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Method of injecting fluid propellants into a rocket combustion chamber
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1991 |
| Description | A rocket injector is provided with multiple sets of manifolds for supplying propellants to injector elements. Sensors transmit the temperatures of the propellants to a suitable controller which is operably connected to valves between these manifolds and propellant storage tanks. Additional valves are opened to furnish propellants to more of the manifolds when cryogenic propellant temperatures are sensed. Only a portion of the valves are opened to furnish propellants to some of the manifolds when lower temperatures are sensed. |
| File Size | 270263 |
| Page Count | 9 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19910016886 |
| Archival Resource Key | ark:/13960/t3227tc4c |
| Language | English |
| Publisher Date | 1991-05-31 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Controllers Propellant Storage Propellants Injectors Thrust Chambers Valves Storage Tanks Fuel Injection Combustion Chambers Cryogenic Temperature Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Patent |
