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 control system having a first loop configured to provide a longitudinal blowback value of a rotor blade during flight and a second loop associated with the first loop, the second loop being configured to provide a design maximum total flapping value and a lateral flapping value. A method includes calculating a flight control limit from the design maximum total flapping value and the lateral flapping value. An upper longitudinal cyclic control limit is calculated by adding the flight control limit to the longitudinal blowback value. A lower longitudinal cyclic control limit is calculated by subtracting the flight control limit from the longitudinal blowback value.

Abstract: A rotor system for a rotorcraft having at least one rotor blade pair operably associated with a differential pitch assembly operably for controlling a pitch angle of an upper rotor blade and the lower rotor blade in the rotor blade pair. Operation of the differential pitch assembly changes the pitch of the upper rotor blade more severely than the pitch of the lower rotor blade. As such, the rotor system is configured to provide optimum pitch of the upper and lower rotor blades during a helicopter mode and an airplane mode.

Abstract: The system and method of the present application relate to a lead/lag damper for a rotorcraft. The lead/lag damper is configured to harvest power from the lead/lag oscillatory motions of rotor blades with an electromagnetic linear motor/generator. Further, the lead/lag damper is configured to treat the lead/lag motions with the electromagnetic linear motor/generator. The system and method is well suited for use in the field of aircraft, in particular, helicopters and other rotary wing aircraft.

Abstract: The invention relates to a filler neck (1) for a fuel tank of a motor vehicle having at least one tubular section (3) provided in the region of the filler inlet (2) in order to receive the outlet pipe of a fuel delivery nozzle (5), and a flame barrier (4) which is provided in the tubular section (3) and surrounds the outlet pipe of the fuel delivery nozzle (5) in the inserted state, wherein the flame barrier (4) comprises at least two segments (6) which are mounted resiliently in the radial direction of the tubular section (3), the diameter of the opening (7) in the flame barrier (4) for the outlet pipe of the fuel delivery nozzle (5) being smaller in the prestressed state of the segments (6) than the diameter of the outlet pipe of the fuel delivery nozzle (5).

Abstract: A utility vehicle includes a first axle, a second axle, an electric motor, an internal combustion engine, and a torque transfer device. The first axle is coupled to first and second wheels. The second axle is coupled to third and fourth wheels. The electric motor drives the first axle in a first direction and a second direction at different times. The internal combustion engine drives a transmission output shaft in one direction. The torque transfer device selectively drives the second axle in the first direction in response to rotation of the transmission output shaft in the one direction. The torque transfer device also selectively drives the second axle in the second direction in response to rotation of the transmission output shaft in the one direction.

Abstract: According to one embodiment, a quality analyzer receives aerodynamic performance data for a part that has been manufactured according to a design. The aerodynamic performance data expresses aerodynamic performance of the part as calculated from a plurality of coordinates measured on the part. The quality analyzer determines whether the aerodynamic performance data for the part satisfies minimum aerodynamic performance requirements.

Abstract: A system for a vehicle includes a vehicle stability module that receives a commanded torque value, that determines whether to apply the commanded torque value based on at least one vehicle position characteristic, a position of an accelerator pedal, and a brake status, and that selectively outputs instructions to apply the commanded torque value in response to the determination. A torque control module receives the instructions from the vehicle stability module and applies a torque, corresponding to the commanded torque value, to at least one wheel of the vehicle based on the instructions.

Abstract: A method of optimizing an operation of a rotorcraft includes measuring actual usage of the tail rotor drive shaft during operation of the rotorcraft, the actual usage including at least a torque measurement. The method further includes a step of adjusting a life of the tail rotor drive shaft based upon the measuring of the actual usage. Another method of the present disclosure includes determining a main rotor mast torque by measuring a tail rotor drive shaft torque and deriving a main rotor mast torque by considering the measured tail rotor drive shaft torque and a total torque output of an engine. A system of the present disclosure is configured for determining the main rotor mast torque in part by measuring the tail rotor torque.

Abstract: According to one embodiment, a method comprises calendering an elastomeric material into an elastomeric layer having a thickness that is more uniform than the elastomeric material prior to the calendaring. After calendaring, the elastomeric layer is vulcanized to a composite shim comprising at least one reinforcement layer and at least one layer of adhesive.

Abstract: The invention relates to a fuel tank (1) with at least one filler pipe (2) enclosing a refueling duct and with at least one vent line (6), which comprises at least one first and one second line section (6a, 6b), the first line section (6a) extending from a vent connection (7) of the fuel tank (1) to a connection on the filler pipe (2), and the second line section (6b) extending from a connection on the filler pipe (2) to a fuel vapor filter (10), wherein at least one line section (6a, 6b) opens directly into the filler pipe (2) via a connection fitting.

Abstract: According to one embodiment, a rotor system comprises a yoke, a grip, an elastomeric bearing, and a bearing restraint. The grip is positioned around a portion of the yoke and has both a closed end and an open end. The elastomeric bearing is coupled to the closed end of the grip and located between the closed end and the yoke.

Abstract: A vibration isolator includes an upper housing and a lower housing; an upper reservoir housing defining a upper fluid chamber; a lower reservoir housing defining a lower fluid chamber; a piston spindle resiliently coupled to the upper housing with an upper elastomer member, the piston spindle being resiliently coupled to the lower housing with a lower elastomer member; an elongated portion having a tuning passage; and a tuning fluid disposed there within. The vibration isolator cancels vibratory forces at an isolation frequency. The vibration isolator is utilized in a pylon system for mounting a transmission in an aircraft. The vibration isolator is located between a pylon structure and a roof structure. The isolator includes a spherical bearing assembly that is located near a waterline location of a rotational axis of a drive shaft.

Abstract: An elastomeric spring-damper has a one-piece tubular body having an integral cap. A tension stop flange is formed in the body near the cap portion, and a compression stop flange opposing the tension stop flange is formed on the cap portion. An inner member located within the body is coupled to the body with an annular elastomeric member, such that longitudinal motion of the inner member relative to the body is allowed through elastic deformation of the elastomeric member. An inner member stop flange is positioned between the compression stop flange and the tension stop flange to limit longitudinal motion of the inner member relative to the body.

Abstract: According to one embodiment, a pitch link includes a first link, a second link coupled to a first end of the first link, a third link coupled to a second end of the first link opposite the first end, and a first bearing housing having a first bearing and a second bearing housing having a second bearing. The first bearing housing is removably coupled to the second link. The second link separates the first bearing housing from the first link. The second bearing housing is removably coupled to the third link. The third link separates the second bearing housing from the first link.

Abstract: An electronic assembly includes an electronic device and a solar shield coupled to the electronic device. The solar shield has an attachment portion which attaches to the electronic device, and a shield portion coupled to the attachment portion. The shield portion prevents direct sunlight from substantially reaching a section of the electronic device. The shield portion defines (i) at least a portion of an air intake, (ii) at least a portion of an air exhaust, and (iii) at least a portion of an air passageway which extends from the air intake to the air exhaust. The air passageway overlies the section of the electronic device enabling ambient air adjacent the air intake to form natural convective airflow into the air intake and out the air exhaust through the air passageway to carry away heat from the section of the electronic device during electronic operation of the electronic device.

Abstract: A crash attenuation system for an aircraft includes an airbag carried by the aircraft that is inflatable generally adjacent an exterior of the aircraft. The airbag is in fluid communication with at least one vent passage for channeling gas from within the interior of the airbag to a region external to the airbag that allows the gas to escape without being obstructed by the airbag. A gas source is in fluid communication with the interior of the airbag for inflating the airbag. A vent valve is provided within the vent passage for controlling a flow of gas through the vent passage, thereby controlling deflation of the airbag. The vent valve is continuously adjustable to and between an open state, a closed state, and any number of partially open states.

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 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: A method for fabricating a repair laminate for a composite part having an exposed surface includes applying a release film to the exposed surface and forming an uncured ply stack assembly on the release film. The uncured ply stack assembly is formed by forming and compacting a series of uncured ply stacks. The release film and ply stack assembly is then removed from the exposed surface. A bonding material is then applied to the exposed surface, and the uncured ply stack assembly is applied to the bonding material. The ply stack assembly and bonding material are then cured.