| KSLV |
home
topic index |
||||||||
South Korean launch vehicle family. Originally they were to be of completely indigenous design; but in 2005 it was now 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.
Manufacturer: KARI .
Version: KSLV-I. Status: In development. Manufacturer's Designation: Korea Space Launch Vehicle-I. 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.
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). KSLV-II.
South Korean launch vehicle, originally scheduled for first flight by 2010. Evidently it would have consisted of a Russian Angara first stage and a South Korean liquid-propellant second stage. In August 2006 it was reported in the Korean press that this launcher configuration was cancelled. The 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: 1,000 kg (2,200 lb). to: 300 km Orbit. at: 38.00 degrees. Liftoff Thrust: 1,910.000 kN (429,380 lbf). Total Mass: 144,000 kg (317,000 lb). Core Diameter: 3.90 m (12.70 ft). Total Length: 35.00 m (114.00 ft).
KSLV-III.
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: 800 km Orbit. at: 97.00 degrees. Liftoff Thrust: 1,910.000 kN (429,380 lbf). Total Mass: 145,000 kg (319,000 lb). Core Diameter: 3.90 m (12.70 ft). Total Length: 35.00 m (114.00 ft).
Bibliography:
Contact us with any corrections, additions, or comments. Conditions for use of drawings, pictures, or other materials from this site.. To contact astronauts or cosmonauts. © Mark Wade, 1997 - 2008 except where otherwise noted. |
|
