• Journal of the Korean Society of Propulsion Engineers
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• v.19 no.3
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• pp.65-72
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• 2015

In present study, a supersonic inlet for dual mode ramjets or RBCC/TBCC engines with a wide range of flight Mach numbers is designed. A conical variable inlet configuration is chosen for the inlet design. Geometric relations with angles of compression cones and conical shock waves are used for the design of the inlet configuration. The performance of the supersonic inlet is confirmed by the numerical analysis. The capture area ratio is maintained around 100% from Mach 3 to 8 conditions.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.207-210
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• 2008

In this study, one type of ramjet intake were designed for the flight condition of Mach number 4 and numerical analysis was performed. In order to widen the flight envelope range (Mach number $2{\sim}6$), movable intake concept was applied. The central body was designed so that the capture area ratio which is one of most important factors of ramjet intake design could be adjusted. And various types of cowl and movable insert part of shell were designed in order to control throat area which could increase total pressure recovery. The numerical results showed that the designed ramjet intake could be applied in various flights Mach number.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.9
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• pp.714-719
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• 2013

A turboprop aircraft for this study is required to operate at icing condition in order that it performs its given mission. So an air intake system of the turboprop aircraft should be designed and verified not only to provide the maximum possible total pressure at engine inlet at normal flight condition, but also to include an inertial separator which protects Foreign Object Debris (FOD) like ice or snow at icing condition from entering into the engine inlet screen which can cause or lead an catastrophic engine failure like engine flame-out or severe damage. So an air intake assembly incorporating a variable geometry inertial separator has been designed and then CFD/structural analysis for the assembly was performed to see its design results. Then 35% scaled model of the air intake assembly was manufactured and wind tunnel test was done. This paper describes the detailed design results for the aerodynamic design, analysis and wind tunnel testing during the development process of the air intake assembly.

• Journal of the Korean Society of Propulsion Engineers
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• v.26 no.5
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• pp.63-73
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• 2022

Investigation on operation of the test apparatus for the M4 semi-freejet tests with a full-scale vehicle model was carried out utilizing domestic facilities. An integrated design of the experimental apparatus and the vehicle model was obtained through iterative computational fluid dynamics (CFD) analysis. The test results showed that the M4 nozzle of the apparatus was fully expanded to provide required test conditions. It was also found that the intake of the vehicle model successfully started, and the corresponding shadowgraph images were recorded during the test. A variable nozzle of the model was set to adjust the back pressure of the model combustor, and wall-static pressures were measured to obtain the pressure distribution at the main locations of the model. The flame of torch ignitors and pilot fuel ignition were observed in a flame-holder of the combustor.

• Proceedings of the Korean Society of Tribologists and Lubrication Engineers Conference
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• 1990.06a
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• pp.32-44
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• 1990

유압 Vane pump는 carming, rotor, vane에 의하여 둘러싸인 공간체적이 rotor의 회전과 함께 변화하면서 pump 작용을 한다. 즉 공간체적이 증가하는 동안은 유압이 저압으로 되어 흡입구에서 유압유를 흡입하고 vane의 존환점 (vane이 가장 많이 출한 점)을 지나면 공간용적이 감소하여 유압류는 고압으로 될 수 있도록 되어있다. 이때 vane은 관성력과 점성력 그리고 유압류의 압력에 의한 힘으로 vane 선단이 캠링의 내면에 밀착되어 회전하도록 되어있다. 유압 vane pump 베인 선단부의 윤활문제와 관련된 지금까지의 연구로서는 Hibi 등에 의한 압력평형형 베인모터, W.D Beck, T.C Edwards에 의한 베인형 콤푸렛셔 Ujiie 등에 의한 베인형 진공펌프, Ueno 등에 의한 가변용량형 베인펌프의 마찰특성에 관한 연구 및 베인 이간 현상에 관한 실험적 연구가 있다. 그러나 이와 같은 연구들의 베인과 캠링 슬라이딩 부분에 관한 취급들은 베인선단 슬라이딩 부분에 가해지는 변동가중이 불명확했기 때문데, 단순히 슬라이딩 부분의 면적이 작다는 이유로 단성유체 윤활상태일 것이라는 확정을 하였을 뿐, 실제적으로 어느 정도의 윤활 상태를 파악하기 위하여 회전하는 vane의 가학적인 거동을 확실하게 규명하고자 함이 본 연구의 목적이다.

• Aerospace Engineering and Technology
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• v.4 no.2
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• pp.27-35
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• 2005

In this study, a performance analysis code was developed for the off-design performance analysis of air turbo ramjet(ATR) engine, and the analyses were performed for the pre-designed ATR engine at several operating points in the envelope. Variable intake and thrust nozzle were assumed to cover the wide envelope. Mathematical models for each components were developed to calculate their off-design performance. Simple design formulas were introduced for some components to explore the performance variation versus the design parameters. As a result, the pre-defined engine couldn't cover the entire mission profile. And it was also found that the effect of the pre-cooler was not very great, especially in the region of low Mach number.

• Journal of the Korean Society of Propulsion Engineers
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• v.10 no.2
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• pp.115-128
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• 2006

A technical analysis of current scramjet and combined-cycle engine is presented. Substantial research has been pursued to characterize the operation mechanism of scramjet propulsion, especially in the areas of flame stabilization and system integration, dramatically over the years in support of both military and space access application. Major technology that had significant impact on the maturation of scramjet propulsion technology are dual combustion ramjet, dual mode ramjet, and combined cycle engine to cover a typical wide rage of flight, up to flight Mach number 10. Notable are the fundamental and practical techniques, for instance, scram propulsion itself, thermal relaxation and protection using endothermic fuel and/or CSiC composit materials, and design/manufacture of movable intake and nozzle, to realize high speed propulsion system in near future.