• 한국소음진동공학회논문집
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• 제15권4호
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• pp.421-428
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• 2005

This paper described operation and vibration characteristics of a 'tail-fan' anti-torque performance test system. KARI (Korea Aerospace Research Institute) developed a 'tail-fan' anti-torque system of a helicopter and a performance test-rig to test the performance of the tail-fan. The performance test-rig consists of driving, supporting and rotating parts. In the process of the performance test, firstly, operation test of the test-rig were carried out to verify design specifications. Secondly, natural frequencies of fan blade and test-rig were measured respectively. Lastly, to find the operation rotating speed for the performance test, vibration test were carried out using accelerometers on tail gear box. The performance test conditions of the tail-fan to avoid a resonance were found from the fan-plot and vibration test results. The tail-fan performance tests were well done safely.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2003년도 추계학술대회논문집
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• pp.310-315
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• 2003

This paper described that rotating test and fatigue test of a small-scale hingeless hub system with composite rectangular blades. Generally Rotating stability and fatigue test technique is one of Key-technology on test and evaluation for helicopter rotor system Rotating test of hingeless rotor system was achieved by means of rotor vibration characteristic and aeroelastic stability test GSRTS, equipped with hydraulic actuator and 6-component rotating balance was used to test hingeless rotor system especially for an observation of blade motion including flawing, lagging and feathering. Rotating test was done in hover and forward flight condition. Small-scaled blade fatigue test condition was determined by blade load analysis with the reference table of composite materials(S-N curve). Fatigue test bench was developed for the estimation of blade fatigue life, and tested its characteristic.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2006년도 춘계학술대회논문집
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• pp.680-685
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• 2006

This paper describes the aeroelastic stability test of the small-scaled 'Next-Generation Blade(NRSB)' with NRSH (Next-Generation Hub System) and HCTH hingeless hub system in hover and forward flight conditions. Excitation tests of rotor system installed in GSRTS(General Small-scale Rotor Test System) at KARI(Korea Aerospace Research Institute) were tarried out to get lead-lag damping ratio of blades with flexures as hub flexure. MBA(Moving Block Analysis) technique was used for the estimation of lead-lag damping ratio. First, NRSB-1F blades with HCTH hub system, Then NRSB-1F with NRSH hub system were tested. Second, NRSB-2F blades with NRSH hub system were tested. Tests were done on the ground and in the wind tunnel according to the test conditions of hover and forward flight, respectively. Non-rotating natural frequencies, non-rotating damping ratios and rotating natural frequencies were showed similar level fir each cases. Estimated damping ratios of NRSB-1F, NRSB-2F with HCTH and NRSH were above 0.5%, and damping ratio increased by collective pitch angle increasement. Furthermore damping ratios of NRSB-2F were higher than damping ratios of NRSB-1F in high pitch angle. It was confirmed that the blade design for noise reduction would give observable improvement in aeroelastic stability compared to paddle blade and NRSB-1F design.

• 한국소음진동공학회논문집
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• 제16권8호
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• pp.848-856
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• 2006

This paper describes the aeroelastic stability test of the small-scaled 'Next-generation Blade(NRSB)' with NRSH (next-generation hub system) and HCTH hingeless hub system in hover and forward flight conditions. Excitation tests of rotor system installed in GSRTS (general small-scale rotor test system) at KARI (Korea Aerospace Research Institute) were carried out to get lead-lag damping ratio of blades with flexures as hub flexure. MBA(moving block analysis) technique was used for the estimation of lead-lag damping ratio. First, NRSB-1F blades with HCTH hub system, then NRSB- 1F with NRSH hub system were tested. Second, NRSB-2F blades with NRSH hub system were tested. Tests were done on the ground and in the wind tunnel according to the test conditions of hover and forward flight, respectively. Non-rotating natural frequencies, non-rotating damping ratios and rotating natural frequencies were showed similar level for each cases. Estimated damping ratios of NRSB-1F, NRSB-2F with HCTH and NRSH were above 0.5%, and damping ratio increased by collective pitch angle increasement. Furthermore damping ratios of NRSB-2F were higher than damping ratios of NRSB-1F in high Pitch angle. It was confirmed that the blade design for noise reduction would give observable improvement in aeroelastic stability compared to paddle blade and NRSB-1F design.

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

• 한국항공운항학회지
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• 제9권1호
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• pp.59-69
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• 2001

복합재로 된 회전날개깃을 상자보로 모델링하고 수동/능동 감쇠를 주기 위해 ACL(Active Constrained Damping Layer)을 상하양면에 부착하고 복합변위이론에 기초한 유한요소방법을 이용하여 구조해석을 수행하였다. 이 이론은 ACL내의 복합재와 점탄성층 그리고 압전층의 전단변형효과를 정확하게 모델링하는데 효과적이다. Hankel 의 특이값을 이용해 축차모델을 유도하였으며 축차모델과 측정된 출력에 기초한 LQG 제어기를 설계하였다. 그러나 LQG 제어기는 공칭 운전속도에서는 좋은 성능을 보여주었으나 운전속도가 변하는 상황에 대해서는 강인안정성을 보여주지 못했다. 이 LQG제어기의 강인안정성을 개선하기 위하여 루프전달회복을 통한 강인한 제어기를 설계하였다. 수치 예를 통해 제시된 제어기가 회전날개깃의 공기역학적인 안정성을 개선하는데 효과적이며 동체모드와 연계된 리드-래그 모드감쇠를 증가시켜 회전날개깃의 진동을 효과적으로 억제하는 것을 보였다.

• Composites Research
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• 제17권3호
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• pp.29-37
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• 2004

본 연구에서는 대변형 보이론을 이용하여 정지 비행 시 복합재 무베어링 로우터 시스템의 공력탄성학적 안정성 해석을 수행하였다. 무베어링 로우터 시스템은 유연보, 토오크 튜브, 피치 링크, 그리고 메인 블레이드로 구성된다. 유연보, 토오크 튜브, 그리고 메인 블레이드를 각각 플랩 굽힘, 리드-래그 굽힘, 비틀림 그리고 축 방향 변형의 탄성 운동을 하는 보로 가정하고, 1차원 보 요소로 모델링을 하였다. 또한, 유연보를 복합재료 적층판으로 구성된 비틀림에 유연한 직사각형 단면을 갖는 보로 모델링 하여, 1차원 보 해석에 필요한 유효 단면 상수를 얻었다. 외력으로는 2차원 준-정상 공기력 모델을 적용하였으며, 보의 유한 요소 지배방정식은 헤밀턴 원리(Hamilton's principle)를 이용하여 얻었다. 공력 탄성학적 안정성 해석을 수행하기 위하여 p-k 방법을 이용하였으며, 유연보의 적층각과 적층 순서에 따른 구조적 연성이 무베어링 로우터 시스템의 공란성 안정성에 미치는 영향을 알아보았다.

• 한국항공우주학회지
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• 제39권5호
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• pp.442-450
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• 2011

회전 블레이드의 모션을 측정하기 위해 스테레오 패턴 인식 (stereo pattern recognition, SPR) 기법을 적용한 측정 시스템을 구성하고 실험을 수행하였다. 시스템 요구사항을 만족시키는 스테레오 카메라를 확보하여 SPR 기반의 측정 시스템을 준비하였다. 시스템의 측정불확도를 계산하기 위한 일련의 실험을 통해, 본 SPR 시스템이 2m~4.2m의 측정 거리에서 0.2mm 이내의 표준불확도를 가짐을 확인하였다. 이를 이용하여 계산한 블레이드 모션의 합성표준불확도는, 리드-래그, 플래핑, 비틀림 운동에 대해 각각 0.296mm, 0.209mm, $0.238^{\circ}$ 이었다. 본 SPR 시스템을 한국항공우주연구원의 소형로터 시험장치에 설치하고 회전속도와 콜렉티브 피치각을 각각 360rpm, 589rpm, 그리고 $0^{\circ}$, $4^{\circ}$, $6^{\circ}$로 바꾸어가며, 지상 제자리비행 조건에서 블레이드의 모션과 탄성 변형을 성공적으로 측정하였다. Higher Harmonic Control Aeroacoustic Rotor Test -II 에서 사용한 측정 시스템과의 비교를 통하여 본 시스템의 장점을 분석하였다.