• 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.

• KSCE Journal of Civil and Environmental Engineering Research
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• v.40 no.6
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• pp.623-631
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• 2020

An electromagnetic pulse (EMP) attack on a nuclear weapon or the airlift of an electronic bomb affects weapons systems, information devices, wired and wireless communication equipment, and power supply equipment. It can lead to confusion on the battlefield. The current standards for EMP protection when applied to the military are centered on fixed and mobile facilities and equipment. It is, however, important to study EMP protection for a single tactical unit centered on the weapon system. In this study, EMP protection standards were established for command and control, maneuvering and firepower systems vulnerable to EMPs, focusing on battle tanks with mobility, firepower, and shock force. Also, specific development plans for EMP protection capabilities are proposed, including the shielding and blocking of EMPs. Through the study, the Korean government intends to ensure a unit's command and control under an EMP attack as well as preserve the viability of a unit's personnel and guarantee the conditions for the execution of a mission.

• Aerospace Engineering and Technology
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• v.13 no.1
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• pp.108-119
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• 2014

In this paper, through the example of international lunar exploration mission the equipment was to investigate, and the amount of data transferred per day were identified. Data storage and the data transfer rate (8.4Mbps less) for the satisfaction of the value within the range of available S and X bands was confirmed by using the communication link budget. The result is to define the range of the sensor information can be obtained, as well as from the values of the parameters calculated for the transmission communication systems will be able to define the specifications.

• Transactions of the Korean Society for Noise and Vibration Engineering
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• v.25 no.4
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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.

• Bulletin of the Korean Space Science Society
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• 2011.04a
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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.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.25 no.3
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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.

• Journal of the Korea Institute of Military Science and Technology
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• v.4 no.2
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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.

• Journal of Institute of Control, Robotics and Systems
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• v.10 no.10
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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.

• Proceedings of the KIEE Conference
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• 2008.07a
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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.

• Journal of the Korea Institute of Military Science and Technology
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• v.14 no.4
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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.