Hostname: page-component-78c5997874-dh8gc Total loading time: 0 Render date: 2024-11-13T04:30:04.302Z Has data issue: false hasContentIssue false
  • English
  • Français

Performance investigation of a high-temperature and power Hall-effect electric propulsion

Published online by Cambridge University Press:  12 November 2019

Lai Li Open the ORCID record for Lai Li [Opens in a new window] ,
Xi Lu ,
Wei Wang ,
Guiping Zhu ,
Hulin Huang  and
Xidong Zhang
Lai Li
Affiliation:
College of Astronautics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
Xi Lu
Affiliation:
Shanghai Key Laboratory of Deep Space Exploration Technology, Shanghai 201109, China
Wei Wang
Affiliation:
Shanghai Key Laboratory of Deep Space Exploration Technology, Shanghai 201109, China
Guiping Zhu*
Affiliation:
College of Astronautics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
Hulin Huang
Affiliation:
College of Astronautics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
Xidong Zhang
Affiliation:
College of Energy and Power Engineering, Nanjing Institute of Technology, Nanjing 211167, China
*
†Email address for correspondence: zhuguiping@nuaa.edu.cn
Get access Rights & Permissions [Opens in a new window]

Abstract

This paper discusses a detailed computational analysis that illustrated the influences of the magnetic field and external potential on the performance of a high-temperature Hall-effect electric thruster. Uniform and non-uniform magnetic field configurations were examined. The Lorentz force in the $x$ direction, acting on the plasma, was shown to substantially enhance the flow velocity in the non-uniform magnetic field, which indicated that the non-uniform magnetic field was more suitable for Hall-effect electromagnetic acceleration. The static temperature increased with the external potential, especially near the region of cathode. This increment in gas temperature, together with the effect of the Lorentz force, results in the enhancement of the velocity at the front and back of the cathode. However, the Mach number and gas density decreased due to static temperature increases caused by the conversion of more electric power into internal energy. The thrust increased eventually with the increase of the average exit velocity.

Keywords

electric dischargesplasma applicationsplasma flows
Type
Research Article
Information
Journal of Plasma Physics , Volume 85 , Issue 6 , December 2019 , 905850605
Copyright
© Cambridge University Press 2019 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

Borowski, S. K., Mccurdy, D. & Packard, T. 2012 Nuclear thermal propulsion (NTP), A proven, growth technology for ‘Fast Transit’ human missions to mars. In IEEE Aerospace Conference, pp. 1–20. IEEE.Google Scholar
Borowski, S. K., Mccurdy, D. R. & Burke, L. M. 2014 The nuclear thermal propulsion stage (NTPS), a key space asset for human exploration and commercial missions to the moon. In AIAA Space Conference and Exposition, pp. 2013–5465. AIAA.Google Scholar
Brown, D. L., Beal, B. E. & Haas, J. M. 2010 Air force research laboratory high power electric propulsion technology development. In IEEE Aerospace Conference, pp. 1–9.Google Scholar
Cassady, R. J., Frisbee, R. H., Gilland, J. H., Houts, M. G., LaPointe, M. R., Maresse-Reading, C. M., Oleson, S. R., Polk, J. E., Russell, D. & Sengupta, A. 2008 Recent advances in nuclear powered electric propulsion for space exploration. Energy Convers. Manage. 49 (3), 412–435.Google Scholar
Choueiri, E. Y. 2004 A critical history of electric propulsion, the first 50 years (1906–1956). J. Propul. Power 20 (2), 193–203.Google Scholar
Clark, J. S., George, J. A., Gefert, L. P., Doherty, M. P. & Sefcik, R. J. 1994 Nuclear electric propulsion, A better, safer, cheaper transportation system for human exploration of Mars. pp. 1–15. American Institute of Physics, NASA-TM-106406.Google Scholar
Florenz, R., Gallimore, A. D. & Peterson, P. Y. 2011 Developmental status of a 100-kW class laboratory nested channel Hall thruster. In 32nd International Electric Propulsion Conference, IEPC-2011-246.Google Scholar
Harada, N., Hishikawa, M., Nara, N. & Sakamoto, N. 2005 Plasma Stability, Generator Performance and Stable Operation of Mixed Inert Gas Non-equilibrium MHD Generator, vol. 1 (07), pp. 59–69. MISM.Google Scholar
Hopkins, M. A., Jason, M., Makela, J. M., Washeleski, R. & King, L.2010 Mass flow control in a magnesium Hall-effect thruster. In 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, AIAA-2010-6681.Google Scholar
Ichihara, D., Uno, T., Kataoka, H., Jeong, J., Iwakawa, A. & Sasoh, A. 2016 Ten-ampere-level, applied-field-dominant operation in magnetoplasmadynamic thrusters. J. Propul. Power 33 (2), 1–10.Google Scholar
Jacobson, D. T., Manzella, D. H., Hofer, R. R. & Peterson, P. Y. 2004 NASA’s 2004 Hall thruster program. AIAA J. 1–11.Google Scholar
Jankovsky, R. S., Tverdokhlebov, S. & Manzella, D. 1999 High power Hall thrusters. In Proceedings of the 35th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, AIAA-99-2949.Google Scholar
Joyner, C. R., Levack, D. & Borowski, S. K. 2012 Development of a small nuclear thermal propulsion flight demonstrator concept that is scalable to human missions. In 48th AIAA/ASME/SAE/ASEE, Joint Propulsion Conference and Exhibit, pp. 2012–4207.Google Scholar
Kim, H., Lim, Y., Choe, W., Park, S. & Seon, J. 2005 Effect of magnetic field configuration on the multiply charged ion and plume characteristics in Hall thruster plasmas. Appl. Phys. Lett. 106 (15), 2579.Google Scholar
Liang, R. & Gallimore, A. D. 2011 Far-field plume measurements of a nested-channel Hall-effect thruster. In 49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, Orlando, Florida, AIAA-2011-1016.Google Scholar
Litchford, R. J. & Harada, N. 2011 Multi-MW closed cycle MHD nuclear space power via nonequilibrium He/Xe working plasma. In Proceedings of Nuclear and Emerging Technologies for Space, Albuquerque, NM, p. 3349.Google Scholar
Mazouffre, S. 2016 Electric propulsion for satellites and spacecraft, established technologies and novel approaches. Plasma Sources Sci. Technol. 25 (3), 033002.Google Scholar
McVey, J. B., Perrucci, A. S. & Britt, E. A.2005 Multichannel Hall effect thruster. United States Patent, Patent No. US 7,030,576 B2.Google Scholar
Mitchner, M. & Kruger, C. H. 1973 Partially Ionized Gases. Wiley.Google Scholar
Ortega, A. L. & Mikellides, I. G. 2016 The importance of the cathode plume and its interactions with the ion beam in numerical simulations of Hall thrusters. Phys. Plasmas 23 (4), 295–865.Google Scholar
Paccani, G., Chiarotti, U. & Deininger, W. D. 2015 Quasisteady ablative magnetoplasmadynamic thruster performance with different propellant. J. Propul. Power 14 (2), 254–260.Google Scholar
Soulas, G. C., Haag, T. W. & Herman, D. A.2012 Performance test results of the NASA-457Mv2 Hall thruster. In 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, AIAA-2012-3940.Google Scholar
Tajmar, M. & Wang, J. 2000 Three-dimensional numerical simulation of field-emission-electric-propulsion neutralization. J. Propul. Power 16 (3), 536–544.Google Scholar
Tanaka, M., Murakami, T. & Okuno, Y. 2014 Plasma characteristics and performance of magnetohydrodynamic generator with high-temperature inert gas plasma. IEEE Trans. Plasma Sci. 42 (12), 4020–4025.Google Scholar
Tanaka, M. & Okuno, Y. 2016 High-temperature inert-gas-plasma Faraday-type magnetohydrodynamic generator with various working gases. J. Propul. Power 32 (4), 1–6.Google Scholar
Wilbur, P. J., Rawlin, V. K. & Beattie, J. R. 1998 Ion thruster development trends and status in the United States. J. Propul. Power 14 (5), 708–715.Google Scholar
Wirz, R. & Goebel, D. 2008 Effects of magnetic field topography on ion thruster external performance. Plasma Sources Sci. Technol. 17 (3), 035010.Google Scholar