• 대한토목학회논문집
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• 제40권6호
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• pp.623-631
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• 2020

핵무기 공격 시나 전자폭탄의 공겨 시 발생하는 전자기펄스(EMP: electromagnetic pulse)는 무기체계, 정보기기, 유·무선 통신장비, 전력공급 장비 등에 영향을 주어 전장에서 혼란을 초래하게 한다. 지금까지의 군에 적용 중인 EMP 방호에 대한 기준은 고정 및 이동시설과 장비를 중심으로 되어 있어 무기체계 중심의 단일 전술제대에 대한 EMP 방호 소요에 대한 연구가 필요한 실정이다. 본 연구에서는 전술제대 중 기동력과 화력, 충격력을 지닌 전차대대의 전차와 지휘용장갑차를 중심으로 EMP에 취약한 지휘통제, 기동, 화력체계에 대하여 EMP 방호기준을 설정하고, EMP 차폐 및 차단 등 EMP 방호능력 발전방안을 구체적으로 제시하였다. 이를 통해 EMP 상황하 부대 지휘통제와 부대원의 생존성을 보장하고 임무수행 여건을 보장하고자 한다.

• 항공우주기술
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• 제13권1호
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• pp.108-119
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• 2014

본 논문에서는 해외 달 탐사의 사례를 통해 임무장비를 조사하고 하루 전송되는 데이터량을 확인하였다. 데이터 저장공간과 데이터 전송속도(8.4 Mbps 이하)를 만족하기 위해 가용한 범위내의 값을 이용하여 S 및 X 대역 통신 링크 버짓을 통해 확인 하였다. 이 결과를 활용하면, 달 탐사선의 하루 생산량 데이터 및 센서 획득 정보의 범위를 정할 수 있을 뿐만 아니라, 전송을 위해 계산된 파라미터 값으로부터 달 탐사 통신시스템의 개발 사양을 정할 수 있을 것이다.

• 한국소음진동공학회논문집
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• 제25권4호
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• pp.255-265
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• 2015

Shelter system is applying to weapon systems as usage of performing specific mission with arranging several electronic equipments and operators. Recently the electronic equipments is changing from development products to COTS(commecial off-the-shelf) for demonstrating high performance at low cost. As internal operators of shelter system conduct several missions for specific or long time in this present situation, one of the most important element considering the best combat power is internal noise level. Therefore, I desire to analyze the features and foresee multiple noise level with test for conforming whether requirements of design is met or not in this research paper.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2011년도 한국우주과학회보 제20권1호
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• pp.33.3-33.3
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• 2011

위성 사업의 핵심 지상 시스템인 Electrical Ground Support Equipment(EGSE)와 Mission Control System(MCS)는 사용시기와 목적, 개발조직이 달라서 지금까지는 별도로 개발 및 발전되어 왔고, 최근 국내에서는 다목적실용위성사업의 EGSE와 MCS에서 핵심 모듈만 서로 공유하는 형태로 개발되어 각각 성공적으로 위성 시험과 운영에 이용되고 있지만, 가까운 미래에는 하나의 통일된 공통지상시스템을 개발하여 위성 발사전 위성시험에서도 이용하고, 위성 발사후 위성 운영 단계에도 사용될 수 있도록 할 예정이다. 이러한 공통지상시스템에서는 위성 시험과 운영에 동시에 사용 가능한 공통절차서언어 개발이 핵심이다. 공통절차서언어를 이용하게 되면, AIT단계에서 위성운영단계로의 자연스러운 단계 전환이 가능하여 위성운영교육 및 준비에 필요한 비용 절감 뿐만이 아니라, AIT단계에서 시험/운영 절차서, 위성 데이터베이스의 사전 검증이 이루어지며, 아울러 위성 사업 일정 및 위성 개발 위험도 최소화 등의 이점이 있다.

• 한국항공운항학회지
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• 제25권3호
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• pp.61-67
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• 2017

The Nose Landing Gear(NLG) of Rotary Wing Aircraft is an essential equipment in Landing System for pilot to perform a flight mission. It supports the fuselage at ground and absorbs the impact from the ground when landing, thereby, these functions sustain operational capability for pilot and crew. However, the A aircraft caused stick-slip behavior when it was stationed on the ground. Therefore, this paper summarizes pilot comment in operation which are classified by cause of occurrence and the troubleshooting process about each comment. It also describes design improvements which was derived from troubleshooting and suggests verification results of flight test.

• 한국군사과학기술학회지
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• 제4권2호
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• pp.227-232
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• 2001

IPresented is a small and handy remotely piloted vehicle(RPV) that can be used for military and non-military surveillance operations. The RPV is equipped with an on-board high resolution color camera to transmit the analog video images and on-board electronics to provide real-time flight information to the pilot, thereby enabling him/her to remotely pilot within the range of 5 km radius. This paper describes the RPV system including its design, manufacturing and flight test results which manifest the stability of on-board mission and flight equipment as well as the remote piloting capability. A future plan for necessary improvements identified from the flight tests are also discussed.

• 제어로봇시스템학회논문지
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• 제10권10호
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• pp.956-960
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• 2004

The Vehicle Dynamic Simulator(VDS) is a key equipment of the performance verification of attitude control subsystem and it simulates the real dynamic environment that spacecraft undergoes during mission operation. All the software models and hardware interfaces necessary for the closed-loop simulation of the spacecraft dynamics are implemented. Using VDS, KOMPAT-2 attitude control logic functions and performance was verified. In this paper, the hardware and software configurations of KOMPSAT-2 VDS was described briefly and the information flow and exchanges between software models and actual hardwares during close loop simulation was described in the systematic point of view.

• 대한전기학회:학술대회논문집
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• 대한전기학회 2008년도 제39회 하계학술대회
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• pp.1949-1950
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• 2008

Activation battery that are required to deliver short pulses to power, for instance, pyrotechnic devices required during jettison payload separation. Activation battery contains 24 Sony US18650 cells configured as 3 strings in parallel, with each string containing 8 series connected cells. This allows to meet voltage and capacity requirements specified for the mission. In this paper design description and specifications of Activation battery are presented. Qualification test flow and results are also shown to make sure the performance in the predicted space environment. Electrical performance was proven on real equipment load assembly.

• 한국군사과학기술학회지
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• 제14권4호
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• pp.598-606
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• 2011

The importance of avionics systems has increased to a significant level in modern aircraft development. Modern avionics system is a complex integrated system of state-of-art hardware and software technology. Specifying the avionics system architecture is the most important task throughout the avionics system design process. This paper reviews modern avionics system architectures and proposes an effective avionics architecture suitable for modern attack helicopters.

• 시스템엔지니어링학술지
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• 제2권1호
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• pp.37-41
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• 2006

The KSLV-I satellite launch vehicle will be launched in a space center currently under construction. The Space Center which is an advance post base of space development of Korea is located on Oenaro island in Kohung, South Cholla Province. A Ground Complex of the Space Center consists of an AC(Assembly Complex), a LC(Launch Complex), and a MCC(Mission Control Center). Assembly and test facilities are located in the AC in which stage assembly, integrated assembly, check-up, certification test, and pre-launch test are made effectively. A launch pad, fuel supply facilities, a launch control center and associated supporting facilities are located in the LC, and the MCC has control over the space center. These ground complex facilities have diverse forms of an interface with mechanical device, electric device, and etc. These should also provide optimum condition and performance during launch operation processes of the launch vehicle. This paper introduces the result of R&D for the AC of the ground complex performed during system design period.