• 제어로봇시스템학회논문지
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• 제13권1호
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• pp.6-14
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• 2007

Modem version of supersonic jet fighter aircraft must have been guaranteed appropriate controllability and stability in HAoA(High Angle of Attack). Limit value of aircraft entering into the departure in HAoA is related to aircraft configuration design. But, the control law such as AoA and yaw-rate limiter is implemented in digital Fly-By-Wire flight control system of supersonic jet fighter to guarantee the aircraft's safety in HAoA. The HAoA flight control law have two parts, one is control law of departure prevention and the other is control law of departure recovery support. The control laws of departure prevention for advanced jet trainer consist AoA limiter, roll command limiter and rudder fader. The control laws of departure recovery support are consist yaw-rate limiter and MPO(Manual Pitch Override) mode. The guideline of pitch rocking using MPO mode is simple, but operating skill of pitch rocking is very difficult by the pilot with inexperience of departure situation. This paper addresses the design and validation of APR(Automatic Pitch Rocker) control law instead of MPO in order to automatic recovery without manual pitch rocking by the pilot. And, recovery characteristic with APR verifies by the nonlinear analysis and pilot evaluation.

• 대한토목학회논문집
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• 제39권5호
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• pp.579-586
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• 2019

지하수의 흐름의 특성에 가장 큰 영향을 미치는 투수계수 정보에 대한 탁월한 추정 방법으로 파일럿 포인트 방법(Pilot Point Method: PPM)이 있다. 이는 투수계수 정보를 비교적 풍부한 측정자료(e.g. 지하수 수두 정보)를 활용하여 얻어내는 역함수 방법의 하나이다. 본 연구는 지하수 수두 정보에 추적자 정보를 활용하여 기 개발된 민감도 분석을 활용한 파일럿 포인트 방법(D-optimality based Pilot Point Method: DBM)과 동시 검색기반 파일럿 포인트 방법(Simultaneous Search based Pilot Point Method: SSBM)의 활용성을 검증하였다. 그 결과 지하수 수두 정보만을 활용하는 것에 비해 추적자 정보를 활용하는 것이 SSBM이나 DBM 모두 투수계수를 찾는 편차를 축소시켰다. 이는 동일한 조건하에 추적자 농도 정보가 투수계수를 찾는 범위를 한정할 수 있음을 보이는 한 예라고 할 수 있다. SSBM의 경우 민감도 분석이 없어 투수계수를 찾는 절차는 감소시켰지만 DBM에 비해 투수계수를 찾는 편차가 늘어나는 경향을 보였으며 초기 투수계수의 값에 의해 투수계수를 찾는데 영향을 받음을 보였다. 본 연구를 통해 동시 검색기반 파이럿 포인트 방법으로 지하수 수두와 추적자 농도를 활용하는 것이 투수계수를 추정하는 데 적합한 것으로 사료된다.

• 제어로봇시스템학회논문지
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• 제16권9호
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• pp.905-912
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• 2010

Modern version of advanced supersonic fighter have ATCS (Automatic Thrust Control System) to maximum flight safety, fuel efficiency and mission capability the integrated advanced autopilot system such as TFS (Terrain Following System), GCAS (Ground Collision Avoidance System) and AARS (Automatic Attitude Recovery System) and etc. This paper addresses the design and verification of ATCS based on advanced supersonic trainer in HILS (Hardware In the Loop Simulator) with minimum hardware modification to reduce of development cost and maintain of system reliability. The function of ATCS is consisted of target speed hold mode in UA (Up and Away) and angle of attack hold mode in PA (Power Approach). The real-time pilot evaluation reveals that pilot workload is minimized in cruise and approach flight stage by ATCS.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1996년도 한국자동제어학술회의논문집(국내학술편); 포항공과대학교, 포항; 24-26 Oct. 1996
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• pp.609-611
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• 1996

Zero-Cross Detector makes pilot signal to control the power to CEDM(Control Element Drive Mechanism). Existing Zero-Cross Detectors has had a problem which can cause unexpected reactor trip resulted from fluctuating frequency of input signal coming from M/G Set. The existing Zero-Cross Detector can't work properly when power frequency is varying because it was designed to work under stable M/G Set operation, and produces wrong pilot signal and output voltage. In this report the Zero-Cross Detector is improved to resolve voltage fluctuating problem by using new devices such as digital noise filtering circuit, variable cycle compensator and alarm circuit. And through the performance verification it shows that new circuit is better than old one. If suggested detector is applied to plant, it is possible to use it under House Load Operation because stable voltage can be generated by new Zero-Cross Detector.

• 한국항공우주학회지
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• 제43권6호
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• pp.548-556
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• 2015

F-22, F-16 및 F-15와 같은 고성능 전투기는 전투성능의 극대화를 위해 고기동성(highly maneuverable)을 보유하고 있다. 이로 인해 고기동 시에 조종사는 고중력가속도(high gravity acceleration)에 노출되고 피로도(fatigue)의 증가로 임무효율의 저하가 발생하며, 심할 경우에는 의식상실(Gravity-induced Loss Of Consciousness, GLOC)에 직면할 수 있다. 선진 항공업체에서는 조종사가 고중력가속도에 견딜 수 있는 내성을 향상시켜 의식상실에 진입하는 것을 방지하는 다양한 기술을 항공기에 적용하고 있다. 특히, 가속도방호복(Anti-G Suit)은 GLOC으로 인한 의식 상실을 방지할 수 있을 뿐만 아니라, 전투 기동 시에 조종사의 피로를 감소시킴으로써 임무성공률을 향상시킬 수 있다. 본 논문에서는 초음속 고등훈련기 모델을 기반으로 하여 고기동 시에 중력가속도의 증가에 따라 AGS에 최적의 공기압을 제공할 수 있는 제어알고리즘을 개발하고 검증하였다. 이러한 결과는 추후에 체계개발이 진행될 한국형전투기개발사업(Korean Fighter eXperimental, KF-X)에서 핵심기술을 개발하는데 기여하리라 기대한다.

• 대한조선학회논문집
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• 제47권3호
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• pp.462-468
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• 2010

A new course keeping controller for RIB(Rigid Inflatable Boat)-type USV(Unmanned Surface Vehicle) is developed using pilot's steering pattern. A pilot's simple steering pattern is found out from various course change tests. It is used to course keeping algorithm, suitable for large course change more than 60 degrees. To validate the course keeping controller, sea trial tests are conducted. From sea trial test, new course keeping controller shows good performance with less overshoot, maximum roll angle less than $20^{\circ}$, which makes it possible that fast course changes without slip motion of USV.

• 한국자동차공학회논문집
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• 제11권6호
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• pp.37-43
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• 2003

The objective of this work is to investigate the effect of swirl, injection pressure and pilot injection on D.I. diesel combustion by using a transparent engine system. The test engine is equipped with common rail injection system to obtain high pressure and to control injection timing and duration. In this study, the combustion analysis and steady flow test were conducted to estimate the heat release rate from in-cylinder pressure. Soot distribution in diffusion flame according to swirl ratio, injection pressure and pilot injection was investigated by using LII technique. As the results, high injection pressure was found to shorten ignition delay as well as enhance peak pressure and heat release rate was greatly affected by injection timing and pilot injection. In addition, the results showed that the period of soot formation corresponded to the diffusion flame.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2001년도 ICCAS
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• pp.116.2-116
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• 2001

Korea Institute of Energy Research(KIER) has designed the 3MW pilot scale wet FGD process based on the experimental results of the bench scale FGD system which can treat 150 m3/hr of flue gases. The effects of process chemistry, packing material, and operating variables including L/G ratio, pH, scrubber pressure drop were investigated. In cooperation with Kyunggi Chemicals, the 3MW pilot scale plant was established on the industrial site at Onsan, Korea. This system has been operating since October 1999. This paper introduces an outline of the design features of the pilot plant and discusses its operational results.

• 한국연소학회지
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• 제8권3호
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• pp.31-37
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• 2003

The objective of this work is to investigate the effect of swirl, injection pressure and pilot injection on D.I.Diesel combustion by using a transparent engine system. The test engine is equipped with common rail injection system to obtain high pressure and to control injection timing and duration. In this study, the combustion analysis and steady flow test were conducted to estimate the heat release rate from in-cylinder pressure and pilot injection was investigated by using LII technique. As the results, high injection pressure was found to shorten ignition delay as well as enhance peak pressure and heat release rate was greatly affected by injection timing and pilot injection. In addition, the results showed that the period of soot formation corresponded to the diffusion flame.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2004년도 추계학술대회논문집
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• pp.546-549
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• 2004

The T-50/A-50 Golden Eagle was developed for a supersonic trainer and light combat aircraft. At the design stage, vibration control plans were established and applied. For cockpit vibration, crew comfort vibration level was defined by the requirement of MIL-A-8892. It is found that the T-50/A-50 meets the requirement of cockpit vibration from the flight test data analysis. This paper contains the results of cockpit vibration analysis using the flight test data and the results of human vibration analysis lot the pilot inside aircraft. The human vibration level of pilot is increased as dynamic pressure is increased and at the specific high dynamic pressure, the ride comfort indicates 'a little uncomfortable'. Overall analysis results show that the vibration level of T-50/A-50 cockpit is tolerable and not critical for pilot's comfort.