• 한국항공운항학회지
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• 제13권3호
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• pp.97-109
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• 2005

A canard type aircraft, which has good wing stall and stall/spin-proof characteristics, is under development. The aircraft prototype has full-depth core sandwich type wing and fixed landing gear, and has been built for test flights. Newly developing aircraft will be equipped with retractable landing gear and conventional foam core sandwich laminate structures and multi-rib wings. In this study, we present the structural test procedure and result for aircraft Firefly.

• 한국항공우주학회지
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• 제31권6호
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• pp.45-51
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• 2003

본 논문에서는 소형 커나드 항공기인 Velocity-173의 가로안정성을 향상시키기 위한 방법에 대하여 연구하였다. Velocity-173의 세로안정성은 매우 우수한 반면, 가로안정성은 상대적으로 나쁘다. 가로안정성을 향상시키기 위해 수직미익의 면적을 증가시키는 작은 패널을 설계 및 제작하였다. 패널 설계 과정에서 AAA를 이용하여 패널 부착으로 인한 가로안정성의 변화를 예측하였다. 패널 부착 효과를 검증하기 위해 비행시험이 수행되었다. 또한, 비행시험 데이터로부터 안정/조종 미계수를 추출하기 위하여 최대공산추정법을 이용하였다. 본 연구를 통해 수직미익 아래에 부착된 패널의 효과를 확인할 수 있었다.

• 한국군사과학기술학회지
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• 제9권4호
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• pp.15-23
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• 2006

In this paper, full-scale airframe static test of 4-seater canard airplane(the Firefly) was explained. From the results of the structural analysis, 5 design limit loads test conditions and 11 design ultimate loads test conditions were selected. Test loads analysis was performed and test fixtures and load control system(LCS) were prepared to realize the test loads. To protect the test article during the test, the overload protection system was prepared. Strain and deflection values were acquired through the data acquisition system(DAS) to verify the structural analysis results.

• 한국전산유체공학회지
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• 제8권4호
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• pp.26-33
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• 2003

Smart UAV Development Program, one of the 21c Frontier R&D Program sponsored by MOST(Ministry of Science and Technology), was launched in 2002 As an air vehicle for the Smart UAV, CRW(Canard Rotor/wing) concept was one of the candidates compared in trade-off study. The CRW concept has not only been proven completely but its aerodynamic characteristics not known in detail yet. Two calculation methods were adopted in this study to obtain aerodynamic data for the CRW First method was the superpose DATCOM method which is capable of three lifting sufaces, and second one is the full Navier-Stokes computation around CRW configuration using overset grid method. Basic aerodynamic characteristics of the CRW configuration was analyzed and the minimum drag level with lift to drag ratio is presented. The peculiar flow characteristics around rotor/wing and hub were also examined and considered in the configuration design.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2001년도 ICCAS
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• pp.167.1-167
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• 2001

Although computational-fluid-dynamic methods and wind-tunnel testing can provide data about the aerodynamic characteristics of an aircraft, the determination of these and other characteristics from flight data plays and important role. The object of this study is the verification of overall aircraft system performance to improve the stability of vehicle. We have test the Velocity-173, canard-type airplane to obtain the stability data. We adopt the two identifications method, EKF and MLE, for the parameter estimation. The results are compared with those of conventional type airplane.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2003년도 추계 학술대회논문집
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• pp.106-113
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• 2003

Smart UAV Development Program, one of the 21c Frontier R&D Program sponsored by MOST(Ministry of Science and Technology), was launched in 2002. As an air vehicle for the Smart UAV, CRW(Canard Rotor/Wing) concept was one of the candidates compared in trade-off study. The CRW concept has not only been proven completely but its aerodynamic characteristics not known in detail yet. Two calculation methods were adopted in this study to obtain aerodynamic data for the CRW. First method was the superpose DATCOM method which is capable of three lifting surfaces, and second one is the full Navier-Stokes computation around CRW configuration using overset grid method. Basic aerodynamic characteristics of the CRW configuration was analyzed and the minimum drag level with lift to drag ratio is presented. The peculiar flow characteristics around rotor/wing and hub were also examined and considered in the configuration design.

• 한국군사과학기술학회지
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• 제19권2호
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• pp.145-154
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• 2016

In this paper, a pneumatic device for the deployment performance verification of canards deployed by inertia has been designed and the performance of the pneumatic device has been proven through analysis and tests. The pneumatic conveying process, orifice opening process and piston movement process of the pneumatic device were investigated by using numerical methods. The orifice diameter, pressure in a pressure tank and type of gas were regarded as the main design parameters of the pneumatic device. The error rate between analysis and test results under the same conditions was within 4 %. The accuracy of numerical methods used in this study were validated.

• EDISON SW 활용 경진대회 논문집
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• 제2회(2013년)
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• pp.316-320
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• 2013

본 논문은 일반 항공기와 카나드를 장착한 항공기의 차이점을 알아보기 위해 카나드와 주익의 수평위치에 따른 공력특성을 비교하였다. 카나드를 장착한 비행기는 비행 안정성에 이점을 얻을 수 있고 주익(Main wing)에서의 실속 현상을 미연에 방지 할 수 있는 장점이 있다. 이러한 현상을 알아보기 위해 카나드와 주익간의 위치를 변화시켜 그에 따른 공력특성을 EDISON 프로그램을 통해 해석하여 보았고 이를 ANSYS의 FLUENT를 이용하여 해석한 결과와 비교분석하여 신뢰성을 확보 할 수 있었다.

• 한국항공운항학회:학술대회논문집
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• 한국항공운항학회 2007년 춘계학술대회 논문집
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• pp.113-116
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• 2007

• 한국항공운항학회:학술대회논문집
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• 한국항공운항학회 2007년 춘계학술대회 논문집
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• pp.117-120
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• 2007