One example of a mount for a rotorcraft comprises a structural support member, a bracket, and an elastomer. The bracket is configured to attach to a component of the rotorcraft. The component of the rotorcraft produces vibrations at a first frequency. The structural support member configured to transfer a weight of the component of a rotorcraft to an airframe of the rotorcraft. A rotor system of the aircraft vibrates the airframe of the rotorcraft at a second frequency. The elastomer is located between a structural support member and a bracket. The elastomer is configured to attenuate noise caused by the vibrations at the first frequency by isolating the vibrations at the first frequency from reaching the airframe of the rotorcraft while the airframe vibrates at the second frequency.

Electric aircraft power plants and associated methods are provided. One power plant includes an emergency power unit (EPU) for providing electric power in the event of a malfunction of a battery pack of an electric aircraft to permit the electric aircraft to make an emergency maneuver. The EPU includes a rocket engine for generating a stream of exhaust fluid using a rocket propellant, a turbine operatively connected to extract energy from the stream of exhaust fluid generated by the rocket engine, and an electric generator operatively connected to be driven by the turbine and to supply electric power to an electric motor propelling the electric aircraft.

Methods and apparatus for accelerating an aircraft fuselage boundary layer via a fan powered by an APU of the aircraft are disclosed. An example aircraft includes a fuselage, an APU, and a fan. The fuselage includes an outer skin. The APU is located within the fuselage. The fan includes a plurality of fan blades arranged circumferentially about the APU and projecting radially outward from the outer skin. The fan further includes a fan drive operatively coupled to the APU. The fan drive is configured to rotate the fan blades in response to a supply of electrical energy provided to the fan drive from the APU. The rotation of the fan blades accelerates a fuselage boundary layer traveling rearward along the outer skin from a first velocity to a second velocity greater than the first velocity.

An electricity generation and propulsion system of an aircraft is provided. The electricity generation and propulsion system includes a fuselage, a hybrid-electric power generation system operably disposed in the fuselage and a ram air turbine (RAT) device. The RAT device is coupled with the hybrid-electric power generation system and is stowable in the fuselage and deployable to an exterior of the fuselage. The RAT device is operable as a RAT when deployed into an airstream that drives rotations of the RAT from which the hybrid-electric power generation system generates electricity, and the RAT device is operable as a propulsor when deployed and driven by the hybrid-electric power generation system.

The present disclosure provides hydrogen energy conversion systems, assemblies and methods. More particularly, the present disclosure provides clean energy hydrogen-powered turbine and emergency hybrid power unit (EHPU) systems, assemblies and methods (e.g., for aircraft or the like). The present disclosure provides for a hydrogen based gas turbine coupled with a hydrogen fuel cell architecture. Both the turbine and the fuel cell (FC) can increase or decrease output. Energy storage batteries or ultra-capacitors can store amounts of emergency peak demand and/or emergency energy. This approach coupled with distributed redundant propulsors creates a safe and highly redundant clean aircraft. The fuel cell can act as emergency power and reduce turbine sizing. The batteries provide peak load capacity and additional emergency power. The fuel cell and gas turbine can keep the battery and/or the supercapacitor fully charged until required.

An engine system includes an engine duct and a tail cone arranged radially inwardly of the engine duct. The tail cone has an outer surface and an inner surface. A generator housing is arranged in the tail cone. The generator housing includes an outer surface portion spaced from the inner surface of the tail cone. A generator is mounted in the generator housing. An air duct extends from the generator, through the generator housing, through the tail cone, and through the engine duct. The air duct includes an opening exposed to an air stream passing over the engine duct.

An aircraft emergency oxygen supply device comprises an oxygen source for supplying oxygen gas; a backup electric power supply system, comprising at least one electric power storage device; and a controller for controlling the operation of the aircraft emergency oxygen supply device. The aircraft emergency oxygen supply device is electrically connectable to an aircraft electric power supply system for being supplied with electric power provided by the aircraft electric power supply system; the at least one electric power storage device is chargeable by electric power provided by the aircraft electric power supply system; and the aircraft emergency oxygen supply device is operational with electric power provided by the backup electric power supply system.

An auxiliary power unit system of an aircraft includes an auxiliary power unit (APU), a cooling unit for the APU including a heat exchanger, an air inlet in communication with the APU and/or with the cooling unit, an air inlet door unit located at the air inlet, a first duct configured to draw air into the APU and having an entrance in communication with the air inlet, a second duct having an entrance in communication with the air inlet, the heat exchanger being at least partially located within the second duct, an air turbine located within the second duct downstream of the heat exchanger, and an electrical generator coupled to the air turbine.

An aircraft includes a fuselage, a wing structure and a tail assembly, and also at least one propeller having the general shape of a ring. The propeller includes a rotor formed by an annular element having blades projecting outwardly therefrom, and a likewise annular base coaxial to the annular element and on which the annular element can turn under the action of a driver. The base is coaxial to the fuselage and integrated into the shell constituting the fuselage. The blades of the rotor are arranged outside the shell.

One example includes an aircraft retrofit system to provide a retrofitted aircraft from an original aircraft. The system includes a plurality of multi-axis vectoring nozzles configured to replace a respective plurality of original nozzles of a respective plurality of original engines of the original aircraft and empennage of the original aircraft, such that the retrofitted aircraft includes no empennage. The system also includes retrofit electronics for controlling the plurality of multi-axis vectoring nozzles to provide yaw control of the retrofitted aircraft.