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pathfinder_01
Guest
I was reading a bit about electric propulsion systems. I.e. (ion, plasma, ect….) I was wondering what would be the advantages/disadvantages of having a spacecraft with a low thrust but fuel-efficient electric system and a high thrust chemical one. From what I have read it seems that with some systems., esp. the ion one the spacecraft would have to begin decelerating halfway to the destination if you wish to go into orbit. <br /><br />Could a spacecraft use an electric system to break out of earth orbit and cruise to a destination then switch to a chemical one to brake into orbit? <br /><br />Would compromising fuel efficiency lead to a quicker travel time or would the extra mass of the chemical system cause a longer time by having to lug so much mass? <br />