• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.339-342
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• 2007

The power control system of Smart UAV is similar to the propeller pitch governing concept of turboprop aircraft. The pilot inputs the engine power directly and the pitch governor controls the propeller pitch to maintain the propeller RPM. The manual back-up system of PW206C engine is used for the engine power control of Smart UAV. Engine performance estimation program is used to predict the control range of power lever arm(PLA) angle according to the variation of flight altitude and speed. These data provide a guide for the engine control in manual mode operation.

• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.4
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• pp.42-47
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• 2008

The power control system of Smart UAV is similar to the propeller pitch governing concept of turboprop aircraft. The pilot adjusts the engine power directly and the pitch governor controls the propeller pitch to maintain the propeller rotational speed. The electronic engine controller(EEC) of PW206C engine developed for helicopter is not fit for the power control concept of Smart UAV, and therefore the manual back-up system of PW206C engine is used for the engine power control of Smart UAV. Engine performance estimation program is used to predict the control range of power lever angle(PLA) according to the variation of engine output shaft speed, flight altitude and flight speed. These data provide a guide for the PLA control in manual mode operation.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.1
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• pp.104-109
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• 2005

The aircraft gas turbine engines with the Electronic Engine Controls(EEC) had been developed to save fuel and enhance their performance in the early days, and had employed the health monitoring function in the Full Authority Digital Engine Controls(FADEC) to improve their reliability. This has led to an increasing demand for the certification technology of these controls. The design and certification issues of power supply, aircraft supplied data, failure modes, software verification/validation, and lightning requirements need to be addressed. This paper presents the design considerations and the certification techniques applied to the electronic engine controls. And it is believed that this paper will be basis to establish a requirement in Korean Airworthiness Standard.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2002.05a
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• pp.991-995
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• 2002

The engine booming noise heard inside a vehicle's cabin is due to the engine vibration that's transferred to the chassis in the form of structural vibration and it often causes discomfort to the passenger. In an effort to seek out the possible relation between the engine booming noise and the engine vibration of a vehicle, a position on the engine mount was selected and the vibration transmission through the position was attenuated to observe the corresponding change in the noise level inside the cabin. A system consisting of an actuator and a hybrid controller that has both the feed-forward and feed-back capabilities was developed in order to carry out the experiment.

• Proceedings of the KIPE Conference
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• 2010.07a
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• pp.528-529
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• 2010

VVA(Variable Valve Actuation) 기술은 엔진의 흡기 밸브 작동 모드를 가변하여, 엔진의 연비와 성능을 향상시키는 차세대 엔진 기술이다. 흡기캠에 의해 밸브가 직접 작동되는 일반 엔진과 달리 VVA 엔진은 흡기캠, VVA기구, 모터, 제어기 등에 의해 밸브 작동 모드가 정밀하게 제어되므로, 엔진에서 발생되는 손실을 줄여 연비가 크게 향상되고 엔진의 최고 성능이 향상된다. 또한 VVA 엔진을 장착한 차량은 차량의 발진 응답성이 향상되고, 배기가스 배출량을 줄일 수 있어 친환경 저연비 차량을 실현하는데 핵심 차량부품기술이다. 본 논문에서는 이와 같은 VVA 기구의 적용을 위한 DC모터 및 제어기를 개발하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.3
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• pp.249-257
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• 2010

Full authority digital engine control systems for gas turbine engines are replacing conventional mechanical control units rapidly. However, setting up design processes of controllers for high performance helicopter engines are not well known because of the complexity of the total system. This paper presents a high fidelity helicopter and engine simulation for control system design and analysis. Using this environment, a feedforward schedule was set up for a utility helicopter. The total engine simulation with the new controller showed better or equal performance compared to the total engine simulation with the pre-existing controller.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.19 no.7
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• pp.1-8
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• 2018

This paper describes new communication methods for transmitting torque commands between the vehicle controller that determines the amount of power generation in a range-extended electric vehicle and the engine controller that performs it. Generally, vehicles use CAN communication, but in this case, the hardware and software of the existing engine controller must be modified. For this reason, it is not easy to apply CAN communication to small and medium sized automotive reorganize companies. Therefore, this research presents a pin-pin communication method for applying the existing mass produced engine controller to range-extended electric vehicles. The pin-pin communication method converts the driver's demand torque control map inside an mass produced engine controller into a virtual accelerator opening position according to the target speed and target torque of the engine, and converts this to a voltage signal for the existing mass produced engine controller to recognize it. The virtual accelerator opening positions are mounted in the form of a control map in the vehicle controller through the reverse conversion process in an offline environment and are determined by the engine generating power requirements and engine optimal operating point algorithm. These algorithms and signal conversion circuits for engine torque transmission have been mounted on the vehicle controller to conduct the virtual accelerator opening position conversion process according to the engine target torque and to establish the virtual accelerator voltage signal using the signal converter.

• Proceedings of the Korean Society of Computer Information Conference
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• 2023.07a
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• pp.105-106
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• 2023

소형제트엔진은 주로 연구, 실험, 교육 등의 목적으로 사용되고 있다. 이러한 소형제트엔진은 고도가 높고 고속으로 비행하는 드론에 추력 발생 장치로서의 중요한 역할을 수행할 수 있다. 그러나 엔진의 실질적인 활용을 위해서는 기존의 유선으로 구성된 컨트롤러를 무선으로 제어할 수 있는 방식으로 재구성하는 것이 필요하다. 이 중에서도 연료펌프의 무선제어시스템이 우선적으로 개발되어야만 다른 부분에 대한 무선제어개발이 가능해질 것이다. 본 논문에서는 소형 제트 엔진의 연료 펌프를 무선으로 제어할 수 있는 방식을 적용한 임베디드 시스템의 구성과 방식에 대해 제안하고 있다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.8-13
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• 2011

본 연구에서는 대형 로켓엔진시스템의 시동 시 안정적인 유량공급을 위한 제어기 설계가 이루어졌다. 펌프, 오리피스, 제어밸브, 파이프, 인젝터 및 재생 냉각채널과 같은 엔진시스템 구성품들에 대한 동특성 모델링을 수행하였고 유량공급 제어가 가능한 밸브의 구동신호를 조절 가능한 PID 제어기를 설계하였다. 시동 시 안정적인 유량공급을 위하여 실험을 통해 얻은 밸브의 적정 개도율을 적용시켰으며, 이를 기준으로 하여 제어밸브의 작동신호를 조절하여 유량비를 제어하였다. 시뮬레이션 한 결과 제어기를 통해 시동 시 정상추력까지 유량공급을 제어 하는 방법이 적절함을 확인하였다.

• Journal of the Korean Society of Propulsion Engineers
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• v.2 no.2
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• pp.38-46
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• 1998

A theoretical and an empirical application of the speed control of a single-shaft turbo-jet engine was done using an observer for Linear Quadratic Gausian(LQG) that is one of the robust control fields. Based on a general controller design with state feedback, a controller with output feedback was designed to find out a sufficient condition in finding an Asymptotic Stability After defining of the total system through the modeling of a real turbo-jet engine, a Tracking Control was carried out. Furthermore, a saturation of the control input was theoretically considered in the output feedback controller to simulate more similar real condition.