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Synergistic use of high and low thrust propulsion systems for piloted missions to mars
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Gilland, James H. |
| Copyright Year | 1992 |
| Description | The use of high thrust, relatively low specific impulse systems, such as chemical or nuclear thermal propulsion, in conjunction with low thrust, high specific impulse nuclear electric propulsion (NEP) was considered for a representative piloted Mars mission. It was concluded that the single burn option in an all-propulsive mission scenario does not yield a significant advantage in reduced trip time for reasonable masses. The multiple burn option allows significant reductions in trip time relative to the NEP system, and may provide a performance advantage over nuclear thermal propulsion, depending upon the system assumptions. The combined systems serve to reduce high thrust systems' sensitivity to mission opportunity. It is considered that 5 kg/kWe systems can provide significant improvements in mass and trip time over the single systems at power levels of 5 to 10 MWe. |
| File Size | 884682 |
| Page Count | 14 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19920014761 |
| Archival Resource Key | ark:/13960/t20c9vv41 |
| Language | English |
| Publisher Date | 1992-03-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Low Thrust Propulsion Propulsion System Performance High Impulse Manned Mars Missions Nuclear Electric Propulsion Interplanetary Spacecraft Low Thrust Specific Impulse High Thrust Propulsion System Configurations Chemical Propulsion Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
