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A Comparison of Nuclear Thermal and Nuclear Electric Propulsion for Interplanetary Missions
| Content Provider | Semantic Scholar |
|---|---|
| Author | Osenar, Michael J. |
| Copyright Year | 2005 |
| Abstract | Abstract : A comparison is made between nuclear thermal rockets and nuclear powered electric propulsion systems. Complete missions are designed to be launched by a single Ariane 5 and fly by Jupiter and Pluto powered either by a nuclear thermal system or a nuclear powered electric system. It is shown that it is feasible to build both nuclear thermal and nuclear electric missions to Jupiter and Pluto. Nuclear thermal systems are designed to go to Jupiter with an inert mass fraction of 0.6094, a power of 281.23 MW and a flight time of 4.13 years. Nuclear thermal systems are designed to go to Pluto with an inert mass fraction of 0.4182, a power of 281.23 MW and a flight time of 19 years. Nuclear electric systems are designed to go to Jupiter with an inert mass fraction of 0.5266, a power of 10.258 kW and a flight time of 4.13 years. Nuclear electric systems are designed to go to Pluto with an inert mass fraction of 0.2656, a power of 10.258 kW and a flight time of 19 years. The results of the system designs are analyzed and an outlook is given for each system. Additional issues of testing, safety and radiological hazards are discussed. |
| File Format | PDF HTM / HTML |
| Alternate Webpage(s) | https://apps.dtic.mil/dtic/tr/fulltext/u2/a431030.pdf |
| Language | English |
| Access Restriction | Open |
| Content Type | Text |
| Resource Type | Article |
