Development of a counterbalanced pendulum thrust stand for electric propulsion

We have designed and tested a thrust stand conceived for the characterization of RF plasma thrusters. The balance has been employed in the development of small-medium size HPT prototypes, therefore it allows for an high number of tests per day with an accuracy within the 10%. The balance relies on the counterbalanced-type pendulum concept, which allows to achieve high sensitivity while maintaining a low overall size of the system; the displacement is measured by means of an high-accuracy laser interferometer put outside the vacuum chamber. The system can be calibrated with both a calibration mass, before the test, and an electro-magnetic device, during the test session. We have verified the linear behavior of the instrument and we have developed a dedicated algorithm in order to correct the thermal drifts of the balance. We have compared the stand measurements with the thrust estimations derived from Faraday probe measurements within the plasma plume, verifying that the two estimates are in agreement within 20%.

[1]  Dmytro Rafalskyi,et al.  Plasma acceleration using a radio frequency self-bias effect , 2015 .

[2]  Simone Rocca.  ONERA micronewton thrust balance: Analytical modelling and parametric analysis , 2011 .

[3]  Francis F. Chen,et al.  Langmuir Probe Diagnostics , 2003 .

[4]  C. L. Enloe,et al.  High‐resolution retarding potential analyzer , 1994 .

[5]  Kunning G. Xu,et al.  High-power, null-type, inverted pendulum thrust stand. , 2009, The Review of scientific instruments.

[6]  M. Patterson,et al.  Thrust Stand Characterization of the NASA Evolutionary Xenon Thruster (NEXT) , 2011 .

[7]  Andrew D. Ketsdever,et al.  Gas dynamic calibration of a nano-Newton thrust stand , 2002 .

[8]  Michael Tsay,et al.  LunarCube: A Deep Space 6U CubeSat with Mission Enabling Ion Propulsion Technology , 2015 .

[9]  Vassilis Angelopoulos,et al.  The ARTEMIS Mission , 2011 .

[10]  Fabio Santoni,et al.  Helicon Plasma Hydrazine.Combined Micro , 2009 .

[11]  G. Thuillier,et al.  The Solar Spectral Irradiance from 200 to 2400 nm as Measured by the SOLSPEC Spectrometer from the Atlas and Eureca Missions , 2003 .

[12]  Francis F. Chen,et al.  1 – Helicon Plasma Sources , 1995 .

[13]  Michael D. West,et al.  Testing a Helicon Double Layer Thruster Immersed in a Space-Simulation Chamber , 2008 .

[14]  A. Lichtenberg,et al.  Principles of Plasma Discharges and Materials Processing: Lieberman/Plasma 2e , 2005 .

[15]  Fabio Trezzolani.  Optimization and Automatic Control of Radio-Frequency Plasma Thrusters for Space Applications , 2015 .

[16]  O. Batishchev,et al.  Minihelicon Plasma Thruster , 2009, IEEE Transactions on Plasma Science.

[17]  Eduardo Ahedo,et al.  Design and development of a 1 kW-class helicon antenna thruster , 2015 .

[18]  A. Lichtenberg,et al.  Principles of Plasma Discharges and Materials Processing , 1994 .

[19]  Ikkoh Funaki,et al.  Development of Electrodeless Plasma Thrusters With High-Density Helicon Plasma Sources , 2014, IEEE Transactions on Plasma Science.