An assembly for an aircraft having a propeller, including a wheel well for a retracted landing gear, first and second cooling ducts; and an engine assembly having an engine shaft configured for driving engagement with the propeller, the engine assembly including a coolant circulation system for circulation of a liquid coolant, a lubricant circulation system for circulation of a lubricant, a first heat exchanger in fluid communication with at least the coolant circulation system, and a second heat exchanger in fluid communication with at least the lubricant circulation system. Each heat exchanger is positioned and configured for receiving a cooling airflow from the respective cooling duct. The wheel well is located between the heat exchangers. A method of cooling a lubricant and a liquid coolant of an engine assembly is also discussed.

A heavy payload, autonomous UAV able to deliver supply by way of airdrop with more precision and at a lower cost. The UAV is equipped with two movable wing systems that rotate from a stowed position to a deployed position upon jettison of the UAV from a mothership. The UAV can be controlled remotely or it can operate autonomously and the movable wings can include ailerons to effectuate flight control of the UAV. The UAV can be reusable or can be an expendable UAV.

A wall covering panel for a nose of an aircraft. The panel comprises a rigid carrying framework preferably having an alveolar structure obtained by 3-D printing, a decor carried by the carrying framework and an acoustically and thermally insulating padding fixed to the carrying framework, and also attachments for fixing the carrying framework to the primary structure of the aircraft. Preferably, the panel also integrates systems, such as electrical route portions or ventilation route portions that traverse the panel from one side to the other or lead to an outlet equipment item also integrated in the panel. Only the carrying structure of the panel, which carries the decor, the insulating padding and any route portions and equipment items, is fixed to the primary structure of the aircraft. The number of attachments is low; the kitting-out and the finishing of the nose of the aircraft are greatly simplified.

A linking part for an aircraft is disclosed having an elongated section including an internal longitudinal seat and a tenon mounted in the seat. The tenon includes a linking element at a free longitudinal end thereof and configured in a retracted position in which the tenon is fully inserted in the seat and does not create an obstruction, enabling the linking part to be easily moved towards the support element, or a deployed position (P2) in which the free longitudinal end of the tenon is outside the seat and is able to be linked using the linking element to the support element, thereby enabling a link to be made simply and quickly.

An electrically powered STOL aircraft having dedicated motors energized to deploy movable landing gear driven to propel short takeoffs and to actively rotate downwardly to engage the runway surface as the aircraft approaches touchdown on landing. The front and rear landing gear, or both, may be powered and actuated in the landing process with braking to shorten the landing distance, each driven landing gear wheel having a dedicated electric motor and coaxial brake.

An electrically powered STOL aircraft having dedicated motors energized to deploy movable landing gear driven to propel short takeoffs and to actively rotate downwardly to engage the runway surface as the aircraft approaches touchdown on landing. The front and rear landing gear, or both, may be powered and actuated in the landing process with braking to shorten the landing distance, each driven landing gear wheel having a dedicated electric motor and coaxial brake. The landing gear modules are configured and controllable to differentially deploy downwardly so as to enable countersteering during taxi maneuvers and turns.

A front landing gear module for an aircraft is disclosed including an open box provided with at least one door and containing a deployable front landing gear. The module may be a one-piece module and also including an attachment system intended to attach it on the aircraft, which allows the module to be manufactured in advance, before it is integrated as an individual assembly into the structure of the fuselage of the aircraft.

An aircraft has a substantially cylindrical body having a longitudinal axis, a cockpit, counter-rotating propellers of an overall diameter substantially greater than a maximum diameter of the body, DC motors powering the propeller sets, a battery compartment at a lower extremity of the cylindrical body, enclosing a DC battery, fixes wings extending a substantial distance away from the cylindrical body in a first direction, a rudder in a plane parallel to the axis of the cylindrical body, landing struts extending from a lower and outer extremity of each wing and of the providing a support structure for the aircraft; and controls operable to move the rudder and the wing flaps, and to manage power and rpm of the counter rotating propellers. The aircraft may lift vertically in hovering flight, transition to level flight, and return to hovering flight to land again.

An anterior zone of an aircraft, having a fuselage with frames, includes a cockpit, arranged partly above a front landing gear compartment, and a service area. The floor includes: a rear main crossbeam which extends in the plane of a frame situated in the service area and which is fixed to said frame, a port main spar and a starboard main spar, the rear ends of which are fixed to the rear main crossbeam, one or more secondary crossbeams, fixed to the port and starboard main spars, and one or more auxiliary spars. The number of crossbeam/frame attachments is reduced. The dimensioning of the principal beams of the floor is optimised; the result thereof is a weight saving.

A fixed-wing cargo aircraft having a kinked fuselage to extend the useable length of a continuous interior cargo bay while still meeting a tailstrike requirement is disclosed. The fuselage defines a continuous interior cargo bay along a majority of its length and a pitch axis about which the cargo aircraft rotates during takeoff while still on the ground. The fuselage includes a forward portion defining longitudinal-lateral plane of the cargo aircraft an aft portion extending aft from the pitch axis to the aft end and containing an aft region of the continuous interior cargo bay that extends along a majority of a length of the aft portion. The aft portion has a centerline extending above the forward upper surface of the aircraft.