• 한국항공우주학회지
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• 제43권3호
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• pp.224-231
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• 2015

람다 날개 형상의 공력 계수에 대한 실험적 연구를 국방과학연구소의 중형아음속 풍동에서 수행하였다. 본 연구의 주목적은 옆미끄럼각의 변화에 따라 다양한 공력 계수가 어떻게 변화하는지를 조사하는 것이다. 옆미끄럼각이 $0^{\circ}C$인 경우, 피칭 모멘트가 급격히 불안정해지는 현상을 확인하였으며, 옆미끄럼각이 증가함에 따라 pitch break 현상이 더 높은 받음각에서 발생하는 것을 확인하였다. 롤링 모멘트는 옆미끄럼각이 있는 경우 pitch break와 유사한 특성을 보여준다. 이런 경향은 옆미끄럼각이 증가할수록 더 심하게 나타났다. 요잉 모멘트는 높은 받음각에서 옆미끄럼각에 따라 기울기가 크게 변화하였고 불안정한 방향 안정성이 뚜렷이 나타났다. 모멘트의 이런 특성들은 비행 제어를 위해서는 보다 효과적인 조종성 증가 장치가 필수적이란 것을 의미하고 있다.

• 한국항공우주학회지
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• 제30권1호
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• pp.1-8
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• 2002

자유류 속도가 40 m/sec 이고 날개의 뿌리시위에 기준한 레이놀즈수가 1.76${\times}$10$^6$인 상태에서 옆미끄럼이 삼각 날개 와류에 미치는 영향을 실험적으로 연구하였다. 받음각 범위는 16$^{\circ}$에서부터 28$^{\circ}$까지 이었으며 옆미끄럼각은 0$^{\circ}$, -10$^{\circ}$, 그리고 -20$^{\circ}$이었다. 옆미끄럼각은 바람쪽과 바람 반대쪽 와류 모두의 강도를 감소시키고, 바람쪽 와류의 붕괴를 촉진시킴이 관찰되었다. 옆미끄럼각 -10$^{\circ}$에서 바람 반대쪽의 와류는 받음각이 증가함에 따라 그 강도가 증가하였다. 이와 같은 옆미끄럼 조건에서 날개 와류의 비대칭적인 발달과 붕괴는 삼각 날개의 롤링모멘트를 어느 특정한 높은 받음각에서 급격히 바뀌게 할 수 있으며, 이는 일종의 롤링 모멘트 불안정성으로 간주할 수 있다.

• Journal of Mechanical Science and Technology
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• 제17권6호
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• pp.914-924
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• 2003

The interaction and breakdown of vortices over the Leading Edge Extension (LEX) - Delta wing configuration has been investigated through wing-surface pressure measurements, the off-surface flow visualization, and 5-hole probe measurements of the wing wake section. The description focused on analyzing the interaction and the breakdown of vortices depending on the angle of attack and the sideslip angle. The Effect of angle of attack and sideslip angle on the aerodynamic load characteristics of the model is also presented. The sideslip angle was found to be a very influential parameter of the vortex flow over the LEX-delta wing configuration. The introduction of LEX vortex stabilized the vortex flow, and delayed the vortex breakdown up to a higher angle of attack. The vortex interaction and breakdown was promoted on the windward side, whereas it was suppressed on the leeward side.

• 한국자동차공학회논문집
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• 제19권1호
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• pp.51-57
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• 2011

Information of the lateral velocity and the sideslip angle in a vehicle is very useful in many active vehicle safety applications such as yaw stability control and rollover prevention. Because cost-effective sensors to measure the lateral velocity and the sideslip angle are not available, reliable algorithms to estimation them are necessary. In this paper, a sliding mode observer is designed to estimate the lateral velocity. The side slip angle is estimated using the recursive least square with the disturbance observer and the pseudo integral. The estimated parameters from the combined estimation method are updated recursively to minimize the discrepancy between the model and the physical plant, and any possible effects caused by disturbances. The performance of the proposed monitoring system is evaluated through simulations and experiments.

• Transactions on Control, Automation and Systems Engineering
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• 제3권2호
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• pp.71-76
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• 2001

This paper deals with an estimation method for sideslip angle by using an unknown disturbance observation technique in 4WS passenger car systems. Firstly, a 4WS vehicle model with 3DOF is derived under the constant velocity and same tyres properties. The vehicle dynamics is transformed into the linear state space model with considering the external disturbances. Secondly, and unknown disturbance observer is introduced and its property which estimating the states of system without any disturbance information is shown. Lastly, the estimated sideslip angle of the 4WS vehicle system is verified through numerical simulation.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2000년도 제15차 학술회의논문집
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• pp.476-476
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• 2000

This paper deals with an estimation method far sideslip angle by using an unknown input observation technique in 4WS passenger car systems. Firstly, a 4WS vehicle model with 3DOP is derived under the constant velocity and same tyre's properties. The induced model is transformed into the linear state space model with considering the external disturbance. Secondly, an unknown input observer is introduced and its property which estimating the states of system without any disturbance information is shown. Lastly, the estimated sideslip angle of the 4WS system is verified through numerical simulation.

• 한국항공운항학회지
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• 제12권2호
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• pp.71-81
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• 2004

There are four methods of landing of B747-400 during the crosswind condition. Pilots can choose either one of them. Those are: Sideslip/Wing low, De-Crab during Flare, Touchdown in Crab, Combining Crab and Sideslip. They decide to use one method by what they have learnt before. During the flight, the pilots choose the method, which depends on the weather forecast, and then try to land according to it. However, the weather condition always changes. In other words, the weather during planning and landing can be different, which can provide a difference between the previously expected situation and the actual one. Therefore, it is very important for the pilots to have the situation awareness. This study shows the direction and the prevention to avoid those errors, which are based on actual landing data of B747-400.

• 한국가시화정보학회지
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• 제2권2호
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• pp.52-57
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• 2004

The development and interaction of vortices over a delta wing with leading edge extension (LEX) was investigated through off-surface flow visualization using micro water droplets and a laser beam sheet. Angles of attack of $20^{\circ}$ and 24$^{\circ}$ were tested at sideslip angles of $0^{\circ}$, $-5^{\circ}$, and $-10^{\circ}$ The flow Reynolds number based on the main-wing root chord was $1.82{\times}10^{5}$. The wing vortex and the LEX vortex coiled around each other while maintaining comparable strength and identity at a zero sideslip. The increase of angle of attack intensified the coiling and shifted the cores of the wing and LEX vortices inboard and upward. By sideslip, the coiling, the merging and the diffusion of the wing and LEX vortices were increased on the windward side, whereas they were delayed significantly on the leeward side. The present study confirmed that the sideslip angle had a profound effect on the vortex structure and interaction of a delta wing with LEX, which characterized the vortex-induced aerodynamic load.

• 한국항공우주학회지
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• 제31권2호
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• pp.17-24
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• 2003

본 논문은 $65^{\circ}$ 후퇴각을 갖는 삼각날개에 대하여 뿌리시위를 기준으로 한 레이놀즈수 $1.76{\times}10^6$에서 정상 풍동실험에 의한 결과를 보였다. 풍동실험은 총 188개의 압력공과 다채널 데이터 처리 시스템을 사용하여 날개 윗면에서의 압력 분포를 측정하였다. 날개 윗면에서의 압력분포의 분석으로부터 옆미끄럼각과 받음각이 날개의 공력 특성에 미치는 복합적인 영향에 대한 직관을 얻을 수 있었다. 옆미끄럼각이 있는 경우, 바람쪽 날개의 와류강도는 바람 반대쪽 날개의 화류강도보다 훨씬 강하였다. 이와 같은 좌우 날개의 비대칭적인 압력분포로 인하여 음의 롤링모멘트가 발생하였다. 하지만, 일정 범위의 받음각과 옆미끄럼각(${\alpha}$=$24^{\circ}{\sim}36^{\circ}C$, ${\beta}$=$-5^{\circ}{\sim}-15^{\circ}C$)에서는 롤링모멘트의 방향이 갑자기 바뀌는 롤링모멘트 역전현상을 관찰할 수 있었다.

• Wind and Structures
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• 제31권3호
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• pp.229-240
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• 2020

In the present work, the main features of primary vortices and the vorticity concentrations downstream of vortex bursting in crossflow plane of a delta wing with a sweep angle of Λ=70° were investigated under the variation of the sideslip angles, β. For the pre-review of flow structures, dye visualization was conducted. In connection with a qualitative observation, a quantitative flow analysis was performed by employing Particle Image Velocimetry (PIV). The sideslip angles, β were varied with four different angles, such as 0°, 4°, 12°, and 20° while angles of attack, α were altered between 25° and 35°. This study mainly focused on the instantaneous flow features sequentially located at different crossflow planes such as x/C=0.6, 0.8 and 1.0. As a summary, time-averaged and instantaneous non-uniformity of turbulent flow structures are altered considerably resulting in non-homogeneous delta wing surface loading as a function of the sideslip angle. The vortex bursting location on the windward side of the delta wing advances towards the leading-edge point of the delta wing. The trajectory of the primary vortex on the leeward side slides towards sideways along the span of the delta wing. Besides, the uniformity of the lift coefficient, C_L over the delta wing plane was severely affected due to unbalanced distribution of buffet loading over the same plane caused by the variation of the sideslip angle, β. Consequently, dissimilarities of the leading-edge vortices result in deterioration of the mean value of the lift coefficient, C_L.