• 항공우주기술
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• 제7권2호
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• pp.205-212
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• 2008

본 논문에서는 스마트무인기 로터시스템의 공진, 로터 공탄성 안정성 및 휠플러터 안정성 해석을 위한 모델링 데이터와 최종 해석결과를 기술하였다 향후 날개구조 설계변경 가능성을 고려하여 날개 빔, 코드 및 비틀림 강성이 훨플러터 안정성에 미치는 영향이 분석되었다. 파라메트릭 분석 결과 날개의 비틀림 강성 및 빔강성의 변화가 코드방향 강성에 비하여 빔모드 댐핑값에 훨씬 큰 영향을 미치는 것으로 분석되었다. 최종 설계된 로터시스템은 공진가능성이 없고, 스마트무인기 TR-S4 로터/파일론/날개에 대하여 로터 공탄성 안정성 및 훨플러터 안정성이 보장됨을 해석적으로 확인하였다.

• 한국항공우주학회지
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• 제33권8호
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• pp.26-33
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• 2005

틸트로터 비행체 개념인 스마트무인기는 수직이착륙, 장기체공, 그리고 고속비행성능을 동시에 요구한다. 이와 같은 세 가지의 상반된 비행체 성능의 구현을 위해서는 비행모드별로 최적의 공력성능을 갖도록 하는 플랩시스템의 운용이 불가피하다. 스마트무인기의 플래퍼론을 설계하는데 있어서 다양한 후보 형상을 생성하고, 이들 형상에 대해 전산유동해석을 수행하여 각 형상에 대한 공력성능을 분석하였다. 이와 같은 공력성능과 실제형상의 구조적인 단순성을 고려하여 스마트무인기의 최종 플래퍼론 형상을 선정하였으며, 40% 축소모델에 대한 풍동시험을 통해 선정된 플래퍼론에 대한 성능을 검증하였다.

• 한국경영과학회:학술대회논문집
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• 한국경영과학회 2008년도 추계학술대회 및 정기총회
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• pp.448-452
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• 2008

Organization wishes to develop newer and more complex system according as social structure is more complex and a technology develops more. Therefore, field of system engineering in development of new system is realized by all-important essential boundary. However cost of SE have considered restrictively being not about SE cost having applied SE. About this problem, this study provides COSYSMO as model for SE cost estimation, as the application example, estimate SE cost for smart UAV system applying COSYSMO in PRICE Trueplanner.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2006년 제4회 한국유체공학학술대회 논문집
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• pp.415-421
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• 2006

The unsteady flow calculation around the proprotor of Smart UAV was conducted. Using the flight scenario of SUAV which composed of hover, transition, and airplane mode, the aerodynamic analysis of proprotor were performed for the variation of collective pitch, rpm, forward speed, and tilt angle. The unsteady compressible Navier-Stokes equations were used for the calculation and the dynamic overset grid technique was applied for the rotating proprotor. The aerodynamic performance of proprotor calculated in this way were validated by comparing with the performance data obtained from the blade element momentum method.

• 대한기계학회논문집B
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• 제29권6호
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• pp.755-762
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• 2005

To evaluate the aerodynamic efficiency of TR-S2 configuration designed by SUDC, wind tunnel tests of $40\%$ scaled model were done in KARI LSWT. The aerodynamic characteristics of plain and Semi-Slotted Flaperon were compared, and vortex generators were installed to improve flow pattern along the wing surface. Effects of the control surface such as elevator, rudder, aileron, and incidence angle of horizontal tail are measured for various testing conditions. Test results showed that Semi-Slotted Flaperon produced more favorable lift, lift/drag, and stall margins and application of vortex generator would be best choice to enhance wing performance. Longitudinal, lateral and directional characteristics of TR-S2 were found to be stable for the pitch and yaw motions.

• 대한기계학회논문집B
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• 제30권10호
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• pp.1012-1018
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• 2006

To evaluate the aerodynamic efficiency of TR-S4 configuration, wind tunnel tests of 40% scaled model were done in KARI LSWT. TR-S4 configuration has different nacelle shape, larger EO/IR camera and aftward wing location compared with TR-S2. Component build-up test after adding each element of model is performed. Also effects of horizontal tail incidences, Flaperon and Aileron deflection. on aerodynamic characteristics are measured. Test results showed that TR-S4 configuration has favorable stability characteristics in longitudinal, lateral and directional for the pitch and yaw motions.

• 항공우주시스템공학회지
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• 제8권2호
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• pp.33-39
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• 2014

Feathering spindle is one of the critical parts of the rotor system in the Smart Unmanned Aerial Vehicle(SUAV) that it was manufactured with special material, Maraging C300. During the initial ground and tie-down flight tests of the SUAV, surface of the feathering spindle contacting to the needle-roller bearings showed excessive wear and dent due to high vibrating loads transferred from the rotating blades. Gas nitriding process was applied to the bearing contact surface of the feathering spindle to increase surface hardness so as to improve the surface defects. This paper briefly presents the gas nitriding process adopted and the spindle quality improvements including wear and corrosion resistance.

• 대한기계학회논문집B
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• 제29권1호
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• pp.35-45
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• 2005

TR-E2 configuration designed by Bell Textron was tested in KARI 1-m wind tunnel. To explore aerodynamic characteristics for the given configuration, a $12\%$ scaled model was fabricated and tested. Wind tunnel test for TR-E2 had been performed by changing the incidence angles of wing and deflection angles of control surfaces. Test result showed that the lower wing incidence angle has more favorable lift to drag ratio compared with original design. Longitudinal and directional characteristics of TR-E2 were found to be stable for the pitch and yaw motions. However, the lateral stability of TR-E2 is not stable for certain control surface deflection.

• 대한기계학회논문집B
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• 제29권3호
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• pp.295-305
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• 2005

To improve the aerodynamic effciency of TR-E2, a new configuration so called TR-E2Sl was introduced. TR-2251 is composed of different wing airfoil section and T-tail shape compared with TR-E2. Wind tunnel test for TR-EBS1 had been performed by changing the incidence angles of wing and deflection angles of control surfaces such as elevator and rudder. Also the on/off effect of ventral fin attached underneath of AFT fuselage was tested. Test result showed that variations of wing incidence angle did not cause any severe differences in aerodynamic characteristics. Longitudinal and directional characteristics of TR-E2S1 show stable for the pitch and yaw motions. However, the lateral stability of TR-E2S1 is not stable for a certain control surface deflection.

• 항공우주기술
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• 제10권2호
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• pp.11-19
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• 2011

스마트무인기 로터 블레이드의 국산화 개발이 수행되었다. 국산화 개발은 원소재와 물성치가 가장 유사한 국내 생산 복합소재의 선정, 새로운 소재의 물성치 데이터 구축을 위한 쿠폰시험, 블레이드 단면 물성치의 재계산, 공진, 정적/피로 강도, 공탄성 안정성의 구조동역학 설계요구조건에 대한 검증 등을 포함하며, 그 결과에 대하여 기술하였다. 또한 본 논문에서는 스마트무인기 국산화 블레이드 개발과정에서 개선된 공정에 대하여 간략히 기술하였다.