Parametric cycle analysis of continuous rotating detonation ejector-augmented rocket engine

A parametric cycle analysis model for the continuous rotating detonation wave ejectoraugmented rocket was developed via the spreadsheet method and MATLAB to estimate and evaluate the maximum potential performance that it can provide in an ejector ramjet as well as a two-stage rocket for low earth orbit (LEO). This was done by integrating Bykovskiis model for the continuous rotating detonation wave rocket (CRDWR) with Heiser & Pratts modified ejector ramjet and their transatmospheric performance model. The performance results of this particular engine in comparison to its regular rocket counterpart were evaluated in terms of specific thrust and specific impulse with respect to flight Mach number in a constant dynamic pressure trajectory as well as in terms of initial payload mass ratio for a transatmospheric trajectory to LEO.