Abstract: A lubrication system is disclosed. The lubrication system may have a collection area for collecting lubricating media and a pumping system for transporting the lubricating media from a withdrawal location of the collection area to a distribution location of the collection area. The lubricating media may collect in the collection area to a static level when the pumping system is off and to a dynamic level when the pumping system is on. The lubrication system may also include a drain valve located between the static level and the dynamic level. The drain valve may operable to open to drain a portion of the lubricating media in response to the lubricating media reaching a predefined threshold temperature and level. The valve may comprise a thermally-activated material, and the material may substantially change phase or volume upon reaching a predetermined temperature.

Abstract: The present disclosure provides a motor connection system and method for mounting and removing a motor to and from a reel assembly frame of a turf-care vehicle without the use of tools. In various embodiments, the system includes a plurality of shoulder bolts longitudinally extending from a mounting end of the motor and a bearing housing that is mountable to a reel assembly frame of a turf-care vehicle. The bearing housing includes a plurality of self-tightening keyhole slots structured and operable to receive a respective one of the shoulder bolts. Each keyhole slot comprises a interior bezel that is interoperable with the respective shoulder bolt such that rotation of the motor to a Home position will structurally hold and secure the motor to the bearing housing.

Abstract: On example of a rotorcraft bearing system includes a bearing housing attached to an elastomeric bearing on a longitudinal axis, an end surface of the elastomeric bearing attached to an end surface of the bearing housing. The rotorcraft bearing system also includes a sliding contact bearing having an end surface. The rotorcraft bearing system also includes an intermediate sliding contact bearing material layer. Under load on the longitudinal axis, the end surface of the sliding contact bearing is configured to contact an opposing end surface of the bearing housing through the intermediate sliding contact bearing material layer to form a rotational slip joint.

Abstract: Some examples of an aircraft engine barrier filtration system include an engine barrier filter layer positioned near an aircraft engine intake. The filter layer filters aircraft engine intake air. The system includes a check valve assembly positioned adjacent to the engine barrier filter layer. The check valve assembly permits the engine intake air to flow into the engine through the filter layer during a first aircraft operation mode and to prevent air flow away from the engine through the filter layer during a second aircraft operation mode that is different from the first aircraft operation mode.

Abstract: The system of the present application includes an engine and pylon arrangement for a tilt rotor aircraft in which the engine is fixed in relation to a wing portion of the aircraft, while the pylon is rotatable. The pylon supports a rotor hub having a plurality of rotor blades. Rotation of the pylon allows the aircraft to selectively fly in a helicopter mode and an airplane mode, as well as any combination thereof.

Abstract: A method of making a composite rotor yoke includes preparing a molded rotor yoke in a closed cavity tool and possibly machining at least one portion of the molded rotor yoke to form the rotor yoke. In the preferred embodiment, preparing the molded rotor yoke is accomplished by applying layers of uncured low-flow composite material and a layer of uncured high-flow adhesive; substantially enclosing the uncured molded rotor yoke in the closed cavity tool; applying pressure so as to compress the uncured molded rotor yoke; and curing the uncured molded rotor yoke. During the curing process, the high-flow adhesive bleeds out of the molded rotor yoke, thereby preventing marcels from forming through movement of the low-flow composite material.

Abstract: According to one embodiment, a flapping lock for a rotor system includes a downstop, a flapping stop, and an actuator. The downstop is in mechanical communication with a shaft. The flapping stop is in mechanical communication with a rotor hub. The actuator is operable to move the downstop towards the flapping stop.

Abstract: A system for optically recognizing, interpreting, and digitizing human readable instruments, annunciators, and controls includes an image acquisition sensor operable to capture images of at least one of the instruments, annunciators, and controls; and a logic processing unit operable to decode the images captured by the image acquisition sensor and interpret the decoded images to determine a state of the at least one of the instruments, annunciators, and controls.

Abstract: A heater system includes a bag forming a cavity, a fluid bladder carried within the cavity and forming a fluidly sealed chamber. The fluid bladder being configured to store electrorheological fluid within a fluidly sealed chamber. The heater system further including an electrical wire in fluid communication with the electrorheological fluid and a heater blanket carried within the cavity. The method includes altering the electrorheological fluid with a current and providing heat with a heater blanket.

Abstract: A system and method to transfer heat energy through a composite structure. The system includes a heat pipe extending through a thickness of the composite material. The method includes extending a heat pipe through the composite material from a first surface exposed to the heat energy to a second surface exposed to airflow.

Abstract: An aircraft includes a rotor blade and a rotor hub system. The rotor hub system includes a lead-lag damper having a rod end and being operably associated with the rotor blade; a blade adapter having a first arm and an opposing second arm; a pin carried by the blade adapter and configured to secure in position via the first arm and the second arm; and an actuator secured to the pin and configured to adjust the position of the lead-lag rod end relative to the first arm and the second arm.

Abstract: A method for applying adhesive to sides of a flange, such as in rotorcraft connection joints, includes attaching an intermediate member to an edge of a flange and flowing adhesive in gaps between sides of the flange and inner edges of a double lap joint element by inserting the flange with the intermediate member into the double lap joint element.

Abstract: A method of increasing the control authority of redundant stability and control augmentation system (SCAS) actuators by utilizing feedback between systems such that one system may compensate for the position of a failed actuator of the other system. Each system uses an appropriate combination of reliable and unreliable inputs such that unreliable inputs cannot inappropriately utilize the increased authority. Each system may reconfigure itself when the other system actuator fails at certain positions so that the pilot or other upstream input maintains sufficient control authority of the aircraft.

Abstract: A collision avoidance and warning system for a helicopter uses a type of emitted energy, for example radio frequency radar, from a transceiver positioned to cover a selected field of view for detecting an object or pedestrian in the vicinity of the helicopter. For helicopters that include a tail rotor assembly, the selected field of view can include a region around the tail rotor assembly so that when the helicopter is running on the ground, an alarm can be issued to persons approaching the tail rotor assembly. When the helicopter is in flight, the collision avoidance and warning system can alert the pilot when a portion of the helicopter outside of the pilot's field of view is in danger of a collision with an object.

Abstract: In accordance with one embodiment of the present disclosure, a trunnion includes a first portion and a second portion. The first portion is capable of coupling directly to a drive tube of an aircraft, wherein the drive tube is capable of rotating around a first axis. The second portion is capable of coupling to a swash plate of the aircraft, wherein the swash plate is capable of causing the pitch of at least one of a plurality of aircraft blades to change.

Abstract: The system is configured for automation of rotorcraft entry into autorotation. The system can provide a means to assist the flight crew of a rotorcraft in maintaining rotor speed following loss of engine power. The system can automatically adjust control positions, actuator positions or both to prevent excessive loss of rotor speed upon initial loss of engine power before the flight crew is able to react. The system uses model matching to provide axis decoupling and yaw anticipation; it includes pitch control initially to assist in preventing rotor deceleration; and it makes use of collective, pitch, roll and yaw trim functions to provide tactile cueing to the pilot to assist when the pilot is in the loop. The system can reduce workload by assisting the crew with controlling rotor speed and forward speed during stabilized autorotation.

Abstract: A nondestructive system and method for measuring non-conductive coating thickness is disclosed. The method includes providing a composite substrate, placing a conductive layer over a surface of the composite substrate, and depositing a plurality of non-conductive coating layers over the conductive layer. An eddy-current measuring coil formed on a printed circuit board is provided atop the coating layers. The coil has a driving trace with first and second driving electrodes, and a receiving trace having first and second receiving electrodes. The receiving and driving traces can be either coaxial or interwoven, are spaced apart, and share a common center. A load administered to the first and second driving electrodes using an eddyscope is measured across the first and second receiving electrodes to determine impedance; the measured impedance is used to determine a total thickness of the plurality of coating layers and whether an overall coating thickness is uniform.

Abstract: An improved flight control system is described, providing for increased or reduced pilot input forces necessary to cause desired control surface deflections.

Abstract: An assembly includes a fish tape device or a duct rodding device having digital measurement unit attached thereto. A tape is housed in the fish tape device or a duct rodding device and is paid out of the device. The digital measurement unit includes an optical sensor which is positioned proximate to the tape. As the tape is passed by the optical sensor, the optical sensor uses digital image correlation to take successive images of the tape to determine a length measurement of tape that has passed by the optical sensor.