• The Bulletin of The Korean Astronomical Society
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• v.37 no.2
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• pp.230.1-230.1
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• 2012

본 논문에서는 대구경 광학탑재체의 조립, 정렬 및 시험에 사용되는 고정밀, 고안정 짐발장치의 개발에 대해서 소개하고자 한다. 광학탑재체의 광학시험을 위해 사용되는 짐발장치는 광축높이를 유지하기 위해서 높이조절이 가능해야하고, 조립과정과 광학시험과정 그리고 시험 후 광학탑재체를 짐발 장치로부터 분리하기 위해 수평상태와 수직상태로의 회전이 가능해야 한다. 광학측정 시험과정 중에 결상위치의 미세한 조절을 위해 광학탑재체를 수평상태에서 상하좌우 정밀한 회전이 가능해야한다. 우주궤도환경 하에서 성능측정을 위해 열진공체임버 안에서의 광학시험이 필요하므로 짐발장치를 구성하는 재질은 모두 진공사용이 적합한 것이어야 한다. 광학측정 중에 측정설비주변에서부터 인가된 외란은 광학시험과 같은 민감한 시험에서는 철저하게 제거되어야 하는데, 이와 관련하여 짐발장치의 광학측정시험형상에서의 고유진동수와 같은 동적 특성도 설계과정에 반영하여 안정적인 측정 장치가 되도록 고려되어야 한다.

• The Bulletin of The Korean Astronomical Society
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• v.37 no.2
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• pp.186.1-186.1
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• 2012

저궤도관측위성에 사용되는 광학 카메라는 대기 상태에서는 물론이고 우주 환경을 모사하는 열진공챔버 내에서도 광학 시험을 수행한다. 광학시험 수행 시, 광학카메라의 변위 및 각도를 조정하기 위하여 짐발을 사용한다. 짐발에 기능을 수행하기 위하여 적용된 기어 및 모터 등의 구조로 인하여 외부 진동에 취약할 수 있으며, 이러한 경우에는 광학시험 수행에 많은 제약을 줄 수 있다. 따라서 광학챔버 짐발의 변위 및 각도 변경 뿐만 아니라 안정적인 자세를 유지하기 위하여 기준 이상의 고유진동수 등의 동특성을 가져야 한다. 본 논문에서는 짐발 및 대상 광학 카메라의 질량특성을 모사한 대상물을 설치한 상태에서 수행한 동특성 시험 결과 및 수행한 분석 결과를 정리하였다.

• The Journal of The Korea Institute of Intelligent Transport Systems
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• v.15 no.1
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• pp.102-108
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• 2016

A flying drone generates vibrations in a great variety of frequencies, and it requires a gimbal system stabilization loop design in order to obtain clean and accurate image from the camera attached to the drone under this environment. The gimbal system for drone comprises the structure that supports the camera module and the stabilization loop which follows the precise angle while blocking the vibration from outside. This study developed a dynamic model for one axis for the stabilization loop design of a gimbal system for drones and applied classical PID controller and intelligent PID controller. The Stabilization loop design was developed by using MATLAB/Simulink and compared the performance of each controller through simulation. Especially, the intelligent PID controller can be designed almost without the dynamic model and it demonstrates that the angle can be followed without readjusting the parameters of the controller even when the characteristics of the model changes.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.35 no.4
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• pp.409-415
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• 2011

A gimbal system in observation reconnaissance aircraft was fabricated by assembling many parts and bearings. This system consists of a camera module and a stabilization gimbal that supports the camera module. During the flight for recording images, the gimbal system experiences various accelerations with wide frequencies. Although base excitation of stabilization gimbal results in vibration of the camera module, the camera module must be able to capture the correct and clear image even while vibrating. Hence, it is important to know the natural frequencies and vibration modes of the gimbal system with the camera module. Considering bearings as spring elements, the vibration characteristic of the gimbal system was analyzed by finite element method. In addition, harmonic response analysis was performed to determine the correct transmissibility of acceleration for the camera module in the frequency range of 0-500 Hz.

• Bulletin of the Korean Space Science Society
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• 2007.10a
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• pp.111.1-111.1
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• 2007

• Journal of the Korean Society of Manufacturing Process Engineers
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• v.9 no.2
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• pp.20-25
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• 2010

A camera module is supported by a gimbal structure in collection equipment of image information. During flight, the gimbal system undergoes serious accelerations with wide frequencies. To get the correct images, the camera module must be stably vibrated under these conditions. If natural frequency unfortunately exists in a exciting frequency range, resonance occurs there. Hence, harmonic responses analysis is needed to know correct vibration characteristic of the gimbal system. Finite element analysis was performed to get an acceleration of the gimbal system by mode superposition after extracting mode shapes and natural frequencies. Considering damping ratio of 2%, the reponses of gimbal structure were calculated from excitations with a design frequency band. As results, a maximum acceleration transmissibility, which is the ratio of response to excitation, was obtained and it can be used to design the gimbal structure effectively.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2012.04a
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• pp.420-424
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• 2012

A 2-axis gimbal system is one of main disturbance sources affecting on image jitter response of a satellite. The gimbal system can be rotated on its azimuth and elevation axes, resulting in variation of its moment of inertia and structural modes, so that generates non-linear vibration characteristics. In order to estimate the jitter response, it is an indispensable process to characterize micro-vibration disturbance of the 2-axis gimbal system. In the present research, the vibration characteristics of the 2-axis gimbal system was investigated with respect to the types of stepping motors. The micro-vibration tests were performed for 2-phase and 5-phase stepping motors. The test results show that the disturbance can be reduced with vibration attenuation ratio of 60% by replacing the 2-phase stepping motor with the 5-phase one.

• Aerospace Engineering and Technology
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• v.6 no.2
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• pp.236-244
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• 2007

The 40% scaled vehicle of Smart UAV has been developed for the investigation of basic flight characteristics and the verification of flight control algorithm. The similar gimbal hub and drive train with the full scale UAV were implemented and a forced air cooling reciprocating engine was installed. The various kind of tests were conducted for the major components of the vehicle. The important performance and mechanical endurance of the fabricated vehicle were identified by ground and hovering test.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.31 no.5
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• pp.625-634
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• 2007

KARI SUAV program was initiated to develop a Smart Unmanned Aerial Vehicle with innovative smart technologies. SUAV is a tilt rotor aircraft of which rotor system is 3-bladed, gimbaled hub type. Several existing concepts of gimbaled hub were analyzed and compared to investigate the applicability to SUAV rotor system design. From the result of these investigations, it was concluded that a new design concept of low cost and high reliability characteristics was necessary for the rotor hub development of SUAV. The design requirements of new gimbal hub concept and the design results were presented. Also, the analysis results to verify the satisfaction of design requirements of SUAV rotor system were presented.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.40 no.4
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• pp.415-422
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• 2016

When shock acceleration is applied to a mechanical system, it may cause malfunctioning and damage to the system. Hence, to prevent these problems when developing a gimbal structure system for observation reconnaissance, the MIL-STD-810G shock standard must be satisfied as a design specification. Rubber vibration isolators are generally assembled on the base of the system in order to reduce the shock transferred from the aircraft. It is difficult to analyze the transient behavior of the system accurately, because rubber has a nonlinear load-deformation curve. To treat the nonlinear characteristic of the rubber, bilinear approximation was introduced. Using this assumption, transient responses of the system under base shock acceleration were calculated by the finite element method. In addition, experiments with a true prototype were performed using the same conditions as the analytical model. Compared with experimental data, the proposed numerical method is useful for the transient analysis of gimbal structure systems, including rubber vibration isolators with nonlinear stiffness and damping.