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Electric propulsion options for the sp-100 reference mission
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Patterson, M. J. Hardy, T. L. Rawlin, V. K. |
| Copyright Year | 1987 |
| Description | Analyses were performed to characterize and compare electric propulsion systems for use on a space flight demonstration of the SP-100 nuclear power system. The component masses of resistojet, arcjet, and ion thruster systems were calculated using consistent assumptions and the maximum total impulse, velocity increment, and thrusting time were determined, subject to the constraint of the lift capability of a single Space Shuttle launch. From the study it was found that for most systems the propulsion system dry mass was less than 20 percent of the available mass for the propulsion system. The maximum velocity increment was found to be up to 2890 m/sec for resistojet, 3760 m/sec for arcjet, and 23 000 m/sec for ion thruster systems. The maximum thruster time was found to be 19, 47, and 853 days for resistojet, arcjet, and ion thruster systems, respectively. |
| File Size | 1074246 |
| Page Count | 26 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19870004989 |
| Archival Resource Key | ark:/13960/t2r54hv0t |
| Language | English |
| Publisher Date | 1987-01-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Electric Propulsion Resistojet Engines Arc Jet Engines Space Shuttle Payloads Nuclear Power Reactors Ion Engines Space Power Reactors Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
