Accession Number:

ADA411147

Title:

Resonant Operation of a Micro-Newton Thrust Stand

Descriptive Note:

Technical paper

Corporate Author:

AIR FORCE RESEARCH LAB EDWARDS AFB CA SPACE AND MISSILE PROPULSION DIV

Report Date:

2003-01-09

Pagination or Media Count:

15.0

Abstract:

A computer automated technique suitable for evaluating micro pulsed plasma thruster micro PPT performance has been constructed and validated in the micro-Newton micro N force range. A swinging gate pendulum architecture oscillates with an 8 second period. Force is applied resonantly with oscillation each half period. The calibration method utilizes an electromagnet to pick up and drop masses to apply a known force in the same resonant fashion as thruster operation. The resulting equilibrium amplitudes are linearly proportional to the applied force with an intercept near zero. Thrust measurements are insensitive to short term random vibrational noise because of the resonant operation and are insensitive to long term drift because the amplitude measurements are relative, rather than absolute. The system is capable of resolving 0.5 micro N over the range of 1 to 100 micro N.

Subject Categories:

  • Plasma Physics and Magnetohydrodynamics
  • Electric and Ion Propulsion

Distribution Statement:

APPROVED FOR PUBLIC RELEASE