• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.364-367
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• 2011

The development of the DCS thrust unit during the attitude control thruster of the launch vehicle and guided missile is introduced. The DCS thrust unit using solid propellants based on a two-axis control is designed and through the thermo-structural and flow analysis is designed in detail. The performance of the thrust unit based on the detail design is demonstrated through a combustion test.

• Journal of the Korean Society of Marine Environment & Safety
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• v.24 no.4
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• pp.482-488
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• 2018

Generally, after stern tube bearing shows a significant increase in local load due to propeller load, which increases the potential adverse effects of bearing failure. To prevent this, research on regarding shaft alignment has been carried out with a focus on reducing the relative slope between the shaft and support bearing(s) under quasi-static conditions. However, for a more detailed evaluation of a shafting system, it is necessary to consider dynamic conditions. In this context, the results revealed that eccentric propeller force under transient conditions such as a rapid rudder turn at NCR, lead to fluid-induced instability and imbalanced vibration in the stern tube. In addition, compared with NCR condition, it has been confirmed that eccentric propeller forces given a rapid rudder starboard turn can lift a shaft from the stern tube bearing in the stern tube, contributes to load relief for the stern tube bearing.

• Journal of Korea Ship Safrty Technology Authority
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• v.16
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• pp.26-37
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• 2004

선박 추진축계의 진동은 크랭크축, 추력축 등의 이상마멸을 초래할 뿐 아니라 과도하면 선체진동을 유발시키기도 한다. 이러한 추진축계의 진동중에서 가장 빈번히 문제가 되는 것이 비틀림 진동이므로 축계의 초기설계 단계부터 이에 대한 신중한 검토가 필요하다 .

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.2
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• pp.165-171
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• 2016

The attitude control, station keeping and wheel off-loading at GEO-KOMPSAT-2 are realized by thrusters firings. Thrusters 1, 2 and 3 are mounted on the same axis as the solar array, which generates the plume disturbance largely. Therefore the effect of plume disturbance should be analyzed from satellite design phase. In this paper, we described the calculation method of plume disturbance and analyzed the plume disturbance of thruster 1,2 and 3 using GEO-KOMPSAT-2 initial configuration.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1108-1111
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• 2017

The nozzle exit shape is scarfed according to the external shape of missile when the nozzle axis should be canted from missile axis due to missile system application. There is inevitable thrust loss for the scarfed nozzle comparing to non-scarfed nozzle. The numerical analysis is necessary to calculate the thrust loss in design process, and ground tests of rocket motor were performed to verify the calculation results. From the comparison of non-scarfed nozzle and scarfed nozzle experiment results, the thrust loss from calculation was about 16.6% and that from experiments was about 15.0%.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.3
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• pp.97-108
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• 2018

It is definitely important to measure thrust during ground test when developing air-breathing engine, and in case of air-breathing engine, gross thrust should be calculated considering not only the measured thrust but also the force induced by the air flow of engine intake. Also, side thrust like yaw and pitch should be measured and analyzed using multi-component thrust measurement system. Engine performance was accurately evaluated by calculating the gross thrust of air breathing engine precisely which is analyzed from below serial procedure: labyrinth seal isolation, 1-axis gross thrust calculation, develop multi-component thrust measurement system, and side thrust analysis.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.3
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• pp.205-212
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• 2021

In this study, two types of thrust stand modeling were proposed for the design of a thrust stand using flexure. Type A model generate combined load for tangential (thrust) and axial compressive load (self weight). And type B generate combined load for tangential and axial tensile load. The research was done by comparing the influence of the load between the models through a 1D calculation and computational analysis. The 1D calculated value and the computational analysis value were compared for a total of 10 sections and the results were confirmed to be very similar. In order to prove the validity of the analysis results, the equivalent stress was confirmed from the computational analysis of the flexure, and the production of the Type B model was selected from the evaluation of the yield condition (Von-Mises Yield Criterion).

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.04a
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• pp.15-15
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• 2000

제트 베인에 의한 추력 방향 제어 장치는 롤 운동 제어를 가능하게 하고, 큰 선회 각도를 얻을 수 있는 장점이 있으나, 기계 장치가 비교적 복잡하고, 제트 베인의 열적, 구조적 문제를 해결하여야 한다. 복잡한 기계 장치는 유동 해석의 측면에서 고려해 볼 때 격자 형성을 어렵게 만들어 유동장 해석을 통한 성능예측을 어렵게 만든다. 구조물의 응력해석을 위하여 제트 베인 표면에서의 정압력과 더불어 마찰력도 고려하여야 하는데, 정확한 마찰력 계산을 위해서는 난류 모델링이 필수적이고, 그에 따라 벽면 근처에서 격자를 밀접시키는 것이 요구된다. 본 연구에서는 상용 유동해석 소프트웨어인 Fluent를 사용하여 제트 베인이 장착된 추력 방향 제어 장치의 3차원 난류 유동장 계산을 수행하였다. 피치, 요 운동의 경우와 롤 운동의 경우로 구분하여 계산하였으며, 최대 받음각을 $25^{\cire}$ 로 하여 제트 베인의 받음각에 따라 회전축에 작용하는 힘과 모멘트를 계산하였다. 본 연구의 결과는 향후 개발될 제트 베인이 장착된 추력 방향 제어 장치의 개념설계 단계에 필요한 기본자료로서 신뢰도를 높이는데 도움이 되리라 판단된다.

• Aerospace Engineering and Technology
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• v.8 no.2
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• pp.122-126
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• 2009

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. To verify the flow rate of the gas charging system and to prepare a nitrogen gas charging scenario, the development of a gas charging simulator for RCS(Reaction Control System) is required. This paper describes the orifice design, development, and test of the gas charging simulator for RCS of KSLV-I.

• Aerospace Engineering and Technology
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• v.12 no.1
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• pp.189-199
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• 2013

This paper summarizes results of second stage attitude control of KSLV-I third flight test. The results show that three axes attitude control at coasting phases of KSLV-I was successfully accomplished by the reaction control system, and pitch and yaw attitude control at thrusting phase where second stage kick motor burns was also normally accomplished by using the thrust vector control system. It is verified that the second stage controller performed successfully for all flight phases regardless of some disturbances due to mass center offset, slag effects, and residual thrust of kick motor. These results may provide an important basis in enhancing domestic technology level of attitude control of launch vehicle.