NASA Scientific and Technical Aerospace Reports

still in progress. One of the issue is their interaction with the surrounding plasma environment. This paper presents a study
performed at the European Space Agency (ESA) for modelling the interaction between a Field Emitter Electric Propulsion
(FEEP) system and a surrounding ionospheric plasma. A detailed 3D PIC model of the FEEP system and of its environment
has been performed, using the PicUp3D code, developed in the framework of the SPINE network (http://www.spis.org). The
model takes into account a detailed geometrical model of the inner volume of the thruster, including all electrodes and the
aperture geometry, and the surrounding ambient plasma in a large computational space. This study helps to validate acceptable
design in order to reduce back-streaming electron currents from ionospheric type environment and to assess the FEEP engine
plume neutralisation process.
Author
Electric Propulsion; Space Plasmas; Spacecraft Propulsion
20040111385 NASA Glenn Research Center, Cleveland, OH, USA
Advanced Technology Development for Stirling Convertors
Thieme, Lanny G.; Schreiber, Jeffrey G.; [2004]; 15 pp.; In English; Space Technology and Applications International Forum,
8-12 Feb. 2004, Albuquerque, NM, USA
Contract(s)/Grant(s): 22-972-30-01; No Copyright; Avail: CASI; A03, Hardcopy
A high-efficiency Stirling Radioisotope generator (SRG) for use on potential NASA space missions is being developed
by the Department of Energy, Lockheed Martin, Stirling Technology Company, and NASA Glenn Research Center. GRC is
also developing advanced technology for Stirling converters, aimed at substantially improving the specific power and
efficiency of the converter.The status and results to date will be discussed in this paper.
Derived from text
Power Effıciency; Stirling Cycle; Thermoelectric Power Generation; Spacecraft Power Supplies
20040111429 NASA Glenn Research Center, Cleveland, OH, USA
Overview 2003 of NASA Multi-D Stirling Convertor Development and DOE and NASA Stirling Regenerator R and D
Efforts
Twe, Roy; Ibrahim, Mounir; Simon, Terrence; Mantell, Susan; Gedeon, David; Qiu, Songgang; Wood, Gary; [2004]; 21 pp.;
In English; Space Technology and Applications International FOrum (STAIF 2004), 8-12 Feb. 2004, Albuquerque, NM, USA
Contract(s)/Grant(s): NAS3-03124; NAG3-2482; WBS 755-60-16; WBS 972-30-02; Copyright; Avail: CASI; A03, Hardcopy
This paper will report on (1) continuation through the 3rd year of a NASA grant for multi-dimensional Stirling CFD code
development and validation, (2) continuation through the 3rd and final year of a Department of Energy, Golden Field Office
(DOE) regenerator research effort. Results of the NASA multi-D code development effort and the DOE regenerator research
efforts will be summarized. Early results and planning for the new regenerator microfabrication contract will also be discussed.
Author (revised)
Computational Fluid Dynamics; Regenerators; Stirling Cycle; Stirling Engines
20040111431 NASA Glenn Research Center, Cleveland, OH, USA
Experimental Investigation from the Operation of a2kWBrayton Power Conversion Unit and a Xenon Ion Thruster
Hervol, David; Mason, Lee; Birchenough, Art; Pinero, Luis; [2004]; 34 pp.; In English; Space Technology and Applications
International Forum, 8-11 Feb. 2004, Albuquerque, NM, USA
Contract(s)/Grant(s): NAS3-00145; WBS 22-973-80-10; No Copyright; Avail: CASI; A03, Hardcopy
A 2kW Brayton Power Conversion Unit (PCU) and a xenon ion thruster were integrated with a Power Management and
Distribution (PMAD) system as part of a Nuclear Electric Propulsion (NEP) Testbed at NASA’s Glenn Research Center.
Brayton Converters and ion thrusters are potential candidates for use on future high power NEP mission such as the proposed
Jupiter Icy Moons Orbiter (JIMO). The use of a existing lower power test hardware provided a cost effective means to
investigate the critical electrical interface between the power conversion system and the propulsion system. The testing
successfully demonstrated compatible electrical operations between the converter and the thruster, including end-to-end
electric power throughput, high efficiency AC to DC conversion, and thruster recycle fault protection. The details of this
demonstration are reported herein.
Author
Brayton Cycle; Ion Engines; Nuclear Electric Propulsion; Spacecraft Propulsion; Nuclear Rocket Engines
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