Abstract: A vibration isolation system for an advancing blade concept rotorcraft having a pylon assembly and an airframe. The vibration isolation system includes one or more pylon links each having first and second ends with the first end coupled to the pylon assembly and the second end coupled to the airframe. Each pylon link includes a vibration isolator, such as a Liquid Inertia Vibration Eliminator unit, that is interposed between the pylon assembly and the airframe. The vibration isolator system is operable to reduce or eliminate transmission of the pylon assembly vibration to the airframe.

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: Embodiments refer generally to systems and methods for providing autorotative enhancement for helicopters using an autorotative assist unit coupled to the transmission of the helicopter. Methods of utilizing an autorotative assist unit as well as retrofitting an autorotative assist unit to an existing helicopter are also disclosed. By employing an autorotative assist unit, improved autorotation can be achieved without the need to increase the weight of the rotor.

Abstract: The invention relates to a container (1) of thermoplastic material with at least one support (4), which is arranged in the interior of the container, extends between opposing container walls (2) and is anchored at each end to the container walls with a positive engagement and/or a material bond, the support (4) comprising at least one supporting strut (5) and the supporting strut (5) substantially absorbing a supporting load on the container walls (2) induced by negative pressure in the container, and a tensile force that is induced by positive pressure being absorbed by at least one tension-resistant bracing element in the form of a tension-resistant band (8) which extends between the container walls (2).

Abstract: A helicopter has a mast axis and a rotorcraft blade assembly. The rotorcraft blade assembly has a main body and a blade tip movable relative to the main body. The rotorcraft blade assembly is selectively rotatable about the mast axis.

Abstract: An aircraft has an airframe with a distributed thrust array attached thereto that includes a plurality of propulsion assemblies each of which is independently controlled by a flight control system. Each propulsion assembly includes a housing with a gimbal coupled thereto and operable to tilt about a single axis. 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 that rotate in a rotational plane to generate thrust having a thrust vector with a magnitude in the longitudinal direction. Actuation of each gimbal is operable to tilt the respective propulsion system relative to the airframe in the longitudinal direction to change the rotational plane of the respective rotor assembly relative to the airframe, thereby controlling the magnitude of the respective thrust vector in the longitudinal direction.

Abstract: The present invention achieves technical advantages as a pilot and passenger seating. An aircraft employs a pilot seat, comprising a contoured structure having ergonomically formed and padded surfaces, with left and right arm supports that include an articulated control knob, movable in three rectangular axes and rotatable about a vertical axis to provide one or more aircraft steering functions for an aircraft, and a touch-sensitive control surface for controlling one or more power system components. A passenger seat, having a contoured structure, having ergonomically formed and padded surfaces, a headrest, a seat, a left support member, and a right support member are adapted to cradle a portion of a passenger's body to support the passenger during travel.

Abstract: The present invention achieves technical advantages as a vehicle cabin, comprising a floor system formed of removable and reconfigurable floor segments extending from a vehicle frame, and a ceiling system formed of removable and reconfigurable ceiling segments disposed in the ceiling of the vehicle cabin. Floor segments that can be positioned to form a floor channel, therebetween. A fixture interface adapted to releasably secure a fixture to the floor system. The fixture can be slidably repositioned within the vehicle along the floor channel. One of the ceiling segments includes one or more of a lighting module, a ventilation outlet, a ventilation inlet, a display screen, or a touch control panel. The ceiling segments can be hexagonal.

Abstract: An aircraft including a nacelle disposed at a fixed location relative a wing member; a proprotor housing coupled to the nacelle, the proprotor housing configured to selectively rotate between a horizontal orientation and a non-horizontal orientation; a door pivotably coupled to the proprotor housing; and a linkage to connect the door and the nacelle, the linkage configured to move with the door from a closed position when the proprotor housing is in a horizontal orientation to an open position when the proprotor housing is in a non-horizontal orientation. In some embodiments, there can be a hinge member for hingedly coupling the door to the proprotor and/or nacelle. In other embodiments, the door includes a flexure portion. In some embodiments, the nacelle includes a plurality of doors. In other embodiments, proprotor includes a forward portion and a stationary aft portion; wherein the forward portion is configured to selectively pivot.

Abstract: A helicopter includes a full authority digital engine controlled (FADEC) engine, a first two-position throttle switch disposed on a first collective control stick, the first two-position throttle switch being movable between a Fly position and an Idle position, and a second two-position throttle switch disposed on a second collective control stick, the second two-position throttle switch being movable between a Fly position and an Idle position.

Abstract: A door roller mechanism for cooperation with a roller track including a carriage member having a door attachment feature; at least one roller disposed for rotation on a first side of the carriage member when the carriage member moves in the rolling direction; at least one roller disposed for rotation on an opposite second side of the carriage member when the carriage member moves in the rolling direction; a first rub member disposed on the first side of the carriage; a second rub member disposed on the second side of the carriage; and at least one biasing element disposed on the carriage member for resiliently biasing the first rub member and the second rub member in opposite lateral directions so as to contact a respective first track surface and a second track surface in a manner to dampen lateral vibration of a door connected to the roller mechanism.

Abstract: A door track assembly for cooperation with a door roller mechanism, including a housing having a longitudinal channel along a length of the housing, wherein the channel descends at an end of the housing to form a stowage recess for the door roller mechanism, and a first track and a second track that are disposed on the housing along a length of the channel and that descend into the stowage recess and along which the door roller mechanism traverses.

Abstract: The present invention achieves technical advantages as an aircraft having an augmented reality flight control system integrated with and operable from the pilot seat and an associated pilot headgear unit, wherein the flight control system is supplemented by flight-assisting artificial intelligence and geo-location systems. The present invention includes an augmented reality flight control system incorporating real-world objects with virtual elements to provide relevant data to a pilot during aircraft flight. A translucent substrate is disposed in the pilot's field of view such that the pilot can see therethrough, and observe virtual elements displayed on the substrate. The system includes a headgear that is worn by the pilot. A flight assistance module is configured to receive data related to the aircraft and provide predictive assistance to the pilot during flight based on the received data based in part on a pilot profile having preferences related to the pilot.

Abstract: The invention relates to a filler neck (1) for a fuel tank of a motor vehicle having at least one tubular section (3) provided in the region of the filler inlet (2) in order to receive the outlet pipe of a fuel delivery nozzle (5), and a flame barrier (4) which is provided in the tubular section (3) and surrounds the outlet pipe of the fuel delivery nozzle (5) in the inserted state, wherein the flame barrier (4) includes at least two segments (6) which are mounted resiliently in the radial direction of the tubular section (3), the diameter of the opening (7) in the flame barrier (4) for the outlet pipe of the fuel delivery nozzle (5) being smaller in the prestressed state of the segments (6) than the diameter of the outlet pipe of the fuel delivery nozzle (5).

Abstract: The system is configured for automation of rotorcraft entry into autorotation. The system can provide a means to assist the flight crew of a rotorcraft in maintaining rotor speed following loss of engine power. The system can automatically adjust control positions, actuator positions or both to prevent excessive loss of rotor speed upon initial loss of engine power before the flight crew is able to react. The system uses model matching to provide axis decoupling and yaw anticipation; it includes pitch control initially to assist in preventing rotor deceleration; and it makes use of collective, pitch, roll and yaw trim functions to provide tactile cueing to the pilot to assist when the pilot is in the loop. The system can reduce workload by assisting the crew with controlling rotor speed and forward speed during stabilized autorotation.

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 filling system on a motor vehicle, having at least two storage tanks for operating materials, comprising a tank closure cover which closes an opening in a body of the motor vehicle and is movable from a first position that closes the opening into a second position that releases the opening, wherein at least two filling openings of the storage tanks are arranged below the tank closure cover, a filler trough that forms an enclosure of the filling opening, wherein the filler trough closes the opening in the body and is fixed to the body; and at least one filler head, wherein the filling openings are formed as a part of the filler head, the filler head defining at least two mouth-hole necks which are combined to form a common component and are integrally connected to each other, each mouth-hole neck forming a filling opening for another storage tank.

Abstract: A vibration control system for a rotor hub provides vibration attenuation in an aircraft by reducing the magnitude of rotor induced vibratory. The system can include a force generating device attached to a rotor hub which rotates along with the rotor at the rotational speed of the rotor. Vibratory shear force is generated by rotating unbalanced weights each about an axis non-concentric with the rotor hub axis at high speed to create large centrifugal forces. The rotational speed of the weights can be a multiple of the rotor rotational speed to create shear forces for canceling rotor induced vibrations. The amplitude of the generated shear force is controlled by indexing the positions of the unbalanced weights relative to each other, while the phase of the shear force is adjusted by equally phasing each weight relative to the rotor.

Abstract: A pedestal assembly receives a pylon assembly of a tiltrotor aircraft having an airframe including a fuselage and a wing. The pedestal assembly includes inboard and outboard tip ribs that extend above the wing and respectively define inboard and outboard slots. The pedestal assembly also includes inboard and outboard bearing cartridges. The inboard bearing cartridge is received within the inboard slot, is coupled to the inboard tip rib and includes an inboard bearing assembly. The outboard bearing cartridge is received within the outboard slot, is coupled to the outboard tip rib and includes an outboard bearing assembly. The inboard and outboard bearing assemblies are operable to receive the pylon assembly therein such that the pylon assembly is rotatably mounted between the inboard and outboard tip ribs to selectively operate the tiltrotor aircraft between a helicopter mode and an airplane mode.

Abstract: A battery heater system for a battery used in cold weather operations and methods for using the battery heater system are described. Embodiments of the battery heater system may incorporate a heater switch with an indicator, a timer circuit, a controller, a voltage meter, a temperature transducer, and a heating element. In some methods of using the device, the battery powers the heating element for a fixed cycle time based on the time to discharge the battery at a cold-soaked temperature. In other methods of using the device, the battery powers the heating element for a varying cycle time as necessary to discharge the battery to a discharge cut-off voltage value. In other methods of using the device, the heating element is operated using a duty cycle that is varied based on the battery temperature.