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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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Context 1
... to keep the simplest transistor-driving approach, a push-pull and center-tapped full-wave rectifier structure is considered; see Figure 1. An explanation of the terms can be found in Table 4. On top of that, derating rules [17], limited availability of space-qualified parts [18], and high voltage isolation requirements [19] make the IIOS converter the most suitable approach. ...Context 2
... connecting the outputs in series, 600 V and 900 V distribution buses are achieved, as shown in Figure 6. Each power cell and SAS is designed and configured with the parameters defined in Table 4. The same prototype board is used for both 600 V and 900 V distribution bus, but only one ...Context 3
... connecting the outputs in series, 600 V and 900 V distribution buses are achieved, as shown in Figure 6. Each power cell and SAS is designed and configured with the parameters defined in Table 4. The same prototype board is used for both 600 V and 900 V distribution bus, but only one can be active at a time. ...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.
