• Journal of Institute of Control, Robotics and Systems
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• v.11 no.3
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• pp.233-239
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• 2005

This paper presents the design and evaluation of a tiltrotor attitude controller. The implemented response type of the command augumentation system is Attitude Command Attitude Hold. The controller architecture can alleviate the need for extensive gain scheduling and thus has the potential to reduce development time. The control algorithm is constructed using the feedback linearization technique. And an on-line adaptive architecture that employs a neural network compensating the model inversion error caused by the deficiency of full knowledge tiltrotor aircraft dynamics is applied to augment the attitude control system. The use of Lyapunov stability analysis guarantees boundedness of the tracking error and network parameters. The performance of the controller is evaluated against ADS-33E criteria, using the nonlinear tiltrotor simulation code for Bell TR301 developed by KARI. (Korea Aerospace Research Institute)

• The Journal of Society for e-Business Studies
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• v.8 no.4
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• pp.33-51
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• 2003

The primary objectives of this study were, using data from Internet users in Korea, to determine users' preference of banner ad through two ad properties; ad presentation type (text vs. image) and ad content (product information vs. prize information) by incorporating the level of involvement into research design. Using within-group experimental design by means of subjects' web-based participation in the study, the study result showed that image-based banner ad was significantly preferred to text-based banner ad. It was found that the level of ad involvement had a significant impact on the preference of banner ads. Also it was found that image-based banner ad had a greater effect on ad preference than text-based banner ad in low involvement situation only, Finally, image-based banner ad was consistently preferred to text-based banner ad regardless of involvement level when the banner ad was product oriented. The study findings suggest that adoption decisions regarding banner ad presentation type and banner ad content should be based on the knowledge of both the level of consumer's ad involvement and the interactive effects between ad presentation and ad content.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.17 no.1
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• pp.159-164
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• 2016

This paper reports the load factor logic design for a fly-by-wire helicopter flight envelope protection. As a helicopter is very complex system with a rotor, fuselage, engine, etc., there are many constraints on the flight region. Because of these constraints, pilots should consider them carefully and have a heavy workload, which causes controllability degradation. In this respect, automatic logic is needed to free the pilot from these considerations. As one of these logics, the flight envelope protection logic for the load factor of a FBW helicopter was designed. The flight to exceed the load factor is caused by an abrupt pitch cyclic stick change. In this scheme, the load factor limit logic was added between the pilot stick command block and pitch attitude command block. From the current load value, the available attitude range was calculated dynamically and simulated on the helicopter simulator model to verify the performance. A comparison of the simulation results at the hovering and forward speed region with and without applying the load limiting logic showed that the load factor limit was exceeded more than 20% when the logic was not applied, whereas with the load factor limit logic the load factor was within the limit. In conclusion, a dynamically allocated limitation logic to helicopter FBW controller was verified by simulation.