A rocket-based combined cycle propulsion system comprising an air inlet and a centerbody extending along a center axis. The centerbody at least partially defines the air inlet. The system further includes a first propulsion system (e.g., a rotating detonation rocket engine, RDRE) and a second propulsion system (e.g., a scramjet) coupled with the first propulsion system. The system further includes an air bleed assembly including an inlet aperture formed in the centerbody, an outlet aperture positioned in the first propulsion system, and a duct fluidly connecting the inlet aperture and the outlet aperture.

A rocket-based combined cycle propulsion system comprising an air inlet and a centerbody extending along a center axis. The centerbody at least partially defines the air inlet. The system further includes a first propulsion system (e.g., a rotating detonation rocket engine, RDRE) and a second propulsion system (e.g., a scramjet) coupled with the first propulsion system. The system further includes an air bleed assembly including an inlet aperture formed in the centerbody, an outlet aperture positioned in the first propulsion system, and a duct fluidly connecting the inlet aperture and the outlet aperture.

Disclosed is a stabilizer composition for rocket grade hydrogen peroxide (H.sub.2O.sub.2) which is not detrimental to the combustion performance of RDREs and not detrimental to the decomposition performance of catalyst beds while simultaneously greatly increasing the storability of H.sub.2O.sub.2 in rocket propellant management systems including but not limited to tankages and regenerative cooling combustion chambers.

Disclosed is a stabilizer composition for rocket grade hydrogen peroxide (H.sub.2O.sub.2) which is not detrimental to the combustion performance of RDREs and not detrimental to the decomposition performance of catalyst beds while simultaneously greatly increasing the storability of H.sub.2O.sub.2 in rocket propellant management systems including but not limited to tankages and regenerative cooling combustion chambers.