Abstract: A method and apparatus for reconfiguring flight control of an aircraft during a failure while the aircraft is flying. The method and apparatus provide a control law that is software-implemented and configured to automatically send flight control data to a mixing/mapping matrix. The method and apparatus also provide a reconfiguration management tool configured to communicate with the mixing/mapping matrix in order to safely transfer authority from a failed actuator to a back-up actuator. The method and apparatus also provide a sensor management tool for providing input to the reconfiguration management tool in order to smooth any transient conditions that may occur during reconfiguration. The method and apparatus provide for a way of smoothing any possible transient situation that might otherwise occur by employment of a fader, the fader being used to gradually convert positioning of failed actuators and positioning of reconfigured actuators.

Abstract: A hybrid overrunning clutch includes a metal outer race and a composite outer ring that are each sized and configured such that the metal race generates a preload on the composite outer race throughout the operational temperature of the clutch. The composite outer ring significantly reduces that total weight of the clutch, as compared to a completely metal outer race. The present application further includes a method of assembling the metal outer race and composite outer ring so that thermal expansion of the metal outer race creates the preload in the composite outer ring. The present application also includes a method of designing a hybrid overrunning clutch.

Abstract: The invention relates to a fuel tank for a motor vehicle, which is made up of two shells which are complementary to one another, wherein the shells are supported against one another by at least one strut penetrating the tank (1), connecting opposing wall regions of the tank. The strut is configured as a two-part hollow strut (4), wherein the parts of the hollow strut are latched together via a plug connection and the latching connection is secured by at least one closure body (12) at least partially filling up the cross section of the hollow strut (4) at least level with the latching connection.

Abstract: A system and method to detect non-ferrous debris from a non-ferrous roller bearing element. The system includes a trap in fluid communication with a lubrication fluid of the non-ferrous bearing and a sensor operably associate with the trap. The method includes trapping the non-ferrous material debris in the lubrication fluid with the trap and triggering the sensor upon detection of the non-ferrous material debris trapped within the trap.

Abstract: A damper system includes a damper and a heater operably associated with the damper. The method includes heating the damper with heat energy from the heater and then monitoring and regulating the heat energy to the damper with a sensor and control subsystem.

Abstract: A rotor hub and method to dampen a force exerted on a rotor hub by a rotor blade during flight. The rotor hub including a central member rotatably coupled to a rotor mast, a blade grip rigidly attached to a blade and movably coupled to the central member, and an adjustable damper operably associated with the blade grip. The method includes damping the force exerted on the rotor hub with the adjustable damper and selectively adjusting the adjustable damper between a first spring rate and a second spring rate.

Abstract: A blow molding tool (1) for producing a plastic article, in particular a fuel tank, comprising at least one clamping frame (2) with mold clamping devices (3) and at least two blow mold halves, which are formed such that they can be moved together and apart by means of an opening and closing movement of the clamping frame (2) and which respectively have at least one cavity (8) for the forming of the plastic article, the blow molding tool (1) being distinguished by the fact that the mold clamping devices (3) respectively have at least one tool holder (6), in which a mold insert (7) is in each case exchangeably inserted, and in that the tool holders (6) respectively form a peripheral sealing edge (10).

Abstract: According to one embodiment, a helicopter rotor system has a bearing disposed between the drive train and the rotor blade. The bearing comprises an elastomeric material, a housing member coupled to the elastomeric material, and an anti-rotation member coupled to the housing member opposite the elastomeric material. A bearing mount is coupled to the grip and comprises a first opening configured to receive the anti-rotation member of the bearing. The first opening is defined at least in part by a first surface that receives the anti-rotation member and prevents the anti-rotation member from completing a rotation within the first opening.

Abstract: A test system for testing a sensor system includes a high-impedance resistor for forming a voltage divider with any corrosion or foreign substance that might be present between a signal conductor and a ground conductor. While a voltage is applied across the voltage divider, the voltage can be measured across the high-impedance resistor for determining whether an undesirable amount of conductance exists between the signal wire and ground. The test system also includes switching means for switching between any number of signal wires of a system undergoing testing.

Abstract: According to one embodiment, a rotorcraft pitch link includes a housing and a piston assembly. The housing comprises a first chamber and a second chamber. A first housing opening allows a first fluid to flow into the first chamber, and a second housing allows a second fluid to flow into the second chamber. The piston assembly is at least partially disposed within the housing and comprises a piston head and a piston rod coupled to the piston head. The piston head separates the first chamber from the second chamber.

Abstract: The present application includes a rotor blade having an erosion protective coating, the coating being a cermet material configured to protect against erosion during the operation of the rotor blade. Further, the present application includes a method of selectively applying the erosion protective coating, a method of selectively repairing/reapplying the erosion protective coating, and a process of developing an erosion surface model map of an optimized erosion protective coating pattern and thickness.

Abstract: A movable seat assembly for a vehicle comprises a predetermined path having an operational location at a first end and an ingress/egress location at a second end, and a seat that travels along the predetermined path between the operational location and the ingress/egress location, wherein the seat has an operational orientation at the operational location and an ingress/egress seat orientation at the ingress/egress location; the ingress/egress seat orientation being substantially angled relative to the operational seat orientation. Another moveable seat assembly for a vehicle comprises a predetermined path having an operational location at a first end, an ingress/egress location at a second end, and a standby location along the path there between; and a seat that travels along the predetermined path between the operational location, the standby location, and the ingress/egress location; wherein the position of the seat is adjustable at the operational location.

Abstract: An airfoil member can have a root end, a tip end, a leading edge, and a trailing edge. The airfoil member can include an upper skin, a lower skin, and a composite core member having a plurality of cells, an upper surface network of the cells can be bonded to the upper skin, a lower surface network of the cells can be bonded to the lower skin. The composite core can have a septum layer embedded in the cells that form the composite core, the septum layer being configured to provide tailored characteristics of the airfoil member.

Abstract: A method of attaching a composite member to a structure. The method including forming a laminate of fabric impregnated with resin; applying heat at a first temperature to the impregnated laminate; applying vacuum at a first pressure to the impregnated laminate to degas the resin and form a degassed, impregnated laminate; positioning the degassed, impregnated laminate on a structure; and curing the degassed, impregnated laminate on the substrate by applying heat at a second temperature and by applying vacuum at a second pressure.

Abstract: According to one embodiment, a condensation control system features a dew point analyzer, a fluid system, and a condensation control engine. The dew point analyzer provides a dew point temperature measurement of environmental conditions outside a fluid line having a refrigerant flowing therein. The fluid system provides a flow of insulating fluid to an insulation chamber at least partially separating the fluid line from environmental conditions outside the fluid line. The condensation control engine instructs the fluid system to provide the flow of insulating fluid to the insulation chamber at a temperature such that the temperature of the insulating fluid exiting the insulation chamber is greater than the dew point temperature measurement.

Abstract: A bi-directional drive system for turf grooming and brushing operations includes a first gear rotatably connected to a reel deck assembly. A reel shaft gear is connected to a reel shaft and rotated in a first axial rotation direction. Second and third gears are rotatably connected to the reel deck assembly. A double sided cogged belt is engaged to the reel shaft gear. An attachment member defining a turf component is rotated in the first axial rotational direction by rotation of the reel shaft gear connected to the first gear by the double sided cogged belt without rotation of the second and third gears. The turf component as a turf groomer is rotated in a second axial rotational direction opposite to the first axial rotational direction by rotation of the reel shaft gear connected to the first, second and third gears by the double sided cogged belt.

Abstract: A hydraulic press unit has a fixed part and a movable part. The movable part is moved relative to the fixed part by a hydraulic piston and is moved back into a starting position by a return spring. In addition, the return motion is actuatable as a function of a predetermined applied pressure by activation of a return valve. A control valve is provided which, in addition to the return valve, opens a hydraulic-medium outlet when in its open state and has a hydraulic-medium inflow side and a hydraulic-medium outflow side. In order to configure the hydraulic press unit, when the return valve opens, the control valve is acted on by the pressure of the returning hydraulic medium on the inflow and outflow sides, the pressure being lower on the inflow side due to throttling.

Abstract: A system and method for a controlling an aircraft with flight control surfaces that are controlled both manually and by a computing device is disclosed. The present invention improves overall flight control operation by reducing the mechanical flight control surface components while providing sufficient back-up control capability in the event of either a mechanical or power-related failure. Through the present invention, natural feedback is provided to the operator from the mechanical flight control surface which operates independent of computer-aided flight control surfaces. Further, through the present invention, force input signals received from the pilot are filtered to improve the operation of the computer-aided flight control surfaces.

Abstract: A vibration attenuator for an aircraft has at least one weight mounted in a rotating system of a rotor hub of the aircraft, each weight being rotatable about an axis of rotation of the hub relative to the hub and to each other weight. Drive means are provided for rotating each weight about the axis of rotation at a selected speed for creating oscillatory shear forces that oppose and attenuate rotor-induced vibrations having a selected frequency. A vertically oriented vibration attenuator is configured to oppose and attenuate vertical rotor induced oscillatory forces that would otherwise travel vertical down the rotor mast and into the airframe.

Abstract: A pylon mounting system with vibration isolation is provided. The system generally includes a housing that defines a first fluid chamber and a second fluid chamber, a fluid disposed within the fluid chambers; a piston assembly at least partially disposed within the housing, and a tuning passage defined by the piston assembly for providing fluid communication between the fluid chambers. The piston assembly has a first arm and a second arm, and each arm has a tubeform bearing for providing pitch and roll stiffness.