• Journal of Astronomy and Space Sciences
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• v.27 no.2
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• pp.135-144
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• 2010

In this paper, we present the result of preliminary design of tracking mount for ARGO-M which is a movable satellite laser ranging (SLR) system developed by Korea Astronomy and Space Science Institute (KASI). The tracking mount consists of a couple of core parts such as driving motors, encoders and bearings, and the requirements of each parts are determined on the basis of the technical consideration. 2D and 3D models for tracking mount were preliminarily designed using the selected core parts. In order to evaluate the validity of the preliminarily design, the simulator to test the elevation axis was designed and manufactured. The test to check the tracking performance and system accuracy of the simulator was performed, and it was confirmed that the preliminary design meets the operating specifications. Additionally, it was found that the repetitive errors and hysteresis errors need to be improved by the additional control algorithm.

• Proceedings of the Korean Institute of Building Construction Conference
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• 2019.11a
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• pp.239-240
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• 2019

The existing evaluation of root barrier resistance takes at least two years as an evaluation based on plant growth, and it is difficult to determine early performance in the process of quality control in the field. In this study, thus, the direction of the root barrier resistance evaluation system was presented by considering the construction specifications and design standards for root barrier design. As a result, it was necessary to establish a test method for reproducing simple and consistent test results for evaluating the durability of root barrier materials.

• 제어로봇시스템학회:학술대회논문집
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• 1994.10a
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• pp.34-37
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• 1994

A satellite communications monitoring and control system(SCMCS) has been developed at ETRI to provide the capabilities of in-orbit test (IOT) for communications payload and communications system monitoring(CSM) for the satellite communications services. The paper discusses the system level design of SCMCS and its tasks.

• International Journal of Aeronautical and Space Sciences
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• v.6 no.1
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• pp.61-70
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• 2005

The currently developed propulsion system(PS) is composed of propellant tank, valves, thrusters, interconnecting line assembly and thermal hardwares to prevent propellant freezing in the space environment. Comprehensive engineering analyses in the structure, thermal, flow and plume fields are performed to evaluate main design parameters and to verify their suitabilities concurrently at the design phase. The integrated PS has undergone a series of acceptance tests to verify workmanship, performance, and functionality prior to spacecraft level integration. After all the processes of assembly, integration and test are completed, the PS is integrated with the satellite bus system successfully. At present, the severe environmental tests have been carried out to evaluate functionality performances of satellite bus system. This paper summarizes an overall development process of monopropellant propulsion system for the attitude and orbit control of LEO(Low Earth Orbit) observation satellite from the design engineering up to the integration and test.

• 한국기계연구소 소보
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• s.16
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• pp.83-94
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• 1986

Grinding machine, one of the precision machine tool, requires high accuracy in spindle system. But, recent Inspection and Test reports by KIMM shows high inferio¬rity ratio in home-made grinding machines and points out that this is mainly due to the lack of design ability and assembling technique of spindle system. In this paper, therefore, static stiffness, dynamic characteristics, thermal defor¬mation and error motion of spindle system were studied. With these results, we presented the general data to design and assemble the spindle system. Test of spindle system modified by this study showed that several factors affecting machining accuracy were improved largely.

• Proceedings of the KSME Conference
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• 2004.11a
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• pp.383-387
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• 2004

The Fuel Test Loop (FTL) consists of In-Pile Test Section (IPS) and Out-of-Pile System (OPS). The test condition in IPS such as pressure, temperature and quality of the main cooling water, can be controlled by the OPS. The FTL has been developed to be able to irradiate three pins to the core irradiation hole (IR1 hole) by considering for its utility and user's irradiation requirement. The IPS vessel assembly (IVA) consists of IPS head, outer pressure vessel, inner pressure vessel, inner assembly and test fuel carrier. The IVA is approximately 5.6 m long and fits within a 74 mm in diameter envelope over the full height of the chimney. Above the top of the chimney, the head of the IPS is enlarged to allow the closure flanges and pipe work connections. IVA was designed to test the CANDU and PWR nuclear fuel pin together. Specially, wished to minimize interference by nuclear fuel change in design and synthesize these items and shape design for IVA.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.325-328
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• 2007

In this study, intended to high flight condition test, air flow test and environmental condition test of Small-sized Gas Turbine (including auxiliary power utility - APU) improve preexisting large size test stand C-9N(SCIAM) in Russia. In the process of developing C-9N test stand, this study includes conceptual design approach. This test stand consists of environmental condition, thermostat, cooling/drying, thrust measuring system and SAR (system of automatic regulation).

• Transactions of the Korean Society of Automotive Engineers
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• v.6 no.2
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• pp.118-128
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• 1998

Finite element analyses are carried out to provide results usable in the design of airbag module that consists of inflater, cushion, cover, mounting plate, etc. In the first phase, a deployment process of airbag module is analyzed to evaluate the pressure waveform of developed airbag and deployment characteristics, and is compared with the test results. Interaction between head form and inflated airbag module is investigated in the second phase. In the last stage, sled test with rigid dummy, airbag midule, driving system and car interior part are simulated to investigate the influence of airbag design factor on the behavior of dummy with seat belt. The procedures can be provided as a guideline for airbag module design and improvement of airbag module performance.

• Journal of the Society of Naval Architects of Korea
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• v.45 no.4
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• pp.396-402
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• 2008

As demands for high speed sea transportations have recently been increased, various high speed ships appear. Among them the WIG is believed to be one of the next generation of the sea transportation system. Test flight of the 20 seaters WIG craft, Haenarae-X1, developed by MOERI was a success in August, 2007. Development of the large WIG is now ongoing, and it is expected to be commercialized in the near future. In this study we designed a remote controled WIG Craft and carried out its performance test in order to establish engineering design procedures of an Unmanned WIG (U-WIG) craft.

• Journal of Aerospace System Engineering
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• v.6 no.2
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• pp.35-41
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• 2012

A reciprocating engine installed on a normal category airplane shall be effectively cooled by air flown through the engine compartment. A airplane powerplant designer has to design cooling air inlets, baffles, seals, and outlets to maintain cylinder head temperatures and oil temperature under the limits, and show compliance with appropriate airworthiness standard. In this study, cooling designs of the installed engine and compliance requirements applicable to the cooling designs were reviewed, and engine cooling flight test results were evaluated for design changes. Engine cooling certification test will be conducted in a next step.