Difference between revisions of "Space electric propulsion"
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Electric thrusters typically use much less propellant than chemical rockets because they operate at a higher specific impulse than chemical rockets. Due to limited electric power the thrust is much weaker compared to chemical rockets, but electric propulsion can provide thrust for a longer time. | Electric thrusters typically use much less propellant than chemical rockets because they operate at a higher specific impulse than chemical rockets. Due to limited electric power the thrust is much weaker compared to chemical rockets, but electric propulsion can provide thrust for a longer time. | ||
[[File:electric_propulsion.png|Schematic Diagram of electric propulsion system]] | [[File:electric_propulsion.png|thumb||left|Schematic Diagram of electric propulsion system]] | ||
[[File:roadmap_overview.png|thumb|Roadmap Overview]] | [[File:roadmap_overview.png|thumb|Roadmap Overview]] | ||
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==Design Structure Matrix (DSM) Allocation== | ==Design Structure Matrix (DSM) Allocation== | ||
Below we can see the DSM Allocation for the electric propulsion system. Sub components have been classified by tier and colour for ease of understanding (for instance, electrons and electric field are related to anode and cathode and thus highlighted in green). Cells shaded in yellow indicate that the corresponding components interact with each other during the operation of the propulsion system. | |||
[[File:DSM_SEP.jpg|thumb||centre|DSM for electric propulsion system]] | |||
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==Roadmap Model using OPM== | ==Roadmap Model using OPM== | ||
==Figures of Merit== | ==Figures of Merit== | ||
Revision as of 14:40, 12 October 2023
Electric Propulsion in Space
Roadmap Overview
Spacecraft electric propulsion uses electrostatic or electromagnetic fields to accelerate mass to high speed and thus generate thrust to modify the velocity of a spacecraft in orbit. This method leverages the charge/mass ratio of propellants, with relatively small potential differences potentially generating high exhaust velocities. This reduces the amount of reaction mass or propellant required, but increases the amount of specific power required compared to chemical rockets.
Electric thrusters typically use much less propellant than chemical rockets because they operate at a higher specific impulse than chemical rockets. Due to limited electric power the thrust is much weaker compared to chemical rockets, but electric propulsion can provide thrust for a longer time.
Design Structure Matrix (DSM) Allocation
Below we can see the DSM Allocation for the electric propulsion system. Sub components have been classified by tier and colour for ease of understanding (for instance, electrons and electric field are related to anode and cathode and thus highlighted in green). Cells shaded in yellow indicate that the corresponding components interact with each other during the operation of the propulsion system.
