• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.11
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• pp.1008-1015
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• 2015

Thermal vacuum test should be performed prior to launch to verify satellites' functionality in extremely cold/hot temperatures and vacuum conditions. A thermal vacuum chamber used to perform the thermal vacuum tests of a satellite system and its components. A cryogenic blower is a core component of the gaseous nitrogen (GN2) closed loop thermal control system for thermal vacuum chambers. A final goal of this research is development of cryogenic blower. Design requirements of a blower are 150 CFM flow rate, 0.5 bara pressure difference, hot and cold temperatures. This paper describes the performance analysis of impeller by 1D, CFD commercial software, the design of the thermal protection interface between the driving part and the fluid part. The performance of the cryogenic blower is confirmed by test at the standard air condition and is verified by on the thermal vacuum chamber at the real operating condition.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1006-1010
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• 2017

This paper describes the design and test of the thermal control and fire safety system for thermal control and the fire/explosion prevention of inside the compartment during the preparation and operation of the space launch vehicle at the launch pad. The system considered here is for the test launch vehicle which is being developed as part of the development of the Korean Space launch vehicle-II. This system applies the high pressure system based on the heritage of Naro launch vehicle. The selection of thermal control and fire safety system from high pressure and low pressure system is done in consideration of the characteristics of the launch pad gas supply system and the characteristics of launch vehicle, and the system configuration is also changed accordingly. As a result, it has been confirmed that the developed system satisfies the initial design conditions through the test. Moreover the system will be applied to the development of the Korean launch vehicle in the future.

• ETRI Journal
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• v.7 no.3
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• pp.30-34
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• 1985

전자장비가 요구되는 신뢰도 및 적절한 응답 속도를 가지기 위해서는 부품 및 장비에 대한 열설계를 통하여 장비의 온도를 특정지워야 한다. 본 고찰에서는 장비의 열설계에 대한 기본적인 사항으로서 열설계에 필요한 인자들을 소개하고 예로서 PCB의 열전달 과정을 해석함으로써 온도 제어를 위한 방법을 제시한다.

• ICROS
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• v.3 no.5
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• pp.12-16
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• 1997

조립 작업시 사람이 이용하는 방법을 수학적으로 구현한 미세외란/상관관계에 기초하여, 이의 기본 원리와 응용에 대하여 살펴보았다. 이 방법의 가장 큰 특징은 기존의 이치 제어기에 외부 궤환 제어기를 첨가함으로써 힘에 의하여 안내되는 제어기로 구조를 개선할 수 있다는 점이다. 이러한 제어기를 갖는 로봇을 열 교환기 조립작업에 응용한 예를 들었으며, 로봇을 이용한 다른 조립 작업에도 매우 유용하게 사용될 수 있으리라 생각된다.

• Aerospace Engineering and Technology
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• v.6 no.1
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• pp.64-73
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• 2007

A Large thermal vacuum chamber (LTVC) for space environment simulation on large satellites was successfully developed and constructed by KARI (Korea Aerospace Research Institute) in Korea with a local company. This chamber has an effective diameter of 8 meters and depth of 10 meters, and is composed of vacuum system, thermal control system, and anti-vibration system. Temperature below $-190^{\circ}C$ is maintained over the thermal shroud wrapping a satellite under $3.7{\times}10^{-5}Pa$ ($5{\times}10^{-7}torr$) vacuum level, and optical test can be done in this chamber by seismic mass with $10^{-5}g_{rms}$ or lower vibration level. In addition, the shroud temperature can be increased up to $123^{\circ}C$ using halogen lamps. Chamber control program based on PLC (Programmable Logic Controller) could control this large thermal vacuum chamber automatically.

• Journal of Bio-Environment Control
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• v.23 no.1
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• pp.26-30
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• 2014

Purpose of this study was a development of a sprayer arm auto control system that could be operated according to distance from pear trees for automation of pest control. Auto control system included two parts, hardware and software. First, controller was made with an MCU and relay switches. Two types of ultra-sonic sensors were installed to measure distance from pear trees: one on/off type that detect up to 3 m, and the other continuous type providing 0~5 V output corresponding to distance of 0~3 m. Second, an auto control algorithm was developed to control. Each spraying arm was controlled according to the sensor-based distance from the pear trees. And it could dodge obstacles to protect itself. Max and min signal values were eliminated, when five sensor signals was collected, and then signals were averaged to reduce sensor's noises. According to results of field experiment, auto control test result was better than non auto control test result. Spraying rates were 69.25% (left line) and 98.09% (right line) under non auto control mode, because pear trees were not planted uniformly. But, auto control test's results were 92.66% (left line) and 94.64% (right line). Spraying rate was increased by maintaining distance from tree.

• Bulletin of the Korean Space Science Society
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• 2005.04a
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• pp.42-42
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• 2005

• 한국신재생에너지학회:학술대회논문집
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• 2009.06a
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• pp.274-277
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• 2009

본 논문에서는 소형 PEM(Proton Exchange Membrane) 연료전지 스택의 BOS(Balance of Stack) 제어에 관하여 논의한다. 별도의 가습 장치가 필요치 않고 BOS의 구성이 비교적 간단한 소형 PEM 연료전지 시스템에서는 팬과 퍼지밸브만의 제어를 통해 스택 내부 수분의 조절과 열 관리가 수행된다. 따라서 본 논문에서는 부하에 따른 최적의 공기유량을 계산하고 요구되는 유량의 공급을 위해 팬을 제어하는 알고리즘을 통해 소형 연료전지 시스템의 과도응답 특성과 안정성을 향상시키는 방법에 관하여 제안한다. 150W급 소형 연료전지 시스템을 꾸미고, 마이크로컨트롤러를 이용한 제어회로를 구현하여 실험함으로써 제안된 알고리즘의 유용함을 검증하였다.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.13 no.8
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• pp.3774-3778
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• 2012

A dynamic simulation of a fully thermally coupled distillation is conducted for the design of a possible operation scheme, and its performance is examined with an example process of reformate fractionation process. The outcome of the dynamic simulation indicates that the column can be operated by using a $3{\times}3$ control structure. The structure consists of three controlled variables of the compositions of overhead, side products and bottom and three manipulated variables of the flow rate of reflux, liquid split ratio between a main column and a prefractionator and steam.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.2
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• pp.179-185
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• 2015

The main objective of thermal design for a space-borne FPA(Focal Plane Assembly) is to provide stable thermal environment during imaging operation and thus maintain the image quality. An FPA must be maintained within its operating temperature range and cooled down to its initial temperature soon enough for the next imaging operation. This paper describes the study result on performing trade-off studies for FPA thermal design by using simplified thermal node analysis about FPA preliminary design. It also describes the verification results of the study by comparing thermal analysis results and trade-off study results. According to results, we can conclude that this approach is useful for simple and quick trade-off studies without thermal analysis based on thermal math models.