Abstract: The present invention discloses an operating fluid container (10) made of thermoplastic material for a motor vehicle and a method for equipping an operating fluid container with a stiffening element (20).

Abstract: A rotorcraft includes airspeed sensors, inertial sensors, and a flight control computer (FCC) operable to provide a longitudinal control for the rotorcraft. The FCC receives a first indication of longitudinal airspeed from the airspeed sensors and receives a first indication of longitudinal acceleration from the inertial sensors. The FCC generates a filtered indication of longitudinal airspeed from the first indication of longitudinal airspeed and generates a scaled and filtered indication of longitudinal acceleration from the first indication of longitudinal acceleration. The FCC combines the filtered indication of longitudinal airspeed with the scaled and filtered indication of longitudinal acceleration to generate a determined longitudinal airspeed. The FCC generates a flight control signal to control operation of the rotorcraft, the flight control signal based on the determined longitudinal airspeed.

Abstract: A propulsion assembly for an aircraft includes a housing having a gimbal coupled thereto that is operable to tilt about first and second axes. A propulsion system is coupled to and operable to tilt with the gimbal. The propulsion system includes an electric motor having an output drive and a rotor assembly having a plurality of rotor blades. The rotor assembly is rotatable with the output drive of the electric motor in a rotational plane to generate thrust having a thrust vector with a direction. The first axis of the gimbal is orthogonal to the second axis of the gimbal. Actuation of the gimbal tilts the propulsion system relative to the housing to change the rotational plane of the rotor assembly relative to the housing, thereby controlling the direction of the thrust vector within a thrust vector cone.

Abstract: The present application provides a drive link for a constant-velocity joint of an aircraft rotor, the link connecting a drive hub attached to a driveshaft to a rotor yoke. The link comprises a leading bearing connected to the drive hub, a trailing bearing connected to the yoke, a central portion between the bearings, and a tension loop connecting the bearings. The tension loop is formed from a composite material and is formed as a continuous band. The tension loop transfers drive forces from the leading bearing to the trailing bearing for driving the yoke in rotation with the driveshaft.

Abstract: In accordance with an embodiment of the present invention, a method of operating a rotorcraft includes operating the rotorcraft in a heading control mode that includes activating a yaw channel path of a heading controller and deactivating a roll channel path of the heading controller when a speed of the rotorcraft is less than a first speed threshold or a heading error is less than a heading error threshold, and activating the roll channel path of the heading controller and deactivating the yaw channel path of the heading controller when the speed of the rotorcraft is greater than a second speed threshold and the heading error is not less than the heading error threshold.

Abstract: A method of determining damage tolerance allowables in a specimen, the method includes applying a cyclic load to a specimen until a first crack emanates from a notch in the specimen, the cyclic load having a maximum load and a minimum load. The method also includes applying a subsequent cyclic load to the specimen until the first crack grows to form a second crack emanating from the first crack, the subsequent cyclic load having the same maximum load but a greater minimum load.

Abstract: The disclosure relates to a multi-chamber container made of thermoplastic plastic as a service-fluid container for a motor vehicle, which multi-chamber container comprises at least two chambers, which constitute separated volumes that are not in fluid connection with each other, at least not directly, and which are each designed to hold a different service fluid, wherein at least two surrounding walls of the chambers adjoin each other, the chambers are components of a continuous container body combination, the surrounding walls of at least two chambers that adjoin each other are connected to each other in a bonded manner by means of at least one material bridge or in a form-closed manner and/or by means of fasteners, and the connection is designed to independently release under the influence of deformation forces caused by impact such that the container body combination is divided into at least two separate container body parts or two container bodies under the influence of deformation forces caused by impact

Abstract: A helicopter has a fuselage, a main rotor system connected to the fuselage and configured to rotate in a rotor direction, the main rotor system comprising a retreating rotor blade side and an opposing advancing rotor blade side, and a first wing extending from the fuselage on the retreating rotor blade side. The helicopter comprises no tail rotor system and comprises no counter-rotating rotor system coaxial with the main rotor system.

Abstract: The present invention discloses an operating liquid container system comprising at least one operating fluid container, a quality and/or filling level sensor arranged in the operating liquid container, for determining at least one quality characteristic of the operating liquid contained in the operating liquid container and/or a filling level of the operating liquid container, and a display device arranged in a tank recess and/or tank flap of the operating fluid container system, wherein the display device is connected to the quality and/or filling level sensor by means of a data line for transmitting data from the quality and/or filling level sensor to the display device, wherein the data represents at least one quality characteristic of the operating liquid contained in the operating liquid container and/or the filling level of the operating liquid container.

Abstract: In some embodiments, a pod assembly transportation system includes a transportation services provider computing system and a plurality of flying frame flight control systems, wherein the system is configured to receive, at the transportation services provider computing system, a request for transportation of a pod assembly; upload a flight plan to a flight control system of a flying frame including an airframe and a distributed propulsion system coupled to airframe; dispatch the flying frame by air to the current location of the pod assembly; couple the pod assembly to the flying frame; transport the pod assembly by air from the current location of the pod assembly to the destination of the pod assembly including transitioning the flying frame between a vertical takeoff and landing mode and a forward flight mode; and decouple the pod assembly from the flying frame at the destination of the pod assembly.

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: A hub system comprises at least one yoke, at least one shear bearing, and at least one mast adapter. The at least one mast adapter is configured to support the at least one yoke and the at least one shear bearing, and the at least one yoke has a flapping hinge that is non-coincident with a flapping hinge of the at least one shear bearing. Another hub system comprises a stacked yoke and a mast adapter. The mast adapter is configured to transfer rotation from a rotor mast to the hub system to rotate the hub system about a central axis of rotation. The mast adapter is further configured to support the stacked yoke such that each yoke in the stacked yoke is configured to accommodate at least some amount of rotation about an axis that is perpendicular to or about perpendicular to the central axis of rotation.

Abstract: Embodiments of the present disclosure include a robotic method for processing an aircraft component that includes determining feature positions by illuminating with light, imaging the reflected light with a camera, and processing images from the camera. The method further includes determining a position offset of the features by comparing to a model of the aircraft component, determining a path offset for movement by a robot arm, and modifying the aircraft component using a processing tool coupled to the robot arm. A robotic system for processing an aircraft component includes a light emitting device and a camera configured for respectively illuminating and imaging features of an aircraft component, a gripper tool for gripping and moving the aircraft component to a workstation, a processing tool for modifying the aircraft component, and a controller to control the light emitting device, camera, gripper tool, workstation, and processing tool to modify the aircraft component.

Abstract: The invention relates to a fuel tank of thermoplastic polymer for a motor vehicle, having at least one reinforcing element inside the fuel tank, the reinforcing element inside the fuel tank extending between opposing tank walls (15), parts of the reinforcing element passing through the tank wall and parts of the reinforcing element engaging behind the tank wall from outside, the fuel tank being distinguished according to the invention in that the reinforcing element (8) is provided with at least one multipart fastening head (11), which comprises a first closing means engaging through the tank wall (15) from inside and a second closing means engaging through the tank wall (15) from outside, which closing means are of mutually complementary construction.

Abstract: A high stiffness hub assembly for a proprotor system operable to rotate with a mast of a tiltrotor aircraft having helicopter and airplane flight modes. The hub assembly includes a yoke and a constant velocity joint assembly. The yoke has four blade arms each adapted to hold a proprotor blade. The constant velocity joint assembly provides a torque path from the mast to the yoke that includes a trunnion assembly, four drive links and four pillow blocks. The trunnion assembly is coupled to the mast and has four outwardly extending trunnions. Each drive link has a leading bearing coupled to one of the trunnions and a trailing bearing coupled to one of the pillow blocks. Each pillow block is independently mounted between an upper surface of the yoke and a hub plate with two connection members that extend through the yoke and the pillow block.

Abstract: A hydraulic system for an aircraft having an engine and an auxiliary power unit includes a first hydraulic subsystem including a first hydraulic pump and a first set of hydraulic-powered components in fluid communication with the first hydraulic pump. The first hydraulic pump is powered by the engine to pump shared hydraulic fluid to the first set of hydraulic-powered components. The hydraulic system includes a second hydraulic subsystem including a second hydraulic pump and a second set of hydraulic-powered components in fluid communication with the second hydraulic pump. The second hydraulic pump is powered by the auxiliary power unit to pump the shared hydraulic fluid to the second set of hydraulic-powered components. A shared return line subsystem and reservoir is in fluid communication with the first and second hydraulic subsystems to return the shared hydraulic fluid to the first and second hydraulic pumps.

Abstract: There is a method of making a tubular specimen with a predetermined wrinkle defect including providing a layup tool with a cavity forming member having a cavity which resembles a desired shape of the at least one wrinkle; orienting a composite material around the mandrel at a wrap angle to form a closed loop; positioning a wrinkle tool on the closed loop; and/or generating at least one wrinkle with a predetermined characteristic in a portion of the closed loop to form a tubular specimen. The predetermined characteristic is at least one of the following: wrinkle location, an outward wrinkle, an inward wrinkle, a wrinkle width, a wrinkle height, and a wrinkle length. In another aspect, there is a method of offset load testing a tubular composite specimen. In a third aspect, there is a method of determining allowable defects for a composite component.

Abstract: In a first aspect, there is a method of making a specimen with a predetermined wrinkle defect, the steps including orienting a composite material around a layup tool at a wrap angle to form a closed loop; and generating at least one wrinkle with a predetermined characteristic in a portion of the closed loop to form a specimen. The predetermined characteristic is at least one of the following: wrinkle location, an outward wrinkle, an inward wrinkle, a wrinkle width, a wrinkle height, and a wrinkle length. In another aspect, there is a method of determining allowable defects for a composite component.

Abstract: A pylon assembly for a tiltrotor aircraft includes a fixed pylon having an outboard end. A rotor assembly is rotatably coupled to the fixed pylon and is operable to rotate between a a vertical takeoff and landing orientation and a forward flight orientation. The rotor assembly includes a proprotor operable to produce a slipstream. A wing extension is rotatably coupled to the outboard end of the fixed pylon. The wing extension is operable to rotate generally with the rotor assembly such that a minimal dimension of the wing extension remains in the slipstream of the proprotor.

Abstract: An auxiliary seating system for a light weight utility vehicle that comprises a seat support cage attachable to a rear portion of the vehicle, and a pair of seat assemblies mounted to the cage structure such that each seat assembly is oriented to be facing at least partially inward toward a longitudinal center line of the vehicle. Each seat assembly comprises a seat bottom that is pivotal between a down position and an up position. Each seat assembly can include a golf bag yoke disposed on an underside of the seat bottom, and a seat belt that retains a passenger within the seat assembly when the seat bottom is in the down position, and retains a golf bag within the respective golf bag yoke when the seat bottom is in the up position.