Abstract: A nozzle for a detonative combustion engine, the engine having multiple combustor tubes, comprises a common plenum communicating with the combustor tubes. The common plenum combines separate exhaust streams from the combustor tubes into a compound subsonic exhaust stream. A compound flow throat communicates with the common plenum. The compound flow throat converts the compound subsonic exhaust stream into a compound sonic exhaust stream. The common plenum and compound flow throat cooperate to maintain a predetermined upstream combustor pressure regardless of down stream pressure exiting the expansion section. Optionally, an interface section is inserted between the plenum and the engine such that it communicates with the common plenum section and with outlets of the combustor tubes. The interface section is compartmentalized into flow passages with each flow passage having a cross-sectional area that increases from that of a particular nozzle intake port connected to a conductor tube exit.

Abstract: The invention provides a liquid fueled pulsed detonation air breathing engine. The engine has at least one, and preferably a multiplicity of, detonation chambers, each of which has an inlet end for opening and receiving a charge of fuel and air, and an outlet end for discharging combustion product gases. A fast-acting valve is located above the inlet ends of the detonation chambers and cyclically opens the fuel and air receiving openings in the inlet ends of the detonation chambers to allow a fuel/air charge to enter the chambers. In a preferred embodiment, the valve is of a rotary type with a body that has at least one opening through which fuel and air can flow into the inlet end of the detonation chamber. Once the valve has closed, detonation is initiated by an ignitor and impulse force is provided by the resultant shock wave. Thereafter, the valve opens again so that the detonation chamber can be charged with fuel and air to recommence the cycle.

Abstract: A pulse detonation rocket engine, having at least two detonation chambers. The rocket propelled vehicle includes at least one fuel delivery system in fluid communication with each of the at least two detonation chambers, and at least one oxidant delivery system in fluid communication with the detonation chambers, along with fast-acting valves to inject fuel and oxidant controlledly into the chambers. An ignitor in each of the detonation chambers intermittently initiates detonation of a fuel and oxidant mixture in the chamber, in a controlled cycle, to provide motive force. Also provided is a combined cycle engine, able to operate in air breathing mode, oxidant augmented mode, and as a rocket engine. The combined cycle engine includes at least one detonation chamber, and may include a plurality of such chambers. The invention further provides methods of intermittently detonating sequentially created fuel and oxygen mixtures in these engines, and methods of using these engines.