• Proceedings of the KIEE Conference
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• 2008.07a
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• pp.1953-1954
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• 2008

The excitation system for class 1E has been developed to apply to the nuclear power plant emergency diesel generator by utilizing the existing digital excitation system. The additional mission was to evaluate the excitation system of safety. It is the safety analysis of the excitaton system, the verification test, the aging test, the safety requirement test and so on. The verification test is classified of hardware and software part for detail.

• Journal of Applied Reliability
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• v.17 no.2
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• pp.150-158
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• 2017

Purpose: The RAM objective is a very important factor that has a great effect on the improvement of the operation ration during the operation maintenance and the reduction of the life cycle cost. It is used as a design criterion during the system development, and its sufficiency should be evaluated during its test evaluation. Method: This study analyzed the cases related to RAM objective setting and suggested the improvement measures. Result: The base data for RAM objective is OMS/MP, which needs to be drawn up under the supervision of the requirement military, and a high-accuracy operating availability should be set through ALDT calculation which reflects the military logistics support environment. In addition, data collection necessary for RAM objective and RAM analysis should be made by supplementing the input data of DELIIS. Conclusion: This study suggests improvement of RAM objective considering for the weapon system.

• Aerospace Engineering and Technology
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• v.1 no.1
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• pp.55-64
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• 2002

A conceptual design of propulsion system for a geosynchronous communication satellite with 12 years design life is presented in this paper. Propellant mass budget for the design life is calculated using total velocity increment (ΔV) flowed-down from mission requirement analysis. Sizes of the fuel and oxidizer tank are derived based on the calculated propellant mass budget, and mass of the pressurant as well as the size and pressure of pressurant tank are calculated too. Thruster positioning, number of rocket engines, and position of tank are determined through Trade-Off Study with Structure & Mechanical Subsystem. Propulsion system configuration and its schematics are presented finally.

• Journal of the Korea Society for Simulation
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• v.26 no.1
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• pp.55-67
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• 2017

The requirement planning system of Korea military has used top down planning approach after introducing Joint Combat Development System since 2007. But this new system has not been propelled harmoniously because it does not have any connection with the current planning system. Due to current time-exhaustive analysis and assessment process in requirement planning system, it not only delays proper decision making, but also hinders understanding on the problem in a whole perspectiveand finding a reasonable solution to our problem. In this study, we present a methodology which can analyze and assess capability utilizing the weapon score of JICM(Joint Integrated Contingency Model). The process identifies capability gap from a mission-oriented perspective in the requirement planning phase and suggests an appropriate solution to our problem. A Quick Look tool which has been developed using Python Script to implement the methodology is also introduced in this study.

• Aerospace Engineering and Technology
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• v.2 no.2
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• pp.167-178
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• 2003

The design on the Telemetry Ground System for launch of KSLV(Korea Space Launch Vehicle) in the korean Space center has been conducted in this study. For the optimized system design, first of all, the system deployment plan reflecting the topographic and geographic environments of the space center and launch vehicle characteristics has been developed. The RF link budget analysis for the maximum tracking range, requirement for receiving subsystem including antenna subsystem, requirement for data processing subsystem are also analyzed based on the On-Board Telemetry characteristics and launch vehicle parameters. Based on those analysis, telemetry ground system containing tracking/receiving subsystem, recording subsystem and data processing subsystem, timing subsystem, calibration subsystem and monitoring and control subsystem are designed. Futhermore, the analysis for the maximum permissible data latency and communication protocol between each telemetry station and control center are conducted and the entire system is designed so that the major telemetry parameters selected to the best quality are provided in real time to the control center(RCC, RSC) for the launch mission operation.

• The Journal of the Institute of Internet, Broadcasting and Communication
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• v.20 no.4
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• pp.93-99
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• 2020

It seems to be increased rapidly that practical uses of intelligent Dron for public mission performance such as surveillance, prevention of disaster accident, relief etc with Dron technology development. Dron is needed for major technology realization of detection and trace technology of target, flight control and obstacle avoidance during flighting, detection and control of landing point functions to use smart safety-city platform construction. This dron system cause a great ripple effect technically and promote industrialization in the field of new technology. In this paper, an effective analysis and design method of dron system software will be presented by showing user requirement analysis using object-oriented method, flowchart and screen design.

• Journal of Advanced Navigation Technology
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• v.24 no.5
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• pp.329-342
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• 2020

In this paper, we analyzed the requirements for the application of UAM, a new concept to solve the traffic congestion in large cities. First, the current domestic and foreign status of research and development related to UAM was investigated and the pros and cons and the time required for each mission radius were analyzed for various configurations of aircraft being commercialized. In addition, in order to analyze the market acceptance of the UAM, the individual's consciousness and reliability requirements were identified and safety requirements were analyzed through accident rate data for each aircraft type. Because it operates in a densely populated urban area, requirement analyses on noise and exhaust, which are environmental factors that can affect the community were performed, and requirements related to aircraft performance, certification standards, and airworthiness standards of FAA and EASA were also analyzed.

• Aerospace Engineering and Technology
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• v.6 no.1
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• pp.103-108
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• 2007

Eurostar 3000 AOCS is optimized for telecommunication mission with no strong requirement on attitude stability and has therefore to be upgraded to comply with COMS high stability requirements for the optical observations. This COMS configuration constraint induces specificities for the wheel. The aim of this analysis is to verify the electrical compatibility of the interfaces which exist between COMS wheels and external equipments. For each interface, this study checked the compatibility between equipments for the power links, commands, digital telemetry, analog telemetry, and failure condition or AIT errors. In addition with this interface compatibility verification, this study outputs electrical and manufacturing recommendations to be applied at harness level.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.1
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• pp.63-68
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• 2011

Many countries all over the world have been doing lunar exploration projects. Korea has also been doing basic research on lunar exploration. The development of communication systems for lunar exploration projects is one of the most important aspects of performing a successful lunar mission. In this paper, we design a DSP (Digital Signal Processor) prototype based on the requirement analysis of a communication link for lunar exploration and implement its core module considering the international standards for deep space communications to perform a basic research on baseband processor development. It is verified by comparing the bit error rate of the DSP prototype with that of a computer simulation.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.7
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• pp.652-659
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• 2011

A computational system to predict flowfield and infrared signature in aircraft exhaust system is developed. As the first step, a virtual mission profile is considered and an engine is selected through a performance analysis. Then a nozzle that meets the requirement of each mission is designed. The internal flow in the exhaustion nozzle at the maximum thrust is analyzed using a state-of-the-art CFD code. In addition, a system to combine information of the skin temperature distribution of the nozzle and after-body surface with an infrared prediction code is developed. Finally, qualitative results for the infrared signature reduction design are obtained by investigating the infrared signature level under various conditions.