Relevant bibliographies by topics / Electrodeless propulsion

Academic literature on the topic 'Electrodeless propulsion'

Author: Grafiati
Published: 10 December 2022
Last updated: 28 January 2023

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Journal articles on the topic "Electrodeless propulsion"

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OTSUKA, Shuhei, Kohei Takizawa, Yuriko TANIDA, Daisuke KUWAHARA, and Shunjiro SHINOHARA. "Study on Plasma Acceleration in Completely Electrodeless Electric Propulsion System." Plasma and Fusion Research 10 (2015): 3401026. http://dx.doi.org/10.1585/pfr.10.3401026.

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NAKAMURA, Takahiro, Kenji YOKOI, Hiroyuki NISHIDA, Takeshi MATSUOKA, Ikkoh FUNAKI, Shunjirou SHINOHARA, Takao TANIKAWA, et al. "Study on Helicon Plasma Lissajous Acceleration for Electrodeless Electric Propulsion." TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 10, ists28 (2012): Tb_17—Tb_23. http://dx.doi.org/10.2322/tastj.10.tb_17.

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Sheppard, Anna J., and Justin M. Little. "Scaling laws for electrodeless plasma propulsion with water vapor propellant." Plasma Sources Science and Technology 29, no. 4 (March 26, 2020): 045007. http://dx.doi.org/10.1088/1361-6595/ab759e.

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Shinohara, S., T. Tanikawa, T. Hada, I. Funaki, H. Nishida, T. Matsuoka, F. Otsuka, et al. "High-Density Helicon Plasma Sources: Basics and Application to Electrodeless Electric Propulsion." Fusion Science and Technology 63, no. 1T (May 2013): 164–67. http://dx.doi.org/10.13182/fst13-a16896.

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Tang, Qiang, Zhibin Hu, Xiaxia Cui, Zechao Tao, and Jau Tang. "A Simple and Stable Atmospheric Pressure Electrodeless Water Vapor Microwave Plasma Torch." Applied Sciences 12, no. 13 (July 5, 2022): 6813. http://dx.doi.org/10.3390/app12136813.

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An atmospheric pressure microwave plasma source operating on water vapor has many potential applications. To avoid the corrosion of metal electrodes in a traditional water vapor microwave plasma system, we propose a simple water vapor electrodeless microwave plasma device. By introducing a ceramic tube, the device can work directly with liquid water without complex evaporation equipment. This study examined the relationship between microwave power and water vapor torch plasma duration. When the microwave power is greater than 800 W, the plasma torch can be excited permanently and stably without the loss of ceramic. The excitation of the oxygen atom, hydroxyl radical, and hydrogen atom was found using optical spectroscopy, confirming the water vapor’s decomposition. In addition, it was also found that the crystallinity of the ceramic was improved after microwave discharge. This work enriches the microwave plasma techniques for water vapor for various applications, such as electric propulsion, hydrogen production, and surface treatment.
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Furukawa, Takeru, Yuichi Ishigami, Daisuke Kuwahara, Jyunichi Miyazawa, and Shunjiro Shinohara. "Convergent neutral gas injection using supersonic gas puffing (SSGP) method for propellant feeding system in RF electric propulsion." Review of Scientific Instruments 93, no. 8 (August 1, 2022): 083501. http://dx.doi.org/10.1063/5.0082821.

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A convergent gas feeding method is proposed to alleviate neutral gas depletion near the central plasma region in typical electrodeless radio-frequency (RF)/helicon plasma thrusters. To achieve further performance improvement, the SuperSonic Gas Puffing (SSGP) system is one of the methods that is expected to overcome the above-mentioned depletion and the density limit. This study discovered that the spatiotemporal profiles of the neutral pressure and the estimated gas diffusion angle vary depending on the SSGP gas feeding condition, i.e., the nozzle size, filling pressure, and the valve opening time. Convergent gas feeding is successfully conducted using the SSGP method in a vacuum. As a preliminary study, high-density plasma is also obtained in the vicinity of the gas injection region using the developed SSGP system. The effects of the gas feeding position and an external divergent magnetic field on the plasma density are investigated. A suitable gas feeding position/region exists for plasma generation using the RF/helicon plasma thruster.
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OTSUKA, Shuhei, Toshiki NAKAGAWA, Hiroki ISHII, Naoto TESHIGAHARA, Hiroaki FUJITSUKA, Shimpei WASEDA, Takamichi ISHII, Daisuke KUWAHARA, and Shunjiro SHINOHARA. "Generation and Acceleration of High-Density Helicon Plasma Using Permanent Magnets for the Completely Electrodeless Propulsion System." Plasma and Fusion Research 9 (2014): 3406047. http://dx.doi.org/10.1585/pfr.9.3406047.

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Kolesnichenko, Ya I., V. V. Lutsenko, and T. S. Rudenko. "Theory of the plasma thruster based on the rotating electromagnetic field." Journal of Plasma Physics 81, no. 2 (December 1, 2014). http://dx.doi.org/10.1017/s002237781400110x.

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A theory of electrodeless electric propulsion systems (EEPS) based on the use of the solenoid magnetic field and the rotating electromagnetic field produced by antennas is developed, which includes a study of the plasma acceleration by the Radio Frequency (RF) field and the concomitant thrust. It was assumed that the frequency of the RF field exceeds the lower hybrid frequency but is much less than the electron gyrofrequency. Relations for the thrust are obtained and analyzed. It is shown that thrust gain is significant only when the RF-induced drift velocity well exceeds the fluid velocity of the injected plasma. It is revealed that the curvature of the magnetic field lines and the plasma acceleration in the region outside the solenoid are the factors which can considerably increase the thrust. On the other hand, it is found that the axial inhomogeneity of the plasma and some other factors are unfavorable for the thrust. The obtained results can be used for the optimization of particular experiments aimed to create a new thruster for long-time space missions.
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Dissertations / Theses on the topic "Electrodeless propulsion"

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Georg, Robin Christopher. "Transient antenna-plasma interaction in inductive plasma thrusters." Thesis, 2022. https://hdl.handle.net/2440/136604.

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An electric thruster using material sourced from beyond Earth as propellant would unlock new possibilities for the exploration and exploitation of space. Compared to other technologies under consideration, inductive plasma thrusters are a promising candidate due to their high thrust density and proven propellant flexibility. In contrast with conventional space propulsion technologies, inductive coupling can deliver energy to a propellant without direct contact, making it a form of electrodeless electric propulsion. This can increase its lifetime and enable a more flexible propellant choice in terms of composition. A significant hurdle to the development and eventual implementation of inductive plasma thrusters is the lack of detailed information on the discharge behaviour and diagnostic tools that can be applied for various power and propellant operating conditions. These two aspects are critical to advance the understanding of underlying phenomena and hence the potential for both optimisation and in-flight health monitoring of future thrusters. Previous work has identified transient antenna current behaviour within an inductive plasma thruster that points to complex antenna-plasma interactions, including coupling mode transitions. This thesis documents investigations into these phenomena in order to assess, quantify, explain and exploit them. Firstly, it is shown that these phenomena are observable under a range of conditions and are strongly linked to coupling mode transitions. Secondly, the effect is quantified and its relationship with the overall propulsive performance is examined. Thirdly, a model is developed that adequately explains and illuminates the phenomena. Finally, these phenomena are exploited to develop a new diagnostic tool for investigating transient effects based on antenna current measurements. The new diagnostic tool is non-intrusive in nature since it relies on antenna current measurements, making it highly suitable for use in flight to aid monitoring and control of the thruster. It is especially compatible with a propellant-flexible thruster because it can be applied to a wide range of propellants. It can be implemented with a sufficiently high sampling frequency to resolve transient effects and it can be operated in real time to support flight hardware. The combination of diagnostics, modelling approaches and generated results form a powerful resource to understand transient antenna-plasma interactions within a highpower and propellant-flexible inductive plasma thruster. These results are based on existing experimental data that includes various mixtures of oxygen, carbon dioxide, nitrogen and argon at flow rates from 1.66 to 3.74 g/s and input powers from 0.9 to 154.5 kW. Overall, this thesis documents and explains transient antenna-plasma interactions within an inductive plasma thruster. This amounts to the generation of a significant related dataset, associated knowledge and a new diagnostic tool to support the design, development, testing and operation of inductive plasma thrusters.
Thesis (Ph.D.) -- University of Adelaide, School of Mechanical Engineering, 2022
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Conference papers on the topic "Electrodeless propulsion"

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Brainerd, Jerome J., Al Reisz, and Glen A. Robertson. "Electrodeless Experimental Thruster." In SPACE, PROPULSION & ENERGY SCIENCES INTERNATIONAL FORUM: SPESIF-2009. AIP, 2009. http://dx.doi.org/10.1063/1.3115486.

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Emsellem, Gregory. "Electrodeless Plasma Thruster Design." In 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-3855.

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Toki, Kyoichiro, Shunjiro Shinohara, Takao Tanikawa, and Konstantin Shamrai. "Feasibility Study of Electrodeless Magnetoplasmadynamic Acceleration." In 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-3935.

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Toki, Kyoichiro, Takashi Hashimoto, Yoshikazu Tanaka, Shunjiro Shinohara, Tohru Hada, Yasushi Ikeda, Takao Tanikawa, Konstantin Shamrai, and Ikkoh Funaki. "Compact Helicon Source Experiments for Electrodeless Electromagnetic Thruster." In 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-5311.

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Longmier, Benjamin, and Noah Hershkowitz. ""Electrodeless" Plasma Cathode for Neutralization of Ion Thrusters." In 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-3856.

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Kammash, Terry, and Ricky Tang. "Electrodeless Plasma Thruster with Self-Generated Electric Field." In 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-4121.

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Petro, Elaine M., Raymond J. Sedwick, and Lubos Brieda. "PIC Simulations of Chemistry Effects in an Electrodeless Water Plasma Thruster." In AIAA Propulsion and Energy 2019 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-3998.

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Oshio, Yuya, Seia Ogasawara, Takeru Furukawa, and Hiroyuki Nishida. "Characteristics of Traveling Magnetic Field Acceleration for Electrodeless RF Plasma Thruster." In AIAA Propulsion and Energy 2020 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-3631.

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Emsellem, Gregory, and Serge Larigaldie. "Low Power Behavior of The High Power Electrodeless Plasma Thruster." In 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-5009.

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Toki, Kyoichiro, Takashi Hashimoto, Kenji Makita, Shunjiro Shinohara, Tohru Hada, Yasushi Ikeda, Takao Tanikawa, Konstantin Shamrai, and Ikkoh Funaki. "Small Helicon Source for Electrodeless Plasma Production and Electromagnetic Acceleration." In 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-4843.

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