• International Journal of Control, Automation, and Systems
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• 제4권3호
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• pp.333-343
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• 2006

In this paper, the baseline-length information is directly modeled as a measurement for the Wald test, which speeds up the resolution convergence of the integer ambiguity of GPS carrier phase measurements. The convergent speed improvement is demonstrated using numerical simulation and real experiments. It is also shown that the integer ambiguities can be resolved using only four actual satellite measurements with very reasonable convergence speed, if the baseline-length information is used just like one additional observable satellite measurement. Finally, it is shown that the improvement of convergence speed of the Wald test is due to the increase of the probability ratio with the use of the baseline-length constraint.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2006년도 춘계학술대회논문집
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• pp.242-245
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• 2006

This paper is an assessment on the dynamic test results of optical bench for LEO satellite. According to the design requirements, optical bench was designed and manufactured. Dynamic test was performed to verify stability of optical bench. Low level random vibration test, sine burst test and sine vibration test are carried out to identify dynamic characteristics and to verify static strength and safety under quasi-static load conditions. From the result it can be stated that the optical bench is well qualified under the launch environmental conditions.

• International Journal of Aeronautical and Space Sciences
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• 제4권2호
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• pp.69-78
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• 2003

In this paper, we develop the so-called functional test model for magnetic bearing wheels. The functional test model developed in this paper is a kind of electromagnetic suspension systems and has three degree of freedom, which consists of one axial suspension from gravity and the other two axes gimbaling capability to small angle, and does not include the motor. For the control of the functional test model, we derive the optimal electromagnetic forces based on the least squares method, and use the proportional-integral derivative controller. Then, we develop a hardware setup, which mainly consists of the digital signal processor and the 12-bit analog-to-digital and digital-to-analog converters, and show the experimental results.

• 한국항공우주학회지
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• 제44권2호
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• pp.156-164
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• 2016

우주기반기술 검증용 극초소형 위성 STEP Cube Lab.(Cube Laboratory for Space Technology Experimental Project)의 주요 탑재체인 집광형 프레넬렌즈가 적용된 고효율 집광형 태양전력시스템, 열선 절단방식이 적용된 무충격 구속분리장치 그리고 MEMS 기반의 고체추력기에 대해 인증수준의 열진공 시험과 열평형 시험을 수행하였다. 이를 통해 열진공 환경 하의 인증수준의 시험온도규격에서 탑재체의 구조건전성 및 정상작동성을 검증하고, 열평형 시험 결과로부터 보다 신뢰성 높은 보정된 열해석 모델을 확립하였다. 본 논문에서는 주요 임무 탑재체의 인증수준의 열환경 시험에 대한 기능시험 결과 및 시험 결과로부터 수행된 열모델 보정과 최종 열모델의 궤도 열해석 결과에 대해 기술하였다.

• 한국정밀공학회:학술대회논문집
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• 한국정밀공학회 2011년도 춘계학술대회 논문집
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• pp.1107-1108
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• 2011

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2006년도 춘계학술대회논문집
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• pp.197-202
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• 2006

The low-altitude earth observation satellite is generally equipped with high performance camera as a main payload which is vulnerable to vibration environment. During the launch process of a satellite, the combustion and jet noise of launch vehicle produce severe acoustic environment and the acoustic loads induced may damage the critical equipments of the satellite including the camera. Therefore to predict and simulate the effect of the acoustic environment which the satellite has to sustain at the lift-off event is very important process to support the load-resistive design and test-qualification of components. Statistical Energy Analysis(SEA) has been widely used to estimate the vibro-acoustic responses of the structures and gives statistical but reliable results in the higher frequency region with less modeling efforts and calculation time than the standard FEA. In this study, SEA technique has been applied to a 3-Dimensional model of a low-altitude earth observation satellite to predict the acceleration responses on the structural components induced by the high level acoustic field in the launch vehicle fairing. In addition, the expected response on each critical component panel was calculated by the classical method in consideration of the mass loading and imposed sound pressure level, and then compared with SEA results.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2004년도 ICCAS
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• pp.413-416
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• 2004

The tracking antenna system must be always pointed to a satellite for data link among moving vehicles. Especially, for an antenna mounted on a moving vehicle, it needs the stabilized the antenna system. So, software and hardware, signal processing of motion detection sensors, real-time processing of vehicle dynamics, trajectory estimation of satellite, antenna servo mechanism, and tracking algorithm, are unified in the antenna system. The purpose of this paper is to design the embedded tracking antenna control system for satellite communication. The embedded OS(Operating System) based stabilization and tracking algorithm was implemented. The performance of the designed embedded control system was verified by the real satellite communication test.

• 항공우주시스템공학회지
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• 제15권5호
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• pp.113-128
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• 2021

본 논문에서는 위성시스템의 교육 방안으로 간이 지상수신국을 제시하고 아마추어 무선분야에서 보편적으로 활용되고 있는 위성통신 기술과 관련 소프트웨어를 이용하여 기능면에서 기존의 고정지상국과 유사하게 제작하였다. 또한 운용 중인 위성의 신호를 수신하는 간이 지상수신국 운용시험을 진행하여 위성신호의 수신경험을 통한 지상국시스템의 이해, 위성의 상태 정보 획득을 통한 위성시스템의 이해, 더 나아가 향후 위성시스템 설계 등 위성시스템 교육을 위한 방안으로의 간이 지상수신국 활용 가능성에 대해 확인하였다.

• Journal of Astronomy and Space Sciences
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• 제30권4호
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• pp.279-290
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• 2013

Due to the continuous space development by mankind, the number of space objects including space debris in orbits around the Earth has increased, and accordingly, difficulties of space development and activities are expected in the near future. In this study, among the stages for space debris removal, the implementation of a vision-based approach technique for approaching space debris from a far-range rendezvous state to a proximity state, and the ground test performance results were described. For the vision-based object tracking, the CAM-shift algorithm with high speed and strong performance, and the Kalman filter were combined and utilized. For measuring the distance to a tracking object, a stereo camera was used. For the construction of a low-cost space environment simulation test bed, a sun simulator was used, and in the case of the platform for approaching, a two-dimensional mobile robot was used. The tracking status was examined while changing the position of the sun simulator, and the results indicated that the CAM-shift showed a tracking rate of about 87% and the relative distance could be measured down to 0.9 m. In addition, considerations for future space environment simulation tests were proposed.

• 항공우주기술
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• 제12권2호
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• pp.14-23
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• 2013

위성 운용 중 발생할 수 있는 오류에 대한 대비를 고장 관리 설계라고 한다. 고장 관리 설계는 위성에 이상 현상이 나타나는 경우 감지하고 고립시키며, 지상에서 위성과 접속한 이후 오류 사항을 파악하고 대응책을 마련할 때까지 위성을 안전한 상태로 유지하는 기능을 포함한다. 안전 모드 운용은 정상 운용과는 다르게 비행 소프트웨어를 탑재한 탑재 컴퓨터와 전력 제어 및 분배 장치 주관 하에 지상국의 접속 없이 이루어진다. 오류 발생 시 고장 관리 설계에 따라 자동화된 동작이 이루어지는 만큼 지상 시험 단계에서 고장 관리 로직 및 관련 하드웨어가 설계된 대로 동작하는지를 철저하게 검증해야 한다. 또한 실제와 유사한 오류를 위성에 손상 없이 인가해야 한다. 고장 관리 설계 검증시험은 위성을 구성하는 다양한 부분체에 대해서 수행되나 본 논문에서는 저궤도 위성의 비행 모델을 대상으로 수행된 자세제어계와 전력계 시험의 설계에 대해 서술하고 결과에 대해 정리하였다.