About this Research Topic
High Power Electric Propulsion is necessary for transfer systems between Earth and Moon, deep-space robotic missions, as well as for the Human Exploration Program.
In the last two decades, EP systems increased the power level by one order of magnitude from kilowatts to tens of kilowatts, as currently designed for the Gateway in lunar orbit. However, it will require a further step by at least one order of magnitude to meet even more challenging missions like an interplanetary mission.
Besides the development and understanding of EP thrusters, the development of other critical components of the system such as power distribution is critical to the success of the mission.
The goal is to have a complete picture of what it will take to implement High Power EP on Spacecraft that we could already build within the next decade.
- Understand which EP technology is better suited to different high power levels.
- Understand criticalities of spacecraft integration of high power EP systems, in particular thermal configuration and other life-limiting factors.
- Identify propellants of interest for high power EP systems, and how to improve system efficiency when using those which are widely available and low cost, as well as the required flow distribution system.
- Understand options and technologies required for power distribution of EP system in the hundreds of kilowatts, and when a direct-drive configuration may be of benefit.
Any manuscript based on analysis or test data is welcome. Additionally, any review paper that compares technologies and leverages already peer-reviewed published work is welcome.
- Papers should be focused on Hall Effect Thruster, Ion Engines, Magneto-Plasma-Dynamics Thrusters, and any other variation of plasma thrusters that could be defined at TRL 3 or higher.
- Papers may focus on power processing units, direct-drive architectures, or others; as well as thruster ignition logic and electrical configuration of the thrusters. This may include also solutions for harnessing, thermal management, and Propellant flow distribution.
Finally, manuscripts focused on the following topics are of special interest: Analysis of mission scenarios based on the adoption of high-power EP; System architectures, and spacecraft integration for high-power EP.
Giovanni Lenguito earned his PhD in Mechanical Engineering from Yale University. He is currently a Principal Engineer at Maxar, where he is leading the development, qualification, and testing effort of new propulsion hardware, with a special focus on electric propulsion products from sub-kW to 10's of kW of power, including power distribution and propellant flow management.
Giovanni Lenguito works for Maxar, a prime contractor that builds spacecraft. Tommaso Andreussi works for Sitael, a manufacturing company of propulsion hardware. Cosmo Casaregola works for Eutelsat, a Telecommunications company that operates GeoStationary Satellites. All other Topic Editors declare no competing interests with regards to the Research Topic subject.
In the last two decades, EP systems increased the power level by one order of magnitude from kilowatts to tens of kilowatts, as currently designed for the Gateway in lunar orbit. However, it will require a further step by at least one order of magnitude to meet even more challenging missions like an interplanetary mission.
Besides the development and understanding of EP thrusters, the development of other critical components of the system such as power distribution is critical to the success of the mission.
The goal is to have a complete picture of what it will take to implement High Power EP on Spacecraft that we could already build within the next decade.
- Understand which EP technology is better suited to different high power levels.
- Understand criticalities of spacecraft integration of high power EP systems, in particular thermal configuration and other life-limiting factors.
- Identify propellants of interest for high power EP systems, and how to improve system efficiency when using those which are widely available and low cost, as well as the required flow distribution system.
- Understand options and technologies required for power distribution of EP system in the hundreds of kilowatts, and when a direct-drive configuration may be of benefit.
Any manuscript based on analysis or test data is welcome. Additionally, any review paper that compares technologies and leverages already peer-reviewed published work is welcome.
- Papers should be focused on Hall Effect Thruster, Ion Engines, Magneto-Plasma-Dynamics Thrusters, and any other variation of plasma thrusters that could be defined at TRL 3 or higher.
- Papers may focus on power processing units, direct-drive architectures, or others; as well as thruster ignition logic and electrical configuration of the thrusters. This may include also solutions for harnessing, thermal management, and Propellant flow distribution.
Finally, manuscripts focused on the following topics are of special interest: Analysis of mission scenarios based on the adoption of high-power EP; System architectures, and spacecraft integration for high-power EP.
Giovanni Lenguito earned his PhD in Mechanical Engineering from Yale University. He is currently a Principal Engineer at Maxar, where he is leading the development, qualification, and testing effort of new propulsion hardware, with a special focus on electric propulsion products from sub-kW to 10's of kW of power, including power distribution and propellant flow management.
Giovanni Lenguito works for Maxar, a prime contractor that builds spacecraft. Tommaso Andreussi works for Sitael, a manufacturing company of propulsion hardware. Cosmo Casaregola works for Eutelsat, a Telecommunications company that operates GeoStationary Satellites. All other Topic Editors declare no competing interests with regards to the Research Topic subject.
Keywords: Hall Effect Thruster, Ion Engine, plasma physics, Power Processing Unit, Direct-Drive, Tug, Interplanetary
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