• International Journal of Aeronautical and Space Sciences
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• v.8 no.1
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• pp.87-94
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• 2007

Tilt rotor-wing concept to show enhanced performance in low speed mission is presented. Three types of stud wings on the existing tilt rotor configuration are suggested and their characteristics are compared. Aerodynamic analysis indicates that the stud wing concept gives significant performance improvement on the endurance and range in the low speed regime when compared with the tilt rotor. Penalties of the stud wing are discussed from the perspectives of conversion corridor, structural weight, configuration design, and cross wind stability. This study concludes that the advantage of the stud wing in general UAV mission performance is so significant as to surpass the penalties in other perspectives investigated.

• Journal of the Korean Institute of Landscape Architecture
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• v.35 no.6
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• pp.97-109
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• 2008

This study first attempted to catch the transformational affairs and motives of the representative pavilion, Hanbyeok in Honam after its construction. Especially, it re-illuminated the morphologic, significant and functional change process of a pavilion after the early Joseon Dynasty by taking the local scenery, Hanbyeokdang as a sample, and considering the space and scenic characteristics, and diachronically understood its creation process and rebuilt its inherent positional meaning to reach the following conclusion. 1. Weoldanglu, at its early foundation, seems to have stressed the function of a private banquet and lecture hall to train younger students, and served as a reception space. Then the reception function gradually increased, and up to before 1530, it seems to have been called Weoldanglu(月塘樓) or Weoldangwon(月塘院). 2. In 1619, Governor Yoo Saek changed the pavilion name to Hanbyeokdang through the subject of a poem. 200 years after Weoldang's death, it became a public space called Hanbyeokdang, an amusement place in which scholars cultivated great morale, and participated in the sending-off and welcoming of predecessors and successors. This seems to have taken a foothold as a public event or entertainment space for the local administration, Jeonjuboo(全州府) through the remodeling process sponsored by the public. 3. Scenic language such as its indicating name, expression type and surrounding view through old map and so on, the shape of Hanbyeokdang evolved and changed to diverse types after the foundation of Weoldanglu, at the heart of which Hanbyeokdang with its two legs standing at a rock was located. 4. During the late 18th century, Hanbyeokdang seems to have been a wing corridor connected closely to the left corridor of the Jeonju stream bed, whose pattern is presumed to have existed even during the early 19308. Such changes in scenic language make us assume that diverse auxiliary space, a wing corridor, was erected for use as a public banquet and amusement spot of Jeonjuboo Castle, the inherent function of Hanbyeokdang after the mid 18th century. 5. Penetration of Hanbyeokgool and the erection of Hanbyeokgyo caused the change of the ancient shape of Hanbyeokdang. Specifically, a great Hanbyeokgyo passing by the pavilion changed the relative scale, so the pavilion image of pursuing unity with nature has lost the old inherent refinement and visual character.

• Journal of Institute of Control, Robotics and Systems
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• v.20 no.11
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• pp.1103-1111
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• 2014

The results of control law design for a tilt-rotor unmanned aerial vehicle that has a nacelle mounted wing extension (WE) are presented in this paper. It consists of a control surface mixer, stability and control augmentation system (SCAS), hold mode for altitude / speed / heading, and a guidance mode for preprogram and point navigation which includes automatic take-off and landing. The conversion corridor and the control moments derivatives between the original tilt-rotor and its variant of the nacelle mounted WE were compared to show the effectiveness of the WE. The nacelle conversion of the original tilt-rotor starts when the airspeed is greater than 30 km/h but its WE variant starts at 0 km/h in order to reduce the drag caused by the high incidence angle of the WE. The stability margins of the inner loop are presented with the optimization approach. The outer loops for the hold mode are designed with trial and error methods with linear and nonlinear simulation. The main control parameter for altitude control of the helicopter mode is thrust command and it is transferred to the pitch attitude command in airplane mode. Otherwise, the control parameter for the speed of the helicopter mode is the pitch attitude command and it is transferred to the thrust command in airplane mode. Therefore the speed and altitude hold mode are coupled to each other and are engaged at the same time when an internal pilot engages any of the altitude or speed hold modes. The nonlinear simulation results of the guidance control for the preprogrammed mode and point navigation are also presented including automatic take-off and landing in order to prove the full control law.