A modular PMAD system for small spacecraft

Button, Robert M.

doi:10.1063/1.52117

Cited by 9 publications

(5 citation statements)

References 3 publications

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“…In addition, Fig. 10(b) also demonstrates the partial power Pp and the total power Pt under different output currents Io1 and Io2 based on (2). Note that the partial power Pp processed by modules is effectively reduced in comparison with the total power Pt for any load condition.…”

Section: B Ppp-based Power Flow Analysismentioning

confidence: 98%

“…Moreover, because the DC-DC converter in the PPP system only processes a small part of the total power, its current and voltage stresses are correspondingly reduced, contributing to decreased cost and increased power density. Owing to these advantages, PPP two-port structures attract increasing attention, and they are already promoted to applications, such as space power systems [2,3], wind turbines [4,5], electric vehicles [6] and so on [7].…”

Section: ⅰ Introductionmentioning

confidence: 99%

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Partial Power Processing Multiport DC–DC Converter With Radial Module Connections

Liu

Chen

et al. 2022

IEEE Trans. Power Electron.

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The partial power processing (PPP) concept has been extensively employed in many two-port converters to achieve high efficiency and high power density by modifying one of the original converter ports to be connected in series between input and output. This is attractive but is confined to two-port applications, and how to extend it to multiport applications is not clear. Hence, this paper aims to explore a generalized PPP multiport scheme by arranging the connection of the module rather than the converter. For a PPP single-input(output)-N-outputs(inputs) converter, one terminal of all N+1 modules is connected together to construct a radial structure, and another terminal is series/parallel connected with the input/output port. Each module only needs to process partial power caused by the voltage or current difference between input and output. Therefore, the required power rating of components is effectively reduced, contributing to low cost as well as low power loss. In this paper, a PPP single-input dual-output converter with active bridge modules is also taken as an example to be introduced in detail, designed and experimented upon, which validates that high efficiency and high power density can be achieved.

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Section: B Ppp-based Power Flow Analysismentioning

confidence: 98%

Section: ⅰ Introductionmentioning

confidence: 99%

Partial Power Processing Multiport DC–DC Converter With Radial Module Connections

Liu

Chen

et al. 2022

IEEE Trans. Power Electron.

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“…Note that it would be possible to employ HET xenon flow control for primary bus voltage regulation for the 28-V, 50-V and 120-V voltage options. This would allow elimination of the ARUs, saving mass, but the PPU converter magnetics would have grow in mass to handle the resulting input voltage variations (Button, 2003).…”

Section: Impact Of Pmad Voltagementioning

confidence: 99%

Effect of Voltage Level on Power System Design for Solar Electric Propulsion Missions

Kerslake

2004

Journal of Solar Energy Engineering

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This paper presents study results quantifying the benefits of higher voltage, electric power system designs for a typical solar electric propulsion spacecraft Earth orbiting mission. A conceptual power system architecture was defined and design points were generated for several system voltages using state-of-the-art or advanced technologies. A 300-V “direct-drive” architecture was also analyzed to assess the benefits of directly powering the electric thruster from the photovoltaic array without up-conversion. Computational models were exercised to predict the performance and size power system components to meet spacecraft mission requirements. Pertinent space environments were calculated for the mission trajectory and an electron current collection model was developed to estimate photovoltaic array losses due to natural and induced plasma environments. The secondary benefits of power system mass savings for spacecraft propulsion and attitude control systems were also quantified. Results indicate that considerable spacecraft wet mass savings were achieved by the 300-V and 300-V direct-drive architectures.

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“…This has the advantage of decoupling the battery design from the primary power bus voltage and allows the designer to tailor the secondary power bus voltage to the available battery cell capacity (Button, 2003). But without discharge control electronics, the spacecraft payloads will see a variable eclipse time voltage.…”

Section: Impact Of Pmad Voltagementioning

confidence: 99%

“…However, these payloads could employ commercially available power converters already designed to handle the 25% voltage variation during battery discharge. Alternatively, for a modest mass penalty, battery discharge voltage could be regulated with a Series Connected Boost Regulator (Button, 1998).…”

Section: Impact Of Pmad Voltagementioning

confidence: 99%

Effect of Voltage Level on Power System Design for Solar Electric Propulsion Missions

Kerslake

2003

Solar Energy

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This paper presents study results quantifying the benefits of higher voltage, electric power system designs for a typical solar electric propulsion spacecraft Earth orbiting mission. A conceptual power system architecture was defined and design points were generated for system voltages of 28-V, 50-V, 120-V and 300-V using state-of-the-art or advanced technologies. A 300-V “direct-drive” architecture was also analyzed to assess the benefits of directly powering the electric thruster from the photovoltaic array without up-conversion. Fortran and spreadsheet computational models were exercised to predict the performance and size power system components to meet spacecraft mission requirements. Pertinent space environments, such as electron and proton radiation, were calculated along the spiral trajectory. In addition, a simplified electron current collection model was developed to estimate photovoltaic array losses for the orbital plasma environment and that created by the thruster plume. The secondary benefits of power system mass savings for spacecraft propulsion and attitude control systems were also quantified. Results indicate that considerable spacecraft wet mass savings were achieved by the 300-V and 300-V direct-drive architectures.

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A modular PMAD system for small spacecraft

Cited by 9 publications

References 3 publications

Partial Power Processing Multiport DC–DC Converter With Radial Module Connections

Partial Power Processing Multiport DC–DC Converter With Radial Module Connections

Effect of Voltage Level on Power System Design for Solar Electric Propulsion Missions

Effect of Voltage Level on Power System Design for Solar Electric Propulsion Missions

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