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Upper stages utilizing electric propulsion
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Byers, D. C. |
| Copyright Year | 1980 |
| Description | The payload characteristics of geocentric missions which utilize electron bombardment ion thruster systems are discussed. A baseline LEO to GEO orbit transfer mission was selected to describe the payload capabilities. The impacts on payloads of both mission parameters and electric propulsion technology options were evaluated. The characteristics of the electric propulsion thrust system and the power requirements were specified in order to predict payload mass. This was completed by utilizing a previously developed methodology which provides a detailed thrust system description after the final mass on orbit, the thrusting time, and the specific impulse are specified. The impact on payloads of total mass in LEO, thrusting time, propellant type, specific impulse, and power source characteristics was evaluated. |
| File Size | 749411 |
| Page Count | 21 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19800007837 |
| Archival Resource Key | ark:/13960/t2d844h54 |
| Language | English |
| Publisher Date | 1980-01-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Electric Propulsion Transfer Orbits Propulsive Efficiency Spacecraft Power Supplies Electron Bombardment Payloads Spacecraft Propulsion Mercury Ion Engines Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
