• 한국항행학회논문지
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• 제24권5호
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• pp.368-373
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• 2020

4차 산업혁명 주요기술을 체계적으로 항공우주력에 적용하기 위해서는 항공우주력 기술 모델이 필요하다. 예전에는 항공우주력 기술 모델링을 위해 항공우주력 기본특성인 고도, 속도, 거리에 기반한 프로펠러 모델이 주로 사용되었다. 그러나 4차 산업혁명 시대에는 수많은 기술들이 융합되기 때문에 새로운 모델이 필요하다. 본 논문에서는 새로운 항공우주력 기술 모델로 제트엔진 모델을 정립하였다. 또한 요구능력 기반이 아닌, 항공우주력 기술 모델을 기반으로 하는 미래 항공우주무기체계 도출과정을 제시한다. 미래 전장환경과 신기술을 적용한 선진국의 개념발전 연구사례를 통해 새로운 개념의 무기체계를 도출할 수 있다.

• 한국항공우주학회지
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• 제50권7호
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• pp.489-496
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• 2022

본 논문에서는 한국항공대학교에서 설계 및 개발한 태양광 무인기인 KAU-SPUAV의 시스템을 소개하고 비행시험을 통하여 성능을 검증하였다. 두 가지 버전의 태양광 무인기의 제원과 전장 구성 그리고 지상 관제 시스템을 소개하였다. 제시한 시스템으로 전파맵 구축, 제주도 해안선 일주 그리고 장기 체공 비행의 세 가지 임무 비행을 수행하였다. 각 임무는 태양광 무인기의 특성을 이용하는 비행으로서 주로 장시간 및 장거리 임무로 구성되었다. 본 연구를 통하여 태양광 무인기의 장기체공 능력을 이용해 다양한 임무에 사용될 수 있음을 보였다. 비행 시험 결과를 기반으로 시스템 추가 개선을 통하여 성능 향상을 도모할 수 있음을 확인하였다.

• 한국유체기계학회 논문집
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• 제17권5호
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• pp.5-10
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• 2014

In this paper, the experimental study was carried to investigate the effect of angle of the anti-vortex holes on the film cooling effectiveness on a flat plate. The pressure sensitive paint technique was applied to measure the film cooling effectiveness. Two anti-vortex hole angles of $0^{\circ}$ and $15^{\circ}$ with respect to the primary hole were considered, and the simple cylindrical hole case was also tested. The blowing ratio based on the cylindrical hole was 0.5 and the same flow rate was kept for all anti-vortex hole cases. Results showed that the film cooling effectiveness for the anti-vortex hole cases were much higher than that of the cylindrical case. Among the anti-vortex hole cases, $15^{\circ}$ angle anti-vortex hole case showed higher film cooling effectiveness than that by the $0^{\circ}$ angle anti-vortex hole case.

• 한국기계가공학회지
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• 제16권2호
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• pp.16-21
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• 2017

An experimental study has been carried out to improve the performance of a commercial abrasive blasting nozzle, by simply redesigning the nozzle's inner contour. The analytical 1-D code, that can evaluate both the frictional effects on the nozzle inner wall and the sphericity effects of the particle, is utilized to calculate the dynamics of the particle inside the nozzle. The analytical results are compared to the experimental ones, that were obtained from images of the particle streaklines downstream from the nozzle exit. It is noted that the particle velocity at the redesigned nozzle exit increases as compared to the original commercial nozzle.

• International Journal of Aeronautical and Space Sciences
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• 제18권1호
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• pp.56-62
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• 2017

Because adhesively bonded joints are used in many structural systems, it is important to predict accurate adhesive strengths. Composite aircraft with many joints are easily exposed to low temperatures and high relative humidity. This paper presents a humidity aging effect on the adhesive strength of a composite single-lap joint (SLJ). The adhesive strength of the SLJ is predicted using a finite element analysis with a cohesive zone model (CZM) technique. The humidity aging effect is evaluated based on the adhesive strength and CZM parameters. A lap joint test is carried out on the composite SLJ specimens, which are exposed for four months of 100% R.H. at $25^{\circ}C$. The predicted strengths are in good agreement with experimental data, and the actual crack propagation is satisfactorily simulated using the local CZM technique.

• 항공우주시스템공학회지
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• 제10권3호
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• pp.23-31
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• 2016

The intermediate mixing chamber is one of various methods for improving the regression rate and combustion efficiency of the hybrid rocket. The mixing chamber with its non-combustible material makes the propulsion performance increase, but it leads to a low fuel-loading density in the combustion chamber; therefore, this performance-related trade-off between the mixing chamber and the low fuel-loading density was studied. In this study, the trade-off was conducted by comparing the intermediate-mixing-chamber case with a w/o-mixing-chamber case. The small hybrid-sounding rocket is designed with internal ballistics for comparing the rocket length to the weight. In addition, an external ballistic analysis was conducted for comparing the performances of the w/- and w/o-mixing-chamber cases. As a result, the intermediate-mixing-chamber case shows that the length and the weight were decreased to 12 % and 8 %, respectively; furthermore, when compared with the normal cases, the estimated altitude result of the w/-mixing-chamber case was increased to approximately 75 m.

• 대한원격탐사학회:학술대회논문집
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• 대한원격탐사학회 2004년도 Proceedings of ISRS 2004
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• pp.336-339
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• 2004

Communication, Ocean and Meteorological Satellite (COMS) has been developed by Korean Aerospace Research Institute (KARI) since 2003. Ocean Color Imager (OCI) is the one of COMS payloads, which will monitor the marine environment around Korean peninsula routinely with the intermediate resolution. But considering COMS is to be located in the geostationary orbit, required geographical coverage is not positioned in the nadir direction of COMS but in specific location with horizontal and vertical offsets from the nadir. In this study, coverage by OCI Field Of View (FOV) is analyzed. First of all, OCI is modeled as the sensor which is a $2,500{\times}2,500$ sized 2-D CCD and the pixel resolution is about 500m. And then, OCI is simulated to be controlled to target the required coverage accurately. As a result of it, coverage by OCI FOV is determined. Finally, all coverages by OCI FOV are mapped.

• Journal of Welding and Joining
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• 제27권2호
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• pp.27-31
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• 2009

Ferritic stainless steels have a good heat resistance and economic advantage. They are used for applications such as automotive exhaust systems where resistance to general corrosion is superior to carbon steels. However, there are not enough research for ferritic stainless steels on weldability mainly used as automotive exhaust manifolds. In this study, mechanical and microstructure properties of as-welded STS 429L and STS 444 ferrite stainless steels were confirmed by tensile, bending, hardness test, optical microscopy and scanning electron microscopy. Tensile strength of the STS 444 is higher than the STS 429L when it is a raw material. In contrast to this fact, STS 429L indicated higher tensile strength after butt welded. In addition, the hardness have a increasing tendency as getting down on the bead.

• 한국정보디스플레이학회:학술대회논문집
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• 한국정보디스플레이학회 2005년도 International Meeting on Information Displayvol.II
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• pp.1459-1461
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• 2005

Carbon nanotube -copper composite structures were fabricated using composite plating method and their field emission characteristics were investigated. Multi-walled carbon nanotubes synthesized by chemical vapor deposition were used in the present study. It was revealed that turn-on field of the structures was about 3.0 $V/{\mu}m$ at the current density of 0.1 ${\mu}A/cm^2$. We observed relatively uniform emission characteristics as well as stable emission currents. CNT-Cu composite plating method is efficient and it has no intrinsic limit on the plating area. Moreover, it gives strong adhesion between emitters and an electrode. The refore, we expect that CNT-Cu composite plating method can be applied to fabricate electron field emitters for large area FEDs and large area vacuum lighting sources.

• 항공우주시스템공학회지
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• 제10권1호
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• pp.95-102
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• 2016

There are many possible disturbance sources on such a spacecraft, but reaction wheel assembly (RWA) which is generally used for spacecraft attitude control is anticipated to be the largest. These effects on degradation of performance of spacecraft such as attitude stability. In reaction wheel, disturbance caused by imbalance and speed error. It is hard to emulate speed error disturbance because it is not coincide with wheel frequency. This paper concentrates on emulating and analyzing the speed error disturbance. Firstly, classify the causes that lead to speed error disturbance which generate RPM fluctuation. Secondly, simulated with disturbance driver module and reaction wheel assembly which are developed by Spacecraft Control Lab. Experimental investigations have been carried out to test the disturbance emulator module as a disturbance generator for RWA. Measurements and test have been conducted on various fault. Frequency analysis of test data show that speed error disturbance effects on wheel settling wheel speed or fluctuation type.