• 항공우주시스템공학회지
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• 제4권3호
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• pp.34-38
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• 2010

ACN(Aircraft Classification Number) is allocated by marketing group during early stage of aircraft design phase and is a critical parameter to decide whether the designed aircraft can be landed or not in a certain airport. The loading on the main landing gear wheels, selection of main landing gear tire and estimation of ACNs for flexible and rigid pavements were done for the proposed medium-class aircraft. The estimated ACN values are compared with the similar class aircraft. And PCN(Pavement Classification Number) values of airport in Korea are surmmarized. Results showed that the currently proposed medium-class aircraft can land any airport in Korea.

• 한국유체기계학회 논문집
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• 제15권5호
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• pp.27-31
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• 2012

Turbine inlet temperature is steadily increasing to achieve high specific thrust and efficiency of gas turbine engines. Turbine cooling technology is essential to increase turbine inlet temperature. For this study, a small or medium sized aircraft engine of 10,000 lbf class with the turbine inlet temperature of $1,400^{\circ}C$, the engine overall pressure ratio of 32.2, and the bypass ratio of 5 was set as the baseline model and its performance analysis was performed at the design point. The engine has the performance of 10,013 lbf thrust and the specific fuel consumption of 0.362 lbm/hr/lbf. The thrust and the specific fuel consumption of the baseline model were compared with those of similar class engines. Based on these results, the turbine design requirements were assigned. In addition, the parametric analysis of the engine, related to aerodynamic and cooling design of the high pressure turbine, was performed. Based on the baseline model engine, the influence of turbine inlet temperature, cooling flow ratio, and high pressure turbine efficiency variations on the engine performance was analyzed.

• 항공우주시스템공학회지
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• 제9권3호
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• pp.1-7
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• 2015

In this study, the design of compound smart materials hydraulic pump that can be applied to a small-medium size UAV having a limited space envelope and weight has been conducted. Compound Smart Material Pump(CSMP) proposed in this paper is composed of a pressurize pump and a flow pump for supplying the high pressure and fluid displacement to overcome the disadvantages of the piezoelectric actuator which has a small strain. Though this compound smart material pump has been designed as small size and lightweight as possible, it can sequentially supply the sufficient large flow rate and pressure required for the brake operation. For the design of CSMP, about 2,700 kg (6,000 lb) class fixed wing manned aircraft was selected. Based on the established requirements, the design of the CSMP have been done by strength, vibration, and fluid flow analysis.

• 한국항공우주학회지
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• 제31권6호
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• pp.102-109
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• 2003

전투기에 장착되는 엔진의 수는 필요한 추력과 가용엔진에 의해 대부분 결정되어 왔으나, 엔진 기술의 발달로 임무성능-체계분석-경제성 등이 중요한 고려요소가 되었다. 베트남전과 걸프전의 실전사례 분석 결과 안전성과 취약성은 쌍발기가, 피격율은 단발기가 다소 우수한 것으로 평가되었다. F404-GE-400과 F-125 엔진을 장착한 초음속 경공격기를 설계하여, 엔진 수에 따른 비교연구를 수행하였다. 쌍발기 형상이 최대이륙중량 8%, Flyaway Cost 26%, LCC 13% 정도 컸으며, 단발기 형상이 기동-저속성능과 RM&S 성능이 다소 우수하였으나 큰 차이는 없었다. 전투기의 획득시 저급(Low) 전투기는 단발엔진을, 중급이상(Med.+)의 전투기는 쌍발엔진을 적용하는 것이 체계분석-경제성-운용개념 등을 고려한 여러 측면에서 유리할 것으로 판단된다.