• Journal of Advanced Navigation Technology
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• v.21 no.6
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• pp.585-592
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• 2017

Recently, as the air traffic volume has been explosively increased, various studies are being conducted to increase the air passenger capacity. In order to compensate the limitation of the separation distance on the aerodrome established on the basis of existing VOR / DME equipment, GNSS utilizing satellite is considered. In addition, we are trying to obtain more precise location information by using SBAS, a system that can correct GNSS error. ICAO recommends introducing SBAS until 2025, and Korea has also started to develop KASS, a Korean SBAS since 2014. Therefore, in this paper, we analyze the interference threshold for the measurement items and the receiving antenna gain according to the elevation angle of the satellite receiving antenna.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.4
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• pp.321-327
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• 2008

The shock tunnel as a hypersonic ground test facility was designed, constructed and its performance test was conducted to reproduce the high speed flow which the hypersonic propulsion system is encountered. The design points were understood and the conceptual design was completed using the quasi one dimensional operation analysis code. After that, the specific performance and compartment design were completed using CFD simulation as the part analysis. The facility was then constructed according to those design results and the performance test was conducted for various operation conditions. In this paper, we suggested the design method of hypersonic shock tunnel including the conceptual and performance design using theoretical analysis and the quasi 1D Multi-species computational fluid dynamics code.

• Journal of Advanced Navigation Technology
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• v.22 no.2
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• pp.70-75
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• 2018

The mounted store on an aircraft shall be subjected to an ground separation test to verify that a safe separation has been made before it is actually installed to the aircraft. In this study, ground ejection test was conducted with dummy missile to verify the stability of the drop on the land. Bomb rack unit essential to testing ground ejection test, operate at high pressure and produce a significant ejection force to push the missile away from any large orifice. Bomb rack unit modified their bombe pressure and orifice diameter to photograph the drop movement of dummy missile with high-speed camera and to analyze their drop displacement and speed. It is considered useful to provide the initial data for the ejection force analysis on aircraft with actual flight and to carry out the ground separation tests of aircraft with future developments.

• Aerospace Engineering and Technology
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• v.13 no.2
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• pp.73-79
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• 2014

During developing cubesat flight software, Communication test between cubesat and ground station is needed. For this, we have constructed indoor ground station without outdoor antenna for decreasing total cost and time. In this time, if output power of ground station is high, it will affect for cubesat transceiver to be fail. For solving this problem, ground station must be designed for output power of it to be lower than input power of cubesat satellite, and it must be verified. In this paper, first, we describe cubesat indoor ground station using UHF and VHF. Second, we describe output power decreasing test for indoor operation of ground station by attaching attenuators in the end of the output connector.

• Journal of the Korea Institute of Military Science and Technology
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• v.16 no.4
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• pp.486-492
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• 2013

The pivoting composite wing is developed for the kit to be mounted on the external stores. The wing has a pivoting structure for the installation to an aircraft and high aspect ratio to increase lift drag ratio. The wing needs to be light and have sufficient strength and stiffness to satisfy structural design requirements. The wing is designed with carbon fiber composite and the structural parts are integrated to reduce cost to manufacture. In order to verify the structural performances, the design load analysis and flight load survey, the static analysis and test, the ground vibration test and flutter analysis are performed. It is shown that the wing has sufficient structural strength and stiffness to satisfy the structural design requirements.

• Aerospace Engineering and Technology
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• v.10 no.1
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• pp.167-174
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• 2011

This paper describes the development of an autonomous system for the precise orbit determination (POD) using GPS raw data. Orbit processing requiring the orbit determination (OD) accuracy of 1m ($1{\sigma}$) or sub-meter is relatively complicated comparing to that of more than several meters. The architecture of the developed system for processing POD automatically and the test results of it were presented. The implemented system is able to be used to the flight dynamics system of the satellite mission control system and moreover can be applied to the multi-satellite POD system by means of incorporating with the automated operational orbit processing system (i.e., Kgs automated Operational Orbit Processing System, KOOPS), which was already developed by the authors.

• 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.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.23 no.4
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• pp.140-145
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• 2015

An on-board reaction wheel is payload of small satellite for space environment test. The reaction wheel is designed for considering physical, electrical, and environmental requirements. In this paper, we report design, manufacturing process and operation performance verification. Furthermore, the specifications of environmental test are performed under environmental conditions for guarantee of stability and reliability. The operation and environment test results are presented to meet the requirements at the reaction wheel flight model.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2000.11a
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• pp.581-586
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• 2000

Explosively activated pyro-technic device is used to release exhausted rocket booster or payloads at prescribed times in the rocket's flight. It creates pyro-shock environment that rocket or payload components must survive. With the shock spectra acquired from flight data, laboratory test should be performed before flight to check whether all of component can sustain the shock environment. The pyro-shock environment simulation was created by the resonance fixture response to a projectile impact. Desired shock spectra is realized by adjusting the natural frequency of resonance plate and the velocity of impact hammer. This paper describes the development process of Pyro-shock testing machine, which is designed and tested by Korean engineers, to verify components of Korean Sounding Rocket(KSR-3) and the other Korean space vehicle. Both analytical and experimental techniques are introduced in this paper.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.11a
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• pp.35-35
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• 2000

추력 편향제어(Thrust Vector Control)는 위성 발사체나 대륙간 탄도 미사일과 같이 공기가 희박한 고 고도에서의 비행자세 제어와 궤도수정, 지대공이나 함대공 유도탄처럼 발사 직후 저속에서 임의의 방향으로 급선회해야 할 경우에 노즐의 배출가스 방향을 직접 조절하여 모멘트를 발생시키는 제어방식을 말한다. 이 방식 중 널리 사용되고 있는 제트 베인 추력 편향제어방식은 베인이 직접 고온, 고속의 가스 흐름내에서 작용하기 때문에 재료는 내열성과 제트 베인 주위에 형성되는 유동 특성, 그리고 베인간의 유동 간섭이 중요한 인자이다. 그러므로, 제트 베인의 실용화는 수치해석에 의존하던 개발 초기나 중기의 설계 단계에서 벗어나 실제 크기나 축소모델의 유동 모사 시험에 의해 성능이 검증되어야 한다.(중략)