• The KIPS Transactions:PartA
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• v.9A no.4
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• pp.459-466
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• 2002

Modern embedded system employs a hybrid architecture which contains a general micro processor and reconfigurable devices such as FPGAS to retain flexibility and to meet timing constraints. It is a hard and important problem for embedded system designers to explore and find a right system configuration, which is known as design space exploration (DSE). With DES, it is possible to predict a final system configuration during the design phase before physical implementation. In this paper, we implement a timing analysis simulator for a DSE on a hybrid embedded system. The simulator, integrating exiting timing analysis tools for hardware and software, is designed by extending Y-chart approach, which allows quantitative performance analysis by varying design parameters. This timing analysis simulator is expected to reduce design time and costs and be used as a core module of a DSE for a hybrid embedded system.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.12
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• pp.1028-1036
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• 2018

KARI plans to launch Korea Pathfinder Lunar Orbiter (KPLO) to the Moon by December 2020 for the first step of the Korea Lunar Exploration Project. This orbiter will be launched to obtain lunar exploration technologies and science data in advance before launching a main orbiter and a lunar probe. This paper describes the verification of thermal design for the orbiter. It is exposed to more extreme thermal environment than that of low Earth orbit satellite due to the heavy infrared emission of the Moon. Accordingly, a thermal design considering this environment is needed to maintain the temperature of payloads and components equipped in the orbiter within operating temperature range in all orbits. We performed the thermal analysis for Earth-Moon transfer orbit, lunar mission orbit and lunar eclipse required for thermal design verification of the lunar orbiter. As a result, this thermal design met the design requirements.

• Current Optics and Photonics
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• v.6 no.4
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• pp.420-429
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• 2022

In this paper, the details and design process of an optical system for space target detection cameras are introduced. The whole system is divided into three structures. The first structure is a short-focus visible light system for rough detection in a large field of view. The field of view is 2°, the effective focal length is 1,125 mm, and the F-number is 3.83. The second structure is a telephoto visible light system for precise detection in a small field of view. The field of view is 1°, the effective focal length is 2,300 mm, and the F-number is 7.67. The third structure is an infrared light detection system. The field of view is 2°, the effective focal length is 390 mm, and the F-number is 1.3. The visible long-focus narrow field of view and visible short-focus wide field of view are switched through a turning mirror. Design results show that the modulation transfer functions of the three structures of the system are close to the diffraction limit. It can further be seen that the short-focus wide-field-of-view distortion is controlled within 0.1%, the long-focus narrow-field-of-view distortion within 0.5%, and the infrared subsystem distortion within 0.2%. The imaging effect is good and the purpose of the design is achieved.

• Journal of Korean Tunnelling and Underground Space Association
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• v.6 no.2
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• pp.101-111
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• 2004

In order to guarantee the stability of a tunnel and its optimum design, it is very important to obtain enough ground investigation data. In realty, however, it is not the case due to the limitation of measuring spatially distributed data and economical reasons. Especially, there are regions where drilling is impossible due to civil appeal and mountainous topology, and it is also difficult to estimate rock mass classes quantitatively with only geophysical exploration data. In this study, therefore, 3 dimensional multiple indicator kriging (3D-MI kriging), which can incorporate geophysical exploration data and drill core data off a tunnel center line, is proposed to cope with such problems. To this end, two dimensional mutiple indicator kriging, which is one of the geostatistical techniques, is extended for three dimensional analysis. Also, the proposed 3D-MI kriging was applied to determine the rock mass classes by RMR system for the design of a Kyungbu express rail way tunnel.

• Journal of Astronomy and Space Sciences
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• v.35 no.3
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• pp.119-131
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• 2018

In spite of a short history of only 30 years in space development, Korea has achieved outstanding space development capabilities, and became the $11^{th}$ member of the "Space Club" in 2013 by launching its own satellites with its own launch vehicle from a local space center. With the successful development and operation of more than 10 earth-orbiting satellites since 1999, Korea is now rapidly expanding its own aspirations to outer space exploration. Unlike earth-orbiting missions, planetary missions are more demanding of well-rounded technological capabilities, specifically trajectory design, analysis, and navigation. Because of the importance of relevant technologies, the Korean astronautical society devoted significant efforts to secure these basic technologies from the early 2000s. This paper revisits the numerous efforts conducted to date, specifically regarding flight dynamics and navigation technology, to prepare for future upcoming planetary missions in Korea. However, sustained efforts are still required to realize such challenging planetary missions, and efforts to date will significantly advance the relevant Korean technological capabilities.

• Aerospace Engineering and Technology
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• v.9 no.2
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• pp.14-21
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• 2010

Ion thruster is a kind of electrostatic thruster that use electrostatic field in order to accelerate ionized propellant. Ion thruster have characteristics of small thrust but very high specific impulse among the electric thrusters. High specific impulse can reduce propellant consumption significantly. So, ion thruster have advantage for long time and long distance mission. Recently, plans for space exploration is increasing gradually not only at traditional forward countries for space like USA, Russia and Europe, but also other countries like Japan, China and India. Exploration for superior planets and asteroids the propellant ratio can go up to about 99% when chemical propulsion is used as a cruising thruster. Therefore, latest space exploration vehicles use the ion thruster as main thruster for del-V burn and use monopropellant thrusters for attitude control. In this paper, the development process of preliminary ECR ion thruster and the ECR discharge test results will be presented.

• Architectural research
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• v.26 no.1
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• pp.1-12
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• 2024

This study introduces a deep reinforcement learning (DRL)-based methodology for optimizing apartment space arrangements, addressing the limitations of human capability in evaluating all potential spatial configurations. Leveraging computational power, the methodology facilitates the autonomous exploration and evaluation of innovative layout options, considering architectural principles, legal standards, and client re-quirements. Through comprehensive simulation tests across various apartment types, the research demonstrates the DRL approach's effec-tiveness in generating efficient spatial arrangements that align with current design trends and meet predefined performance objectives. The comparative analysis of AI-generated layouts with those designed by professionals validates the methodology's applicability and potential in enhancing architectural design practices by offering novel, optimized spatial configuration solutions.

• Journal of Astronomy and Space Sciences
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• v.38 no.2
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• pp.105-117
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• 2021

In this study, a preliminary trajectory design is conducted for a conceptual spacecraft mission to a near-Earth asteroid (NEA) (99942) Apophis, which is expected to pass by Earth merely 32,000 km from the Earth's surface in 2029. This close approach event will provide us with a unique opportunity to study changes induced in asteroids during close approaches to massive bodies, as well as the general properties of NEAs. The conceptual mission is set to arrive at and rendezvous with Apophis in 2028 for an advanced study of the asteroid, and some near-optimal (in terms of fuel consumption) trajectories under this mission architecture are to be investigated using a global optimization algorithm called monotonic basin hopping. It is shown that trajectories with a single swing-by from Venus or Earth, or even simpler ones without gravity assist, are the most feasible. In addition, launch opportunities in 2029 yield another possible strategy of leaving Earth around the 2029 close approach event and simply following the asteroid thereafter, which may be an alternative fuel-efficient option that can be adopted if advanced studies of Apophis are not required.

• The Journal of Korean Institute of Communications and Information Sciences
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• v.39B no.1
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• pp.1-7
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• 2014

This paper proposes an efficient test wrapper design that reduces overall test time in multi-core SoC. After initial local wrapper solution sets for all the cores are determined using well-known Combine algorithm, proposed algorithm selects a dominant core which consumes the longest test time in multi-core SoC. Then, the wrapper characteristics in the number of TAM wires and the test time for other cores are adjusted based on test time of the dominant core. For some specific cores, the number of TAM wires can be reduced by increasing its test time for design space exploration purposes. These modified wrapper characteristics are added to the previous wrapper solution set. By expanding previous local wrapper solution set to global wrapper solution set, overall test time for Multi-core SoC can be reduced by an efficient test scheduler. Effectiveness of the proposed wrapper is verified on ITC'02 benchmark circuits using $B^*$-tree based test scheduler. Our experimental results show that the test time is reduced by an average of 4.7% when compared to that of employing previous wrappers.

• 제어로봇시스템학회:학술대회논문집
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• 2005.06a
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• pp.1802-1807
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• 2005

Tangible interface can be understood as a newly defined concept, which can provide an effective and seamless interaction between the human as a subjective existence and the cyberspace as an objective existence. Tactile sensation is essential for many exploration and manipulation tasks in the tangible space. In this paper, we suggest the design of an integrated tactile sensor-display system that provides both of sensing and feedback with kinesthetic force, pressure distribution, vibration and slip/stretch. A new tactile sensor with PDVF strips and display system with bimorph actuators has been developed and integrated by developed signal processing algorithm. In the scenario of haptic navigation in the tangible space, tactile feedback system is successfully experimented.