• Applied Science and Convergence Technology
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• v.24 no.5
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• pp.132-135
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• 2015

Schematic of RAON vacuum system is introduced. Vacuum test for superconducting cavity with liquid nitrogen is performed. Schematic plan for RAON vacuum system is introduced and vacuum control system for superconducting cavity test is constructed. Vacuum pressure of cavity is shown as a function of pumping time. The temperature of cavity is shown as a function of cooling time. Outgassing species from cavity is also detected. Detailed experimental procedure is presented to test the cavity vacuum with liquid nitrogen.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.827-829
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• 2011

Vacuum facility is required for high altitude space environment test to develop satellites or space launch vehicles. We, at Chungnam, National University, developed turbo molecular pump vacuum test facility up to $1.0{\times}10-6$ torr to simulate 200 km altitude environment. In this paper, we present some preliminary vacuum performance test results.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 2005.06a
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• pp.777-780
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• 2005

The high vacuum in a electron beam lithography is basic condition, because electron beam vanish by collision with air molecules in generally atmosphere. To make high vacuum state, the vacuum control valve is essential. Most vacuum control valve are manual units. So, user of manual vacuum valve must have understanding vacuum process to change from low vacuum to high vacuum state. The user of electron beam lithography are troubled with operation of manual vacuum valve, in case the vacuum chamber is frequently open. In this paper, the design and performance test of auto vacuum control valve for electron beam lithography are described. With the auto vacuum control valve, the high vacuum level can reach 2.8E-5 Torr.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.8
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• pp.842-847
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• 2010

Thermal analysis for the simulation of satellite component level thermal vacuum test processes was carried out by considering thermal vacuum test environment condition, thermal vacuum chamber configuration, and satellite's inner thermal environment. The transient analysis results can be obtained for the temperatures of component and thermal vacuum chamber assemblies. The thermal analysis model was verified with the component thermal environmental test results by using enhanced thermal vacuum chamber.

• Proceedings of the KIEE Conference
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• 2003.10a
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• pp.160-163
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• 2003

This paper represent a test method for the reliability assessment on the indoor vacuum circuit breakers used in the distribution system by an accelerated life test. In order to guarantee the lifetime in service of the vacuum circuit breaker, additional test methods are suggested. Multiple closing-opening operation test under no load condition as a mechanical endurance test and a check of the quality in the vacuum interrupter are adopted to assure the long-term reliability of the vacuum circuit breaker.

• Proceedings of the Korean Institute of Electrical and Electronic Material Engineers Conference
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• 2010.06a
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• pp.45-45
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• 2010

This paper discusses the simulation and LI(light impulse) test of the shieldless vacuum interrupter concept. The shields of vacuum interrupter play an important role in absorbing the metal vapor. But shield distort the electric field distribution of inner vacuum interrupter. Therefore, the insulation efficiency will improve. if shield of vacuum interrupter inside does not exist. As a result, FEM simulation show that improve distribution of electrical field and equi-potential line. But LI test result dissimilar to FEM simulation result. Shieldless vacuum interrupter model lower BIL(breakdown impulse light) than vacuum interrupter have installed shield. Because conditioning process occurred metal vapor. This paper compared that FEM analysis and LI test of installed shield model and shieldless model.

• Journal of Applied Reliability
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• v.9 no.1
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• pp.47-58
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• 2009

In this paper, an accelerated life test procedure for a vacuum cleaner motor is proposed. We investigate the failure mechanism of the motor and select some accelerating factors and determine the orifice size as a key accelerating factor. Three stress levels of orifice size are tested and the failure data with censored data are analyzed. The modified accelerating test will reduce the test time in design phase by using the accelerating factor.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.49-52
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• 2007

Vacuum facility is required for high altitude space environment test to develop small thruster. We, at Chungnam National University, developed vacuum test facility up to $10^{-5}$ torr to simulate $100{\sim}120km$ altitude environment. Prior to operation, we predict vacuum pump performances and present preliminary calculation and experiments.

• Journal of Applied Reliability
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• v.3 no.2
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• pp.103-116
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• 2003

We carry out reliability tests and investigate the failure mechanisms. of the wafer level vacuum packaged MEMS gyroscope sensor using an accelerated degradation test. The accelerated degradation test (ADT) is used to evaluate reliability (and/or life) of the MEMS vacuum package and to select the accelerated test conditions, which reduce the reliability testing time. Using the failure distribution model and stress-life model, we are able to estimate the average life time of the vacuum package, which is well agreed with the measured data. After improving several package reliability issues such as prevention of gas diffusion through package, we carry out another set of accelerated tests at the chosen acceleration level. The results show that reliability of the vacuum packaged gyroscope has been greatly improved and can survive without degradation of performance, which is the Q-factor in gyroscope sensor, during environmental stress reliability tests.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.5
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• pp.407-415
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• 2021

The performance of satellite parts must be verified under the space orbit environment before the launch. This paper develops a model formula considering the thermal environment such as conduction, radiation, heat loss and internal heating between satellite parts and a small thermal vacuum chamber for thermal vacuum tests. System identification is carried out using test data from 20 recent thermal vacuum tests conducted by the Korea Aerospace Research Institute. It is verified that the model formula and the identification results are valid, except when the heating of the functional test of the test specimen is not constant.