Encyclopedia Astronautica
KSLV-I 2002



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KSLV-I 2002
KSLV-I as conceived in 2002, with the indigenous South Korean engine shown beside it.
Credit: © Mark Wade
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S Korean LVs
South Korean indigneous rockets.
Credit: © Mark Wade
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S Korean LVs
South Korean space launch vehicles, including Russian Angara-derived vehicles.
Credit: © Mark Wade
South Korean orbital launch vehicle. 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.

LEO Payload: 100 kg (220 lb) to a 300 km orbit at 38.00 degrees.

Stage Data - KSLV-I 2002

  • Stage 0. 2 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.
  • Stage 1. 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.
  • Stage 2. 1 x 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: Hardware 2002. Comments: All values except thrust estimated.

Status: In development.
Gross mass: 20,000 kg (44,000 lb).
Payload: 100 kg (220 lb).
Height: 30.00 m (98.00 ft).
Diameter: 3.90 m (12.70 ft).
Thrust: 244.00 kN (54,853 lbf).
Apogee: 300 km (180 mi).

More... - Chronology...


Associated Countries
  • Korea South South Korea became familiar with large-scale rocketry through maintenance and modification activities on American-supplied Honest John and Nike Hercules tactical missiles. By the 1990's Korea had developed an independent capability to manufacture solid propellant rocket motors of up to one tonne mass. In 1990 KARI was funded to build the first indigenous sounding rockets, flown as the KSR-I and KSR-II. In December 1997 KARI was allowed to proceed with development of liquid oxygen/kerosene rocket motor for an orbital launcher, but this was abandoned when the South Korean government decided it wanted to be among the top ten spacefaring nations by 2015. The existing program was too limited in growth potential to allow that. Therefore it was decided to leapfrog the technology by contracting with Russian companies. First launch of the KSLV-I launch vehicle from the new space centre took place in 2010. More...

See also
  • KSR South Korean indigenous sounding and test rocket family, using solid rocket motors and a test vehicle with a liquid oxygen/kerosene motor. Further development of the latter into the KSLV satellite launch vehicle was abandoned in 2005 in favor of licensed Russian technology. More...

Associated Manufacturers and Agencies
  • KARI South Korean agency overseeing development of rockets and spacecraft. Korea Aerospace Research Institute, Korea South. More...

Associated Stages
  • KSR-3 Lox/Kerosene propellant rocket stage. Loaded/empty mass 5,000/700 kg. Thrust 122.50 kN. Vacuum specific impulse 280 seconds. All values except thrust estimated. More...
  • KSR-1 Solid propellant rocket stage. Loaded/empty mass 1,000/100 kg. Thrust 86.20 kN. Vacuum specific impulse 250 seconds. All values except thrust estimated. More...

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