Plasma Stabilization in Low-Power C Band Microwave Arcjets
Abstract
Performance evaluation of a 100 Watt 7.5 GHz resonant cavity microwave thruster was conducted using helium, nitrogen and ammonia propellants exhausting to both atmospheric and vacuum conditions. Emission spectroscopy of the plasma was made in order to measure the plasma electron temperature at different specific power levels, and the assumption of Local Thermodynamic Equilibrium (LTE) was examined. Electron temperature values of approximately 4000 Kelvin were measured. In order to obtain specific impulse data under vacuum conditions, the Doppler shift between light emitted by the exhaust plume parallel and perpendicular to the gas flow was measured using a high resolution Fabry-Perot interferometer. Centerline specific impulse values were obtained for helium propellant at various specific powers with a maximum value of 1330 seconds measured.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 31, 1999
- Accession Number
- ADA378396
Entities
People
- D. Nordling
- F. Souliez
- Michael M. Micci
Organizations
- Pennsylvania State University