A multi-axis amphibious copter for flying and cruising at high speeds. The multi-axis amphibious copter includes six propulsion points i.e., four propellors oriented vertically, a coaxial rotor oriented vertically, and a mini turbine thruster on the rear of the aircraft body and configured to propel the multi-axis amphibious copter forward. The multi-axis amphibious copter can land and take off vertically from congested places and can fly at cruising speeds.

An aircraft propulsion unit includes a drive unit with a static part and a rotary part which rotates a fan situated downstream from the drive unit, an assembly of fixed blades situated downstream from the fan, and a nacelle in which the fan and the assembly of fixed blades are accommodated. The propulsion unit also includes an assembly of at least two coaxial shafts, wherein a fan shaft connects the fan to the rotary part, and a stator blading shaft connecting the assembly of fixed blades to the static part extends concentrically, and for at least part of its length in the interior of the fan shaft. This rigid and compact configuration limits the variations of distance between the end of the fan blades and a fan housing situated in the inner duct of the nacelle.

An aircraft propulsion unit includes a drive unit with a static part and a rotary part which rotates a fan situated downstream from the drive unit, an assembly of fixed blades situated downstream from the fan, and a nacelle in which the fan and the assembly of fixed blades are accommodated. The propulsion unit also includes an assembly of at least two coaxial shafts, wherein a fan shaft connects the fan to the rotary part, and a stator blading shaft connecting the assembly of fixed blades to the static part extends concentrically, and for at least part of its length in the interior of the fan shaft. This rigid and compact configuration limits the variations of distance between the end of the fan blades and a fan housing situated in the inner duct of the nacelle.

A power system for an aircraft engine provides rotational drive to propeller driven and turbofan jet engine powered aircraft by use of a propeller or fan drive motor. Electrical power is provided to the drive motor by a high efficiency electrical power generator with reduced electromagnetic drag or reverse torque. The electric generator utilizes a solid state rotor that does not rotate which allows for power generation without reverse torque or the usual energy required to rotate the rotor inside the stator of the generator. Only the magnetic poles of the disclosed rotor rotate to generate the power. The fan blades of the turbofan jet engine are driven by the electric drive motor in which the rotor is a part of the fan as well as the drive from the high pressure turbine.

A power system for an aircraft engine provides rotational drive to propeller driven and turbofan jet engine powered aircraft by use of a propeller or fan drive motor. Electrical power is provided to the drive motor by a high efficiency electrical power generator with reduced electromagnetic drag or reverse torque. The electric generator utilizes a solid state rotor that does not rotate which allows for power generation without reverse torque or the usual energy required to rotate the rotor inside the stator of the generator. Only the magnetic poles of the disclosed rotor rotate to generate the power. The fan blades of the turbofan jet engine are driven by the electric drive motor in which the rotor is a part of the fan as well as the drive from the high pressure turbine.

An engine vibration isolation subframe for aircraft includes a forward frame and a forward beam connected to the forward frame. The forward beam includes a first end configured to connect to a first engine and a second end configured to connect to a second engine. An aft frame is disposed aft of the forward frame and includes a first aft beam connected to the aft frame and the first engine and a second aft beam connected to the aft frame and the second engine, where the second aft beam is disposed substantially opposite the first aft beam. At least one forward isolator assembly is connected to the forward frame and at least one aft isolator assembly is connected to the aft frame.

An engine vibration isolation subframe for aircraft includes a forward frame and a forward beam connected to the forward frame. The forward beam includes a first end configured to connect to a first engine and a second end configured to connect to a second engine. An aft frame is disposed aft of the forward frame and includes a first aft beam connected to the aft frame and the first engine and a second aft beam connected to the aft frame and the second engine, where the second aft beam is disposed substantially opposite the first aft beam. At least one forward isolator assembly is connected to the forward frame and at least one aft isolator assembly is connected to the aft frame.

A latch mechanism configured to engage a mating pin is disclosed. In various embodiments, the latch mechanism includes a latch frame; a latch arm pivotally mounted to the latch frame at a pivot axis; and a bias member configured to apply a load to the latch arm in a transverse direction generally perpendicular to the pivot axis and to bias the latch arm from rotating in a first rotational direction about the pivot axis and from rotating away from the mating pin.

An aircraft defines a longitudinal direction and includes a fuselage extending between a forward end and an aft end along the longitudinal direction of the aircraft. An aft engine is mounted to the aft end of the fuselage. The aft engine further includes a nacelle including a forward section. An airflow duct extends at least partially through the nacelle of the aft engine and defines an outlet on the forward section of the nacelle for providing an airflow to the forward section of the nacelle.

An aircraft defines a longitudinal direction and includes a fuselage extending between a forward end and an aft end along the longitudinal direction of the aircraft. An aft engine is mounted to the aft end of the fuselage. The aft engine further includes a nacelle including a forward section. An airflow duct extends at least partially through the nacelle of the aft engine and defines an outlet on the forward section of the nacelle for providing an airflow to the forward section of the nacelle.