A vehicle for supersonic or hypersonic flight comprises a thermal rocket engine (1b) with a nozzle (2) and an active cooling system (8). The active cooling system cools a heat shield (6, 7). A working fluid absorbs heat inside the active cooling system and the heated working fluid expands through the nozzle to create thrust. Such a vehicle is suitable to fly a multi-skip trajectory, a boost-glide trajectory, a trajectory with a cruise phase or a re-entry into an atmosphere, for example.

A rotating detonation engine comprising: an outer cylinder that extends in an axial direction; a base that is connected to the outer cylinder, and comprises a plurality of fuel injection ports positioned in a circular ring shape and injecting a fuel, and a plurality of oxidizing agent injection ports positioned in a circular ring shape and injecting an oxidizing agent; an inner cylinder that is positioned in the outer cylinder, and is positioned in the axial direction relative to the base; and a mechanism that switches a combustion space, wherein the combustion space is switched in accordance with a combustion mode.