A hybrid aircraft architecture is disclosed that uses an electric motor-generator-propeller propulsion system for takeoff, landings, and low speed flying, and wave engines for cruise-condition flying and flying at high speeds. The propeller of the electric motor-generator-propeller propulsion system can be located at the nose or aft end (tail) of the aircraft. The wave engines can be located at the aft end of the fuselage, or under or integrated into the wing structures. The wave engines can be deployed in pairs and the wave engines of the pair may be cross-connected and operated in an anti-phase mode to reduce the noise and vibration that would exist if each wave engine is operated independently.
B64D 27/35 - Arrangements for on-board electric energy production, distribution, recovery or storage
B64D 31/18 - Power plant control systemsArrangement of power plant control systems in aircraft for electric power plants for hybrid-electric power plants
2.
APPARATUS FOR FUEL-AIR MIXING AND FLAME-HOLDING IN PULSE COMBUSTORS
A system and method are disclosed for improving the operation of pulse combustors that are used in pulsejets by disposing a turbulator in the inlet pipe near where it is connected to the combustion chamber to cause increased turbulence in the combustion chamber to enhance fuel/air mixing, increased combustion chamber pressure, and flame-holding.
A hybrid aircraft architecture is disclosed that uses an electric motor-generator-propeller propulsion system for takeoff, landings, and low speed flying, and wave engines for cruise-condition flying and flying at high speeds. The propeller of the electric motor-generator-propeller propulsion system can be located at the nose or aft end (tail) of the aircraft. The wave engines can be located at the aft end of the fuselage, or under or integrated into the wing structures. The wave engines can be deployed in pairs and the wave engines of the pair may be cross-connected and operated in an anti-phase mode to reduce the noise and vibration that would exist if each wave engine is operated independently.
A system and method is disclosed for improving fuel injection systems for pulse combustors that reduce protrusions that can detrimentally impact the performance of pulsejet aircraft to which such pulse combustors are associated. The fuel injection system disclosed herein can be used with a pulse combustor to minimize protrusions, with the pulse combustor including at least an inlet pipe, a combustion chamber, an exhaust pipe, an ignition device, a fuel supply system, with the fuel injection system
F02C 5/10 - Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the working fluid forming a resonating or oscillating gas column, i.e. the combustion chambers having no positively actuated valves, e.g. using Helmholtz effect
F02K 7/02 - Plants in which the working-fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fanControl thereof the jet being intermittent, i.e. pulse jet
F23R 7/00 - Intermittent or explosive combustion chambers
F02C 9/28 - Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
5.
APPARATUS FOR FUEL-AIR MIXING AND FLAME-HOLDING IN PULSE COMBUSTORS
A system and method are disclosed for improving the operation of pulse combustors that are used in pulsejets by disposing a turbulator in the inlet pipe near where it is connected to the combustion chamber to cause increased turbulence in the combustion chamber to enhance fuel/air mixing, increased combustion chamber pressure, and flame-holding.
F02K 7/02 - Plants in which the working-fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fanControl thereof the jet being intermittent, i.e. pulse jet
F23R 7/00 - Intermittent or explosive combustion chambers
F02C 5/10 - Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the working fluid forming a resonating or oscillating gas column, i.e. the combustion chambers having no positively actuated valves, e.g. using Helmholtz effect
6.
FUEL INJECTION AND MIXING APPARATUS FOR PULSE COMBUSTORS
A system and method is disclosed for improving fuel injection systems for pulse combustors that reduce protrusions that can detrimentally impact the performance of pulsejet aircraft to which such pulse combustors are associated. The fuel injection system disclosed herein can be used with a pulse combustor to minimize protrusions, with the pulse combustor including at least an inlet pipe, a combustion chamber, an exhaust pipe, an ignition device, a fuel supply system, with the fuel injection system.
F02K 7/02 - Plants in which the working-fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fanControl thereof the jet being intermittent, i.e. pulse jet
7.
System and method for ram air intake for pulse combustors
A system and method for ram air intake for pulse combustion systems is disclosed that improves the ability of pulse combustions to ingest air into the inlet pipe when the pulse combustion system is moving in a direction opposite the direction the open end of the inlet pipe is facing and the system and method includes the ability to increase the thrust output from the pulse combustion system.
F02C 5/10 - Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the working fluid forming a resonating or oscillating gas column, i.e. the combustion chambers having no positively actuated valves, e.g. using Helmholtz effect
F02C 5/02 - Gas-turbine plants characterised by the working fluid being generated by intermittent combustion characterised by the arrangement of the combustion chamber in the plant
F02C 5/11 - Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the working fluid forming a resonating or oscillating gas column, i.e. the combustion chambers having no positively actuated valves, e.g. using Helmholtz effect using valveless combustion chambers
F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants
8.
SYSTEM AND METHOD FOR RAM AIR INTAKE FOR PULSE COMBUSTORS
A system and method for ram air intake for pulse combustion systems is disclosed that improves the ability of pulse combustions to ingest air into the inlet pipe when the pulse combustion system is moving in a direction opposite the direction the open end of the inlet pipe is facing and the system and method includes the ability to increase the thrust output from the pulse combustion system.
F02K 7/04 - Plants in which the working-fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fanControl thereof the jet being intermittent, i.e. pulse jet with resonant combustion chambers
9.
Method and apparatus for the start-up and control of pulse combustors using selective injector operation
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.
F23R 7/00 - Intermittent or explosive combustion chambers
F02K 7/067 - Plants in which the working-fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fanControl thereof the jet being intermittent, i.e. pulse jet with combustion chambers having valves having aerodynamic valves
F02C 9/48 - Control of fuel supply conjointly with another control of the plant
F02C 5/10 - Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the working fluid forming a resonating or oscillating gas column, i.e. the combustion chambers having no positively actuated valves, e.g. using Helmholtz effect
09 - Scientific and electric apparatus and instruments
Goods & Services
Pulse jet engines for the propulsion of aircraft; equipment and parts for pulse jet engines for the propulsion of aircraft, namely, exhaust and inlet tubing, combustion chambers, ignition systems, fuel supply systems comprised of fuel injectors and engine controllers in the nature of hydraulic and pneumatic controls for engines Recorded and downloadable computer software, hardware, analyzers in the nature of liquid and residual gas analyzers, fluid velocity sensors, pressure sensors and temperature sensors, sold as a unit, for pulse jet engine operation, control, diagnosis, and maintenance, for analyzing and measuring pulse jet engine operating functions and performance, namely, fuel consumption, thrust production, engine temperature, air intake volume, engine pressure, fuel/air mixture for combustion, operating engine frequencies, engine frequency suppression, and anti-phase operation; Electrical systems consisting of computer hardware, embedded firmware, and embedded software, for the integration of pulse jet engines into aircraft; electrical systems consisting of electrical controllers and mechanical controllers in the nature of mechanical remote controls for pulse jet engines, electrical wires, electrical cables, and electrical connectors for integration of pulse jet engines into aircraft
11.
Method and apparatus for the start-up and control of pulse combustors using selective injector operation
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.
F23R 7/00 - Intermittent or explosive combustion chambers
F02K 7/067 - Plants in which the working-fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fanControl thereof the jet being intermittent, i.e. pulse jet with combustion chambers having valves having aerodynamic valves
F02C 9/48 - Control of fuel supply conjointly with another control of the plant
F02C 5/10 - Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the working fluid forming a resonating or oscillating gas column, i.e. the combustion chambers having no positively actuated valves, e.g. using Helmholtz effect
12.
Systems and methods for air-breathing wave engines for thrust production
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.
F02K 7/02 - Plants in which the working-fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fanControl thereof the jet being intermittent, i.e. pulse jet
F02K 7/067 - Plants in which the working-fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fanControl thereof the jet being intermittent, i.e. pulse jet with combustion chambers having valves having aerodynamic valves
F02K 7/04 - Plants in which the working-fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fanControl thereof the jet being intermittent, i.e. pulse jet with resonant combustion chambers
F02C 5/10 - Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the working fluid forming a resonating or oscillating gas column, i.e. the combustion chambers having no positively actuated valves, e.g. using Helmholtz effect
F23C 15/00 - Apparatus in which combustion takes place in pulses influenced by acoustic resonance in a gas mass
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.
F02K 7/02 - Plants in which the working-fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fanControl thereof the jet being intermittent, i.e. pulse jet
14.
METHOD AND APPARATUS FOR THE START-UP AND CONTROL OF PULSE COMBUSTORS USING SELECTIVE INJECTOR OPERATION
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.
F23R 7/00 - Intermittent or explosive combustion chambers
F02D 41/38 - Controlling fuel injection of the high pressure type
F02K 7/02 - Plants in which the working-fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fanControl thereof the jet being intermittent, i.e. pulse jet
F02C 5/10 - Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the working fluid forming a resonating or oscillating gas column, i.e. the combustion chambers having no positively actuated valves, e.g. using Helmholtz effect
A pulse combustor system for reducing noise and/or vibration levels. The system includes a pulse combustor including a combustion chamber, an inlet pipe, an exhaust pipe, and a first fuel injector for injecting fuel into the combustion chamber. The pulse combustor has a fundamental oscillation mode and one or more additional oscillation modes. The system includes at least one pressure sensor for measuring a pressure inside the fuel combustor and/or a at least one fluid velocity sensor for measuring fluid velocity at the inlet pipe or at the exhaust pipe. A controller adjusts a rate of fuel supply to the pulse combustor if the measured pressure and/or the measured velocity is above a predetermined threshold value to reduce excitation of the one or more additional oscillation modes.
F02K 7/04 - Plants in which the working-fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fanControl thereof the jet being intermittent, i.e. pulse jet with resonant combustion chambers
F02K 7/06 - Plants in which the working-fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fanControl thereof the jet being intermittent, i.e. pulse jet with combustion chambers having valves
F02C 5/10 - Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the working fluid forming a resonating or oscillating gas column, i.e. the combustion chambers having no positively actuated valves, e.g. using Helmholtz effect
F02C 9/28 - Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
F02K 7/02 - Plants in which the working-fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fanControl thereof the jet being intermittent, i.e. pulse jet
F02C 5/12 - Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the combustion chambers having inlet or outlet valves, e.g. Holzwarth gas-turbine plants
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.
F02C 5/10 - Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the working fluid forming a resonating or oscillating gas column, i.e. the combustion chambers having no positively actuated valves, e.g. using Helmholtz effect
F23C 15/00 - Apparatus in which combustion takes place in pulses influenced by acoustic resonance in a gas mass
18.
Systems and methods for air-breathing wave engines for thrust production
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.
F02K 7/02 - Plants in which the working-fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fanControl thereof the jet being intermittent, i.e. pulse jet
F02K 7/067 - Plants in which the working-fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fanControl thereof the jet being intermittent, i.e. pulse jet with combustion chambers having valves having aerodynamic valves
19.
Systems and methods for improving operation of pulse combustors
A pulse combustor system for reducing noise and/or vibration levels. The system includes a pulse combustor including a combustion chamber, an inlet pipe, an exhaust pipe, and a first fuel injector for injecting fuel into the combustion chamber. The pulse combustor has a fundamental oscillation mode and one or more additional oscillation modes. The system includes at least one pressure sensor for measuring a pressure inside the fuel combustor and/or a at least one fluid velocity sensor for measuring fluid velocity at the inlet pipe or at the exhaust pipe. A controller adjusts a rate of fuel supply to the pulse combustor if the measured pressure and/or the measured velocity is above a predetermined threshold value to reduce excitation of the one or more additional oscillation modes.
F02K 7/04 - Plants in which the working-fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fanControl thereof the jet being intermittent, i.e. pulse jet with resonant combustion chambers
F02K 7/06 - Plants in which the working-fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fanControl thereof the jet being intermittent, i.e. pulse jet with combustion chambers having valves
F02C 5/10 - Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the working fluid forming a resonating or oscillating gas column, i.e. the combustion chambers having no positively actuated valves, e.g. using Helmholtz effect
F02C 9/28 - Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
F02K 7/02 - Plants in which the working-fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fanControl thereof the jet being intermittent, i.e. pulse jet
F02C 5/12 - Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the combustion chambers having inlet or outlet valves, e.g. Holzwarth gas-turbine plants
A pulse combustor system for reducing noise and/or vibration levels. The system includes a pulse combustor including a combustion chamber, an inlet pipe, an exhaust pipe, and a first fuel injector for injecting fuel into the combustion chamber. The pulse combustor has a fundamental oscillation mode and one or more additional oscillation modes. The system includes at least one pressure sensor for measuring a pressure inside the fuel combustor and/or a at least one fluid velocity sensor for measuring fluid velocity at the inlet pipe or at the exhaust pipe. A controller adjusts a rate of fuel supply to the pulse combustor if the measured pressure and/or the measured velocity is above a predetermined threshold value to reduce excitation of the one or more additional oscillation modes.
