Does it Exist, the New Theoretical Limits for Specific Impulse of Rocket Engines

The technical thermodynamics solution of rocket engine cycle optimization is introduced here. The traditional approximations of thrust production process are critically evaluated and, as a consequence, a noncontroversial thermodynamic approach is presented. This paper underlines the uniqueness of the physical nature of such a thrust production process.

The thermodynamics analysis results show that new limits of theoretical rocket engine specific impulse exist within this approach, and this can lead in future to a reduction of launch costs, environmental benefits for space system use and development of a specific, more efficient rocket system, such as nuclear and SSTO.

New investigations ought to be organised and directed toward finding the practical possibilities to implement the ideas introduced here.