• 한국항행학회논문지
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• 제12권6호
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• pp.559-566
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• 2008

본 논문에서는 UAV를 포함한 모든 항공기를 위한 음성지시기반의 새로운 이륙시스템의 구현을 제안한다. 본 이륙제어 시스템은 음성인식, 환경결정, 명령수행으로 구성된다. 음성인식기술을 도입함으로써 제안된 이륙시스템은 조종사에게 단순화된 이륙과정과 더욱 신뢰할 수 있는 편리한 이륙제어 수단을 제공한다. 이 새로 제안된 음성인식기반 이륙 시스템은 이륙과정에서 발행할 수 있는 조종사 실수나 출발지연과 같은 문제를 감소시킴으로써 사고를 예방할 수 있고 궁극적으로는 항공안전에 크게 기여할 수 있다는 장점을 갖는다.

• 한국항행학회논문지
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• 제27권5호
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• pp.658-665
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• 2023

이륙중량은 항공기의 탄소 배출량과 연료 소모량을 추정할 때 정확도를 향상시킬수 있는 중요한 열쇠이다. 하지만 이륙중량은 항공사의 경영전략을 유추할 수 있는 민감한 유상하중 정보가 포함되어 있어 외부 유출이 불가능하다. 선행연구에서 이륙중량을 추정할 수 있는 몇 가지 모델이 제시되었지만, 연구자는 알 수 없는 조종사가 설정하는 변수들에 의해 연구의 한계가 존재한다고 지적한다. 본 연구에서는 이러한 한계를 통제할수 있는 방법을 제시하기 위해 이륙중량과 연관된 여러 변수를 확인하였다. 그중 이륙중량의 정확도를 향상시킬수 있는 변수를 선별하였고 이를 상용화된 ADS-B 정보에 적용하여 추정 방법을 제시한다. 제시하는 추정 식은 평균적인 이륙중량을 추정하는 것이 아니라 이륙중량 범위 내의 모든 구간에서 추정을 할 수 있다.

• 한국기계가공학회지
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• 제19권11호
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• pp.87-93
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• 2020

A key component of aviation safety is to eliminate the errors in commercial aircraft air data systems to ensure stable aviation operation. Although the technical aspects such as the maintenance and inspection play a pertinent role, human errors are expected to have a similar or even larger influence on the aviation safety. Aviation maintenance and inspection tasks are often performed by a complex organization, in which individuals perform a variety of tasks in an environment involving time pressure, sparse feedback, and complex conditions. These situational characteristics, combined with the general tendency of human error, may lead to various types of errors, which may have critical consequences such as accidents and loss of life. For instance, if an amber message "IAS DISAGREE" is displayed on the primary flight display while the aircraft is rolling on the runway to takeoff, the crew immediately performs a rejected takeoff operation and troubleshoots the air data system. This paper proposes alternative approaches to address the occurrence of defects due to the human factors involved in the practical processes of the air data system of commercial aircraft.

• 제어로봇시스템학회논문지
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• 제21권7호
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• pp.691-698
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• 2015

Inertial Navigation Systems (INS) are widely used as the main navigation device for aircraft. To get the initial attitude, the INS requires the initial alignment before navigation starts. An aircraft also needs an engine test procedure that causes some vibrations before flight. An INS can't be aligned in a vibration environment so the initial alignment is performed before the aircraft engine test. Therefore, the initial alignment time of an INS has been a major factor in limiting an aircraft's takeoff response time. In this paper, we designed an initial alignment algorithm that can be executed even in disturbances such as aircraft run-up. We demonstrated verification of the algorithm that is embedded on the real INS and testing methods to evaluate the alignment of the INS. We also analyzed the test results of the proposed initial alignment algorithm that is performed during a real aircraft run-up.

• 한국항행학회논문지
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• 제26권5호
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• pp.272-280
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• 2022

항공모함은 해상에서 항공기지 역할을 하는 전투함으로 항공기를 운용하는 군용함정으로 탑재된 항공기를 통하여 전투를 수행한다. 해군은 2033년경 수직이착륙 전투기와 헬기를 탑재할 수 있는 4만 톤급의 경항공모함 운용계획을 제시하였는데 본 연구는 이러한점에 착안하여 해외사례를 기초로 우리나라에서 경항공모함을 운영에서 요구되는 항공지원시스템 가운데 항공관제장비의 운영에 대해 고찰하였다. 필수장비로 공역 관제를 위한 PriFly, TWR의 ILARTS, ILM와 접근관제를 위한 ASR, PAR, LAAS 또는 RNAV, PALS(JPALS) 이 필요하며, 항행안전시설을 위한 URN-25 TACAN, ICLS(El/Az), ACLS OLS, MOVLAS, IFLOLS 등과 함께 통신네트워크를 위한 LINK-16 및 CEC, SATCOM이 요구되며, 적아 식별장비의 구축이 요구된다. 본 연구는 2부로 구성되며 2부에서는 구체적인 항공모함에서의 관제 방법을 기술할 것이다.

• Advances in aircraft and spacecraft science
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• 제8권1호
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• pp.17-30
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• 2021

This is an investigation for a more electric regional aircraft, considering the ATR 72 aircraft as an example and the electrification of its four double slotted flaps, which were estimated to require an energy of 540 Wh for takeoff and 1780 Wh for landing, with a maximum power requirement of 35.6 kW during landing. An analysis and evaluation of three energy harvesting systems has been carried out, which led to the recommendation of a combination of a piezoelectric and a thermoelectric harvesting system providing 65% and 17%, respectively, of the required energy for the actuators of the four flaps. The remaining energy may be provided by a solar energy harvesting photovoltaic system, which was calculated to have a maximum capacity of 12.8 kWh at maximum solar irradiance. It was estimated that a supercapacitor of 232 kg could provide the energy storage and power required for the four flaps, which proved to be 59% of the required weight of a lithium iron phosphate (LFP) battery while the supercapacitor also constitutes a safer option.

• 한국항공운항학회지
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• 제29권1호
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• pp.74-81
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• 2021

UAM(Urban Air Mobility) systems have evolved in the form of helicopters in the 1960~1970s, tiltrotors in the 1980s, small aircraft transportation systems in the 2000s, and electric-powered Vertical Take-Off and Landing (eVTOL) in the 2010s; accordingly, the early heliport has evolved to its current form of a Vertiport. Vertical Takeoff and Landing Sites, Vertiports, are important factors for the successful introduction of UAM, along with the resolution of air traffic control (ATC), air security, and noise problems. However, there are no domestic or international installation standards and guidelines yet. Therefore, in this study, installation standards were prepared by referring to domestic and international case studies, ICAO standards, and MIT research papers. The study proposes to establish standards for Final Approach and Takeoff Area (FATO) as 1.5D, 1D for Touchdown and Lift-Off Area (TLOF), and 1.5D for Safety Area (SA). It also proposes to add "UAM Vertiport Installation Standards" to the 「Act on the Promotion and Foundation of Drone Utilization, Drone Act」.

• 대한전기학회:학술대회논문집
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• 대한전기학회 2004년도 하계학술대회 논문집 D
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• pp.2182-2184
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• 2004

This paper presents a systematic and straightforward fault estimation approach for process fault detection. isolation and accommodation. The approach includes the design of a reduced-order observer and an algebraic-fault estimator. The observer is designed for an unknown input and fault-free system, which is obtained by coordinate transformations of original systems with unknown inputs and faults. The observer information is devoted to- the fault estimation for fault detection and isolation. The fault estimates can be used to form an additional control input to accommodate the fault. The suggested scheme is verified through simulation studies performed on the control of a vertical takeoff and landing (VTOL) aircraft in the vertical plane.

• Advances in aircraft and spacecraft science
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• 제4권1호
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• pp.81-91
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• 2017

The performances of lifting surfaces are particularly critical in specific flight conditions like takeoff and landing. Different systems can be used to increase the lift and drag coefficients in such conditions like slat, flap or ailerons. Nevertheless they increase the losses and make difficult the mechanical design of wing structures. Morphing surfaces are a compromise between a right increase in lift and a reduction of parts movements involved in the actuation. Furthermore these systems are suitable for more than one flight condition with low inertia problems. So, flap and slats can be easily substituted by the corresponding morphing shapes. This paper deals with a genetic optimization of an airfoil with morphing flap with an already optimized nose. Indeed, two different codes are used to solve the equations, a finite volume code suitable for structured grids named ZEN and the EulerBoundary Layer Drela's code MSES. First a number of different preliminary design tests were done considering a specific set of design variables in order to restrict the design region. Then a RANS optimization with a single design point related to the take-off flight condition has been carried out in order to refine the previous design. Results are shown using the characteristic curves of the best and of the baseline reported to outline the computed performances enhancements. They reveal how the contemporary use of a morphing acting on the nose of the main component and the trailing edge of the flap drive towards a total not negligible increment in lift.

• 한국항행학회논문지
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• 제19권1호
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• pp.1-6
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• 2015

전 세계적으로 급속하게 증가하는 항공교통량으로 인해 ICAO는 기존의 항행장비를 위성항법 기반으로 대체해 나가고 있으며, 이의 일환으로 기존의 ILS를 이용한 이착륙 서비스를 GBAS 로 대체할 계획을 수립 하였다. GBAS는 활주로까지 항공기를 유도하는 정밀 접근 서비스와 공항 주위의 정밀위치정보 서비스를 제공하는 위성항법 보강시스템을 이용하여 ILS와 달리 한 개의 시스템으로 활주로의 수에 관계없이 요구 성능을 제공할 수 있으며 curved approach가 가능하다는 장점을 보유하고 있다. 본 논문에서는 태안비행장 비행시험을 통한 ILS접근 절차와 GBAS curved approach절차를 비교하여 비행시간 단축 및 연료 감소효과를 분석하였으며 실제 비행시험을 통하여 이를 측정 확인 하였다.