KSLV-II

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.

LEO Payload: 1,000 kg (2,200 lb) to a 300 km orbit at 38.00 degrees.

Stage Data - KSLV-II

• Stage 1. 1 x 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: Development 2004. Comments: Can be throttled to 95%. Propellant ration 2.6:1, chamber pressure 257 bar.

• Stage 2. 1 x 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: Hardware 2002. Comments: All values except thrust estimated.