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메니스커스 드래깅 증착법을 이용한 산화아연 나노선의 수평 정렬 연구
강동헌,신동명,김형국,황윤회 한국물리학회 2017 새물리 Vol.67 No.1
We fabricated laterally-aligned ZnO nanowires by using the meniscus dragging deposition (MDD) technique under various deposition conditions. The ZnO nanowire alignment exhibits a linear response with increasing number of deposition cycles, indicating that the deposited ZnO nanowires were tightly fixed on the substrate and showing that the degree of alignment was constant at $\sim$65%. Also, we could regulate the density and the degree of alignment by controlling the deposition angle, temperature and speed. The MDD technique for fabricating laterally-aligned ZnO nanowires can be useful for synthesizing functional materials in numerous electronic and optoelectronic devices, including field-effect transistors, nanogenerators and ultraviolet sensors. 본 연구에서는 메니스커스 드래깅 증착법 (meniscus dragging deposition, MDD)을 이용해 다양한 분위기에서 산화아연 나노선을 수평 방향으로 정렬하였다. 산화아연 나노선의 수평 정렬정도는 증착 횟수에 선형적으로 비례하였다. 기판 위에 한번 증착된 나노선은 새로운 드래깅 증착에 큰 영향을 받지 않으며, 새로운 나노선 증착 시에는 항상 일정한 비율 ($\sim$65%)로 정렬된 특성을 보여주었다. 또한, 증착 각도, 증착 온도 및 증착 속도 등을 조절하여 산화아연 나노선의 정렬 정도 및 정렬 밀도를 조절할 수 있었다. 본 연구에서 산화아연 나노선의 수평 정렬을 위해 사용한 메니스커스 드래깅 증착법은 전계효과 트랜지스터, 나노발전기 및 자외선 센서 등의 다양한 대면적 전자기기와 광전자기기의 제작에 쉽게 활용될 수 있을 것으로 기대한다.
연속발사 충격에 강인한 SDINS 신속 초기정렬기법 설계
이형섭(Hyung-Sub Lee),한경준(Kyung-Jun Han),이상우(Sang-Woo Lee),유명종(Myeong-Jong Yu) 대한전기학회 2016 전기학회논문지 Vol.65 No.6
In this paper, a SDINS(Strapdown Inertial Navigation System) rapid initial alignment technique robust to the pyro-shock in multi-launch rocket system is proposed. The proposed method consists of three steps. Firth, transfer alignment is performed to estimate misalignment between MINS(Master INS) and SINS(Slave INS), and the estimated misalignment is written in the memory when transfer alignment is completed. Next, the pre-filtering process is performed to get rid of the acceleration error induced by launcher vibration. Finally, the horizontal alignment is performed to compensate misalignment variation caused by pyro-shock. We verified the performance of the proposed alignment method comparing with the conventional transfer alignment method. The simulation shows that the proposed initial alignment technique improves alignment performance.
박홍철(Hong-Chul Park),손영선(Young-Seon Son),최종연(Jong-Yeon Choi),윤용식(Yong-Sik Yoon) 한국항공우주학회 2004 韓國航空宇宙學會誌 Vol.32 No.7
위성체 얼라인먼트 측정은 측정 정밀도가 ±0.5° 이하로 매우 정밀한 것이다. 일반적으로 이러한 측정은 3 대 이상의 데오드라이트를 사용하여 측정되고 있다. 그러나 위성체의 위치 안정성 등에 의해 측정 정밀도 오차가 발생될 수 있다. 이에 따라, 데오드라이트, 회전 테이블 및 전자식 수평계 등을 조합하여 새로운 얼라인먼트 측정 시스템을 개발하게 되었다. 본 논문에서 이러한 측정 시스템의 개념과 측정 방법을 기술 하였고, 기존의 측정 방법보다 더 좋은 정밀도를 얻을 수 있음을 알 수 있다. A spacecraft alignment measurement requires highly precise measurement accuracy which is less than ±0.5° In general, such an alignment measurement has been performed by using three or more theodolites. However, it contains the latent accuracy error because of a position stability of spacecraft, etc. The new alignment measurement system which consists of a theodoilte, a rotating table and a digital inclinometer has been developed to possibly reduce the error. This paper describes the concept and methodology of measurement system It was found that new measurement system can provide more accurate results than the conventional system.
전투기 형상의 외부 장착물과 꼬리 날개 공력 간섭에 대한 수치적 연구
김민재(M.J. Kim),권오준(O.J. Kwon),김지홍(J.H. Kim) 한국전산유체공학회 2007 한국전산유체공학회 학술대회논문집 Vol.2007 No.-
A three-dimensional inviscid flow solver has been developed based on unstructured meshes for the simulation of steady and unsteady flowfields around a generic fighter aircraft and for the investigation of the aerodynamic interference between the external stores and the tail surfaces. The flow solver is based on a vertex-centered finite-volume method and an implicit point Gauss-Seidel relaxation scheme. To validate the flow solver, calculations were made for a steady flow and the computed results were compared with experimental data. An unsteady time-accurate computation of the generic fighter aircraft with external stores at transonic flight conditions showed that the external stores cause undesirable vibration on the horizontal tail surface due to the mutual interference between their wake and the horizontal tail surface. It was shown that downward deflection of the trailing edge flap significantly reduces the undesirable interference effect.
데오도라이트를 이용한 위성체 얼라인먼트 측정에 관한 연구
윤용식,이동주 한국공작기계학회 2003 한국생산제조학회지 Vol.12 No.6
A measurement of spacecraft alignment is an important process of spacecraft assembly, integration and test because it is necessary that a ground station controls the precise positions of on-orbit spacecraft by using the alignment data of attitude orbit control sensors(AOCS) on spacecraft. In addition, accuracy of spacecraft alignment requirement is about 0.1°- 0.7°. The spacecraft alignment is measured by autocollimation of theodolite. This paper describes the measurement principle and method of spacecraft alignment. The result shows that all of the AOCS on the spacecraft are aligned within the tolerance quired through the alignment measurement.