• Journal of Advanced Navigation Technology
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• v.27 no.5
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• pp.574-579
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• 2023

The radar flight test has many restrictions on simulating various targets, clutter and jamming signal. Therefore, in this study, a radar HILS system that performs a radar operation simulation function according to an operation scenario was developed. Radar HILS simulates the radar mission environment through radar beam operation simulation, radar operation control, simulated signal generation, and flight attitude simulation.. HILS generates and modulates simulated target signals(single, multiple targets) containing radar mission environments(clutter, jamming etc.) based on flight scenarios, and transmits them to AESA radar over RF. And Scenario-based radar performance was verified by detecting simulated targets and confirming detection results.

• Aerospace Engineering and Technology
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• v.1 no.2
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• pp.57-65
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• 2002

The Electrical Power System (EPS) shall supply required power to maintain spacecraft and payload during the mission. The EPS sizing are based on space environment, satellite mission and lifetime, and allocated budgets. The type of the primary and secondary power is determined according to satellite design-level and allocated subsystem budgets. The design of EPS has closely related to system and others' subsystems design. To supply the sufficient power to the satellite, the implementation of the larger power source and energy storage is impossible actually. And there will be some problems of the attitude control of the satellite, the handling power capability of the electronic boxes, and launch vehicle selection caused by EPS oversizing. Also, the thermal control is not easy in the space by extra power. And the maintenance of the satellite within the specific orbit from orbit-drag is a big design burden of the thruster. So the various technologies have been developed to optimize the EPS sizing and to operate the power system efficiently.

• International Commerce and Information Review
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• v.13 no.4
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• pp.297-321
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• 2011

Under the UN Security Council Resolution 1540/1810 in 2004 to restrict the proliferation of WMD (weapons of mass destruction) and their means of delivery, many countries have taken great efforts to, control the export of strategic items, thereby preventing the transfer of ABCM (atomic, biological, chemical weapons, missiles) and technologies and goods related to conventional weapons or dual-use items, Compliance Program (CP) in Korea or Internal Compliance Program(ICP) in Japan refers to a company's internal system or rules to comply with the export control laws and regulations, and is to prevent the unintentional illegal export of strategic items. This paper analyzes the Compliance Program (CP) of strategic export control system between Korea and Japan. Both countries have very similar legal frameworks under the guiding principles of multilateral export control regimes. However, there are some differences in actual procedures, classification service, supporting system, export license, sanctions for illegal exporters, etc. Korea should take more active and customer-oriented measures to promote the Compliance Program (CP) into Korean export companies for better awareness and positive attitude, practical information and education, smoothy government-firm communication, closer cooperation between Korea and Japan, etc.

• Proceedings of the KIEE Conference
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• 2004.11c
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• pp.586-588
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• 2004

Although stable control algorithm has been implemented to the biped robot, the stability is not guaranteed because of encoder errors and/or rigid body elastics. Hence precise body pose estimation is required for more natural and long term walk. Specially pelvis sloping by gravity or uneven ground on landing place are most critical reason for undulated motion. In order to overcome these difficulties an estimation system for foot position and orientation using PSD sensors and Gyro sensors is proposed along with calibration algorithm and experimental verification.

• Aerospace Engineering and Technology
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• v.9 no.2
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• pp.138-142
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• 2010

The thrust axis alignment of the launch vehicle is very important because of the misalignment causes the unstable attitude control and results in mission failure. Generally, optical methods such as digital theodolite and laser tracker and mechanical method such as turn table method are used to align thrust axis to vehicle axis. This article deals with the simple method of thrust axis alignment of Kick Motor.

• Knowledge Management Research
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• v.11 no.5
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• pp.79-90
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• 2010

As the volume of South Korean trading increased, the pressure from the international community on South Korea to perform export control system for strategic items (ECS) increased as well. However, the South Korean government has been giving a tepid response toward the ECS, due to lack of the knowledge on psychological reactance of firms. This paper investigates the structural relationships between environmental factors and the attitude toward the ECS, and the adoption of the ECS. The author discuss the implications of the findings in this article which are useful for the government to find strategic policy direction.

• 제어로봇시스템학회:학술대회논문집
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• 2005.06a
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• pp.888-893
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• 2005

Since inertial sensor errors which increase with time are caused by initial orientation error and sensor errors(accelerometer bias and gyro drift bias), the accuracy of these devices, while still improving, is not adequate for many of today's high-precision, long-duration sea, aircraft, and long-range flight missions. This paper presents a navigation error compensation scheme for Strap-Down Inertial Navigation System(SDINS) using star tracker. To be specific, SDINS error model and measurement equation are derived, and Kalman filter is implemented. Simulation results show the boundedness of position and attitude errors.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.32 no.2
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• pp.202-208
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• 2008

A 6 DOF Multi axis simulation table (MAST) is used to perform vibration and fatigue tests for parts or assemblies of automobiles, aircraft, or other systems. It consists of a table and 6 linear actuators. For its attitude control, we have to adjust the lengths of 6 actuators properly. The system is essentially a parallel mechanism. Three actuators are connected to the table directly and other three actuators are connected indirectly. Because of these, the MAST shows also a serial mechanism#s property: the inverse kinematics is more complicated than a pure parallel mechanism and each actuator can operate independently. The authors have performed a kinematics analysis of the 6 DOF MAST. We have presented an analytical and a numerical solution for the inverse and forward kinematics, and we have verified the solutions by a 3D CAD software.

• Journal of the Korean Institute of Rural Architecture
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• v.13 no.3
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• pp.11-20
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• 2011

The present age demands a change in attitude based on a differentiated life value from city. It will provide to a fundamental solution for the gap of living level in the farming and fishing communities and recreate distinguishing comfortable communities. The purpose of this study was to deduct the formation characteristics of the townscape of Korean slow city according to analyze resources and structure of landscape. Planning of slow city's townscape is a process of imagification of filtrate unique meaning. The glob share synchronic unique values by slow city's network. Therefore instead of putting emphasis on promoting tourist business for short-term revenue, it will be under control to raise the standard of living and to be not forfeited and diluted the rights for sustainable slow city's status. Participation of resident needs in this process. Accordingly it need a strategy of landscape formation design and a interdepartmental practice system for a continuous slow city's image by renewal of disharmonious townscape in the built-up area.

• Proceedings of the KSME Conference
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• 2004.04a
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• pp.1280-1285
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• 2004

Microsystem technology has been applied to space technology and became one of the enabling technology by which low cost and high efficiency are achievable. Micro propulsion system is a key technology in the miniature satellite because micro satellite requires very small and precise thrust force for maneuvering and attitude control. In this paper research on micro solid propellant thruster is reported. Micro solid propellant thruster has four basic components; micro combustion chamber, micro nozzle, solid propellant and micro igniter. In this research igniter, solid propellant and combustion chamber are focused. Micro igniter was fabricated through typical micromachining and evaluated. The characteristic of solid propellant was investigated to observe burning characteristic and to obtain burning velocity. Change of thrust force and the amount of energy loss following scale down at micro combustion chamber were estimated by numerical simulation based on empirical data and through the calculation normalized specific impulses were compared to figure out the efficiency of combustion chamber.