A system includes an inboard tiltrotor subsystem and an outboard tiltrotor subsystem. The inboard tiltrotor subsystem includes an inboard pylon, an inboard tiltrotor, and a single and non-redundant drivetrain. The outboard tiltrotor subsystem includes an outboard pylon that is coupled to a wing and an outboard tiltrotor. The outboard tiltrotor has a range of motion and is coupled to the wing via the outboard pylon, such that the outboard tiltrotor is aft of the wing. The outboard tiltrotor subsystem further includes a redundant drivetrain (which has a plurality of motors and a plurality of motor controllers) that drives one or more blades and the one or more blades.

Fixed-wing short-takeoff-and-landing aircraft and related methods. The aircraft comprise an airframe comprising a rear wing assembly and a forward wing assembly positioned forward of the rear wing assembly, a rear plurality of blowing rotor assemblies operatively coupled to the rear wing assembly that are configured to blow air across the rear wing assembly to induce lift in the rear wing assembly, and a forward plurality of blowing rotor assemblies that are operatively coupled to the forward wing assembly and configured to blow air across the forward wing assembly to induce lift in the forward wing assembly. The methods comprise inducing lift in a forward wing assembly by blowing air across the forward wing assembly with a forward plurality of blowing rotor assemblies and inducing lift in a rear wing assembly by blowing air across a rear wing assembly with a rear plurality of blowing rotor assemblies.

A compound aircraft embodies an array of rotors for vertical flight positioned on support booms and wing elements for cruise flight coupled to a central fuselage housing avionics and a pusher propeller for forward propulsion. The aircraft accommodates a cargo-carrying container with mating of the surfaces between container and fuselage and latching mechanisms for attaching and detaching the container and vehicle.

A compound aircraft embodies an array of rotors for vertical flight positioned on support booms and wing elements for cruise flight coupled to a central fuselage housing avionics and a pusher propeller for forward propulsion. The aircraft accommodates a cargo-carrying container with mating of the surfaces between container and fuselage and latching mechanisms for attaching and detaching the container and vehicle.

An aircraft having a frame assembly that supports a compressor having an outer shell that defines front and rear nozzle ports with rotatable nozzles for selectable vertical or horizontal thrust. The inner shell and the outer shell define an intake gap therebetween such as an annulus. A first fan unit within the inner shell and is configured to exhaust air through the front nozzle ports. A second fan unit within the outer shell intakes air through the intake gap and exhausts air through the rear nozzle ports. The fan units are preferably connected to one another via a drive shaft that is surrounded by a streamlining tube. The fan units each include a plurality of fans having stators therebetween. The stators have a plurality of stator arms with a wing structure pivotally attached to the trailing edge for angling air flow from a front to a rear fan.

The invention relates to the field of aeronautical engineering, specifically to convertiplanes. A convertiplane comprises a fuselage, a control system, aerodynamic outer wings with aerodynamic control surfaces, an all-moving foreplane with aerodynamic control surfaces, a tail plane, and propulsion systems with propellers. The propulsion systems with propellers are arranged rotatably on tips of the foreplane and on the tail plane. The convertiplane is designed to permit the aerodynamic centre of pressure and the resultant thrust vector to coincide. The convertiplane is designed to permit the mutual dynamic and static scalar control thereof by operating the aerodynamic control surfaces and thrust vectoring of each of the propulsion systems. The propulsion systems arranged on the tips of the foreplane are capable of counterrotation of the propeller and are capable of dynamically displacing the centre of pressure and are also capable of displacing the axis of rotation of the front propulsion systems in the ZX plane. The propulsion systems have an axial degree of freedom, and are also capable of independently of one another controlling thrust vectoring and revolutions by controlling the pitch angle of the blades and the diameter thereof.

An aircraft includes a structure exhibiting a median plane XZ and including a fuselage, a fixed vertical stabilizer at the rear of the fuselage, an adjustable horizontal stabilizer rotatably mounted about a horizontal axis on a first section of the structure, and extending on either side of the median plane XZ, and at the rear, two elevators mounted rotatably about a horizontal axis on a second section of the structure on either side of the median plane XZ independently of the adjustable horizontal stabilizer. In an aircraft of this kind, the elevators no longer have any impact on the adjustable horizontal stabilizer, which allows, among other things, the dimensions of the adjustable horizontal stabilizer, and also of the actuator operating them, to be reduced.

An aircraft includes a structure exhibiting a median plane XZ and including a fuselage, a fixed vertical stabilizer at the rear of the fuselage, an adjustable horizontal stabilizer rotatably mounted about a horizontal axis on a first section of the structure, and extending on either side of the median plane XZ, and at the rear, two elevators mounted rotatably about a horizontal axis on a second section of the structure on either side of the median plane XZ independently of the adjustable horizontal stabilizer. In an aircraft of this kind, the elevators no longer have any impact on the adjustable horizontal stabilizer, which allows, among other things, the dimensions of the adjustable horizontal stabilizer, and also of the actuator operating them, to be reduced.

A long-distance drone having a main body, a left hind wing, a right hind wing, a left forewing, and a right forewing. There is a left linear support connecting the left forewing to the left hind wing, and a right linear support connecting the right forewing to the right hind wing. A plurality of propellers are disposed on the left and the right linear supports.