• Aerospace Engineering and Technology
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• v.12 no.1
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• pp.87-93
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• 2013

The conceptual design lunar lander demonstrator has been developed to use as a test bed for advanced spacecraft technologies and to test a prototype planetary lander capable of vertical takeoff and landing. Size of the lunar lander demonstrator is the same as that of lunar lander conceptually designed, however, the weight of lunar lander demonstrator is designed in 1/6 scale in consideration of gravity difference between moon and earth. The thruster clustering and virtual flight test were performed in the demonstrator fixed on the ground. The demonstrator ground test has been conducted for two months in the test site for the solid motor combustion of the Goheung Flight Center. The purposes of ground test of demonstrator are to demonstrate and verify essential electronics, propulsion system, control algorithm, embedded software, structure and system operation technologies before developing the flight model lander. This paper is described about the virtual flight test including test configuration, test aims and test facilities

• 제어로봇시스템학회:학술대회논문집
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• 1986.10a
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• pp.262-265
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• 1986

미사일의 동특성은 공력계수(aerodynamic coefficients)들의 구조 및 그 계수값에 의해 결정된다. 현재까지 공력계수는 풍동시험(wind tunnel test)에 의한 모형법으로 구하는 것이 보편적이었으나 모형과 실제 시스템의 차이에 의해 발생하는 오차, 풍동시험의 오차, 모형의 스케일 팩터(scale factor)오차, 실제 대기조건의 특성에 의한 오차 등에 의해, 시제품을 이용한 실제 비행시험 결과가 풍동시험 모델을 이용한 컴퓨터 시뮬레이션(computer simulation)의 가상 비행 데이타와 차이를 나타내게 된다. 이러한 차이를 감소시키기 위하여 필터 이론을 적용하기 위해서는 수학적 계수 모델이 필요하게 된다. 본 연구에서는 풍동시험모델로부터 3가지의 수학적 모델을 가정하고 이를 이용하여 확장칼만필터(extended Kalman Filter: EKF)와 최대공산법(maximum likelihood method :ML)을 각각 적용시켰을때 추정된 계수치에 의한 가상비행데이타와, 풍동시험모델에 의한 가상비행데이타를 비교하여, 수학적 계수 모델 설정에 따른 각 알고리즘의 추정결과를 알아보고, 이에의해 계수 모델 설정의 방법 및 기준, 그리고 계수구조 설정에 따른 EKF와 ML의 성질을 조사하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.3
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• pp.263-269
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• 2014

Flight test data visualization functions can improve an understanding of flight test results, test procedures, and the performance of a flight vehicle after flight tests. FlyingView was developed for researchers to analyse flight test data in a 3D virtual environment. It also can display X-Y plots using flight test data. It was developed and applied to flight tests of an air-to-ground weapon system of ADD. This paper describes the capabilities of FlyingView.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.3
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• pp.264-273
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• 2010

In this work, autonomous formation flight tests of multiple UAVs are experimentally studied. After a guidance and control system for a UAV is designed and tested, PID formation controller for follower UAV is tested using longitudinal and lateral distance feedback. It is shown that more stable and efficient formation guidance system is obtained by using position and attitude of the leader aircraft, which is exploited to calculate virtual waypoint for follower. In order to improve transient response during turn, part of roll command of the leader is added to the guidance command. Finally, autonomous formation flight test results of 3 UAVs are shown by using the best guidance algorithm suggested.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.1
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• pp.61-69
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• 2013

In an evaluation process of aircraft flying qualities, a clear and concise application interface is important since an evaluation process requires numerous repeated evaluation. This flight evaluation program have implemented efficient flight evaluation user interface along with changed trim condition interface and composed of comprehensive evaluation interface have mounted all automated FQ evaluation modules that was selected to be compose of 14 items in respect of an unmanned fixed-wing aircraft. Accordingly when it is necessary to design the flight control system as well as to develop a FQ considered aircraft, this S/W can be utilized as a tool that is a useful test evaluation S/W with scalability and enable to reduce the time and the cost of verification and evaluation process.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.7
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• pp.660-665
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• 2011

Reconfigurable Flight Simulator for an airborne tactical mission based on virtual reality technology is developed as a software configurable cockpit with computer display as virtual instruments. It can simulate F-15K, KF-16, T/A-50 class fighter and depending on simulated cockpit, control stick and throttle are replaceable. For effective immersion, Video See-Through type HMD is applied.

• Journal of Advanced Navigation Technology
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• v.18 no.4
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• pp.296-303
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• 2014

Recently a system is being required to replace ILS due to increasing air traffic. In this paper, Curved approach is applied to an airport where ILS approach cannot be applied due to its geographical condition and restricted aerospace condition, and verified by flight test. After analysing conditions of Tae-an airfield of Hanseo University with virtual ILS approach, airfield applicability was evaluated by Curved approach using by GPS. Normally simulation is performed after establishing approach procedure using electric map, but recently verification is being performed by flight test without simulation because accuracy and reliability are increased. In this paper, established procedure is verified modified by flight test with Pilot Test and Auto Pilot test and controllability and passenger's stability were also checked.

• Journal of Advanced Navigation Technology
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• v.27 no.4
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• pp.473-480
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• 2023

This study evaluated a novel method of defining the automatic flight path of unmanned aerial vehicles (UAVs) for search and rescue missions in a VR environment. The developed VR content reserves miniature digital twins of a building in the fire and a steep mountain terrain site. The users drow the UAV's scanning path using hand gestures on the surface of digital twins, and then the UAV make an automatic flight along the defined path. According to human-in-the-loop simulation tests comparing the novel method with a conventional manual flight task with 19 participants, the novel method did not improve the mission performance but participants felt a lower mental workload. The designer may need to consider the automation support on the vulnerable points of the SAR mission environment while maintaining experts' mapping capability.

• 한국항공운항학회:학술대회논문집
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• 2016.05a
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• pp.233-239
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• 2016

NASA(미국 항공우주청)를 중심으로 무인항공기교통관리(UTM) 체계를 이용한 드론 항공교통통제 모의시험을 진행하고 있다. 국내에서도 2017년부터 안전한 무인항공기교통관리(UTM) 체계 구축을 위한 '저고도 무인기 감시관리 기술 개발 및 시스템 시범 운용사업'을 진행할 예정이다. 본 논문은 지상도로망을 버드뷰(Birdview)처럼 내려다보며 비행할 수 있는 저고도 드론이 안전하고 효율적인 운항을 보장하기 위해서는, 상공에 장애물이 없는 지상도로망의 상공에 가상도로망과 가상신호체계를 확장시킨 한국형 가상 'SKYWAY' 항법 및 관제 체계(${\mu}$ATM)에 관한 기획 연구에 관한 것이다.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.15 no.3
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• pp.311-318
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• 2004

It is required to design the RF link with sufficiently stable signal margin to minimize bit errors and improve the quality of received data in the telemetry system modulated digitally like PCM/FM. In case of the vehicle flying at a high speed, the variation of the gain pattern between transmitting and receiving antenna and the fee space loss due to flight distance cause the fluctuation of link. In this paper, KSR(Korea Sounding Rocket)- III, the first domestic liquid rocket which was successfully launched in Nov. 2002 is introduced. The SNR(signal-to-noise ratio) variation of the telemetry signal which was measured at S-band ground station, the one which was simulated considering the flight trajectory, and the attitude variation such as roll, pitch and yaw are compared, analyzed, and agree very well. In addition, two virtual flying situations are simulated and evaluated-only one antenna is equipped in one case, and rocket is roll-free in the other.