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황국하 원광대학교 인문학연구소 2010 열린정신 인문학연구 Vol.11 No.1
Soon-eon, the commentary of Lao-tzu written by Yulgok, gave a significant influence on changing the heretical view of Neo-Confucianism in Josun Dynasty. Contemporary philosophers agree with the influence on this change of the heretical view about Lao-tzu. However, they point out that this way is based on the presumption that Yulgok interpreted Taoism from the point of view of Confucianism. They say that Neo-Confucianists who published the commentaries of Taoism judged Taoism from the perspective of Neo-Confucianism.In this article, by analyzing Tao-Zeuk-CheonTao intensively taken as a remarkable phrase in Yulgok’s reading Lao-tzu, I’m going to prove Yulgok’s Soon-eon is written to express a gap between Confucianism and Taoism that couldn’t be clearly expressed by analyzing it fairly and philosophically, not from the point of view of Yi-Yu-Hae-Tao. That is to say, I’d like to express that Yulgok comprehended Lao-tzu accurately enough and he tried to deliver that at a fair position.
이동규,황국하,김병규 대한기계학회 2017 JOURNAL OF MECHANICAL SCIENCE AND TECHNOLOGY Vol.31 No.6
Conventional rectangular path generating mechanisms can not avoid structural complexity due to the large number of components andhigh degree of freedom. Therefore, the authors present a simplified rectangular path generating mechanism using an ellipse. The mechanismnot only consists of much fewer components than conventional mechanisms, but also has one degree of freedom. In the designprocedure, a reverse kinematic design is implemented, and a theoretical analysis of the displacement, velocity and acceleration is conductedto validate the superiority of this mechanism. In particular, this paper highlights the low acceleration values at the contact pointsbetween the ellipse and the frame. This is noteworthy since acceleration is directly correlated with impulsive forces that induce earlymalfunctions, low stability and wear in devices using such mechanisms. In addition, this paper discusses achieving optimal eccentricity tohave the lowest acceleration at the corners. Lastly, a dynamics analysis for two cases – a mechanism with a perfect circle and a mechanismwith an ellipse – is carried out using dynamic analysis software to investigate real reaction force at the corners. Conclusively, thenovelty of the mechanism using an ellipse is validated through the kinematics and dynamics analyses.
스프링 클램프와 형상기억합금 와이어를 이용한 비폭발식 분리장치
최준우,이동규,황국하,이민형,김병규,Choi, Junwoo,Lee, Dongkyu,Hwang, Kukha,Lee, Minhyung,Kim, Byungkyu 항공우주시스템공학회 2015 항공우주시스템공학회지 Vol.9 No.2
In this paper, we report a non-explosive separation device for a small satellite which utilize a shape memory alloy actuator and spring clamp. In order to increase the preload, the proposed device employs spring clamp that can generate high toque when the shape memory alloy actuator makes the cylinder key unlatch a holding ball effectively. Owing to simple design of separation device configuration, we could obtain good repeatability(up to 30 times activation). Conclusively, we could develop a non-explosive separation device which can reliably activate within 1.2 sec under high preload(up to 300kgf).
A Mechanism for a Deployable Optical Structure of a Small Satellite
최준우,이동규,황국하,김병규 한국정밀공학회 2015 International Journal of Precision Engineering and Vol. No.
In this paper, we present a deployment mechanism that is applicable to a deployable optical structure where the focus is on satellite miniaturization. It is designed with a passive deployment mechanism that utilizes a spring hinge. In order to confirm the feasibility of the designed deployable mechanism, we theoretically analyze the alignment errors (de-space, tilt, and de-center) that influence the optical performance of the structure. The theoretical results are as follows: a de-space of 180.0 μm, a tilt of 1941.3 μrad, and a decenter of 45.3 μm. In addition, we measure alignment errors to evaluate the actual alignment errors for a manufactured deployable mechanism. The experimental results are as follows: a de-space of 180.2 μm, a tilt of 218.8 μrad, and a de-center of 617.5 μm. Finally, we investigate the factors causing the differences between the theoretical and experimental values, and we suggest a method for improving the alignment errors.
최준우(Junwoo Choi),이동규(Dongkyu Lee),황국하(Kukha Hwang),이민형(Minhyung Lee),김병규(Byungkyu Kim) 한국항공우주학회 2015 韓國航空宇宙學會誌 Vol.43 No.7
본 논문에서는 형상기억합금 구동기를 이용한 소형위성용 비폭발식 분리장치를 소개한다. 앞선 연구결과를 바탕으로 분리장치의 부품의 교체를 통하여 제안된 분리장치의 신뢰성을 향상시킴으로써 고사전하중(preload) 하에서도 구동이 가능하도록 하였다. 또한 충격실험을 통하여 비폭발식분리장치의 장점인 저충격 발생을 확인하였고, 발사환경 및 우주환경실험을 통하여 안정적으로 작동하는 것을 검증하였다. 결론적으로 본 연구에서는 충격실험, 진동실험 및 열진공실험 후 고사전하중에서 저충격을 발생시키며 안정적으로 작동 가능한 비폭발식 분리장치를 개발하였다. In this paper, we report a non-explosive separation device for a small satellite which utilize a shape memory alloy actuator. Based on previous research, we try to increase the reliability of the proposed device by changing some components. It enables the proposed device to activate under high preload. Also, we confirm it generates low shock which is main advantage of non-explosive separation device. Finally, vibration test which mimics launching environment and thermal vacuum test which mimics space environment are carried out respectively. After each environment test, we confirm the proposed device is successfully activated. Conclusively, we develop a non-explosive separation device which can activate with low shock under high preload after shock and environment tests(vibration and thermal vacuum tests).