KSR-III

South Korean sounding rocket. 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 development 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.

Payload: 150 kg (330 lb) to a 80 km altitude.

Stage Data - KSR-III

• 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.