• 대한기계학회논문집A
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• 제31권5호
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• pp.625-634
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• 2007

KARI SUAV program was initiated to develop a Smart Unmanned Aerial Vehicle with innovative smart technologies. SUAV is a tilt rotor aircraft of which rotor system is 3-bladed, gimbaled hub type. Several existing concepts of gimbaled hub were analyzed and compared to investigate the applicability to SUAV rotor system design. From the result of these investigations, it was concluded that a new design concept of low cost and high reliability characteristics was necessary for the rotor hub development of SUAV. The design requirements of new gimbal hub concept and the design results were presented. Also, the analysis results to verify the satisfaction of design requirements of SUAV rotor system were presented.

• 한국항공우주학회지
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• 제34권1호
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• pp.8-17
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• 2006

• 한국항공운항학회지
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• 제15권3호
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• pp.33-45
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• 2007

The collision avoidance maneuver flight simulation for tilt rotor unmanned aerial vehicle was performed by time-accurate numerical integration method based on wind tunnel test data. Five representative collision avoidance maneuvers were simulated under constraints of aerodynamic stall, propulsion power, structural load, and control actuator capability. The collision avoidance performances of the maneuvers were compared by the computed collision avoidance times. The sensitivities of initial flight speed and collision zone shape on the collision avoidance time were investigated. From these results, it was found that the moderate pull-up turn maneuver defined using moderate pitch and maximum roll controls within simulation constraints is the most robust and efficient collision avoidance maneuver under the various flight speeds and collision object shapes in the tilt rotor UAV applications.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2008년도 학술대회
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• pp.166-170
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• 2008

The changing process from hovering mode to transition one is of importance to determine a stability of tilt-rotor aircraft, which is utilized in UAV(Unmaned Aerial Vehicle). The analysis on fluid flows and aerodynamic characteristics according to variation of tilting angle of rotor is essential step in development of tilt-rotor. In the present study, the computation domain is divided into the rotating and stationary regions in order to consider the rotating blades. For the convenient realization of various tilting angle as well as application of boundary condition, the whole computation region is constructed into sphere domain. The near farfield boundary condition is adopted. The airfoil used in computation is NACA 0012. The computation results for the hovering mode are validated by comparing with previously conducted experimental results. From the results, the flow fields around rotor blade and the aerodynamic characteristics in transition mode are observed. The computational result will provide the basis for development and performance evaluation of tilt-type aircraft.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2005년도 춘계 학술대회논문집
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• pp.21-24
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• 2005

Numerical analysis were made for the unsteady flow fields of the rotor system of a Tilt-Rotor aircraft in cruise mode. The Reynolds-averaged thin-layer Wavier-Stokes equations were discretized by Roe's upwind differencing scheme and integrated in time by the LU-SGS algorithm. The computational domain of the rotor system was constructed by seven multi-block Chimera grids. Comparison of pressure coefficient on the surface of the main wing and blades were made for 3cases of advance ratio(0.325, 0.350, 0.375) and thrust and power coefficients for the rotor were compared with experimental data.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2007년도 춘계학술대회논문집
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• pp.1000-1007
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• 2007

In this study, structural vibration analyses of a smart unmanned aerial vehicle (UAV) have been conducted considering dynamic hub-loads of tilt rotor. Practical computational structural dynamics technique based on the finite element method is applied using MSC/NASTRAN. The present UAV(TR-S5-04) finite element model is constructed as a full three-dimensional configuration with different fuel conditions and tilting angles for helicopter, transient and airplane flight modes. In addition, the 3-dimensional supporting equipment structures of electronic devices are considered for vibration analysis. As the results of this study, transient structural displacements and accelerations are presented in detail. Moreover, vibration characteristics of structural parts and installed equipments are investigated for different fuel conditions and tilting angles.

• 항공우주기술
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• 제7권1호
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• pp.49-60
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• 2008

스마트무인기 기술개발사업단에서 개발 중인 틸트로터 스마트무인기의 드라이브장치 개발과 관련하여, 주요 구성부품의 설계와 해석을 중심으로 개발 결과를 기술한다. 스마트무인기의 로터 구동을 위한 드라이브장치는 매우 정밀한 고난이 도의 시스템으로서 국내 개발 경험이 전혀 없는 기술 분야의 하나이다. 따라서 드라이브장치의 개발을 위해서 미국의 선진업체(EATI)와의 공동연구개발을 수행하였다.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2004년도 추계 학술대회논문집
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• pp.87-90
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• 2004

A numerical analysis was made for the unsteady flow fields of rotor system of a Tilt-Rotor aircraft in cruise mode. The Reynolds-averaged thin-layer Navier-Stokes equations were discretized by Roe's upwind differencing scheme and integrated in time by the LU-SGS algorithm. The computational domain of the rotor system was constructed by six multi-block Chimera grids. Simulated unsteady flow fields of rotating blades were studied in several different view points.

• 한국항공우주학회지
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• 제36권6호
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• pp.541-549
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• 2008

피로해석은 반복하중 하에서의 항공우주 구조물에 대한 구조적 파괴를 예방하기 위해 수행된다. 본 논문에서는 틸트로터형 무인 항공기에 대하여 피로수명에 대한 평가를 하였다. 먼저 틸트로터형 무인항공기의 기동에 맞는 하중 스펙트럼을 생성해 내었으며, F.C.L. 부품중 하나인 플랩퍼론 연결부위에 대하여 피로해석을 수행 하였다. 틸트로터형 무인항공기는 크게 두 가지 기동 형태로 나눌 수 있는데, 이 착륙시의 헬리콥터 형태와 순항시의 고정익 형태가 되겠다. 전체적인 피로하중 스펙트럼을 만들기 위해서 헬리콥터 형태에는 FELIX를, 고정익 형태에서는 TWIST를 사용하였다. 한편으로는, S-N 실험점이 해석에 사용될 때 재료수명의 전 영역에 대한 S-N 회귀식을 얻기 위하여 크리깅 메타 모델이 사용되었다. 그리고 최소 자승법을 이용한 이차 회귀식에 대한 S-N 커브 역시 생성하였다. 더욱이 이 커브들이 갖고 있는 정확도를 측정하기 위하여 결정 계수법을 사용하였다. 마지막으로는 플랩퍼론 연결 부위에 대한 피로수명 결과를 MSC. Fatigue와 비교하였다.

• 항공우주기술
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• 제4권1호
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• pp.39-44
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• 2005

로터의 성능 예측 검증을 위해 tilt rotor aeroacoustic model(TRAM)에 대한 3차원 CFD 해석을 수행하였고 로터 파워 효과에 의한 영향을 분석하기 위해 수치해석을 행하였다. 수치 기법은 multiple reference method(MRF)와 sliding mesh technique을 사용하였다. TRAM 실험치와 비교 결과 정지 비행시에는 수치해석이 실험보다 적은 추력을 예측하였고 전진 비행시에는 실험결과와 매우 유사한 결과를 예측하였다. 로터효과를 고려한 비행체의 양력은 감소하고 항력 및 피칭 모멘트는 거의 변화가 없는 것으로 판단된다.