Abstract: An aircraft rotor assembly has a central yoke and a plurality of rotor blades coupled to the yoke for rotation with the yoke about an axis, each blade having a Lock number of approximately 5 or greater. A lead-lag pivot for each blade is a radial distance from the axis and allows for in-plane lead-lag motion of the associated blade relative to the yoke, each pivot allowing for in-plane motion from a neutral position of at least 1 degree in each of the lead and lag directions. Lead and lag motion of each blade is opposed by a biasing force that biases the associated blade toward the neutral position, and the biasing force is selected to achieve a first in-plane frequency of greater than 1/rev for each blade.

Abstract: A method for repairing damage to a composite part includes creating an aperture through the composite part and preparing the surfaces surrounding the aperture on both sides of the part; inserting a plurality of resin impregnated fibers through the aperture and spreading the end portions of the plurality of fibers radially against the prepared surfaces on both sides of the part; and maintaining contact of the plurality of fibers with the prepared surfaces while the resin cures.

Abstract: A cargo transportation system includes a cargo platform having an upper surface and a perimeter. A propulsion system is disposed about the perimeter of the cargo platform. The propulsion system includes a plurality of propulsion assemblies, each including a propulsion unit disposed within a housing defining an airflow channel having an air inlet for incoming air and an air outlet for outgoing air such that the outgoing air is operable to generate at least vertical lift. A power system disposed within the cargo platform provides energy to drive the propulsion system. A flight control system operably associated with the propulsion system and the power system controls flight operations of the cargo transportation system.

Abstract: In some embodiments, an aircraft includes a flying frame having an airframe with first and second wing members having a plurality of pylons extending therebetween, a distributed propulsion system including a plurality of propulsion assemblies securably attached to the airframe and a flight control system operably associated with the distributed propulsion system. The flying frame has a vertical takeoff and landing mode with the wing members disposed in generally the same horizontal plane and a forward flight mode with the wing members disposed in generally the same vertical plane. The flight control system is operable to command the propulsion assemblies responsive to at least one of remote flight control, autonomous flight control and combinations thereof.

Abstract: The present invention relates to a multilayer composite having barrier properties, objects, in particular fuel containers, comprising the same, a process for producing the multilayer composite or the objects comprising the same and also the use of the multilayer composite or the objects for reducing the emission of volatile organic compounds.

Abstract: An unmanned aircraft system has a vertical takeoff and landing flight mode and a forward flight mode. The unmanned aircraft system includes an airframe, a rotor assembly rotatably coupled to the airframe and a propeller rotatably coupled to the airframe. The rotor assembly including at least two rotor blades having tip jets that are operably associated with a compressed gas power system. The propeller is operably associated with an electric power system. In the vertical takeoff and landing flight mode, compressed gas from the compressed gas power system is discharged through the tip jets to rotate the rotor assembly and generate vertical lift. In the forward flight mode, the electric power system drives the propeller to generate forward thrust and autorotation of the rotor assembly generates vertical lift.

Abstract: A modular refueling system for an aircraft includes a modular bay recessed within the aircraft. The modular bay includes a modular bay interface. The modular refueling system includes a plurality of payload modules each having a respective function and a payload interface adapted to connect to at least a portion of the modular bay interface. The plurality of payload modules includes an aerial refueling module. The payload modules are interchangeably insertable into the modular bay to enable the modular bay to support the functions of the payload modules. The aerial refueling module is insertable into the modular bay to enable the aircraft to provide fuel to recipient aircraft during flight.

Abstract: A noise control system for a ducted rotor assembly, the ducted rotor assembly including a hub, a duct, and two or more blades coupled to the hub and supported by the duct. The noise control system including a microphone configured to receive a sound input generated by the ducted rotor assembly, the microphone configured for association with the hub; a speaker unit configured to generate a cancellation noise, the speaker configured for association with the hub; and a controller operably connected to the microphone and the speaker unit, the controller configured to selectively adjust harmonics of the cancellation noise to reduce an acoustic signature of the ducted rotor assembly. In another aspect, there is provided a rotorcraft with a ducted rotor assembly in a tail portion including a noise control system. In a third aspect, there is a method of reducing an acoustic signature of a ducted rotor assembly.

Abstract: A rotor blade including a root portion adapted to be connected to a helicopter rotor hub for rotation therewith, the root portion having a first edge surface; a first movable member having a first movable surface adjacent to the first edge surface; a first elastomeric joint disposed between the root portion and the first movable member, the first elastomeric joint having an inner surface facing the first edge surface of the root portion and an outer surface facing the movable surface of the first movable member; and an actuating system mounted within the root portion and the first movable member for moving the first movable member. The first elastomeric joint deforms to adjust for shear from actuation of the first movable member to a first position during helicopter mode; and to a second position during airplane mode.

Abstract: An adjustable balance module for the balancing of rotatable blades. The adjustable blade balance module includes a frame that retains and covers an adjustment screw with a mass that translates along a threaded shaft of the adjustment screw. The adjustment screw is incrementally controlled by an adjustment dial that is accessible from an exterior surface of the blade.

Abstract: In a first aspect, there is a helicopter skid landing gear assembly including a front cross tube configured to interconnect two skid tubes; and a rear cross tube configured to interconnect two skid tubes; wherein at least one of the cross tubes comprises a monolithic metallic tube having a cross-section with a round exterior shape and an elliptical hollow portion therein. In a second aspect, there is a method for retrofitting a helicopter with a landing gear assembly; the method including providing a front cross tube and a rear cross tube, at least one of the front cross tube and the rear cross tube comprises a monolithic metallic tube having a cross-section with a substantially round exterior shape and an elliptical hollow portion therein; and connecting the front cross tube and rear cross tube to a fuselage.

Abstract: A hybrid composite reinforced ring gear minimizing radial deformation during high RPM conditions includes a composite backing secured to a metal rim. In use, at operating temperature the composite backing contracts while the metal rim expands thus creating a compressive stress on the metal rim and significantly reduces radial deformation due to centrifugal forces as compared to an all steel ring gear.

Abstract: A hybrid composite and metallic gear includes a generally cylindrical shaft interface. A composite web is coupled to the shaft interface. The composite web includes a generally cylindrical rim having an outer surface. The outer surface includes a plurality of locks each having a radially outwardly extending profile. A generally cylindrical metallic gear ring having a plurality of external teeth includes an inner surface. The inner surface includes a plurality of detents each having a radially outwardly extending profile that corresponds with one of the locks of the composite web. When the composite web is positioned within the metallic gear ring, the corresponding locks and detents each form a lock and detent coupling establishing an interlocking interface between the composite web and the metallic gear ring.

Abstract: A propulsion assembly for a rotorcraft includes a mast and a proprotor hub assembly coupled to the mast and having a gimballing degree of freedom relative to the mast. The proprotor hub assembly includes a hook receiver. The propulsion assembly includes a gimbal lock positioned about the mast. The gimbal lock includes a locking ring and a gimbal lock hook. The gimbal lock is movable between a disengaged position and an engaged position relative to the proprotor hub assembly. The gimbal lock enables the gimballing degree of freedom in the disengaged position and disables the gimballing degree of freedom in the engaged position. The gimbal lock hook is hooked to the hook receiver in the engaged position to secure the locking ring to the proprotor hub assembly.

Abstract: The present invention discloses an operating fluid container for a motor vehicle, wherein the operating fluid container comprises a fill level sensor, a tank control device and an electrically and/or electromagnetically actuable actuator; the tank control device is connected to the actuator by means of a first data exchange connection and to the fill level sensor by means of a second data exchange connection; the fill level sensor is designed to transmit data representing a fill level of the operating fluid container to the tank control device via the second data exchange connection; the tank control device is designed to transmit a filling stop signal to the actuator via the first data exchange connection upon receiving data which represent a predetermined fill level of the operating fluid container; and the actuator initiates the termination of a filling procedure of the operating fluid container upon receiving the filling stop signal.

Abstract: A propulsion assembly for a rotorcraft includes a mast and a proprotor hub assembly coupled to the mast and having a gimballing degree of freedom relative to the mast. The propulsion assembly includes a gimbal lock assembly positioned about the mast and including a plurality of radially outwardly extending and circumferentially distributed rollers. The gimbal lock assembly is movable between a disengaged position and an engaged position relative to the proprotor hub assembly. In the disengaged position, the gimbal lock assembly enables the gimballing degree of freedom. In the engaged position, the rollers of the gimbal lock assembly contact the proprotor hub assembly to disable the gimballing degree.

Abstract: Disclosed are systems and methods for grounding insulated P-clamps used to secure fuel conduits. To do so, one end of the device is adapted to be secured between the flanges of the P-clamp, and a second end is adapted to extend into the clamp to make electrical contact with the conduit. The device creates an electrical path to the grounded structure to which the clamp is secured.

Abstract: A wing airframe for a wing of a tiltrotor aircraft includes a wing airframe core assembly and a wing skin assembly disposed on the wing airframe core assembly. The wing skin assembly includes a lower wing skin assembly disposed on the bottom side of the wing airframe core assembly. The tiltrotor aircraft includes a fuselage underneath the wing. The lower wing skin assembly has one or more buckle zones outboard of the fuselage. The buckle zones are locally susceptible to buckling in response to an impact of the tiltrotor aircraft, thereby protecting the fuselage from being crushed by the wing.

Abstract: Some examples of a cable cutting system include a first cutting apparatus that includes a recess to receive a cable. The system includes a second cutting apparatus separate from and attached to the first cutting apparatus. The second cutting apparatus includes multiple cutting surfaces arranged to cut the cable received at the recess.

Abstract: A wing pivot apparatus for rotating a wing between a flight orientation and a stowed orientation relative to a fuselage of a tiltrotor aircraft. The apparatus includes a stow ring that is rotatably mounted to the fuselage. Forward and aft wing attach assemblies are coupled respectively to forward and aft spars of the wing and are coupled to the stow ring. Forward and aft connecting assemblies are coupled respectively between the forward and aft wing attach assemblies and the stow ring and are selectively securable respectively to first and second fore-aft beams of the fuselage. A plurality of lock assemblies selectively secures the connecting assemblies to the fore-aft beams of the fuselage when the wing is in the flight orientation. An actuator coupled to the fuselage is operable to reversibly rotate the wing between the flight orientation and the stowed orientation.