• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.8
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• pp.687-693
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• 2018

In this paper, we studied on the thermal design of the active antenna system for stable performance considering thermal reliability. The active antenna has high performance and heat flux elements in T/R modules. Thermal heating of elements in T/R modules has to be dissipated effectively and the antenna has to be operated over the range of suggested temperature by the thermal design. T/R modules of high heat flux in the active antenna can be dissipated effectively by liquid cooling. In this study, we studied on the thermal design including the liquid cooling system to optimize the thermal performance of the active antenna. And the thermal design was verified by numerical analysis.

• Proceedings of the SAREK Conference
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• 2009.06a
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• pp.1385-1390
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• 2009

In this study the purpose is development of passive cooling system for telecommunication cabinet used by latent heat material. This cooling system is not required for electronic power. It was tested for the performance of the telecommunication combined latent heat material with $48^{\circ}C$ of phase changed temperature and heat pipe. At $45^{\circ}C$ of outside temperature, when heater power was 1,000 W and 1,500 W, the inside temperature of the cabinet was $55^{\circ}C$ and $62^{\circ}C$. This system was showed better performance than the other systems.

• Journal of the Korea Institute of Military Science and Technology
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• v.22 no.2
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• pp.249-254
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• 2019

A Digital Transmitter/Receiver Module(DTRM), which is an essential part in active phased-array radar systems, generates a high heat density, and needs to be properly cooled for stable operation. A tile-type DTRM that is a stacking structure of multi-layer components was modeled with simplification and heat dissipation characteristics of the DTRM model were studied using computational fluid dynamics(CFD) simulations. Most of the heat was dissipated by the heat conduction through the cold plate, but the heat transfer by the forced convection on top of the DTRM also was found to play an important role in the thermal management. Under the given conjugated heat transfer environment, the DTRM was confirmed to secure a stable operating temperature range.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.1
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• pp.56-64
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• 2010

A system design has been conducted of the liquid rocket engine for Korean launch vehicle (KSLV-II, Korea Space Launch Vehicle II). The present turbopump-fed liquid rocket engine of vacuum thrust 76 ton and vacuum specific impulse 297 sec adopts gas generator cycle. The combustion pressure of the regeneratively cooled combustor is 60 bar. The propellant is LOx/kerosene. The engine is started by pyrostarter and the combustor is ignited by TEA (TriEthylAluminium). The engine system performance and the subsystems performance requirements are given through energy balance analysis. The combustion pressure, specific impulse and the engine mass are analyzed to be reasonable comparing with the published data. The startup analysis method which will be used in the future has been validated against the turbopump-gas generator coupled test. The tuning method for performance variation of the engine which is not actively controled has been prepared by mode analysis and performance deviation analysis.