A folding/unfolding device for folding/unfolding a tail boom, the device being arranged in association with a rear power transmission shaft of a tail rotor of the rotorcraft, the folding/unfolding device comprising pivot means enabling a movable portion of the tail boom to move in pivoting relative to a stationary portion of the tail boom, the relative pivoting movement being performed between two distinct extreme positions, namely an unfolded, working position enabling the rear power transmission shaft to transmit driving torque to the tail rotor, and a folded, rest position enabling the overall length of the rotorcraft to be reduced. According to the invention, the folding/unfolding device includes motor-driven decoupling/coupling means for mechanically decoupling/coupling together two portions of a single rear power transmission shaft before/after the relative pivoting movement of the movable portion of the tail boom relative to the stationary portion.

The present application discloses an aircraft. The present application discloses a method of assembling or disassembling an aircraft. The assembly method includes mounting a first engine nacelle to a first wing, mounting a second engine nacelle to a second wing, causing the first wing to be extended relative to a fuselage mount, causing the second wing to be extended relative to the fuselage mount, and mounting the fuselage to the fuselage mount.

A folding mechanism for a tail located on a helicopter has a front region on the tail, a rear region connected to the front region can be folded around the axis on which it is supported, a first shaft located on the front region and a second shaft located on the rear region enables power to be transmitted to the tail rotor during the flight movement of the helicopter, a first coupling and a second coupling located on the first shaft with a threaded form, a first hub located on the first shaft surrounding the first coupling all around and is form-fitting to the first coupling to enable the first coupling to make at least a partial spherical rotational movement, and a second hub located on the second shaft is arranged opposite the second coupling and being form-fitting to the second coupling with a dampener located on the front region.

An apparatus includes a frame and a plurality of propellers coupled to the frame and configured to produce sufficient thrust to allow the apparatus to hover. Each propeller from the plurality of propellers having a horizontally oriented blade and a first propellor from the plurality of propellors overlapping a second propellor from the plurality of propellers in a vertical plane.

A tail located on a helicopter has a front area located on the tail, a rear area connected to the front area in a foldable manner around the axis, and a first shaft at the front area and a second shaft at the rear area allows power transfer to the tail rotor throughout the flight movement of the helicopter. A first coupling and a second coupling are located on the first shaft in a gear form. A first hub on the first shaft surrounds the first coupling and is form-compatible with the first coupling to allow the first coupling to perform at least partially a spherical rotational movement, and a second hub form-compatible with the second coupling located on the second shaft opposite the second coupling.

A helicopter tail folding mechanism for a tail located on the helicopter has a front region located on the tail, a rear region connected to the front region to make a folding movement around the axis on which it is supported, a first shaft located on the front region and a second shaft located on the rear region enables power to be transmitted to the tail rotor during the flight movement of the helicopter, a first coupling and a second coupling located on the first shaft both with a threaded form, a first hub located on the first shaft surrounding the first coupling all around that is form-fitting to the first coupling to enable the first coupling to make at least a partial spherical rotational movement, and a second hub located on the second shaft to be arranged opposite to the second coupling and being form-fitting to the second coupling.

An apparatus includes a frame and a plurality of propellers coupled to the frame and configured to produce sufficient thrust to allow the apparatus to hover. Each propeller from the plurality of propellers having a horizontally oriented blade and a first propellor from the plurality of propellors overlapping a second propellor from the plurality of propellers in a vertical plane.

A rotary wing aircraft comprising a fuselage, a cabin volume enclosed by the fuselage, a main rotor arranged above the fuselage, a tail rotor mounted on a tail, the tail being attached to a rear part of the fuselage supporting the tail at its rear end, whereas the tail includes two beam boom elements, one element extending at the port side and the other element extending at the starboard side of the rotary wing aircraft, the front root end of each element being hinged to the corresponding lateral side of the fuselage, and both elements being canted with respect to the longitudinal axis of the rotary wing aircraft so as to be interconnected to each other at the rear portion of the tail.

A vehicle capable of being converted between a flying condition and an automotive riding condition. The vehicle has a telescopically extendable tail having a first tubular tail segment and a second tail segment disposed axially slideable within the first tubular tail segment. The tail is provided with at least two form-closing coupling members located at an axial distance from each other for providing a force-transferring coupling between the second tail segment and the first tubular tail segment in the extended state of the second tail segment, each of the form-closing coupling members capable of transferring torque and transverse forces, and each of the form-closing coupling members coming into engagement by axial displacement of the second tail segment in the outward direction.

The present application discloses an aircraft. The aircraft comprises a first wing and a second wing, a fuselage to which the first wing and the second wing are mounted, a first engine operatively mounted to the first wing, and a second engine operatively mounted to the second wing. The aircraft is configured to vertically take-off and land. The first engine and the second engine are used for both (i) vertical take-off and landing, and (ii) horizontal flight.