• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.11 no.2
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• pp.278-285
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• 2000

This paper presents the basic characteristics of the beam tilting dipole antenna element in which one reactance element is used for the impedance matching at the feed point. The radiation pattern is tilted by the properly determined driving point position, and the loading reactance is used to obtain forced resonance without great changes in tilt angle. The numerical results demonstrate that the reactance element should be loaded in the region where the driving point is placed to obtain forced resonance of the antenna with little changes in beam tilt angle. In case the proposed forced resonant beam tilting antenna with $0.8\lambda$ length is driven at $0.2\lambda$ from the center, the main beam tilt angle o.5 57.7 degrees, the highest power gain of 8.6 dB are obtained.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.6
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• pp.509-516
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• 2007

Mathematical modeling and vibration control of a tiltrotor aircraft composite wing-rotor system are investigated in this study. A wing-mounted rotor can be tilted from the vertical position to a horizontal one, and vice versa. Effect of vibration control of the wing-rotor system via piezoelectricity is studied as a function of tilt angle, ply angle of composite wing and rotor's spin speed. Composite wing is modeled as a thin-walled box beam having a circumferentially uniform stiffness configuration that produces elastic coupling between flap-lag and between extension-twist behavior. Numerical simulations are provided and pertinent conclusions are outlined.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.389-392
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• 2011

In this study, the engine performance data was extracted and analyzed through the flight test of Smart UAV which is tilt rotor aircraft. The flight test was conducted for the transition flight regime where the tilt angle of prop-rotor varies from 90 degree to 0 degree and vice versa. The engine performance data such as engine power and specific fuel consumption gathered from flight tests were compared well with the results of engine performance analysis program.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.3
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• pp.228-235
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• 2010

This paper deals with an autonomous flight controller design problem for a tilt-rotor aircraft in rotary-wing mode. The inner-loop algorithm is designed using the output-based approximate feedback linearization. The model error originated from the feedback linearization is cancelled within allowable tolerance by using single-hidden-layer neural network. According to Lyapunov direct stability theory, the adaptive update law is derived to run the neural network on-line, which is based on the linear observer dynamics. Moreover, the outer-loop algorithm is designed to track the trajectory generated from way-point guidance. Especially, heading and flight-path angle line-of-sight guidance are applied to the outer-loop to improve accuracy of the landing tracking performance. The 6-DOF nonlinear simulation shows that the overall performance of the flight control algorithm is satisfactory even though the collective input response shows instantaneous actuator saturation for a short time due to the lack of the neural network and the saturation protection logic in that loop.

• Journal of Advanced Navigation Technology
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• v.26 no.3
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• pp.144-160
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• 2022

Research on urban air mobility (UAM) is being actively conducted as a method of next-generation transportation. eVTOL, an airplane to be used for urban air mobility, is classified into a complex type, a tilt rotor type, a tilt wing type, a tilt duct fan type, and a multicopter type according to the propulsion method. In this study, conceptual design was performed for the next generation eVTOL of the new tilt rotor type in accordance with the existing design requirements. The aerodynamic analysis programs of OpenVSP and XFLR5 were used to perform aerodynamic analysis. The power required for each flight mission stage was calculated, the battery and motor were selected accordingly, and MTOW (Maximum Take-Off Weight) was predicted by estimating the weight of each component.

• Journal of the Institute of Electronics Engineers of Korea TC
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• v.39 no.4
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• pp.209-215
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• 2002

This paper describes beam-tilting characteristics of horizontally polarized EMCD (electromagnetically coupled dipole) array antennas. The result of one element radiator is used for array elements designs and is evaluated its characteristics. Theoretical frequency characteristics and radiation pattern of the horizontally polarized EMCD array antennas analyzed by FDTD method agree well with the measured results of the practically fabricated way antennas. The measured main beam tilt ang1e and 3 dB beam width of the fabricated 20-element array antennas are 47$^{\circ}$and about $\pm$7.5$^{\circ}$, respectively. A good radiation pattern and beam tilting characteristics are observed in experiments.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.6
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• pp.75-82
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• 2006

Tiltrotor aircraft can fly about twice faster and several times further than conventional helicopters. These aircraft provide advantages preventing compressibility of advancing side and stall of retreating side of blades because they take forward flight with tilting rotor systems. However, they have limit on forward flight speed because of the aeroelastic instability known as whirl flutter. First, the parametric study on the aeroelastic stability of the isolated rotor system has been performed in this paper. And the effects of pitch-link stiffness, gimbal spring constant, and precone angle on the whirl flutter stability of Smart-UAV have been investigated through CAMRAD II analysis.

• Journal of the Korean Institute of Electrical and Electronic Material Engineers
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• v.13 no.1
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• pp.75-79
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• 2000

In this study, we investigated the pretilt angle generation and liquid crystal (LC) alignment by ultravi-olet (UV) light irradiation during imidization of polymide. The generated pretilt angle of nematic (N) LC by using the in-situ photo-alignment method was smaller than that of the conventional UV photo-alignment method. Also, generated pretilt angle of NLC tends to increase by annealing. In case of using the polymer(AL-3046), we found that the in-situ Uv photo-alignment method has higher thermal stability of LC alignment, but it has a disadvantage to control pretilt angle.

• The KIPS Transactions:PartD
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• v.10D no.2
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• pp.337-342
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• 2003

In this paper, a web based remote control system located at too dangerous field to access for the worker. The system was designed and implemented for three-dimensional stereo camera connected to web server which can be controlled easily by client side person working in the safe monitoring room. The user in the client side can control the vergence/focus control and zoom-in/out and pan/tilt functions through an user interface. The user interface for remote control environment was designed and implemented with Java applet mechanism, and was tested the operation result of the system.

• Aerospace Engineering and Technology
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• v.5 no.2
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• pp.240-247
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• 2006

Tilt rotor aircraft is a multi-configuration airplane which has three independent flight modes; helicopter, conversion, and aiplane. The control surface mixer resign is reqctired to generate and distribute efficient control forces and moments in each flight mode. In the conversion mode, the thrust vector is changed from helicopter mode to airplane, therefore the thrust vector makes undesired forces and moments which affect on pitch, roll and yaw dynamics. This paper describes the design results of control surface mixer design which minimize the undesired forces and moments due to nacelles tilting angle change for 4O% scaled model.