KSLV-I 2002 Credit - © Mark Wade

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.

KSR-I.

KSR-I Credit - © Mark Wade

Status: Retired 1993. Manufacturer's Designation: Korea Sounding Rocket-I.

First South Korean sounding rocket, an unguided single solid propellant stage vehicle. Development began in 1990 and the rocket was flown two times in 1993.

Development began in 1990, which was the first domestic single-stage unguided solid-propellant scientific rocket with a length of 6.7m, a diameter of 0.42m and lift-off weight of 1.2tons. KSR-I was launched on June 4 and September 1, 1993, respectively carrying an ultraviolet radiometer with the mission to measure the vertical ozone distribution in the stratosphere over the Korean peninsular. Temperature, acceleration and the other parameters were also measured to examine the performance of the rocket throughout the test flights. KSR-I had the payload capacity of 150kg and could reach the altitude of 75km.

Manufacturer: KARI. Launches: 2. First Launch Date: 1993-06-04. Last Launch Date: 1993-09-01. Payload: 150 kg (330 lb). Apogee: 75 km (46 mi). Liftoff Thrust: 86.000 kN (19,333 lbf). Total Mass: 1,200 kg (2,600 lb). Core Diameter: 0.42 m (1.37 ft). Total Length: 6.70 m (21.90 ft).

KSR-II.

KSR-II Credit - © Mark Wade

Status: Retired 1998. Manufacturer's Designation: Korea Sounding Rocket-II.

Two-stage South Korean sounding rocket, using two of the solid rocket motors developed for the KSR-I in tandem. Flown twice in 1997-1998.

Launches: 2. First Launch Date: 1997-07-09. Last Launch Date: 1998-06-11. Payload: 150 kg (330 lb). Apogee: 160 km (90 mi). Liftoff Thrust: 86.000 kN (19,333 lbf). Total Mass: 2,000 kg (4,400 lb). Core Diameter: 0.42 m (1.37 ft). Total Length: 11.04 m (36.22 ft).

KSR-III.

KSR-III Credit - © Mark Wade

Status: Active. Manufacturer's Designation: Korea Sounding Rocket-III.

Test bed for development of an orbital launch vehicle, powered by the liquid oxygen/kerosene engine planned for the KSLV-I. However flown only once in 2002.

The go-ahead for KARI to proceed with developement of a liquid propellant launch vehicle came in December 1997. The KSR-III demonstrated key technologies for the KSLV-I satellite launch vehicle in the propulsion, guidance, control, and mission design areas.

The Korea-developed pressure-fed liquid oxygen/kerosene motor provided a thrust of 12,500 kgf at sea level. This would be equivalent to the X-405 motor developed in the United States for the Vanguard space launcher in the 1950's. For the test launch, available pressurant only allowed a burn time of 53 seconds, with about 2500 kg of propellant consumed. Available tank volume indicated the stage was designed to be loaded with over 4000 kg of propellant.

Launches: 1. First Launch Date: 2002-11-28. Last Launch Date: 2002-11-28. Payload: 150 kg (330 lb). Apogee: 80 km (49 mi). Liftoff Thrust: 122.000 kN (27,426 lbf). Total Mass: 6,000 kg (13,200 lb). Core Diameter: 1.00 m (3.20 ft). Total Length: 14.00 m (45.00 ft).