A foldable multi-rotor UAV includes: a fuselage; and a plurality of arms, wherein a first end of each of the arms is connected to a side face of the fuselage through a rotating mechanism; a motor and foldable blades connected to the motor are provided on a second end of each of the arms; each of the arms rotate relatively to the fuselage through the rotating mechanism; wherein the arms comprises a front arm and a rear arm; during a folded state, the rear arm upwardly rotates towards the fuselage for folding, in such a manner that the rear arm is contained at a lower portion of the side face of the fuselage; then the front arm upwardly rotates towards the fuselage for folding, in such a manner that the front arm is contained at an upper portion of the side face of the fuselage.

A foldable multi-rotor UAV includes: a fuselage; and a plurality of arms, wherein a first end of each of the arms is connected to a side face of the fuselage through a rotating mechanism; a motor and foldable blades connected to the motor are provided on a second end of each of the arms; each of the arms rotate relatively to the fuselage through the rotating mechanism; wherein the arms comprises a front arm and a rear arm; during a folded state, the rear arm upwardly rotates towards the fuselage for folding, in such a manner that the rear arm is contained at a lower portion of the side face of the fuselage; then the front arm upwardly rotates towards the fuselage for folding, in such a manner that the front arm is contained at an upper portion of the side face of the fuselage.

A folding rotor blade assembly for a tiltrotor aircraft comprising a rotor blade pivotally connected to a grip with dual concentric blade bolts having a common central axis providing a pivotal axis inboard of an outboard bearing. A folding spindle connects the outboard bearing to an outboard tip of a yoke. The outboard bearing and the spindle fold with the rotor blade relative to the yoke. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.

A folding rotor blade assembly for a tiltrotor aircraft comprising a rotor blade pivotally connected to a grip with dual concentric blade bolts having a common central axis providing a pivotal axis inboard of an outboard bearing. A folding spindle connects the outboard bearing to an outboard tip of a yoke. The outboard bearing and the spindle fold with the rotor blade relative to the yoke. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.

A folding yoke comprising a center yoke pivotally connected to separate foldable flexible yoke arms permits rotor blade fold about a single through bolt connection inboard of a set of bearings. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.

A folding yoke comprising a center yoke pivotally connected to separate foldable flexible yoke arms permits rotor blade fold about a single through bolt connection inboard of a set of bearings. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.

There is disclosed a multicopter vertical takeoff and landing (VTOL) aircraft. The aircraft comprises am airframe with spatial design, a pilot seat, a cockpit, controls, engine units, engine compartment, control system, remote control system. The airframe consists of a central section and, at least, two peripheral sections, wherein peripheral sections can be folded up or down, or be retracted under the central section. The central section and peripheral sections of the airframe have spatial design. Each of the peripheral sections comprises at least three standard engine compartments which are connected to each other. Inside each engine compartment there is an engine unit which comprises at least one engine and at least one horizontally rotating propeller together with the control hardware. Each engine unit is an autonomous member of the distributed control system (DCS).

There is disclosed a multicopter vertical takeoff and landing (VTOL) aircraft. The aircraft comprises am airframe with spatial design, a pilot seat, a cockpit, controls, engine units, engine compartment, control system, remote control system. The airframe consists of a central section and, at least, two peripheral sections, wherein peripheral sections can be folded up or down, or be retracted under the central section. The central section and peripheral sections of the airframe have spatial design. Each of the peripheral sections comprises at least three standard engine compartments which are connected to each other. Inside each engine compartment there is an engine unit which comprises at least one engine and at least one horizontally rotating propeller together with the control hardware. Each engine unit is an autonomous member of the distributed control system (DCS).

Propeller for an aircraft engine comprising: a blade mounting associated with each blade, mounted so as to pivot on the hub according to an incident pitch axis; a pivoting link between each blade mounting and the root, allowing the blade to pivot relative to the blade mounting thereof according to a blade collapsing axis; associated with at least one of the blades, a member for controlling the collapsing/extension of the blade configured to pivot the root relative to the blade mounting according to the collapsing axis; and a passive device for synchronising the collapsing/extension of the blades, including a central synchronisation element mounted so as to rotate relative to the hub according to the propeller rotation axis, as well as a coupling element associated with each blade, including a first end mounted on the blade root and a second end mounted on the central synchronisation element.

Propeller for an aircraft engine comprising: a blade mounting associated with each blade, mounted so as to pivot on the hub according to an incident pitch axis; a pivoting link between each blade mounting and the root, allowing the blade to pivot relative to the blade mounting thereof according to a blade collapsing axis; associated with at least one of the blades, a member for controlling the collapsing/extension of the blade configured to pivot the root relative to the blade mounting according to the collapsing axis; and a passive device for synchronising the collapsing/extension of the blades, including a central synchronisation element mounted so as to rotate relative to the hub according to the propeller rotation axis, as well as a coupling element associated with each blade, including a first end mounted on the blade root and a second end mounted on the central synchronisation element.