Global models of plasma thrusters: Insights from PIC simulation and fluid theory,” in Proceedings of 35th International Electric Propulsion Conference, Atlanta, GA, October 2017 (2017), Paper No. , Google Scholar CrossrefĬoncepts, capabilities, and limitations of global models: A review: Concepts, capabilities, and limitations of global models,” Plasma Processes Polym. , Google Scholar Crossref, ISIįoundations of modelling of nonequilibrium low-temperature plasmas,” Plasma Sources Sci. Results of multiple parametric scans are presented and discussed in detail, with emphasis on plasma acceleration and EUV light production.Įlectrodeless plasma thrusters for spacecraft: A review,” Plasma Sci. The transport coefficients are deduced from a two-point comparison to experimental data. The equations are integrated numerically using a new unconditionally stable method. The resultant non-linear system of normalized stiff ordinary differential equations describes the evolution of the temperatures and densities of the plasma components under the quasi-neutrality constraint. Specific power/mass flow densities and discharge vessel geometry are factorized into equations.

Plasma acceleration in the ambipolar electric field is treated phenomenologically. Other major plasma processes are also included: ionization by electron impact, wall recombination, anomalous cross field diffusion, and charge-exchange. Experimental extreme-ultraviolet (EUV) spectra are analyzed and photon emission is incorporated via the most important ground-state transitions for neutral and ionic species.

Read more about the VASIMR plasma rocket on this Ad Astra Rocket product page.A semiempirical physical model of a strongly magnetized argon discharge is presented. MIT has also posted YouTube videos of both the normal thruster tests and the tests using soda bottles and cans instead. Read more about the Mini-Helicon Plasma Thruster in this MIT press release. TFOT has also reported on other new or innovative rocket and propulsion tests including a new NASA rocket created using a combination of liquid oxygen and liquid methane, the CECE cryogenic engine designed to reduce thrust for moon landings, a ramjet rocket built by students at the Technion in Haifa, and the Australian H圜AUSE (Hypersonic Collaborative Australia/United States Experiment) scramjet rocket. TFOT has previously reported on the VASIMR plasma rocket, the first stage of which inspired the Mini-Helicon Plasma Thruster. However, significantly more testing is needed before the thruster can be produced commercially, in part to ensure compliance with NASA certification policies. In fact, the group built a thruster from a glass soda bottle and aluminum soda can (acting as the radio antenna) and it worked without a hitch. Such a design is simple and easy to replicate. The exhaust from the system travels at ten times the velocity of that from standard chemical rockets, reducing the amount of propellant needed for specific tasks. The magnets also confine, guide, and accelerate the gas, which produces thrust as it exits the tubes. Gas – in this case nitrogen – is pumped into the tube and turned into plasma by radio waves running through the antenna and the surrounding magnets. It consists of a quartz tube wrapped in a coiled antenna and surrounded by magnets. The resulting thruster is small enough to fit into a large shoe box. The Mini-Helicon is based on the first stage of design of the larger rocket and should provide sufficient power to maintain a satellite’s orbit, push a craft from one orbit to another, or generate other necessary maneuvers in space. VASIMR is a three stage plasma rocket designed for long range propulsion of heavy rockets. The idea for the thruster came from the much more powerful VASIMR plasma rockets designed by Ad Astra Rocket and its founder, former astronaut and MIT alum Franklin Chang Diaz. The Mini-Helicon Plasma Thruster is one of several new thrusters under design at the Space Propulsion Laboratory. Smaller, less expensive, and more energy efficient than traditional chemical rockets, the Mini-Helicon Plasma Thruster could use as little as ten times less fuel as conventional systems to produce the same results.

Researchers at the Massachusetts Institute of Technology Department of Aeronautics and Astronautics Space Propulsion Laboratory are developing new plasma thrusters designed for satellite course corrections.

Mit mini helicon plasma thruster