• 한국항공운항학회지
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• 제14권2호
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• pp.9-16
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• 2006

FAA AC120-40B Level D flight dynamics model for T-50 Full Mission Trainer was successfully developed. Since AC120-40B Level D requires the quantitative validation tests for simulation model compared with flight test data, T-50 flight test data for each validation test item was gathered, and also automatic test environments which include AFT (Automatic Fidelity Tester) and STA (Simulation Test Analyzer) were developed. The final test results after the iterative test-tuning processes were all within the tolerances specified in AC120-40B Level D. Qualification Test Guide, QTG contains the detail test processes and results.

• 한국직업건강간호학회지
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• 제21권1호
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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.

• 한국항공우주학회지
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• 제44권12호
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• pp.1035-1042
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• 2016

상용 비행시뮬레이션 게임 엔진 X-Plane을 이용하여 구성한 비행시뮬레이터에 대해 FTD level 5를 만족시킬 수 있는 QTG작성에 대해 연구하였다. 모델은 Cirrus사(社)의 SR-20을 대상으로 하였다. QTG의 테스트항목 중에는 조종반력을 측정하는 항목도 있다. 따라서 Brunner사(社)의 CLS(Control Loading System)을 조종 장치에 설치하여 조종반력을 측정할 수 있도록 구성하였다. X-Plane은 자체적으로 트림루틴을 제공하지 않으므로 외부에서 Autopilot을 구성하여 항공기가 트림상태에 도달할 수 있도록 하였다. 또한 테스트를 자동으로 수행할 수 있는 알고리듬을 개발하여 수동으로 조종하여 테스트하는 번거로움을 피하고 같은 테스트를 같은 조건으로 진행할 수 있도록 하였다. FTD Level 5의 경우 실제 비행데이터가 아닌 alternative data source를 적용할 수 있으며 이를 활용하여 모든 테스트 결과가 주어진 범위를 만족하였다.

• 한국항공우주학회지
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• 제37권4호
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• pp.406-412
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• 2009

헬리콥터 시뮬레이터용 비행 시뮬레이션 모델은 비행 성능과 조종특성에 직접적인 영향을 주는 핵심 모델 중 하나로서, 헬리콥터 설계/제작사로부터 원천 자료 및 모델을 확보하여 개발하는 것이 일반적이다. 본 연구에서는 일반적인 개발 방식과는 다르게 헬리콥터 운용/정비 관련 가용한 자원을 활용하여 기본 모델을 구성하고 이를 비행시험 결과와 비교 튜닝하여 검증하는 방법을 채택하였다. 즉, 대상 헬리콥터인 KA-32T의 제작사로부터 헬리콥터 데이터를 확보할 수 없는 현실을 감안하여 정비교범, 비행교범, 해석, 실측, 논문 등을 기준으로 비행 시뮬레이션 기본 모델을 개발하였다. 이후 기준 데이터 획득을 위해 KA-32T를 대상으로 비행시험을 수행하였으며, 시뮬레이션 결과를 획득된 비행시험 결과와 비교 튜닝하여, 개발된 비행 시뮬레이션 모델이 FAA AC120-63 Level C 규격에 적합한 충실도를 보유함을 검증하였다.

• 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.

• 환경영향평가
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• 제18권3호
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• pp.143-150
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• 2009

The present study investigates the effects of the flight paths of military aircraft on noise map and its WECPNL(Weighted Equivalent Continuous Perceived Noise Level) distribution. Aircraft noise modeling and simulation have been performed on a Korean military air base by means of INM(Integrated Noise Model) with the input data of airfield location, aircraft specifications, flight paths and aircraft's operation schedules. The result of noise modelling has been verified in comparison with the result of measured noise level. The flight path of military aircraft, as the key parameter of the present study, was modeled by combining takeoff, overfly, approach and touch-and-go modes. The present INM simulations have been conducted for various flight path cases with different takeoff, approach modes and overfly modes. The simulation results showed that the change of flight path can remarkably affect the noise influence region and the WECPNL distribution around the airfield.

• 항공우주시스템공학회지
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• 제8권3호
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• pp.47-54
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• 2014

This is a research on the method of how to improve stall characteristics for the small general aviation airplanes to meet the FAR part 23 requirements. This research is based on the experience of certification flight tests of KC-100 airplane for Korea type certification. KAS/FAR Part 23.201/203 are the stall characteristics requirements. 23.201 requires to show the stable stalling tendency of the wings level stall and 23.203 requires to show the stable stalling tendency of stall characteristics during turning flight. In this paper, the stall characteristics requirements, improvement methods and flight test experience of KC-100 airplane for type certification.

• 한국항공운항학회지
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• 제22권1호
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• pp.22-31
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• 2014

Military UAV(Unmanned Aerial Vehicle) operated as a RC(Remotely Control) model level within the limit of the military special use airspace until now. However, the high and medium altitude of URA(Unmanned Reconnaissance Aircraft) which the ROKAF have been trying to import recently is at the UAV level and needs the criteria for the classified airspace flights. The required flight criteria includes operator location, mission operation limit, equipment, etc., which are the principle and standard applied based on the airspace use for UAV. Also, the general flight rules, visual flight rules, instrument flight rules are required in order to have to be applied to the actual flight. Besides, an appliance regulation needs to be arranged regarding two-way communication, ATC and communication issue, airspace and area in-flight between UAS( Unmanned Aircraft System) users. An operation of the UAV in the air significantly requires the guarantee of the aircraft's capacity, and also the standardized flight criteria. A safe and smooth use is ensured only if this criteria is applied and understood by the entire airspace users. For the purpose, a standardized military UAV flight operations criteria that is to be applied for each airspace by UAV is to be prepared through analysis of the present state, a legend UAV system, and a special character analysis.

• 한국항공우주학회지
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• 제35권9호
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• pp.783-791
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• 2007

FAA AC 120-63 등급 C 또는 FTD 등급 5에 규정된 헬리콥터 모의 비행 훈련장치에 사용될 단일 로터 회전익기의 수학적 모델에 대해 고찰하였다. 선정된 비행 운동 모델의 비행 운동 성능 평가를 통해서 그 유용성을 파악하였다. 이로부터 훈련은 물론 조종 성능시험이 가능한 비행 훈련장치 개발을 통해서 헬리콥터 비행성 평가를 위한 모의 비행 시험환경을 구현하였다.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2003년도 ICCAS
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• pp.2560-2565
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• 2003

The paper presented here covers the work associated with the flight control law design, ground based and in flight simulation and handling qualities assessment of the Fly-by-Wire type Aircraft (FBWA). The control law was designed for the most unstable aircraft configuration flight regime for the target aircraft (FBWA). The ground based simulation including math-model, real-time pilot-in-the-loop and iron bird simulation were used for validation of the control law before the experimental in-flight simulation on the IFS (In.Flight-Simulator) aircraft. The flight tests results showed that Level 1 handling qualities for the most unstable flight regime were achieved.