IEC Thrusters for Space Probe Applications and Propulsion

Journal Article · Mon Mar 16 04:00:00 EDT 2009 · AIP Conference Proceedings

DOI:https://doi.org/10.1063/1.3115492· OSTI ID:21293368

Miley, George H; Momota, Hiromu; Linchun, Wu; Reilly, Michael P ^[1]; Teofilo, Vince L ^[2]; Burton, Rodney ^[3]; Dell, Richard; Dell, Dick ^[4]; Hargus, William A ^[5]

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1. Dept. of Nuclear, Plasma and Radiological Engineering, University of Illinois, Urbana, IL (United States)
2. Lockheed Martin Space Systems Co., Advanced Technology Center, Palo Alto, CA (United States)
3. Dept. of Aerospace Engineering, University of Illinois, Urbana, IL (United States)
4. Advanced Aerospace Resource Center (AARC), Raleigh, NC (United States)
5. Air Force Research Laboratory, Edwards AFB, CA 217-333-3772 (United States)

Earlier conceptual design studies (Bussard, 1990; Miley et al., 1998; Burton et al., 2003) have described Inertial Electrostatic Confinement (IEC) fusion propulsion to provide a high-power density fusion propulsion system capable of aggressive deep space missions. However, this requires large multi-GW thrusters and a long term development program. As a first step towards this goal, a progression of near-term IEC thrusters, stating with a 1-10 kWe electrically-driven IEC jet thruster for satellites are considered here. The initial electrically-powered unit uses a novel multi-jet plasma thruster based on spherical IEC technology with electrical input power from a solar panel. In this spherical configuration, Xe ions are generated and accelerated towards the center of double concentric spherical grids. An electrostatic potential well structure is created in the central region, providing ion trapping. Several enlarged grid opening extract intense quasi-neutral plasma jets. A variable specific impulse in the range of 1000-4000 seconds is achieved by adjusting the grid potential. This design provides high maneuverability for satellite and small space probe operations. The multiple jets, combined with gimbaled auxiliary equipment, provide precision changes in thrust direction. The IEC electrical efficiency can match or exceed efficiencies of conventional Hall Current Thrusters (HCTs) while offering advantages such as reduced grid erosion (long life time), reduced propellant leakage losses (reduced fuel storage), and a very high power-to-weight ratio. The unit is ideally suited for probing missions. The primary propulsive jet enables delicate maneuvering close to an object. Then simply opening a second jet offset 180 degrees from the propulsion one provides a 'plasma analytic probe' for interrogation of the object.

• OSTI ID: 21293368
• Journal Information: AIP Conference Proceedings, Journal Name: AIP Conference Proceedings Journal Issue: 1 Vol. 1103; ISSN APCPCS; ISSN 0094-243X
• Country of Publication: United States
• Language: English

Related Subjects

70 PLASMA PHYSICS AND FUSION TECHNOLOGY
CURRENTS
DESIGN
ELECTROSTATICS
EROSION
GIGAWATT POWER RANGE
GRIDS
INERTIAL CONFINEMENT
ION PROPULSION
ION THRUSTERS
PLASMA
PLASMA JETS
PROPULSION SYSTEMS
SPHERICAL CONFIGURATION
XENON IONS