Analytical Parametric Cycle Analysis Of Continuous Rotating Detonation Ejector-augmented Rocket Engine

Abstract

An analytical parametric cycle analysis model for the continuous rotating detonation wave ejector-augmented rocket was developed to estimate and evaluate the maximum potential performance that the continuous rotating detonation wave rocket (CRDWR) itself can provide in an ejector ramjet as well as the two-stage rocket for low earth orbit (LEO). This was done by integrating Bykovskii's model for CRDWR with Heiser & Pratt's modified ejector ramjet and their transatmospheric performance model. The performance results of this unique engine in comparison to a regular rocket counterpart were evaluated primarily 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.