Use of propellants different from hydrogen for the space propulsion
| dc.contributor.author | Leonardi, Erminia | |
| dc.contributor.author | Rubbia, Carlo | |
| dc.date.accessioned | 2014-06-04T10:38:58Z | |
| dc.date.available | 2014-06-04T10:38:58Z | |
| dc.date.issued | 2000 | |
| dc.description.abstract | The possibility of hydrogen heating by the fission fragments has been widely discussed in the work “Fission fragment heating for space propulsion” [1], in which an innovative method, developed by C. Rubbia, is presented. In that work the criterions in the choice of the propellant for a spacecraft have been well discussed; for instance, a high enthalpy at an acceptable temperature is an important requirement in order to obtain a high exhaust speed, as shown in the St. Vennant and Wenzel formula. | IT |
| dc.identifier.uri | http://hdl.handle.net/11050/989 | |
| dc.language.iso | en | IT |
| dc.subject | fission fragments | IT |
| dc.subject | space propulsion | IT |
| dc.subject | spacecraft | IT |
| dc.subject.een-cordis | EEN CORDIS::ENERGIA::Fissione nucleare / fusione nucleare::Fissione nucleare / fusione nucleare | IT |
| dc.title | Use of propellants different from hydrogen for the space propulsion | IT |
| dc.type | Report | IT |