• Journal of the Korean Society of Propulsion Engineers
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• v.6 no.4
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• pp.37-45
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• 2002

The development process of KSR-III propulsion feeding system is subscripted. The purpose of propulsion feeding system is to feed a certain amount of propellant from propellant tank to engine by the end of combustion. Pressure-fed liquid rocket, KSR-III has the unique characteristics of both pressure regulator and cavitation venturi as a passive flow control device. Main parameters of feeding system are confirmed by both water test and CFD(전산유체) technique. Flow control effect with venturi is confirmed by water test. Initial stabilization characteristic of pressure regulator is confirmed by real propellant test. And, to avoid the effect of resonance between rocket and feeding system, this article deal with POGO(포고) analysis to the feeding system.

• Journal of Astronomy and Space Sciences
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• v.18 no.3
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• pp.249-256
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• 2001

KARI(Ko.ea Aerospace Research Institute) has measured the ionospheric electron temperature and density over the Korean Peninsular with the Langmuir and Electron Probe(LEP) onboard the Korean Sounding Rocket-II(KSR-II) In 1998. The purpose of LEP is to measure the electron density and temperature profile in the ionosphere. LEP consists of the Langmuir probe(LP) and the Electron temperature Probe(ETP) which are widely used for the measurement of the ionospheric plazma environment . We discuss the development of the Langmuir and Electron Probe which will be onboard the KSR-III and some test results in a simulated space plasma environment with the plasma chamber at the ISAS in Japan. These measurements could contribute to the basic study of ionospheric environment which also can be compared with other reference models such as IRI and PIM.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.7
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• pp.137-143
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• 2002

This paper concerns the spin-stabilization for the second stage of KSR-III(Korea Sounding Rocket-III). The error sources in the second stage are defined, and then the effect on attitude error of KSR-III is analyzed quantitatively and qualitatively. Based on the analysis, some conditions for optimal spinning frequency and optimal steady-spinning duration are suggested. Among several solutions, an optimal value can be determined in the point of minimum impact-point error. An approach to a sub-optimal solution is also suggested. Application to the KSR-III shows that a proper spinning frequency and a steady-spin duration to give the smallest impact-point error can be effectively determined.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.1
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• pp.106-111
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• 2004

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.2
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• pp.95-102
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• 2004

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.2
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• pp.103-109
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• 2004

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.2
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• pp.110-118
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• 2004

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.10
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• pp.83-92
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• 2004

This paper concerns servo filter design for KSR-III gimbal engine actuation system. When the actuator system is attached to engine mount frame, unexpected resonant modes in low frequency can occur and make the control system unstable. In order to prevent the resonance in the actuation system, a proper lowpass servo filter is designed. Based on the dynamic test data including the resonant effect, the shape of the servo filter is determined, and then the corresponding parameters are optimally designed. The best solution is finally selected via dynamic tests including the servo filter.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.2
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• pp.80-88
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• 2003

This paper describes the development of an ozone detector and an electron probe as parts of scientific payloads for sounding rockets such as the KSR-III. Each detector consists of sensor parts and electronic parts. We successfully carried out the calibration tests with developed ozone detector and the space plasma simulation chamber tests with electron detector. These payloads could be onboard the KSR-III and with measured data, it is expected and temperature profile over the Korean Peninsular.

• Journal of the Korean Society of Propulsion Engineers
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• v.6 no.3
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• pp.19-27
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• 2002

The sequence of the propellant supply for ignition of a liquid rocket engine combustor is very important in the reliable and safe operation of the engine. The ignition sequence of KSR-III main engine was briefly described and the measuring parameters and their reliability determining ignition sequence were examined in this paper. The filling time of the engine propellant manifolds and the valve open/close time were reviewed to obtain the exact and reliable time of the propellant supply to the combustor. The combustion characteristics of the engine at starting were discussed at different supply lead of propellant. Finally, the hot firing test results with cyclogram determined by measuring parameters were presented.