• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.1
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• pp.33-38
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• 2005

Forcing at the rotor blade passing frequencies is responsible for the majority of vibration related problems on helicopters. Blade passing frequencies of helicopters are generally in the range 10~30 Hz and the interest modes of the helicopters also exist in the range. By the way, the installation of a heavy sensor at the front extremities of an imported helicopter may change the modal characteristics of the airframe and results in the resonance with rotor passing frequencies. To avoid too large a change in the dynamics of the overall airframe, we determined how to install a heavy sensor through conceptual approach and finite element analysis. The results of a ground vibration test for airframe with sensor mount system clearly demonstrate that the installation design is acceptable dynamically.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.691-698
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• 2017

In this study, the injector transfer function (ITF) of a gas-gas coaxial jet-swirl injector is measured by applying excitation to jet or swirl flow using a loudspeaker. As a result of measuring the ITF according to the variation of feed system length, the ITF peak occurs at the resonance frequency of the space where the perturbed flow passes. When applying the excitation to the jet flow, as the jet flow increases up to 56 slpm, the magnitude of ITF decreases, and ITF increases thereafter. Therefore the larger the velocity difference between the jet and the swirl flow, the larger the ITF. In the case of the swirl excitation, the ITF decreases as the jet flow increases because of the decrease of the energy with respect to the constant flow at the downstream. This difference is caused by the location of the hot wire anemometer on the downstream of the injector center axis.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.4
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• pp.99-107
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• 2018

In this study, the injector transfer function (ITF) of a gas-gas coaxial jet-swirl injector is measured by perturbing jet or swirl flow using a speaker as jet flow increases. As a result of measuring the ITF varying feed system length, a peak occurs at a resonance frequency of space where the perturbed flow passes. With jet excitation, the ITF magnitude decreases, but increases thereafter as increasing the jet flow. Therefore the larger the velocity difference between jet and swirl flow, the larger the ITF. With swirl excitation, ITF decreases as increasing the jet flow because of the energy decrease with respect to the constant downstream flow.

• Journal of the Korean Vacuum Society
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• v.16 no.2
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• pp.91-98
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• 2007

The Korea Research Institute of Standards and Science (KRISS) has developed a residual gas analyzer (RGA) calibration system and measured gas sensitivities for two different types QMSs using nitrogen, argon, and helium. Different gas sensitivities were identified according to mass and pressure, so it was revealed that the gas sensitivity correction is necessary for proper use of mass spectrometers.

• The Korean Journal of Rheology
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• v.9 no.4
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• pp.190-199
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• 1997

단열용도의 폴리우레탄 미세포 포움의 가공에 대한 연구를 수행하였다. 미세포 구조 를 얻기 위해서는 핵생성율을 증진시키고 균일한 분포의 기포를 생성시켜야 한다. 이를 위 해 이산화탄소 기체를 풀리올과 이소시아네이트에 각각 과포화시키고 충돌혼합하여 초음파 가진을 적용하였다. 이산화탄소 기체가 수지 내부에서 기포 내부로 확산함에 따라 기포의 성장이 조절된다고 가정하고 금형이 충전되는 동안에 금형 내부에서의 기포성장기구를 이해 하기 위하여 수치적인 방법으로 이론적 연구를 수행하였다. 경화 시간과 확산 경계를 고려 하여 최종적인 기포의 크기를 계산하였으며 반응속도론을 고려하여 중합반응동안의 폴리우 레탄의 점도의 변화를 예측하고 경화 시간을 결정하였다. 실험적으로 결정된 기체 분자수를 기준으로 하여 이론적으로 확산경계를 예측하였다. 화학적 발포제인 물과 함께 물리적 발포 제인 이산화탄소를 각각 1,2,3기압의 포화압력으로 변화시키면서 폴리올과 이소시아네이트에 포화시켜 폴리우레탄 포움을 제작하고 제작된 포움의 밀도, 열전도도, 및 기포의 수와 지름 을 측정하였다. 측정된 결과로부터 이산화탄소의 포화압력과 초음파 가진이 포움의 기포핵 생성에 미치는 영향을 살펴보았다.

• Journal of ILASS-Korea
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• v.20 no.3
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• pp.168-174
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• 2015

Combustion instability is critical problem in developing liquid rocket engine. There have been many efforts to solve this problem. In this study, the method was sought through the injector as part of these efforts to suppress combustion instability. If the injector can suppress the disturbance coming from the supply line as a kind of buffer it will serve to reduce combustion instability. Especially we target at gas propellant oscillation in gas-centered swirl coaxial injector. The phenomenon is simulated with acoustic excitation of speaker. The film thickness response at injector exit was measured by using a liquid film electrode. Also the response of spray to the disturbance was observed by high-speed photography. Gas-liquid momentum flux ratio and the frequency of feeding gas oscillation were changed to investigate the effect of these experimental parameters. The trend of response by varying these parameters and the cause of weak points was studied to suggest the better design of injector for suppressing combustion instability.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.5
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• pp.482-489
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• 2010

This paper describes the test procedure, instrumentation, verification methodology and the results of the ground vibration test(GVT) and force vibration test(FVT) of the SmartUAV aircraft to estimate experimentally dynamic characteristics of the aircraft. Bungee cords are used to emulate free-free boundary conditions of the test aircraft. The SmartUAV is excited by three shakers and one-hundred frequency response functions(FRF's) is measured. The FRF's are reduced and analyzed to identify the dynamics parameters of the SmartUAV. To extract modal parameters of the SmartUAV such as, natural frequencies and damping ratios, the poly-reference least square complex exponential method is used in the time domain. The mode shape coefficients are estimated with the least squares frequency domain method to identify the vibration modes. The FVT was performed by fixed sine frequency with three shakers on the x, y and z direction and vibration characteristics of structures and detail equipments are measured.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.04a
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• pp.25-25
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• 2000

가스발생기와 같이 로켓모터에서 추력이 아닌 기체압 형태의 에너지를 일정한 시간동안 얻고자 하는 경우, 로켓모터의 크기 및 추진제 충전율을 고려하여 그레인 형태를 단면 연소형으로 선택할 수 있다. 단면 연소형 그레인을 가진 로켓모터는 그레인의 연소시, 일찍 연소된 부분의 라이너가 추진제 연소 화염에 노출되면서 표면부터 서서히 분해가 진행되며, 분해물질의 일부는 추진제에 포함된 산화제 성분에 의해 산화되어 기체화 될 수 있다. 산화제 성분이 충분치 않은 경우에는 고체 입자 형태로 추진제 연소 기체와 함께 배출되며, 이는 일차연기(primary smoke)의 일종으로 볼 수 있다. 가스 발생기에서 얻고자 하는 기체는 고체 입자가 포함되지 않은 깨끗한 기체형태인 경우가 대부분이며, 따라서, 무연 라이너 및 내열재의 연구가 필요하다.

• Proceedings of the Materials Research Society of Korea Conference
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• 2003.03a
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• pp.42-42
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• 2003

Ni/Si 기판상에 CH$_4$, H$_2$, $N_2$의 혼합기체를 사용하여 $700^{\circ}C$에서 5분 동안 MPECVD법으로 탄소나노튜브 성장시켰다. 이 과정에서 CH$_4$, H$_2$에 대한 $N_2$의 유량비를 여러 가지 값으로 변화시켜 그 성장 양상을 살펴보았다. 혼합기체 내 질소의 함량에 따라 나노튜브의 성장길이와 quality가 달라짐을 SEM과 Raman spectroscopy 측정을 통하여 확인하였다. 나노튜브의 성장 시 혼합기체 내 주입하는 질소량에 의해 나노튜브의 성장길이가 변화됨을 SEM을 통해 관찰할 수 있었고 혼합기체 내 질소의 비율이 커질수록 carbonaceous particle 등의 감소로 인한 나노 튜브의 quality가 향상됨을 Raman spectra를 통해 확인할 수 있었다. 또한 TEM과 SEM 관찰을 통해 성장된 탄소나노튜브가 대나무(bamboo) 구조를 가진 수직 배향된 다중벽 탄소나노튜브임을 확인하였다.

• Membrane Journal
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• v.12 no.2
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• pp.107-119
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• 2002

Carbon-silica ($C-SiO_2$) membranes can be easily prepared by the pyrolysis of two-phase copolymers containing an aromatic imide block and a siloxane block and remarkably high permselectivities of $He/N_2, O_2/N_2,$ and $CO_2/N_2$. The pyrolysis of the imide-siloxane block copolymers was carried out at different final temperatures, $600^{\circ}C, 800^{\circ}C,$ and $1000^{\circ}C$ under an inert atmosphere, and is the first reported case of the precursors being used for the preparation of carbon membrane. The polymeric precursors were synthesized in a wide range of siloxane content and different final morphology, and the pyrolozed membranes were tested with a high vacuum time-lag method at $25^{\circ}C$ and 76cmHg of feed pressure. In experiments with He, $CO_2, O_2 \;and \;N_2$, the membranes were found to have good $O_2/N_2$ selectivity up to 32.2 and $O_2$ permeability on the order of $10-8/cm^2(STP)cm/cm^2seccmHg.$.