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무베어링 헬리콥터 주 로터의 허브 파라미터 변화에 따른 로터 안정성 특성 해석
윤철용(Yun, Chul-Yong),기영중(Kee, Young-Jung),김태주(Kim, Tae-Joo),김덕관(Kim, Deog-Kwan),김승호(Kim, Seung-Ho) 한국소음진동공학회 2012 한국소음진동공학회 논문집 Vol.22 No.8
This paper describes a stability and dynamic characteristics of bearingless helicopter main rotor in hover. Baseline rotor configuration is defined and modal analysis for the configuration is taken to verify the dynamic characteristics. The kinematic pitch-lag couplings through ways of pitch link installation are analyzed to know effects on loads, frequencies and stability. The effects of pitch link attachments in spanwise direction and chordwise direction as well as pitch link inclination on thrust, power, flpa-lag-pitch mode frequencies and inplane damping are examined. Pitch link at trailing edge location in chordwise direction has influence on aeroelastic stability of the rotor. Also, the pitch link with negative inclination angle makes inplane damping increase.
윤철용(Yun, Chul-Yong),기영중(Kee, Young-Jung),김태주(Kim, Tae-Joo),김덕관(Kim, Deog-Kwan),김승호(Kim, Seung-Ho) 한국소음진동공학회 2012 한국소음진동공학회 논문집 Vol.22 No.4
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.
헬리콥터 로터 블레이드의 기본 물리량 및 비회전 동특성 시험
윤철용(Chul Yong Yun),김태주(Taejoo Kim),기영중(Young-Jung Kee),심헌수(Heon-Su Sim),김승호(Seung-Ho Kim) 한국소음진동공학회 2013 한국소음진동공학회 학술대회논문집 Vol.2013 No.10
This paper describes basic properties tests and non-rotating dynamic test for rotor blade, flexbeam, and torque tube of which bearingless rotor in helicopter consists. A basic properties test are bending and twist test to find the flap stiffness, lag stiffness, and twist stiffness of specimens. The purpose of dynamic test is to find natural frequencies and modes in non-rotating state. The test results are used to update the analysis model. The updated analysis results using rotorcraft comprehensive code match the tests quite well. The updated model input based on the tests will be utilized to analysis the conditions of rotating whirl tower test before the whirl test and will be compared with the whirl tower test results.
무베어링 헬리콥터 주 로터의 허브 파라미터 변화에 따른 로터 안정성 특성 해석
윤철용(Chul Yong Yun),기영중(Young-Jung Kee),김태주(Taejoo Kim),김덕관(Deog-Kwan Kim),김승호(Seung-Ho Kim) 한국소음진동공학회 2012 한국소음진동공학회 학술대회논문집 Vol.2012 No.4
This paper describes a stability and dynamic characteristics of bearingless helicopter main rotor in hover. Baseline rotor configuration is defined and modal analysis for the configuration is taken to verify the dynamic characteristics. The kinematic pitch-lag couplings through ways of pitch link installation are analyzed to know effects on loads, frequencies and stability. The effects of pitch link attachments in spanwise direction and chordwise direction as well as pitch link inclination on thrust, power, flpa-lag-pitch mode frequencies and inplane damping are examined. Pitch link at trailing edge location in chordwise direction has influence on aeroelastic stability of the rotor. Also, the pitch link with negative inclination angle makes inplane damping increase.
기영중(Young-Jung Kee),김태주(Tae-Joo Kim),윤철용(Chul-Yong Yun),김승호(Seung-Ho Kim),한정호(Jeongho Han) 대한기계학회 2013 대한기계학회 춘추학술대회 Vol.2013 No.12
KARI(Korea Aerospace Research Institute) has been developing a 11.5m diameter four bladed bearingless main rotor system, and this rotor system can be used for 7,000lb class helicopter. Flexbeam and torque tube can be considered as key structural components, and the effect hinge offset can be realized by large elastic deformation and twist of flexbeam induced by pitch control motion. This paper describes the manufacturing process of flexbeam and torque tube, and composite lay-up sequences and information were presented. Also, the basic properties tests were performed to find the flap, lag and torsion stiffness of flexbeam and torque tube, and the test results were presented
기영중(Kee, Young-Jung),윤철용(Yun, Chul-Yong),김덕관(Kim, Doeg-Kwan),김승호(Kim, Seung-Ho) 한국소음진동공학회 2012 한국소음진동공학회 논문집 Vol.22 No.2
Recently, KARI(Korea Aerospace Research Institute) has been developing a modern 11.5 m diameter four bladed bearingless main rotor system, and this rotor system can be used for 7,000 lb class helicopter. Flexbeam and torque tube can be considered as key structural components, and large elastic twist of flexbeam induced by pitch control motion of torque tube can influence the nonlinear aeroelastic behavior. In this paper, the dynamic characteristic analysis results of bearingless rotor system were presented. In order to construct a input model and validate the analysis procedures, calculated results using the comprehensive helicopter analysis program CAMRAD II were compared with the measured natural frequencies and lag damping data from small-scale wind tunnel test. Next, the analysis model was extended to a full-scale model, and the dynamic analysis results were presented.