Abstract: A rotorcraft including a flight control computer (FCC) providing a vertical speed hold for the rotorcraft, a collective control, and a collective trim motor connected to the collective control. The collective trim motor moves the collective control according to a collective set command generated by the FCC according to a target vertical speed and when the FCC determines the collective control is in-detent. A collective position sensor is connected to the collective control. The collective position sensor generates, and sends to the FCC, a collective position signal indicating the position of the collective control. A flight control device controls a flight parameter of the rotorcraft in response to a flight control device control signal received from the FCC. The FCC generates the flight control device control signal according to the collective position signal, and sends the flight control device control signal to a flight control device.

Abstract: A modular payload system for an aircraft includes a modular bay recessed within the aircraft. The modular bay includes a modular bay interface. The modular payload 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 are interchangeably insertable into the modular bay to enable the modular bay to support the functions of the plurality of payload modules.

Abstract: A rotary system including a grip having an opening forming a first bridge for receiving a centrifugal force bearing that faces inwardly towards the rotor mast. A rotor blade couples to the grip and a pitch horn positioned outside the opening pitches the rotor blade during flight. A bearing assembly attaches the first bridge to the yoke and controls blade forces exerted against the hub assembly during flight.

Abstract: A method and apparatus for determining failure diagnosis of drive systems of rotorcrafts through measuring the spectral characteristics of rotational oscillations and torsional oscillations and steady windup of a drive shaft. Mechanical anomalies of the drive system will alter the spectral characteristics of rotational oscillations and torsional oscillations and steady windup as detected by a pair of variable reluctance sensors in conjunction with a radial grating mounted on the drive shaft.

Abstract: A blade for an aircraft rotor has a trailing-edge tab, the tab being movable between a stowed position, in which substantially all of the tab is located within the blade, and a deployed position, in which at least a portion of the tab extends from a trailing edge of the blade. At least one actuator system is selectively operable to cause movement of the tab between the stowed position and the deployed position for changing a chord length of the blade.

Abstract: An airframe for a tiltrotor aircraft includes a wing airframe including a rib, a fuselage airframe including a fore-aft overhead beam and a cradle support assembly. The cradle support assembly includes a forward wing support coupled to the fore-aft overhead beam and the wing airframe and an aft wing support coupled to the fore-aft overhead beam and the wing airframe. The rib, the fore-aft overhead beam, the forward wing support and the aft wing support are substantially aligned to form a wing-fuselage integrated airframe beam assembly to support the wing airframe.

Abstract: An aircraft rotor assembly has a yoke and a plurality of rotor blade assemblies coupled thereto. Each of the rotor blade assemblies include a rotor blade, a bearing, and a blade grip coupling the rotor blade to the bearing. Each of the rotor blades is rotatable about a lead-lag axis, flap axis, and a pitch change axis, wherein all the axes intersect within the bearing. Adjacent pairs of rotor blade assemblies are coupled together via a damper assembly that is coupled to the pitch change axis of each of the rotor blade assemblies.

Abstract: A hybrid power system for a vertical takeoff and landing (“VTOL”) aircraft including a first power source operable to provide a power output for at least a forward flight mode; and a second power source configured to provide a high specific power output for an altitude adjustment flight mode, the second power source including an auxiliary gas generator coupled to a turbine and a drive system. In other aspects, there is provided a VTOL aircraft and methods for providing power to a VTOL aircraft.

Abstract: A tiltrotor aircraft has a vertical takeoff and landing flight mode and a forward flight mode. The tiltrotor aircraft includes a longitudinally extending fuselage with a wing extending laterally therefrom having oppositely disposed wing tips distal from the fuselage. Tip booms respectively extend longitudinally from the wing tips. Forward rotors are coupled to the forward ends of the tip booms. The forward rotors are reversibly tiltable between a vertical lift orientation, wherein the forward rotors are above the tip booms, and a forward thrust orientation, wherein the forward rotors are forward of the tip booms. An aft rotor is coupled to the aft end of the fuselage. The aft rotor is reversibly tiltable between a vertical lift orientation, wherein the aft rotor is below the fuselage, and a forward thrust orientation, wherein the aft rotor is aft of the fuselage.

Abstract: A tiltrotor aircraft has a vertical takeoff and landing flight mode and a forward flight mode. The aircraft includes an airframe having a wing with oppositely disposed wing tips. Tip booms respectively extend longitudinally from the wing tips. Forward rotors are coupled to the forward ends of the tip booms and aft rotors are coupled to the aft ends of the tip booms. The forward rotors are reversibly tiltable between a vertical lift orientation, wherein the forward rotors are above the tip booms, and a forward thrust orientation, wherein the forward rotors are forward of the tip booms. The aft rotors are reversibly tiltable between a vertical lift orientation, wherein the aft rotors are below the tip booms, and a forward thrust orientation, wherein the aft rotors are aft of the tip booms. One of a plurality of payload modules is interchangeable coupled to the airframe, wherein each payload module has a respective function.

Abstract: The present invention discloses a device for producing a reinforcing structure, which comprises a strip that is fiber-reinforced and comprises thermoplastic material, on the surface of a molding. The device is characterized in that it is designed such that the laser diode array directly irradiates the heating-up area of the strip and/or the heating-up area of the surface of the molding or of the already formed reinforcing structure, wherein the laser diodes of the laser diode array are formed as surface emitters.

Abstract: The invention relates to a vent valve (1) for controlling the internal tank pressure of a fuel tank, having at least one valve housing (2) having at least one first connection (3) to the fuel tank and at least one second connection (4), which can be connected to a vent line leading to a fuel vapor filter. The vent valve (1) comprises at least one valve element, which is held in a valve seat (8) in a position in which it closes the first connection (3) by the force of gravity and/or by spring loading and, after a given pressure threshold is exceeded, is raised from the valve seat (8) and, when a given pressure threshold is undershot, returns to the initial position. The valve element and/or the valve element guide has/have at least one relief opening (10), which forms a bypass for a gap flow which arises, for example, during a return movement of the valve element.

Abstract: A tiltrotor aircraft having a VTOL flight mode, a forward flight mode and a storage mode includes a fuselage having a wing rotatably mounted thereto. The wing has an orientation generally perpendicular to the fuselage, in the flight modes, and an orientation generally parallel to the fuselage, in the storage mode. First and second pylon assemblies are positioned proximate outboard ends of the wing. First and second mast assemblies are respectively rotatable relative to the first and second pylon assemblies and have generally vertical orientations, in the VTOL flight mode, and generally horizontal orientations, in the forward flight mode and the storage mode. First and second proprotor assemblies are respectively rotatable relative to the first and second mast assemblies. Each proprotor assembly includes a plurality of rotor blades and has a radially extended orientation, in the flight modes, and a stowed orientation, in the storage mode.

Abstract: Disclosed herein is an aircraft that includes an exhaust manifold for combining one or more system exhaust paths located upstream of equipment inlets and directing the exhausts upwards towards the rotor linkages such that the exhaust is expelled and diffused forward of the equipment inlets. According to one aspect of the present disclosure, the exhaust manifold includes a structure for supporting a transmission cowling at the top of the aircraft and/or on the sides of the aircraft. For example, the exhaust manifold may include a platform that contains the exhaust ducts and may include a frame extending from the platform that follows the contours of the cowling, such that the cowling lays along the support frame for additional mechanical support.

Abstract: An inertia weight assembly positionable within a receiving portion of a rotor blade for use on a rotorcraft. The inertia weight assembly includes a weighted core and a casing having a closed outboard end and forming a cavity. The weighted core is disposed in the cavity such that the casing at least partially encloses the weighted core. The weighted core is formed from a first material and the casing is formed from a second material that is dissimilar to the first material. The casing provides an interface between the weighted core and the receiving portion of the rotor blade. The second material is more bondable to the receiving portion of the rotor blade than the first material.

Abstract: An aircraft rotor assembly has a yoke defining a plurality of bearing pockets. Each bearing pocket houses an axisymmetric elastomeric spherical bearing at least partially therein. The axisymmetric elastomeric spherical bearings comprise flap, lead-lag, and pitch hinges for rotor blades coupled thereto. The rotor blades maintain a first in-lane frequency of less than 1/rev through the use of damper assemblies coupled between adjacent blades.

Abstract: A door system for a nacelle of a tiltrotor aircraft, the nacelle including a movable proprotor housing rotatable relative to a fixed portion of the nacelle from a forward flight mode to a vertical flight mode and a proprotor gearbox door connected to the movable proprotor housing and pivotably coupled to the fixed portion. The door system including a linkage to pivotably couple the door and the fixed portion of the nacelle; a track assembly mounted to the movable proprotor housing; and a door roller mechanism connected to the proprotor gearbox door. The door roller mechanism traverses the track assembly during rotation of the movable proprotor housing.

Abstract: In one embodiment, an apparatus comprises a processing device configured to: obtain sensor data from one or more sensors associated with an aircraft, wherein the one or more sensors are configured to detect information associated with an operating environment of the aircraft; detect an object near the aircraft based on the sensor data; obtain a camera feed from a camera associated with the aircraft, wherein the camera feed comprises a camera view of at least a portion of the aircraft; generate a display output based on the camera feed and the sensor data, wherein the display output comprises a visual perspective of the object relative to the aircraft; and cause the display output to be displayed on a display device.

Abstract: A system and method for measuring, or otherwise determining pitch length adjustments to a pitch link coupled to a rotor blade in a rotorcraft includes vertical track adjustment indicators machined onto an exterior of the tube of the pitch link and a vertical reference indicator machined onto an exterior of the upper or the lower rod of the pitch link. A metric of a pitch length adjustment can be determined by tracking or counting how many track adjustment indicators pass the reference indicator while the tube of the pitch link is being turned in either direction for increasing or decreasing the pitch length. The track adjustment indicators can be relied upon to track one or a series of adjustments for tracking a rotor blade installed in a rotor assembly.

Abstract: A an open relay device and system includes a chassis having one or more openings; external connectors on a first wall of the chassis, the external connectors having a plurality of external connection terminals; ground bussing modules attached to a second wall of the chassis; junction bussing modules attached to a third wall of the chassis; relay sockets attached to a fourth wall of the chassis; and wiring electrically connecting the external connectors to the ground bussing modules, the junction bussing modules, and the relay sockets, the wiring further electrically connecting the relay sockets to the junction bussing modules and the ground bussing modules.