Kh-35

Kh-35 (NATO reporting name: AS-20 'Kayak') 3M24 Uran (SS-N-25 'Switchblade') 3K60 Bal (SSC-6 'Sennight')
Kh-35E in MAKS-2009
Type	air-to-surface, surface-to-surface missile
Place of origin	Soviet Union
Service history
In service	2003
Used by	Russian Navy Indian Navy Vietnamese People's Navy
Production history
Designer	Zvezda
Designed	1983-2003
Manufacturer	Tactical Missiles Corporation
Unit cost	$500,000 (2010)
Produced	1996 for export, 2003 for Russia
Specifications
Weight	520 kg (1,150 lb) 610 kg (1,340 lb) (heli version)
Length	385 cm (152 in) 440 cm (173 in) (heli version)
Diameter	42.0 cm (16.5 in)
Warhead	HE shaped charge
Warhead weight	145 kg (320 lb)
Engine	turbofan 450 kgf
Wingspan	133 cm (52.4 in)
Propellant	kerosene
Operational range	130 km (70 nmi) 300 km (160 nmi) (2015)
Flight altitude	10-15 m en route and about 4 m at terminal area
Speed	Mach 0.8 (609 mph; 980 km/h)
Guidance system	inertial guidance and ARGS-35E X-band terminal active radar homing
Launch platform	Su-24, MiG-29M/K, Su-27SM, Su-30MKI, Su-34, HAL Tejas, Ka-27, Ka-28, also ships and boats, coastal, LACM, TEL variants.

The Zvezda Kh-35U ('Star', Russian: Х-35У, AS-20 'Kayak') is the jet-launched version of a Russian subsonic anti-ship missile. The same missile can also be launched from helicopters, surface ships and coastal defence batteries with the help of a rocket booster, in which case it is known as Uran ('Uranus', SS-N-25 'Switchblade', GRAU 3M24 ) or Bal ('Ball', SSC-6 'Sennight', GRAU 3K60). It is also nicknamed "Harpoonski", because it looks like and functions very similar to the American Harpoon Anti-Ship missile. It is designed to attack vessels up to 5000 tonnes.

Zvezda started work on the Kh-35 in 1983 by a decree of the USSR Council of Ministers and the USSR CPSU Central Committee to arm ships of medium tonnage.

The Kh-35 missile is a subsonic weapon featuring a normal aerodynamic configuration with cruciform wings and fins and a semisubmerged air duct intake. The propulsion unit is a turbofan engine. The missile is guided to its target at the final leg of the trajectory by commands fed from the active radar homing head and the radio altimeter.

Target designation data can be introduced into the missile from the launch aircraft or ship or external sources. Flight mission data is inserted into the missile control system after input of target coordinates. An inertial system controls the missile in flight, stabilizes it at an assigned altitude and brings it to a target location area. At a certain target range, the homing head is switched on to search for, lock on and track the target. The inertial control system then turns the missile toward the target and changes its flight altitude to an extremely low one. At this altitude, the missile continues the process of homing by the data fed from the homing head and the inertial control system until a hit is obtained.