Abstract: Methods and systems for automated placement of composite material on a surface of a component, the composite material including unidirectional fibers, is provided. A set of fiber paths along the surface is established, the set of fiber paths comprising at least one ply, each ply comprising a respective plurality of fiber paths being substantially aligned with a respective direction. An isotropy factor for the component is determined based on the set of fiber paths, the isotropy factor being indicative of a distribution of the plurality of fiber paths on the surface. When the isotropy factor exceeds a predetermined threshold, a respective layer of composite material is applied to the surface of the component using an automated fiber placement machine and for each of the at least one ply, wherein the unidirectional fibers of the composite material are applied along the set of fiber paths.

Abstract: A rotorcraft has a rotor blade having a spar comprising an internal space. A weight system is disposed within the spar and the weight system includes a weight tray having an open top, a weight guide rod connected to the weight tray. The weight guide rod extends in a spanwise direction through an interior of the weight tray and a weight is disposed on the weight guide rod and vertically captured by at least one side wall of the weight tray. The weight guide rod is insertable into the weight tray from a location above the weight tray to restrict longitudinal movement of the weight guide rod relative to the weight tray.

Abstract: A landing wheel assembly for a rotorcraft having a light on gear phase during takeoff and landing includes a tire and an anti-roll oscillation rim. The tire has first and second side walls and forms a center aperture. The anti-roll oscillation rim includes a center disc disposed in the aperture of the tire, a first side wall support plate protruding from the center disc and extending at least 25 percent of the vertical length of the first side wall of the tire and a second side wall support plate protruding from the center disc and extending at least 25 percent of the vertical length of the second side wall of the tire. The first and second side wall support plates support the first and second side walls, respectively, to stiffen the tire in the light on gear phase of takeoff and landing, thereby reducing roll oscillations of the rotorcraft.

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: One embodiment is an aircraft comprising a fuselage; a rotor system connected to the fuselage and comprising at least one rotor blade; a pilot input device; a single hydraulic servo actuator in mechanical communication with the pilot input device and the rotor system for providing force assistance in connection with the pilot input device; and a magnetorheological (MR) actuator in mechanical communication with the pilot input device and the rotor system for providing auto pilot assistance in connection with the pilot input device; wherein subsequent to detection of a failure of the single hydraulic servo actuator, the MR actuator is caused to provide force assistance to the pilot input device.

Abstract: A table is incorporated into an aircraft staircase design. The table can be deployed when the stairs are stowed inside the aircraft cabin area. The table is upwardly biased such that when it is released from a locking mechanism the table flips up to horizontal.

Abstract: A tailsitter aircraft includes an airframe having first and second wings with first and second pylons extending therebetween, a thrust array attached to the airframe, payloads and payload saddle assemblies coupled to the pylons each configured to secure a respective payload. The thrust array includes propulsion assemblies configured to transition the airframe between a forward flight orientation for wing-borne lift and a VTOL orientation for thrust-borne lift. Each payload saddle assembly includes a latch assembly and a retainer configured to secure the respective payload against a respective pylon. A latch assembly is movable between various positions including an open position and a closed position and is configured to secure the respective payload in the closed position and release the respective payload in the open position. Each latch assembly is configured to move from the closed position to the open position to release the respective payload in the VTOL orientation.

Abstract: An aircraft includes a fuselage, a pylon, a wing positioned between the fuselage and the pylon, and a plurality of drive shafts located inside the wing and adapted to drive a rotor associated with the pylon.

Abstract: An engine support truss assembly for aircraft includes a mounting plate having a front side and a back side opposite the front side, a truss structure mechanically coupled to the front side of the mounting plate, and a backup structure mechanically coupled to the back side of the mounting plate. The truss structure includes a plurality of structural members each including precipitation-hardened stainless steel. The backup structure is configured to provide mechanical support to the truss structure.

Abstract: A track door system for an aircraft includes a door having a first side and a second side opposite the first side. A first roller track and a second roller track are aligned adjacent one another on the first side of the door. A third roller track and a fourth roller track are aligned adjacent one another on the second side of the door. A first motion driver is configured to move the door along the first roller track and the second roller track. A second motion driver is configured to move the door along the third roller track and the fourth roller track. A drive unit is operatively coupled to the first motion driver and the second motion driver to provide electromechanical power for cooperatively moving the door forward to an open position or aft to a closed position.

Abstract: An aircraft is described and includes a fuselage; wings attached to the fuselage; and a torque box within the fuselage, the torque box including a side panel, the side panel comprising a composite laminate material including a plurality of stiffening beads integrated therewith.

Abstract: A fuel-cell system for powering an electrical load, the system having first and second fuel cells, each having a positive node and a negative node. The positive node of the second fuel cell is electrically coupled to the negative node of the first fuel cell, and the positive node of the first fuel cell and the negative node of the second fuel cell are electrically coupled to the electrical load. Each fuel cell is electrically coupled to the electrical load without a power converter.

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.

Abstract: A pump assembly, comprising a pump and housing having an inlet passage and an outlet passage. The pump includes inlet and outlet ports and opposing first and second drive inputs configured to be rotated together in a pumping direction to operate the pump. The pump can be installed in the housing in a first orientation, in which the first drive input is configured for being rotated by a drive source in a first external direction to operate the pump, and a second orientation, in which the second drive input is configured for being rotated by the drive source in a second external direction opposite of the first external direction to operate the pump. In both the first orientation and the second orientation, the inlet port is in fluid communication with the inlet passage and the outlet port is in fluid communication with the outlet passage.

Abstract: A Bluetooth plus radio frequency identification (RFID) beacon for use vehicle fleet management and geofencing system, wherein the beacon comprises a housing, and a circuit board disposed within the housing. The circuit board comprises a Bluetooth communication circuitry portion containing a unique media access control (MAC) address, and an RFID circuitry portion integrated with the Bluetooth communication circuitry portion such that the RFID circuitry portion is associated with the Bluetooth circuitry MAC address whereby the Bluetooth beacon can be identified, via the MAC address, by an RFID reader communicating with the RFID circuitry portion using the MAC address of the Bluetooth communication circuitry portion.

Abstract: A rotorcraft has a rotor blade having a spar comprising an internal space. A weight system is disposed within the spar and the weight system includes a weight tray having an open top, a weight guide rod connected to the weight tray. The weight guide rod extends in a spanwise direction through an interior of the weight tray and a weight is disposed on the weight guide rod and vertically captured by at least one side wall of the weight tray. The weight guide rod is insertable into the weight tray from a location above the weight tray to restrict longitudinal movement of the weight guide rod relative to the weight tray.

Abstract: A chip agitation system for use on a rotorcraft with an engine and transmission system. The chip agitation system is configured to produce a mass flux of fluid to agitate chip debris towards a chip detection device. The chip agitation system includes a reservoir and valve that can be selectively opened and closed.

Abstract: An elastomeric bearing has a first end interface, a second end interface, an activation element disposed between the first end interface and the second end interface, and a clutch component disposed between the activation element and the second end interface. A method of operating an elastomeric bearing includes providing a first end interface, providing a second end interface, providing an activation component between the first end interface and the second end interface, providing a clutch component between the activation component and the second end interface, and rotating the first end interface relative to the second interface to cause rotation of the clutch component relative to the second end interface.

Abstract: One embodiment is a rotor assembly for an aircraft, the rotor assembly comprising a plurality of rotor blades, wherein at least one of the rotor blades comprises a rotor alignment drag assembly comprising a drag structure on a surface of the at least one of the rotor blades, wherein the drag structure is moveable between a first position in which the drag structure is stowed within the at least one of the rotor blades, and a second position in which the drag structure is extended from the surface of the at least one of the rotor blades; and an actuation mechanism for moving the drag structure from the first position to the second position when a speed of the rotor assembly falls below a first threshold speed.