KSLV-I 2002 Credit - © Mark Wade Media Gallery

In 2002 South Korea announced it was planning to develop a small satellite launch vehicle by 2005, based on technology flown on the KSR-III test vehicle. By 2005 this was replaced by a completely different design, based on the Russian Angara space booster.

Originally it was planned that the KARI Space Launch Vehicle would be entirely indigenous, building on the systems developed for the KSR-III liquid-propellant sounding rocket launched on November 28, 2002. A drawing of this vehicle showed it to be based on the 12.5-tonne thrust liquid oxygen/kerosene rocket flown on the KSR-III Two KSR-III stages would flank the core, forming the first stage. The second stage would be the first stage of the core, consisting of a single KSR-III. A solid propellant motor, perhaps based on that flown on the KSR-I and KSR-II, would provide the third stage.

Manufacturer: KARI . LEO Payload: 100 kg (220 lb). to: 300 km Orbit. at: 38.00 degrees. Liftoff Thrust: 244.000 kN (54,853 lbf). Total Mass: 20,000 kg (44,000 lb). Core Diameter: 3.90 m (12.70 ft). Total Length: 30.00 m (98.00 ft).

• Stage Number: 0. 2 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.

• Stage Number: 1. 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.

• 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.

• Marinin, Igor, Novosti kosmonavtiki, . A biweekly Russian-language magazine on the past, present, and future of space exploration and space technology. Subscriptions: here.

• Wire service and TV news reports..