• Aerospace Industry
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• v.75
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• pp.54-55
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• 2001

충남 연기군에 위치한 썬에어로시and#49852;(주)는 최근 중소기업창에서 1만번째로 벤처기업 확인을 받은 국내 유일의 군용 시뮬레이터 설계, 제작업체이다. 이 업체는 항공기 Full Scale Mock-Up과 군용 항공기 풍동모델은 물론, 군용 항공기 및 자주포, 미사일 시뮬레이터, 항공기 시험장비, 복합재료에 이르기까지 항공기 분야에 대해 연구 개발하는 항공기 시뮬레이터 전문 개발업체이다.

• The Bulletin of The Korean Astronomical Society
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• v.34 no.1
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• pp.168.1-168.1
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• 2009

• Aerospace Engineering and Technology
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• v.12 no.2
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• pp.173-179
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• 2013

This paper describes a testbed that was designed and implemented for the development of KSLV-II onboard equipment simulator. It used the CPCI-based industrial hardware system for scalability and the QNX real-time operating system for reliability and real-time simulation. In addition, a real-time application under QNX for function simulations of the KSLV-I PDU was developed and it was verified through interface experiments with KSLV-I upper-stage test equipment. The implemented simulator testbed will be used to verify the development feasibility in the design and development phase of a real KSLV-II onboard equipment simulator.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.3
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• pp.30-36
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• 2004

As fiber reinforced composite materials are widely used in aircraft, space structures and robot arms, the study on the non-destructive testing methods of the composite materials has become an important research area for improving their reliability and safety. In this paper, the AE signal analyzer with the resonance circuit to extract the specified frequency of the acoustic emission signal were designed and fabricated. The noise levels of the fabricated AE signal analyzer by the disturbance such as impact or mechanical vibration had a very small value comparable to those of the conventional AE signal analyzer. Also, the fabricated AE signal analyzer was proved to have about the same crack detection capabilities with the conventional AE signal analyzer under the static and dynamic tensile tests of the composite materials.

• The Korean Journal of Air & Space Law and Policy
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• v.27 no.2
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• pp.29-65
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• 2012

Der neue strukturelle Ansatz der Kommbination eines Rahmen$\ddot{u}$bereinkommens und eines ausr$\ddot{u}$stungsspezifischen Sonderprotokolls bedingt einen neuen organisatorischen Anstz f$\ddot{u}$r die Zusammenarbeit zwischen internationalen Organisationen bei der Schaffung von internationalem Einheitsprivatrecht. So haben hier zwei internationale Organisationen gemeinsam die Verantwortung f$\ddot{u}$r einmultilaterales $\ddot{U}$bereinkommen $\ddot{u}$bernommen: auf der einen Seite UNIDROIT als die internationale Organisation, die generell f$\ddot{u}$r die Vereinheitlichung des Privatrechts kompetent ist; auf der anderen Seite ICAO als die f$\ddot{u}$r die private Luftfahrt zust$\ddot{a}$ndige internationale Organisation. Dieses neue, f$\ddot{u}$r die Luftfahrzeugausr$\ddot{u}$stung praktizierte organisatorische Modell eines joint venture zweier internationaler Organisation bei der Einheitsrechtsetzung, namlich die Betreuung eines allgemeinen privatrechtsvereinheitlichenden Rahmens$\ddot{u}$bereinkommens durch UNIDROIT und die Wahrnehmung der sektorspezifischen Belange in einem ausr$\ddot{u}$stungsspesifischen Sonderprotokoll durch die jeweils zust$\ddot{a}$ndige internationale Spezialorganisation, hat bereits f$\ddot{u}$r die Sektoren der Eisenbahn- und Weltraumausrustung Schule gemacht. Das in Kapstadt beschlossene v$\ddot{o}$lkervertragliche Regelungswerk hat erstmals ein einheitsrechtliches - grunds$\ddot{a}$atzlich weltweite Geltung anstrebendes - Sicherungsrecht geschafen. Dies kann f$\ddot{u}$r die Sachenrechtsintergration einen $\ddot{a}$hnlichen Durchbruch bedeuten, wis das Wiener UN-kaufrechts$\ddot{u}$bereinkommen von 1980 f$\ddot{u}$r das Schuldvertragsrecht. Voraussetzung daf$\ddot{u}$r ist allerdings die juristische Qualit$\ddot{a}$t und Praxisgerechtigkeit des Regelungswerkes und - insbesondere - das Funktionieren des Registersystems. Von wesentlicher Bedeutung f$\ddot{u}$r den Erfolg des $\ddot{U}$bereinkkommens wird auchsein, ob es Rechtssicherheit zu gew$\ddot{a}$hrleisten vermag.

• Bulletin of the Korean Space Science Society
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• 2003.10a
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• pp.95-95
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• 2003

점차 정밀화 및 대형화되고 있는 통신위성의 운영 우주환경은 고진공 환경이며 태양 복사열에 의한 고온 환경 및 극저온이 반복되는 가혹한 환경으로 특징지어진다. 위성체는 지상에서 발사되어 우주궤도에 진입한 순간부터는 계속해서 우주환경에 노출되며 이러한 가혹한 우주환경에 의해서 위성체의 주요부품에 기능장애가 초래되기도 하고 이는 결국 임무의 실패로 이어지도 한다. 즉 우주환경은 지상 환경과는 판이하게 다르기 때문에 지상에서는 제대로 작동하는 것으로 관찰되는 위성체가 우주환경에서는 예상하지 못한 기능장애를 보이기도 하고 이는 때때로 임무성공에 치명적인 영향을 미치기도 한다. 위와 같은 이유들로 인하여 위성체는 지상에서 우주환경시험을 거쳐 기능 및 작동상태를 점검해야 하며, 이를 위해서는 우주환경을 모사 할 수 있는 우주환경 모사장비가 필요하다. 본 논문에서는 정지궤도 위성과 같은 대형 위성체의 우주환경 모사에 필요한 대형 열진공 챔버의 설계에 필요한 요소들을 살펴보고자 한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.7
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• pp.666-673
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• 2011

To perform effective integration test of avionics equipments, the importance of a setup for integration test environment has been increasing in recently developed aircraft. Especially, the development of integration test equipment is necessary for minimizing the development period and reliability of integration test. This paper treats the model development for optimal working of integration test after analyzing the characteristics of each MEP equipments for Surion(KUH). Models, whose main role is troubleshooting of equipment and simulation for missing equipments, consists of dynamic, behavior, and ICD models depending on the dynamic characteristics. Software test for both unit level and system level are performed to verify the model reliability. By conducting integration test using SIL, it is confirmed that the developed models are suitable for integration function test of the MEP system.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.48 no.8
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• pp.621-629
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• 2020

LRU layout is a complex problem that requires consideration of various criteria such as airworthiness, performance, maintainability and environmental requirements. As aircraft functions become more complex, the necessary equipment is increasing, and unmanned aerial vehicles are equipped with more equipment as a substitute for pilots. Due to the complexity of the problem, the increase in the number of equipment, and the limited development period, the placement of equipment is largely dependent on the engineer's insight and experience. For optimization, quantitative criteria are required for evaluation, but criteria such as safety, performance, and maintainability are difficult to quantitatively compare or have limitations. In this study, we consider the installation and maintenance of the equipment, simplify the deployment model to the traveling salesman problem, Optimization was performed using a genetic algorithm to minimize the weight of the connecting cable between the equipment. When the optimization results were compared with the global calculations, the same results were obtained with less time required, and the improvement was compared with the heuristic.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.2
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• pp.147-154
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• 2021

In this paper, the configuration and design of the test equipment are presented to examine the impact of rapid temperature change in cooling-air that may occur during the operation of the fixed wing aircraft Environmental Control System (ECS) on avionic electronic equipment. At the start of the ECS, the temperature of the air supplied by the aircraft ECS may be increased to 5.0℃ per second. In order to ensure operating of the avionic electronic equipment that is mounted on the aircraft and receives cooling-air from the ECS, testing equipment that can implement the cooling-air characteristic test environment is required. During design of test equipment was verified cooling-air rapid rate of temperature change by performing a thermal/flow analysis, performance of the test equipment implemented was verified by applying an avionic electronic equipment.

• The Bulletin of The Korean Astronomical Society
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• v.37 no.2
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• pp.192.2-192.2
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• 2012

위성시스템 소형화, 탑재체 수용증대, 발사비용절감, 탐사임무 효율화 등의 요구로 인하여, 위성 설계에 있어 경량화는 오랜 기간 진행되어온 연구 주제였다. 이러한 연구결과로서, 위성 구조체를 복합재료로 대신하기 위한 구조 경량화 연구와 적용이 성과를 거두었으며, 현재 위성체 프레임이나 전개형 안테나, 광학구조물 등에 경량 탄소섬유 강화 복합재료의 적용은 보편화되어 있다. 한편, 위성시스템에서 전력, 통신, 명령/데이터처리, 자세제어 및 관측기기의 각종 전자장비를 보호하는 하우징 구조물에는 여전히 금속재료가 광범하게 적용되고 있다. 특히, 알루미늄 합금은 하우징 재료로 널리 사용되는데, 강도, 강성, 열전달, 우주방사, 전기전도도 및 EMI 차폐특성과 더불어 가공성이 우수하다는 장점을 지닌 반면에, 금속재료로서 중량이 상당하여 위성 경량화 관점에서는 한계를 갖게 하는 단점이 있다. 전자장비에 부여된 전자기능 측면에서 보면, 하우징은 기생 구조물로서, 경량으로 제공될수록 전자장비 전체 무게에서 전자유닛만의 무게가 차지하는 전기전자기능비가 향상되고 위성 경량화에 크게 기여할 수 있다. 구조 경량화를 위하여 전자장비 하우징을 경량 복합재로 대체하여 설계 및 제작하였으며, 복합재 하우징의 강도, 강성, 열전달, 우주방사, 전기전도도 및 EMI 차폐를 검증할 수 있는 방법에 대하여 검토하였다.