Abstract: In one aspect, there is a method of making a pre-cured laminate having a total number of plies in a mold, the mold having a periphery defined by a forward edge, an aft edge, and outboard ends. The method includes selecting a first plurality of resin impregnated plies that continuously extend beyond the periphery of the mold, the first plurality of resin impregnated plies includes at least 50 percent of the total number of plies; laying the plies in a mold; compacting the plies in a mold; and pre-curing the plies to form a pre-cured laminate, which can extend beyond the periphery of the mold. In an embodiment, a pre-cured laminate includes a first plurality of resin impregnated plies that continuously extend beyond the periphery of the mold, the first plurality of resin impregnated plies includes at least 50 percent of the total number of plies.

Abstract: In some embodiments, an aircraft includes a flying frame having an airframe, a distributed propulsion system attached to the airframe, a flight control system operably associated with the distributed propulsion system and a pod assembly selectively attachable to the flying frame. The distributed propulsion system includes a plurality of propulsion assemblies that are independently controlled by the flight control system, thereby enabling the flying frame to have a vertical takeoff and landing mode and a forward flight mode.

Abstract: In some embodiments, a passenger pod assembly transportation system includes a transportation services provider computing system and a plurality of flying frame flight control systems, wherein the system is configured to receive, at the transportation services provider computing system, a request for transportation of a passenger pod assembly having a current location and a destination; upload a flight plan to a flight control system of a flying frame including an airframe and a propulsion system; dispatch the flying frame to the current location of the passenger pod assembly; couple the flying frame to the passenger pod assembly at the current location of the passenger pod assembly; transport the passenger pod assembly by air from the current location of the passenger pod assembly to the destination of the passenger pod assembly; and decouple the passenger pod assembly from the flying frame at the destination of the passenger pod assembly.

Abstract: In some embodiments, an aircraft includes a flying frame having an airframe with first and second wing members having a plurality of pylons extending therebetween, a distributed propulsion system including a plurality of propulsion assemblies securably attached to the airframe and a flight control system operably associated with the distributed propulsion system. The flying frame has a vertical takeoff and landing mode with the wing members disposed in generally the same horizontal plane and a forward flight mode with the wing members disposed in generally the same vertical plane.

Abstract: An aircraft having a vertical takeoff and landing fight mode and a forward flight mode. The aircraft includes an airframe and a versatile propulsion system attached to the airframe. The versatile propulsion system includes a plurality of propulsion assemblies. A flight control system is operable to independently control the propulsion assemblies. The propulsion assemblies are interchangeably attachable to the airframe such that the aircraft has a liquid fuel flight mode and an electric flight mode. In the liquid fuel flight mode, energy is provided to each of the propulsion assemblies from a liquid fuel. In the electric flight mode, energy is provided to each of the propulsion assemblies from an electric power source.

Abstract: A method of limiting vertical axis augmentation in a rotorcraft, the method comprising: measuring a torque with a sensor; deriving a comparison of the torque to a lower torque limit, using a computer processor; and adjusting a vertical axis control command based upon the comparison of the torque to the lower torque limit.

Abstract: A propulsion system for a tiltrotor aircraft includes an engine supported by the airframe and a fixed gearbox operably coupled to the engine. Inboard and outboard tip ribs extend above the wing and define slots. Inboard and outboard bearing cartridges are received in respective slots. The inboard and outboard bearing cartridges respectively include inboard and outboard bearing assemblies. A pylon assembly is rotatably coupled between the inboard and outboard bearing assemblies. The pylon assembly includes a spindle gearbox having an input gear, a mast operably coupled to the input gear and a proprotor assembly operable to rotate with the mast. The spindle gearbox is rotatable about a conversion axis to selectively operate the tiltrotor aircraft between helicopter and airplane modes. A common shaft, rotatable about the conversion axis, is configured to transfer torque from an output gear of the fixed gearbox to the input gear of the spindle gearbox.

Abstract: In some aspects, a wireless system is configured for estimating a thickness of a material layer on a surface of an aircraft. The wireless system includes a tag device located beneath a material layer. The tag device is capable of transmitting an electromagnetic signal in response to an electromagnetic signal. In some aspects, a transceiver device is configured to estimate the thickness of a material layer on a surface of an aircraft. The transceiver can be configured to communicate with a tag using electromagnetic signals. The transceiver can include one or more processors configured to measure signal strength and correlate the signal strength to the thickness of a material layer.

Abstract: The invention concerns a process for the production of a container, in particular a fuel tank of thermoplastic material, by extrusion blow molding, wherein during shaping of the container within a multi-part tool the container is provided with at least one connecting element passing through the wall thereof, wherein with at least a part of the connecting element as a lost shaping male die the wall of the container is displaced from one side into a tool placed on the oppositely side of the container wall and removed. The invention further concerns a fuel tank with at least one connecting element which is connected to the tank wall at least in region-wise manner by intimate joining of the materials involved.

Abstract: A drive coupling has first and second coaxial end adapters. A first set of at least two coaxial helical elements has a first end of each element attached to the first end adapter, and a second end of each element is coupled to the second end adapter. At least one biasing device biases the end adapters relative to each other. Torque applied to one of the end adapters is transferred through the first set of helical elements to the other end adapter, the helical elements allowing for misalignment of the end adapters during operation.

Abstract: Complex laminated composites may be repaired by removal of individual damaged plies through peeling in order to exploit the weaker interlaminar properties of these composites. Upon removal of the individual damaged plies through peeling, replacement plies may be added to restore the laminated composite. In addition, when damage extends through the thickness of a laminated composite, a plug may be used to allow plies to be replaced while maintaining contour within the repair region. A caul plate also may be used to stiffen and maintain the contour of a repair region while peeling and removing plies from the repair region.

Abstract: A method of repairing a core stiffened structure, including removing a damaged portion of the core stiffened structure; bonding a shelf onto a first core member; bonding a second core member to a shelf; and securing a skin patch over the second core member.

Abstract: A method and apparatus provide for automatically controlling the flight of a tiltrotor aircraft while the aircraft is in flight that is at least partially rotor-borne. The method and apparatus provide for automatically tilting nacelles in response to a longitudinal-velocity control signal so as to produce a longitudinal thrust-vector component for controlling longitudinal velocity of the aircraft. Simultaneously, cyclic swashplate controls are automatically actuated so as to maintain the fuselage in a desired pitch attitude. The method and apparatus also provide for automatically actuating the cyclic swashplate controls for each rotor in response to a lateral-velocity control signal so as to produce a lateral thrust-vector component for controlling lateral velocity of the aircraft. Simultaneously, collective swashplate controls for each rotor are automatically actuated so as to maintain the fuselage in a desired roll attitude.

Abstract: An automated bender and its method of operation according to some embodiments of the disclosure is provided. The automated bender includes a carousel which has all of the necessary components for bending a variety of conduit sizes provided thereon. The carousel can be rotated to a desired bending position to bend a particular type of conduit. A straight workpiece is fed into the automated bender and a bent workpiece, which may have multiple bends therein, is output from the automated bender. This bending process is performed without manual intervention. Software for achieving same is provided.

Abstract: According to one embodiment, a method of dispersing nanoparticles into a destination material includes providing a plurality of nanoparticles suspended in a carrier, adding a solvent to the plurality of nanoparticles suspended in a carrier, removing at least some of the carrier to yield the plurality of nanoparticles suspended in the solvent, mixing the nanoparticles suspended in the solvent with a destination material, and removing at least some of the solvent from the mixture of nanoparticles suspended in the solvent and the destination material.

Abstract: According to one embodiment, a bearing features an elastomeric portion having an opening therethrough, a member disposed within the opening of the elastomeric portion, and a separation feature disposed between the member and the elastomeric portion. The member comprises a conical body portion arranged such that an interior diameter of the conical body portion is smaller than an exterior diameter of the conical body portion. The separation feature prevents contact between the member and the elastomeric portion.

Abstract: A system and method for automatically controlling an engine of a turf-care vehicle. The method comprises receiving, at an engine speed control module, a mode selection input from an engine speed control mode selection device. The mode selection input is indicative of one a plurality of engine speed control modes, and all of the engine speed control modes are implementable by the engine speed control module. The method additionally comprises monitoring, via the engine speed control module, an operating status of one or more vehicle systems and/or one or more vehicle sensors. The method further comprises automatically controlling, via the engine speed control module, a rotational speed of the engine based at least in part on the selected engine speed control mode and the operating status of the one or more vehicle systems and/or one or more vehicle sensors.

Abstract: Systems and methods are provided for statistically equivalent level of safety modeling. One method includes identifying sub-fleets within a fleet based upon usage profiles, determining a sub-fleet reliability value for each sub-fleet, determining a baseline fleet reliability for the fleet by combining the sub-fleet reliability values on a weighted basis, applying at least one credit to at least one sub-fleet, determining a post-credit sub-fleet reliability value for each sub-fleet based upon the at least one credit, determining a post-credit fleet reliability for the fleet by combining the post-credit sub-fleet reliability values on a weighted basis, comparing the baseline fleet reliability with the post-credit fleet reliability to identify a change in fleet reliability and determining whether the change in fleet reliability is within a predetermined threshold to validate the at least one credit.

Abstract: A control system having at least a first control loop and a second control loop for determining the upper and lower cyclic limit increments due to the contribution of collective pitch in rotorcraft based at least on nacelle angle and airspeed. The aircraft is more robustly controlled by generating flight control limits for the aircraft, modifying the flight control limits based upon impending hazardous flight conditions, and adjusting a size of a flight control envelope as the aircraft transitions between non-hazardous flight conditions and hazardous flight conditions.

Abstract: A quick change height adjustment mechanism allows a reel stand to accommodate differently sized storage spools. The mechanism includes a plate, a locking pin and a pivot pin. The plate forms a cavity into which a post is seated and has at least one space which receive a spindle of the spool. The locking pin extends from the plate and into the cavity. The locking pin is vertically spaced from, and positioned on a first side of, a centerline of the plate. The pivot pin is attached to the plate, is vertically spaced from, and positioned on a second, opposite side of, the centerline. The pivot and locking pins are positioned on opposite sides of the post. In use, the plate can be pivoted relative to the post around pivot pin to engage or disengage the locking pin with holes in the post.