Abstract: A hybrid propulsion aircraft is described having a distributed electric propulsion system. The distributed electric propulsion system includes a turbo shaft engine that drives one or more generators through a gearbox. The generator provides AC power to a plurality of ducted fans (each being driven by an electric motor). The ducted fans may be integrated with the hybrid propulsion aircraft's wings. The wings can be pivotally attached to the fuselage, thereby allowing for vertical take-off and landing. The design of the hybrid propulsion aircraft mitigates undesirable transient behavior traditionally encountered during a transition from vertical flight to horizontal flight. Moreover, the hybrid propulsion aircraft offers a fast, constant-altitude transition, without requiring a climb or dive to transition. It also offers increased efficiency in both hover and forward flight versus other VTOL aircraft and a higher forward max speed than traditional rotorcraft.

Abstract: A hybrid propulsion aircraft is described having a distributed electric propulsion system. The distributed electric propulsion system includes a turbo shaft engine that drives one or more generators through a gearbox. The generator provides AC power to a plurality of ducted fans (each being driven by an electric motor). The ducted fans may be integrated with the hybrid propulsion aircraft's wings. The wings can be pivotally attached to the fuselage, thereby allowing for vertical take-off and landing. The design of the hybrid propulsion aircraft mitigates undesirable transient behavior traditionally encountered during a transition from vertical flight to horizontal flight. Moreover, the hybrid propulsion aircraft offers a fast, constant-altitude transition, without requiring a climb or dive to transition. It also offers increased efficiency in both hover and forward flight versus other VTOL aircraft and a higher forward max speed than traditional rotorcraft.

Abstract: An engine for use in operating an aircraft is disclosed, the engine comprising a decomposition chamber configured to decompose into at least one combustible constituent element a first chemically unstable substance in the presence of a catalyst, wherein the decomposition of the first chemically unstable substance releases a first amount of heat; a first turbine configured to accept the constituent elements and the first amount of heat from the decomposition chamber and thereby rotate; a compressor rotationally connected to the first turbine, and configured to compress air when the first turbine rotates; and a combustion chamber configured to accept the compressed air and constituent elements and combust the combination, substantially regardless of an altitude above sea level and ambient air pressure, and output the combustion products into a power turbine, causing it to rotate, whereby the rotation of the first turbine and/or the power turbine rotate a propeller rotationally coupled to the first and power tur

Abstract: A vibration isolation engine mount system and method for ducted fan aircraft, such as ducted fan vertical takeoff and landing (VTOL) aircraft, includes an engine for driving the ducted fan. The system includes an engine support structure for supporting the engine within the ducted fan. A rotor of the ducted fan is coupled to an engine shaft of the engine via a rotor hub. The system includes a plurality of vibration isolators configured to mount the engine to the engine support structure. Each of the plurality of vibration isolators is substantially concentrically oriented along a surface of a sphere. A center of the sphere is located at a center of the rotor hub.

Abstract: An engine for use in operating an aircraft is disclosed, the engine comprising a decomposition chamber configured to decompose into at least one combustible constituent element a first chemically unstable substance in the presence of a catalyst, wherein the decomposition of the first chemically unstable substance releases a first amount of heat; a first turbine configured to accept the constituent elements and the first amount of heat from the decomposition chamber and thereby rotate; a compressor rotationally connected to the first turbine, and configured to compress air when the first turbine rotates; and a combustion chamber configured to accept the compressed air and constituent elements and combust the combination, substantially regardless of an altitude above sea level and ambient air pressure, and output the combustion products into a power turbine, causing it to rotate, whereby the rotation of the first turbine and/or the power turbine rotate a propeller rotationally coupled to the first and power tur

Abstract: An aircraft including a ducted fan and an engine for driving the ducted fan includes a plurality of vanes movably mounted to the aircraft at a substantially rectangular exhaust end of the aircraft. Each of the plurality of vanes is substantially rectangular or square. The plurality of vanes are configured to alter an exit area of the exhaust end. The aircraft includes a sensor circuit for detecting a RPM of the engine and for outputting a RPM signal. The aircraft includes a control circuit coupled to the sensor circuit and the plurality of vanes. The control circuit is configured to actuate the plurality of vanes to alter the exit area of the exhaust end to vary a pressure load on the ducted fan to control the RPM of the engine in response to the RPM signal.

Abstract: A vibration isolation engine mount system and method for ducted fan aircraft, such as ducted fan vertical takeoff and landing (VTOL) aircraft, includes an engine for driving the ducted fan. The system includes an engine support structure for supporting the engine within the ducted fan. A rotor of the ducted fan is coupled to an engine shaft of the engine via a rotor hub. The system includes a plurality of vibration isolators configured to mount the engine to the engine support structure. Each of the plurality of vibration isolators is substantially concentrically oriented along a surface of a sphere. A center of the sphere is located at a center of the rotor hub.

Abstract: An aircraft including a ducted fan and an engine for driving the ducted fan includes a plurality of vanes movably mounted to the aircraft at a substantially rectangular exhaust end of the aircraft. Each of the plurality of vanes is substantially rectangular or square. The plurality of vanes are configured to alter an exit area of the exhaust end. The aircraft includes a sensor circuit for detecting a RPM of the engine and for outputting a RPM signal. The aircraft includes a control circuit coupled to the sensor circuit and the plurality of vanes. The control circuit is configured to actuate the plurality of vanes to alter the exit area of the exhaust end to vary a pressure load on the ducted fan to control the RPM of the engine in response to the RPM signal.