KSLV-I 2005 Credit - © Mark Wade

In 2005 it was announced that the KSLV-I would not fly until 2007. It was now a completely different vehicle, consisting of a first stage derived from the Russian Angara launch vehicle, and a solid propellant second stage of South Korean manufacture.

It had been decided to develop a first stage in collaboration with Russia, based on the still-in-development Angara launcher. This would be an order-of-magnitude larger than the original KSLV-I design. The first test of this vehicle, still designated KSLV-I, was moved to 2007 and would consist of a launch of the first stage with a South Korean solid rocket motor kick stage to place the small 100-kg satellite into orbit.

KARI oversaw basic system design, ystem management of the launch vehicle, and basic design of the ground equipment. International cooperation plans called for joint development of the launch vehicle and interface design for the 100 kg Science Satellite 2.

Manufacturer: KARI . LEO Payload: 100 kg (220 lb). to: 300 km Orbit. at: 38.00 degrees. Liftoff Thrust: 1,910.000 kN (429,380 lbf). Total Mass: 140,000 kg (300,000 lb). Core Diameter: 3.90 m (12.70 ft). Total Length: 30.00 m (98.00 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-1. Gross Mass: 1,000 kg (2,200 lb). Empty Mass: 100 kg (220 lb). Thrust (vac): 86.200 kN (19,379 lbf). Isp: 250 sec. Burn time: 25 sec. Isp(sl): 220 sec. Diameter: 0.42 m (1.37 ft). Span: 0.42 m (1.37 ft). Length: 4.70 m (15.40 ft). Propellants: Solid. No Engines: 1. Status: In development. All values except thrust estimated.

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