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Summary of commercial 1.2 kV-10 A SiC Schottky diodes. In grey, 150 V-20 A space-qualified Si Schottky diode for comparison.
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This article proposes a photovoltaic power processor for high-voltage and high-power distribution bus, between 300 V and 900 V, to be used in future space platforms like large space stations or lunar bases. Solar arrays with voltages higher than 100 V are not available for space application, being necessary to apply power conversion techniques. The...
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... DCX operates under soft-switching conditions, so the capacitive charge of the diode will not significantly impact the losses but will affect the switching frequency. Table 3 summarizes a selection of commercially available SiC Schottky diodes rated for 1.2 kV-10 A and, for comparison purposes, a space- Aerospace 2024, 11, 690 5 of 14 qualified 150 V-20 A Si Schottky diode. Due to the lack of commercial devices and to ensure proper functioning in the worst-case scenario, the STPSC10H12 diode has been selected. ...Citations
... The responsibility of carrying out space missions was mainly under the jurisdiction of powerful space agencies such as NASA, ESA, CNSA, JAXA, ROSCOSMOS, and ISRO. These space research organizations, being governmental institutions, carried out societal functions such as being carriers of knowledge and education and promoting advanced technology [3]. With the passage of time, many universities and SMEs (Small/Medium Enterprises) emerged and entered this market with the objective of organizing space missions at a fraction of the cost, accepting the failure risk in space exploration due to cheaper production and shorter development periods [4]. ...
Electric power supply (EPS) is the heart of any aerospace mission and plays an important role in improving the performance and service lifetime of spacecraft. It generates, converts, stores, and distributes power to different voltage levels. The EPS is composed of solar panels, a power conditioning unit (PCU), batteries, and a power distribution unit (PDU). This paper describes the design and analysis of an efficient power conditioning system for a CubeSat standard small satellite. For this purpose, the aim of this paper is to propose a two-input maximum power point tracker (MPPT)-based interleaved boost converter. The design copes with the fact that when a satellite revolves around the Earth, a single panel or at most two panels face solar radiation at different angles. In order to extract maximum power from the panels, the designed converter drives the solar panels at the maximum power point (MPP). A small signal model is drawn for the converter, and the closed-loop gain of the converter is analyzed using a Bode diagram. To improve the phase margin and gain, a PID compensator is designed and added to the closed loop of the converter. Finally, the performance of the proposed converter is validated by the simulation results.
