• 한국군사과학기술학회지
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• 제5권3호
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• pp.77-86
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• 2002

An experimental study of the vortex interaction characteristics of a delta wing/LEX configuration was conducted in a wind tunnel using the micro water droplet and laser beam sheet visualization technique. The main focus of this study was to analyze the effect of the angle of attack and sideslip angle on the vortex interaction and vortex breakdown. These tests were accomplished at angles of attack between $16^{\circ}$ and $28^{\circ}$ and sideslip angle between $0^{\circ}$ and $-15^{\circ}$ at free-stream velocity of 6.2 m/s. Flow visualization data provide a description of the vortex interaction between LEX and wing vortices, and of the vortex breakdown. The introduction of LEX vortex stabilized the vortical flow, and delayed the vortex breakdown up to higher angle of attack. The vortex interaction and breakdown was promoted on the windward side, whereas they are suppressed on the leeward side.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2003년도 추계학술대회
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• pp.1524-1529
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• 2003

In this paper deals with a unique method for measuring vehicle states such as body sideslip angle and tire sideslip angle using GPS velocity information in conjunction with other sensors. A method for integrating Inertial Navigation System (INS) sensors with GPS measurements to provide higher update rate estimates of the vehicle states is presented, and the method can be used to estimate the tire cornering stiffness. The experimental results for the GPS velocity-based sideslip angle measurement and cornering stiffness estimates are compared with the theoretical predictions. From the experimental results, it can be concluded that the proposed method has an advantage for future implementation in a vehicle safety system.

• 한국항공우주학회지
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• 제30권3호
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• pp.37-45
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• 2002

옆미끄럼이 있는 조건에서 LEX를 갖는 $65^{\circ}$ 후퇴각 삼각날개의 와류와 공력 특성을 실험적으로 연구하였다. 자유 유동속도는 40m/sec이고 이 속도와 날개뿌리 시위를 기준으로 한 단위길이당 레이놀즈 수는 $1.76{\times}10^6$이다. 받음각 범위는 $12^{\circ}$ 부터 $28^{\circ}$ 까지 이고, 시험된 옆미끄럼각은 $0^{\circ}$ , $-10^{\circ}$ , $-20^{\circ}$ 이다. 날개의 바람쪽에 있는 LEX 와류는 바람 반대쪽 LEX 와류보다 훨씬 더 강하고 날개면에 더 가깝게 날개 후류영역으로 진입한다. LEX 와류와 날개 와류는 서로 연동하여 집중되고 강한 와류를 형성하거나 날개 하류지역에서 붕괴된다. LEX 와류와 날개 와류의 상호작용으로 인하여 바람쪽 날개면에는 높은 흡입압력이 유지되고, 바람 반대쪽 날개면에는 낮은 흡입압력이 형성된다.

• 한국항공우주학회지
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• 제30권7호
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• pp.105-112
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• 2002

높은 받음각 상태에 있는 연장된 앞전을 갖는 편요된 삼각날개 주위의 와류 유동 특성에 대하여 날개 윗면에서의 압력 측정을 통하여 연구하였다. 본 연구에서는 와류 유동의 물리적 현상, 특히 높은 받음각 상태에서 받음각과 옆미끄럼각이 날개 형상 주위의 공력 특성에 미치는 영향에 중점을 두었다. 실험 데이터로부터 LEX 와류가 날개와류에 유익한 효과를 부여함을 명확하게 알 수 있었다. 이는, 작은 옆미끄럼각 상태에서는 비교적 높은 받음각에 이르기까지 와류의 붕괴 없이 날개와류를 안정화시킴을 알 수 있다. 특정 범위의 받음각과 옆미끄럼각 상태에서는 롤링 모멘트가 역전되는 흥미로운 유동 현상을 관찰할 수 있었다.

• 한국항공우주학회지
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• 제30권5호
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• pp.109-117
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• 2002

옆미끄럼이 있는 조건에서 LEX를 갖는 삼각날개의 와류 특성을 유동의 가시화에 의한 실험적 방법으로 연구하였다. 모델은 $65^{\circ}$ 후퇴각의 갖는 평판 날개이다. 자유 유동속도는 6.2 m/s이며, 이 속도와 날개뿌리 시위를 기준으로 한 레이놀즈 수는 $4.4\times10^5$ 이다. 받음각 범위와 옆미끄림각 범위는 각각 $16^{\circ}\sim28^{\circ}$와 $0^{\circ}\sim-15^{\circ}$ 이다. 미세수적과 레이저 평면광에 의한 가시화는 오공 프로브에 의한 측정으로부터 얻을 수 없었던 보다 자세한 와유동 구조를 관찰 할 수 있도록 하였다. 옆미끄럼각이 있는 경우, 바람쪽은 LEX 와류와 날개 와류의 상호작용과 붕괴가 촉진되는 반면, 바람반대쪽은 두 와류의 상호작용과 붕괴가 억제되었다.

• International Journal of Aeronautical and Space Sciences
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• 제4권1호
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• pp.63-74
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• 2003

The vortical flow of a 65-deg flat plate delta wing with a leading edge extension(LEX) was examined through off-surface visualization, 5-hole probe and hot-film measurements. The off-surface flow visualization technique used micro water droplets generated by a home-style ultrasonic humidifier and a laser beam sheet. The angles of attack ranged from 10 to 30 degrees, and the sideslip angles ranged from 0 to -15 degrees. The Reynolds number was $1.82{\times}10^5$ for the flow visualization, and $1.76{\times}10^6$ for the 5-hole probe and hot-film measurements. The comparison of the visualization photos and the flow field measurement showed that the two results were in a good agreement for the relative position and the structure of the wing and LEX vortices, even though the flow Reynolds numbers of the two results were much different. The wing vortex and the LEX vortex coil each other while maintaining a comparable strength and identity at zero sideslip. Neither a looping of the wing vortex around the strake vortex, nor the lopsided coiling of the stronger strake and the weaker wing vortices was observed. At non-zero sideslip, the downward movement of the LEX vortex when going downstream was enhanced on the windward side, and the downward and inboard movement of the LEX vortex when going downstream was suppressed on the leeward side. The counterclockwise coiling of the wing and LEX vortices was decreased significantly on the leeward side.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2003년도 ICCAS
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• pp.1706-1709
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• 2003

This paper demonstrates a unique method for measuring vehicle states such as body sideslip angle and tire sideslip angle using Global Positioning System(GPS) velocity information in conjunction with other sensors. A method for integrating Inertial Navigation System (INS) sensors with GPS measurements to provide higher update rate estimates of the vehicle states is presented, and the method can be used to estimate the tire cornering stiffness. The experimental results for the GPS velocity-based sideslip angle measurement. From the experimental results, it can be concluded that the proposed method has an advantage for future implementation in a vehicle safety system.

• Journal of Electrical Engineering and Technology
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• 제8권4호
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• pp.899-910
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• 2013

This paper presents a novel lateral stability control system for electric vehicle based on sideslip angle estimation through Kalman filter using the integration of a single antenna GPS receiver and yaw rate sensor. Using multi-rate measurements including yaw rate and course angle, time-varying parameters disappear from the measurement equation of the proposed Kalman filter. Accurate sideslip angle estimation is achieved by treating the combination of model uncertainties and external disturbances as extended states. Active front steering and direct yaw moment are integrated to manipulate sideslip angle and yaw rate of the vehicle. Instead of decoupling control design method, a new control scheme, "two-input two-output controller", is proposed. The extended states are utilized for disturbance rejection that improves the robustness of lateral stability control system. The effectiveness of the proposed methods is verified by computer simulations and experiments.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2005년도 ICCAS
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• pp.1005-1007
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• 2005

A Nonlinear approach to control of Small Scale Rotary Wing Unmanned Aerial Vehicle (R-UAV) is presented. Using Backstepping, a globally stabilizing control law is derived. We derive backstepping control law for angle of attack and sideslip control. The inherent nonlinear nature of the system are considered here which helps in naturally stabilizing without extensive external effort. Thus, the resulting control law is much simpler than if the feedback linearization had been used.

• 한국자동차공학회논문집
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• 제9권2호
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• pp.176-184
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• 2001

The VDC(Vehicle Dynamics Control) is a control system whose target is to improve vehicle stability under critical motion. The system has a good potential of becoming a standard active safety unit in passenger vehicles since it can be implemented on top of the ABS/TCS system with little extra cost. This, however, is possible only when the signals that the VDC system demands can be obtained with sufficient accuracy. In this research, estimators for the road friction coefficient and body sideslip angle have been designed. The two variables have great influence upon performance of the VDC system but not directly measurable. For the estimator design, the Newton method and the nonlinear observer theory have been exploited. The performance of the estimator have been verified via simulations on critical driving conditions.