Transport Processes in Pulsed Plasma Thrusters
Abstract
The simplicity of the pulsed plasma microthruster (PPT) allowed its selection for space flight application, even with low efficiency relative to other concepts. Improvements to PPT thrust efficiency and specific impulse represent today's challenges for research and development. Self consistent modeling of PPT behavior requires a description of the flow composition as it changes from complex molecular forms to highly ionized, constituent atoms. Heat flux from the plasma discharge to the solid propellant, (traditionally, Teflon), depends on transport coefficients for electrical and thermal conductivity in the partially ionized flow. Numerical simulations now use an existing, single temperature equation of state for Teflon (from the SESAME tables) along with classical transport formulas based on Coulomb collisions. The principal effort under the present grant has been to develop a two-temperature, LTE model for Teflon in the regime of interest for PPTs. This model includes 25 species (atoms, molecules, ions and electronics) and allows separates heavy-particle and electron temperatures. An idealized analysis, limited to one-dimensional, quasi-steady MHD flow, but incorporating resistive heating and thermal diffusion, has also been developed and provides useful guidance on PPT operation and propellant behavior.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1997
- Accession Number
- ADA340455
Entities
People
- P. J. Turchi
Organizations
- Ohio State University