• International Journal of Aeronautical and Space Sciences
• /
• 제4권1호
• /
• pp.19-25
• /
• 2003

A low speed wind tunnel test for the canard airplane model was conducted in KARI LSWT. To measure the required level of accuracy, the image system was applied for all elevator deflection and different canard incidence conditions. By doing so, the difference in aerodynamic characteristics between the forward swept and straight canards can be precisely evaluated, and the pros and cons of both canards arrangements can be discussed. Compared with both canard configurations at the same incidence angle setting, the straight canard has benefits in lift and drag, and the slope of pitching moment increases more moderately than the forward swept canard. The listed data and discussion would be useful to whom wants to design a canard airplane.

• Journal of Mechanical Science and Technology
• /
• 제16권1호
• /
• pp.125-131
• /
• 2002

A low speed wind tunnel test was conducted for a canard airplane model in KARI LSWT. The purpose of the presented paper is to investigate the proper testing approach to correct tare precisely and the interference effects for the canard models which has 21% of canard-to-wing area ratio. Most of tests were performed with image system installation for various elevator deflection conditions at the flexed canard incidence angles. To evaluate the effectiveness of the image system, the obtained correction quantity at an zero elevator setting condition with image system was applied to the rest of elevator deflections and compared with the acquired results for all elevator deflections with image system. Test result showed that the amount of correction quantities were strongly dependent on the elevator deflections, and the difference in aerodynamic coefficients for two approaches was gradually amplified as the elevator deflection angles increased. An adoption of the image system was strongly recommended for the higher canard-to -wing area ratio model, if a proper level of accuracy was required.

• 항공우주기술
• /
• 제6권2호
• /
• pp.35-39
• /
• 2007

본 논문에서는 4인승 선미익 항공기에 대한 구조해석 절차와 전기체 시험결과를 소개하였다. 전기체 유한요소모델 구축은 항공기 구조해석 시 중요한 업무이며 구조적 안전성에 직접적인 영향을 미치게 된다. 구축된 유한요소모델은 전기체 시험결과를 이용하여 정밀하게 보정된다. 구조해석 결과를 이용하여 5가지의 설계제한하중 시험조건과 11가지의 설계 극한하중 시험조건을 결정하였다. 소개된 절차를 이용하여 4인승 선미익 항공기의 구조적 안전성을 성공적으로 확보하였다.

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

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

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

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

• 한국항공운항학회:학술대회논문집
• /
• 한국항공운항학회 2007년 춘계학술대회 논문집
• /
• pp.109-112
• /
• 2007

• International Journal of Aeronautical and Space Sciences
• /
• 제2권1호
• /
• pp.103-109
• /
• 2001

Productivity enhancement program of wind tunnel testing has begun at Korea Aerospace Research Institute Low Speed Wind Tunnel (KARI LSWT). A previous test record of a canard airplane model was adopted to examine the current status of wind tunnel testing efficiency. The time consumed to perform testing activities from the model preparation to data collection was broken down and the results were compared with those of the recent Boeing low speed test result. The efforts to improve the wind tunnel productivity consisted of the installation of mini crane underneath of test section, fabricating lift device for image fairings, model configuration changing rigs and the modifications of external balance system. Time reductions for changing strut interface platform and installation of image fairings. These effects showed more than 70% improvement over the previous test time. Integration of the new and modified systems will improve productivity of wind tunnel testing in KARI LSWT.

• 한국항공운항학회지
• /
• 제14권2호
• /
• pp.71-78
• /
• 2006

In this paper, it is described on the exportation trend and future development paradigm of the localized small aircraft which was recently developed four seated canard type aircraft for exportation purpose. Presently, even though the development of small aircraft is recessed, if we start development of the proper airplane models by integrating domestic power of industry-university-institute on the base of research experience from now on, we can go into the global market and take up the level of world top 10 makers without doubt. For successful operation of exportation system of small aircraft, it is needed to set up development strategy paradigm by forming consortium centering around the medium and small enterprises.