CHINA RUSIA US
PL-21
 Mass : 270 kilogram (600 lb)
 Length : 5,5 meter (18 kaki)
 Diameter : 250–300 mm (9,8–11,8 in)
 Warhead : 6kg blast-frag, or expanding rod
(RF-fuse)
 Detonation mechanism : Active infrared,
laser proximity fuse(PL-5EII)
 Engine : Ramjet
 Wingspan 0.657m (PL-5B, PL-5C), 0.617m
(PL-5E)
 Operational range : 150 – 200 km
 Speed Mach 2.5
 Guidance Sistem : Actif radar with AESA
 Launch platform : Aircraft,
 Medium Range
R-77
 Mass : 175 kg (R-77), 190 kg (R-77-1)
 Length : 3.6 m (R-77), 3.71 m (R-77-1)
 Diameter : 200 mm
 Warhead : 22.5 kg HE fragmenting (R-77)
 Detonation mechanism Laser proximity fuse
 Engine Solid fuel rocket motor (R-77), air-
breathing ramjet (R-77-PD)
 Wingspan700 mm
 Operational range 80–100 km (R-77), 110 km
(R-77-1), 193 km (R-77M)
 Flight altitude : 5–25 km (16,000–82,000 ft)
 Speed Mach 4, Mach 5 for K-77PD (RVV-AE-
PD)
 Guidance system : Inertial with mid-course
update and terminal active radar
homing/infrared homing (R-77T)
 Launch platform : Aircraft:
 Medium Range
AIM 120-AMRAM
 Mass : 335 lb (152 kg)
 Length : 12 ft (3.7 m)
 Diameter : 7 in (180 mm)
 Warhead : High explosive blast-fragmentation
 Detonation mechanism : Active RADAR
Target Detection Device (TDD), Quadrant
Target Detection Device (QTDD) in AIM-120C-
6 – lots 13+
 Engine Solid-fuel rocket motor
 Wingspan20.7 in (530 mm) AIM-120A/B
 Operational range : AIM-120A/B: 55–75 km
(30–40 nmi), AIM-120C-5: >105 km (>57
nmi), AIM-120D (C-8): >160 km (>86 nmi)[6]
 Speed Mach : 4 (4,900 km/h; 3,045
mph)[citation needed
 Guidance system : inertial guidance, terminal
active radar homing
 Launch platform : Aircraft:
 Medium Range.
AIR TO AIR MISSILE (MEDIUM RANGE)

CHINA RUSIA US
DF-12 M20
 Type Short-range surface-to-air missile
System
 Country users : China
 Warhead : 480 kg
 System reaction time :10 sec.
 Armament : Two missiles in individual
container ready to fire
 Range missile : Minimum 100 km;
Maximum 280 km
 Guidance system : Inertial guidance and
INS with satellite guidance
 Radar and command station : Command
and control vehicle
9K720 ISKANDER-M/SS-26 STONE
 Missile Variants : Iskander-M; Iskander-E
(export)
 Mobility and Role : Road-mobile; surface-to-
surface short-range ballistic missile
 Designer/Producer : Machine-Building Design
Bureau
 Range : 400-500 km (Iskander-M); 280 km
(Iskander-E)
 Warhead Type and Weight : Nuclear and
conventional – 700 kg
 Guidance System/Accuracy : Inertial and
optical/10-30 m CEP (Iskander-M);
Inertial/30-70 CEP (Iskander-E)
 Stages/Propellant : One/Solid
 IOC/Retirement : 2006 (Iskander-M)/Not
Available Need updating by 2020
MGM-140 ATACMS
 Mass : 3,690 pounds (1,670 kg)
 Length : 13 feet (4.0 m)
 Diameter : 24 inches (610 mm)
 Maximum firing range: 190 mi (300 km)
 Wingspan55 inches (1.4 m)
 Flight ceiling : 160,000 ft (50 km)
 Speed : In excess of Mach 3 (0.6 mi/s; 1.0
km/s)
 Guidance System : GPS-aided inertial
navigation guidance
 Launch platform : M270, HIMARS.
BALISTIC MISSILE (TACTICAL MISSILE)

CHINA RUSIA US
DF-11
 Type : SRBM (Short Range Balistic Missile)
 Used by PRC
 Production history
 Manufacturer :Academy of Rocket Motors
Technology
 Specifications
 Mass 3,800 kg[1]
 Length 7.5-8.5 m[2]
 Diameter 0.86 m
 Warhead 500 kg: 2/10/20 kiloton nuclear
warhead, fuel-air explosive (FAE), chemical,
or submunition
 Engine single-stage solid-propellant rocket
 Operational range : DF-11：300+ km
 DF-11A：700+ km, DF-11AZT：600 km
 Guidance System :Astro-inertial guidance
(including ring-laser gyroscope) + Beidou
 Launch Platform : Road-mobile TEL
P-800 ONIKS (SS-N-26)
 Russian/NATO Designation P-800 Oniks (Land-
based Yakhont)/SS-N-26 Strobile Variants
BrahMos
 Mobility and Role :
 Surface-to-Surface Anti-Ship Cruise Missile
 Max Speed 3000 km/h
 Designer/Producer NPO Mashinostroyeniya
 Range 300km
 Warhead Type and Weight
 3000kg launch weight
 HE warhead; Armor-Piercing Warhead Yield
 200kg HE warhead;
 250 kg Armor-piercing warhead
 Guidance System/Accuracy
 1.5m CEP
 Satellite Guidance; Active Radar Seeker
 Cruise Altitude Max 14,000 m
 Propellant Solid-fuel Booster;
Liquid-Fuel Ramjet Sustainer
 IOC/Retirement :2002/Operational
 Status/Number of Units Operational/Unknown
 Launch Vehicles
 Nakat class missile ship; Yasen class
submarine;
 Bastion-P/Bastion-S ground-launch system
PGM-11 REDSTONE
BALISTIC MISSILE (SHORT RANGE)
 Mass : 61,207 pounds (27,763 kg) at ignition
 Length : 69.3 feet (21.1 m)
 Diameter : 5.83 feet (1.8 m)
 Blast yield :3.5 megatons of TNT (15 PJ) or 500
kilotonnes of TNT (2.1 PJ)
 thermonuclear warhead
 Engine : Rocketdyne North American Aviation
75–110 A-7
 78,000 pounds-force (350 kN) thrust at sea level
for 121 seconds
 Payload capacity : 6,305 pounds (2,860 kg)
 Propellant ethyl alcohol, liquid oxygen, hydrogen
peroxide
 Fuel capacity : alcohol: 11,135 pounds (5,051 kg),
liquid oxygen: 25,280 pounds (11,470 kg),
hydrogen peroxide: 790 pounds (360 kg)
 Operational range : 57.5 miles (92.5 km) to 201
miles (323 km)
 Flight altitude : 28.4 miles (45.7 km) peak
minimum to 58.7 miles (94.5 km) peak maximum
 Boost time: 97 seconds to 117 seconds
 Speed Mach : 5.5 maximum at re-entry interface
 Guidance System : Ford Instrument Company
ST-80 inertial guidance
 Steering System : Carbon jet vanes, air rudders,
spatial air jet nozzles, air vanes
 Accuracy : 300 metres (980 ft) CEP
 Launch platform :Guided missile platform
launcher M74

CHINA RUSIA US
DF-21
- Mass 14,700 kilograms (32,400 lb)
- Length 10.7 metres (35 ft)
- Diameter 1.4 metres (4.6 ft)
- Warhead 600kg: 1, or 5-6 (improved variant)[1]
200-300-500 kt nuclear[2]
- Engine Solid fueled
- Operational range :1,770 km (1,100 mi) (DF-
21/DF-21A), 1,700 km (1,100 mi) (DF-21C)
- 1,500 km (930 mi; 810 nmi) (DF-21D ASBM)[4]
- Speed Mach : 10
- Guidance System:Inertial + terminal active radar
guidance
- Accuracy :DF-21 700m, DF-21A 50m, DF-21B
10m CEP (with BeiDou Navigation Satellite
System and active radar)
- Launch Platform : Mobile launcher
SSC - 8
 Country of origin : Russia
 Entered service : 2018
 Crew : 3 men
 Number of missiles : 4
 Weight : ~ 40 t
 Length : 13.25 m
 Width : 3.51 m
 Height : 3.94 m
 Missile length (including booster) : ~ 8 m
 Missile diameter : 0.53 m
 Wing span : ~ 3 m
 Missile weight : ~ 2 300 kg
 Warhead weight : 400 ~ 500 kg
 Warhead type : Nuclear
 Range : 2 000 ~ 2 500 (?)
 CEP : ~ 5 m
Mobility :
 Engine : YaMZ-846 diesel
 Engine power : 500 hp
 Maximum road speed :70 km/h
 Range : 1 000 km – 5000 Km
 Maneuverability
 Gradient :45%
 Side slope : 30%
 Vertical step : ~ 0.6 m
 Trench : 2 m
 Fording : 1.4 m
AGM-86
 Overall length: 19.82 m (65.0 ft)
 Span: 2.74 m (9.0 ft)
 Weight: 49,800 kg (109,800 lb)
 Empty weight: 3,125 kg (6,889 lb)
 Core Diameter: 2.44 m
 Maximum range: 2,400 km (1,500 mi)
 Ceiling: 480 km (300 mi)
 Guidance: Inertial
 Maximum speed: 17,740 km/h (11,020 mph)
 Engines: Vernier: 2x Rocketdyne LR101-NA; 4.5 kN
(1000 lbf)
 Warhead : One W49 warhead on Mk. 2 reentry
vehicleMass 3,150 pounds (1,430 kg)
 Length 20 ft. 9 in. (6.3 m)
 Diameter 24.5 inches (620 mm)[
 Warhead W80 thermonuclear weapon (AGM-86B)
 conventional warhead (AGM-86C)
 AUP warhead (AGM-86D)
 Warhead weight : 908kg (AGM-86C Block 0)
 1362kg (AGM-86C Block 1)
 1,200 lb class advanced unitary penetrating
warhead (AGM-86D)
 Engine : Williams International
 F107-WR-101 turbofan engine
 600 lbf (2.7 kN) thrust
 Wingspan 12 feet (3.7 m)
 Guidance system : AGM-86B: Litton inertial nav
system element with TERCOM, AGM 86C: Litton
INS element integrated with GPS
 Launch platform : Boeing B-52H Stratofortress
BALISTIC MISSILE (MEDIUM RANGE)

CHINA RUSIA US
JL-2
 Type : SLBM (Submarine Launched Balistic
Missile)
 Place of origin :People's Republic of China
 Service history
 In service Active as of 2015
 Used by People's Liberation Army Navy
 Specifications
 Mass : 42,000 kilograms (93,000 lb)[2]
 Length : 13 metres (43 ft)[2]
 Warhead : 1 nuclear warhead[3]
 Blast yield : 1 megaton of TNT (4.2 PJ)[4]
 Propellant : Solid-fuel rocket
 Operational Range : 7,200 km (4,500 mi)[5]
 Guidance System : Astro-inertial[4] with
Beidou
 Launch Platform : Type 094 submarine
SS-19 STILLETO
 Length (m) : 17.2
 Body diameter (m) : 2.5
 Fueled weight (t) : 86.3
 Engine Designation : RD-0233 / RD-0234,
 RD-0235 (14/15D113)
 Vernier Engine Designation RD-0236 (15D114)
 Bus Engine Designation Third Stage RD-0237
 Fuel : UDMH
 Oxidizer : Nitrogen Tetroxide
 Payload (t) : 4.350
 Total length (m) : 24.3
 Warhead (m) : 21.1
 Missile Diameter (m) : 2.50
 Launch Weight (t) : 103.4 - 105.6
 Fuel Weight (t) : 93.1
 Range (km) : 10,000
MINUTEMAN III
 Berat : 78,000 lb (35,300 kg)
 Panjang : 59 ft 9.5 in (18.2 m)
 Diameter : 5 ft 6 in (1.7 m) (1st stage)
 Hulu ledak : Nuclear W62, W78, or (2006-) W87
 Jenis Mesin : Three solid-propellant rocket
motors; first stage - Thiokol TU-122 (M-55);
second stage - Aerojet-General SR-19-AJ-1;
third stage - Aerojet/Thiokol SR73-AJ/TC-1
 Daya jelajah : 8,100 miles (13,000 km)
 Ketinggian terbang : 700 miles (1,120
kilometers)
 Kecepatan Approximately : 15,000 mph (Mach
23, or 24,100 km/h, or 7 km/s) (terminal phase)
 Sistem penuntun : Inertial
 Alat Peluncur : Silo
BALISTIC MISSILE (LONG RANGE)

CHINA RUSIA US
QW-2 VANGUARD 2
 Type MANPAD
 Service history 1990’s to present
 Used by China and Bangladesh
 Production history
 Produced : Since Mid 1990’s
Specifications
 Weight : 11.32 kg, 18 kg with launcher
 Length : 1.59 meter
 Detonation
 mechanism : Impact & Proximity
 Engine rocket
 Propellant : solid rocket
 Operational Range : 6 km maximum
 Flight ceiling : 3 km
 Flight altitude : 10 meter minimum
 Speed > 600 m/s
 Guidance System : Infrared homing
 Launch Platform : MANPADS, Type 95
SPAAA
PANTSIR (S1, S2 & S3)
 Armament : Twelve ground-to-air missile
launcher 57E6 / 57E6-E, two dual 2A38M 30
mm autocannon guns
 Country users : Iran, Iraq, Serbia, United Arab
Emirates, Jordan, Russia, Syria, Vietnam
 Designer Company : KBP Instrument Design
Bureau
 Accessories : Radio commands with IR or radio
direction finding, autonomous acquisition radar
and tracking radar
 Crew : 3 soldiers
 Radar System : Autonomous acquisition and
tracking radar 1RS2-1
 Range missile : 1 – 30 km
 Weight missile : 90 kg with container
MIM-104 PATRIOT (PAC3)
 Specifications (PAC-1)
 Mass : 700 kg (1,500 lb)
 Length : 5,800 mm (19 ft 0 in)
 Diameter : 410 mm (16 in)
 Warhead : M248 Composition B HE blast/
fragmentation with two layers of pre-formed
fragments and Octol 75/25 HE blast/
fragmentation
 Warhead weight : 200 lb (90 kg)
 Detonation mechanism : Proximity fuze
 Wingspan : 920 mm (3 ft 0 in)
 Propellant : Solid-fuel rocket
 Operational Range : PAC-3: 20 km against
ballistic missile, PAC-3 MSE: 35 km against
ballistic missile
 Flight altitude : 79,500 feet (24,200 m)
 Speed : PAC-1: Mach 2.8, PAC-2/PAC-3: Mach
4.1
 Guidance System : PAC-1: Radio command with
Track Via Missile semi-active homing, PAC-3: Ka
Band AESA seeker
 Launch Platform : Mobile trainable four-round
semi-trailer
SURFACE TO AIR MISSILE (SHORT RANGE)

CHINA RUSIA US
KS-1
 Weight: 900 kg
 Warhead: > 100 kg
 Length: 5.6 m
 Diameter: 0.4 m
 Speed: 1,200 m/s
 Maneuverability: > 20 g
 Maximum target speed: 750 m/s
 Maximum target maneuverability: > 5 g
 Maximum range: > 50 km
 Minimum range: 100 m
 Maximum altitude: > 25 km
 Minimum altitude: < 500 m
S-300 VM
 Operational Range : 200 (250) km against
MRBMs
 9M82M missile
 Type : Surface-to-air missile
 Place of origin : Russia
 Production history
 Designer : Almaz-Antey
 Designed 2000s
 Manufacturer : Almaz-Antey
 Produced : 2013-present
 Variants 9M82M, 9M83M
 Specifications (9M82M
 Operational Range :
200 kilometres (120 mi)
 Flight altitude :
30,000 metres (98,000 ft)
MIM-104 PATRIOT (PAC1 & PAC2)
 Specifications (PAC-1)
 Mass : 700 kg (1,500 lb)
 Length : 5,800 mm (19 ft 0 in)
 Diameter : 410 mm (16 in)
 Warhead : M248 Composition B HE blast/
fragmentation with two layers of pre-formed
fragments and Octol 75/25 HE blast/
fragmentation
 Warhead weight : 200 lb (90 kg)
 Detonation mechanism : Proximity fuze
 Wingspan : 920 mm (3 ft 0 in)
 Propellant : Solid-fuel rocket
 Operational Range : PAC-1: 70 km
 PAC-2: 96 km-160 km
 Flight altitude : 79,500 feet (24,200 m)
 Speed : PAC-1: Mach 2.8, PAC-2/PAC-3: Mach
4.1
 Guidance System : PAC-1: Radio command with
Track Via Missile semi-active homing, PAC-3: Ka
Band AESA seeker
 Launch Platform : Mobile trainable four-round
semi-trailer
SURFACE TO AIR MISSILE (MEDIUM RANGE)

CHINA RUSIA US
HG-9
 Mass :1300 kg
 Length : 6.8 m
 Warhead weight :180 kg
 Engine Two-stage solid propellant rocket
 Operational Range : 200 km (FD-2000
version) 250 km (HQ-9A version) 300+ km for
HQ-9B version
 Flight ceiling : 27 km, 41 km for HQ-9B
 Speed Mach : 4.2
 Guidance System Inertial guidance with mid-
course update and terminal active radar
homing
 Launch Platform : Taian TA580/TAS5380 8×8
transporter erector launcher (TEL)
 Type 052C destroyer
 Type 052D destroyer
 Type 055 destroy
S-500 PROMETHEUS
 S-500 launcher based on the BAZ-69069
chassis
 Country of origin : Russia
 Entered service : Expected in 2025
 Crew 3 men
 Weight 54 t
 Length ~ 14.5 m
 Width ~ 3 m
 Range of fire : 500 ~ 600 km
 Altitude of fire : ~ 40 km
 Mobility :
 Engine : diesel
 Engine power : 550 hp
 Maximum road speed ~ 70 km/h
 Range ~ 1 000 km
 Maneuverability
 Gradient 60%
 Side slope 30%
 Vertical step ~ 0.6 m
 Trench ~ 2 m
 Fording 1.7 m;
AN/TWQ-1 AVENGER
 Country of origin : United States
 Entered service : 1990
 Crew : 2 men
 Weight 4.3 t
 Length 4.95 m
 Width 2.49 m
 Height 2.64 m
 Missile length 1.52 m
 Missile diameter 0.07 m
 Missile weight 10.1 kg
 Warhead weight 3 kg
 Warhead type HE-FRAG
 Range of fire 4 - 8 km
 Altitude 3.5 - 3.8 km
 Guidance : Infrared homing
 Engine Detroit Diesel diesel
 Engine power 135 hp
 Maximum road speed 100 km/h
 Range 480 km
 Maneuverability
 Gradient 60%
 Side slope : 30%
 Vertical step : 0.5 m
 Trench : 0.5 m
 Fording : 0.75 - 1.5 m
SURFACE TO AIR MISSILE (LONG RANGE)

CHINA RUSIA US
YJ-12B
 Country of origin China
 Crew ~ 5
 Weight ~ 40 t
 Length ~ 16 m
 Width ~ 3 m
 Height ~ 3.5 m
 Warhead weight 200 kg
 Warhead type HE-FRAG
 Range of fire 400 ~ 500 km
 Guidance : Inertial with active radar homing
 Mobility
 Engine Deutz diesel
 Engine power : 544 hp
 Maximum road speed :70 km/h
 Range 650 km
 Maneuverability
 Gradient 40%
 Side slope : 20%
 Vertical step : 0.4 m
 Trench 2.5 m
 Fording 1.2 m
BAL
 Country of origin Russia
 Entered service 2004
 Crew 3 men
 Weight ~ 40 t
 Length ~ 12.8 m
 Width ~ 3 m
 Height ~ 3.6 m
 Missile length 4.4 m
 Missile diameter 0.42 m
 Wing span 1.33 m
 Missile weight 620 - 670 kg
 Warhead weight 145 kg
 Warhead type HE-FRAG
 Range of fire 130 / 260 km
 Engine YaMZ-846
 Engine power 500 hp
 Maximum road speed 70 km/h
 Range 1 000 km
 Maneuverability Gradient 45%
 Side slope 30%
 Vertical step ~ 0.6 m
 Trench 2 m
 Fording 1.4 m
BGM-109G GRYPHON
 Country of origin United States
 Entered service 1983
 Crew 3 men
 Number of missiles 4
 Weight 36 t
 Length 19.8 m
 Width 2.44 m
 Height ~ 3 m
 Missile length (without booster) 5.56 m
 Missile diameter 0.52 m
 Missile launch weight 1 200 kg
 Warhead weight 176 kg
 Warhead type Nuclear, 150 kT yield
 Range of fire 2 500 km
 CEP ~ 30 m
 Engine MAN D2866 KFG diesel
 Engine power 360 hp
 Maximum road speed 80 - 90 km/h
 Range ~ 800 km
 Maneuverability
 Gradient (with trailer) ~ 20%
 Fording ~ 1.2 m
COASTAL DEFENSE SYSTEM (ANTI SHIP MISSILE)