Abstract: An aerial resupply system (ARS) including a supply aircraft. The supply aircraft includes at least one of supply fuel, an ordinance, and data. The supply aircraft also includes a retractable boom system (RBS) configured for selective stowage within a fuselage of the supply aircraft and configured to supply at least one of supply fuel, the ordinance, and data to a location external to the fuselage.

Abstract: A battery housing arrangement, in particular a battery housing assembly of a vehicle traction battery which can be temperature-controlled by a fluid, comprises a battery housing which encloses an interior space for receiving battery cells, and a heat transmission device which has an inlet tube, an outlet tube and a heat exchanger element arranged fluidically therebetween. The fluid is able to flow through the heat transmission device from the inlet tube via the heat exchanger element to the outlet tube. The heat exchanger element can be accommodated in the battery housing. The battery housing has at least one through-opening for feeding through the inlet tube and the outlet tube, and the battery housing has at least one closure element which is inserted into the at least one through-opening and forms a closure between the inlet tube and/or the outlet tube and the at least one through-opening.

Abstract: A device for fastening tank insert parts, wherein the device has a holding element for holding the tank insert part and at least one elastically deformable clamping device which is connected to the holding element and by means of which a fastening structure can be received. Furthermore, a plastic tank having a fastening structure which is arranged in the interior thereof, and having a device according to the invention which is arranged thereon for fastening tank insert parts.

Abstract: One embodiment is an aircraft including first and second fuselages; a wing assembly connecting the first and second fuselages, wherein the first and second fuselages are parallel to one another; first and second forward propulsion systems tiltably attached to forward ends of the first and second fuselages; and first and second aft propulsion systems fixedly attached proximate aft ends of the first and second fuselages.

Abstract: A rotor-hub flap-measurement system includes a rotor hub operable to flap relative to a rotational axis of a rotor mast. The rotor hub includes a fork driver fixedly coupled to the rotor mast and operable to rotate about the rotational axis, a drive plate operable to rotate about the rotational axis and to rotate out of a plane perpendicular to the rotational axis, out-of-plane rotation indicating flapping of the rotor hub, and a universal joint coupled to the drive plate and comprising a cross, the cross comprising four trunnions equally spaced azimuthally about the rotational axis. The rotor-hub flap-measurement system also includes a magneto-resistive sensor system coupled to the cross and operable to detect rotation of a first trunnion of the four trunnions.

Abstract: A flight control computer (FCC) may implement automatic rotor tilt control by gathering or receiving, as inputs, airspeed or a commanded airspeed for the aircraft, acceleration or a commanded acceleration for the aircraft, pitch attitude of the aircraft and pilot pitch bias commands for the aircraft, a rotor tilt angle, and/or the like. The FCC calculates, from the airspeed, the commanded airspeed, the acceleration, the commanded acceleration, the pitch attitude, the pilot pitch bias commands, and/or the like, a commanded rotor tilt angle for the aircraft. From the aircraft rotor tilt angle and the commanded rotor tilt angle, the FCC calculates a rotor tilt angle error for the aircraft, and from the rotor tilt angle error, calculates a rotor tilt rate command for the aircraft. The FCC outputs the resulting rotor tilt rate command to (an) aircraft flight control element actuator(s) to tilt the aircraft rotor.

Abstract: A dual-motor system includes a first motor rotationally coupled to a first drive shaft. The first drive shaft is coupled to a common shaft couplable to a rotationally driveable member. The dual-motor system also includes a second motor rotationally coupled to a second drive shaft. The second drive shaft is coupled to the common shaft. The first motor and the second motor are coaxially aligned with the first drive shaft passing through the second drive shaft.

Abstract: A fuel-cell system at 540 VDC for powering an electrical load of a rotorcraft with a first fuel cell and a second fuel cell. Each fuel cell is configured identically and features a positive electrical node and a negative electrical node. Each fuel cell is configured to provide one half of the electrical load of the rotorcraft and one half of the voltage of the electrical load.

Abstract: A device to verify main rotor swashplate positioning includes an inner surface of a first section and a gradient surface of a second section. The gradient surface of the second section may have a plurality of graduation indications. In one implementation, the inner surface of the first section at least partially defines a travel arc that is parallel to and concentric with the inner surface. In such an implementation, the device may be configured to move along the travel arc as it rotates about a collective sleeve to contact a swashplate lug.

Abstract: A replaceable web structure for an aircraft frame is described and includes a plurality of structural members fabricated from a first type of material, the replaceable web structure comprising a plurality of web members fabricated from thin sheets of a second type of material, wherein each of the web members is fastened to a web frame of one of the structural members to replace a web portion of the one of the structural members; wherein the second type of material is stronger than the first type of material such that one of the sheets of the second type of material is lighter weight than a sheet of equal strength of the first type of material.

Abstract: A rotorcraft has a horizontal stabilizer movable about an axis of rotation and a horizontal stabilizer control system configured to control the horizontal stabilizer to at least one of move the rotorcraft into a minimum drag position, maintain the aircraft in a minimum drag position, efficiently achieve a maneuver, enter efficient autorotation, and maintain efficient autorotation.

Abstract: A seat base includes a plurality of linear actuators each having a first end pivotally mounted to a base member and a second end pivotally mounted to a seat member. A controller is adapted for controlling an extension length of each of the plurality of linear actuators in a coordinated manner for adjusting a position of the seat member with six degrees-of-freedom and for damping vibration of the seat member. An active vibration mitigation method for reducing vibrations of an aircraft seat includes receiving vibration data from one or more accelerometers mounted to the aircraft seat and determining a vibration profile based on the vibration data. When vibration mitigation is warranted, control signals for damping vibration are determined and transmitted to a plurality of linear actuators adapted to support the aircraft seat.

Abstract: A vibration attenuator has a first spinner configured for rotation about a first axis and a first mass coupled to the first spinner for rotation therewith, the first mass being movable radially relative to the first axis between an inner position and an outer position. An actuator is coupled to the first mass for selectively controlling a radial location of the first mass relative to the axis, and a first motor is configured for driving the first spinner in rotation about the first axis.

Abstract: A yaw control system for a helicopter having a tailboom includes one or more tail rotors rotatably coupled to the tailboom and a quiet mode controller. The quiet mode controller includes a noise monitoring module configured to monitor one or more flight parameters of the helicopter and a quiet mode command module configured to selectively switch the one or more tail rotors to a quiet mode based on the one or more flight parameters. The quiet mode command module is also configured to modify one or more operating parameters of the one or more tail rotors in the quiet mode to reduce noise emitted by the helicopter.

Abstract: A rotorcraft including a pilot control having a sensor that generates pilot control position data, a flight control that controls a flight characteristic of the rotorcraft, a trim system connected to the pilot control and configured to move the pilot control, and a flight control computer (FCC) configured to receive the pilot control position data from the sensor. The FCC executes a first flight control process and generates, according to the first flight control commands, a trim signal indicating a target position for the pilot control and to send the trim signal to the trim system to cause the trim system to attempt to move the pilot control to the target position to reflect a position of the flight control, and to monitor a working state of the trim system and execute a retrim process in response to determining that the trim system has failed.

Abstract: A tail rotor isolation system for rotorcraft includes a secondary engine, first and second freewheeling units, an isolation assembly and a tail rotor system. The secondary engine is coupled to the input race of the first freewheeling unit. A main rotor system is coupled to the output race of the second freewheeling unit. The isolation assembly is coupled to the output race of the first freewheeling unit and has a fully engaged position coupling the input and output races of the second freewheeling unit and a partially engaged position coupled to the input race but decoupled from the output race of the second freewheeling unit. The tail rotor system is coupled to the input race of the second freewheeling unit such that in the partially engaged position of the isolation assembly, the overrunning mode of the second freewheeling unit isolates the tail rotor system from the main rotor system.

Abstract: An aircraft is configured for thrust-borne lift in a vertical takeoff and landing flight mode and wing-borne lift in a forward flight mode. The aircraft includes an airframe having a first wing and a first payload station. A distributed propulsion system that is coupled to the airframe includes a plurality of propulsion assemblies configured to provide vertical thrust in the vertical takeoff and landing flight mode and forward thrust in the forward flight mode. A control system is operably associated with the distributed propulsion system and is operable to independently control each of the propulsion assemblies. A payload module is configured to be transported by the airframe from a pickup location to a delivery location. The payload module is magnetically coupled to the first payload station during transportation and, responsive to a command from the control system, is magnetically decoupled from the first payload station at the delivery location.

Abstract: An aircraft includes an airframe having at least one wing. A distributed propulsion system is attached to the airframe and includes first and second pluralities of propulsion assemblies. In a vertical takeoff and landing flight mode, each of the propulsion assemblies generates vertical thrust with rotor assemblies of the first plurality of propulsion assemblies rotating in a horizontal plane and rotor assemblies of the second plurality of propulsion assemblies rotating in a parallel horizontal plane. In a forward flight mode, each of the propulsion assemblies generates forward thrust with the rotor assemblies of the first plurality of propulsion assemblies rotating in a vertical plane and the rotor assemblies of the second plurality of propulsion assemblies rotating in a parallel vertical plane. In both the vertical takeoff and landing flight mode and the forward flight mode, a pod assembly coupled to the airframe remains in a generally horizontal attitude.

Abstract: A rotor assembly for generating vehicle thrust. The rotor assembly includes a rotor hub with a plurality of rotor blade assemblies coupled thereto. Each rotor blade assembly includes a metallic bearing race, a composite rotor blade and a split collet assembly. The split collet assembly includes two circumferentially distributed collet members each having an inner inboard conical seat configured to mate with a radially outwardly extending conical feature of the bearing race and an inner outboard conical seat configured to mate with a radially outwardly extending conical feature of the rotor blade. The split collet assembly also includes an outer sleeve having an inner conical surface that mates with outer conical surfaces of the collet members to maintain the collet members in a circumferential orientation around the bearing race and the rotor blade such that the split collet assembly provides a centrifugal force load path therebetween.

Abstract: Systems and methods are described for applying a self-heating structural adhesive to components of aircraft or other structures. A conductive scrim can be placed in between layers of adhesive for use in joining two components together. Leads can be provided to apply an electrical current to the scrim, which can raise the temperature of the system and cure the adhesives, creating a strong bond with a conductive layer there between.