• Journal of the Korean Society of Propulsion Engineers
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• v.2 no.3
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• pp.80-89
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• 1998

Propulsion subsystem transfers KOMPSAT into mission orbit and controls its attitude. Design factor consists of structure safety, electrical circuit design, consumable power estimation of thermal hardwares, damping device design of fuel transient pressure, and system configuration design by considering plume effect from thruster firing. System level analysis should be performed for verification of system design under launch vehicle and orbital environment. Electrical functional test of thermal control hardware, proof pressure test, cleanliness verification test, and internal/external leakage test of fuel feeding system should be carried out for performance estimation of propulsion system. Design and assembly process of propulsion subsystem was depicted and reliability of system was verified by test analysis in this paper.

• Journal of Aerospace System Engineering
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• v.18 no.5
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• pp.103-111
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• 2024

A spaceborne cryogenic cooler is known to undesirable microvibration disturbances during its on-orbit operation, which is one of the main sources that degrades the image quality of an observation satellite with a high resolution. Several types of vibration isolation systems based on passive approaches have been developed for reducing such microvibration of a linear cooler. A dual coil-spring-type passive isolator was developed. To verify its performance and structural characteristics, transmissibility measurement and modal survey were performed with properly designed dummy instead of a cooler. Results were then used as pass/fail criteria before/after each test. To verify structural and thermal stability of the dual coil-spring-type passive isolator for launch and on-orbit environment, vibration (random and sinusoidal) test, shock test, and thermal cycle test were performed successfully.

• Journal of Aerospace System Engineering
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• v.17 no.2
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• pp.86-93
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• 2023

Pyrotechnic separation devices have been widely used as holding and release mechanism for deployable appendage. However, pyro-shock can cause temporal or permanent damage on shock sensitive components such as electronics, mechanism, and brittle components. This study proposed a low-stiffness blade based passive shock absorber using a multi-layered stiffener laminated with viscoelastic acrylic tapes for reducing transmitted pyro-shock upon explosion of pyrotechnic separation devices. The multi-layered structure with viscoelastic tape has high-damping characteristics to effectively secure structural integrity of low-stiffness blades under the launch environment. The design effectiveness was verified through a shock test by dropping a pendulum. The structural integrity of the shock absorber under a launch environment was evaluated through structural analysis under load conditions with a deployable payload.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.48 no.5
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• pp.383-390
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• 2020

Wedge locks have been widely used for spaceborne electronics for mounting or removal of a printed circuit board (PCB) during integration, test and maintenance process. However, it can basically provide a mechanical constraint on the edge of the board. Thus, securing a fatigue life of solder joint for electronic package by limiting board deflection becomes difficult as the board size increases. Previously, additional stiffeners have been applied to reduce the board deflection, but the mass and volume increases of electronics are unavoidable. To overcome the aforementioned limitation, we proposed an application of multi-layered PCB sheet with viscoelastic adhesive tapes to implement high-damping capability on the board. Thus, it is more advantageous in securing the fatigue life of package under launch environment compared with the previous approach. The basic characteristics of the PCB with the multi-layered sheet was investigated through free-vibration tests at various temperatures. The effectiveness of the proposed design was validated through launch vibration test at qualification level and fatigue life prediction of electronic package based on the test results.

• The Journal of the Korea institute of electronic communication sciences
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• v.11 no.9
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• pp.855-860
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• 2016

This study describes the design and implementation of digital Payload power supply. We materialized the interface of the PLDIU and power supply of a satellite bus, and minimized the potential for the occurrence of such erroneous operation circuit ESD through the WCA of the space environment. We designed a reliable power supply through simulation for a TID according to the vibration generated during the launch and space radiation environment, and found no problem in the function and performance through the test space environment after production.

• Journal of the Korean Home Economics Association
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• v.39 no.7
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• pp.59-70
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• 2001

The study was designed to heap reduce daily household waste and promote the recycling of society's resources. the focus is on promoting environment-friendly activities and slevating a sense of nature-conscious domestic welfare, as well as providing wars to encourage garbage-savvy shopping, waste disposal by content and recycling. The thesis utilized demographic data obtained from 225 female homemakers and includes results based on frequency, ratio, mean, Duncan's Multiple range Test and Multiple Regression analysis. The main results are as follows: 1. Environmental consciousness appears to be higher than that of the adjustment of purchases to reduce waste and of recycling. Conversely more action seems to be taken on the waste disposal separation established since the launch of the volume-based waste collection fee system than on environmental education. 2. Homemakers with relatively higher environmental consciousness reciprocate with correspondent shopping habits, waste disposal eparation and recycling. Factors that influence daily waste reducing action include environmental consciousness homemaker employment status and the type of residence. 3. Activities reducing daily domestic wastes appear to effect a meaningful variable in explaining a sense of environmental welfare. The more respondents practice related shopping habits, waste disposal separation or recycling the more they recognize their living environment as desirable.

• Proceedings of the KSRS Conference
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• 2007.10a
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• pp.282-285
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• 2007

Satellite observed brightness temperature simulation using a radiative transfer model (here after, RTM) is useful for various fields, for example sensor design and channel selection by using theoretically calculated radiance data, development of satellite data processing algorithm and algorithm parameter determination before launch. This study is focused on elaborating the simulation procedure, and analyzing of difference between observed and modelled clear sky brightness temperatures. For the CMDPS (COMS Meteorological Data Processing System) development, the simulated clear sky brightness temperatures are used to determine whether the corresponding pixels are cloud-contaminated in cloud mask algorithm as a reference data. Also it provides important information for calibrating satellite observed radiances. Meanwhile, simulated brightness temperatures of COMS channels plan to be used for assessing the CMDPS performance test. For these applications, the RTM requires fast calculation and high accuracy. The simulated clear sky brightness temperatures are compared with those of MTSAT-1R observation to assess the model performance and the quality of the observation. The results show that there is good agreement in the ocean mostly, while in the land disagreement is partially found due to surface characteristics such as land surface temperature, surface vegetation, terrain effect, and so on.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 2003.06a
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• pp.768-771
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• 2003

The impulse between launch vehicle and atmosphere can generate a lot of noise and vibration during the process of launching a satellite. Structurally, electronic equipment (KOMPSAT 2, RDU : Remote Drive Unit) of a satellite consists of aluminum case containing PCB (Printed circuit boards). Each PCB has resistors and IC (Integrated circuits). Noise and vibration of wide frequency band are transferred to the inside of fairing, subsequently creating vibration of the electronic equipment of the satellite. In this situation. random vibration can cause malfunctioning of the electronic equipment of the device. Furthermore, when tile frequency of random vibration meets with natural frequency of PCB. fatigue fracture nay occur in the part of solder joint. The launching environment, thus. needs to be carefully considered when designing the electronic equipment of a satellite. In general. the safety of the electronic equipment is supposed to be related to the natural frequency, shapes of mode and dynamic deflection of PCB in the electronic equipment. Structural vibration analysis of PCB and its electronic components can be performed using either FEM(Finite Element Method) or vibration test. In this study. the natural frequency and dynamic deflection of PCB are measured by FEM, aud the safety of the electronic components of PCB is being evaluated according to the results. This study presents a unique method for finite element modeling and analysis of PCB and its electronic components. The results of FEA are verified by vibration test. The method proposed herein may be applicable to various designs from the electronic equipments of a satellite to home electronics.

• The Journal of the Korea institute of electronic communication sciences
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• v.12 no.3
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• pp.427-432
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• 2017

This study describes the design and implementation of SHF band Downconverter Digital Satellite Communication. The SHF band Downconverter unit consists of PLDRO and Frequency converter. In Frequency converter, microstrip BPF and LPF designed through the pre EM simulation are implemented to minimize the unwanted spurious in Frequency converter. Through the pre-simulation analysis of space environment, the possibility of and minimized about the malfunction of equipment and we designed a reliable SHF band Downconverter through simulation for a TID according to the vibration generated during the launch and space radiation environment, and compared pre-simulation of main performance results to test results about main performances of SHF band Downconverter after production.

• Aerospace Engineering and Technology
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• v.2 no.2
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• pp.66-75
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• 2003

A high intensity acoustic test facility has been constructed at Korea Aerospace Research Institute (KARI). Spacecrafts are tested in the facility to check the reliability on acoustic environment of launch vehicles. The reverberant chamber of the facility has a volume of 1,228 cubic meters and provides an acoustic environment of 152 dB over the frequency range of 25 Hz to 10,000 Hz. This paper describes how the basic parameters of the facility including a chamber and power generation system are designed. Moreover, design parameters including acoustic spectrum, acoustic modulator characteristics, reverberation time and isolation characteristics are experimentally verified during acceptance tests.