• 대한공간정보학회지
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• 제24권4호
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• pp.105-113
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• 2016

산불방사열에너지(fire radiative power)는 산불로부터 방출되는 에너지로서 산불의 연소과정에서 발생하는 온실가스를 추정하기 위한 기초자료로 이용된다. 유럽, 아프리카, 아메리카 지역의 정지궤도 위성센서들은 준실시간의 산불방사열에너지를 산출 및 제공하고 있지만 아시아권에는 아직까지 정지궤도 위성기반의 공식적인 산불방사열에너지 산출물이 제공되지 않고 있다. 본 연구에서는 중적외 복사휘도법(mid-infrared radiance method)을 이용하여 히마와리(Himawari-8) 위성 기반의 산불방사열에너지를 최초로 산출하였으며, 산출정확도를 검증하기 위해 인도네시아 수마트라 지역에 대해 Aqua/Terra 위성의 MODIS(moderate resolution imaging spectroradiometer) 산불방사열에너지 산출물과의 비교검증을 실시하였다. 이 과정에서 NDVI(normalized difference vegetation index)와 FVC(fraction of vegetation coverage)를 이용하여 중적외 복사휘도법의 중요인자인 지표면 방출률을 지면피복 종류에 따라 계산하였으며, 최적화 실험을 통하여 히마와리 AHI(advanced Himawari imager)의 센서계수 a = 3.11을 도출하였다. 본 연구를 통해 산출된 히마와리 산불방사열에너지는 MODIS를 기준으로 약 20%의 평균절대백분비오차를 나타내었으며 이는 미국과 유럽연합의 정지궤도위성의 산불방사열에너지 검증결과와 유사한 수준의 정확도로 평가된다. 히마와리 산불방사열에너지의 산출정확도는 산불의 크기와 위성관측각에 따라 일부 차이를 보였으나 태양천정각과 토지피복에 따른 영향은 거의 없는 것을 알 수 있었다. 이 연구는 아시아권의 정지궤도위성 산불방사열에너지 산출을 위한 참고자료로서 활용가치가 있으며 산불방출 온실가스 추정에 기초자료로 활용될 수 있을 것으로 기대한다.

• KIEE International Transaction on Electrical Machinery and Energy Conversion Systems
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• 제3B권3호
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• pp.147-154
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• 2003

This paper presents a high-frequency boost type ZVS-PWM chopper-fed DC-DC power converter with a single active auxiliary edge-resonant snubber at the load stage which can be designed for power conditioners such as solar photovoltaic generation, fuel cell generation, battery and super capacitor energy storages. Its principle operation in steady-state is described in addition to a prototype setup. The experimental results of boost type ZVS-PWM chopper proposed here, are evaluated and verified with a practical design model in terms of its switching voltage and current waveforms, the switching v-i trajectory and the temperature performance of IGBT module, the actual power conversion efficiency, and the EMI of radiated and conducted emissions, and then discussed and compared with the hard switching scheme from an experimental point of view. Finally, this paper proposes a practical method to suppress parasitic oscillation due to the active auxiliary resonant switch at ZCS turn-off mode transition with the aid of an additional lossless clamping diode loop, and can be reduced the EMI conducted emission.

• Advances in aircraft and spacecraft science
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• 제9권3호
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• pp.195-215
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• 2022

The increasing interest in CubeSat platforms ant their capability of enlarging the frontier of possible missions impose technology improvements. Miniaturized electrical propulsion (EP) systems enable new mission for multi-unit CubeSats (6U+). While electric propulsion systems have achieved important level of knowledge at equipment level, the investigation of the mutual impact between EP system and CubeSat technology at system level can provide a decisive improvement for both the technologies. The interaction between CubeSat and EP system should be assessed in terms of electromagnetic emissions (both radiated and conducted), thermal gradients, high electrical power management, surface chemical deposition, and quick and reliable data exchanges. This paper shows how a versatile CubeSat Test Platform (CTP), together with standardized procedures and specialized facilities enable the acquisition fundamental and unprecedented information. Measurements can be taken both by specific ground support equipment placed inside the vacuum facility and by dedicated sensors and subsystems installed on the CTP, providing a completely new set of data never obtained before. CTP is constituted of a 6U primary structure hosting the EP system, representative CubeSat avionics and batteries. For the first test campaign, CTP hosts the ambipolar plasma propulsion system, called Regulus and developed by T4I. After the integration and the functional test in laboratory environment, CTP + Regulus performed a Test campaign in relevant environment in the vacuum chamber at CISAS, University of Padua. This paper is focused on the test campaign description and the main results achieved at different power levels for different duration of the firings.