• 전기학회논문지
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• 제57권2호
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• pp.256-260
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• 2008

The Ring Laser Gyro makes use of the Sagnac effect within a resonant ring cavity of A He-Ne laser and has more accuracy than the other Gyros. The Low Earth Orbit satellite for observatory use require the high accuracy Gyro to control and determine the altitude because of the need of payload pointing accuracy. In this paper, The theory of the Path Length Control is explained. The electrical design of Path Length Controller is described. The Design for Path Length Controller is composed of the demodulator, Integrator, Phase shifter, High Voltage Amplifier. We apply the circuit to 28cm square ring laser gyro and get the test results.

• 대한전기학회:학술대회논문집
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• 대한전기학회 2008년도 제39회 하계학술대회
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• pp.1949-1950
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• 2008

Activation battery that are required to deliver short pulses to power, for instance, pyrotechnic devices required during jettison payload separation. Activation battery contains 24 Sony US18650 cells configured as 3 strings in parallel, with each string containing 8 series connected cells. This allows to meet voltage and capacity requirements specified for the mission. In this paper design description and specifications of Activation battery are presented. Qualification test flow and results are also shown to make sure the performance in the predicted space environment. Electrical performance was proven on real equipment load assembly.

• 전기학회논문지
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• 제57권9호
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• pp.1584-1588
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• 2008

The Ring Laser Gyroscope makes use of the Sagnac effect within a resonant ring cavity of a He-Ne laser and has more accuracy than the other gyros. The Low Earth Orbit satellite for observatory use require the high accuracy Gyro to control and determine the altitude because of the need of payload pointing accuracy. In this paper, The theory of the Path Length Control is explained. The electrical design of Path Length Controller is described. The Design for Path Length Controller is composed of the demodulator, integrator, phase shifter, high voltage amplifier. We apply the circuit to 28cm square ring laser gyro and get the test results.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2011년도 추계학술대회 논문집
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• pp.64-71
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• 2011

In this study, steady and unsteady aerodynamic analyses of a huge rocket configuration have been conducted in a transonic flow region. The launch vehicle structural response are coupled with the transonic flow state transitions at the nose of the payload fairing. The developed fluid-structure coupled analysis system is applied for aeroelastic computations combining computational structural dynamics(CSD), finite element method(FEM) and computational fluid dynamics(CFD) in the time domain. It can give very accurate and useful engineering data on the structural dynamic design of advanced flight vehicles. For the nonlinear unsteady aerodynamics in high transonic flow region, Navier-Stokes equations using the structured grid system have been applied to the rocket configurations. Also, it is typically shown that the current computation approach can yield realistic and practical results for rocket design and test engineers.

• 시스템엔지니어링학술지
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• 제1권1호
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• pp.32-38
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• 2005

This paper presents the brief generation process of system requirements for Smart UAV from a development objective. The current Smat UAV requirements deal with the restricted life cycle from development to test and verification exclusive of full life cycle because of the new technology demonstration research program funded by governments. The Smart UAV system consists of flight vehicle, avionics, communication link, payload, ground control station and ground supporting system. In this paper, top-down flown requirements are introduced how to allocate to each sub-system.

• 한국콘크리트학회:학술대회논문집
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• 한국콘크리트학회 2006년도 추계 학술발표회 논문집
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• pp.85-88
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• 2006

This paper deals with shaking table tests on RC piers to evaluate the seismic performance under near fault motion. Small scale models were fabricated and axial force was applied by introducing prestress at the centroid of the column section. Mass effect of the superstructures was simulated by mass frame which was linked with a pier model by steel bars because of the limited payload of shaking table. Friction of the mass frame when it moves was minimized by special details and it was proved before tests. Scale factor of the RC piers was 4.25. Main parameters of the test were details of reinforcements. After verifying the results of shaking table tests, seismic performance was evaluated by increasing the acceleration of the near fault motion.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2000년도 추계학술대회논문집
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• pp.581-586
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• 2000

Explosively activated pyro-technic device is used to release exhausted rocket booster or payloads at prescribed times in the rocket's flight. It creates pyro-shock environment that rocket or payload components must survive. With the shock spectra acquired from flight data, laboratory test should be performed before flight to check whether all of component can sustain the shock environment. The pyro-shock environment simulation was created by the resonance fixture response to a projectile impact. Desired shock spectra is realized by adjusting the natural frequency of resonance plate and the velocity of impact hammer. This paper describes the development process of Pyro-shock testing machine, which is designed and tested by Korean engineers, to verify components of Korean Sounding Rocket(KSR-3) and the other Korean space vehicle. Both analytical and experimental techniques are introduced in this paper.

• 항공우주기술
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• 제7권1호
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• pp.108-114
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• 2008

본 해석의 목적은 통신해양기상위성 통신 탑재체의 진행파관증폭기와 외부 유닛들 사이의 전기접속에 대해 적합성을 검증하는 것이다. 본 연구에서는 전력링크, 명령, 디지털 측정, 아날로그 측정 및 실패상태 또는 조립시험 오류들에 대해 유닛들 사이의 적합성을 확인하였다. 본 접속 적합성 검증에 추가적으로 본 연구는 하니스 레벨에서 적용되는 전기 및 제작에서 권고사항을 제공한다.

• 대한원격탐사학회지
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• 제26권6호
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• pp.645-652
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• 2010

The performance of the payload Electro-Optical System (EOS) in satellite system is affected by various factors, such as optics design, camera electronics design, and the characteristics of the CCD (Charge Coupled Device) used, etc. Of these factors, the camera electronics design is somewhat unique in that its operational parameters can be adjusted even after the satellite launch. In this paper, the effect of video gain on the non-uniformity correction performance is addressed. And a new optimal non-uniformity correction scheme is proposed and analyzed using the data from real camera electronics unit based on a TDI (Time Delayed Integration) type of CCD. The test results show that the performance of the conventional non-uniformity correction scheme is affected significantly when the video gain is added. On the other hand, in our proposed scheme, the performance is not dependent on the video gain. The insensitivity of the non-uniformity performance on the video-gain is mainly due to the fact that the correction is performed after the dark signal is subtracted from system response.

• 한국광학회지
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• 제12권5호
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• pp.382-388
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• 2001

1999년 5월 26일 발사되었던 우리별 3호 인공위성에는 지구관측 전자광학 카메라가 탐재되어 있다. MEIS는 직경 95 mm Mangin 망원경으로 고도 720 km에서 13.8 m의 지상화소로 48km의 폭을 3개의 서로 다른 광 대역에서 관측한다. 본 논문에서는 우리별 3호 카메라의 설계와 제작/조립 및 시험결과를 비교 분석하고, 발사후의 운영에 관련된 문제점을 논하였다.