• 한국항공우주학회지
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• 제31권10호
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• pp.79-88
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• 2003

전자식 비행제어 항공기의 비행제어계설계, 지상 모의 시험 및 공중 모의 비행시험에 의한 비행성 평가를 수행하였다. 전자식 비행제어 항공기는 고등훈련기 형상을 가지며, 세로축 비행제어법칙은 수직가속도와 피치 각속도 추종시스템이며, 가로/방향축 비행제어법칙은 롤 각속도 및 가로가속도 추정시스템을 채택하였다. 대상항공기의 비행운동 평가는 공중모의 시험 항공기를 활용하였으며, 비행시험결과 최대불안정 영역에서는 Level 1, 착륙 접근 영역에서는 Level 1/2의 만족할 만한 비행성 결과를 보여 본 비행제어계 설계 타당성을 입증하였다.

• 한국항공운항학회지
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• 제28권2호
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• pp.1-11
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• 2020

This study was carried out to verify how much instructor's communication skill affects the student pilot's study motivation and satisfaction. The instructor's communication styles are classified into 3 groups by pre-analysis. Three types are cooperative type, control type and professional type. Intellectual cause, performance proficiency cause, social cause and stimulation avoidance cause are extracted and analyzed for the cause of study motivation. Cooperative and control type affected all of 4 factors of student's study motivation by influence analysis. Intellectual cause affected control and cooperative type positively, especially more to cooperative type. Performance proficiency cause also had positive influence to control and cooperative type. Stimulation avoidance cause didn't appear to affect all sub-classified 4 factors of instructor's communication type. Influence analysis of student's study satisfaction from instructor's communication style showed that independent variable affected all sub factors positively. Degree of positive influence affected the control type the most, cooperative type was the 2nd, and professional type was the 3rd.

• 한국동물학회지
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• 제16권1호
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• pp.43-53
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• 1973

年齡에 따른 미토콘드리아의 構造的變化를 調査하기 위하여 電子顯微鏡을 利用하여 배추흰나비, Pieris rapae L.의 飛筋을 觀察하였다. 미토콘드리아는 크리스타가 잘 발달되지 않은 A型과 크리스타가 복잡하게 발달된 B型의 두種類가 存在하였다. 羽化直後의 것에서는 A型과 B型미토콘드리아가 꼭같이 存在하였고 羽化後 10日 經過한 것에서는 B型미토콘드리아에 比하여 A型이 急速히 減少하였다. 羽化後 10日이 經過된 것의 筋細胞에서는 B型미토콘드리아가 年齡의 增加에 따른 微細構造的變化를 이르켰다. 이러한 老衰된 미토콘드리아의 微細構造的 變化像은 部分的으로 그 內膜이 髓　狀構造를 再形成하는 것으로 나타났는데 이것은 곧 年齡에 따른 退化를 意味한다. 髓　狀構造를 形成하는 것은 많은 同心圓體이며 이 同心圓體의 數와 크기는 年齡과 比例하면서 增加했다. 筋細胞의 細胞質에서 미토콘드리아 內로 侵入한 글리코겐 粒子는 同心圓體의 中央에서도 觀察되었다.

• 한국항공운항학회지
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• 제24권4호
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• pp.62-69
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• 2016

The purpose of this study is to develop questionnaire items for the Pilot Aptitude Personality Test(PAPT) which can predict the flight training achievement through personality and personal characteristics. To do this, we investigated the personality traits required to successfully conduct flight training for 30 flight instructors as a subject. The results were as follows: motivation, concentration, concentration, situational awareness, and concentration. Based on this, preliminary 300-item questionnaire was prepared by combining the existing studies related to pilot aptitude. Survey was conducted using preliminary questionnaire for 152 student pilots as a subject. As a result of the correlation analysis between the results of the questionnaire and the flight training, 16 questions were derived. Finally, factor analysis showed that the final 14 questionnaire items were confirmed. The internal concept of an item is categorized as personality, perception, and motivation. This study suggests that the pilot aptitude should be viewed from an extended point of view by analyzing individual characteristics and pilot aptitude in relation to flight training achievement.

• 제어로봇시스템학회논문지
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• 제13권7호
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• pp.694-702
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• 2007

The SSWM(Software Switching Mechanism) of I-processor concept using non-real time in-house software simulation program is an effective method in order to develop the flight control law in desktop or HQS environment. And, this system has some advantages compare to HSWM(Hardware Switching Mechanism) such as remove the time delay effectiveness and reduce the costs of development. But, if this system loading to the OFP(Operational Flight Program), the OFP guarantee the enough throughput in order to calculate the two control law at once. Therefore, the HSWM(Hardware Switching Mechanism) of 2-processor concept is necessary. This paper addresses the concept of HSWM of the HQS-PC interface using TCP/IP(Transmission Control Protocol/Internet Protocol) communication based on flight control law of advanced supersonic trainer. And, the fader logic of TFS(Transient Free Switch) and stand-by mode of reset '0' type are designed in order to reduce the abrupt transient response and minimize the integrator effect in pitch axis. The result of the analysis based on HQS pilot simulation using HSWM reveals that the flight control systems are switching between two computers without any problem.

• 항공우주시스템공학회지
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• 제9권1호
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• pp.12-18
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• 2015

The inter-conversion between different control laws in flight has a lot of risk. The SWM(Switching Mechanism) including logic and stand-by mode is designed to analyze the transient response of aircraft during inter-conversion between different control laws, based on the in-house software for non-real-time and real-time simulation. The SWM applies the fader logic of TFS(Transient Free Switch) to minimize the transient response of an aircraft during the inter-conversion, and applies the reset '0' type of the stand-by mode to prevent surface saturation due to integrator effect in the disengaged flight control law. The transition time is also important to minimize the objectionable transient response in the inter-conversion, as well as the transition control law design. This paper addresses the results of non-real-time simulation for the characteristics of transient response to different transition time to select the adequate transient time, and the real-time pilot evaluation, using SSWM(Software Switching Mechanism) and HSWM(Hardware Switching Mechanism), which is met for Level 1 flying qualities and assures safety of flight.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1994년도 Proceedings of the Korea Automatic Control Conference, 9th (KACC) ; Taejeon, Korea; 17-20 Oct. 1994
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• pp.271-276
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• 1994

In this paper we deal with a design of CCV adaptive flight control system having adaptive observer under the mircroburst circumstances. First, based on the observerbility indices of the controlled system, which is a general multi-variable one, the adaptive observer is constructed, and the unknown interactor matrix can be estimated by using the identified parameters. Next, CCV adaptive flight control law is calculated based upon the estimated ones. Finally, the proposed CCV adaptive flight controller is applied to STOL flying boat and numerical simulations under the microburst circumstances can be show to justify the proposed scheme.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2001년도 ICCAS
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• pp.148.3-148
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• 2001

This paper deals with a problem of decreasing the airspeed and the altitude of a transport aircraft using thrust only. Such a situation can occur, if the aircraft loses all hydraulic power that drives the control surfaces. A controller for flight path angle control is designed using the model following servo control method, which is a PI-type optimal regulator. For computer simulation, a simulation model that covers a range of flight envelope is made using given linear models and trim points at some flight conditions. Nondimensional aerodynamic coefficients, derivatives and trim points that are not at the given trim points are computed by linear interpolation. The model is effective in simulation where the trim point varies. Simulation using ...

• 제어로봇시스템학회논문지
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• 제11권3호
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• pp.262-269
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• 2005

Automatic landing of UAVs receives increasing interest these days, with increasing number of the developed UAV systems. In this paper, a glidepath tracking algorithm of the subscale UAV was proposed and the performance was analyzed. Flight data analysis shows that the existing autolanding flight control algorithm has a classical type glidepath control. This paper presents an alternative glidepath tracking strategy based on embedded flight control law. The performance of the proposed strategy was investigated through the TDP(Touch Down Point) error analysis with regard to various flight environment: steady headwind, atmospheric disturbance, communication transfer delay. It was verified that the proposed glidepath tracking strategy can be successfully applied to the practical autolanding of UAV systems.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2008년도 추계학술대회A
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• pp.762-767
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• 2008

Estimated values for maximum lift coefficients of a light airplane, ChanGong-91, derived from an analytical method using a test database, a computational fluid dynamic method, a wind tunnel test, and a flight test are compared. The DATCOM method and VSAERO code are applied as the analytical method and the computational fluid dynamic method, respectively, in order to estimate the maximum lift coefficients of a light airplane. The wind tunnel test is conducted using a 1/14.5 scaled model installed in a closed circuit type wind tunnel. For the flight test approach, the wings-level power-off stall tests are performed to obtain the maximum lift coefficients. As a point of reference for the flight test results of the maximum lift coefficients, the differences of both estimates derived from the DATCOM method and the wind tunnel test data are smaller than those derived from VSAERO.