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Solid State Ionics: from Michael Faraday to green energy-the European dimension. [PDF]
Sci Technol Adv Mater, 2013 Funke K.
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2017 International Aircraft Cabin Air Conference. [PDF]
J Health Pollut, 2019 europepmc +1 more source
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The synergy of spacecraft electric propulsion and power
Space technology and applications international forum (STAIF - 97), 1997The combination of spacecraft electrical power and on-board propulsion can consume as much as three-fourths of the mass of a spacecraft depending upon the mission. With the current emphasis on reducing costs (including launch vehicle costs) and on reducing the mass of future spacecraft it is apparent that the use of advanced spacecraft electrical power
Gary L. Bennett +4 more
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New Electrical Power Supply System for All-Electric Propulsion Spacecraft
IEEE Transactions on Aerospace and Electronic Systems, 2017This paper proposes a novel electrical power supply system architecture (power conditioning and processing unit, PCPU) for high-power all-electric propulsion spacecraft platform with high-voltage power bus (HVBUS) powering thrusters and regulated power bus (VBUS) powering onboard payloads, respectively.
Ming Fu, Donglai Zhang, Tiecai Li
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Acta Astronautica, 2021
Abstract Outer solar system exploration by a small spacecraft using a solar power sail is investigated. A solar power sail is an extended form of a solar sail that has thin-film solar cells attached over its surface. This concept makes it possible to generate a large amount of power with less weight resources than conventional means.
Yuki Takao +3 more
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Abstract Outer solar system exploration by a small spacecraft using a solar power sail is investigated. A solar power sail is an extended form of a solar sail that has thin-film solar cells attached over its surface. This concept makes it possible to generate a large amount of power with less weight resources than conventional means.
Yuki Takao +3 more
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Configurable High Voltage Power Supply for Full Electric Propulsion Spacecraft
2019 European Space Power Conference (ESPC), 2019The present paper describes several technological topics featured in a new prototype of anode/beam supply for 5 kW Power Processing Unit (PPU), dedicated to be compatible with many thruster types and operating modes thanks to a configurable output stage and wide output voltage range.
Marc Bekemans +3 more
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Evaluation of cryogenic power conditioning subsystems for electric propulsion spacecraft
IECEC 96. Proceedings of the 31st Intersociety Energy Conversion Engineering Conference, 2002The power requirement of vehicles designed to transport cargo supporting a piloted expedition to Mars is in the range of megawatts. Therefore, it is imperative that the megawatt class power processing unit designed for high-power nuclear electric propulsion vehicles using turboalternators and advanced magnetoplasmadynamic (MPD) thrusters should be such
R.S.L. Das, S. Krauthamer, R.H. Frisbee
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Grounding Aspects of Power Processing Units for Electric Propulsion Onboard Spacecrafts
10th International Energy Conversion Engineering Conference, 2012The accommodation of Electric Propulsion and the associated Power Processing Units (PPU) within a Spacecraft must lead to an integrated system providing full function and performance. An important aspect is the grounding of the electric propulsion system.
Matthias Gollor, Benjamin Fallis
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Solar System Research, 2016
The problem of optimizing the interplanetary trajectories of a spacecraft (SC) with a solar electric propulsion system (SEPS) is examined. The problem of investigating the permissible power minimum of the solar electric propulsion power plant required for a successful flight is studied. Permissible ranges of thrust and exhaust velocity are analyzed for
A. V. Ivanyukhin, V. G. Petukhov
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The problem of optimizing the interplanetary trajectories of a spacecraft (SC) with a solar electric propulsion system (SEPS) is examined. The problem of investigating the permissible power minimum of the solar electric propulsion power plant required for a successful flight is studied. Permissible ranges of thrust and exhaust velocity are analyzed for
A. V. Ivanyukhin, V. G. Petukhov
openaire +1 more source