KSLV-II Credit - © Mark Wade

South Korean launch vehicle, originally scheduled for first flight by 2010. Evidently it would have consisted of a Russian Angara first stage and a South Korean liquid-propellant second stage. In August 2006 it was reported in the Korean press that this launcher configuration was cancelled.

The second stage would logically be a repackaged version of the liquid oxygen/kerosene stage tested on the KSR-III in 2002 and originally intended to power the completely-indigenous original version of the KSR-I launch vehicle.

Manufacturer: KARI . LEO Payload: 1,000 kg (2,200 lb). to: 300 km Orbit. at: 38.00 degrees. Liftoff Thrust: 1,910.000 kN (429,380 lbf). Total Mass: 144,000 kg (317,000 lb). Core Diameter: 3.90 m (12.70 ft). Total Length: 35.00 m (114.00 ft).

• Stage Number: 1. 1 x Stage: Angara UM. Gross Mass: 140,000 kg (300,000 lb). Empty Mass: 10,000 kg (22,000 lb). Thrust (vac): 2,094.700 kN (470,907 lbf). Isp: 338 sec. Burn time: 300 sec. Isp(sl): 310 sec. Diameter: 2.90 m (9.50 ft). Span: 2.90 m (9.50 ft). Length: 25.00 m (82.00 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RD-191. Status: In development. Can be throttled to 95%. Propellant ration 2.6:1, chamber pressure 257 bar.

• Stage Number: 2. 1 x Stage: KSR-3. Gross Mass: 5,000 kg (11,000 lb). Empty Mass: 700 kg (1,540 lb). Thrust (vac): 122.500 kN (27,539 lbf). Isp: 280 sec. Burn time: 95 sec. Isp(sl): 240 sec. Diameter: 1.00 m (3.20 ft). Span: 1.00 m (3.20 ft). Length: 9.60 m (31.40 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: KSR-3. Status: In development. All values except thrust estimated.

• Wire service and TV news reports..