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High temperature thruster technology for spacecraft propulsion
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Schneider, Steven J. |
| Copyright Year | 1991 |
| Description | A technology program intended to develop high-temperature oxidation-resistant thrusters for spacecraft applications is considered. The program will provide the requisite material characterizations and fabrication to incorporate iridium coated rhenium material into small rockets for spacecraft propulsion. This material increases the operating temperature of thrusters to 2200 C, a significant increase over the 1400 C of the silicide-coated niobium chambers currently used. Stationkeeping class 22 N engines fabricated from iridium-coated rhenium have demonstrated steady state specific impulses 20-25 seconds higher than niobium chambers. These improved performances are obtained by reducing or eliminating the fuel film cooling requirements in the combustion chamber while operating at the same overall mixture ratio as conventional engines. |
| File Size | 6743432 |
| Page Count | 16 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19920005907 |
| Archival Resource Key | ark:/13960/t08w8b43n |
| Language | English |
| Publisher Date | 1991-01-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power High Temperature Coatings Steady State Niobium Thermal Stability Spacecraft Propulsion Fabrication Oxidation Resistance Stationkeeping Specific Impulse Iridium Rhenium Film Cooling Combustion Chambers Rocket Engine Design Refractory Coatings Operating Temperature Technology Utilization Thrustors Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
