An aircraft power plant comprising a monolithic powertrain block with a composition of individual modules grouped by functionality, further comprising electric motors, high power motor controllers, logical control electronics (drivetrain computer), cooling system, hydraulics system, low voltage power system, and high voltage power source, wherein the engine mounting frame of the airplane is the main structure for mounting all individual modules.

An assembly for mounting an aircraft engine to an aircraft includes an engine casing flange having a first annular wall extending radially to terminate at an annular rim. A second flange of an additional engine component mounted aft of the engine casing includes a second annular wall. An aft mount bracket has an annular body extending uninterrupted about the center axis and a spigot extending axially from the annular body, the spigot extending circumferentially about an entire circumference of the annular body. The aft mount bracket is axially disposed between the engine casing flange and the additional engine component, with corresponding holes in the first annular wall, second annular wall and aft mount bracket being circumferentially aligned, and the spigot radially abutting the annular rim of the engine casing flange.

An assembly for mounting an aircraft engine to an aircraft includes an engine casing flange having a first annular wall extending radially to terminate at an annular rim. A second flange of an additional engine component mounted aft of the engine casing includes a second annular wall. An aft mount bracket has an annular body extending uninterrupted about the center axis and a spigot extending axially from the annular body, the spigot extending circumferentially about an entire circumference of the annular body. The aft mount bracket is axially disposed between the engine casing flange and the additional engine component, with corresponding holes in the first annular wall, second annular wall and aft mount bracket being circumferentially aligned, and the spigot radially abutting the annular rim of the engine casing flange.

An aircraft includes a central wing accommodating passengers and/or freight and two lateral wings that pivot on the central wing about respective axes of rotation. The various wings obey the following geometric characteristics: 0.3×Long<L.sub.arg<L.sub.ong, 0.11×L.sub.ong<H.sub.aut<0.25×L.sub.ong, E.sub.nv>1.4×L.sub.ong, wherein L.sub.arg being the distance between the two axes, L.sub.ong being the length of the central wing, H.sub.aut being the height of the central wing, E.sub.nv being the wingspan of the aircraft. The axes of rotation are inclined by an angle relative to the vertical axis of the aircraft such that the lateral pivot from rear to front and vice versa so as to come closer to, or deploy on either side from, the fuselage.

An aircraft includes a central wing accommodating passengers and/or freight and two lateral wings that pivot on the central wing about respective axes of rotation. The various wings obey the following geometric characteristics: 0.3×Long<L.sub.arg<L.sub.ong, 0.11×L.sub.ong<H.sub.aut<0.25×L.sub.ong, E.sub.nv>1.4×L.sub.ong, wherein L.sub.arg being the distance between the two axes, L.sub.ong being the length of the central wing, H.sub.aut being the height of the central wing, E.sub.nv being the wingspan of the aircraft. The axes of rotation are inclined by an angle relative to the vertical axis of the aircraft such that the lateral pivot from rear to front and vice versa so as to come closer to, or deploy on either side from, the fuselage.

An aircraft assembly including a wing component and an engine mounting pylon component. The wing component has three fastening locations arranged in a triangle and a plane. The engine mounting pylon component is connected to the wing component by three tension fasteners, wherein each of the tension fasteners passes through a different one of the fastening locations. The wing component comprises three first spherical surfaces positioned such that the center of each first spherical surface is at a different one of the fastening locations. The engine mounting pylon component comprises three second spherical surfaces having equal and opposite curvature to the first spherical surfaces. Each of the second spherical surfaces is in contact with a different one of the first spherical surfaces.

An aircraft assembly including a wing component and an engine mounting pylon component. The wing component has three fastening locations arranged in a triangle and a plane. The engine mounting pylon component is connected to the wing component by three tension fasteners, wherein each of the tension fasteners passes through a different one of the fastening locations. The wing component comprises three first spherical surfaces positioned such that the center of each first spherical surface is at a different one of the fastening locations. The engine mounting pylon component comprises three second spherical surfaces having equal and opposite curvature to the first spherical surfaces. Each of the second spherical surfaces is in contact with a different one of the first spherical surfaces.

A lighter than air airship (1) comprising a gas-filled flexible hull (2) which is elongate with a longitudinal axis (1′) and with a front end (4) and a rear end (5), wherein a harness-structure (3) is abutting an outer side of the hull (2) and not perturbing the hull and not extending through the hull, the harness-structure (3) is made of a bendable material and carries a propeller engine (10) for forward thrust of the airship (1), rechargeable batteries (11) for providing electrical power to the propeller engine (10), and a solar panel for providing electrical power to recharge the batteries (11).

A lighter than air airship (1) comprising a gas-filled flexible hull (2) which is elongate with a longitudinal axis (1′) and with a front end (4) and a rear end (5), wherein a harness-structure (3) is abutting an outer side of the hull (2) and not perturbing the hull and not extending through the hull, the harness-structure (3) is made of a bendable material and carries a propeller engine (10) for forward thrust of the airship (1), rechargeable batteries (11) for providing electrical power to the propeller engine (10), and a solar panel for providing electrical power to recharge the batteries (11).

An aircraft having a vertical takeoff and landing fight mode and a forward flight mode. The aircraft includes an airframe and a versatile propulsion system attached to the airframe. The versatile propulsion system includes a plurality of propulsion assemblies. A flight control system is operable to independently control the propulsion assemblies. The propulsion assemblies are interchangeably attachable to the airframe such that the aircraft has a liquid fuel flight mode and an electric flight mode. In the liquid fuel flight mode, energy is provided to each of the propulsion assemblies from a liquid fuel. In the electric flight mode, energy is provided to each of the propulsion assemblies from an electric power source.