• 항공우주시스템공학회지
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• 제7권3호
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• pp.15-19
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• 2013

Tail wing is important to designing of civil aircrafts, because it is responsible for aircraft stability and control. Tail wing has a role in aircraft control and makes aircraft fly stably without any pilot control input. Also, designing of tail wing determine trim drag force in whole aircraft. Center of gravity(CG) of aircraft travels with various effects as placement of passenger's seats, location of cargo bay, etc. In designing horizontal tail volume, aircraft CG travel has to be considered to have margin so that it should be sized to provide adequate stability and control for the airplane's entire CG range throughout the flight envelope. Finally, it is essential to have sufficient elevator control to perform stall at forward CG for all flaps down configurations. Such stalls establish the FAR stall speed which airplane take-off and landing performance. This paper deals with the process for tail wing design regarding the aircraft CG travel and results for 95-seat type turboprop aircraft.

• 항공우주정책ㆍ법학회지
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• 제18권
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• pp.325-362
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• 2003

군항공기사고조사의 전문성과 독립성을 제고하기 위하여 상설사고조사기구를 신설하여야 한다. 상설조사기구를 신설함으로써 조사기구의 위상을 높이고 조사의 신뢰성을 확보할 수 있다. 민과 군이 모두 관련된 사고조사시 민과 군의 조사권한의 주제, 업무협조 등에 관한 규율이 부재하고 있으므로 이를 입법화해야 한다. 군과 관련된 민항공기 사고조사시 군의 전문가들이 참여함이 바람직하다. 조사의 실효성 보장을 위하여 항공사고에 대한 정보를 직접 수집하는 조사관의 활동을 보장하는 규정을 마련해야 한다. 또한, 사고조사의 목적은 오직 사고예방에만 있으므로 정보의 공개범위를 제한하고 조사결과를 형사절차나 징계절차에서 사용할 수 없도록 하여 조사의 객관성을 확보해야 할 것이다.

• 비파괴검사학회지
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• 제30권1호
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• pp.54-59
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• 2010

After the advent of B787(Boeing Co.), a civil aircraft using composite materials more than 50% of it total structural weight for weight savings，best performances and efficiencies, various endeavors to develop and apply the state of art of structural health monitoring(SHM) technologies for composite aircraft have been made for many years. Despite their plentiful advantages composite aircraft structures are susceptible to the hidden or barely visible impact damages(BVID) and excessive loads that if unchecked may lead to lower structural integrity, loss of operational performance and finally a sudden catastrophic failure of the aircraft structure. In this paper background of SHM technology and relevant technologies for application of SHM technology to the composite aircraft in the near future and requirements for certification of SHM system are shortly presented.

• 한국항공운항학회지
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• 제23권3호
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• pp.35-41
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• 2015

Multilateration(MLAT) is commonly used in civil and military surveillance applications to accurately locate an aircraft, vehicle or stationary emitter. MLAT calculates the TDOA of signals by transmitted aircraft and determines the aircraft's location. With more than four receivers it is possible to estimate the 3D position of the aircraft by calculating the intersection of the resulting hyperbolas and the system integrity. In this study, our objectives are to apply MLAT technique to Jeju terminal control area and to propose a MLAT receiver network to properly estimate the positions of aircraft approaching this area. Based on computer simulations, we determine locations of ground receivers in Jeju terminal control area, calculate estimated position errors of the aircraft with respect to the selected receiver networks, and find the best receiver network with the least position error.

• 항공우주정책ㆍ법학회지
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• 제5권
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• pp.321-384
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• 1993

The paper is to study and analyze the civil aviation industry of China and to present some cooperative and developing models between Korea and China in the fields of civil aviation on the basis of mutul benefit. In this study, civil aviation includes both the air transport industry and aircraft manufacturing industry. As it is not easy and realistic for us to conduct field survey on the civil aviation of China so far, this study has havily depended upon the literature data gathered from the ICAO and other published materials. This study includes the following major contents. 1. The historical development of China civil aviation 2. The present status and future prospect of Civil Aviation Adminstration of China(CAAC) 3. The present status of Chinese aircraft industry 4. Administration of airport and airspace of China 5. Air transport industry of China 6. The design of Korea-China civil aviation cooperation

• 한국전산구조공학회논문집
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• 제26권2호
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• pp.157-164
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• 2013

본 연구에서는 여객용 항공기 충돌 시 강섬유보강콘크리트를 사용한 철근콘크리트 원전 격납건물의 구조적 거동을 유한요소해석을 이용하여 고찰한다. 항공기 충돌에 의해 원전 격납건물에 가해지는 하중은 Riera 충격하중 시간함수와 충돌 시 접촉면적을 이용하여 모델링하였다. 강섬유보강콘크리트의 재료모델은 CSCM Concrete Model을 사용하였다. 기존에 제안된 강섬유보강콘크리트의 강도예상모델을 이용하여 재료모델의 입력변수를 결정하였다. 강섬유의 함유량에 따른 원전 격납 건물의 항공기 충돌에 대한 구조적 거동을 상용 유한요소 해석 프로그램인 LS-DYNA를 이용하여 해석하였다. 해석결과를 바탕으로 항공기 충돌에 대한 저항성을 평가하였으며, 보수적인 안전성이 요구되는 원전 격납건물에 강섬유보강콘크리트를 적용할 경우 항공기 충돌에 대한 저항성 증대 효과를 기대할 수 있는 것으로 고찰되었다.

• 한국항공운항학회지
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• 제9권2호
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• pp.63-76
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• 2001

The number of civil aviation aircraft registered in Korea has continuously increased. Accordingly the accidents accompanying loss of human or economic resources occurred repeatedly. But the analysis of flight data recorded in FDR was not done by ourselves in the accident investigation because of lack of analysis technology. Therefore, this study is performed to secure the safety of civil aviation by establishing systematic analysis ability of Flight Data Recorder. Through this study, download flight data to personal computer, editing interface file to convert from binary data to engineering data, three dimensional graphical analysis and numerical analysis are performed. For the analysis, the flight of B747-400 model aircraft between Narita(Japan) and Gimpo(Korea) was selected.

• Structural Engineering and Mechanics
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• 제17권1호
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• pp.29-50
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• 2004

A total life model was developed to assess the service life of aging aircraft. The primary focus of this paper is the development of crack growth life projection using the response surface method. Crack growth life projection is a necessary component of the total life model. The study showed that the number of load cycles N needed for a crack to propagate to a specified size can be linearly related to the geometric parameter, material, and stress level of the component considered when all the variables are transformed to logarithmic values. By the Central Limit theorem, the ln N was approximated by Gaussian distribution. This Gaussian model compared well with the histograms of the number of load cycles generated from simulated crack growth curves. The outcome of this study will aid engineers in designing their crack growth experiments to develop the stochastic crack growth models for service life assessments.

• 항공우주기술
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• 제7권1호
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• pp.245-253
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• 2008

민간항공분야의 품질은 제품 및 공공의 안전을 유지하기 위해서 매우 중요하며, 항공기 설계와 생산 및 운항에 있어서도 엄격한 인증제도를 법적으로 규정하고 있다. 본 연구에서는 미국 FAA의 항공산업체의 품질시스템 평가프로그램인 ACSEP의 전반적인 검토를 통하여 항공기 및 항공부품에 대한 품질시스템 요구조건을 제시하고, 항공분야 품질시스템 평가에 대한 정책을 확인하였다.

• International Journal of Aeronautical and Space Sciences
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• 제17권2호
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• pp.268-283
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• 2016

Aircraft manufacturing companies have to consider multiple derivatives to satisfy various market requirements. They modify or extend an existing aircraft to meet new market demands while keeping the development time and cost to a minimum. Many researchers have studied the derivative design process, but these research efforts consider baseline and derivative designs together, while using the whole set of design variables. Therefore, an efficient process that can reduce cost and time for aircraft derivative design is needed. In this research, a more efficient design process is proposed which obtains global changes from local changes in aircraft design in order to develop aircraft derivatives efficiently. Sensitivity analysis was introduced to remove unnecessary design variables that have a low impact on the objective function. This prevented wasting computational effort and time on low priority variables for design requirements and objectives. Additionally, uncertainty from the fidelity of analysis tools was considered in design optimization to increase the probability of optimization results. The Reliability Based Design Optimization (RBDO) and Possibility Based Design Optimization (PBDO) methods were proposed to handle the uncertainty in aircraft conceptual design optimization. In this paper, Collaborative Optimization (CO) based framework with RBDO and PBDO was implemented to consider uncertainty. The proposed method was applied for civil jet aircraft derivative design that increases cruise range and the number of passengers. The proposed process provided deterministic design optimization, RBDO, and PBDO results for given requirements.