• Journal of Advanced Navigation Technology
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• v.27 no.4
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• pp.391-395
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• 2023

Helicopter accidents due to spatial disorientation in low visibility conditions continue to persist as a major issue. These incidents often stem from human error, typically induced by stress, and frequently result in fatal outcomes. This study employs machine learning to analyze flight data and evaluate the efficacy of a flight illusion detection algorithm, laying groundwork for further research. This study collected flight data from approximately 20 pilots using a simulated flight training device to construct a range of flight scenarios. These scenarios included three stages of flight: ascending, level, and descent, and were further categorized into good visibility conditions and 0-mile visibility conditions. The aim was to investigate the occurrence of flight illusions under these conditions. From the extracted data, we obtained a total of 54,000 time-series data points, sampled five times per second. These were then analyzed using a machine learning approach.

• Proceedings of the Korean Association of Geographic Inforamtion Studies Conference
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• 2008.06a
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• pp.265-268
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• 2008

Lidar(Light Detection and Hanging, Ladar)는 물체에 반사되어 되돌아오는 광학신호를 관측하여 물체와의 거리를 측정하는 센서로 정밀한 3차원 모델 생성 및 도시지역의 변화탐지 등에 효율적으로 적용될 수 있다. 시뮬레이션은 시스템의 동작을 인공적으로 만들어 내고, 이 동작의 실행을 관찰하여 실제 시스템의 특성을 추론하는 일련의 활동으로, 하드웨어의 설계 및 분석, 보완, 성능 평가 등에 효율적으로 이용된다. 본 연구에서는 Lidar 시스템의 원리 및 구조 분석을 통해서 Lidar 데이터를 시뮬레이션하기 위한 소프트웨어를 설계하였다. Lidar의 특성이 시뮬레이션 소프트웨어에 정확하게 구현되도록 하기위해 Lidar 동작과 관련된 내부 및 외부요소를 분석하고 기능에 따라 추상화하여 소프트웨어 모들로 구성하였다. 시스템 내부요소로 송신부 수신부 신호/영상처리부 모델과 외부환경요소로 비행환경 모델, 타겟 모델, 대기 모델을 정의하였다. 또한, Lidar 시스템 실행 중에 발생하는 주요 프로세스를 함수 모듈로 정의함으로서, 모델들 간의 구조적인 관계를 정의하였다. 본 연구의 설계결과는 이후 Lidar시뮬레이션 소프트웨어의 보다 체계적인 구현에 적용될 예정이다.

• Journal of Advanced Navigation Technology
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• v.15 no.6
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• pp.1053-1058
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• 2011

In this paper, we propose a concatenated single antenna diversity system to assure the data transmission reliability between flight type air nodes which move according to their atypical orbit, then analyze its performance. The proposed system achieve a diversity gain using single antenna and a coding gain from convolutional code simultaneously. Simulation result about the bit error rate(BER) of the proposed system shows that its BER performance is about 9.5dB greater than convolutional code at $10^{-4}$ and about 14dB greater than space time block code at $10^{-3}$ which has a full diversity gain. In addition, compared with space time trellis code with diversity gain and coding gain, the proposed system shows the better 4dB at a BER of $10^{-5}$. Therefore, it is necessary that concatenated single antenna diversity should be adopted to the reliable data transmission of flight type air nodes.

• Journal of Aerospace System Engineering
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• v.17 no.1
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• pp.79-87
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• 2023

To design a control law of an aircraft, an accurate aircraft dynamic model is required. To obtain an aerodynamic database (DB) to build a dynamic model, a large number of wind tunnel tests are typically required. However, when flight test data of target aircraft exist such as in the process of unmanned conversion of a manned aircraft, an aircraft dynamic model can be obtained through a parameter estimation method and a DB tuning procedure. This paper describes a nonlinear model construction process and a verification method for KC-100 OPV aircraft. Flight data compatibility analysis was performed to determine suitability of the estimation method application. Linear model estimation was performed using the maximum likelihood estimation method. Results of aerodynamic DB tuning process and verification applying the FFS standard to the nonlinear model constructed are presented.

• Proceedings of the Korean Institute of Intelligent Systems Conference
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• 2003.09b
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• pp.105-119
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• 2003

일반적인 로봇시스템은 자신이 이동해야 할 목표 지점을 자율적으로 생성할 수 없으므로 어떤 다른 시스템의 정보를 이용하여 주변을 탐색하거나 장애물을 인식하고 식별하여 자신의 제어전략을 수립한다. 그러므로 본 논문에서 제시한 시스템은 초소형 비행체를 이용하여 주위 환경과 자율 이동로봇의 위치 정보를 탐색할 수 있도록 시스템을 구성하였다 이러한 시스템의 성능은 로봇이 위치하고 있는 주위의 불완전한 정보로부터 적절한 결론을 유도해 낼 수 있어야 한다. 그러한 비선형적인 문제는 현재까지도 문제 해결을 위해 많은 연구가 진행되고 있다. 본 연구에서는 자율이동로봇의 행동 환경을 공간상의 제약을 받지 않는 비선형 시스템인 초소형 비행체에 극초단파(UHF16채널) 영상장치를 이용하여 호스트 PC로 전송하고 호스트 PC는 로봇의 현재 위치, 이동해야 할 목표위치, 장애물의 위치와 형태 등을 분석한다. 분석된 결과 파라메타는 RF-Module을 이용해서 로봇에 전송하고, 로봇은 그 데이터를 분석하여 동작하게 된다. 로봇이 오동작 또는 장애물로 인해 정확한 목적지까지 도달하지 못할 때 호스트 PC는 새로운 최단경로를 생성하거나 장애물을 회피 할 새로운 전략을 로봇에게 보내준다. 본 연구에 적용한 알고리즘은 초소형 비행체에서 탐지한 불완전한 영상정보에서도 비교적 신뢰도 놀은 결과를 보이는 A* 알고리즘을 사용하였다 적용한 알고리즘은 실험을 통하여 실시간으로 정보를 처리할 수 있었으며, 자율 이동로봇의 충돌회피나 최단 경로 생성과 같은 문제를 실험을 통하여 그 성능과 타당성을 검토하였다.delta}textitH]$를 도출하였다.rc}C$에서 30 ㎫의 압력으로 1시간동안 행하였다 소결한 시편들은 직사각형 형태로 가공하였으며 표면은 0.5$\mu\textrm{m}$의 다이아몬드 입자로 연마하였다. XRD, SEM 및 TEM을 이용하여 상분석 및 미세조직관찰을 행하였다. 파괴강도는 3중점 굽힘 법으로 (3-point bending test) 측정하였다. 이때 시편 하부의 지지 점간의 거리는 30mm, cross-head 속도는 0.5 mm/min으로 하였고 5개의 시편을 측정하여 평균값을 구하였다.ell/\textrm{cm}^3$, 혼합재료 3은 0.123$\ell/\textrm{cm}^3$, 0.017$\ell/\textrm{cm}^3$, 혼합재료 4는 0.055$\ell/\textrm{cm}^3$, 0.016$\ell/\textrm{cm}^3$, 혼합재료 5는 0.031$\ell/\textrm{cm}^3$, 0.015$\ell/\textrm{cm}^3$, 혼합재료 6은 0.111$\ell/\textrm{cm}^3$, 0.020$\ell/\textrm{cm}^3$로 나타났다. 3. 단일재료의 악취흡착성능 실험결과 암모니아는 코코넛, 소나무수피, 왕겨에서 흡착능력이 우수하게 나타났으며, 황화수소는 펄라이트, 왕겨, 소나무수피에서 다른 재료에 비하여 상대적으로

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.7
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• pp.507-514
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• 2022

The EO/IR targeting pod mounted on a fighter to acquire information about tactical targets is typically mounted and operated at the bottom of the aircraft fuselage. Since the aircraft equipped with such an external attachment has complexed aerodynamic and inertial characteristics compared to the aircraft flying without an external attachment, a method of system performance analyses is required to identify development risk factors in the early stages of development and reflect them in the design. In this study, a development plan was presented to provide the necessary modeling and simulation tools to develop a pod that can acquire measurement data stably in a highly maneuverable environment. The limiting operating conditions of the pods mounted on the highly maneuverable aircraft were derived, the aerodynamics and inertial loads of the mounted pods were analyzed according to the limiting operating conditions, and a flight data generation and transmission system were developed by simulating the mission of the aircraft equipped with the mounted pods.

• The Journal of Korean Institute of Communications and Information Sciences
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• v.29 no.5B
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• pp.476-481
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• 2004

Since the bands 27.5 ∼ 28,350㎓ and 31.0 ~ 31.30Hz for existing fixed-satellite service were allocated to tile HAPS system in WRC-2000, the analysis on the interference effects between the existing FSS/GSO system and FS/HAPS system should be needed. To do study on the interference effects between above two systems, we can consider two frequency operational conditions, one is the Reverse mode, the other is Forward mode. In this paper, we analyzed the interference effects from airship of HAPS systems to satellite of the GSO system in the case of Reverse condition mode due to the C/I criterion, the latitude of HAPS and transmitting power of HAPS airship. In future, these results will be vital data to share between HAPS and GSO systems.

• Journal of Advanced Navigation Technology
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• v.27 no.5
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• pp.495-501
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• 2023

P-3C/K aircraft for maritime patrols that Republic of Korea Navy is using, is equipped with a variety of sensors and communication devices. Collected data from the aircraft is managed as tactical information by flight operators and stored. When the flight mission is completed, this information is transferred to tactical support center on the ground and played back or used for follow-up work through a analysis tool. During a flight mission, there are tens of thousands of detection objects within an hour in KADIZ (Korea air defense identification zone). In contrast, in TSD (tactical situation display), which displays a map when using the analysis tool, all detected objects are expressed as symbols. The increase in display symbols has a significant impact on the TSD image updating and consequently interferes with the smooth operation of operators. In this paper, we propose applying multiple threads and multiple layers to improve the performance of existing TSD. And the performance improvement is proven through the execution results.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.5
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• pp.406-414
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• 2014

In this paper, it is introduced characteristics of FMCW-type Radar Altimeter for KUH, and its defects occurred during ground/flight test in initial product phase. In addition, it is also described 'data/control flow model' based fault analysis results of S/W and processes of verifying improvement design through flight test as well as aircraft system integration test called MEP SIL. As a result of design improvement and verification, it is validated that settling the defects and improving not only safety but also capability of the KUH.

• Journal of Advanced Navigation Technology
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• v.28 no.1
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• pp.95-101
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• 2024

This paper aims to establish a reconfigurable flight simulation environment to conduct safety evaluation of various electric vertical take-off and landing (eVTOL) aircraft. Since the inceptor, aircraft dynamics model, and controller applied to each eVTOL aircraft are different, it was configured to be variable so that a simulation can be executed for each eVTOL aircraft. Test elements and performance indicators were set to perform safety evaluation of eVTOL aircraft. Ground auxiliary equipments were designed and implemented in a simulation environment according to test procedures for each test element. In addition, to analyze safety performance, a simulation flight data collection environment based on MATLAB/Simulink and a tool for safety performance analysis were implemented. Test flight and analysis were conducted in the implemented simulation environment in this paper. Finally, this study shows the environment was verified by confirming that it was performed normally.