• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.237-240
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• 2011

Numerical simulation was carried out to investigate the effect of pintle inflection point on the performance of the SNECMA modulatable thrust devices. Results show that the effect of inflection points in the pintle is to decrease aerodynamic load while maintaining required thrust level.

• Aerospace Engineering and Technology
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• v.7 no.2
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• pp.88-94
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• 2008

In this study, triaxial velocity is analyzed for COMS(Communication, Ocean and Meteorological Satellite) configuration, which is generated when thrusters are used to dump wheel momentum. Since COMS is designed to periodically change the thruster set in order to uniformly decrease the performance of thrusters, triaxial velocity would be different during the change of thruster set. So, the triaxial velocity generated due to the change of thruster set is optimized.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.4
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• pp.73-79
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• 2004

An experimental and computational study has been performed for investigation of the jet interaction in supersonic flow with a ramp located behind a sonic, lateral jet. The experimental techniques include schlieren, pressure taps, and Pressure Sensitive Paint. The numerical solver used in this study is AeroSoft's structured flow solver GASP Version 4.0. A Mach 4 crossflow with a pressure ratio of 532, and the 3D ramp was designed by parametric study using GASP. The results showed that the ramp located downstream of the jet decrese the nose-down pitching moment by 70% without a force loss.

• Journal of Astronomy and Space Sciences
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• v.18 no.2
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• pp.137-144
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• 2001

This paper presents the REA thrusters performance estimation results for the KOREASAT F1&F2 launched in 1995 The satellite tracking data obtained from the ground system from end of 1999 to beginning of the 2000 are used to estimate the thruster performance. The estimation algorithm is derived from the least square estimation theory and designed to estimate the velocity change induced by the on-boarded thruster firing as well as the orbit parameter. The estimation results show that the Koreasat F1 thruster are in bad thruster condition of 64% performance for REA when it fires in on-pulse mode. Here, the performance is defined by the ratio of the resulted velocity change to that of planned. But, in the case o( the Koreasat F2, it is found that the performance approximately reaches up to 100%, even after the 5 years of the mission.

• Journal of the Institute of Electronics Engineers of Korea SC
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• v.47 no.3
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• pp.19-27
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• 2010

KSLV(Korea Space Launch Vehicle)-I is designed as a launch vehicle to enter a 100 kg-class satellite to the LEO(Low-Earth Orbit). Attitude angles of the upper-stage, including roll, pitch and yaw are controlled by cold gas thruster system using nitrogen gas. The thruster for the KSLV-I is the main pneumatic valve in the RCS(Reaction Control System). In this paper, the design, function tests, and environment tests of the thruster for KSLV-I are described. The developed thrusters are experimentally evaluated and successfully passed the required qualification and acceptance tests.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.110-113
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• 2007

For the development of hydrazine decomposition catalyst, Hot-fire test to verify performance of catalyst is required. The purpose of a long-life firing test is to demonstrate the capability of a design to perform for the maximum duration or cycles of operation. This paper describes the progress of the catalyst performance test, explains the test matrix, and presents the test results.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.581-584
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• 2010

Korea Aerospace Research Institute (KARI) started preliminary research about the propulsion system for lunar orbiter and moon lander this year in order to prepare korean moon exploration plan of 2020s. The final goal of this study is to develop a prototype propulsion system for lunar exploration and to perform ground landing test using this propulsion system. In this year, preliminary design of propulsion system and 200N class monopropellant thruster have been conducted. In this paper, the trade-off study result and the design concept of the propulsion system for Korean moon exploration will be introduced and preliminary design of propulsion system will be presented.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.371-374
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• 2008

The performance of several catalysts to decompose the high test peroxide (HTP) was described in this paper. Manganese oxide, Platinum and Iridium were coated on the gamma alumina. The response time of various catalysts was measured with a 50 Newton class thruster. Ir/$Al_2O_3$ that showed the fastest response time at the thruster, failed the reaction when continuous mode test was carried out with the thruster. Pt/$Al_2O_3$ and MnO_2/Al_2O_3$ can be substitutes to decompose the HTP. In addition, for larger thruster, MnO_2/Al_2O_3$ can be a good catalyst because its cost is below 5 % of Pt/$Al_2O_3$.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.27-30
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• 2005

Hanwha Corporation succeeded in domestic development of thruster heat shield for KOMPSAT-2 propulsion subsystem partly. Thruster heat shield, one of the main components of DTM, is designed to prevent the critical radiative heat exchange between thruster and satellite during firing. To overcome the manufacturing difficulties, an electro-forming process is preferred to classical welding process. In this case, an inner diameter of a new shield will be decreased a little due to the change of manufacturing process. The interference problem between thruster nozzle and heat shield was investigated through structural analysis by KARI. Hanwha manufactured heat shield based on the analysis results. In this paper, full development process is described for design, analysis, manufacturing of heat shield.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.336-339
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• 2011

Hot-fire test facility is one of the most important infrastructure for thruster development and evaluation. During the past three years, Korea Aerospace Research Institute (KARI) and Hanwha Corporation have successfully performed the construction of hot-fire test facility for medium-scale monopellant thruster to the maximum 200N thrust level. In general, thruster hot-firing test should be performed in vacuum conditions to simulate space environment. The hot-fire test facility is divided into three subsystems, vacuum system, propellant supply system and data measurement & control system. The goal of this facility is to extend the capability from small thruster for satellite mission to medium-scale thruster for launch vehicle and lunar mission. In this paper, the progress and overview for thruster hot-fire test facility was introduced and test results were also presented.