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: The present application relates to a system and method for providing real-time indications of economic impact of aircraft operations to an aircraft operator. The system and method allow the aircraft operator to reduce economic impact during flight of the aircraft. Such an analysis and cue to the aircraft operator allows the operator to make real-time changes during flight to reduce damage of life-limited aircraft components, thereby reducing the economic impact of aircraft operation that is directly associated with maintenance and component replacement. The system and method can also include pre-flight and post-flight analysis methods for reduction of economic impact of flight operations.

Abstract: An aircraft rotor assembly has upper and lower hub plates adapted to be mounted to a central rotor mast for rotation therewith. A plurality of radial arms is connected to at least two flap bearings mounted between the hub plates and forming a discrete flap hinge, each flap hinge defining a flap axis and allowing rotation of the associated arm relative to the hub plates and about the corresponding flap axis. Each of a plurality of blade grips is rotatably connected to one of the arms for rotation about a pitch axis and adapted for mounting of a blade to each blade grip, such that each blade is capable of rotation with the grip about the pitch axis and capable of rotation together with the corresponding arm relative to the hub plates and about the corresponding flap axis.

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.

Abstract: A twin-rotor side-by-side compound rotorcraft has a fuselage and variable incident wing assembly that pivots relative to fuselage. The aircraft also has landing gear assembly and a tail fin assembly. The variable incident wing assembly is pivotally attached to the fuselage, and includes wing members, engines fixedly mounted to the wing members or another area of the rotorcraft, and a mast attached at a fixed angle relative to the wing members. Then engines may also be located near the fuselage or another area of the rotorcraft. The variable incident wing assembly is capable of pivoting about a pivot axis, thereby allowing mast orientation in at least a hover mast position and a forward flight mast position. The rotors provide additional forward thrust and the wings provide additional lift, when the mast is in the forward flight mast position.

Abstract: A system and method to adjustably create a reacting force in response to a vibrating force of a vibrating structure. The system includes an adjustable vibration absorber that creates a range of reacting forces. The method includes continuously monitoring the reacting force and the vibrating force with a sensor system operably associated with a control unit having an algorithm to determine if adjustment of the vibration absorber is required. If required, the control unit commands a driver to selectively adjust the vibration absorber such that the reacting force equals the vibrating force.

Abstract: The invention relates to a fuel tank (1) for a motor vehicle with at least one filler pipe (3) which extends partially outside the filling volume (5) of the fuel tank (1), with at least one refuelling venting path from a refuelling venting device (10) to a fuel vapour filter (9), and with at least one operational venting path to the fuel vapour filter (9). The fuel tank (1) comprises at least one operational venting line (14) which is attached to the filler pipe (3) inside the filling volume of the fuel tank (1).

Abstract: The test instrument is used to perform both time domain reflectometry (TDR) and analysis of transmission signals on a line under test. Further, the test instrument provides for both pulse TDR and step TDR. A coupling transformer having an enhanced low frequency response provides for coupling of the test instrument to the line under test. Isolation circuits between the coupling transformer and the line under test to prevent damage to the test instrument due to voltages on the line under test allow the test instrument to be used in connection with an active line under test. Two isolation circuits are utilized to maintain longitudinal balance of the circuit. During step TDR, the positive and negative transmitter circuits provide step-shaped impulse signals.

Abstract: A system includes a plurality of actuators and a control system operably associated with the plurality of actuators. The control system having a control logic architecture having a dynamic command input shaping model associated with an input command, a robust inner loop associated with the dynamic command input shaping model, and a time delay cancellation model. The method includes selecting a control law based upon a flight performance of an aircraft, decoupling the control law into a first individual component and a second individual component of the aircraft flight motion, analyzing each individual component separately, regrouping the component of flight motion, analyzing the control law with a time delay cancellation model and providing the necessary dynamic flight quickness with a different command input condition.

Abstract: The invention relates to a method for producing thermoplastic hollow articles, comprising: producing web-shaped or plate-shaped parisons from melted plastic in such a way that the parisons receive a specific wall thickness profile; cooling the parisons to obtain dimensionally stable semifinished products that still have the same wall thickness profile; heating the semifinished products and shaping the heated semifinished products into parts of a hollow article; and welding the semifinished products together to obtain a substantially closed hollow article.

Abstract: A system and method to isolate vibrations from a vibrating structure. The system includes an adjustable vibration isolator that creates a reacting force matching the vibratory force of the vibrating structure. The method includes continuously monitoring the reacting force and vibratory force with a sensor system operably associated with a control unit having an algorithm to determine if adjustment of the vibration isolator is required. If required, the control unit commands a driver to selectively adjust the vibration isolator.

Abstract: The vibration suppression system includes a vibration isolator located in each corner in a four corner pylon mount structural assembly. The combination of four vibration isolators, two being forward of the transmission, and two being aft of the transmission, collectively are effective at isolating main rotor vertical shear, pitch moment, as well as roll moment induced vibrations. Each opposing pair of vibration isolators can efficiently react against the moment oscillations because the moment can be decomposed into two antagonistic vertical oscillations at each vibration isolator. A pylon structure extends between a pair of vibration isolators thereby allowing the vibration isolators to be spaced a away from a vibrating body to provide increased control.

Abstract: An electronic passkey system enables modification of operating profiles of a vehicle. When the passkey is connected to the vehicle controller, the system determines if the passkey has been used previously. If so, the operating profile cannot be modified. If not, the vehicle profile can be modified. In other configurations the passkey can be used to modify the operating profile of multiple vehicles.

Abstract: A twin-rotor side-by-side compound rotorcraft has a fuselage and variable incident wing assembly that pivots relative to fuselage. The aircraft also has landing gear assembly and a tail fin assembly. The variable incident wing assembly is pivotally attached to the fuselage, and includes wing members, engines fixedly mounted to the wing members or another area of the rotorcraft, and a mast attached at a fixed angle relative to the wing members. Then engines may also be located near the fuselage or another area of the rotorcraft. The variable incident wing assembly is capable of pivoting about a pivot axis, thereby allowing mast orientation in at least a hover mast position and a forward flight mast position. The rotors provide additional forward thrust and the wings provide additional lift, when the mast is in the forward flight mast position.

Abstract: A system includes a plurality of actuators and a management system operably associated with the plurality electronic and mechanical devices. The management architecture includes interfaces configured to the entire electronics and mechanics to provide a parameter to a computer. The computer includes a control and management architecture using modular finite state flow designs configured to analyze the parameter. The computer with a plurality of finite state machines can conduct a plurality of control laws operably associated with one or more actuators for finite functions of mobility. The method includes matching the parameter with the finite state machine and controlling the actuator via control law operably associated with finite state machine. The method can therefore be achieved either manually, semi-autonomously and autonomously with seamless and switchless control using a central control computer with integration of electronic and mechanic sensors and devices.

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 fluid conduit having a self-healing sleeve in a spaced relationship from the conduit to provide protection against leaks due to ballistic projectiles, such as small arms fire.

Abstract: A vehicle instrument support and storage apparatus for a vehicle driven by a human driver who occupies a driver's seat of the vehicle provides a frame having a plate configured for attachment to a selected vehicle. The frame has a plurality of docking station positions. A rotary bearing is attachable to the vehicle. An instrument support includes a support panel and an arm having an inner and outer end portions, the arm inner end portion being connected to the rotary bearing. The instrument support panel is affixed to the outer end portion of the support arm. An interlock of the instrument support with one docking station places the instrument support panel in front of the driver of the vehicle. An interlock of the instrument support with the other docking station places the instrument support in a position that is spaced away from (laterally, circumferentially and/or radially) first position.