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Electric propulsion for low earth orbit constellations (Document No: 19990009563)
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Sankovic, John M. Oleson, Steven R. |
| Copyright Year | 1998 |
| Description | Hall effect electric propulsion was evaluated for orbit insertion, satellite repositioning, orbit maintenance and de-orbit applications for a sample low earth orbit satellite constellation. Since the low masses of these satellites enable multiple spacecraft per launch, the ability to add spacecraft to a given launch was used as a figure of merit. When compared to chemical propulsion, the Hall thruster system can add additional spacecraft per launch using planned payload power levels. One satellite can be added to the assumed four satellite baseline chemical launch without additional mission times. Two or three satellites may be added by providing part of the orbit insertion with the Hall system. In these cases orbit insertion times were found to be 35 and 62 days. Depending, on the electric propulsion scenario, the resulting launch vehicle savings is nearly two, three or four Delta 7920 launch vehicles out of the chemical baseline scenario's eight Delta 7920 launch vehicles. |
| File Size | 615724 |
| Page Count | 12 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19990009563 |
| Archival Resource Key | ark:/13960/t6935s22j |
| Language | English |
| Publisher Date | 1998-11-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Electric Propulsion Satellite Constellations Low Earth Orbits Stationkeeping Comparison Hall Effect Orbit Insertion Spacecraft Launching Orbital Maneuvers Chemical Propulsion Payloads Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
