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경량압전 복합재료 작동기의 작동범위를 이용한 총유효 모멘트 (M<sup>E</sup>)의 예측
윤광준,김철웅,Yoon Kwang-Joon,Kim Cheol-Woong 대한기계학회 2006 大韓機械學會論文集A Vol.30 No.2
The fatigue behavior of LIPCA was so sensitive to the manufacturing condition, the environmental factors and the change of the test apparatus. Therefore, we could be considering not only the relationship between the stroke range $({\Delta}h)$ and actuating frequency but also the relationship between the stroke range $({\Delta}h)$ and the total effective moment $(M^E)$. Thus, this study proposed the calculation method of the applying $M^E$ when the $({\Delta}h)$ of LIPCA was increased from 1.mm to 20mm. To estimate the relationship between the total effective moment $(M^E)$ and the Bernoulli-Euler bending moment (M) was reviewed. And the residual stress distribution of LIPCA and THUNDER using the CLT was evaluated. In conclusions, converting the $({\Delta}h)$ of LIPCA to the radius of curvature (p) and calculating the $(M^E)$, it was found that the p by the $M^E$ changed similarly as the $({\Delta}h)$. It was found that the $M^E$ was 2.2 times as the M. While CFRP and PZT of LIPCA, which had the superior compressive characteristic, had the compressive residual stress, GFRP was subject to the tensile residual stress. Since this reversed configuration between the compressive residuals stress and the tensile one was made, the requirement of the stroke range $({\Delta}h)$ increase was satisfied.
Micro Flying Robot with Flapping Wings
윤광준(Kwang-Joon Yoon),박준혁(Joon-Hyuk Park) 대한기계학회 2008 대한기계학회 춘추학술대회 Vol.2008 No.5
Two kinds of ornithopter were developed to diversify the ability of vehicle in way of receiving data and landing gear system. And we also tried to reach the minimum size of ornithopter with RC control capability. Wing span of 36㎝ ortnithopter with capability of take off and landing within 3m distance was developed successfully. Moreover, we applied vision sensor in order to receive vision data during flight. At first, it seemed to be little difficult to filming for flapping air vehicle due to its vibration occurred by flapping motion. But we eventually found the suitable position which could send a vision data with less vibration. This vision sensing with landing gear system ornithopter can perform under 5m/s of head wind and has l5min of flight duration. On the other hand, l5㎝ ornithopter was also developed successfully with I min of flight duration. This vehicle was developed on purpose of breaking the limitation of smallest flapping air vehicle.
윤광준(Joon Hyuk Park),박준혁,윤광준(Kwang Joon Yoon) 대한기계학회 2008 대한기계학회 춘추학술대회 Vol.2008 No.11
This research describes about designing and manufacturing X-wing type flapping micro aerial vehicle which intends to improve the performance of one-pair wing flapping vehicle with innovated design. This design, X-wing as we call, was introduced for some time ago from many laboratories but still there hasn’t any reports dealing on its theoretical or numerical analysis. By manufacturing the X-wing with our own design and succeeding its flight test will give us the general idea on X-wing which may guide us to conduct the numerical and experimental analysis later on. We focused to design the X-wing and introduce some conceptual theories about its characteristics on this report.
절연막을 이용한 자기정렬 이중 리세스 공정에 의한 전력 MESFET 소자의 제작
이종람,윤광준,맹성재,이해권,김도진,강진영,이용탁,Lee, Jong-Ram,Yoon, Kwang-Joon,Maeng, Sung-Jae,Lee, Hae-Gwon,Kim, Do-Jin,Kang, Jin-Yeong,Lee, Yong-Tak 한국전자통신연구원 1991 전자통신 Vol.13 No.4
본 연구에서는 기상 성장법 (VPE : vapor phase epitaxy) 으로 성장된 $n^+(Si:2X10^18cm^-3)$/$n(Si:1x10^17cm^-3)$구조의 시편 위에 SiN 과 감광막 등 식각 선택비가 서로 다른 두 물질로 보호된 소스와 드레인 사이의 게이트 형성 영역을 건식식각과 습식식각방법으로 리세스 에칭을 하여 형성한 후, 게이트를 자기정렬하여 형성시킬 수 있는 이중 리세스공정 기술을 개발하였고, 이를 통하여 전력용 MESFET 소자를 제작하였다.게이트 형성부분의 wide recess 폭은 건식식각으로 SiN을 측면식각(lateral etch) 함으로써 조절하였는데, 이 방법을 사용하여 MESFET 소자의 임계전압을 조절할 수 있고, 동시에 소스-드레인 항복전압을 30V 까지 향상시킬 수 있었다. 소스-드레인 항복전압은 wide recess 폭이 증가함에 따라, 그리고 게이트 길이가 길어짐에 따라 증가하는 경향을 보여주었다. 이 방법으로 제작한 여러종류의 MESFET 중에서 게이트 길이가 $2\mum$이고 소스-게이트 간격이 $3 \mum$인 MESFET의 전기적 특성은 최대 트랜스컨덕턴스가 120 mS/mm, 게이트 전압이 0.8V 일 때 포화드레인전류가 170~190mA/mm로 나타났다. 제작된 MESFET이 ($NH_4$)$_2$$S_x$ 용액에 담금처리될때 , 공기중에 노출된 게이트-드레인 사이의 n-GaAs층의 표면이 유황으로 보호되어 공기노출에 의한 표면 재산화막의 형성이 억제되었기 때문으로 사료된다.
CFRP 배향각에 따라 변화하는 PZTCA의 작동변위(Δ h)와 곡률반경(ρ)의 관계식 제안
홍정화,윤광준,김철웅,Hong Jung-Hwa,Yoon Kwang-Joon,Kim Cheol-Woong 대한기계학회 2006 大韓機械學會論文集A Vol.30 No.3
Due to the diversified use of recent Piezoelectric Zirconate Titanate Composite Actuate. (PZTCA), various PZTCAs with the different ply orientation of the fiber layer have been applied. For this reason, the applicable bending moment equation is necessary even though the fiber layer ply orientation and the laminate configuration are changed. The aim of this research is to evaluate the relationship between the total effective moment $(M^E)$ and Bernoulli-Euler bending moment (M) when the ply orientations of UD CFRP are changed. In conclusions, firstly, as the performance test results by the CFRP ply orientation, the performance of [0] and [90] were stable. However, while the performance of [+45] was suddenly decreased after 5 hours. Secondly, the change of $(M^E)$ by the CFRP ply orientation was evaluated. As the CFRP ply orientation was increased from [0] to [+60], the $(M^E)$ were gradually decreased. However, they became a little bit increased from [+60] to [90]. Finally, after the change of M by the CFRP ply orientation was evaluated, it was found that $M^E=2.2M$ was valid for just [0] and that there was a relationship between $M^E$ and M according to the ply orientation.