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모멘텀 휠의 내부 진공 유지를 위한 커넥터 밀봉방법 개발
전동익,공성철,오화석,이승우,Cheon, Dong-Ik,Gong, Sung-Chul,Oh, Hwa-Suk,Lee, Seung-Wu 항공우주시스템공학회 2008 항공우주시스템공학회지 Vol.2 No.4
In general, we utilize momentum wheel to control spacecraft. It needs vacuum test to analyze the effect of space environments. The conventional vacuum connector which is composed of steel has problems for test with built in momentum wheel because of weight, thermal expansion, etc. We suggest possibility to manufacture the vacuum connector using aluminum mount, epoxy and industrial D-Sub considering cost, weight. We verify the performance through vacuum test.
전동익,오화석,이상철,변상균,박종승,강민영,이승우,Cheon, Dong-Ik,Oh, Hwa-Suk,Lee, Sangchul,Byun, Sang-Kyun,Park, Jong-Seung,Kang, Min-Young,Rhee, Seung-Woo 항공우주시스템공학회 2007 항공우주시스템공학회지 Vol.1 No.4
Labyrinth seal is most common way to protect the bearings installed in Reaction wheel. In spite of wide applications, no such research was found about the sealing utility of the Labyrinth seal in the condition of vacuum and high temperature. In this research, we tried to verify the utility of Labyrinth seal. Numerical analysis had been executed to predict the benefit of the Labyrinth seal and also experiments were performed to verify the utilization. Two Bearings were installed at the vacuum chamber, one was assembled with Labyrinth seal and the other was stand alone. After executing the vacuum test, it was found to be the stand alone bearing had lost more weight than the one that was assembled with the labyrinth seal. In this result, it is verified that the Labyrinth seal has useful function to preserve the lubricant that affects to the life-cycle of the Bearing.
김동훈,전동익,오화석,이상철,방효충,이승우,Kim, Dong-Hoon,Cheon, Dong-Ik,Oh, Hwa-Suk,Lee, Sangchul,Bang, Hyochoong,Rhee, Seung-Wu 항공우주시스템공학회 2007 항공우주시스템공학회지 Vol.1 No.3
When the reaction wheel rotates, the disturbance occurs mainly due to the mass imbalance. It is necessary to predict the effect of disturbance on the attitude stability of the satellite. The disturbance forces and torques are identified and the attitude jitter of the satellite is analyzed depending on the configuration of the wheels. On the analysis the equation of the satellite motion is combined with the translational and rotational dynamics of the wheels. The accuracy of analysis is verified by simulation of STSAT-3 satellite.
이상욱,김동훈,전동익,오화석,김응현,김규선,Lee, Sang-Wook,Kim, Dong-Hoon,Cheon, Dong-Ik,Oh, Hwa-Suk,Kim, Eung-Hyun,Kim, Gyu-Sun 항공우주시스템공학회 2008 항공우주시스템공학회지 Vol.2 No.1
The line of sight(LOS) is affected by the vibration of spacecraft. It is necessary to predict the effect of disturbance on LOS stability. Reaction wheel assembly is anticipated to be the largest disturbance source on spacecraft. The disturbance which is occurred mainly due to the mass imbalance is analyzed with harmonic numbers. The accuracy and stability are verified by probability density function with dynamic equation of the satellite motion.
SCL EM 반작용 휠의 시간응답 최적화를 위한 비례 이득 추정
김준호,이상욱,전동익,오화석,Kim, Joon-Ho,Lee, Sang-Wook,Cheon, Dong-Ik,Oh, Hwa-Suk 항공우주시스템공학회 2009 항공우주시스템공학회지 Vol.3 No.4
The driver's speed control to the satellite's mission is required. Therefore, optimal control over the value of benefits is required. Driver to control the characteristics of the driver and the driver was analyzed. Experimental results based on the estimated parameters using the equations of motion and was passed to save the function. Using optimization techniques applied to estimate the proportional term gain was the result of the analysis.
전위차계를 이용한 무인항공기 조종면 변위 측정 장치 구현 및 적용
김지철,최일규,공성철,전동익,이상철,오화석,강민영,Kim, Ji-Chul,Choi, Il-Gyu,Gong, Sung-Chul,Cheon, Dong-Ik,Lee, Sangchul,Oh, Hwa-Suk,Kang, Min-young 항공우주시스템공학회 2009 항공우주시스템공학회지 Vol.3 No.3
Aircraft flight control surfaces which are one of the most important elements of safety allow a pilot to adjust and control the aircraft's flight attitude. This paper is described of the control surface deflection angle measuring device. Data analysis through ground test and flight test can provide reliability of this device using the present system. It is also shown that measuring system is capable of detecting failure of control surfaces.
심상현,김지철,양성욱,전동익,이상철,오화석,강민영,금동교,Shim, Sanghyun,Kim, Ji-Chul,Yang, Sungwook,Cheon, Dong-Ik,Lee, Sangchul,Oh, Hwa-Suk,Kang, Min-Young,Keum, Dong-Kyo 항공우주시스템공학회 2009 항공우주시스템공학회지 Vol.3 No.1
Quad-rotor is one kind of a rotorcraft in Unmanned Aerial Vehicle (UAV), which consists of four rotors in total and fixed-pitch blades located at the four corners. This vehicle is emerging as popular platform for UAV research due to the simplicity of its construction, the ability of hovering and the vertical take-off and landing (VTOL) capability, etc. Because of those specific capabilities, this vehicle can be applied to many fields: search and rescue, mobile sensor networks, fire observation, etc. However a quad-rotor is much affected by the disturbance due to the characteristics of structure. So this vehicle needs attitude control for stabilizing. In this paper, we design the control law for automatic stabilization. The PID controller is used to control a brushless DC motor. And an accelerometer is used to measure the roll and pitch angles of a quad-rotor.