Credit: © Mark Wade
S Korean LVs
South Korean space launch vehicles, including Russian Angara-derived vehicles.
Credit: © Mark Wade
South Korean launch vehicle, to consist of a Russian Angara first stage, a South Korean liquid propellant second stage, and a South Korean solid propellant apogee kick motor. Scheduled for first flight by 2015. In August 2006 the Korean press reported that the first and second stages would both be Angara-UM modules... how this configuration would work (stacked versus parallel) was unclear.
The originally-planned 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: 1,500 kg (3,300 lb) to a 800 km orbit at 97.00 degrees.
Stage Data - KSLV-III
- 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.
- Stage 3. 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.
More... - Chronology...
Gross mass: 145,000 kg (319,000 lb).
Payload: 1,500 kg (3,300 lb).
Height: 35.00 m (114.00 ft).
Diameter: 3.90 m (12.70 ft).
Thrust: 1,910.00 kN (429,380 lbf).
Apogee: 800 km (490 mi).
First Launch: 2009.08.25.
Number: 1 .
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...
KSLV South Korean launch vehicle family. Originally they were to be of completely indigenous design; but in 2005 it was announced that they would use the (in-development, unflown) Russian Angara booster module as the basis. The program, like that of the Angara, was subject to continuous funding shortages and schedule delays. First launch 2009.08.25. More...
Associated Manufacturers and Agencies
KARI South Korean agency overseeing development of rockets and spacecraft. Korea Aerospace Research Institute, Korea South. More...
Associated Launch Sites
Goheung South Korean space center, built on Woenaro Island, off the Goheung peninsula, at the southern end of the Korean peninsula. The space center would be built in four phases through 2015 on a 4.95 million square meter landfill on the shore of the island. More...
Angara UM Lox/Kerosene propellant rocket stage. Loaded/empty mass 140,000/10,000 kg. Thrust 2,094.70 kN. Vacuum specific impulse 337.5 seconds. Can be throttled to 95%. Propellant ration 2.6:1, chamber pressure 257 bar. More...
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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