• Transactions of the Korean Society of Mechanical Engineers B
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• v.37 no.9
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• pp.863-871
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• 2013

Flow characteristics of velocity-control trim in a valve is investigated numerically with high pressure drop. A basic trim widely used for a valve in domestic powerplants is selected and designed for a baseline of velocity-control trim. The numerical analysis is focused on flow rate and cavitation with the basic trim. For a condition of high-pressure drop, pressure drop between inlet and outlet and fluid temperature are selected to be 18.1 MPa and $160^{\circ}C$, respectively, which are typical ones considering operating conditions adopted in powerplants. With this baseline model and condition, design changes are made for improvement of flow rate and cavitation phenomenon. For re-design, trim is divided into three zones in radial direction and design parameters of flow area, stage, and flow direction are considered in each zone. With these combined parameters applied to each zone, 4 models with design changes are proposed and their flow rates and cavitation areas are investigated. From comparison with those in the baseline model of a basic trim, proposed models show better performance in both flow rate and cavitation.

• Journal of the Korean Society of Marine Environment & Safety
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• v.28 no.6
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• pp.1070-1077
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• 2022

The International Maritime Organization has recently strengthened its marine environment regulations. The energy efficiency index has long been an important indicator of ship design, and now, energy efficiency is being enforced for existing ships as well as new ships. To increase the energy efficiency of existing ships, methods such as retrofitting the bow bulb, selecting an optimized trim during ship operation, and installing an energy saving device have been applied. In this study, the ship resistance was numerically simulated using computational fluid dynamics (CFD) under various bow and stern trim conditions. In addition, the bulb was redesigned to further improve the resistance performance under the selected trim conditions. When the improved bulb was applied, the effective horse power increased by approximately 5%. It is, however, necessary to verify whether the redesigned bulb can reduce ship resistance in waves.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.7
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• pp.497-505
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• 2022

Performance and hub vibratory load analyses for a lift-offset coaxial rotor are conducted using a rotorcraft comprehensive analysis code, CAMRAD II. The lift-offset coaxial rotor is trimmed to match the total rotor thrust(lift-offset coaxial rotor's thrust) or the individual rotor thrust(upper and lower rotor thrusts, respectively) in this study. The individual rotor's lift and torque, and effective rotor lift to drag ratio for the total rotor are investigated for various advance ratios and lift-offset values. The two result sets with different trim methods are similar to each other and they are correlated well with the wind-tunnel test results. Therefore, the present study using CAMRAD II validates successfully the aeromechanics modeling and analysis techniques for the lift-offset coaxial rotor.

• Journal of the Korea Institute of Military Science and Technology
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• v.2 no.1
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• pp.121-131
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• 1999

Automatic Rudder Trim System(ARTS) is a device to reduce the pilot's work load for rudder trimming greatly required in varying abruptly aircraft's engine power. This paper represents a technical analysis and a design of control law of the ARTS. The control law of the ARTS is designed based on the analysis of aircraft's characteristics, system's requirements, and limitations. The control law is comprised of open loop control using the rudder trim map for a specific aircraft and closed loop control to compensate the error of the open loop control system. flight test results show that the ARTS can reduce pilot's work load for rudder trimming dramatically and can compensate the aircraft's transient yaw motion.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.1
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• pp.42-48
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• 2003

To get a periodic trim solution from Level II helicopter flight dynamic equations, DAE based PPT A (partial Periodic Trimming Algorithm) has been proposed. Iterative update of state variables from PPT A can cause a numerical instability in DAE solver which needs compatible initial conditions. By simply adjusting the order of DAE solver a periodic trim can be obtained with good accuracy. Application for CBM (Common Baseline Model) helicopter showed the same trim result as harmonic balance method and the effective elimination of unrealistic initial responses at the start of flight simulation.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.192-195
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• 2008

A sensor fault detection method for small turbo shaft engine considering multiple trim conditions is proposed. This engine is used in a helicopter. Firstly, under multiple trim conditions, we derive the linearized models from a nonlinear model which includes engine, rotor and feedback control loop. As a fault detection method, we adopt the Kalman filter based method. To keep continuity of estimates between the changes of trim conditions, we reconfigure the initial values of state variables at trim changes. We detect the faults with two steps that when the first filter does not alarm the faults for some sensors, the second filter is runned for other sensor. Via some simulations we show that the proposed method works well under multiple trim conditions.

• Proceeding of EDISON Challenge
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• 2016.11a
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• pp.35-43
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• 2016

본 연구에서는 EDISON의 해석자를 활용하여 선박의 최적 운항 자세 도출과 같은 실용적 문제 해석뿐 만 아니라 자유 수면 및 대칭 경계 조건이 수직한 몰수 익형 주위 유동에 미치는 영향을 분석하는 학술적 연구를 수행하였다. 선박의 자세에 따른 저항 변화를 분석한 결과 0.5m 선수 트림에서 선체 저항이 가장 작은 것으로 나타났으며, 이는 유동 가속에 의한 선수 어깨부의 낮은 압력 및 선미부에서의 압력 회복에 의한 것이다. 반면, 1.0m 선미 트림에서 선체 저항이 가장 큰 것으로 나타났는데, 평형 상태보다 선미부의 압력 회복이 약하기 때문이다. 또한 자유 수면과 대칭 경계 조건이 날개 성능에 미치는 영향을 분석한 결과, 비현실적 대칭경계 조건으로 인해 날개 양력이 13%~16% 크게 나타났으므로 대칭경계조건을 사용할 경우에는 이러한 오차를 감안해야 한다.

• Proceeding of EDISON Challenge
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• 2016.03a
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• pp.588-592
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• 2016

선박의 최적 운항 자세를 찾기 위해 자유 수면을 포함한 저항 해석을 수행할 경우 많은 격자를 이용한 비정상 해석으로 인해 계산 시간이 오래 소요되는 단점이 있다. 본 연구에서는 이를 개선하여 이중 모형을 이용한 정상 해석을 통해 보다 효율적으로 선박의 최적 운항 자세를 도출하는 방법을 연구하였다. KCS를 대상선으로 선정하여 설계속도(24knots)와 저속(15knots)인 경우에 대하여 평형 상태 및 선수/선미 트림 상태에서 이중 모형 수치해석을 수행하고 기존의 연구결과와 비교하였다. 그 결과 자유수면 유무와 속도에 상관없이 선체 자세에 따른 저항 값은 동일한 경향을 갖는 것을 확인하였다. 하지만 저속일 경우 트림조건에 따른 저항의 변화의 폭에서 차이를 보였으며, 이는 압력저항에 기인한 것이다. 따라서 이중 모형을 이용한 저항 해석은 압력저항의 변동이 큰 경우에는 적용되기 어렵다는 한계점이 있다. 하지만 마찰 저항이 주요한 경우에 적용되어 계산효율을 획기적으로 높일 수 있으며, 정성적인 경향을 제시할 수 있는 타당한 방법이라 사료된다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.8
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• pp.657-664
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• 2013

The flight loads analysis was carried out on the aircraft with high aspect ratio flexible wings by using commercial software MSC/NASTRAN. The aerodynamic model for flight loads analysis was corrected, compared with results of the wind tunnel test. And in-house program was developed for pre and post works. In-house program enabling management of much data automatically consists of three modules: 'Construction of the mass distributed model', 'Selection of critical load cases', 'Generation of external loads for structural design'. By utilizing these techniques and programs, the procedure of flight loads analysis was established for effective development of an aircraft.

• Journal of the Society of Naval Architects of Korea
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• v.50 no.2
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• pp.88-94
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• 2013

The primary objective of the current work is to obviously analyze regarding effects of trim conditions of a ship on resistance performance using model test and CFD. Model tests at a towing tank are conducted to investigate resistance for trim conditions at the given same displacement. Measured resistance shows small but distinct differences according to trim conditions. However, these differences are difficult to be clarified by measured physical quantities and wave pattern analysis from model tests. CFD is employed for the assessment of resistance performance according to trim conditions. The flow computation is conducted considering free surface and dynamic trim using a commercial CFD code (STAR-CCM+). The initiative of the present work is to systematically demonstrate pressure resistance acting on each region of divided finite zones of ship surface along the length and draught direction of surface when pressure distribution on the ship is interpreted. Also, a standard to assess the pressure resistance applied on the divided regions of a ship is established.