• Proceedings of the KAIS Fall Conference
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• 2011.12b
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• pp.660-663
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• 2011

우주방사선이나 과도펄스(Transient Radiation) 형태의 감마 방사선이 반도체에 조사되면 소자 내부에서 짧은 시간에 다량의 전하가 생성된다. 이 전하들과 증폭된 과전류는 소자의 고장(Upset, Latchup)과 오동작을 유발시키게 되고 나아가 전자부품이 소진(Burnout)되는 직접적인 원인이 된다. 본 연구에서는 이러한 핵폭 방출 과도방사선에 대한 전자부품/장비의 내방사선관련 기초연구로 군전자부품의 감마-과도방사선에 대한 피해분석 시험을 수행하고 나아가 과도방사선 방호기술 체계구축의 필요성에 대해 논하였다. 과도펄스 방사선시험은 군용으로 분류된 반도체 칩을 대상으로 포항 전자빔가속기를 사용하였다. 핵폭발 방출 과도방사선을 모사하기 위해 감마선 변환장치를 MCNP 설계를 통해 제작하고 단일모드의 마이크로초 단위 감마펄스 방사선을 방출시켜 시험대상 칩을 부착한 시험보드에 조사하는 과정으로 실험을 진행하였다. 온라인 고속 측정장치를 통한 전자소자의 과도방사선시험에서 다양한 피해현상을 측정할 수 있었고, 열상카메라 촬영을 통하여 과열상태를 관측함으로써 피해현상의 검증과 더불어 소진현상으로의 전개 가능성을 확인하였다.

• Proceedings of the KIEE Conference
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• 2008.07a
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• pp.1031-1033
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• 2008

차세대 한국형 고속열차는 분산형 시스템으로 최고속도 400km/h, 운행속도 350km/h을 목표로 개발중에 있다. 차세대 고속열차의 신호시스템은 기존선의 자동열차정지(ATS, Automatic Train Stop) 및 자동열차방호(ATP, Automatic Train Protection)와 고속선의 자동열차제어(ATC, Automatic Train Control) 신호방식을 모두 사용하는 ATP+ATS+ATC 형태의 차상장치가 개발 설치될 예정이다. 따라서 이러한 장치의 개발과 연계하여 차세대 한국형 고속열차는 기존 경부고속선에서 시험주행을 할 예정이다. 따라서 기존 경부고속선에서 차세대 고속열차의 최고 속도시험를 위한 신호분야의 방안을 검토하고자 한다. 본 논문에서는 3가지의 방안을 제시하여 적합성과 운영효율성을 고려하여 최적의 방안을 도출하는 방식으로 전개할 예정이다.

• Journal of the Korea Institute of Military Science and Technology
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• v.19 no.2
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• pp.145-154
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• 2016

In this paper, a pneumatic device for the deployment performance verification of canards deployed by inertia has been designed and the performance of the pneumatic device has been proven through analysis and tests. The pneumatic conveying process, orifice opening process and piston movement process of the pneumatic device were investigated by using numerical methods. The orifice diameter, pressure in a pressure tank and type of gas were regarded as the main design parameters of the pneumatic device. The error rate between analysis and test results under the same conditions was within 4 %. The accuracy of numerical methods used in this study were validated.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.6
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• pp.529-534
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• 2014

Pyrotechnic devices are widely used for space appendages. However, a cube satellite requirements do not permit the use of explosive pyrotechnic device. A nichrome burn wire release has typically been used for holding and release of deployable appendages of the cube satellite due to its simplicity and low cost. However, relatively low mechanical constraint force and system complexity for application of multi-deployable systems are disadvantages of the conventional mechanism. To overcome these drawbacks, we developed a hinge driving segmented nut type holding and release mechanism based on the nichrome burn wire release. The functional performance of the mechanism has been verified through release function test, static load test and shock level measurement test.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.4
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• pp.53-59
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• 2003

Strain Energy Hinge(SEH) has been used in Korea Multi-purpose Satellite(KOMPSAT) series to deploy the solar panel due to the good record of reliability. However, when it reached a desired deployment position, a large buckling force is applied to the main body. This may cause structural damage and also affect control of the satellite. Therefore, reliable dynamic analysis for the deployment system is required at a design stage. Moreover, various mission of a satellite has made the size of solar panels got bigger, so elastic effect has to be considered seriously to get more precise analysis results. In this paper, a dynamic analysis method to predict the deployment is verified by KOMPSAT-2 deployment test.

• Journal of Aerospace System Engineering
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• v.13 no.5
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• pp.94-101
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• 2019

The dynamic characteristics of the composite reflector panels are numerically and experimentally investigated. A dynamics model of the panel is analytically developed based on a deployment mechanism of the antenna. The deployment is passively activated using elastic energy of a spring with two rotational degrees of freedom. Using the flexible multi-body dynamic analysis ADAMS, dynamic behavior of the panels such as velocities, deformations, as well as reaction forces during the deployment, are investigated in the gravity and zero-gravity cases. The reflector panel is manufactured using carbon fiber reinforced plastics (CFRPs) and its deployment characteristics are experimentally observed using a zero-gravity deployment test. The impact response and vibration problems that occur during deployment of the antenna panel have been identified and reliably deployed using dampers.

• 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 Society of Naval Architects of Korea
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• v.38 no.3
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• pp.23-30
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• 2001

The cavitation noise of high-speed propellers was experimentally studied using new measurement device in KRISO cavitation tunnel. A series of cavitation noise tests were carried out for 6 propellers with various sections, loading distributions, and a different area ratio. From the experimental results, the noise characteristics for various cavitation patterns and the noise performance for a series of propellers were analyzed. These can be used for full-scale prediction study of the noise and optimum design of high-speed propellers.

• 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 Aerospace System Engineering
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• v.17 no.2
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• pp.94-102
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• 2023

A nylon wire holding and release mechanism (HRM) has been widely used for deployable applications of CubeSat owing to its simplicity and low cost. In general, structural safety of solar panel with an HRM has been designed by performing structural analysis under a launch environment. However, previous studies have not performed thermal analysis for HRM in an on-orbit environment. In this study, Launch and Early Orbit Phase (LEOP) thermal analysis was performed to evaluate thermal stability of the mechanism in the orbital thermal environment of the pogo pin-based HRM applied to CubeSat. In addition, the effectiveness of the thermal design and performance of the pogo pin-based HRM were verified through a thermal vacuum test.