• Journal of the Korean Society of Propulsion Engineers
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• v.8 no.2
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• pp.46-53
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• 2004

Ultrasonic testing method has been developed to evaluate flaw of adhesive layers in blast tube for the reliability of the rocket nozzle. The ultrasonic reflection from the interface between the steel sheet and the epoxy adhesive is measured with a high-frequency Pulse-echo setup in order to identify contact debonding and missing adhesive in epoxy layer between steel and FRP layers. The steel sheet is resonated by low-frequency ultrasound, and the gap size underneath the measuring location is estimated from the resonance responses. For practical application in industry an automated testing system has been developed where the proposed approach is implemented. The performance of the proposed approach has been verified by actual measurement of gap sizes from the cross-sections of cut specimens using an optical microscope.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.10a
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• pp.230-237
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• 2003

Ultrasonic testing method has been developed to evaluate adhesive layers in blast tube for the reliability of the rocket. The main objective of the present work was to find debonding and missing adhesive in epoxy layer between steel and FRP layers. In this approach, the ultrasonic reflection from the interface between the steel sheet and the epoxy adhesive is measured with a high-frequency pulse-echo setup in order to identify contact debonding and missing adhesive. Then, the steel sheet is excited to resonance by low-frequency ultrasound, and the gap size underneath the measuring location is estimated from the resonance responses. For practical application in industry an automated testing system has been developed where the proposed approach is implemented. The performance of the proposed approach has been verified by actual measurement of gap sizes from the cross-sections of cut specimens using an optical microscope.

• Journal of the Korea Institute of Military Science and Technology
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• v.20 no.1
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• pp.98-107
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• 2017

Electric components equipped with naval shipboards must endure mechanical shock caused by various mechanical impulsive sources. Thus the components must be designed carefully and reliability test is an essential procedure before use. In this study, a new design technology applicable to a large and heavy shock generation system which can generate various specific real mechanical shocks in specified time domain was introduced. Commonly, the shock transmitted through the wall of naval shipboard consists of dual shocks. The primary shock is of a very high amplitude and very short period half-sine form. The following shock is of an exponentially decaying harmonic form of relatively longer period. Based on the different dynamic characteristics of two shocks, we proposed a sequential design procedure to determine spring and damping coefficients of the generation system. Some numerical simulation results showed the feasibility of the proposed method.

• Proceedings of the KIPE Conference
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• 2012.11a
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• pp.245-246
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• 2012

ITER 초전도자석 전원공급장치의 예비설계가 실제 크기 6펄스 R&D 컨버터의 제작 및 시험결과를 기반으로 수행되었다. ITER 컨버터는 자체적으로 지지되는 알루미늄 버스바 구조로 제작되며, 이 버스바에 양면 클램핑 방식으로 조립되는 Thyristor 스위치는 4인치 규격으로써 컨버터의 종류에 따라 한 개의 암 당 8 - 16 개의 소자가 병렬로 구성된다. ITER 컨버터 예비설계는 알루미늄 버스바 구조설계, 컨버터 냉각설계, 컨버터 전기회로 설계, 컨버터 고장해석 및 보호설계, 시험절차 및 요건 등을 포함하며, 본 논문에서 그 설계결과를 기술한다. ITER 컨버터는 예비설계 결과를 기반으로 상세설계 및 제작설계를 거친 후 제작된다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.163-167
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• 2008

This paper presents pressure fluctuation characteristics of a 30 ton-f class liquid rocket engine combustor. Combustion stability of the combustor was evaluated using the results 46 firing tests performed with a varying O/F ratio and chamber pressure. The RMS value of pressure fluctuation during the steady state combustion was less than 2.6% of the static chamber pressure, demonstrating static stability of the combustion phenomenon. The decay time of pressure fluctuation caused by forced disturbance of a pulse gun was found to be less than 3.5 msec verifying dynamic stability of the combustor.

• The Journal of Korean Institute of Communications and Information Sciences
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• v.27 no.2B
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• pp.160-169
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• 2002

While radar operator recognizes and tracks threat targets through the scope, it is essential to overcome the jamming signal that disturbs the normal operation of the radar. Therefore, to train operator and test the EW capability of the radar, this paper proposed the jamming signal simulation algorithm and design results to generate the deception jamming(range, velocity, angle deception and multiple false targets) and noise jamming signals(spot, barrage, swept spot and cover pulse noise). And also, the radar jamming signal simulator composed of the 6 constituents is developed on basis of the proposed algorithm and digital circuit design technique and confirmed the validity of the developed simulator by means of the test results to generate the various jamming signal.

• Proceedings of the Korean Vacuum Society Conference
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• 2014.02a
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• pp.244.2-244.2
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• 2014

금속, 플라스틱, 유리 등의 재료 표면에 다양한 색상을 표현하기 위해 일반적으로 습식 도금을 많이 적용하고 있다. 하지만 습식 도금은 공정 수가 많을 뿐만 아니라 위험물질 및 오염물질을 많이 사용하기 때문에 산업사고, 환경오염 등을 야기 시킨다. 따라서 본 연구에서는 친환경적 방법인 물리적기상증착(PVD ; Physical Vapor Deposition) 방식의 한 종류인 스퍼터링(Sputtering)으로 색상을 구현하였다. PVD 방식의 증착은 습식 도금 방식에 비해 친환경적이며, 전처리에서 후처리까지 한 공정으로 가능하다는 점이다. 스퍼터링은 PVD의 다른 방식인 E-beam 방식에 비해 대량생산을 할 수 있다는 장점이 있다. 양산형 스퍼터링 장비(${\Phi}1200mm{\times}H1400mm$)로 실험을 진행하였으며, 증착 물질은 Ti, Al, Cr 을 사용하였고, 반응성 가스(Reactive Gas) 로는 N2, C2H2 가스를 사용하였다. 전처리는 LIS (Linear Ion Source)로 식각(Etching) 하였고, 펄스직류전원공급장치(Pulsed DC Power Supply)를 사용하여 증착 하였으며, 증착시 기판에 bias (-100 V)를 인가 하였다. 그 결과 회색계열, 갈색계열 등 여러가지 색을 구현할 수 있었으며, 증착된 박막의 특성을 알아보기 위하여 색차계, 내마모 시험기, 연필경도 시험기를 사용하였다. 향후 후처리 공정으로 내지문(AF ; anti fingerprint coating) 박막 등과 같은 실용적인 박막을 증착할 계획이다.

• Journal of the Korean Society of Propulsion Engineers
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• v.13 no.6
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• pp.34-40
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• 2009

The present study describes the methods and standards for the combustion stability assessment of a thrust chamber and a gas generator as parts of a liquid rocket engine. The first method uses a statistical approach through typical static combustion tests and the second one a dynamic assessment identifying decaying characteristics of pressure fluctuations excited by a pulse generating device. Based on accumulated test results, it is concluded that the maximal values for combustion stability are 3% of a chamber static pressure with a Root-Mean-Square value of pressure fluctuations, and 10 msec with a decay time.

• Journal of the Korean Society of Propulsion Engineers
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• v.8 no.4
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• pp.84-90
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• 2004

A performance evaluation is made in terms of thrust, impulse bit. and specific impulses for a set of mono-propellant hydrazine thrusters producing 0.95 lbf of nominal thrust at an inlet pressure of 350 psia. With a brief description on the hot-firing test configuration and procedures. a typical data obtained from steady-state firing mode is given directly showing the variational behavior of propellant supply pressure, mass flow rate, vacuum condition, and thrust. The performance features are successfully compared to the reference criteria of 1-lbf standard mono-propellant rocket engine. Additionally. a statistical inter-thruster treatment is concisely depicted for the justification of selected thrusters as a grouped member of flight model for spacecraft propulsion system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.230-237
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• 2012

The ultrasonic resonance method was applied to detect the disbond interface and empty layer between steel and FRP of the exit cone. The ultrasonic resonance method can easily detect the disbond interface and empty layer by amplifying the ultrasonic signal, but pulse echo method is difficult to distinguish adhesive interface from disbond interface or empty layer. The resonance frequency was predicted using the pressure reflection coefficient of 3-layered medium, and measured from ultrasonic signal of the test block using Fast Fourier Transform. The ultrasonic resonance proved that the predicted resonance frequency was in good agreement with the measured resonance frequency.