• Journal of the Korean Society for Aviation and Aeronautics
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• v.26 no.2
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• pp.31-38
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• 2018

The pilot aptitude test so far has been conducted with a dichotomous concept of cognitive factor and non-cognitive factor, so it was not easy to explain concrete factors about pilot aptitude. Therefore, an integrated approach is needed to construct pilot aptitude test including all factors that can predict pilot aptitude. In previous study, we developed questionnaire items for the Pilot Aptitude Personality Test(PAPT) which can predict the flight training achievement through personality and personal characteristics. And those items were categorized as personality, cognition, and motivation factors. The flight training grades were correlated with all the test factors of the items, and the cognitive factors were high. As a result of the regression analysis, the total score of the three factors together accounted for 16% of the flight training grades. The results of the ANOVA showed that the cognition factors and motivation factors had significant effects on the completion of the flight training. The factors of PAPT predicted not only the completion of the flight training but also the flight performance. This is because the existing paper-pencil pilot aptitude test can only discriminate the flight training completion status. This is also a result of the fact that the introductory flight training consists of various factors including not only basic cognition but also personality and motivation.

• Korean Journal of Occupational Health Nursing
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• v.21 no.1
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• pp.66-75
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• 2012

Purpose: This study is aimed at obtaining the information on the physical fitness level of female flight attendants at a local airline. Methods: The subjects are 2,409 female flight attendants who have had medical examination and physical fitness tests at an airline medical center from January 2 to December 30, 2008. The independent variables include socio-demographic & behavioral characteristics, and medical examination results, whereas the dependent variable is their physical strength score representing their fitness level. Results: Factors that affect the fitness strength score are age, flight hours per year, and fasting blood sugar level. It is found that physical fitness level is higher when the subjects are over 35, on board for over 850 hours per year and their fasting blood sugar level is over 100 mg/dL. Conclusion: It is concluded that for the improvement of flight attendants' health, more exercise to develop cardio-respiratory endurance and muscular strength is needed, and further study needs to be done to develop fitness enhancement programs considering flight attendants' job characteristics, working years, and flight hours per year, and programs for those returning to their workplace after a long-term leave, and new employees.

• Journal of Institute of Control, Robotics and Systems
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• v.10 no.2
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• pp.139-144
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• 2004

The flight control system designed for an unmanned airship, which is under development by KARI, is in reduced. First, the dynamic characteristics of the airship are addressed, which are fairly different from those of the nominal aircraft. In order to implement autonomous flight for the unmanned airship, flight control logic is designed including autopilot and guidance law. The autopilot is designed under consideration of the velocity region of the unmanned airship. The guidance laws are implemented in main operational modes such as point navigation, station keeping and spiral up/down for emergency return. Their simulation results are also presented in order to validate performances of the flight control system.

• 제어로봇시스템학회:학술대회논문집
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• 1997.10a
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• pp.1659-1662
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• 1997

The objective of this paper is to estimate the aerodynamic derivatives of a single turbo-prop aircraft at a specified flight condition for the best deduction of the dynamic characteristics using modified maximum likelihood estimation method whcih is known to be unbiased, efficient, and consistent. The flight test data necessary to the estimation of aerodynamic derivatives is obtained by implementing the six degree of freedom nonlinear flight simulation to consider the effects of several control input types, control deflection amplitudes, and intensity of turbulence. The simulated data is added with the measurement noise, which is regarded as the actual flight test data.

• Journal of Institute of Control, Robotics and Systems
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• v.20 no.12
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• pp.1217-1224
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• 2014

This paper presents a modified track guidance algorithm for formation flight of multiple UAVs. The suggested guidance algorithm is the spatial version of the first order dynamic characteristics for a time-dependent system so the algorithm is able to generate a path without overshoot to track the desired line. A crucial design parameter is a spatial constant that controls the shape of the convergence to an assigned flight path similarly to a time constant. Reference flight trajectories are designed based on a two-dimensional vehicle model, and the performance of the proposed guidance law is verified by numerical simulation using rigid body UAV dynamics with MATLAB/Simulink Aerosim Blockset.

• 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.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.18 no.4
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• pp.1-8
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• 2010

In the aerospace field, the study on a morphing-wing is in progress to improve flight performance and perform multi flight mission. There are many concepts of morphing-wing such as camber-change, wing-twist, variable-span, and so on. In this study, the aerodynamic characteristics and flight control of an air vehicle with a variable-span morphing wing (VSMW) have been investigated. VSMW with symmetric span control(SSC) can increase cruising range of aircraft by reducing drag in various flight condition. VSMW with anti-symmetric span control(ASSC) can be used in the roll control of an aircraft. The flight control about pure rolling dynamic system and full dynamic system have been performed about the cruise missile.

• 한국전산유체공학회:학술대회논문집
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• 2007.04a
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• pp.14-16
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• 2007

A critical problem in the integration of stores into new and existing aircraft is the safe separation of the stores from the aircraft at a variety of flight conditions representative of the aircraft flight regime. Typically, the certification of a particular store/aircraft/flight condition combination is accomplished by a flight test. Flight tests are very expensive and do expose the pilot and aircraft to a certain amount of risk. Wind tunnel testing, although less expensive than flight testing, is still expensive. Computational Fluid Dynamics(CFD) has held out the promise of alleviating expensive and risk by simulating weapons separation computationally. The forces and moments on a store at carriage and at various points in the flow field of te aircraft can be computed using CFD applied to the full aircraft and store geometry. This study needs full dynamic characteristics study and flow analysis for securing store separation safety. Present study performs dynamic simulation of store separation with flow analysis using Chimera grid scheme which is usually used for moving simulations.

• Journal of the Korea Institute of Military Science and Technology
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• v.17 no.4
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• pp.430-435
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• 2014

This paper presents the case study of the airworthiness certification for the flight control system of tactical UAV. Airworthiness regulations for flight characteristics and design and construction based on the STANAG 4671 are selected, and safety assessment is performed. Stall protection on wing level and turning flight criteria, and flap interconnection system failures were analyzed and applied to the flight control system design. The Hardware-in-the-loop simulation including math model, integrated system verification and validation test and failure mode and effects test were also performed and they are used to validate the means of compliance of the proposed airworthiness.

• 제어로봇시스템학회:학술대회논문집
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• 2005.06a
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• pp.463-467
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• 2005

In this paper, the guidance law applicable to formation flight of UAV in three-dimensional space is proposed. The concept of miss distance, which is commonly used in the missile guidance laws, and Lyapunov stability theorem are effectively combined to obtain the guidance commands of the wingmen. The propose guidance law is easily integrated into the existing flight control system because the guidance commands are given in terms of velocity, flight path angle and heading angle to form the prescribed formation. In this guidance law, communication is required between the leader and the wingmen to achieve autonomous formation. The wingmen are only required the current position and velocity information of the leader vehicle. The performance of the proposed guidance law is evaluated using the complete nonlinear 6-DOF aircraft system. This system is integrated with nonlinear aerodynamic and engine characteristics, actuator servo limitations for control surfaces, various stability and control augmentation system, and autopilots. From the nonlinear simulation results, the new guidance law for formation flight shows that the vehicles involved in formation flight are perfectly formed the prescribed formation satisfying the several constraints such as final velocity, flight path angle, and heading angle.