- High Power Electric Propulsion
High Power Electric Propulsion (HiPEP) is a variation of
ion thruster. It was ground-tested in 2003by NASAand intended for use on the Jupiter Icy Moons Orbiter, which was canceled in 2005.
The HiPEP thruster differs from earlier ion thrusters because the
xenonions are produced using a combination of microwaveand magneticfields. The ionization is achieved through a process called Electron Cyclotron Resonance(ECR). In ECR, the small number of free electrons present in the neutral gas gyrate around the static magnetic field lines. The injected microwaves' frequency is set to match this gyrofrequency and a resonance is established. Energy is transferred from the right-hand polarized portion of the microwaveto the electrons. This energy is then transferred to the bulk gas/plasma via the rare - yet important - collisions between electrons and neutrals. During these collisions, electrons can be knocked free from the neutrals, forming ion-electron pairs. The process is a highly efficient means of creating a plasma in low density gases. Previously the electrons required were provided by a hollow cathode.
The thruster itself is in the 20-50 kW class, with a
specific impulseof 6,000-9,000 seconds, and a propellant throughput capability exceeding 100 kg/kW. The goal of the project, as of June 2003, was to achieve a Technology readiness levelof 4-5 within 2 years.
On page 8 of the September 2004 HiPEP report NASA/TM—2004-213194 says the pre-prototype HiPEP produced 670 mN of thrust at a power level of 39.3 kW using 7.0 mg/s of fuel giving a specific impulse of 9620. Downrated to 24.4 kW, the HiPEP used 5.6 mg/s of fuel giving a specific impulse of 8270 and 460 mN of thrust.
* [http://www.grc.nasa.gov/WWW/ion/present/hipep.htm NASA GRC Media Packet on HiPEP] .
* [http://gltrs.grc.nasa.gov/reports/2004/TM-2004-213194.pdf The High Power Electric Propulsion (HiPEP) Ion Thruster NASA/TM—2004-213194 AIAA–2004–3812] .
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