• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.03a
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• pp.499-505
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• 2004

A Propulsion System of the CRW(Canard Rotor Wing) type UAV(Unmanned Aerial Vehicle) was composed of the turbojet engine to generate the propulsive exhaust gas, and the duct system including straight bent ducts, tip-jet nozzles, a master valve and a variable main nozzle for three flight modes such as lift/landing mode, low speed transition flight mode and high speed forward flight mode. In this study, in order to operate safely the propulsion system, the dynamic Performance behavior of the system was modeled and simulated using the SIMULIN $K^{ }$, which is the user-friendly GUI type dynamic analysis tool provided by MATLA $B^{ }$. In the transient performance model, the inter-component volume model was used. The performance analysis using the developed models was performed at various flight condition, valve angle positions and fuel flow schedules, and these results could set the safe flight mode transition region to satisfy the inlet temperature overshoot limitation as well as the compressor surge margin. Performance analysis results using the SIMULIN $K^{ }$ performance program were compared with them using the commercial program GSP.m GSP.

• Journal of Institute of Control, Robotics and Systems
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• v.11 no.11
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• pp.913-919
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• 2005

An advanced method of Relaxed Static Stability (RSS) is utilized for improving the aerodynamic performance of modem version supersonic jet fighter aircraft. The flight control system utilizes RSS criteria in both longitudinal and lateral-directional axes to achieve performance enhancements and improve stability. Standard CLDA (Control Law Design and Analysis) process is provided that reduce the development period of the flight control system. In addition, if this process is employed in developing flight control laws, it reduces the trial and error development and verification of control laws. This paper details the design process of developing a flight control law for the RSS aircraft, utilizing military specifications, linear and nonlinea, analysis using XMATH and ATLAS(Aircraft, Tim Linear and Simulation), handling quality tests using the HQS (Handling Quality Simulator), and real flight test results to verify aircraft dynamic flight responses.

• Journal of Institute of Control, Robotics and Systems
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• v.11 no.11
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• pp.963-969
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• 2005

An advanced method of Relaxed Static Stability (RSS) is utilized for improving the aerodynamic performance of modem version supersonic jet fighter aircraft. The flight control system utilizes RSS criteria in both longitudinal and lateral-directional axes to achieve performance enhancements and improve stability. The T-50 advanced trainer employs the RSS concept in order to improve the aerodynamic performance and the flight control law in order to guarantee aircraft stability, The T-50 longitudinal control laws employ the dynamic inversion and proportional-plus-integral control method. This paper details the design process of developing longitudinal control laws for the RSS aircraft, utilizing the requirement of MIL-F-8785C. In addition, This paper addresses the analysis of aircraft characteristics such as damping, natural frequency, gain and phase margin about state variables for longitudinal inner loop feedback design.

• Fashion & Textile Research Journal
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• v.23 no.1
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• pp.118-128
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• 2021

This study used a preliminary survey to help develop an ergonomic flight jacket that is suitable for the working environment and mission performance. The results are as follows. The ergonomic sleeve pattern was designed with a forward 165° incline that considers a shoulder joint direction suitable for the motion; in addition, a closely design opening provided warmth and safety from fire. As a result of the dimensional suitability, pilots evaluated that sleeve length and total length of the developed flight jacket were a little long (p<.01), while flight engineers and crew evaluated that those of the developed flight jacket were appropriate (p<.01). Pilots evaluated that chest circumference and waist circumference were large (p<.05), while flight engineers and crews evaluated that those of the developed flight jacket were appropriate. The evaluation of the motion suitability indicated that pilots, flight engineers and crew found the developed flight jacket more comfortable than the current flight jacket (p<.05, p<.01, p<.001). The evaluation of the usability of pockets and penholders indicated that pilots, flight engineers and crew found the developed jacket easier to use (p<.01). The flight engineers and crew evaluated that the appearance of the developed flight jacket was better than the current flight jacket (p<.05). The results of this study show that the difference of environment and mission performance has a significant influence on evaluation; therefore, it is necessary to develop separate military uniforms that included a winter flight jacket to reflect the needs of each group.

• Journal of Advanced Navigation Technology
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• v.27 no.6
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• pp.763-769
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• 2023

Flight control computers for unmanned aerial vehicles are avionics that require high reliability and are generally designed to be multiplexed for margins on failures. The multiplexed flight control computer should include an interface through discrete signals and CCDL for synchronization and fault separation between channels. With the development of unmanned aerial vehicle technology, various types of platforms such as AAM and LPI are being developed in the private and military, which require advanced control performance for high-performance flight control and SWaP optimization of onboard equipment. In this paper, we designed a optimized flight control computer architecture for unmanned aerial vehicles for multiplexing processing and performed a software design for input and output control. In addition, input/output processing performance was evaluated through the implemented flight control computer and input/output software.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.18 no.4
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• pp.92-99
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• 2010

This study aimed to provide empirical evidence about expert performance approach in aviation field and the results suggested that the amount of experience(e.g. total flight hour) is necessary but not sufficient index of a pilot's expertise or superior performance. 43 pilots participated and completed a spatial span task and SA (situation awareness) tasks. To explore the factors predicting the performance in routine and non-routine situations, discriminant analysis was conducted. The results of discriminant analysis indicated that different variables are related with the performance in routine and non-routine situation. The factors predicting performance in routine situation were the spatial span scores and total flight hours. On the other hand, the factors predicting performance in non-routine situation were age and the qualification for instrument flying. In real world, total flight time which represents the quantity of experience has been frequently used to predict flight abilities and as an important index of expertise. The results of this study suggest that these kinds of factors have to be used cautiously to predict the performance in abnormal situation.

• Journal of Advanced Navigation Technology
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• v.27 no.4
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• pp.323-329
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• 2023

This study aims to examine the factors influencing successful flight training performance in helicopter pilot education. To this end, an exploratory factor analysis was used to extract individual cognitive and non-cognitive characteristics, and a hierarchical regression analysis was conducted to find out how these characteristics (factors) affect flight training performance. As a result, it was found that the higher the spatial perception ability, resilience, and mastery goal-oriented learning attitude, the higher the flight training performance had a positive effect. This reconfirms the importance of spatial awareness, which is particularly required for pilots, and reconfirms that the role of a flight instructor in a limited cockpit space and the right motivation and effort of an individual affect flight training performance. These results are expected to be useful indicators for effective flight training of helicopter pilots in the future.

• Science of Emotion and Sensibility
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• v.26 no.4
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• pp.29-40
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• 2023

Anxiety is known to upset the balance of the attentional system and prioritize the stimulus-driven system over the goal-directed system; however, self-instruction induces goal-directed behavior with the self-regulation effect. This study verified the effects of meteorological and self-instruction conditions on pilot anxiety and flight task performance for in-service pilots in a virtual reality environment. The meteorological conditions were divided into visual meteorological and very low visibility conditions, and the flight tasks were conducted by varying whether or not self-instruction was performed. The experiment results reveal that anxiety and heart rate were higher, and the performance of the flight task was lower in the very low visibility condition. However, anxiety and heart rate were lower, and the performance of the flight task was higher in the self-instruction condition. This result suggests that accidents due to difficulty in flight may increase because of anxiety, but such accidents may decrease because of flight performance improvement by self-instruction.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.13 no.2
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• pp.14-26
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• 2005

A tilt-rotor aircraft has various flight modes : helicopter, airplane, and conversion. Each of flight mode has unique and nonlinear flight characteristics. Therefore the gain schedules for whole flight envelope are required for effective flight performance. This paper proposes collective, flap, and nacelle angle scheduler for whole flight envelope of the Smart UAV(Unmanned Air Vehicle) based on CAMRAD(Comprehensive Analytical Model of Rotorcraft Aerodynamics and Dynamics) II analysis results. The scheduler designs are improved so that the pitch attitude angle of helicopter mode was minimized. The range of scheduler are reduced inside of engine performance limits. The conversion corridor and rotor governor are suggested also.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.10a
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• pp.215-218
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• 2003

In this study, a performance model of the Smart UAV propulsion system with ducts, tip jets and variable main nozzle, which has flight capability of the rotary wing mode for the take-off/landing and low speed forward flight as well as the fixed wing mode for high speed forward flight, has been newly developed. With the proposed model, steady-state performance analysis was performed at various flight modes and conditions, such as rotary wing mode, fixed wing mode, compound wing, mode altitude and flight speed.