Resistojet Thruster Shield Evaluation
Abstract
A multipropellant resistojet was selected as a low-thrust option for the Space Station System. It is planned to use this system to dispose of a variety of excess fluids that are expected to be present on the space station and to use the thrust developed in this process for drag make up. It has been concluded that use of these excess fluids in this manner will result in a reduction in Space Transportation System costs which would be associated with launching of the necessary propellants as well as the removal of the excess fluids from the space station. A series of tests has been completed at AEDC to define the flow field of a resistojet plume in a hard vacuum. The purpose of these tests was to provide an experimental data base which could be used in the development of plume shields that are required for the effective operation of the resistojet on the NASA Space Station. In the present investigation, plume characteristics of a heated carbon dioxide expansion were evaluated. Three flow diagnostics were used in this evaluation, rotary pitot probe, rotary liquid- nitrogen-cooled quartz crystal micro-balance and an ion gage pressure probe. Keywords: Exhaust plumes; Low density; Nozzle flow; Flow field mapping.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1987
- Accession Number
- ADA188406
Entities
People
- A. B. Bailey
Organizations
- Arnold Engineering Development Complex