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 method is provided. An airship is maneuvered to a desired location and oriented with the thruster such that ambient wind is traveling in a direction that is substantially parallel to the longitudinal axis of the fuselage. The airflow from the ambient wind is straightened with the flow straightener to generate a substantially laminar flow. The turbine is engaged with the airflow generated by the ambient wind to generate electricity, and the electricity generated by the turbine is rectified with the rectifier and stored in the storage array.

A method is provided. An airship is maneuvered to a desired location and oriented with the thruster such that ambient wind is traveling in a direction that is substantially parallel to the longitudinal axis of the fuselage. The airflow from the ambient wind is straightened with the flow straightener to generate a substantially laminar flow. The turbine is engaged with the airflow generated by the ambient wind to generate electricity, and the electricity generated by the turbine is rectified with the rectifier and stored in the storage array.

A method is provided. An airship is maneuvered to a desired location and oriented with the thruster such that ambient wind is traveling in a direction that is substantially parallel to the longitudinal axis of the fuselage. The airflow from the ambient wind is straightened with the flow straightener to generate a substantially laminar flow. The turbine is engaged with the airflow generated by the ambient wind to generate electricity, and the electricity generated by the turbine is rectified with the rectifier and stored in the storage array.

A method is provided. An airship is maneuvered to a desired location and oriented with the thruster such that ambient wind is traveling in a direction that is substantially parallel to the longitudinal axis of the fuselage. The airflow from the ambient wind is straightened with the flow straightener to generate a substantially laminar flow. The turbine is engaged with the airflow generated by the ambient wind to generate electricity, and the electricity generated by the turbine is rectified with the rectifier and stored in the storage array.

A method for supporting aerial operation over a surface includes obtaining a three-dimensional (3D) representation of the surface; converting the 3D representation of the surface to a two-dimensional (2D) representation of the surface; obtaining a 2D flight path of the aircraft based on the 2D representation of the surface; converting the 2D flight path to a 3D flight path including location coordinates; and controlling the aircraft to conduct a flight mission following the 3D flight path.

A method for supporting aerial operation over a surface includes obtaining a three-dimensional (3D) representation of the surface; converting the 3D representation of the surface to a two-dimensional (2D) representation of the surface; obtaining a 2D flight path of the aircraft based on the 2D representation of the surface; converting the 2D flight path to a 3D flight path including location coordinates; and controlling the aircraft to conduct a flight mission following the 3D flight path.

A heat exchanger system for a propulsion system inlet duct includes a heat exchanger assembly that is disposed within an inlet duct assembly. The heat exchanger includes a heat exchanger with a front facing area that is greater than an area of the inlet duct that is transverse to a longitudinal length of the inlet duct.

A propulsion system of an unmanned aerial vehicle (UAV) includes a first and a second propulsion devices each including a rotor mount assembly including a base and a lock structure arranged at the base. The lock structure includes a protrusion protruding from the base. An angle between an extension direction of the protrusion and a rotation plane of the rotor mount assembly has an absolute value larger than 0° and smaller than 90°. Each of the first and second propulsion devices further includes a rotor blade assembly configured to be locked to the corresponding rotor mount assembly by the corresponding lock structure. The rotor mount assembly of the first propulsion device is configured to not allow the rotor blade assembly of the second propulsion device to be assembled to the rotor mount assembly of the first propulsion device.

A hybrid wing aircraft has an engine embedded into a body of the hybrid wing aircraft. The embedded engine has a fan that is received within a nacelle. The body of the aircraft provides a boundary layer over a circumferential portion of a fan. A system delivers additional air to correct fan stability issues raised by the boundary layer.