Abstract: The invention relates to a method for controlling the recovery of water in a motor vehicle, in which method, to recover water in an air-conditioning system (12) of the motor vehicle, air is cooled to a temperature below its dew point, and the water dropping out as a result of the cooling is collected in a water container (13). During water recovery, the air-conditioning system (12) is controlled by means of a water recovery control device (11), wherein, to control the water recovery by means of the water recovery control device (11), the air-conditioning system (12) is adjusted on the basis of at least one parameter value which is detected by a detection unit (10) and transmitted to the water recovery control device (11).

Abstract: An aircraft employs articulated, variable-position electric rotors having different operating configurations and transitions therebetween, as well as variable-pitch airfoils or blades, for generating vectored thrust in the different configurations. Control circuitry generates rotor position signals and blade pitch signals to independently control rotor thrust, rotor orientation and rotor blade pitch of the variable-position rotors in a manner providing (i) the transitions among the operating configurations for corresponding flight modes of the aircraft, which may include both vertical takeoff and landing (VTOL) mode as well as a forward-flight mode, and (ii) commanded thrust-vectoring maneuvering of the aircraft in the different configurations, including tailoring blade pitch to optimize aspects of aircraft performance.

Abstract: A modular battery system provides propulsive power to the rotor system of an aircraft. The modular battery system includes an array of battery modules arranged in at least one stack. Each battery module includes a plurality of battery cells, a first side having positive and negative receptacles and a second side, that is opposite of the first side, having positive and negative plugs. The receptacles and plugs are configured such that adjacent battery modules in a side-by-side relationship are electrically coupled together via plug and receptacle connections and such that the battery modules are electrically coupled together in parallel. An interconnection electrically couples each stack of battery modules together via plug and receptacle connections with one of the battery modules in each stack such that the stacks of battery modules are electrically coupled together in parallel.

Abstract: A rotor assembly for an aircraft operable to generate a variable thrust output at a constant rotational speed. The rotor assembly includes a mast rotatable at the constant speed about a mast axis. A rotor hub is coupled to and rotatable with the mast. The rotor hub includes a plurality of spindle grips extending generally radially outwardly. Each of the spindle grips is coupled to one of a plurality of rotor blades and is operable to rotate therewith about a pitch change axis. A collective pitch control mechanism is coupled to and rotatable with the rotor hub. The collective pitch control mechanism is operably associated with each spindle grip such that actuation of the collective pitch control mechanism rotates each spindle grip about the respective pitch change axis to collectively control the pitch of the rotor blades, thereby generating the variable thrust output.

Abstract: A system and method for preventing a maximum asymmetric condition between pylon tilt angles due to a degraded pylon in a fly-by-wire tiltrotor aircraft during transitions between airplane mode and helicopter mode includes a conversion system for imparting movement on a right and left pylon. A flight control computer is operatively connected to a set of transducers for measuring pylon angles. The flight control computer is further connected to a set of actuators which are attached to each pylon. The flight control computer receives flight dynamics input from the set of transducers and/or the pilot and sends pylon command to the set of actuators. The conversion system measures the difference between the pylon angles during the transition and provides a pylon command adjustment if the difference exceeds a preset threshold.

Abstract: A method of displacing rotors of an aircraft between a hover mode and an aircraft mode includes rotating a spindle drivingly connected to the rotors about a spindle axis to displace the rotors between the hover and aircraft modes until a component displaceable with the spindle abuts against a downstop of the aircraft and applies a load against the downstop. The method includes passively maintaining the component against the downstop to maintain the load applied against the downstop. An aircraft is also disclosed.

Abstract: The invention relates to an arrangement (100) having a liquid tank (10), at least one line (11, 11a, 11b) connected to the liquid tank (10), through which liquid (F) can be transported from the liquid tank (10), and a pump (13) connected to the at least one line (11, 11a, 11b) for conveying the liquid (F) from the liquid tank (10) through the at least one line (11, 11a, 11b) in the direction of flow (R) during an operating phase, wherein a pressure accumulator (14) connected to the at least one line (11, 11a, 11b) is provided, by means of which a pressure can be generated in the at least one line (11, 11a, 11b) outside of the operating phase, and a ventilating element (15, 15a, 15b), which can be transitioned into an open position and into a closed position, is arranged along the at least one line (11, 11a, 11b), wherein, outside of the operating phase, a pressure impulse within the at least one line (11, 11a, 11b) can be generated by the pressure generated by the pressure accumulator (14) and a subsequent tr

Abstract: An aircraft has a seat that has at least one of (1) a nonplanar back surface profile and a touch sensitive film display system carried by the seat and configured to conform to the nonplanar back surface profile and (2) a privacy screen selectively stowed within an interior of the seat. An aircraft has a pilot seat, a passenger seat disposed aft relative to the pilot seat, and a holographic display system configured to project a holographic image in a space between the pilot seat and the passenger seat.

Abstract: Embodiments are directed to a rotor system for an aircraft comprising a gearbox configured to receive torque from a drive train, a mast having a first end and a second end, wherein the first end is attached to the gearbox and the mast configured to rotate in response to the torque from the drive train, a rotor hub attached to the second end of the mast, a first light transceiver mounted adjacent to the first end of the mast, wherein the first light transceiver is does not rotate relative to the mast, and a second light transceiver mounted adjacent to the second end of the mast, wherein the second light transceiver rotates with the mast.

Abstract: Disclosed is a system for an amphibious aircraft where floats on each side of the aircraft include aerodynamic structures. The structures are configured to compensate for aerodynamic imbalances (e.g., in yaw and pitch) created by the incorporation of the floats onto the aircraft.

Abstract: An exemplary clamp system for securing a proprotor blade in a stowed position includes a clamp having a pair of opposing pads operable between an open position to receive a portion of a proprotor blade between the pair of opposing pads and a closed position to grip the portion of the proprotor blade with the pair of opposing pads and a rotary actuator in connection with the clamp to operate the clamp between the open and the closed position.

Abstract: An operating fluid tank for a motor vehicle, in particular for storing an aqueous additive, comprising: a tank wall made of a thermoplastic material, wherein the tank wall has a top, a bottom and side walls, and the tank wall delimits a tank volume, wherein the tank volume has a height, a depth and a width; and at least one electrically operated heating device having one or more heating elements, the heating element being inserted into an outer depression of the tank wall, or into an outer recess or opening in the tank wall, or into an inner structure that is integrally formed with the tank wall and that extends into the tank volume, and said heating element extending over at least one third of the height of the tank volume and being electrically contacted outside the tank volume.

Abstract: A gimbaled rotor assembly for an aircraft. The gimbaled rotor assembly including a static mast; a spherical bearing comprising an inner component and an outer component pivotable relative to each other about a bearing focus, the inner component fixedly coupled to the static mast; a rotor hub rotatably coupled to the outer component, allowing for relative rotation of the rotor hub about a rotor axis and for pivoting together with the outer component about the bearing focus; and a primary hub spring coupling the outer component to the static mast and configured for opposing pivoting of the rotor hub about the bearing focus from a neutral position.

Abstract: An air intake system for an aircraft, which is switchable between a performance mode and a filtered mode, includes a duct forming filtered air inlet slits. The air intake system also includes interconnected gills adjacent to the filtered air inlet slits. The gills are movable between various gill positions including a closed position substantially covering the filtered air inlet slits and an open position substantially exposing the filtered air inlet slits. The air intake system also includes an actuator configured to move the gills into the closed position in the performance mode and the open position in the filtered mode.

Abstract: A method of constructing a fuel cell system includes providing an open cell structure to form a first end plate, filling at least part of the open cell structure with a stiffening material, disposing a fuel cell stack between the first end plate and a second end plate, and compressing the fuel cell stack by moving the first end plate toward the second end plate. A fuel cell system includes a first end plate comprising an open cell structure, a second end plate, and a fuel cell stack compressed between the first end plate and the second end plate.

Abstract: An aircraft including a nacelle configured as a housing for an engine and 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 hingedly coupled to the proprotor housing by a first hinge joint and hingedly coupled to the nacelle by a second hinge joint. An aspect includes an aircraft with a proprotor coupled to a wing member, the proprotor comprising a forward portion and an aft portion; wherein the forward portion is configured to selectively pivot between a horizontal orientation and a non-horizontal orientation about a conversion axis C; and wherein when the forward portion is in a non-horizontal orientation, the aft portion is in a horizonal orientation.

Abstract: A gear system includes a gear assembly having a shaft that is at least partially disposed within a housing of the gear system. A thrust bearing has inner and outer races with the outer race coupled to the housing. A bearing flexure is disposed between the inner race of the thrust bearing and the shaft. The bearing flexure includes a cylindrical cage having at least one shaft journal ring and a plurality of circumferentially distributed axially extending fingers coupled thereto with the shaft journal ring coupled to the shaft. A cylindrical bearing journal has inner and outer surfaces with the outer surface coupled to the inner race of the thrust bearing. Each of a plurality of circumferentially distributed radially extending struts extends between one of the fingers and the inner surface of the cylindrical bearing journal. The bearing flexure has an axial stiffness that is greater than its radial stiffness.

Abstract: An internal battery heating system includes an electrical conversion device electrically coupled to an electrochemical sub-cell or battery modules to form a heating circuit. The electrical conversion device alternately raises and lowers a voltage of the heating circuit to drive current between the heating circuit and the electrochemical sub-cell or battery modules. A controller commands the electrical conversion device to cyclically charge and discharge the electrochemical sub-cell or battery modules for internally heating the battery modules. Alternatively, a battery module may be electrically coupled to electrochemical sub-cells via pairs of switches to form a heating circuit. The pairs of switches are adapted for switching the heating circuit alternately between a parallel arrangement and a series arrangement to alternate charging and discharging of the battery module which results in internal heating of the battery module.

Abstract: The present invention discloses a method and operating liquid container system for controlling the internal pressure of an operating liquid container of a motor vehicle, wherein the method includes determining an internal pressure of the operating liquid container by means of a pressure sensor arranged in an operating liquid container interior; comparing the determined internal pressure with a predetermined maximum internal pressure by means of an electronic control device; outputting an opening signal from the control device to a vent valve that is arranged in a vent line or between the operating liquid container interior and the vent line, wherein the vent line fluidically connects the operating liquid container interior to the atmosphere when the determined internal pressure is equal to the maximum internal pressure or above the maximum internal pressure; and transferring the vent valve into an open position.

Abstract: A proprotor system for a ducted aircraft convertible between a vertical takeoff and landing flight mode and a forward flight mode includes a plurality of proprotor blades and a duct surrounding the proprotor blades. The duct includes an adaptive geometry device movable into various positions including a hover position and a cruise position. One or more actuators coupled to the adaptive geometry device are configured to move the adaptive geometry device between the hover position and the cruise position based on the flight mode of the ducted aircraft, thereby improving flight performance of the ducted aircraft.