• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 2003년도 추계학술발표대회 논문집
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• pp.119-122
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• 2003

This report describes the procedure of detailed design and structural test for the composite flexure which is a part of the hingeless hub system. First, stacking sequence design for composite flexure was done, and structural analysis by using NASTRAN was made to verify structural stability and safety. Using FPS installed at KIMM, composite flexure was laid up and cured using a autoclave. Before rotor ground test, the basic structural tests such as a bench test, tensile strength test and shear strength test, for flexure, were accomplished. Through replacing existing metal hub part with new fabricated composite flexure, improvement of aeroelastic stability and weight reduction were achieved. This result will be applied to composite rotor system design fur helicopter.

• 한국항공운항학회:학술대회논문집
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• 한국항공운항학회 2007년 춘계학술대회 논문집
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• pp.85-88
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• 2007

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2013년도 춘계학술대회 논문집
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• pp.347-352
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• 2013

Seoul National University Flap (SNUF) blade is a small-scaled rotor blade incorporating a small trailing-edge flap control surface driven by piezoelectric actuators at higher harmonics for vibration attenuation. Initially, the blade was designed using two-dimensional cross-section analysis and a geometrically exact one-dimensional beam analysis, and material configuration was finalized. Flap deflection angle of ${\pm}45^{\circ}$ was established as the criterion for better vibration reduction performance based on an earlier simulation. Flap linkage mechanism design is carried out and static bench tests are conducted to verify the flap actuation mechanism performance. Different versions of test beds are developed and tested with the flap and chosen APA 200M piezoelectric actuators. Through significant improvements, a maximum deflection of ${\pm}3.7^{\circ}$ was achieved. High frequency experiments are conducted to evaluate the performance and transfer function of the test bed is determined experimentally. As the static tests are almost completed, rotor power required for testing the blade in whirl tower (centrifugal environment) is calculated and further preparations are under way.

• 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.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2006년 제4회 한국유체공학학술대회 논문집
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• pp.37-40
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• 2006

Wind tunnel testings to develope tilt-rotor Smart Unmanned Aerial Vehicle (SUAV) were intensively performed. Small wind tunnel was used to find and evaluate design parameters and to fix general layout of configuration. The application of large tunnel with 40% scaled model is to collect performance and stability related aerodynamic data. During large scale model test wind tunnel is used as a tool to compare Flaperon types, to improve lift characteristics by using different height vortex generators and to alleviate nacelle separated flow effects on the wing.

• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 2002년도 춘계학술발표대회 논문집
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• pp.173-176
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• 2002

This paper describes the design procedure of composite parts for hingeless hub system of helicopter. These composite parts are composed of flexure and sleeve. The design of this composite flexure is an important technique in hingeless hub system since the rotor system stability and dynamic characteristics depends on this flexure characteristics. The objective of this research is to replace the existing metal hub parts with composite to improve the performance and stability. First, the coupon test of candidate composite material for hub parts was conducted. The hub parts was designed based on test results and the manufacturing possibility by using Fiber Placement System(FPS) was checked. Also the dynamic analysis and stress analysis of composite hub parts was conducted. Through this research, we will find out the possibility of replacing existing metal hub parts with composite.

• 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.

• 한국항공우주학회지
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• 제38권9호
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• pp.943-954
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• 2010

본 연구에 적용된 터빈은 반경류형이며, 동익의 외경은 108 mm이다. 터빈은 1.4-4.1%의 낮은 부분분사율에서 작동하므로 익형은 축류형으로 설계되었으며 3단으로 구성되었다. 터빈에서 부분분사율과 팁간극 및 노즐유동각의 변화에 따른 성능의 변화를 측정하였다. 또한 터빈의 단수를 변경하면서 각 단수에서 발생되는 출력의 차이에 대한 측정이 이루어졌다. 본 연구의 터빈은 다양한 작동조건에서 운전되므로 넓은 작동범위에 따른 비교를 위하여 회전수를 변경하면서 탈설계 영역에서의 성능 평가가 이루어졌다. 뿐만 아니라 다양한 작동조건에 합당한 시스템의 평가를 위하여 총비오크가 얻어졌다. 아울러 소형터빈의 설계 및 성능예측을 위하여 유동해석을 수행하였으며 얻어진 예측의 결과는 실험으로 얻어진 결과와 잘 일치하였다.