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Proceedings ArticleDOI

Activities on electric propulsion in japan - space flight from basic research -

TLDR
The microwave discharge ion engine system on MUSES-C and the DC arcjet on DRTS are now under preparation for space flight in this year and the Kaufman type ion engine on ETS-VIII will be launched soon.
Abstract
The microwave discharge ion engine system on MUSES-C and the DC arcjet on DRTS are now under preparation for space flight in this year. The Kaufman type ion engine on ETS-VIII will be launched soon. Besides these well-developed system some joint ventures with universities and companies invest energetic R & D efforts to the large ion engines, the Hall thruster with high performance, the space applicable PPT and the low power DC arcjet. The academic activities are still brisk in the field of electric propulsion and related topics in Japan. 1. INTRODACTION Many universities and institutes in Japan have investigated the physics of electric propulsion and the related phenomena since 1970’s because they are very attractive topics. Based on the academic research some kinds of electric propulsion system and the integration technology were developed. Some flight demonstrations supplied a lot of information and experiences to Japanese industry and academic community. Passing through the R & D era the electric propulsion is applied to the main system in the bus technology. The MUSES-C and DRTS spacecraft will be launched accompanying with electric propulsion in this year. The flight of ETSVIII is close at hand. In order to support wide variety of space application including huge system and micro probes a lot of engineering effort is invested energetically by joint ventures with universities and companies. The academic research is still active in the field of electric propulsion. This paper will report the recent activities related on the electric propulsion of Japan in the following three sections.

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Citations
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Proceedings ArticleDOI

Monte Carlo simulation for electron Near Wall Conductivity in Hall Thrusters

TL;DR: In this paper, a Monte Carlo model on near wall conductivity (NWC) in the channel of a Hall thruster was proposed and the relationship between electrical field, magnetic field and electron current density due to NWC was calculated.

Development History and Current Status of DC-Type Ion Engines at JAXA

TL;DR: In this article, the development history and current status of DC-type ion engines at JAXA were described, and the first north-south station keeping using ion engines in Japan was conducted in March, 2007.

Effects of Channel Wall Material on Performance and Plasma Characteristics of Hall Thrusters

TL;DR: In this paper, the effects of channel wall material on Hall thruster performance and on plasma characteristics were investigated in a laboratory-model THT-III with three channel wall materials of BN, BNSiN and BNAlN.
References
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TL;DR: In this article, a laser-driven in-tube accelerator for accelerating a projectile using laser power is described, which is characterized by accelerating the projectile in a tube and by supplying the laser beam from the direction opposite to the projectile motion.
Journal ArticleDOI

Overdense Plasma Production in a Low-power Microwave Discharge Electron Source

TL;DR: In this paper, a low-power microwave discharge electron source was developed for neutralization of the 150 mA-class ion beam exhausted from an ion thruster, which consists of a small discharge chamber of 18 mm diameter, into which an L-shape antenna is directly inserted into the magnetic circuit comprised of permanent magnets and iron yokes.
Journal ArticleDOI

Laser-propelled ram accelerator

TL;DR: In this article, the concept of laser-propelled ram accelerator (L-RAMAC) was proposed, which is capable of achieving a higher launch speed than that by a chemical ram accelerator because a higher specific energy can be input to the propellant gas.

Performance Improvement of Pulsed Plasma Thruster for Micro Satellite

TL;DR: In this article, the authors proposed a propulsion system for the small, micro and nano-satellite attitude control, station keeping, de-orbit and drag compensation because of following reasons: Simplicity No tankage, seals nor mechanical valves.