Abstract: An aircraft includes a fuselage and a wing assembly that is rotatable between a substantially perpendicular orientation relative to the fuselage in flight modes and a substantially parallel orientation relative to the fuselage in a wing stowage mode. The wing assembly includes a wing that is pivotable between forward flight and VTOL orientations by a pivot angle. A distributed thrust array is coupled to the wing that includes outboard and inboard propulsion assemblies, each propulsion assembly having an axis of rotation that has a fixed angle relative to a chord axis of the wing. In a VTOL flight mode, the axis of rotation of each propulsion assembly is substantially vertical and the wing is in the VTOL orientation. In a forward flight mode, the wing is in the forward flight orientation and the axis of rotation of each propulsion assembly is tilted forward from the vertical by the pivot angle.

Abstract: A method for controlling a filling process of a motor vehicle tank comprising the following steps: determine a geographical location of the motor vehicle tank; determining, by means of a tank control device, whether the geographical location of the motor vehicle tank is within a predetermined geographical area; and determining a shut-off filling volume dependent on the geographical location of the motor vehicle tank, if the geographical location of the motor vehicle tank is within the predetermined geographical area.

Abstract: A tiltrotor aircraft is described and includes a rotor system, a pylon coupled to the rotor system, a spindle coupled to the pylon, an actuator arm coupled to the spindle, and an actuator. The actuator can cause the actuator arm to rotate, thereby causing the spindle to rotate the pylon and the rotor system. In an example, the actuator is in front of a forward spar of the wing of the tiltrotor aircraft and the actuator arm is about one-half (0.5) of an inch to about five (5) inches from the wing.

Abstract: In an embodiment, a battery connector includes: power terminals configured to be coupled to a load having an input capacitance; power pins electrically coupled to the power terminals; a charge pin, the charge pin being longer than each of the power pins; and an antispark circuit electrically interposed between the charge pin and the power terminals, the antispark circuit including: a dissipation circuit configured to charge the input capacitance of the load in response to a battery being coupled to the charge pin; and a delay circuit configured to delay charging of the input capacitance of the load for a predetermined duration after the battery is coupled to the charge pin.

Abstract: An aircraft includes a fuselage airframe and a wing airframe that is subject to flight loads. The fuselage airframe includes fore/aft floor beams having a plurality of floor intercostals laterally extending therebetween and fore/aft roof beams with a plurality of roof intercostals laterally extending therebetween. Each of a plurality of cabin frames extends generally vertically between respective floor and roof beams. The wing airframe includes forward and aft wing spars with a plurality of wing ribs extending therebetween. At least one fuel tank, that is configured to contain a pressurized fuel such as pressurized hydrogen fuel, integrally forms at least a portion of one of the beams, the intercostals, the frames, the spars and/or the ribs such that the fuel tank is subject to the flight loads.

Abstract: Systems, methods and non-transitory computer readable storage media for airspace management within an airspace region at a node of a peer to peer network having a plurality of nodes and maintaining a blockchain containing a current deconflicted flight schedule for the airspace region. One method includes receiving requests for airspace reservations, each including flight plan data, from other nodes over the peer to peer network, compiling the flight plan data to identify conflicts between the requests and the current deconflicted flight schedule, validating the flight plan data of the requests that do not conflict with the current deconflicted flight schedule to generate validated airspace reservations, creating a block containing the validated airspace reservations and interlinking the block with the blockchain such that the blockchain contains a new deconflicted flight schedule for the airspace region for broadcast to the other nodes over the peer to peer network.

Abstract: Techniques involve utilizing a multi-track cargo handling assembly to guide individual cargo items in parallel tracks to an aft end of a deck of an amphibious air cushion vehicle when unloading from the aft end. Such a multi-track cargo handling assembly includes a framework constructed and arranged to couple with the deck of the amphibious air cushion vehicle, and a set of guide rails coupled with the framework. The set of guide rails defines the parallel tracks and is constructed and arranged to constrain movement of the cargo items along the parallel tracks.

Abstract: In accordance with one embodiment of the present disclosure, a method for manufacturing a honeycomb core sandwich panel includes placing a thermoset facesheet in contact with a thermoplastic honeycomb core without using a separate adhesive and attaching the thermoset facesheet to the thermoplastic honeycomb core by using a curing profile comprising a temperature that is lower than a gel point temperature of the thermoset facesheet and higher than a softening point temperature of the thermoplastic honeycomb core.

Abstract: A 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. Each of the battery modules includes a thermal conditioning system configured to thermally isolate the battery module from the other battery modules.

Abstract: An aircraft includes a fuselage and a wing system having first and second oppositely disposed wings that extend laterally from the fuselage. A tiltable propulsion system is rotatably coupled to the fuselage between the first and second wings. The tiltable propulsion system includes a frame system having four diagonally extending arms each having a propulsion assembly coupled thereto. A flight control system is configured to independently control each of the propulsion assemblies and the orientation of the tiltable propulsion system. In a VTOL flight mode of the aircraft, the tiltable propulsion system is substantially perpendicular to the aircraft's yaw axis in a vertical thrust orientation such that the propulsion assemblies are configured to provide vertical thrust. In a forward cruise flight mode of the aircraft, the tiltable propulsion system is substantially perpendicular to the aircraft's roll axis in a forward thrust orientation such that the propulsion assemblies provide forward thrust.

Abstract: A rotor system comprising a driveshaft; at least one motor for providing rotational energy for the driveshaft; an overrunning clutch connected to the motor and disposed around the driveshaft, wherein the overrunning clutch is rotated by the at least one motor; and a pump assembly associated with the at least one motor, the pump assembly comprising a large bore through which the driveshaft passes such that the pump assembly is arranged concentric to the driveshaft, the pump assembly further comprising a gerotor pump comprising inner and outer gerotor pump gears, wherein an inner bore of the gerotor pump engages and is driven by the overrunning clutch; and a cover disposed over the gerotor pump for providing a sump for the gerotor pump.

Abstract: A light apparatus includes an array of light-emitting diodes (LEDs) in parallel arrangement, in which the LEDs have respective first terminals coupled together for connection to a supply node of a power source that provides the drive current to the LEDs during operation. Driver circuity is disposed between respective second terminals of the LEDs and a return node of the power source. The driver circuitry includes a respective LED driver for each of the LEDs, and each LED driver includes (1) a transistor connected to the second terminal of the respective LED, and (2) a resistor in series between the transistor and a return node of the power source, the transistors of the LED drivers having respective control inputs for receiving respective LED drive signals to control operation of the LEDs.

Abstract: A rotor system for an aircraft is described and includes an open rotor assembly comprising a plurality of rotor blades connected to a rotor mast; and a drive system for providing rotational energy to the open rotor assembly via the rotor mast. The drive system includes at least one electric motor for providing rotational energy to a motor shaft; and a gearbox connected to the drive shaft for receiving rotational energy from the at least one electric motor via the motor shaft and providing rotational energy to the rotor mast via a rotor shaft.

Abstract: A configurable electrical architecture for an eVTOL aircraft having a takeoff and landing power mode and a cruise power mode. The configurable electrical architecture includes a power-optimized power source including a high-power battery array and an energy-optimized power source selected from a plurality of interchangeable energy-optimized power sources including a high-energy battery array, a hydrogen fuel cell system and a turbo-generator system. A distribution system is electrically coupled to the power-optimized power source and the energy-optimized power source. At least one electric motor is electrically coupled to the distribution system. In the takeoff and landing power mode, both the power-optimized power source and the energy-optimized power source provide electrical power to the at least one electric motor.

Abstract: A method for determining an aggregate state of an operating liquid in an operating liquid container for a motor vehicle, which operating liquid container has at least one capacitor fastened to a container wall of the operating liquid container and has a first electrode and a second electrode opposite said first electrode. A first method determines the aggregate state of the operating liquid by means of a frequency-dependent phase profile of the impedance of the at least one capacitor. Another method determines the aggregate state of the operating liquid by means of a frequency-dependent capacitance profile of the at least one capacitor. Further, an operating liquid container is designed for carrying out the methods.

Abstract: A removable and portable storage tote for an under seat storage system that comprises a front side constructed of a pliable material, a back side constructed of the pliable material, a left side constructed of the pliable material, a right side constructed of the pliable material, a bottom connected to the front side, the back side, the left side and the right side, and a top side constructed of a pliable material, that is hingedly connected to the back side and selectively connectable to the left side, right side and front. The storage tote additionally comprises a plurality of tether mechanisms attached to at least one of the front side, back side, left side and right side that are structured and operable to removably retain the tote within a cavity beneath a seat of a vehicle.

Abstract: A yaw control system coupled to a tailboom of a helicopter includes tail rotors. The tail rotors include a clockwise tail rotor and a counterclockwise tail rotor. The clockwise tail rotor is configured to rotate in a first rotational direction. The counterclockwise tail rotor is configured to rotate in a second rotational direction, the second rotational direction opposite of the first rotational direction.

Abstract: An architecture for an electric distributed propulsion system includes one or more generators connected to a gearbox, a first and a second plurality of motors connected to the one or more generators, each motor of the plurality of motors connected to a blade to provide thrust, a first and a second power bus electrically connected between the one or more generators and the first and the second plurality of motors, each power bus independent of the other power bus, a first and a second controller independently connected to each of the first and second plurality of motors, each of the first and second controllers serving as a primary and a backup controller, and dual channels in communication between pilot input sensors and the first and the second controllers, and the dual channels including an additional channel to provide redundant communication to the first and second controllers.

Abstract: One embodiment is a navigation system for an aircraft including a positioning system to generate information related to a position of the aircraft, a group of cameras mounted to a body of the aircraft, each camera of the group of cameras to simultaneously capture images of a portion of an environment that surrounds the aircraft, and a processing component coupled to the positioning system and the group of cameras, the processing component to determine a current position of the aircraft based on the information related to the position of the aircraft and the images.

Abstract: A transition duct assembly includes a shared connector, and a plurality of primary cooling pathways for cooling one or more systems or components. Each primary cooling pathway includes a transition duct in fluid communication with the shared connector, and a transition connector in fluid communication with the transition duct.