Plausability of a Plasma Jet Electric Thruster

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SUMMARY

The discussion centers on the feasibility of a plasma jet electric thruster, a project initiated by three scientists seeking $70,000 in funding. Current technology, such as pulsed plasma thrusters, operates at 1kW input power with an exhaust velocity of 20 km/s, yielding a maximum thrust of 0.1N, which is further reduced to 0.01N due to a 10% efficiency rate. Comparatively, ion thrusters demonstrate better efficiency metrics. While there is potential for size reduction, significant improvements in efficiency and thrust remain challenging.

PREREQUISITES
  • Understanding of plasma physics and propulsion mechanisms
  • Familiarity with electric thruster technology, specifically pulsed plasma thrusters
  • Knowledge of thrust-to-power ratios in aerospace applications
  • Basic principles of space travel and propulsion efficiency
NEXT STEPS
  • Research advancements in pulsed plasma thruster technology
  • Explore ion thruster efficiency improvements and comparisons
  • Investigate the latest developments in electric propulsion systems for spacecraft
  • Learn about the funding and crowdfunding processes for aerospace projects
USEFUL FOR

Aerospace engineers, propulsion scientists, and investors interested in innovative space travel technologies will benefit from this discussion.

AnTiFreeze3
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I frequent this website occasionally, but most of the projects on it aren't nearly as outreaching as this one appears to be.

http://www.kickstarter.com/projects...ctric-thrusters-for- spacecraft ?ref=category

It's basically a group of 3 scientists trying to raise upwards of $70,000 to fund a plasma jet electric thruster, which they hope will be a far more efficient process for space travel. This is all way over my head, so I was wondering if anyone with the proper credentials could clarify whether or not this is feasible.
 
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1kW input power, 20km/s exhaust velocity correspond to a maximal thrust of 0.1N - with the 10% efficiency number, this is reduced to 0.01N. Ion thrusters have similar values, but this table indicates a better efficiency. Maybe they can decrease the size, but in terms of efficiency they won't get much. More maximal thrust would be interesting, too.
 

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