• 한국소음진동공학회논문집
• /
• 제22권4호
• /
• pp.352-357
• /
• 2012

The ground resonance instability of a helicopter with bearingless main rotor hub were investigated. The ground resonance instability is caused by an interaction between the blade lag motion and hub inplane motion. This instability occurs when the helicopter is on the ground and is important for soft-inplane rotors where the rotating lag mode frequency is less than the rotor rotational speed. For the analysis, the bearingless rotor was composed of blades, flexbeam, torque tube, damper, shear restrainer, and pitch links. The fuselage was modeled as a mass-damper-spring system having natural frequencies in roll and pitch motions. The rotor-fuselage coupling equations are derived in non-rotating frame to consider the rotor and fuselage equations in the same frame. The ground resonance instabilities for three cases where are without lead-lag damper and fuselage damping, with lead-lag damper and without fuselage damping, and finally with lead-lag damper and fuselage damping. There is no ground resonance instability in the only rotor-fuselage configuration with lead-lag damper and fuselage damping.

• International Journal of Aeronautical and Space Sciences
• /
• 제7권1호
• /
• pp.54-64
• /
• 2006

To augment weakly damped lag mode stability of a hingeless helicopter rotor blade in hover, piezoelectric shunt with a resistor and an inductor circuits for passive damping has been studied. A shunted piezoceramics bonded to a flexure of rotor blade converts mechanical strain energy to electrical charge energy which is dissipated through the resistor in the R-L series shunt circuit. Because the fundamental lag mode frequency of a soft-in-plane hingeless helicopter rotor blade is generally about 0.7/rev, the design frequency of the blade system with flexure sets to be so. Experimentally, the measured lag mode frequency is 0.7227/rev under the short circuit condition. Therefore the suppression mode of this passive damping vibration absorber is adjusted to 0.7227/rev. As a result of damping enhancement using passive control, the passive damper which consists of a piezoelectric material and shunt circuits has a stabilizing effect on inherently weakly damped lag mode of the rotor blades, at the optimum tuning and resistor condition.

• 한국소음진동공학회:학술대회논문집
• /
• 한국소음진동공학회 2010년도 춘계학술대회 논문집
• /
• pp.632-633
• /
• 2010

• Journal of Electrical Engineering and Technology
• /
• 제10권2호
• /
• pp.487-495
• /
• 2015

This paper proposes a new robust decentralized power oscillation dampers (POD) design of doubly-fed induction generator (DFIG) wind turbine for damping of low frequency electromechanical oscillations in an interconnected power system. The POD structure is based on the practical $2^{nd}$-order lead/lag compensator with single input. Without exact mathematical model, the inverse output multiplicative perturbation is applied to represent system uncertainties such as system parameters variation, various loading conditions etc. The parameters optimization of decentralized PODs is carried out so that the stabilizing performance and robust stability margin against system uncertainties are guaranteed. The improved firefly algorithm is applied to tune the optimal POD parameters automatically. Simulation study in two-area four-machine interconnected system shows that the proposed robust POD is much superior to the conventional POD in terms of stabilizing effect and robustness.

• Journal of Electrical Engineering and Technology
• /
• 제5권2호
• /
• pp.197-208
• /
• 2010

Unified power flow controller (UPFC) is the most reliable device in the FACTS concept. It has the ability to adjust all three control parameters effective in power flow and voltage stability. In this paper, a linearized model of a power system installed with a UPFC has been presented. UPFC has four control loops that by adding an extra signal to one of them, increases dynamic stability and load angle oscillations are damped. In this paper, after open loop eigenvalue (electro mechanical mode) calculations, state-space equations have been used to design damping controller and it has been considered to influence active and reactive power flow durations as the input of damping controller, in addition to the common speed duration of synchronous generators as input damper signal. To increase stability, further Lead-Lag and LQR controllers, a novel on-line adaptive controller has been used analytically to identify power system parameters. Closed-loop calculations of the electro mechanical mode verify the improvement of system pole placement after controller designing. Suitable operation of adaptive controller to decrease rotor speed oscillations against input mechanical torque disturbances is confirmed by the simulation results.

• 한국항공우주학회지
• /
• 제37권2호
• /
• pp.181-186
• /
• 2009

본 연구의 목적은 주로터 블레이드와 장애물 충돌 시 실제 파괴형상과 유사한 시뮬레이션을 통해 발생되는 하중을 구하고, 이것을 이용하여 허브 및 변속장치의 안전성을 검토함으로써 승무원의 안전성을 확보하는 것이다. 헬리콥터의 실제 운용 시에 주로터 복합재 블레이드 바깥쪽 10% 지점에 직경 203mm의 강체실린더가 충돌할 경우에도 주로터주축은 파괴가 발생하지 않아야 하고 변속장치가 탑승공간으로 침투하는 위험한 변위가 발생하지 않아야 한다. 강체와 블레이드 충돌 시 주로터의 주축과 변속장치의 영향성을 확인하기 위하여 탄소성 손상 재질을 사용하여 복합재 블레이드와 나무(강체실린더의 경우는 강체)의 해석모델을 구성하였으며, 파괴진행과정을 실제와 유사하게 구현하기 위해 여러 개의 접촉면을 생성하여 충돌해석을 수행하였고, 구형베어링 및 리드래그댐퍼에 전달되는 하중을 구하였다. 또한, 블레이드 회전속도 및 피치각도의 변화가 전달하중에 미치는 영향을 검토하였다.