• 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.

• Proceedings of the Korean Institute of Electrical and Electronic Material Engineers Conference
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• 2008.06a
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• pp.46-46
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• 2008

스텔스 기능을 가진 군사용 항공기는 레이다 망의 추적을 피하기 위해 일반 냉각수 대신에 절연유를 냉각매체로 사용한다. 그러나 절연유는 물에 비하여 열전달특성이 매우 낮기 때문에 항공기 전기전자 기기/부품 발열부를 효과적으로 냉각시키지 못하는 한계성을 가지고 있다. 따라서 본 연구에서는 나노유체(Nanofluid) 개념을 이용하여 절연유에 알루미나 및 질화알루미늄 나노분말을 미랑 분산시킨 나노절연유를 제조하고 이것의 열전달특성을 순수 절연유의 그것과 비교 평가함으로써, 냉각특성이 크게 개선된 새로운 냉매로서의 적용 가능성을 확인하고자 하였다. 다만 나노절연유를 제조함에 있어서 가장 큰 장애물은 오일에 대한 분산성 확보에 있기 때문에, 비드밀 및 초음파를 이용한 나노분말 응집체의 습식분산 및 분산제를 이용한 친유성 표면개질을 동시에 수행함으로써 장시간 안정된 분산성을 확보하도록 노력하였다. 나노유체의 열전도도 및 대류열전달계수는 비정상열선법을 이용하여 측정하였으며, 유체 속의 분말 분산 상태는 원심력을 이용한 분산안정성 평가장치 및 cryo FE-SEM을 이용하여 확인하였다. 또한 분말 형상이 대류열전달에 미치는 영향을 조사하기 위하여 알루미나 나노분말은 구상과 침상의 분말을 모두 사용하였고, 질화알루미늄 외에 다이아몬드 나노절연유도 함께 제조, 평가함으로써 냉각 및 절연특성, 그리고 물리화학적 안정성이 우수하고 실적용 가능성이 가장 높은 재료를 도출하고자 하였다.

• Telecommunications review
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• v.24 no.4
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• pp.468-480
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• 2014

The current-generation avionics systems are based on a federated architecture, where an electronic device runs a single software module or application that collaborates with other devices through a network. This architecture makes the internal system architecture very complicate, and gives rise to issues of Size, Weight, and Power (SWaP). In this paper, we show that the partitioning defined by ARINC 653 can efficiently deal with the SWaP issues on small unmanned aerial vehicles, where the SWaP issues are extremely severe. We especially install the integrated mission system on real hexacopter and quadcopter and perform successful flight tests. The presented software technology for integrated mission system and software consolidation methodology can provide a valuable reference for other SWaP sensitive real-time systems.

• Journal of the Korea Institute of Military Science and Technology
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• v.5 no.3
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• pp.98-104
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• 2002

An airborne-based Direction-Finding System is developed for the application of ELINT and ES(Electronic Support). The system takes the phase-comparison technology, and has the configuration of multi-based antenna array for the solution of ambiguity due to the increased Direction-Finding resolution. This thesis describes the design of optimized distances among antennas, the electrical characteristics, the method of compensation, the direction-finding accuracy, and et. al. under the condition of the airborne-based environment.

• Aerospace Engineering and Technology
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• v.8 no.1
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• pp.172-178
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• 2009

Recently, autopilot is essential to reduce pilot's workload and increase flight safety. Avionics system of the small aircraft also has progressively adopted centralized multi-processor and multi-process computing architectures similar to the integrated modular avionics of B-777. It is increased more and more that importance of the flight control system. In this paper, the performance of the autopilot for the small aircraft has been verified with Hardware-In-the-Loop Simulation(HILS). Also, the autopilot algorithm that is operated in the Flight Control Computer(FCC) for the Fly by Wire(FBW) was verified with PILS and compared with the HILS results for the several commercial autopilots.

• Aerospace Industry
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• v.84
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• pp.34-37
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• 2004

1997년에 설립된 L-3 Commucinations사는 뉴욕시에 본사를 둔 정보, 감시, 정찰 제품, 보안통신시스템 제품, 항공해상 전자공학제품, 훈련용 제품, 마이크로파 소자와 원격측정장치, 계측기 , 우주및 무선제품 등에 있어 업계를 선도하는 업체이다.<중략>

• The Journal of the Korea Contents Association
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• v.12 no.8
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• pp.77-86
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• 2012

Avionics system are composed of multiple electronic device that performs important missions the number of electronic devices for the performance of aircraft has been gradually increasing. As a result, cost of development, maintenance and operating have increased. To solve this problem, technology paradigm of avionics has been shifting from federated avionics systems that manage to each system independently to IMA(Integrated Modular Avionics) systems. Unlike federated systems, fault tolerance becomes an essential technology in IMA systems. Because each aircraft features integrated in the an IMA system, a fault can jeopardize the entire system. In this paper, we define faults which can occur on the ARINC 653 based IMA system first, and design the ARINC 653 compliant HM(health Monitoring) system for the system can continue to operate be normal when occur a fault.

• Defense and Technology
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• no.7 s.245
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• pp.38-47
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• 1999

대기의 상태는 지역, 시간, 기상 조건 등에 따라 변하므로 고도를 계산하는데는 북반구 중위도 지방에서 관측된 기상자료 등을 기준으로 제정한 표준대기를 적용한다. 속도를 계산하는데 전압과 정압의 압력차로 정의하는 항공기용 대기속도계 차압표를 사용한다. 계산된 에어 데이터는 비행계기나 cockpit display에 표시되어 조종사에게 정보로 전달됨과 동시에 자동조종 장치, 관성항법 장치, 비행관리 시스템, 항공관리 트랜스폰더 등에 기초 자료로 공급된다

• Proceedings of the KAIS Fall Conference
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• 2011.12b
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• pp.620-623
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• 2011

안전핀은 기계적으로 과도한 힘이 작용할 때, 파손되어 다른 구성품 및 사람을 보호하는 역할을 하며 이는 전자/전기 시스템에서 Fuse와 같은 역할이다. 안전핀은 재설기의 구동시스템 또는 항공기 Pushback Bar 등에 사용된다. 본 논문에서는 항공기 착륙장치에 적용된 안전핀의 역할과 파손 확률 계산 방안에 대해 소개하고자 한다.

• Journal of Advanced Navigation Technology
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• v.1 no.1
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• pp.59-69
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• 1997

In this paper, we construct a navigation geography database using R-tree, and develop a software for avionics systems such as VOR, ILS, DME, and NDB. First, we design the navigation geography database using R-tree, and construct a database for navigation aids facilities of every airport. In order to implement avionics software, we develop some calculating algorithms for distance, bearing, and deviation angle between an aircraft and a VOR station for VOR, and deviation angle from a LLZ, glide slope from a GP, and range of markers for ILS. The navigation geography database system is composed of map data manager which can construct and update the database, real-time searcher which provides information about the avionics system, geography database, and user interface.