• Current Industrial and Technological Trends in Aerospace
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• v.6 no.1
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• pp.35-43
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• 2008

Technical trends of propulsion system for small aircraft are investigated. Currently, most small aircraft are equipped with piston engine, turboprop and turbofan engines, and the technology development is going continuously. For piston engines, new diesel engines are arising besides gasoline engine. The diesel engines use relatively low-cost and easy to get fuel(Jet A), so the demand for small aircraft is getting increased, and new engines with high reliability and efficiency are being developed. For gas turbine engines, application of small turbofan is getting increased for newly arising VLJ market and the engine demand will be rapidly increased in the future. On the other hand, some electric propulsions without fossil fuels are being developed without high cost of fuel and environmental effects. In the future, propulsion system for small aircraft will be developed having enhancement of performance and efficiency with higher reliability and safety.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2002.04a
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• pp.33-34
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• 2002

성능해석 프로그램은 가스터빈 엔진의 개발단계에서는 성능시험의 대체로 개발 비용의 절감과 실제 시험이 어려운 영역의 성능해석을 통해 보다 광범위한 운용 범위의 성능을 파악할 수 있도록 하며 엔진의 운용단계에서는 엔진 상태를 실시간으로 파악하여 엔진 상태에 따른 적절한 정비를 통해 수명 연장과 운용비용 절감의 효과를 가져온다. 이러한 성능해석 프로그램의 중요성은 선진국에서는 이미 70년대부터 부각되어 그 연구가 활발히 진행되어져 왔으며 아날로그 컴퓨터, 하이브리드 컴퓨터, 디지털 컴퓨터 등 다양한 형태로 개발되어 왔다. 최근에는 퍼스날 컴퓨터의 발달로 보다 정밀한 해석이 가능한 프로그램들이 많이 개발되고 있으며 보다 사용자에게 친숙한 GUI(Graphical User Interface) 방식이나 Object-Oriented 방식의 프로그램 개발에 관한 연구가 활발히 이루어지고 있다. 또한 보다 빠르고 복잡한 성능해석이 가능한 프로그램 개발을 위해 MATLAB, MATRIX-x 등 공학용 소프트웨어를 이용한 프로그램들이 개발되고 있다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.389-392
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• 2011

In this study, the engine performance data was extracted and analyzed through the flight test of Smart UAV which is tilt rotor aircraft. The flight test was conducted for the transition flight regime where the tilt angle of prop-rotor varies from 90 degree to 0 degree and vice versa. The engine performance data such as engine power and specific fuel consumption gathered from flight tests were compared well with the results of engine performance analysis program.

• Aerospace Engineering and Technology
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• v.10 no.1
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• pp.175-182
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• 2011

Optimized design was performed for a subsonic aircraft wing. The subsonic aircraft is dual turbo-prop and carrying less than 100 passengers. The cruise speed is Mach 0.6. The design was performed by two stages. The first stage is to decide the height of horizontal tail by analyzing the directional stability with Vorstab and then, the optimized wing configuration was selected with Piano, a optimizer commercially available. Fluent, a commercial CFD software was utilized to predict the aerodynamic performance of the aircraft. Drag of the aircraft was minimized with maintaining constant lift for cruise. The optimization reduced 10 counts from the initial wing configuration.

• Journal of Aerospace System Engineering
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• v.9 no.4
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• pp.62-66
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• 2015

During the conceptual design of turboprop aircraft, the power effect driven from rotating propeller is typically obtained from empirical data. In the present paper, propeller power effect was obtained by using unsteady three-dimensional Navier-Stokes solver with $k-{\omega}$ turbulence model for the accurate prediction of turboprop aircraft performance. In order to simulate the relative motion between propeller and fuselage, unsteady sliding mesh method was used. During simulation, three flow conditions such as climb, cruise and descending flight were selected considering the flight envelop of the real turboprop aircraft. For the correction of aerodynamic coefficients, the thrust effect of engine exhaust gas was included based on the engine manufacturer's data. Using the computational results, the correction table for the aerodynamic coefficient of turboprop aircraft was suggested for the performance analysis of turboprop aircraft.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1995.05a
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• pp.71-81
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• 1995

The Propulsion System Integration can be defined as the optimization technology of combining the propulsion system components with the airframe to achieve the overall aircraft misson performance goals. The disposition of propulsion system components on engine compartment enveloped by front fuselage and fire bulkhead is very restricted because of the interference with nose L/G and engine mountig strut. The design of components depends on the traditional technical data base. The engine satisfying a customer's ROC was selected among worldwide existing engines by the comparision studies of performance analysis with enigine installed effect, future growth potential, ILS, and application to aircrafts, etc. The ground test of the propulsion system integration was performed in the test cell and on the aircraft to assure the function of the components. The flight test was performed to confirm complying the performance requirements.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.606-608
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• 2017

The computational fluid analysis was carried out to investigate structural stability of exhaust duct for turboprop engine. In order to calculate the thrust and shear force acting on the flight condition of the aircraft, the flow in the exhaust duct and the flow in the direction of the exhaust duct flange were analyzed by Fluent software to obtain thrust, shear force and bending moment. As a result of the analysis, it was confirmed that the allowable loads set idle engine manual were not exceeded.

• Journal of the Korean Society of Propulsion Engineers
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• v.3 no.4
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• pp.93-103
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• 1999

The steady-state performance analysis program for turboprop engine which was used for a small, middle industrial aircraft and a basic trainer aircraft was developed and linear Gas Path Analysis method was applied to Engine Health Monitoring for Turboprop engine. This program was compared with TURBOMARCH program which is well known with performance and power according to flight Mach No. at the standard atmospheric condition to prove a steady-state performance analysis program. From the result, inlet, exit temperature and pressure of each component had error within 3% and especially power according to flight Mach No. had error within 2.4% so that this program could be assured. To make sure if linear Gas Path Analysis is reasonable four cases were selected. The first is the case that fouling is occurred in compressor only. The second is the case that fouling is occurred in compressor and erosion is occurred in turbine. The third is the case that erosion is occurred in both compressor and turbine and power turbine at the same time. Finally, the case that fouling and erosion are occurred in compressor, compressor turbine and power turbine was selected. Different parameters were selected impartially among the independent parameters so that the effect of measurement parameter selection was observed. From the result, the more measurement parameters the smaller RMS error and even though the number of measurement parameters was the same, the RMS error was obtained differently according to which measurement parameters were selected. The case using eight instrument parameters of case IV-4 had small error comparably and was economic and it was important to select optimal number of measurement and optimal measurement parameters.

• Journal of the Korean Society of Propulsion Engineers
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• v.4 no.4
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• pp.87-97
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• 2000

A steady state performance simulation and diagnostics program for the turboprop engine (PT6A-62), which is the power plant of the first developed military basic trainer KT-1 in Republic of Korea, was developed. The developed steady state performance analysis program was evaluated with the performance data provided by the engine manufacturer and with analysis results of GASTURB program, which is well known for the performance simulation of gas turbines. Performance parameters were discussed to evaluate validity of the developed program at various cases such as altitude, flight velocity and part load variation. GPA(Gas Pass Analysis) allows engine performance deterioration to be identified at the module level in terms of reduction in component efficiencies and changes in mass flow. In order to find optimal instrument set to detect the physical faults such as fouling, erosion and corrosion, a gas path analysis approach is utilized. This study was performed in two cases for selection of optimal measurement parameters. One case was considered with the effect of instrument number by changing independent parameter number. The other case was performed with selection of independent parameter set. According to the analysis results, the optimal measurement parameters selected were eight dependent variables such as shaft horsepower, fuel flow rate, compressor exit pressure and temperature, compressor turbine inlet pressure and temperature and power turbine inlet pressure and temperature.

• Journal of Aerospace System Engineering
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• v.7 no.3
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• pp.15-19
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• 2013

Tail wing is important to designing of civil aircrafts, because it is responsible for aircraft stability and control. Tail wing has a role in aircraft control and makes aircraft fly stably without any pilot control input. Also, designing of tail wing determine trim drag force in whole aircraft. Center of gravity(CG) of aircraft travels with various effects as placement of passenger's seats, location of cargo bay, etc. In designing horizontal tail volume, aircraft CG travel has to be considered to have margin so that it should be sized to provide adequate stability and control for the airplane's entire CG range throughout the flight envelope. Finally, it is essential to have sufficient elevator control to perform stall at forward CG for all flaps down configurations. Such stalls establish the FAR stall speed which airplane take-off and landing performance. This paper deals with the process for tail wing design regarding the aircraft CG travel and results for 95-seat type turboprop aircraft.