• 대한전기학회논문지
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• 제35권10호
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• pp.458-464
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• 1986

This paper introduces a method for design verification and performance evaluation of flight control system. The method is a real time hardware in the loop simulation using the hybrid computer and motion table facility. As a typical illustration, a roll control system of flight vehicle is applied. The simulation validity is demonstrated by comparing hardware test results with analog simulation results.

• 한국항행학회논문지
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• 제23권4호
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• pp.281-288
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• 2019

비행시험은 항공기 개발 및 인증을 비롯한 항공기 수명 주기에서 감항성 유지를 위해 반드시 수행해야 하는 중요한 절차로서 관련 표준에 대한 적합성을 입증 또는 검증하기 위한 것이다. 비행시험 항공사고 분석 결과는 항공기 자체 요소뿐만 아니라 다양한 복합 원인에 의해 발생되었음을 확인한다. 국제민간항공기구는 항공기 사고 방지를 위해 안전관리시스템 구축 및 이행을 권고하고 있으나 비행시험의 특수성은 반영되어 있지 않다. 이에 항공선진국들은 이해관계자의 비행시험 안전관리 수행을 지원하기 위해 별도의 기준을 제공하고 있다. 본 논문에서는 국내 국가종합비행성능시험장 구축에 맞춰 항공선진국의 관련 규정을 조사, 분석하고 조직 구성, 안전 및 리스크 관리, 비행 운영, 인력 관리, 행정 사항 등의 내용을 포함하는 비행시험 운영 매뉴얼 개발을 위한 정부차원의 기준 안을 제시한다.

• 항공우주시스템공학회지
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• 제10권1호
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• pp.111-117
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• 2016

A new configuration of tiltrotor UAV previously suggested by Korea Aerospace Research Institute (KARI) for the purpose of increasing the endurance performance in airplane mode flight has extended wings attached to the nacelle and rotated with the nacelle according to the flight modes. In this research, the effectiveness of the extended wing on the enhancement of the endurance performance of KARI tiltrotor UAV (TR60) was analytically investigated based on CFD analysis results. Flight tests and ground tests of measuring the fuel consumption were also conducted to directly compare the endurance performance for the two configurations of TR60 baseline and TR60 extended-wing model.

• 한국항공운항학회지
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• 제14권3호
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• pp.1-6
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• 2006

The altitude engine test is a sort of engine performance tests carried out to measure the performance of a engine at the simulated altitude and flight speed environments prior to that at the flight test. During the performance test of a engine, various values such as pressures and temperatures at different positions, air flow rate, fuel flow rate, and the load by thrust are measured. These measured values are used to derive the representative performance values such as the net thrust and the specific fuel consumption through a momentum equation. Hence each of the measured values has certain effects on the total uncertainty of the performance values. In this paper, the combined standard uncertainties of the performance variables at the engine test were estimated by the uncertainty analysis of the measurement values and the repeatability and reproducibility of the altitude test measurement were assessed by the analysis of variation on the repeated test data with different operator groups.

• International Journal of Aeronautical and Space Sciences
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• 제18권4호
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• pp.740-756
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• 2017

This paper proposes a feedback-linearization-based control algorithm for multirotor unmanned aerial vehicles (UAVs). The feedback linearization scheme is highly efficient for considering nonlinearity between the rotational and translational motion of multirotor UAVs. We also propose a dynamic equation that reflects the aerodynamic effects of the vehicles; the equation's parameters can be determined through curve fitting using actual flight data. We derive the feedback linearization controller from the proposed dynamic equation, and propose a Luenberger observer to attenuate measurement noises. The proposed algorithm is implemented using our in-house flight control computer, and we describe its implementation in detail. To investigate the performance of the proposed algorithm, we carry out two flight scenarios: the first scenario, an autonomous landing on a moving platform, is a test of maneuverability; the second, picking up and replacing an object, test the algorithm's accuracy. In these scenarios, the proposed algorithm precisely controls multirotor UAVs, and we confirm that it can be successfully applied to real flight environments.

• Journal of Astronomy and Space Sciences
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• 제26권4호
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• pp.635-642
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• 2009

This paper describes the Flight Dynamics Automation (FDA) system for COMS Flight Dynamics System (FDS) and its test result in terms of the performance of the automation jobs. FDA controls the flight dynamics functions such as orbit determination, orbit prediction, event prediction, and fuel accounting. The designed FDA is independent from the specific characteristics which are defined by spacecraft manufacturer or specific satellite missions. Therefore, FDA could easily links its autonomous job control functions to any satellite mission control system with some interface modification. By adding autonomous system along with flight dynamics system, it decreases the operator's tedious and repeated jobs but increase the usability and reliability of the system. Therefore, FDA is used to improve the completeness of whole mission control system's quality. The FDA is applied to the real flight dynamics system of a geostationary satellite, COMS and the experimental test is performed. The experimental result shows the stability and reliability of the mission control operations through the automatic job control.

• 제어로봇시스템학회논문지
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• 제17권8호
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• pp.833-842
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• 2011

The objectives of this research are development of guidance, navigation and control system for RUAV on virtual instrumentation and real flight test. For this research, the system is divided to DAQ (data acquisition) section, actuator section and controller section. And the hardware and software on each sections are realized on LabVIEW base. Waypoint guidance and control of auto flight are realized using PID gain tuning and waypoint vector tracking guidance algorism. For safe flight test, auto/manual switching module isolated from FCS (Flight Control System) is developed. By using the switch module, swift mode change was achieved during emergency flight case. Consequently, a meter level error of flight performance is achieved.

• 드라이브 ㆍ 컨트롤
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• 제20권3호
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• pp.25-34
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• 2023

In this study, we conducted a research on optimizing the spraying performance of agricultural drones and predicted the spraying performance in various flight conditions using the multi-layer perceptron (MLP). Data was collected using a test device for pesticide spraying performance according to the water sensitive paper (WSP) evaluation. MLP training involved supervised learning to achieve a coefficient of variation (CV), which indicates the degree of uniform spraying. The performance evaluation was conducted using R-squared (R²), the test samples showed an R² of 0.80. The results of this study showed that drone spraying performance can be predicted under various flight environments. In addition, the correlation analysis between flight conditions and predicted spraying performance will be useful for further research on optimizing the spraying performance of agricultural drones.

• 한국항공우주학회지
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• 제37권4호
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• pp.406-412
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• 2009

헬리콥터 시뮬레이터용 비행 시뮬레이션 모델은 비행 성능과 조종특성에 직접적인 영향을 주는 핵심 모델 중 하나로서, 헬리콥터 설계/제작사로부터 원천 자료 및 모델을 확보하여 개발하는 것이 일반적이다. 본 연구에서는 일반적인 개발 방식과는 다르게 헬리콥터 운용/정비 관련 가용한 자원을 활용하여 기본 모델을 구성하고 이를 비행시험 결과와 비교 튜닝하여 검증하는 방법을 채택하였다. 즉, 대상 헬리콥터인 KA-32T의 제작사로부터 헬리콥터 데이터를 확보할 수 없는 현실을 감안하여 정비교범, 비행교범, 해석, 실측, 논문 등을 기준으로 비행 시뮬레이션 기본 모델을 개발하였다. 이후 기준 데이터 획득을 위해 KA-32T를 대상으로 비행시험을 수행하였으며, 시뮬레이션 결과를 획득된 비행시험 결과와 비교 튜닝하여, 개발된 비행 시뮬레이션 모델이 FAA AC120-63 Level C 규격에 적합한 충실도를 보유함을 검증하였다.

• 한국항행학회논문지
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• 제8권2호
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• pp.105-111
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• 2004

최근의 무인항공기는 정찰임무를 비롯하여 무인기에 미사일을 장착하여 지대공 공격 임무를 수행하기까지 군용으로 뿐만 아니라 기상 관측, 해상 관측 등의 목적으로 폭넓게 활용하고 있으며, 점차 필요성이 높아지고 있다. 이러한 무인기는 정밀한 자세제어를 위하여 자세정보를 제공하는 AHRS와 같은 센서를 장착하는데 비용이 500만원 정도에서 고급 센서는 수 천 만원에 이르고 있다. 최근 한국항공우주연구원에서는 이러한 고가의 센서 출력정보인 자세각 정보를 사용하지 않고 각속도 정보를 기반으로 저가형 자동비행시스템을 개발하여 소형표적기와 무인표적기 비행시험을 통하여 성능을 입증하였다. 본 논문에서는 무인항공기의 항법시스템 설계를 위하여 목표로 하는 신뢰성을 충족시키면 동시에 저가형인 GPS 센서를 선택하기 위하여 Hardware in the Loop Simulation(HILS)을 통하여 GPS 출력주파수에 따른 성능을 확인하였다. 마지막으로 무인표적기에 자동비행시스템과 항법시스템을 장착하여 비행시험을 수행하였으며, 설계된 항법시스템 성능을 비행시험 결과를 통하여 확인하였다.