Performance and endurance testing of ti 1.35 k W thruster with anode layer (TAL) developed at the Central Research Institute of Machine Building (TsNTIMASH) is described. The TAL evaluated herein Is designated the D-$5 and is characterized by an external acceieration zone to maximize engine life. Performance measurements indicate that the D-SS performance is comparable to that of the SPT-100 for operathn at 1.35 kW. A 636 hour accelerated wear test was performed to assess the thruster service life capability. For this test the TsNnNASH cathode was replaced by a cathode fabricated at JPL to eliminate concerns over cathode durability since the primary objective was to evaluate the discharge chamber erosion characteristics. Post test examhatian indicated that the volume of material removed over the course of $ $ y e v test wfrs approxhiately an order of magnitude less than for the SPT-100 over the same operating duration. Most of the engine erosion takes place on guard rings which protect the magnetic circuit pole pieces from erosion. Changing this ring material from stainless steel to a more sputter-resistant material, such as graphite, will further reduce the erosion rate and yield engine life times estimated to be greater than 5,000 hours.
In the Very High Isp Thruster with Anode Layer (VHITAL) Program the performance, plume and lifetime capability of the radiatively-cooled two stage, bismuth-fueled VHITAL-160 will be characterized in the U.S. and Russia. The demonstration and further characterization of this technology is motivated by its excellent performance, unique propellant attributes and potentially significant mass and trip time savings over chemical and ion thruster systems for NEP missions. This Russian-developed electric propulsion technology $rill be improved from its previously tested state over 1-5 ycrrs ago with an advanced feed system, novel erosion and plume diagnostics and models of the thruster performance, lifetime and plume interactions with the spacecraft. The VHITAL-160 design documentation has been completed with thermal and structural analysis showing the capability of this thruster to operate in a self-heated mode at 25 and 36 kW. The previously existing TAL-160 was refurbished at TsNllMASH and recently demonstrated operation in a discharge mode and the functionality of the thruster support systems. An all-carbon AIAA 2005-4564This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States.resistively heated prototype vaporizer with porous plug was successfully demonstrated for the flight-like feed system. Hydrodynamic models of the first and second stages of the discharge have been developed with good agreement with experimental results. Significant progress has been made in the development and demonstrations of the thruster diagnostics. I walls. This attribute of the propellant significantly relaxes the pumping speed requirements placed on facilities used for testing bismuth fueled thrusters, which is a significant factor when testing at increasingly high power levels for high power electric thruster performance and lifetime assessments. Two stage TALs operating on Bi propellant could be tested at power levels exceeding 100 kW in existing facilities. Multiple thrusters could be tested in existing facilities at total power levels exceeding 1 MW. Additional attributes of the bismuth propellant include its low ionization potential and high mass, enabling high efficiency thruster operation. It is also environmentally friendly and non-toxic.The VHITAL Program P-I is Dr. Mark Cappelli of Stanford University. He is also leading the thruster lifetime assessment element. He is responsible for implementing the near-field plume diagnostics and leading the near-field plume characterization and the assessment of the thruster lifetime. Anita Sengupta, a Co-1. is the VHITAL Program Manager at JPL. Dr. Colleen Marrese-Reading is a Co-1 as the technical lead of the thruster support system technology development and the thruster performance assessment at JPL. Drs. Sergey Tverdokhlebov and Sasha Sememkin, at TsNIIMASH, are responsible for the thruster, cathode and a feed system. Dr. lain Boyd, at the University of Michigan, is also a Co-1 who will lead the spacecraft contamination-ass...
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