Railgun thruster

A satellite, comprising:

• at least one thrust terminal;
• at least one railthruster connected to each thrust terminal by a mounting bracket, each railthruster comprising:
• first and second spaced apart coaxial electrodes extending along a central axis together defining a bore having a muzzle end and a plasma initiation end, a length of said bore being equal to a distance between said muzzle end and said plasma initiation end and a width of said bore being equal to a spacing between said first and second electrodes at said muzzle end, an aspect ratio of said bore exceeding 3:1;
• a pulse generator for supplying pulsed electrical energy to each railthruster;
• and
• an electrical connection between said second electrode and said mounting bracket, said plasma initiation end being between said electrical connection and said muzzle end.

A railgun thruster device for generating and accelerating a high energy plasma jet, comprising:

• a mounting bracket including means for mounting said railgun thruster device to a utilization apparatus;
• first and second spaced apart coaxial electrodes extending along a central axis and defining a bore having a muzzle end and a plasma initiation end, said bore having a width equal to a spacing between said first and second electrodes at said muzzle end and a length equal to a distance between said muzzle end and said plasma initiation end, an aspect ratio of said bore being at least 3:1;
• said pair of electrodes being coated with a material extending for a distance of from 1 to 10 bore widths along said electrodes from said plasma initiation end, said material being selected from the group consisting of refractory metal, noble metal, precious metal, metal matrix composites and pyrolytic graphite;
• and
• an electrical connection between said second electrode and said mounting bracket, said plasma initiation end being between said electrical connection and said muzzle end.

A satellite thruster system comprising:

• at least one thrust terminal;
• at least one railthruster connected to each thrust terminal by a mounting bracket, each railthruster including:
• first and second spaced apart electrodes extending along a central axis together defining a bore having a muzzle end and a plasma initiation end, a length of said bore being equal to a distance between said muzzle end and said plasma initiation end and a width of said bore being equal to a spacing between said first and second electrodes at said muzzle end, an aspect ratio of said bore exceeding 3:1;
• wherein said first electrode has at least one ignition spoke at said plasma initiation end which extends from said first electrode toward said second electrode and defines an initiation gap;
• and
• wherein said second electrode has at least one ignition spoke at said plasma initiation end which extends from said second electrode toward said first electrode and defines an initiation gap;
• and
• a pulse generator for supplying pulsed electrical energy to each railthruster;
• an electrical connection between said second electrode and said mounting bracket, said plasma initiation end being between said electrical connection and said muzzle end;
• and
• a solid propellant coupled to said ignition spokes.