Abstract: A punch assembly includes a punch, a sleeve, a draw stud and a die. The punch has a punch profile which provides a cutting edge that has a uniform “sharpness” along entire perimeter of the punch. The punch assembly provides additional punch-to-die clearance over what was done in the prior art. This reduces excessive punching forces which result from axial deflection of the draw stud and “tipping” of a large diameter punch as the draw stud deflects under a load.

Abstract: A system is provided in one embodiment for real-time detection of an object in a fluid without interfering with fluid flow. The system may include a sensor element coupled to a fluid passage, which can transmit energy substantially parallel to the flow direction of a fluid in the fluid passage and receive energy reflected from an incident object in the fluid. Reflected energy can also be analyzed as a function of object size and material such that an object can be classified or characterized through appropriate signal analysis. A method is provided in another embodiment for detecting an object in a fluid passage. The method may include transmitting ultrasonic energy through an interface membrane into the fluid and receiving ultrasonic energy reflected from the object. A pressure change in the reflected ultrasonic energy may be measured and converted to a signal for an output device.

Abstract: The electrical harness system is configured for routing a harness between a rotor yoke and a rotor blade. A recess in an inboard cap member is configured to house a connector and an associated harness. As the recess extends along a radial path in the chordwise direction of the rotor blade, the harness is configured to lie within the recess. Operationally induced centrifugal forces promote positioning the slack of harness within the recess, while the slack in the harness remains available for relative dynamic movements between the rotor blade and the rotor yoke. Such a routing of the harness reduces aerodynamic drag and minimizes damage that could otherwise occur to the harness.

Abstract: A restraint system for a transmission in an aircraft can include a first strut having a first fluid chamber, a first piston resiliently coupled to a first housing with a first elastomeric member. The restraint system can include a second strut having second fluid chamber, a second piston resiliently coupled to a second housing with a second elastomeric member. The restraint system can include a fluid line between the first fluid chamber and the second fluid chamber. The first strut and the second strut collectively provide not only torque restraint, but also torque measurement and fore/aft vibration isolation.

Abstract: A vibration isolator can include an upper housing defining an upper fluid chamber; a lower housing defining a lower fluid chamber; a piston resiliently coupled to the upper housing with an upper elastomer member, the piston being resiliently coupled to the lower housing with a lower elastomer member; a tuning passage associated with the piston; and a tuning fluid disposed within the upper fluid chamber, the lower fluid chamber, and the tuning passage, the tuning fluid comprising a polytungstate.

Abstract: An assembly is provided for forming holes in a workpiece. The assembly includes an arbor, a pin sleeve and a cutting device. The arbor has a nose having at least one threaded portion and at least one unthreaded portions on an external surface thereof. The arbor also has at least one pin passageway extending therethrough. The pin sleeve has at least one pin extending from a main body. The arbor extends through the pin sleeve. The cutting device has a back plate and a plurality of teeth extending therefrom. The back plate has a passageway defined by a wall with at least one threaded portion and at least one unthreaded portion. The at least one threaded portion of the cutting device is capable of engaging with the at least one threaded portion of the nose, and the at least one pin of the pin sleeve is capable of engagement with the at least one pin passageway of the arbor to secure the components together.

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: A series battery start controller for starting an aircraft turbine engine and method thereof is provided, wherein the battery series start controller connects two batteries in series when an aircraft engine starter is engaged to provide a higher voltage to start the aircraft engine and to provide adequate operational voltage to aircraft engine instruments and other aircraft electrical systems, and wherein the battery series start controller reconnects the batteries in parallel when the electrical load drawn by the starting aircraft engine decreases and the supplied voltage to the aircraft rises to a predetermined threshold.

Abstract: An inflatable life raft system for an aircraft includes a window coupled to a fuselage portion of the aircraft. A mechanism is used to selectively detach the window from the fuselage. An inflatable life raft is deployable to the exterior of the aircraft upon detachment of the window from the aircraft.

Abstract: According to one embodiment, a radial fluid device comprises a cylinder block, a first plurality of pistons including a first piston, and a second plurality of pistons including a second piston. Each of the first plurality of pistons are slidably received within a different one of a first plurality of radially extending cylinders. Each of the second plurality of pistons are slidably received within a different one of a second plurality of radially extending cylinders. The second piston is configurable to begin its stroke at a different time relative to the first piston within the first cylinder pair.

Abstract: A system and method to diagnosis an actuator of a flight control system. The system and method includes interfacing a diagnostic computer to the flight control system, commanding movement of an actuator with the diagnostic computer via the flight control system, measuring performance of the actuator via the diagnostic computer, and comparing the measured performance of the actuator with allowable performance values.

Abstract: The invention relates to a plastic fuel tank (1) for motor vehicles having at least one tank wall (2) surrounding at least one fuel volume, wherein the tank wall (2) is provided at least in a certain area or certain areas with means for increasing flexural rigidity in the form of two-dimensionally extended reinforcing layers (3) connected materially and/or positively thereto (FIG. 1).

Abstract: The present application relates a core member for a core-stiffened structural assembly. The core member includes a plurality of cell members oriented a direction to provide a tailored stiffness in a certain direction. The core member can further include one or more planar members that can aid in shear transfer between cell members. The cell members can be made from bonding a plurality of corrugated layers together. The core-stiffened structure can be a rotor blade for an aircraft. In such an embodiment, the torsional stiffness of the rotor blade can be tailored in at least one of the chordwise and spanwise directions to provide tailor a torsional stiffness at any give location in the rotor blade.

Abstract: An apparatus comprising a housing, a gearing system disposed within the housing and comprising a plurality of targets, a plurality of sensors incorporated within the housing, a processor in electrical signal communication with the sensors, and a user interface in signal communication with the processor. A method comprising providing a drive system comprising a drive system power measuring and diagnostic system, wherein the drive system is configured to rotate one or more components comprising a plurality of targets, sense the targets with a sensor pair, thereby producing a data signal, process the data signal from the one or more sensor pairs, thereby producing a processed data signal, and output the processed data signal to a user.

Abstract: A method of manufacturing a composite core can include: wrapping a mandrel in a mandrel wrapping process by securing a mandrel with a winding jig; orienting the composite material at a wrap angle to the mandrel; and depositing the composite material around a circumference of the mandrel. The method can further include assembling the wrapped mandrels in a tool and applying a pressure to the composite material during a curing cycle.

Abstract: A system to control flight of an aircraft includes a rotor blade, an actuator operably associated with the rotor blade, a controller operably associated with the actuator, and a flight control system. The flight control system having a subsystem adapted to modify a flight control limit of the aircraft based upon detection of an impending hazardous flight condition and a display showing available flight control limits provided by modification of design control limits based upon the detection of the impending hazardous flight condition. The method includes generating the control limits, modifying the control limits based upon the impending hazardous flight condition, and displaying the displacement of actuator position relative to the displayed control limits thus cueing the pilot as to the cyclic stick or pedal inputs required to increase the control margin from the impending hazardous condition.

Abstract: A method for operating an aircraft to prevent/recover from a stall condition includes the steps of detecting an actual vertical velocity of the aircraft, calculating vertical velocity error of the aircraft, the vertical velocity error being based upon a comparison between the actual vertical velocity of the aircraft and a commanded vertical velocity of the aircraft, and determining if the aircraft is in one of a near stalled condition and a stalled condition based upon at least the detected vertical velocity error and the polarity of the vertical velocity error. The method further includes the steps of taking control of the aircraft from an operator of the aircraft, reducing a bank angle of the aircraft, pitching the aircraft downward, and increasing the airspeed of the aircraft if the aircraft's airspeed is outside an airspeed window if the aircraft is in one of the near stalled condition and the stalled condition.

Abstract: A method of carving a contour surface on a composite core can include positioning a first edge of the composite core against a first tooled member; locating a first magnet within an outer cell member along the first edge of the composite core so that the first edge of the composite core is magnetically drawn to the first tooled member; locating a second magnet along a second edge of the composite core such that the second edge of the composite core is magnetically drawn to a second tooled member; and carving a first contour of the composite core.

Abstract: The present application relates to a method and system for optimizing a composite system by electrically monitoring the reactive and physiological behavior of the resin binder in a composite system, so as to develop the desired properties of the resin during the cure process. A method of manufacturing a composite part can include assembling a composite preform with a resinous material and an open circuit. Further, the method can include subjecting the composite preform to a curing cycle so that a resin in the resinous material melts and closes the open circuit. Further, the method can include electrically monitoring a current through the resin during the curing cycle. Further, the method can include selectively controlling a manufacturing variable in response to the step of electrically monitoring the current through the resin.

Abstract: A multi-function detection liner is applied to a non-cured composite material at the point of manufacturing for building a composite part. The detection liner includes a first insulative layer and a first conductive layer. The detection liner is configured to be detectable from a plurality of non-destructive inspection tests. The first insulative layer is detectable by ultrasound and radiograph within the composite part. The first conductive layer is configured to provide an eddy current signal and to enhance ultrasound attenuation of the detection liner within the composite part. Alternatively, the detection liner may include an integrated layer that combines the functions of an insulative layer and a conductive layer. The detection liner is releasably bonded to a surface of the non-cured composite material.