An engine system with a multi-gas-generator, tip-turbine driven lift fan with pressurized air circulation control for use on vertical and short-take-off and landing (V/STOL) aircraft is disclosed. Gas generators located around the periphery of the fan drive the fan through action on a fan blade-tip turbine or provide compressed gas (hot or cold) to circulation control devices. Variable pitch fan blades improve part-power cruise performance. Enclosed in a nacelle, the engine employs circulation control to enhance V/STOL performance. In some embodiments, a core cruise turbine gas generator mounted in the center of the fan duct powers the fan during cruise mode. In some hybrid gas and electric power embodiments, the core cruise gas generator is replaced by an electric motor that draws power from a battery in the fuselage. The battery may be charged by an electric generator driven by a gas generator around the periphery of the fan.

Sounds are generated by an aerial vehicle during operation. For example, the motors and propellers of an aerial vehicle generate sounds during operation. Disclosed are systems, methods, and apparatus for actively adjusting the position and/or configuration of one or more propeller blades of a propulsion mechanism to generate different sounds and/or lifting forces from the propulsion mechanism.

Sounds are generated by an aerial vehicle during operation. For example, the motors and propellers of an aerial vehicle generate sounds during operation. Disclosed are systems, methods, and apparatus for actively adjusting the position and/or configuration of one or more propeller blades of a propulsion mechanism to generate different sounds and/or lifting forces from the propulsion mechanism.

A method and system are provided for coordinating a propeller with a controller module including a machine having a controller module and a propeller mounted to a propeller shaft at a hub. The shaft is arranged to be received in the machine, and a sensor is mounted to the machine, connected to the electronic controller module, and configured to sense the propeller when the propeller shaft is received in the machine.

A method and system are provided for coordinating a propeller with a controller module including a machine having a controller module and a propeller mounted to a propeller shaft at a hub. The shaft is arranged to be received in the machine, and a sensor is mounted to the machine, connected to the electronic controller module, and configured to sense the propeller when the propeller shaft is received in the machine.

An aircraft includes a wing having a first upstream longeron and a second downstream longeron extending in the direction of the span of said wing, and at least one propulsion unit supported by the wing. The propulsion unit includes a turboprop engine and a propeller. The propeller includes an external annular casing fixed to a suction surface of the wing, and at least to the first upstream longeron via at least one first and second fastener.

A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one fore conduit and at least one tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the fore conduit, coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element is coupled to the tail portion. A surface of the primary airfoil element is located directly downstream of the first and second fore ejectors such that the fluid from the first and second fore ejectors flows over the such surface.

A ducted-rotor aircraft includes a fuselage, one or more ducts, and a spindle that rotatably couples the one or more ducts to the fuselage. Each duct includes a hub that is configured to support a rotor, a plurality of stators that are coupled to the hub, a duct ring that is coupled to the plurality of stators, and a fitting that is coupled to a first stator of the plurality of stators. The fitting has a tubular collar that defines a first aperture that extends through the fitting. The collar is configured to receive a portion of the spindle. The first stator includes a rib that is spaced inward from the fitting and that defines a second aperture that is aligned with the first aperture and that is configured to receive an end of the spindle.

Locking device, propeller, and aerial vehicle are provided. An exemplary propeller includes a blade; and a locking part, configured for locking the blade to a driving shaft. The locking part includes a fastening portion and a pressing portion. The pressing portion includes a pressing end, an abutting end including an accommodating hole, and an abutting part configured within the accommodating hole for abutting against the fastening portion. The fastening portion is accommodable within the accommodating hole of the pressing portion. The pressing portion of the locking part is slidably connected with the blade. A portion of the driving shaft protrudes into the accommodating hole of the pressing portion. The fastening portion is abutted against the abutting part of the pressing portion and engaged with the driving shaft to lock the driving shaft on the blade.

Locking device, propeller, and aerial vehicle are provided. An exemplary propeller includes a blade; and a locking part, configured for locking the blade to a driving shaft. The locking part includes a fastening portion and a pressing portion. The pressing portion includes a pressing end, an abutting end including an accommodating hole, and an abutting part configured within the accommodating hole for abutting against the fastening portion. The fastening portion is accommodable within the accommodating hole of the pressing portion. The pressing portion of the locking part is slidably connected with the blade. A portion of the driving shaft protrudes into the accommodating hole of the pressing portion. The fastening portion is abutted against the abutting part of the pressing portion and engaged with the driving shaft to lock the driving shaft on the blade.