• Title/Summary/Keyword: 꼬리날개

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A wing-tail interference for a tail-controlled missile (꼬리날개 조종 유도무기의 주날개-꼬리날개 간섭 현상)

  • Kim, Duk-Hyun;Lee, Dae-Yeon;Kang, Dong-gi;Lee, Hyoung Jin
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.45 no.10
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    • pp.817-824
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    • 2017
  • This paper presents the characteristics of wing-tail interference for a tail-controlled missile. The magnitude of wing-tail interference was calculated with wind tunnel test results and its effects on aerodynamic coefficients were investigated. The downwash angle of tail wing was calculated with experimental data and the effect of wing-tail interference was expressed as a ratio of angle of attack. Numerical simulations were made to examine flow characteristics of wing-tail interference and the vorticity contour of missile were compared with respect to angle of attack. Experimental and numerical analysis results show that the wing-tail interference has significant effects on static stability of tail-controlled missile.

Study on the Relationship between the Tail Graphics of Various Airlines and National Branding Correspondence (항공사별 꼬리날개 그래픽과 국가브랜드 인지도 상관관계에 관한 연구)

  • Zhou, Dan;Seo, Han-Sok
    • The Journal of the Korea Contents Association
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    • v.19 no.10
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    • pp.21-31
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    • 2019
  • With the development of the aviation industry, aircraft painting design also plays the role of transmitting the national image while conveying the individual image of the airline. The recognition and recognition of the national image can be obtained by building a national brand. As a result, more and more companies are using the national brand image of their own country or other countries to add value to the company. Objective: To better reflect the national brand recognition for the design of the tail fin in the future aircraft painting design. This paper mainly studies the correlation between the tail graphic elements of aircraft painting design and national brand recognition based on the tail graphics of the three major airline alliance members. Based on the prior research, the relevant hypotheses were proposed and the questionnaire was designed. Secondly, a questionnaire survey was conducted on the passengers using the aircraft, and the correlation analysis was performed on the data by the SPSS regression analysis method. Conclusion: Data analysis has a strong correlation.

Study on the Correction of a Wing-tail Interference Effect in a Semi-empirical Aerodynamic Analysis Tool (반경험적 공력 해석도구의 주날개-꼬리날개 간섭 효과 보정에 대한 연구)

  • Lee, Dae-Yeon;Kim, Jae-Hyun;Kang, Dong-Gi
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.49 no.2
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    • pp.85-93
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    • 2021
  • In this paper, the aerodynamic characteristics of general tail controlled missile were predicted and corrected the result using semi-empirical analysis tool. The cause of the error was confirmed by comparing the aerodynamic characteristics prediction result of the semi-empirical analysis tool with the wind tunnel test result, and the main error factor of the semi-empirical analysis tool was the interference component between the main wing and the tail wing. The semi-empirical analysis results were corrected using the wind tunnel test results and the computational analysis results, and it was confirmed that the corrected data agrees well with the wind tunnel test results. Through this study, it was confirmed that the wing-tail interference component correction is needed when predicting the aerodynamic characteristics of a general tail controlled missile using a semi-empirical analysis tool.

Experimental Analysis of Towing Attitude for I-type and Y-type Tail Fin of Active Towed SONAR (I 형 및 Y 형 꼬리 날개 능동 예인 음탐기의 예인 자세에 대한 실험적 분석)

  • Lee, Dong-Sup
    • Journal of the Korea Academia-Industrial cooperation Society
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    • v.20 no.8
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    • pp.579-585
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    • 2019
  • Increasing the detection probability of underwater targets necessitates securing the towing stability of the active towed SONAR. In this paper, to confirm the effects of tail wing fin on towing attitude and towing stability, two scale model experiments and one sea trials were conducted and the results were analyzed. The scale model tests measured the towing behavior of each of the tail fin shapes according to towing speed in a towing tank. The shape of the tail fin used in the scale model test was tested with an I-type tail fine and four Y-type tail fins, totaling five tail fins of the two kinds. The first scale model test confirmed that the Y-type tail fin was superior to the I-type tail fin in towing attitude and towing stability. The second scale model test confirmed the characteristics of the vertical tail fin height increase and the lower horizontal tail fin inclination angle application shape based on the Y-type tail fin. The shape of the application of the lower horizontal tail fin inclination angle showed the best performance. In order to verify the results of the scale model test, a full size model was constructed, sea trials were performed, and the towing attitude was measured. The results were similar to those of the scale model test.

Ornithopter actuator characteristics analysis by motion capture experiment (모션캡쳐 실험을 통한 조류모방 날갯짓 비행체 구동 특성 분석)

  • Gim, Hakseong;Kim, Seungkeun;Suk, Jinyoung
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.45 no.3
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    • pp.173-179
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    • 2017
  • This paper analyzes actuator characteristics for main wing and tail surfaces of an ornithopter by using a motion capture test. Experiments with the ornithopter are conducted indoor, and its fuselage is held on a jig to reduce interaction with vibration generated by flapping motion. The motion capture system detects the movement of markers attached on the main wing and tail wing tip. Experimental results show that the main wings tend to change its amplitude according to the flapping frequency, and the lift and thrust generation simulation is implemented by applying the experimental results and the ornithopter specification to Modified Strip Theory. Step input excitation is applied for experimental analysis of the tail wing in horizontal and vertical directions. As a result, horizontal and vertical tail wings have different characteristics in terms of overshoot, final value, damping ratio and natural frequency because they have different wing structures and linkages.

Simulation Analysis on Air Stream Around the Tail Wing of Airplane (비행기 꼬리날개 주위의 기류에 관한 시뮬레이션 해석)

  • Han, Moon-Sik;Cho, Jae-Ung
    • Journal of the Korean Society of Manufacturing Technology Engineers
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    • v.20 no.1
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    • pp.23-27
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    • 2011
  • This study analyzes about the variation of pressure and stream velocity according to the movement of tail wing. The pressure at the front part of airplane becomes lower than at the rear part and the stream velocity has decreased by being bumped against the wing of airplane. The pressure at the front part of rudder becomes higher than at its rear part according to the movement of rudder among the tail wings of airplane. The more stream velocity becomes decreased, the more rudder spreads out. As the tail wing of airplane folds, the pressure at its front part becomes higher. And the pressure at its rear part becomes lower than at its front part. The more tail wing of airplane folds, the more stream velocity becomes decreased.

미래의 전투기 X-36 - 모형 출고에 즈음하여 특징을 알아본다

  • 한국항공우주산업진흥협회
    • Aerospace Industry
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    • v.40
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    • pp.54-57
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    • 1996
  • 날개비행기인 B-2 폭격기가 취역한데 이어 이번에는 꼬리날개가 없는 X-36이라는 미래형 전투기가 축소형 모형으로 만들어져 방금 지상시험이 진행중에 있어 세계 항공기 개발업계에 비상한 관심이 모으고 있다. 미국의 NASA와 MD사가 반반씩 비용을 부담하여 개발한 미래형 전투기의 기선을 제압할 X-36의 이모 저모를 알아본다.

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Empennage Design of Solar-Electric Powered High Altitude Long Endurance Unmanned Aerial Vehicle (고고도 장기체공 전기 동력 무인기의 꼬리 날개 설계)

  • Hwang, Seung-Jae;Lee, Yung-Gyo;Kim, Cheol-Wan;Ahn, Seok-Min
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.41 no.9
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    • pp.708-713
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    • 2013
  • KARI is developing a solar-electric powered HALE UAV(EAV-3). For demonstrating the technology, EAV-2H, a down-scaled version of EAV-3, is developed and after EAV-2H's initial flight test, the directional stability and control need to be improved. Thus, the vertical tail and rudder of EAV-2H are redesigned with Advanced Aircraft Analysis(AAA). Size of the rudder is increased from mean chord ratio of rudder to vertical tail, $C_r/C_v(%)=30$ to $C_r/C_v(%)=60$ and size of the vertical tail is reduced 15%. As a result, the directional control to side wind($v_1$) is improved to sideslip angle, ${\beta}(deg)=25^{\circ}$ and $v_1(m/sec)=3.54$. Also, variation of airplane side force coefficient with sideslip angle ($C_{y_{\beta}}$) and variation of airplane side force coefficient with dimensionless rate of change of yaw rate ($C_{y_r}$) are reduced 15% and 22%, respectively to minimize the effect of side wind. The empennage design of EAV-2H is verified with flight tests and applied to design of KARI's solar-electric-powered EAV-3.

Sensorless BLDC Motor Control to Drive Fins for Flight Attitude Control of a Guided Artillery Munition (유도형 탄약의 조종날개 제어용 Sensorless BLDC 전동기 구동시스템 개발)

  • Kim, Sang-Hoon;Lee, Tae-Hyung;Cho, Chang-Yeon;Pak, Chang-Ho;Kim, Jae-Ho
    • Proceedings of the KIPE Conference
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    • 2014.07a
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    • pp.49-50
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    • 2014
  • 본 논문에서는 유도형 활공 탄약의 비행경로 제어와 자세유지를 위해 장착된 꼬리 날개 구동을 위한 BLDC 전동기 제어시스템을 개발하였다. 이 시스템에서는 높은 고도에서의 비행 시 압력에 취약한 홀(Hall) 센서와 같은 회전자의 위치 검출 센서를 사용하지 않는 센서리스(Sensorless) 구동 방식을 적용하였다. 측정된 극전압으로부터 상전환 신호를 추출하여 BLDC 전동기의 센서리스 구동을 실현하였으며, 또한 상전환 신호로부터 추정된 속도를 사용하여 속도 제어를 통해 꼬리날개의 변위 명령 추종을 위한 위치 제어를 수행하였다. 실제 구현된 시스템에서의 실험을 통해 개발된 센서리스 제어 알고리즘을 적용하여 위치 제어의 성능이 우수함을 확인하였다.

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Development of Technology for Optimized Wing Design of Subsonic Aircraft (아음속 항공기 날개 최적 설계 기술 개발)

  • Kim, Cheol-Wan;Choi, Dong-Hoon
    • Aerospace Engineering and Technology
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    • v.10 no.1
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    • pp.175-182
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    • 2011
  • Optimized design was performed for a subsonic aircraft wing. The subsonic aircraft is dual turbo-prop and carrying less than 100 passengers. The cruise speed is Mach 0.6. The design was performed by two stages. The first stage is to decide the height of horizontal tail by analyzing the directional stability with Vorstab and then, the optimized wing configuration was selected with Piano, a optimizer commercially available. Fluent, a commercial CFD software was utilized to predict the aerodynamic performance of the aircraft. Drag of the aircraft was minimized with maintaining constant lift for cruise. The optimization reduced 10 counts from the initial wing configuration.