• Journal of the Korean Society for Aviation and Aeronautics
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• v.17 no.3
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• pp.7-13
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• 2009

This study examined 1) student pilots' personality types, 2) the correlation between students' personality types and their achievement in flight training, 3) the correlation between students' personality types and Instructor Pilot(IP)s' personality type. The study used the Korean version of Myers-Briggs Type Indicator (MBTI) form. A total of 164 students in the year of 2000-2003 completed the inventory. The noticeable majority of student pilot were extroverted (59.6%) - Sensing (79.5%) - Thinking (70.2%) - Judgers (68.9%). Comparing personality types with flight achievement in showed no significant correlation. There was, however, a significant difference seen in comparing personality types with students' flight achievements. Thinking-type students showed higher flight achievements than feeling-type, and some of the personality types combination affects trainee's flight achievement. When both student and the Instructor have same attitude such as E-E or I-I, student's flight achievement was higher than when they have opposite attitude of personality. these findings implicate that the cooperation of students' and IP's personality could affect the students' flight achievement.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.23 no.4
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• pp.57-65
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• 2015

In this study, MBTI(Myers-Briggs Type Indicator) test was carried out targeting flight instructors and student pilots in charge of introductory flight training course. The results was analyzed in accordance with the personality type, the preferred indicator, and the combination of preferred indicators in order to see how these characteristics affect the flight training results. Most of personality types of the instructor, regardless of the attitude category such as E or I, were -STJ(70.6%), however the student pilot showed a variety of personality types, rather than professors. Sensing-type(S) students showed higher academic achievement scores than Intuition-type(N), and Judging-type(J) students showed higher academic achievement scores and pilot qualification scores than Perceiving-type(P). The success rate of Extraversion-type(E) student pilots was higher than that of Introversion-type(I) student pilots. As the personality combinations of instructor and student pilot, the academic achievement scores of Judging-Judging(J-J) type were higher than those of Perceiving-Perceiving(P-P) type. The combination of Extraversion-Extraversion(E-E) type showed higher success rate than Extraversion-Introversion(E-I). This result suggests that if both instructor and student pilot have same attitude of Extroversion(E), good training results can be expected.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.29 no.1
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• pp.30-37
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• 2021

This study wanted to confirm whether the DiSC behavior types of student pilots and instructors in the training course of Helicopter pilots affect the flight training achievement. The results of the study are as follows. First, in the distribution of DiSC behavior types of student pilots and instructors, student pilots had the largest number of Dominance with 40.2 percent, while Instructors had the highest number of conscientiousness with 46.5 percent. Second, it was analyzed that the flight training achievement was influenced by the behavior type of student pilots. In basic flight and aircraft type conversion flight, Steadiness had the highest achievement in flight training, and in tactical flight, conscientiousness was the highest. Third, the behavior patterns of student pilots and instructors have been confirmed to have interaction effects in tactical flight.

• International Journal of Aeronautical and Space Sciences
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• v.8 no.1
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• pp.32-45
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• 2007

The T-50 advanced supersonic jet trainer employs the Relaxed Static Stability (RSS) concept to improve the aerodynamic performance while the flight control system stabilizes the unstable aircraft and provides adequate handling qualities. The T-50 flight control laws employ a proportional-plus-integral type controller based on a dynamic inversion method in longitudinal axis and a proportional type controller based on a blended roll system with simple roll rate feedback and beta-betadot feedback system. These control laws are verified by flight tests with various maneuver set flight envelopes and the control laws are updated to resolve flight test issues. This paper describes several concepts of flight control laws used in T-50 to resolve those flight test issues. Control laws for solving the roll-off problem during pitch maneuver in asymmetric loading configurations, improving the departure resistance in negative angle of attack conditions and enhancing the fine tracking performance in air-to-air tracking maneuvers are described with flight test data.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.03a
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• pp.513-520
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• 2004

A steady-state/transient performance simulation model was newly developed for the propulsion system of the CRW (Canard Rotor Wing) type UAV (Unmanned Aerial Vehicle) during flight mode transition. The CRW type UAV has a new concept RPV (Remotely Piloted Vehicle) which can fly at two flight modes such as the take-off/landing and low speed forward flight mode using the rotary wing driven by engine bypass exhaust gas and the high speed forward flight mode using the stopped wing and main engine thrust. The propulsion system of the CRW type UAV consists of the main engine system and the duct system. The flight vehicle may generally select a proper type and specific engine with acceptable thrust level to meet the flight mission in the propulsion system design phase. In this study, a turbojet engine with one spool was selected by decision of the vehicle system designer, and the duct system is composed of main duct, rotor duct, master valve, rotor tip-jet nozzles, and variable area main nozzle. In order to establish the safe flight mode transition region of the propulsion system, steady-state and transient performance simulation should be needed. Using this simulation model, the optimal fuel flow schedules were obtained to keep the proper surge margin and the turbine inlet temperature limitation through steady-state and transient performance estimation. Furthermore, these analysis results will be used to the control optimization of the propulsion system, later. In the transient performance model, ICV (Inter-Component Volume) model was used. The performance analysis using the developed models was performed at various flight conditions and fuel flow schedules, and these results could set the safe flight mode transition region to satisfy the turbine inlet temperature overshoot limitation as well as the compressor surge margin. Because the engine performance simulation results without the duct system were well agreed with the engine manufacturer's data and the analysis results using a commercial program, it was confirmed that the validity of the proposed performance model was verified. However, the propulsion system performance model including the duct system will be compared with experimental measuring data, later.

• Journal of Aerospace System Engineering
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• v.8 no.3
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• pp.20-26
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• 2014

This paper presents the procedures and the results of the pitch control force via flight test for a light airplane in order to make out the stability of the aircraft and the compliance with concerned regulation. The flight test procedures were determined in order to obtain the aircraft type certification. The instrumentation equipments including airspeed indicator, accelerometer, and pitch control force measurement tools are used to perform the flight test. For the flight test, the airspeed and the pitch control force with related normal acceleration are measured sustaining turn flight with bank angle derived from trim speed. The flight test results showed that the handling qualities of the airplane are complied with the KAS-23, the regulation of the Korean government for the light airplane type certification.

• Journal of information and communication convergence engineering
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• v.9 no.6
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• pp.625-628
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• 2011

Dynamic sensor network(DSN) technology which is based on swarming flight type air node offers analyzed and acquired information on target data gathered by air nodes in rotation flight or 3 dimension array flight. Efficient operation of dynamic sensor network based on air node is possible when problems of processing time, data transmission reliability, power consumption and intermittent connectivity are solved. Delay tolerant network (DTN) can be a desirable alternative to solve those problems. DTN using store-and-forward message switching technology is a solution to intermittent network connectivity, long and variable delay time, asymmetric data rates, and high error rates. However, all processes are performed at the bundle layer, so high power consumption, long processing time, and repeated reliability technique occur. DSN based on swarming flight type air node need to adopt store-and-forward message switching technique of DTN, the cancelation scheme of repeated reliability technique, fast processing time with simplified layer composition.

• Journal of Institute of Control, Robotics and Systems
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• v.17 no.1
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• pp.54-60
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• 2011

The flight control law designed for prototype aircraft often leads to degraded stability and performance, although developed control law verify by non-real time simulation and pilot based evaluations. Therefore, the proper evaluation methods should be applied such that flight control law designed can be verified in real flight environment. The one proposed in this paper is IFS (In-Flight Simulator). Currently, this system has been implemented into the F-18 HARV (High Angle of Attack Research Vehicle), SU-27 and F-16 VISTA (Variable stability In flight Simulation Test Aircraft) programs. The IFS necessary switching control law such as fader logic and integrator stand-by mode to reduce abrupt transient and minimize the integrator effect for each flight control laws switching. This paper addresses the concept of switching mechanism with fader logic of "TFS (Transient Free Switch)" and stand-by mode of "feedback type" based on SSWM (Software Switching Mechanism). And the result of real-time pilot evaluation reveals that the aircraft is stable for inter-conversion of flight control laws and transient response is minimized.

• Journal of Institute of Control, Robotics and Systems
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• v.22 no.9
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• pp.759-765
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• 2016

This paper presents the principle, dynamics modeling and control, hardware implementation, and flight test result of a hybrid-type unmanned aerial vehicle (UAV). The proposed UAV was designed to provide both hovering and fixed-wing type aerodynamic flight modes. The UAV's flight mode transition was achieved through the attitude transformation in pitch axis, which avoids a complex rotor tilt mechanism from a structural and control viewpoint. To achieve this, a different navigation coordinate was introduced that avoids the gimbal lock in pitch singularity point. Attitude and guidance control algorithms were developed for the flight control system. For flight test purposes, a quadrotor attached with a tailless fixed-wing structure was manufactured. An onboard flight control computer was designed to realize the navigation and control algorithms and the UAV's performance was verified through the outdoor flight tests.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.19 no.2
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• pp.58-63
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• 2011

A Continuous Descent Approach(CDA) is defined as a simple, cost-effective, noise and emission abatement technique for any powered aircraft on approach. CDA also can be optimised within energy, speed and safety constraints by avoiding unnecessary flap, air brake and engine thrust. This study includes comparison on fuel consumption between Continuous Descent type and Step Down type by using flight data. In particular, we investigated fuel flow per hour, calibrated airspeed and pressure altitude for all flight time. During descent flight, the fuel consumption of Continuous Descent type was less than the fuel consumption of Step Down type.