• Journal of the Korean Society of Propulsion Engineers
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• v.6 no.2
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• pp.53-63
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• 2002

The steady-state and transient performance simulation program for a turboprop engine(PT6A-62) was developed. Specially this program included some algorithms, such as flat-rated behaviors in performance and limit control algorithms to prevent the compressor surge and the compressor-turbine inlet limit temperature overshoot. In order to minimize analysis errors, on interpolation method in component characteristics using matching errors and specific heat and specific heat ratio, which are functions of temperatures were used. The developed steady state performance analysis program can handle various conditions such as altitude, bleed extraction, inlet temperature and pressure and part throttle, and the transient performance analysis program incorporated a general mode for transient simulation and a control mode for prevention of the compressor surge and the turbine inlet limit temperature overshoot.

• Aerospace Engineering and Technology
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• v.4 no.2
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• pp.142-152
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• 2005

There are two definite objects for developing the startup transient of liquid rocket engine. One is to achieve the repeatability of startup to ensure higher reliability, and the other is to reduce the time of the startup transient. Typically in the initial phase of engine development as we are currently opposing, it is hard to estimate engine startup time due to the lack of experiences. In this work, a startup transient analysis tool was developed with the introduction of the mathematical model for each component of pump-fed liquid rocket engine system. Startup transient was investigated for a 25 ton class gas generator cycle engine to find necessary time for reaching steady state from startup and this enabled to reveal dynamic characteristics of the engine.

• Journal of the Korean Society of Propulsion Engineers
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• v.11 no.3
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• pp.20-28
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• 2007

The easiest way to see the phenomena of compressor surge is to show the static and dynamic operation characteristic on the map. Its operation zone will be restricted by the surge limit and, static and transient process must have some margin for it. Effect of rotor moment of inertia, air/gas volumes and heat transfer are factors to cause the transition from the static line. In case a large volume such as heat exchanger exists in the system it will exert a substantial influence to dynamic characteristics. In the present paper, influence of air volume bled from the compressor exit on transient process is investigated with an example of an auxiliary power unit micro-turbine engine. Turbine mass, pressure ratio, rotation speed, power and moment are calculated based on mass and work conservation. Result from the present study can give guidance to design the control system. A computer program is developed to calculate the dynamic process using the MathCAD commercial software.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.40 no.3
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• pp.327-336
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• 2016

Manufacturers of aircraft engines have introduced computer-aided manufacturing (CAM) software to operate and control computerized numerical control (CNC) machine tools. However, the generation of a CAM model is a time consuming and error-prone task since machining procedure and operational details are manually defined. For the automatic generation of a CAM model, feature recognition techniques have been widely studied. However, their recognition coverage is limited so that complex shapes such as a jet engine cannot be fully developed. This study presents a novel approach to quickly generate a CAM model from a CAD model using shape search techniques. Once an operator sets a machining operation as a reference operation, the same shapes as the shapes referenced by the operation are searched. The reference operation is copied to the positions of the searched shapes. The proposed method was verified through experiments with a jet engine compressor case.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.3
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• pp.88-94
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• 2004

The KSR-III rocket is a liquid propellant sounding rocket and thrust vector control actuators and cold gas thrusters are used to control pitch and yaw, roll attitude respectively during thrusting phase. In this paper, the structure of designed attitude controller and gain scheduling, results of stability analysis for KSR-III rocket are presented. The attitude controller is implemented with flight software in the domestically developed INS and successfully performed its function in the flight test. The flight data are coincident with simulation results.

• Transactions of the Korean Society of Automotive Engineers
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• v.5 no.5
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• pp.86-96
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• 1997

In this paper, engine-CVT consolidated control algorithm was developed. Engine -CVT control strategy suggested uses throttle control based on power difference and CVT ratio control based in CVT ratio map. Simulation results showed that the larger the rate of CVT ratio, the better the engine performance in the optimal operation line. Also, it was found that the engine performance where the magnitude of the acceleration changes abruptly depends on the magnitude of the rate of CVT ratio. Comparing the results of CVT control only without engine control, the engine-CVT control algorithm suggested in this work showed better performance demonstrating that the consolidated control algorithm should be required for the engine optimal operation.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2001.11a
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• pp.213-218
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• 2001

A magnetorheological(MR) engine mount for a passenger vehicle and its vibration control performance is experimentally evaluated. A mixed-mode model for the MR engine is derived by incorporating Herschel-Bulkely model of the MR fluid. After analyzing the field-dependent damping force, a appropriate size of the MR engine mount is manufactured. The field-dependent is displacement transmissibility of the engine mount is evaluated in the frequency domain at various excitation levels. In addition, time-dependant damping force is experimentally investigated by changing the excitation amplitude.

• Transactions of the Korean Society for Noise and Vibration Engineering
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• v.19 no.7
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• pp.679-684
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• 2009

Low frequency exhaust noise of marine diesel engine is one of the most important noise sources in vessels. However, conventional absorptive silencers are ineffective to control exhaust noise because of low absorption in the low frequency range. In the paper, exhaust noise control of marine diesel engine was studied by using the hybrid silencer, which was composed of virtually divided array of concentric hole-cavity resonators and conventional absorptive silencer. A series of tests including field tests were performed to investigate the acoustic performance of the hybrid silencer. Consequently, its high performance of 5${\sim}$10 dB noise reduction in the low frequency range was confirmed and it is expected to be very helpful in reducing the exhaust noise of marine diesel engine.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2011.04a
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• pp.596-597
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• 2011

본 연구에서는 선박용 디젤엔진의 저주파수 대역 소음저감을 위해, 엔진 점화주파수 성분을 제어하고자 연장관과 헬름홀쯔 공명기, 흡음재로 구성된 소음기를 제안하고, 성능테스트를 통해 저감성능을 확인하였다. 개발된 소음기의 성능 계측결과, 저주파수 대역에서 5dB 이상의 감음성능을 확인할 수 있었다.

• Journal of the Korean Institute of Intelligent Systems
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• v.10 no.6
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• pp.597-604
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• 2000

본 연구에서는 전기자동차에 사용되는 전자식 차동 시스템의 신경망 모델을 제안한다. 차량이 곡선도로를 따라 주행할 경우 내측 바퀴와 외측 바퀴의 회전속도가 서로 달라야 진동이나 뒤틀림 없이 완만한 선회 주행을 할 수 있다. 전기자동차는 그 구조적 특성상 각각의 바퀴가 독립된 구동원을 갖는다. 이 때문에 일반 엔진 차량의 기어식 차동장치를 대신할 전자식 차동장치가 요구된다. 이러한 차동장치는 차량의 구조뿐만 아니라 차량의 주요 파라미터인 조향각 및 속도에 따라서 비선형적인 관계를 가지고 있어서 해석하기가 쉽지 않다. 따라서 이와 같은 비선형적인 관계 모델을 학습 능력을 가진 신경망에 의하여 모델링 함으로써 제어에 적용할 수 있다. 이를 실현하기 위해 제작한 전기자동차로 곡선도로를 주행하여 다양한 곡률과 주행속도에 따른 내측 외측 바퀴의 회전속도 데이터를 획득하고, 데이터의 비선형 특성을 고려한 차동 속도 제어기의 구조를 설계한다. 이 제어기에 적합한 모델은 신경망을 이용하여 실측 데이터를 학습시킴으로써 차동기능을 수행할 수 있는 제어기를 구현한다.