Helicon Double Layer Thruster
The Helicon Double Layer Thruster is a prototype spacecraft propulsion engine. It was created by Australian scientist Dr. Christine Charles, based on a technology invented by Professor Rod Boswell, both of the Australian National University.
The design has been verified by the ESA, which is participating in its development.
Theory of operation 
A Helicon Double Layer Thruster (HDLT) is a type of plasma thruster, which ejects high velocity ionized gas to provide thrust to a spacecraft. In this thruster design, gas is injected into a tubular chamber (the source tube) with one open end. Radio frequency AC power (at 13.56 MHz in the prototype design) is coupled into a specially shaped antenna wrapped around the chamber. The electromagnetic wave emitted by the antenna causes the gas to break down and form a plasma. The antenna then excites a helicon wave in the plasma, which further heats the plasma. The device has a roughly constant magnetic field in the source tube (supplied by Solenoids in the prototype), but the magnetic field diverges and rapidly decreases in magnitude away from the source region, and might be thought of as a kind of magnetic nozzle. In operation, there is a sharp boundary between the high density plasma inside the source region, and the low density plasma in the exhaust, which is associated with a sharp change in electrical potential. The plasma properties change rapidly across this boundary, which is known as a current-free electric double layer. The electrical potential is much higher inside the source region than in the exhaust, and this serves both to confine most of the electrons, and to accelerate the ions away from the source region. Enough electrons escape the source region to ensure that the plasma in the exhaust is neutral overall. Like most ion propulsion devices, the HDLT is a low thrust, high specific impulse (Isp) thruster. A prototype 15 cm diameter thruster, operated in low-magnetic field mode, underwent initial thrust testing in 2010, however, a more complete testing method would be necessary to properly calculate the total thrust .
The Helicon Double Layer Thruster has two main advantages over most other ion thruster designs; first, it creates an accelerating electric field without inserting unreliable components like high voltage grids into the plasma (the only plasma facing component is the robust plasma vessel). Secondly, a neutralizer isn't needed, since there are equal numbers of electrons and (singly charged) positive ions emitted.
The primary application for this thruster design is intended for satellite station keeping, long term LEO to GEO orbit transfers and deep space applications. While a typical design could provide a 50 year life span, or a saving of 1000 lb (≈454 kg) of launch weight for large satellites, this type of thruster could also significantly reduce the length of interplanetary space trips. For example, a trip to Mars could be shortened to 3 months instead of the 8 to 9 months with conventional chemical rockets.  In the near term, the next target for HDLT application is to maintain station-keeping for a satellite to be launched around 2013 in collaboration with EADS-Astrium .
See also 
- Helicon Double Layer Thruster Development - Website at ANU
- ESA: ESA Accelerates Towards A New Space Thruster
- Dr. Boswell and Charles' patent
- Plasma thruster tested for Mars mission