Encyclopedia Astronautica
KSLV-I



zkslvi05.jpg
KSLV-I 2005
Revised version of KSLV-I, using a derivative of the Russian Angara booster.
Credit: © Mark Wade
zksrlvs2.jpg
S Korean LVs
South Korean space launch vehicles, including Russian Angara-derived vehicles.
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. First launch 2009.08.25.

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.

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

Stage Data - KSLV-I

  • 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-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.

AKA: Naro-1.
Status: Active.
Gross mass: 140,000 kg (300,000 lb).
Payload: 100 kg (220 lb).
Height: 30.00 m (98.00 ft).
Diameter: 3.90 m (12.70 ft).
Thrust: 1,910.00 kN (429,380 lbf).
Apogee: 300 km (180 mi).
First Launch: 2009.08.25.
Last Launch: 2010.06.10.
Number: 2 .

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
  • 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 Stages
  • 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-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...

KSLV-I Chronology


2009 August 25 - . 08:00 GMT - . Launch Site: Goheung. LV Family: KSLV. Launch Vehicle: KSLV-I. LV Configuration: Naro KSLV-1. FAILURE: First and second stages operated correctly, but half of payload fairing failed to separate. Extra mass prevented the second stage and payload from reaching orbital velocity, and the satellite reentered over New Guinea..
2010 June 10 - . 18:01 GMT - . Launch Site: Goheung. LV Family: KSLV. Launch Vehicle: KSLV-I. LV Configuration: Naro-1. FAILURE: First stage failure..
  • STSAT-2B - . Mass: 99 kg (218 lb). Nation: Korea South. Agency: KARI. Class: Technology. Type: Technology satellite. Spacecraft: STSAT. Summary: Science and Technology Satellite with Lyman-alpha imaging solar telescope and laser altimeter..

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