Space electric propulsion

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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.

Schematic Diagram of electric propulsion system
Roadmap Overview


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
DSM for electric propulsion system


Roadmap Model using OPM

DSM for electric propulsion system

Figures of Merit