publication . Article . 2011

Performance characterization of a helicon double layer thruster using direct thrust measurements

Christine Charles; Sabrina Pottinger; Roderick Boswell; Viaos Lappas;
Open Access English
  • Published: 16 May 2011
  • Publisher: HAL CCSD
Abstract
International audience; The performance of a Helicon Double Layer Thruster (HDLT) has been characterised using a pendulum type thrust stand and retarding field energy analyser. Data recorded for a fixed propellant flow rate of 16 sccm of krypton and fixed magnetic field topology show that the thrust generated increases linearly with increasing radio frequency input power over a range of 250 W to 650 W. Over the power range investigated thrust levels of approximately 1 to 2.8 mN were achieved. A maximum effective specific impulse of 280 s was determined using the thrust data. Ion energy distribution functions indicate that increasing power corresponds to improved...
Subjects
free text keywords: Physical Sciences, Acoustics and Ultrasonics, Electronic, Optical and Magnetic Materials, Surfaces, Coatings and Films, Condensed Matter Physics, Volumetric flow rate, Chemistry, Plasma, Electrically powered spacecraft propulsion, Radio frequency, Specific impulse, Computational physics, Nuclear magnetic resonance, Thrust, Propellant, Magnetic field
Related Organizations
18 references, page 1 of 2

[1] C. Charles. Plasmas for spacecraft propulsion. J. Phys. D: Appl. Phys., 42:1{18, 2009.

[2] M. Martinez-Sanchez and J. E. Pollard. Spacecraft electric propulsion{an overview. Journal of Propulsion and Power, 14:1167{1179, 1998.

[3] C. Charles, R. W. Boswell, R. Laine, and P. MacLellan. An experimental investigation of alternative propellants for the helicon double layer thruster. J. Phys. D: Appl. Phys., 41:1{ 6, 2008.

[4] C. Charles and R. W. Boswell. E ect of exhaust magnetic eld in a helicon double-layer thruster operating in xenon. IEEE Transactions on Plasma Science, 36:2141{2146, 2008.

[5] M. D. West, C. Charles, and R. W. Boswell. Testing a helicon double layer thruster immersed in a space-simulation chamber. Journal of Propulsion and Power, 24:134{141, 2008.

[6] S. J. Pottinger, T. Harle, V. J. Lappas, W. Cox, T. La eur, P. Alexander, C. Charles, R. W. Boswell, M Perren, and R Laine. Helicon double layer thruster development for low power operation. Proceedings of Space Propulsion 2010, San Sebastian, Spain:1{10, 2010.

[7] M. D. West, C. Charles, and R. W. Boswell. A high sensitivity momentum ux measuring instrument for plasma thruster exhausts and di usive plasmas. Rev. Sci. Instrum., 80:1{9, 2009.

[8] B. W. Longmier, G. Chavers, and E. A. Bering III. Validating a plasma momentum ux sensor to an inverted pendulum thrust stand. Journal of Propulsion and Power, 25:746{752, 2009. [OpenAIRE]

[9] D. L. Rudakov, M. G. Shats, R. W. Boswell, C. Charles, and J. Howard. Overview of probe diagnostics on the H-1 heliac. Rev. Sci. Instrum., 70:476{479, 1999.

[10] C. Charles. A review of recent laboratory double layer experiments. Plasma Sources Sci. Technol., 16:R1{R25, 2007.

[11] F. N. Gesto, B. D. Blackwell, C. Charles, and R. W. Boswell. Ion detachment in the helicon double-layer thruster exhaust beam. Journal of Propulsion and Power, 22:24{30, 2006.

[12] P. F. Schmit and N. J. Fisch. Magnetic detachment and plume control in escaping magnetized plasma. J. Plasma Physics, 75:359{371, 2009.

[13] C. M. Franck, O. Grulke, and T. Klinger. Mode transitions in helicon discharges. Physics of Plasmas, 10:323{325, 2003.

[14] C. Charles, R. W. Boswell, and M. A. Lieberman. Xenon ion beam characterization in a helicon double layer thruster. Applied Phys. Letters, 89:1{3, 2006.

[15] J. S. Snyder, D. M. Goebel, R. R. Hofer, J. E. Polk, N. C. Wallace, and H. Simpson. Performance evaluation of the T6 ion engine. 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Nashville, TN, AIAA 2010-7114:1{13, 2010.

18 references, page 1 of 2
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