A pulse combustor system for efficiently operating a pulse combustor. The pulse combustor system includes the pulse combustor and a duct. The pulse combustor has a combustion chamber defining an internal space, a conduit having a first end in fluid communication with the internal space and a second end in fluid communication with an environment outside of the pulse combustor system, and a fuel injector configured to inject fuel into the internal space of the combustion chamber. The duct has two openings, with one opening disposed adjacent to the second end of the conduit. The pulse combustor system has an average operating frequency, and the duct has a length that is about one quarter of a wavelength corresponding to the average operating frequency. The pulse combustor and the duct each has a central longitudinal axis, and the two axes are substantially aligned.

A system and method is disclosed for the start-up and control of pulsejet engines and this system includes an Electronic Fuel Injection (“EFI”) system that further includes one or more electrically controlled fuel injectors that can be selectively operated for start-up and control of such pulsejet engines. According to the system and method, the rate and/or pattern of fuel delivery to pulsejet engines can be varied not only by controlling the amount of time the fuel injectors are open versus closed to define a “duty cycle,” but also with the capability to selectively disable one or more fuel injectors in the programmed manner for start-up and control of such pulsejet engines.

A system and method is disclosed for the start-up and control of pulsejet engines and this system includes an Electronic Fuel Injection (EFI) system that further includes one or more electrically controlled fuel injectors that can be selectively operated for start-up and control of such pulsejet engines. According to the system and method, the rate and/or pattern of fuel delivery to pulsejet engines can be varied not only by controlling the amount of time the fuel injectors are open versus closed to define a duty cycle, but also with the capability to selectively disable one or more fuel injectors in the programmed manner for start-up and control of such pulsejet engines.

A pulse combustor system for efficiently operating a pulse combustor. The pulse combustor system includes the pulse combustor and a duct. The pulse combustor has a combustion chamber defining an internal space, a conduit having a first end in fluid communication with the internal space and a second end in fluid communication with an environment outside of the pulse combustor system, and a fuel injector configured to inject fuel into the internal space of the combustion chamber. The duct has two openings, with one opening disposed adjacent to the second end of the conduit. The pulse combustor system has an average operating frequency, and the duct has a length that is about one quarter of a wavelength corresponding to the average operating frequency. The pulse combustor and the duct each has a central longitudinal axis, and the two axes are substantially aligned.

A pulse combustor system for efficiently operating a pulse combustor. The pulse combustor system includes the pulse combustor and a duct. The pulse combustor has a combustion chamber defining an internal space, a conduit having a first end in fluid communication with the internal space and a second end in fluid communication with an environment outside of the pulse combustor system, and a fuel injector configured to inject fuel into the internal space of the combustion chamber. The duct has two openings, with one opening disposed adjacent to the second end of the conduit. The pulse combustor system has an average operating frequency, and the duct has a length that is about one quarter of a wavelength corresponding to the average operating frequency. The pulse combustor and the duct each has a central longitudinal axis, and the two axes are substantially aligned.

A combustion method is disclosed, which includes the steps of mixing fuel and an oxidizer into a mixture, wherein fuel originates from a fuel manifold and the oxidizer originates from an oxidizer manifold, and combusting the mixture in a combustion chamber, the fuel manifold, the oxidizer manifold, and the combustion chamber forming parts of an injector assembly wherein each of the fuel and oxidizer manifolds communicates with the combustion chamber via a plurality of dedicated radially disposed Tesla valves around the combustion chamber each via a corresponding port with only one Tesla valve between the fuel manifold and the corresponding port on the combustion chamber and with only one Tesla valve between the oxidizer manifold and the corresponding port on the combustion chamber, wherein the plurality of Tesla valves substantially eliminate reverse flow of exhaust gases from the combustion chamber back to the fuel manifold or the oxidizer manifold.

A combustion method is disclosed, which includes the steps of mixing fuel and an oxidizer into a mixture, wherein fuel originates from a fuel manifold and the oxidizer originates from an oxidizer manifold, and combusting the mixture in a combustion chamber, the fuel manifold, the oxidizer manifold, and the combustion chamber forming parts of an injector assembly wherein each of the fuel and oxidizer manifolds communicates with the combustion chamber via a plurality of dedicated radially disposed Tesla valves around the combustion chamber each via a corresponding port with only one Tesla valve between the fuel manifold and the corresponding port on the combustion chamber and with only one Tesla valve between the oxidizer manifold and the corresponding port on the combustion chamber, wherein the plurality of Tesla valves substantially eliminate reverse flow of exhaust gases from the combustion chamber back to the fuel manifold or the oxidizer manifold.

A pulse combustor system for efficiently operating a pulse combustor. The pulse combustor system includes the pulse combustor and a duct. The pulse combustor has a combustion chamber defining an internal space, a conduit having a first end in fluid communication with the internal space and a second end in fluid communication with an environment outside of the pulse combustor system, and a fuel injector configured to inject fuel into the internal space of the combustion chamber. The duct has two openings, with one opening disposed adjacent to the second end of the conduit. The pulse combustor system has an average operating frequency, and the duct has a length that is about one quarter of a wavelength corresponding to the average operating frequency. The pulse combustor and the duct each has a central longitudinal axis, and the two axes are substantially aligned.

A pulse combustor system for efficiently operating a pulse combustor. The pulse combustor system includes the pulse combustor and a duct. The pulse combustor has a combustion chamber defining an internal space, a conduit having a first end in fluid communication with the internal space and a second end in fluid communication with an environment outside of the pulse combustor system, and a fuel injector configured to inject fuel into the internal space of the combustion chamber. The duct has two openings, with one opening disposed adjacent to the second end of the conduit. The pulse combustor system has an average operating frequency, and the duct has a length that is about one quarter of a wavelength corresponding to the average operating frequency. The pulse combustor and the duct each has a central longitudinal axis, and the two axes are substantially aligned.

A system and method is disclosed for improving the performance of pulsejet engines and of flight vehicles that incorporate pulsejet engines as a propulsion system. The system and method will decelerate the oncoming airstream to which a U-shaped pulsejet engine that is the propulsion system for a flight vehicle is exposed so that larger amounts of atmospheric air will be ingested into a rearward-facing inlet pipe for improved engine operation at low and high speeds/altitudes. The system and method provide for the recovery of the dynamic pressure of the incoming fresh airstream to raise the static pressure around the rearward facing inlet pipe to generate higher pressures and higher air density for improving the ingestion of air mass into the inlet pipe of the pulsejet engine thereby producing greater engine power and thrust.