-29SM, MiG-23-98, Su-30KI,

Su-32, Su-35, MiG-31BM.

AB C A#C!C  «A EFG -

 AG » !# I F#  G-29

p9<EB6PB6L<B6 E5; 8C96q<BA; :AEA=>W B6P<=B>W A B6E-

:CEB>W r<5<I @A86 q<5<PCK<@CBB>W F?9>@AI, 7@6rACB69-

B>W q<5<PBCEC9CqB>W A XC77<IB>W =C7@C:, 89C=>X5<B-

B>W 7CC9Fq<BAI, 7?56EC:, K<@CBA9C:6BB>W pp, ?C96K-

5<I A E<76B@BC-:>76ECLB>W 79<E7@:.

#-29 A=<<@ 8677A:BFN @<5<:APACBBFN 7A7@<=F 76=CB6-

:<E<BA;, FGC5 8C5; P9<BA; ?C@C9CI : 9<qA=< 8CA7?6 96-

:<B 12W16

A : 9<qA=< 6:@C7C89C:CqE<BA; r<5A - 2,1W2,8

$6?7A=65DB6; FG5C:6; 7?C9C7@D 5ABAA :APA9C:6BA; -

10 G96E./7. A7@<=6 F896:5<BA; : :<9@A?65DBCI 85C7?C7-

@A 96KC@6<@ : E:FW 9<qA=6W: 6:@CBC=BC= A 76=CB6:<E<-

BA;. :@CBC=BC< F896:5<BA< C7FO<7@:5;<@7; B6

B6L65DBC= s@68< 8C5<@6, 76=CB6:<E<BA< - B6 8C75<EB<=

8C =<@CEF 89C8C9rACB65DBCGC 7K5Aq<BA;.

!5; @96B78C9@A9C:?A A W96B<BA; 96?<@> #-29 A78C5DPF-

<@7; ?CB@<IB<9.

tC7A@<5A: F-17$4, F-24$, F-39, F-27$,

$AV-27($,!), $AV-29$, $AV-23-98, F-30u, F-32,

F-35, $AV-31($.

397

PART 2  2

AIR-TO-GROUND

AND AIR-TO-SHIP MISSILES

  « !"# - $%»,

« !"# - ()»

GROUP 14

GUIDED MISSILES

Class 1410 Guided Missiles

 14    !

! ( !#)

5677 1410 "896:5;<=>< 96?<@> A 96?<@>-BC7A@<5A

Kh-31A SUPERSONIC

TACTICAL ANTISHIP

MISSILE

The missile is designed to engage surface combatants

and transport vessels.

It features a normal aerodynamic configuration with

cruciform wings and ruddervators. Four round super-

sonic air intakes are located on the sides of the body

in the plane of the airfoils.

The Kh-31A can be used against targets whose coordi-

nates are known in advance and those detected by the

aircraft radar in flight (main method), if the carrier is

within the zone of potential missile launches.

The Kh-31A can be launched from a carrier aircraft at

a target located within relative bearings of ±8 degrees.

After target detection, missile launch preparation and

input of target designation data and carrier flight para-

meters into the missile control unit the missile is fired

in response to the launch signal.

After liftoff, the missile flies independently in compli-

ance with the program to an area of target search by

the active homing head. The estimated point of missile

arrival to the target lockon area is located at a range of

7.5 km and an altitude of 100 m. After target lockon for

automatic tracking, the

missile zooms to exclude

its splashdown during

approach to the target at

extremely small angles.

The target is defeated by

explosion of the missile

warhead after penetrat-

ing the ship in the event

of a direct hit or by high-

explosive and fragmenta-

tion effect in case of a

near miss.

A sealed container is

used to transport and

store the missile.

Carriers: Su-32, Su-35,

MiG-29SM, MiG-21-93,

MiG-31BM, Su-24M.

,- . ,/0, ,.

 ,  1#. 

  0. /-31

`9<aB6bB6c<B6 a5; 8C96d<BA; eC<:>f B6a:CaB>f ?C96e-

5<g, 6 @6?d< @96B78C9@B>f 7haC:.

>8C5B<B6 8C BC9=65iBCg 6j9CaAB6=Ac<7?Cg 7f<=< 7

#-Ce96bB>= 9678C5Cd<BA<= ?9>56 A 9h5<g. k6 ?C98h7< :

85C7?C7@A B<7hlAf 8C:<9fBC7@<g 9678C5Cd<B> c<@>9<

eC?C:>f ?9hm5>f 7:<9fb:h?C:>f :CbahfCb6eC9BA?6.

#-31 =Cd<@ 89A=<B;@i7; 8C n<5;= 7 b696B<< Ab:<7@B>-

=A ?CC9aAB6@6=A, 6 @6?d< CeB69hd<BB>= 76=C5<@BCg

 : 89Cn<77< 8C5<@6 (C7BC:BCg 78C7Ce) 89A h75C:AA

B6fCda<BA; BC7A@<5; : bCB< :Cb=CdB>f 8h7?C: 96?<@>.

`h7? #-31 7 76=C5<@6-BC7A@<5; :Cb=Cd<B 8C n<5A, 967-

8C5Cd<BBCg : 89<a<56f ?h97C:>f hm5C: ±8°. `C75< CeB6-

9hd<BA;, 8CamC@C:?A ? 8h7?h A ::Ca6 a6BB>f n<5<h?6b6BA;

A 8696=<@9C: 8C5<@6 76=C5<@6-BC7A@<5; : e5C? h896:5<-

BA; 96?<@> 8C 7AmB65h «8h7?» 89CA7fCaA@ << ?6@68h5i@A-

9C:6BA<.

`C75< 7@69@6 96?<@6 7C:<9p6<@ 6:@CBC=B>g 8C5<@ 8C 89C-

m96==< : 96gCB 8CA7?6 n<5A 6?@A:BCg mC5C:?Cg 76=CB6:<-

a<BA;. 67c<@B6; @Cc?6 :>fCa6 << : bCBh b6f:6@6 B6fCaA@7;

B6 9677@C;BAA 7,5 ?= C@ n<5A B6 :>7C@< 100 =. `C75< b6-

f:6@6 n<5A B6 6:@C7C89C:Cda<BA< 96?<@6 7C:<9p6<@ «8Ca-

7?C?», A7?5qc6qlAg :Cb-

=CdBC7@i 89A:CaB<BA; 96-

?<@> 89A 8Ca5<@< ? n<5A 7

=65>=A hm56=A. `9A 89;-

=C= 8C86a6BAA 8Ca9>: eC-

<:Cg c67@A 96?<@> 89CA7-

fCaA@ 8C75< 89CBA?BC:<-

BA; << :Bh@9i ?C96e5;. `9A

89C5<@< 96?<@> n<5i 8C96-

d6<@7; b6 7c<@ C7?C5CcBC-

rhm67BCmC a<g7@:A;.

!5; @96B78C9@A9C:?A A

f96B<BA; 96?<@> 89A=<B;-

<@7; m<9=C?CB@<gB<9.

kC7A@<5A: h-32, h-35,

$As-29$, $As-21-93,

$As-31($, h-24$.

2345367 89:9;<7:=2<=;=

$6?7A=65iB6; a65iBC7@i 8h7?6, ?= 50

$6776, ?m:

7@69@C:6; 610

eC<:Cg c67@A 90

(C<:6; c67@i 89CBA?6ql6;

A7@<=6 B6:<a<BA; 6:@CBC=B6;, 6?@A:B6; 96aAC5C?6nACBB6;

CcBC7@i B6:<a<BA; (), = 5 - 8

A8 a:Am6@<5iBCg h7@6BC:?A `!

9<aB;; 7?C9C7@i 8C5<@6, =/7 600 - 700

96<?@C9A; ?C=eABA9C:6BB6;

s6e69A@B>< 96b=<9> 96?<@>

(a5AB6 f aA6=<@9 f 96b=6f C8<9<BA;), = 4,7 f 0,36 f 1,005

Basic Characteristics

Max launch range, km 50

Launch weight, kg 610

Warhead weight, kg 90

Warhead type penetrating

Guidance system independent, active radar

Guidance accuracy (CEP), m 5 - 8

Propulsion system ramjet

Average flight speed, m/s 600 - 700

Trajectory type combined

Overall dimensions of missile

(length x diameter

x fin span), m 4.7 x 0.36 x 1.005

398

PART 2  2

AIR-TO-GROUND

AND AIR-TO-SHIP MISSILES

  « !"# - $%»,

« !"# - ()»

GROUP 14

GUIDED MISSILES

Class 1410 Guided Missiles

 14    !

! ( !#)

5677 1410 "896:5;<=>< 96?<@> A 96?<@>-BC7A@<5A

%&'(&)* +,-,./*-0%/0.0

$6?7A=65DB6; E65DBC7@D 8F7?6, ?= 300 - 400

$6776, ?G:

7@69@C:6; 5780

KC<:CL M67@A 930

(C<:6; M67@D NFG67BC-?F=F5;@A:B6;

A7@<=6 B6:<E<BA; 6:@CBC=B6;, 6?@A:B6;

A5A 8677A:B6; (96EAC5C?6PACBB6;)

RA75C $ 8C5<@6 3

96<?@C9A; :<9SB;;, BATB;;

$6776 ?CB@<LB<96, ?G 3400

U6K69A@B>< 96V=<9> 96?<@>

(E5AB6 S :>7C@6 S 96V=6S ?9>56), = 11,65 S 1,81 S 3,0

Basic Characteristics

Max launch range, km 300 - 400

Launch weight, kg 5,780

Warhead weight, kg 930

Warhead type HEAT

Guidance system self-contained,

active (or passive) radar

Flight speed, Mach number 3

Trajectory type upper, lower

Container weight, kg 3,400

Overall dimensions of missile

(length x height x wing span), m 11.65 x 1.81 x 3.0

Kh-22M SUPERSONIC AIR-TO-SURFACE

CRUISE MISSILE

The missile is designed to engage radar-contrast

mobile and stationary sea targets and separate ground

targets and also radio emitting facilities.

The combined missile control system consists of a self-

contained control and a homing subsystem. Within the

first 25 s after separation of the missile from the carri-

er the self-contained control system stabilizes the mis-

sile in yaw and roll and smoothly increases its pitch

angle, while the homing head tracks the target. In the

vertical plane, the missile flight is controlled by the self-

contained system which brings the missile to a cruising

altitude, ensures its level flight at this altitude, and

makes the missile go into a dive when the angle from

the missile to the target constitutes 30 deg. During the

dive, the missile switches to active radar homing by

direct guidance.

A container is used to transport the missile.

Carriers: Tu-22M2, Tu-22M3.

?@ A ?BC? ?A #A 

«? CEB -  ?B » B-22!

n9<EB6VB6M<B6 E5; 8C96T<BA; 96EAC5C?6PACBBC-?CB@96-

7@B>S =C97?AS (C@E<5DB>S B6V<=B>S) 8CE:ATB>S A B<8CE-

:ATB>S P<5<L, 6 @6?T< 96EACAV5FM6opAS CKq<?@C:.

C=KABA9C:6BB6; 7A7@<=6 F896:5<BA; 96?<@> 7C7@CA@ AV

8CE7A7@<= 6:@CBC=BCGC F896:5<BA; A 76=CB6:<E<BA;. 

@<M<BA< 8<9:>S 25 7 8C75< C@P<8?A 96?<@> C@ 76=C5<@6-

BC7A@<5; 7A7@<=6 6:@CBC=BCGC F896:5<BA; 7@6KA5AVA9F-

<@ FG5> ?F976 A ?9<B6 A 856:BC F:<5AMA:6<@ << FGC5 @6B-

G6T6, GC5C:?6 76=CB6:<E<BA; C7Fp<7@:5;<@ 75<T<BA< V6

P<5Do.  :<9@A?65DBCL 85C7?C7@A 8C5<@C= 96?<@> F896:-

5;<@ 6:@CBC=B6; 7A7@<=6, ?C@C96; CK<78<MA:6<@ B6KC9

=69r<:CL :>7C@>, GC9AVCB@65DB>L 8C5<@ B6 s@CL :>7C@<

A 8<9<:CE << : 8A?A9C:6BA< 89A FG5< 8<5<BG6 P<5A C@BC-

7A@<5DBC 96?<@>, 96:BC= 30°. u6 FM67@?< 8A?A9C:6BA; 96-

?<@6 8<9<SCEA@ B6 96EAC5C?6PACBBC< 76=CB6:<E<BA< 8C

=<@CEF 89;=CGC B6:<E<BA;.

!5; @96B78C9@A9C:?A 96?<@6 8C=<p6<@7; : ?CB@<LB<9.

uC7A@<5A: F-22$2, F-22$3.

399

PART 2  2

AIR-TO-GROUND

AND AIR-TO-SHIP MISSILES

  « !" - #$»,

« !" - '(»

GROUP 14

GUIDED MISSILES

Class 1410 Guided Missiles

 14    !

! ( !#)

4566 1410 !78594:;<=; 85>;?= @ 85>;?=-AB6@?;4@

%&'(&)* +,-,./*-0%/0.0

#5>6@<54CA5: D54CAB6?C 7E6>5, >< 40

#5665, >F :

6?58?B95:/IB;9BJ K56?@ 310/90

>BA?;JA;85 6 85>;?BJ 530

'B;95: K56?C MEF56A5:

@6?;<5 A59;D;A@: 7566@9A5:, 85D@B4B>5N@BAA5:

BKAB6?C A59;D;A@: (), < 3-5

85;>?B8@: 6 «FB8>BJ»

Q5I58@?A=; 85R<;8= 85>;?=, <:

D4@A5 6 SQ-1S/6 SQ-2S 4,194/4,294

D@5<;?8 0,275

85R<5V B7;8;A@: 0,755

Basic Characteristics

Max launch range, km 40

Launch weight, kg 310

Warhead weight, kg 90

Weight of container with missile, kg 530

Warhead type HE

Guidance system passive radar

Guidance accuracy (CEP), m 3 - 5

Trajectory type with zoom

Overall dimensions of missile, m:

length with PRGS-1VP/ PRGS-2VP 4.194/4.294

diameter 0.275

fin span 0.755

Kh-25MP

AIR-RADAR MISSILE

The missile is designed to engage operating radars.

It has a combined control system. In the vertical plane,

guidance is effected in two stages. During the first stage,

the self-contained control system ensures missile motion

along the logarithmic trajectory. As soon as the departure

angle reaches 27 degrees, the missile goes into a dive.

During the second stage, the missile follows the radiation

of the target radar. The control system stabilizes the mis-

sile in pitch, yaw and roll. Depending on the target radia-

tion band, the missile carries the PRGS-1VP or PRGS-2VP

passive radar target seeker. The PRGS-1VP seeker

searches for radar targets and tracks them within a sec-

tor of ±30 degrees while suspended on the carrier. The

maximum angular tracking rate of the PRGS-1VP seeker

antenna is 6 deg/s. The PRGS-2VP seeker searches for

radar targets and tracks them, when carried by the par-

ent aircraft, within a sector of ±30 degrees in yaw and

from +20 to -40 degrees in pitch. The maximum angular

tracking rate of the PRGS-2VP seeker antenna is 8 deg/s.

A container is used to transport and store the missile.

Carriers: Su-17M3, Su-17M4, MiG-27K, MiG-27M,

MiG-27D.

>? @ >#@!@ 

«> BCD - #» D-25!

S8;DA5RA5K;A5 D4: 7B85q;A@: 85IB?5rs@V .

@6?;<5 E78594;A@: 85>;?= - >B<I@A@8B95AA5:.  9;8?@-

>54CAB< >5A54; A59;D;A@; B6Es;6?94:;?6: 9 D95 t?575. u5

7;89B< - 6 7B<BsCr 59?BAB<ABJ 6@6?;<= E78594;A@:, >B-

?B85: BI;67;K@95;? D9@q;A@; 85>;?= 7B 4BF58@M<@K;6>BJ

?85;>?B8@@. S8@ DB6?@q;A@@ EF45 7;4;AF5 27

85>;?5 7;8;-

9BD@?6: 9 7@>@8B95A@;. u5 9?B8B< - 65<BA59;D;A@; 7B @R-

4EK;A@r -N;4@. @6?;<5 E78594;A@: 6?5I@4@R@8E;? 85-

>;?E 7B ?5AF5qE, >E86E @ >8;AE.  R59@6@<B6?@ B? D@575RB-

A5 @R4EK;A@: N;4;J E6?5A594@95;?6: 7566@9A=J 85D@B4B>5-

N@BAA=J >BB8D@A5?B8 N;4@ SQ-1S @4@ SQ-2S. BB8-

D@A5?B8 SQ-1S 7BR9B4:;? 78B@R9BD@?C 7B@6> 85D@B4B-

>5N@BAA=V N;4;J @ 64;q;A@; R5 A@<@ A5 7BD9;6>; AB6@?;-

4: 9 6;>?B8; ±30

. #5>6@<54CA5: EF4B95: 6>B8B6?C 64;q;-

A@: 5A?;AA= >BB8D@A5?B85 SQ-1S - 6 F85D./6. BB8D@A5-

?B8 SQ-2S B6Es;6?94:;? 7B@6> -N;4;J @ 64;q;A@;

R5 A@<@ A5 7BD9;6>; AB6@?;4: 9 6;>?B8; ±30

7B >E86E @ B?

+20 DB -40

- 7B ?5AF5qE. #5>6@<54CA5: EF4B95: 6>B8B6?C

64;q;A@: 5A?;AA= >BB8D@A5?B85 SQ-2S - 8 F85D./6.

4: ?85A67B8?@8B9>@ @ V85A;A@: 85>;?= @67B4CRE;?6: >BA-

?;JA;8.

uB6@?;4@: E-17#3, E-17#4, #@Q-27, #@Q-27#, #@Q-27 .

400

PART 2  2

AIR-TO-GROUND

AND AIR-TO-SHIP MISSILES

  « !" - #$»,

« !" - '(»

GROUP 14

GUIDED MISSILES

Class 1410 Guided Missiles

 14    !

! ( !#)

2344 1410 !5637289:;9 63<9=; > 63<9=;-?@4>=92>

%&'(&)* +,-,./*-0%/0.0

#3<4>:32A?38 B32A?@4=A 5C4<3, <: 120

69B?88 4<@6@4=A 5@29=3, :/4 450 - 600

#3443, <H:

4=36=@738 650

J@97@K L34=> 150

'@9738 L34=A MCH34?38

N3J36>=?;9 63O:96; 63<9=;

(B2>?3 Q B>3:9=6 Q 63O:3Q <6;23), : 4,813 Q 0,38 Q 1,17

>5 B7>H3=92A?@K C4=3?@7<>  

Basic Characteristics

Max launch range, km 120

Average flight speed, m/s 450 - 600

Launch weight, kg 650

Warhead weight, kg 150

Warhead type HE

Overall dimensions of missile

(length x diameter x wing span), m 4.813 x 0.38 x 1.17

Propulsion system solid-propellant

rocket motor

Kh-58E AIR-TO-SURFACE

MISSILE

The missile is designed to engage radars, including

those with changeable parameters and operating in the

intermittent modes, at standoff ranges.

The control system comprises a passive radar homing

head of an appropriate frequency band, a control unit

and an actuator unit.

Carriers: Su-17M3(M4), Su-24M, MiG-31BM, and air-

craft of the Su-27 family.

@A B @#B!B 

«@ DEF -  @F » F-58H

j69B?3O?3L9?3 B28 5@63k9?>8 63B>@2@<3l>@??;Q 4=3?-

l>K, 63J@=3mn>Q 7 =@: L>429 7 5696;7>4=@: 69k>:9 >O-

2CL9?>8 > 4 59694=63>739:;:> 5363:9=63:>, J9O 7Q@k-

B9?>8 43:@29=3-?@4>=928 7 O@?C 5@63k9?>8 .

>4=9:3 C563729?>8 4@4=@>= >O 5344>7?@K 63B>@2@<3l>-

@??@K H@2@7<> 43:@?379B9?>8 (jN) 4@@=79=4=7Cmn9H@

2>=963, J2@<3 C563729?>8 > J2@<3 o29<=6@M6><l>@??;Q

:3p>?.

q@4>=92>: C-17#(#4), C-24#, #>N-31'#, 43:@29=;

49:9K4=73 C-27.

401

PART 2  2

AIR-TO-GROUND

AND AIR-TO-SHIP MISSILES

  « !"# - $%»,

« !"# - ()»

GROUP 14

GUIDED MISSILES

Class 1410 Guided Missiles

 14    !

! ( !#)

2344 1410 "5637289:;9 63<9=; > 63<9=;-?@4>=92>

%&'(&)* +,-,./*-0%/0.0

$3<4>:32A?38 B32A?@4=A 5C4<3, <: 115

$36E9738 7;4@=3 5@29=3, : 50 - 1100

69B?88 4<@6@4=A 5@29=3, :/4 280

!32A?@4=A 2>?>> 478I>, <: 140

$3443, <J:

4=36=@738 930

N@97@O P34=> 320

(@9738 P34=A 56@?><3QR38

>4=9:3 ?379B9?>8 =9297>I>@??@-<@:3?B?38

>5 B7>J3=92A?@O C4=3?@7<> 4=36=@7;O !, :36E97;O !!

Basic Characteristics

Max launch range, km 115

Cruising altitude, m 50 - 1,100

Average flight speed, m/s 280

Communications range, km 140

Launch weight, kg 930

Warhead weight, kg 320

Warhead type penetrating

Guidance system TV command

Propulsion system solid-propellant booster,

turbofan sustainer

;< = ;#=!= 

«; ?@A -  ;A » A-59!F

e69B?3I?3P9?3 B28 5@63f9?>8 ?3I9:?;g > ?3B7@B?;g h9-

29O, 7>IC32A?@ @N?36Cf>739:;g @5963=@6@: 7 2QN@9

769:8 B?9: 7 56@4=;g :9=9@C42@7>8g.

 4@4=37 63<9=?@J@ <@:529<43 7g@B8=:

- 63<9=3 #-59$j;

- C?>796432A?;O 5@B794?@O <@?=9O?96;

- 37>3h>@??@9 <3=35C2A=?@9 C4=6@O4=7@;

- 5C2A= @5963=@63 > >?B><3=@6 h92>.

l@4>=92>: C-24$, 43:@29=; 49:9O4=73 C-27.

Kh-59ME AIR-TO-SURFACE

MISSILE

The missile is designed to engage ground and water-

borne targets detected by the operator at any time of

the day in visual meteorological conditions.

The missile system comprises:

- Kh-59ME missile;

- universal detachable pod;

- airborne catapult;

- operator’s control panel and target indicator.

Carriers: Su-24M and aircraft of the Su-27 family.