• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2004년도 제22회 춘계학술대회논문집
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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.

• 제어로봇시스템학회논문지
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• 제11권11호
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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.

• 제어로봇시스템학회논문지
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• 제11권11호
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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.

• 한국의류산업학회지
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• 제23권1호
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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.

• 한국항행학회논문지
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• 제27권6호
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• pp.763-769
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• 2023

무인항공기용 비행제어컴퓨터는 높은 신뢰성이 요구되는 항전 장비로, 고장에 대한 마진을 위해 다중화 설계되는 것이 일반적이다. 다중화 된 비행제어컴퓨터는 채널 간 동기화 및 고장분리를 위해 디스크리트 신호 및 CCDL (cross channel data link)을 통한 인터페이스가 포함되어야 한다. 무인항공기 기술이 발전함에 따라 민간 및 군에서 AAM (advanced air mobility) 및 저피탐 등 다양한 형태의 플랫폼들이 개발되고 있으며, 이러한 플랫폼들은 고성능 비행제어를 위한 제어 성능 고도화 및 탑재장비의 SWaP (size, weight and power) 최적화를 요구하고 있다. 본 논문에서는 이러한 무인항공기용 최적화된 다중화 비행제어컴퓨터 아키텍처를 설계하고 입출력 제어를 위한 소프트웨어 설계를 수행하였다. 또한 구현된 비행제어컴퓨터와 입출력 소프트웨어를 통해 입출력 처리 성능을 평가 하였다.

• 한국항공운항학회지
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• 제18권4호
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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.

• 한국항행학회논문지
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• 제27권4호
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• pp.323-329
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• 2023

본 연구는 헬리콥터 조종사 교육에 있어서 성공적인 비행훈련 성과에 영향을 미치는 요인을 살펴보고자 한다. 이를 위해 탐색적 요인분석을 이용하여 개인의 인지적 특성과 비인지적 특성을 추출하고, 계층적 회귀분석을 통해 이러한 특성(요인)들이 비행훈련 성과에 얼마나 영향을 미치는지 알아보았다. 그 결과 공간지각능력, 회복탄력성, 숙달목표지향적 학습태도 성향이 높을수록 비행 교육성과에 긍정적인 영향을 미치는 것으로 나타났다. 이는 조종사에게 특히 요구되는 공간지각능력의 중요성을 재확인할 수 있었고, 그리고 제한된 조종석 공간에서의 비행교관의 역할, 개인의 올바른 동기부여와 노력이 비행훈련 성과에 영향을 미친다는 것을 재확인시켜준다. 이러한 결과는 향후 헬기 조종사의 효과적인 비행교육에 유용한 지표가 될 것으로 기대한다.

• 감성과학
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• 제26권4호
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• pp.29-40
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• 2023

불안은 주의 시스템의 균형을 깨트려 목표 지향 시스템보다 자극 주도 시스템을 우선하게 만드는 것으로 알려져 있으나, 자기 교시는 자기 조절의 효과로 목표 지향적 행동을 유도하게 한다. 본 연구는 가상현실 환경에서 현직 조종사를 대상으로 기상 및 자기 교시 조건이 조종사에게 발생하는 불안과 비행 과제의 수행에 미치는 영향을 검증하였다. 기상 조건은 시계비행 기상 상황과 악기상 상황으로 구분하였고 자기 교시의 수행 여부를 달리하여 비행 과제를 수행하게 하였다. 실험 결과 악기상 상황에서 불안과 심박수가 더 높고 비행 과제의 수행도가 더 낮은 것으로 나타났으나, 자기 교시를 수행하는 조건에서는 불안과 심박수가 더 낮고 비행 과제의 수행도가 더 높은 것으로 나타났다. 이 결과는 불안의 영향으로 비행에 어려움을 겪어 사고로 연결될 가능성이 증가할 수 있으나, 자기 교시에 의한 비행 수행의 향상으로 사고로 연결될 가능성이 감소할 수 있음을 시사한다.

• 한국항공운항학회지
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• 제13권2호
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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.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2003년도 제21회 추계학술대회 논문집
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• pp.215-218
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• 2003

본 연구에서는 회전익 상태에서 이/착륙, 저속 전진비행을 하고, 고정익 상태에서 고속 전진비행을 하는 스마트 무인기 추진시스템을 모델링하고 회전익 모드, 고정익 상태의 고속 비행모드, 팁 제트 노즐과 주 엔진 노즐을 모두 이용하는 혼합모드에 대해 정상상태 성능해석을 수행하였다.