• 한국항행학회논문지
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• 제21권6호
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• pp.544-548
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• 2017

국제민간항공기구에서는 전 세계적으로 PBN 이행 촉구를 위해 2025년까지 모든 항공기의 SBAS 사용을 권고하고 있는 상황이다. 이에 국내에서도 한국형 SBAS인 KASS 개발이 진행 중에 있다. ICAO에서는 SBAS에 대한 인증 및 운용에 있어서 해당 항공 당국에 그 권한을 부여하고 있으며, KASS 또한 시스템 상세 설계, 제작, 설치 가 수행된 후 시스템에 대한 검증이 이루어 질 예정이다. 이에 본 논문에서는 국제 표준의 비행검사 규정을 통해 비행시험 파라미터를 도출 하였으며 이를 측정하기 위한 탑재측정장비의 구성방안에 대해서 제안 하였다.

• 한국군사과학기술학회지
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• 제15권4호
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• pp.507-512
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• 2012

Image blurring in airborne camera can be prevented through timely actuation of LOS(Line of Sight) into the opposite direction to the aircraft advancement, i.e. FMC(Forward motion compensation). Performance verification of FMC requires installation of camera to the aircraft. However, in many ways the verification process has little choice but to be implemented in the laboratory. In this paper verification method of FMC performance in the laboratory is introduced. With collimator target installed in the known reference position image obtained by actual mission plan naturally displays image blurring as well as LOS displacement by FMC effect. Through comparison of the amount of those image blurring and LOS displacement to the equivalent image distortion expected by the application of the FMC reference command can the performance be verified. In this paper we propose a new verification method of FMC performance in laboratory along with generalized solution of FMC reference command, and assess the validity of our proposition.

• 한국항공운항학회지
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• 제29권4호
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• pp.166-172
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• 2021

Obstacle Limitation Surfaces (OLS) are set to protect a certain amount of airspace to limit objects, such as building, other structures, penetrating OLS for safety and regularity of aircraft operations in the vicinity of aerodromes. However, many civil petitions have been raising for effective utilization of lands and permission of building construction which penetrating OLS. While Republic of Korea are limiting installation of penetrating objects based on the National law of airport facilities, such objects are possibly permitted, only if, the possible risks coming from objects are acceptable or negligible in terms of safety and regularity in aircraft operations through the evaluation process, called as an aeronautical study. However, many countries are currently applying their own criteria, processes resulting in failing secure reliable results in aeronautical study. This research aims to establish the framework on criteria, process, and methodologies how the aeronautical study works including work flows between many stakeholder and responsibilities to be specified in national regulation system.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2006년도 춘계학술대회논문집
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• pp.89-101
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• 2006

This study is a part of ???A study of the community noise:new guideline and policy' which have three main topics and ten sub-topics. Accordingly this part deals with a transpotation noise specifying road traffic ,railroad and aircraft noise, respectively. At first, the ,roadside traffic noise of whole country in 2004 ,22 major cities of total 29 was exceeded the envionmetal noise standards, 55dB(A) at night time ,therefore 24 milion people ,52.4% of korean, who reside at roadside estimates to be exposured the basic problems of this serious noise polluation comes from:: i)It's very limited noise mitigation measures against to continuously increase the number of automobile yearly. ii) and at beginning of road design, It has been neglect to introduce the anti-noise design and layout of road structural scheme as gadient,cutting and viaduct,embankment and zonning of roadside land-buffer area and also re-designation of noise sensitive areas,etc. Secondly ,concerned with the railroad trafffic noise, a inhabitants who are over the envionmetal noise limits,70dB(A), 65 dB(A) in day and night for 34 locations of mayor cities was exposured of 167,000 and 329,000 respectively. With the development of noise mitigation schemes in line with this study it is likely that noise monitoring system needs new installation as well as common use of noise assessment index with $L_{MAX}\;and\;L_{EQ}$. Lastly,noise complaints of millitary aircraft has been rapidly increasing ,so 2.9%(1.4 minion) person demands a compansation of \2,133 billion complying with their requirements we suggest to minimise the airport noise that is to develop of noise abatement procedure ,to make new noise index, to increase budget for house insulations and also to more increase of those the noise monitoring system and to unify the management etc.

• 한국항공우주학회지
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• 제43권3호
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• pp.187-194
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• 2015

탄도수정탄은 기존 포탄의 신관에 카나드가 장착된 조종 장치를 탑재하여 정확도를 향상시키는 지능탄이다. 본 논문에서는 2D 탄도수정탄의 카나드를 설계하기 위하여 다양한 형상 변수에 대한 공력성능을 반실험적 기법을 이용하여 분석하였으며, 이를 바탕으로 초음속에서 항력이 상대적으로 더 적은 카나드 형상을 설계하였다. 또한 CFD 기법을 통한 탄도수정탄의 공력해석 기법을 연구하였으며, 포탄의 탄저 부분 기저항력 예측에 O-type 격자를 바탕으로 한 k-${\omega}$ SST 난류모델이 적합함을 확인하였다. 최종적으로 앞서 개발한 해석 기법을 바탕으로 2D 탄도수정탄의 공력특성 및 탄도조종장치 장착에 따른 항력변화를 계산하였다.

• 한국항해항만학회:학술대회논문집
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• 한국항해항만학회 2006년도 International Symposium on GPS/GNSS Vol.2
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• pp.33-37
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• 2006

Since 1993, the civil aviation community through RTCA (Radio Technical Commission for Aeronautics) and the ICAO (International Civil Air Navigation Organization) have been working on the definition of GNSS augmentation systems that will provide improved levels of accuracy and integrity. These augmentation systems have been classified into three distinct groups: Aircraft Based Augmentation Systems (ABAS), Space Based Augmentation Systems (SBAS) and Ground Based Augmentation Systems (GBAS). The last one is an implemented system to support Air Navigation in CAT-I approaching operation. It consists of three primary subsystems: the GNSS Satellite subsystem that produces the ranging signals and navigation messages; the GBAS ground subsystem, which uses two or more GNSS receivers. It collects pseudo ranges for all GNSS satellites in view and computes and broadcasts differential corrections and integrity-related information; the Aircraft subsystem. Within the area of coverage of the ground station, aircraft subsystems may use the broadcast corrections to compute their own measurements in line with the differential principle. After selection of the desired FAS for the landing runway, the differentially corrected position is used to generate navigation guidance signals. Those are lateral and vertical deviations as well as distance to the threshold crossing point of the selected FAS and integrity flags. The Department of Applied Science in Naples has create for its study a virtual GBAS Ground station. Starting from three GPS double frequency receivers, we collect data of 24h measures session and in post processing we generate the GC (GBAS Correction). For this goal we use the software Pegasus V4.1 developed from EUROCONTROL. Generating the GC we have the possibility to study and monitor GBAS performance and integrity starting from a virtual functional architecture. The latter allows us to collect data without the necessity to found us authorization for the access to restricted area in airport where there is one GBAS installation.

• 한국항공우주학회지
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• 제46권9호
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• pp.782-789
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• 2018

한국형 기동헬기(KUH)의 다기능시현기(MFD)는 항공기 운용 중 임무컴퓨터(MC)로부터 영상정보(항법, 비행, 생존, 지형 및 정비 관련 정보)를 입력받아 시현한다. 체계개발 단계에서 식별된 MFD 이상시현(화면 깜박임 현상 등)은 항공기 초도양산 과정에서 DVI 케이블 차폐 성능 개선과 DVI 케이블 장착 경로 변경을 통하여 해소하였다. 항공기 납품 후 1~2년 정도 경과하였을 때 MFD 이상시현이 다시 발생하였고, 파생형헬기 시험평가 과정에서도 식별되었다. 이러한 MFD 이상시현의 해결을 위하여 항공기 체계 단위의 종합 검토를 수행하였고, DVI 케이블의 개선을 통한 설계 개선방안을 도출하였다. 본 논문에서는 MFD 이상시현의 발생원인을 분석하였고, 설계 개선방안 검토과정을 정리하였다. 그리고 설계 개선사항에 대한 타당성을 DVI 케이블 조립체 비교시험, SIL/지상/비행시험 결과를 바탕으로 입증하였다.

• Advances in aircraft and spacecraft science
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• 제3권3호
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• pp.243-257
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• 2016

The increase of air traffic volume has brought an increasing amount of issues related to carbon and NOx emissions and noise pollution. Aircraft manufacturers are concentrating their efforts to develop technologies to increase aircraft efficiency and consequently to reduce pollutant discharge and noise emission. Ultra High By-Pass Ratio engine concepts provide reduction of fuel consumption and noise emission thanks to a decrease of the jet velocity exhausting from the engine nozzles. In order to keep same thrust, mass flow and therefore section of fan/nacelle diameter should be increased to compensate velocity reduction. Such feature will lead to close-coupled architectures for engine installation under the wing. A strong jet-wing interaction resulting in a change of turbulent mixing in the aeroacoustic field as well as noise enhancement due to reflection phenomena are therefore expected. On the other hand, pressure fluctuations on the wing as well as on the fuselage represent the forcing loads, which stress panels causing vibrations. Some of these vibrations are re-emitted in the aeroacoustic field as vibration noise, some of them are transmitted in the cockpit as interior noise. In the present work, the interaction between a jet and wing or fuselage is reproduced by a flat surface tangential to an incompressible jet at different radial distances from the nozzle axis. The change in the aerodynamic field due to the presence of the rigid plate was studied by hot wire anemometric measurements, which provided a characterization of mean and fluctuating velocity fields in the jet plume. Pressure fluctuations acting on the flat plate were studied by cavity-mounted microphones which provided point-wise measurements in stream-wise and spanwise directions. Statistical description of velocity and wall pressure fields are determined in terms of Fourier-domain quantities. Scaling laws for pressure auto-spectra and coherence functions are also presented.

• 한국전자파학회논문지
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• 제27권3호
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• pp.253-260
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• 2016

본 논문에서는 항공기 탑재용 경량화 지지 구조를 갖는 평면 LPDA(Log-Periodic Dipole Array) 안테나를 제안한다. 제안된 안테나는 항공기 탑재에 적합하도록 가볍고, 구조적 진동에 견딜 수 있는 평면형 골격 지지 구조를 적용하여 설계하였다. 평면형 골격 지지 구조의 재질은 강도와 온도 특성이 우수한 Peek(Polyether ether ketone)를 사용하였으며, 제안된 안테나는 지지 구조 양면에 LPDA 안테나 방사소자를 결합하여 제작되었다. 지지 구조 유전체로 인하여 변화된 입력 임피던스는 일부 방사소자 간격과 길이를 조절하여 매칭시켰다. 설계된 평면 LPDA 안테나의 10-dB 반사손실 대역폭은 시뮬레이션 및 측정 결과, 각각 0.4~3.1 GHz(7.3:1), 0.41~3.5 GHz(8.2:1)로 광대역이었다. 평균 이득은 0.5~3 GHz 대역내에서 시뮬레이션은 평균 6.77 dBi, 측정은 6.55 dBi이었다. 따라서 설계된 안테나는 가볍고 견고한 구조와 광대역 지향성 방사특성을 가져 항공기 탑재 용도로 적합함을 확인하였다.

• 항공우주시스템공학회지
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• 제18권1호
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• pp.64-71
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• 2024

항공기 외부연료탱크는 항공기의 항속거리를 증가시키는 주요 구성품으로써, 비상시 파일런에서 안정적으로 분리될 수 있어야 된다. 이 때, 외부연료탱크의 핀(fin)과 피벗(pivot)에는 분리하중이 작용하게 되는데, 외부연료탱크의 안정적인 분리를 위해서는 핀과 피벗의 구조 건전성이 입증되어야 한다. 본 연구에서는 항공기로부터 외부연료탱크가 분리 될 때 외부연료탱크의 핀과 피벗의 구조건전성 검증을 위해 수행된 구조시험 결과를 제시하였다. 본문에서는 구조시험에 사용되는 유압 및 하중제어장비, 데이터 획득장치 그리고 공압공급장치로 구성되는 시험구성도를 설명하였고, 각 시험조건에 대한 시험설치와 시험하중 인가계획을 제시하였다. 구조시험 결과, 각 시험조건에서 시험하중과 시험체의 내부압력이 허용 범위 내에서 적절히 제어되는 것으로 파악되었고, 시험체에서도 심각한 구조적 결함이 발생하지 않았음이 확인되었다. 최종적으로, 설계 제한하중과 설계 극한하중에 대한 구조시험을 통해서 본 연구의 항공기용 외부연료탱크 핀과 피벗은 충분한 구조 강도를 보유하고 있음을 확인하였다.