Mu Space Engineering Spacecraft-C (MUSES-C) was launched into the transfer orbit in May 9, 2003. Microwave discharge ion engines are used as its primary propulsion system. The Data Relay Test Satellite (DRTS) with 1.8kW/250mN-class hydrazine DC arcjet thruster systems was launched on September 10, 2002, and now on service on the geostationary orbit. Ion engine systems onboard Engineering Test Satellite VIII (ETS-VIII) will be also launched in 2004 by the H-IIA rocket. Basic re searches of many kinds of electric thrusters are also being carried out in lots of academic places.

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Thermal analysis and thrust performance of a low power arcjet thruster

An overview of electric propulsion activities in japan

Purpose




This paper aims to provide an overview of current and historical arcjet development. The reviewed arcjets are considered with respect to both design and thruster relevant parameters. Correspondingly, the paper enables the identification of adequate design criteria and of the probable thruster parameters.




Design/methodology/approach




The approach consists of a database for thruster relevant parameters in conjunction with relevant operational requirements (such as type of propellant) and specific design criteria (such as e.g. propellant injection systems).




Findings




The synopsis of both operational parameter and respectively assigned design allows for the derivation of development approaches for arcjets under given high level requirements such as power regime.




Research limitations/implications




The paper is a general review. However, its strength is in the synthesis of the arcjet classification, the functional evidence of design criteria and the application scenario.




Practical implications




Not only basic but also specific design criteria are analyzed and evaluated leading to a recommendation feature of the paper with respect to the overall design of adequate arcjets.




Social implications




Within the scope of the Clean Space initiative, new applications and scenarios from the operation of arcjets arise enabling EOL phases of spacecraft that fulfill respective levels of debris mitigation and, in addition, the requirements concerning the adequately adapted re-entry of spacecrafts that are at end of life.




Originality/value




The paper is a general review. However, its strength is in the synthesis of the arcjet classification, the functional evidence of design criteria and the application scenario.

Overview of thermal arcjet thruster development

∗ Presented as Paper IEPC-01-000 at the 27 International Electric Propulsion Conference, Pasadena, CA, 15-19 October, 2001. † Copyright  2001 by the Electric Rocket Propulsion Society. All rights reserved. ‡ Professor, Senior Member AIAA This paper describes the current status of electric propulsion technology development and related studies in Japan. Ion engine systems (IES) onboard the Engineering Test Satellite VI (ETS-VI) and the Communications and Broadcasting Engineering Test Satellite (COMETS), and a quasisteady MPD thruster onboard the Space Flyer Unit (SFU) were successfully demonstrated. The National Space Development Agency of Japan (NASDA) is to launch an improved IES onboard the Engineering Test Satellite VIII (ETS-VIII) in 2003. 1.8 kW/ 250 mN-class hydrazine DC arcjet thrusters are to be used on the Data Relay Test Satellite (DRTS). The Institute of Space and Astronautical Science (ISAS) is developing the sample and return space mission from an asteroid, the MUSES-C, which is scheduled to be launched in 2002 and to bring back some specimens to the Earth in 2007 from an extraterrestrial object. In the MUSES-C mission, a cathode-less microwave discharge ion engine system is ready as a primary propulsion in the interplanetary space. Electric propulsion studies at universities, research institutes and industries are also aiming at applications as well as fundamental physics.

An Overview of Electric and Advanced Propulsion Activities in Japan

Application of multiple electrostatic probes to a low power arcjet

A thermal arcjet thruster system of very low power of less than 300 W is developed for the needs of small satellite systems with low power budgets. This thruster shall expand the arcjet thruster range of the Institute of Space Systems (IRS) ranging currently from 1 kW to 100 kW thruster systems 1 . The new thruster is derived from a 1 kW laboratory model and is developed in close reference to former very low power arcjets developed by NASA Lewis Research Center (LeRC) 2,3 and Institute of Space and Astronautical Science (ISAS) 4 in the 1990s. The thruster’s performance with ammonia, hydrogen and argon and possible missions are presented within this paper.

Thermal analysis and thrust performance of a low power arcjet thruster

Citations

An overview of electric propulsion activities in japan

Overview of thermal arcjet thruster development

An Overview of Electric and Advanced Propulsion Activities in Japan

Application of multiple electrostatic probes to a low power arcjet

A Very Low Power Arcjet (VELARC) for Small Satellite Missions

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