• 대한조선학회논문집
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• 제61권2호
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• pp.125-134
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• 2024

The Safe Operating Envelope (SOE) combined with Short-Take-Off and Vertical Landing (STOVL) performance is an essential consideration of a light aircraft carrier for design of hull shape with excellent seakeeping performance in terms of naval air operations as well as traditional naval ship missions such as Transit and Patrol (TAP), and Replenishment at Sea (RAS) and so on. A variety of procedures are systematically combined to determine SOE considering rather complicated missions associated with operation of aircraft onboard. The evaluation of take-off and landing safety missions onboard should consider wind effect on deck and severer seakeeping indices and standards compared with conventional naval ships. In order to support take-off and landing missions, various support activities of the crews are required. So, additional evaluation is needed for indicators such as MSI(Motion sickness Index) and MII(Motion Induced Interruptions), which are quantitative indicators of work ability that appear as a result of motion response. In this study, a standard procedure is developed including the seaworthiness performance indicators, standards, and evaluation procedures that should be considered during design of STOVL aircraft carrier. Analysis results are discussed in terns of air-wake on deck as well as seakeeping indices associated with design parameter changes in view of conceptual design of a light aircraft carrier.

• 한국항공운항학회지
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• 제18권4호
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• pp.21-29
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• 2010

The main purpose of this study is to obtain linear models for the design of automatic flight controller in order to operate the Light Sport Aircraft as unmanned air vehicle. Flight test equipments installed on the aircraft to acquire flight test data are described and maneuvers for practical speed calibration are introduced. Parameters for the linear models of lateral and longitudinal motion are estimated by the Output error method as well as trim data analysis using the flight test data. Simulated data using the estimated parameters is shown to agree well with the measurement data. Estimated parameters obtained for several flight conditions can be used to improve the aerodynamic database of the simulation program.

• 한국항공운항학회지
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• 제21권3호
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• pp.41-45
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• 2013

In this study, we surveyed the operating status of the Runway for the Light Sport Aircraft(LSA) in Korea, and analyzed the Airfield Facilities Manual for the Air Leisure and the Standard Specification for Recreational Airpark Design. Based on the information, we presented the displacement of the threshold concept, to ensure the Runway Length and the Runway Safety Area, and operation of LSA in Korea.

• 한국항공운항학회지
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• 제21권1호
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• pp.62-67
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• 2013

Human Powered Aircraft (HPA) should be light in weight and have high efficiency because power source of propulsion is human muscles. Airframe structure takes up most of empty weight of aircraft, so weight reduction of structure is very important issue for HPA. In this paper, design/analysis/test procedures for ultra light weight structure of the HPA developed by Korea Aerospace Research Institute (KARI) are explained briefly. Structural design is conducted through case studies on HPA in the USA and Japan. Loads analysis is performed to calculate design loads which is needed for structural design and analysis. Structural analysis is conducted for structure sizing. Static strength test of main wing spar which is primary structure of wing is performed to verify structural integrity.

• 품질경영학회지
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• 제46권1호
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• pp.169-188
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• 2018

Purpose: The purpose of this study is to analyze low-temperature starting performance of the light attacker and to search and improve the aircraft system including battery and Battery Charge and Control Unit(BCCU). Methods: In order to improve the starting up performance of the light attacker at low-temp, various deficiency cause were derived and analyzed using Fault Tree Analysis method. As a result, it was confirmed there were drawbacks in the charging and discharging mechanism of the battery. The inactivation of the battery's electrolyte at low-temp and the premature termination of the battery charge were the main cause. After long error and trial, we improved these problems by improving performance of battery and optimizing the charging algorithm of BCCU. Results: It was confirmed that the problems of starting up failures were solved through the combined performance test of the battery and BCCU, the ground test using the aircraft system and the operation test conducted by Korea Airforce operating unit for 3 months in winter. Conclusion: This study showed that the improvement of quality reliability was achieved and thus the start-up performance issue of the light attacker has been resolved at low temperature. And it is expected that the design methodologies of temperature-affected electrical system of aircraft will contribute to the development of the aircraft industry in the future.

• 한국융합학회논문지
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• 제11권12호
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• pp.131-135
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• 2020

본 연구에서는 경비행기를 날게 하는 프로펠러인 3개 및 5개 또는 10개가 있는 날개의 모델들로서 공기 유동 해석을 하였다. Model A에 대해서는 5개의 날개들이 있는 유동 형상으로서 Model A가 가장 이상적인 공기의 흐름을 보이고 있다. 너무 많거나 적지도 않은 날개 수로 공기의 흐름이 가장 원활히 흐르는 형상을 나타내고 있다. 프로펠러 날개의 수가 적으면 적을수록 공기의 유동이 작아지는 것을 볼 수 있다. Model A는 공기 유동의 전면부에서 최대 0.5631 MPa의 압력을 받고 있다. 또한 Model B와 Model C는 0.5758 MPa 및 0.5589 MPa의 압력을 각각 받고 있다. 각 유동 모델들에 대한 압력 등고선들을 비교해 보면, Model B가 그 압력 분포가 제일 높은 것으로 볼 수 있다. 본 연구 결과를 활용하면 실제 시험을 하지 않고서도 공기 유동을 조사할 수 있다. 또한 경비행기 프로펠러의 미적인 융합 설계에 도움이 될 수 있다고 보인다.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1989년도 한국자동제어학술회의논문집; Seoul, Korea; 27-28 Oct. 1989
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• pp.972-978
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• 1989

Proposed is improved compact self-mixing type semiconductor-laser range finder, which measures mode-hop time interval (MHI). Measurement error caused by the fluctuation of MHI is greatly reduced by averaging many contiguous MHI's. The main cause of measurement error 1.5% at ranges from 0.1m to 0.8m is attributed to the optical phase change of a returned light from a focusing lens. Accuracy improvement by stabilization of the returned light is suggested.

• 항공우주시스템공학회지
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• 제6권2호
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• pp.7-12
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• 2012

De-icing system is essential for any aircraft to fly in icing conditions. So there are two kinds of aircraft-those that are certificated for flight in icing conditions and those that are not. Icing certification involves a rigorous testing program, and relatively few light aircraft carry this approval. From a legal perspective, aircraft that do not have all required ice protection equipment installed and functional are prohibited from venturing into an area where icing conditions are known. There are a few kinds of de-icing system. It is necessary to review the systems in point of aircraft certification considering the operational and safety issues.

• 한국콘텐츠학회:학술대회논문집
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• 한국콘텐츠학회 2008년도 춘계 종합학술대회 논문집
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• pp.324-327
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• 2008

본 연구는 항공안전기술개발사업의 일부로 진행되고 있는 소형항공기의 개발 및 BASA 인증사업의 경제적 타당성을 사전적 예비적으로 평가하고, 개발 대상 기종의 선정에 참고하게 하는 목적으로 진행되었다. 이러한 목적을 달성하고자 본 연구는 소형항공기 개발 및 BASA 인증사업의 진행에 소요되는 비용과 동 사업을 통하여 기대되는 직접적 경제적 효과인 민간 항공기수출을 통하여 얻는 국민 경제적 편익을 추정하였다. 비용과 편익은 후보기종별로 현금흐름액으로 추정되었으며, 이를 기초로 후보기종별로 소형항공기 개발 및 BASA 인증사업의 경제적 타당성을 검토하기 위한 편익/비용 비율 (B/C ratio), 순현재 가치(NPV), 내부수익률(IRR)을 산출하였다. 분석결과 후보기종인 VLJ급 항공기와 Piston 항공기에 의한 사업진행 모두 경제적 타당성이 있으며, 사업대상 후보기종 VLJ급 항공기와 Piston 항공기중 VLJ급 항공기에 의한 사업진행이 더 유리한 결과가 나타나는 것으로 분석되었다.

• 한국항공운항학회:학술대회논문집
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• 한국항공운항학회 2015년도 추계학술대회
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• pp.25-28
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• 2015

Aircraft conceptual design usually uses low to medium fidelity analysis to determine the basic configuration of an aircraft. Optimum solution is bounded by at least one of the constraints in most cases. This solution has risk to fail at later stage when analyzed with more sophisticated analysis tools. This research uses pre-constructed database to estimate the analysis prediction errors associated with simplified analysis methods. A possibility based design optimization framework is developed to utilize the newly proposed piecewise-linear fuzzy membership functions that compensate the discrepancies caused by simplified analysis. The proposed approach for aircraft design produces the optimum aircraft configurations that are less likely to fall into infeasible region when analyzed using higher fidelity analysis at later design stages.