Nuclear Electric Propulsion Of Spacecraft
£5.00
A. R. Martin. (1995), JBIS, 48, pp.517-524
Refcode: 1995.48.517
Abstract:
Conventional propulsion systems for spacecraft, based upon the combustion of chemicals to provide a hot gaseous exhaust, and hence thrust, are limited in the exhaust velocities that they can produce by the limit to the energy that can be provided by the chemical reactions. This exhaust velocity restriction means, as a result of the rocket equation, that large amounts of chemicals are needed to give a large velocity increment to a spacecraft.
