Korean Sounding Rocket Program in Korea

Paper number

IAC-06-B1.P.1.01

Author

Dr. Seung-Hyun Hwang, Korea Aerospace Research Institute, Korea

Coauthor

Dr. Eui Seung Chung, Korea Aerospace Research Institute, Korea

Coauthor

Dr. Jeong Joo Park, Korea Aerospace Research Institute, Korea

Coauthor

Dr. Gwang-Rae Cho, Korea Aerospace Research Institute, Korea

Year

2006

Abstract

As a part of Korea national space program, Korean Government has led Sounding Rocket Program via Korea Aerospace Research Institute (KARI) providing enhanced capabilities across a spectrum of earth sciences or astrophysics related disciplines. In this paper, the Korea Sounding Rocket Program during 1993-2002 is introduced: This program includes KSR(Korea Sounding Rocket)-I, KSR-II, and KSR-III and total five of soundings were carried out. Two had flown in KSR-I series, two in KSR-II, and one in KSR-III. The main mission objective is to provide the opportunity to scientists for researching earth sciences or astrophysics and to improve Korean rocket development technologies including payload instruments, flight systems, ground systems, operational techniques, and interfaces between subsystems.
KARI had launched the first indigenous sounding rocket, KSR-420S-1 in 1993 as one of the KSR-I series. This rocket had featured unguided, single-staged, 6.7m long, 41.3cm diameter, and 1.1 ton rocket attained 39km altitude with the solid propellant and had successfully measured the ozone concentration over Korea. The KSR-420S-2 had attained 49km and also obtained the ozone profile.
KSR-II series were upgraded version of the KSR-I having two-staged solid propellant. The Inertia Navigation System (INS) and Flight Termination System (FTS) had adopted in this system. The 11.1m long, 42cm diameter, and 2 ton rocket had flown with 150kg onboard scientific payloads reaching at 137km and measured the ionospheric properties, celestial X-ray, and ozone concentration.
As a final series, the KSR-III has successfully launched on Nov. 2002 using Korean first liquid propulsion engine system. For scientific mission, it has acquired ozone concentration and earth magnetic fields data during the flight. It features 14m long, 1m diameter, and 6 tons, and has thrust vector controlling system. The onboard INS is enhanced to the launch vehicle applicable grade system. The key goal of developing liquid propulsion system in KSR-III is to secure technologies applicable for the space launch vehicle.
As increased the demand for launching of low-orbit earth satellites internally and externally, the Korean government is ambitiously firing the Korea Space Launch Vehicle (KSLV) Program, based on experience throughout the sounding rocket program and preparing into the world market for space launch vehicles.

Abstract document

IAC-06-B1.P.1.01.pdf

Manuscript document

IAC-06-B1.P.1.01.pdf (🔒 authorized access only).

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