• Proceedings of the Korean Society of Marine Engineers Conference
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• 2005.11a
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• pp.148-149
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• 2005

In this study, among the precision decline main causes of sounding, I suggested the characteristics of sounding data acquired by echo sounder with increasing of turbidity For this, I acquired sounding data by inputting turbidity inducer artificially in artificial water tank. And then achieved regression analysis. Conclusion are as following : Sounding Capabilities can be divided into three ranges according to the turbidity : normal range, critical range and the range where data can not be obtained by an echo sounder

• Journal of the Korean Society of Surveying, Geodesy, Photogrammetry and Cartography
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• v.23 no.2
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• pp.197-203
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• 2005

Dredging and reclaiming on coast, harbor construction etc. of when construct, the interest about efficiency and accuracy of sounding by measurement condition very rise. However, there are only a few studies on the accuracy improvement concerning water depth sounding condition. In this study, among the precision decline main causes of sounding, 1 suggested the characteristics of sounding data acquired by echo sounder with increasing of turbidity and the critical turbidity range under a given transducer frequency. For this, I acquired sounding data by inputting turbidity inducer artificially in artificial water tank. And then achieved regression analysis. Conclusion are as following Sounding Capabilities can be divided into three ranges according to the turbidity . normal range, critical range and the range where data can not be obtained by an echo sounder. When the turbidity exceeds $217\~259$ NTU which was considered as critical range, depth sounding was impossible.

• Journal of information and communication convergence engineering
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• v.13 no.2
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• pp.69-73
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• 2015

We focus on a sounding signal design for single-input single-output orthogonal frequency division multiplexing (SISO-OFDM) systems. We show that the frequency spectrum of an optimum sounding signal has a constant magnitude across the frequency band for the cases with or without Doppler effects. Simulation results show that the designed optimum sounding signal outperforms random sounding signals and that the performance of a maximal-length shift register sequence is indistinguishable from that of the optimum sounding signal.

• Proceedings of the Korean Society of Surveying, Geodesy, Photogrammetry, and Cartography Conference
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• 2010.04a
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• pp.143-144
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• 2010

Nowadays, sounding is done by either manually on a boat or through the use of survey. These existing measures are considered to be very inefficient. they are not only greatly limited by environmental circumstances but also requires much of time, expenses, and manpower. Therefore, there emerges a greater need for a new sounding system which will allow us to measure the depth of water, less affected by financial and environmental restrictions, within a short period of time. This is a base study for developing an automatic sounding system, which will enhance the advantages of manned sounding and unmanned sounding, raise the effectiveness and economic efficiency, and acquire more precise data.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.144-149
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• 2011

A study to determine the optimal jet conditions for maximizing altitude of the sounding rocket is conducted. The behavior of a simplified linear momentum equation including aerodynamic drag is investigated. The analytic solutions are obtained and compared with numerical solutions. It is shown that there are the optimal jet conditions for maximizing altitude of a sounding rocket according to the rocket mass ratio.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.466-475
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• 2011

This paper presents development status of sounding rockets containing scientific payload and telemetry at home and abroad. The case of outside, United States is launching sounding rockets in 20-30 flights per year by the NASA program which offers to carry payload weights of 38-680 kg and altitude of 88-1500 km. Europe is launching in 4-5 flights per year by the ESA program. The case of Korean sounding rockets was successful with the launch of three times(KSR-I,II,III), but Korea lags far behind the advanced countries in the field of development technologies for space launch vehicle. We expect that our scientific and industrial technologies will be improved through the research and development of sounding rockets. In this study we proposed necessity and future direction of development in domestic sounding rockets.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.3
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• pp.70-79
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• 2011

This paper presents development status of sounding rockets containing scientific payload and telemetry at home and abroad. The case of outside, United States is launching sounding rockets in 20-30 flights per year by the NASA program which offers to carry payload weights of 38-680 kg and altitude of 88-1500 km. Europe is launching in 4-5 flights per year by the ESA program. The case of Korean sounding rockets was successful with the launch of three times(KSR-I,II,III), but Korea lags far behind the advanced countries in the field of development technologies for space launch vehicle. We expect that our scientific and industrial technologies will be improved through the research and development of sounding rockets. In this study we proposed necessity and future direction of development in domestic sounding rockets.

• International Journal of Aeronautical and Space Sciences
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• v.16 no.4
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• pp.529-536
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• 2015

Various R&D programs for rocket-based combined cycle (RBCC) engines have progressed worldwide for the space development and the defense applications. As a way toward indigenous domestic RBCC program, a preliminary design of flight test conditions was studied in this study for a sub-scale RBCC engine using a sounding rocket. Launch and flight profiles were calculated for several booster options and compared with that of HyShot II program. The result shows that the Korea Sounding Rocket-II (KSR-II) is a proper candidate to perform the flight test available in Korea. The recommend flight test conditions with KSR-II are Mach 6.0 with a test vehicle of 230 kg and Mach 7.4 with 50 kg. Present study will soon be followed by a design of sub-scale RBCC for a flight test using a sounding rocket.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.356-359
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• 2011

In this study, applicable to Sounding Rocket about the development of high-performance propellant was studied. Sounding Rocket requires generally multistage rocket system for atmospheric research. This study describes the development of two types solid propellant compositions which are based on HTPB/AP for the two-stage rocket. CEA code of NASA and internal ballistic analysis were used for confirming the theoretical performance of designed propellants. The strand burner and JANNAF tensile test was used to measure ballistic and mechanical properties of designed propellants. Finally, static fired test of standard motors was performed to prove the possibility of development.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.207-210
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• 2009

This paper presents development status of sounding rockets containing scientific payload and telemetry at home and abroad. The case of outside, united state is launching sounding rockets in 20-30 flight per year by the NASA program which offer to carry payload weights of 38-680 kg and altitude of 88-1,500 km. Europe is launching in 4-5 flight per year by the ESA program. Japanese sounding rockets are being applied an Antarctic exploration and flight verification in 1-2 flight per year. The case of korean sounding rockets was successful with the launch of three times(KSR-I,II,III), but our development techniques for space launch vehicle lag behind other industries. Therefore, Launch vehicle development should enable with the support and acquirement of advanced technology.