Abstract: A method of constructing a composite component includes at least one of laterally and longitudinally aligning a material strip relative to a concavity of a layup tool, at least one of laterally and longitudinally extending the material strip to a predetermined location relative to the layup tool, wherein the material strip is substantially rectangular, and vertically abutting the material strip to the concavity of the layup tool, wherein the longitudinally extending the material strip includes at least one of (1) measuring a longitudinal distance of the material strip and (2) aligning a longitudinal end of the material strip with a longitudinal distance indicium and wherein the laterally extending the material strip includes at least one of (1) measuring a lateral distance of the material strip and (4) aligning a lateral end of the material strip with a lateral distance indicium.

Abstract: An alternative system for damping the dutch roll mode in an aircraft is provided using roll control surfaces. Classical yaw dampers for the dutch roll mode utilize the yaw control surfaces such as a rudder to dampen the dutch roll mode oscillations. An alternative damper is described that utilizes roll control surfaces such as spoilers or ailerons to dampen the dutch roll mode.

Abstract: According to one embodiment, a stability augmentation system includes a master linkage, a stability augmentation motor, and three linkages. A first linkage is coupled to the master linkage and operable to receive movements representative of pilot commands from a pilot command system. A second linkage is coupled between the stability augmentation motor and the master linkage and operable to receive movements representative of augmentation commands from the stability augmentation motor. A third linkage is coupled to the master linkage and operable to transmit movements representative of blade position commands to a blade control system in response to the movements representative of pilot commands and the movements representative of augmentation commands.

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. The bearing restraint is coupled to the grip between the yoke and the open end at a distance from the closed end such that the yoke contacts the bearing restraint when the rotor system is subject to a first centrifugal force but does not contact the bearing restraint when the rotor system is subject to a second centrifugal force greater than the first centrifugal force.

Abstract: The invention provides a laminate composite fabric which is robust, laundry-durable, and a method for forming such fabric. The laminate fabric is provided with at least one element that provides heat or warmth (heating element). Generally, the laminate fabric with heating element(s) is sufficiently robust for incorporation into garments or warming textile structures (pads and blankets). The laminate fabric may include one or more stretch and recovery elements to cause the laminate to be more adaptable for securing about any three dimensional body.

Abstract: An assembly includes a hole saw, an arbor, a collar and a nut. The hole saw is formed from a back plate and a skirt which has a cutting edge on its free end. A passageway is provided through the hole saw. The arbor is rotatably mounted to the hole saw and extends through the passageway. The collar is nonrotatably mounted on the arbor. The collar has a protrusion extending from an end face thereof. A nut is rotatably mounted on the arbor. The collar is trapped between the nut and the hole saw. The nut directly bears against the end face and the protrusion of the collar, which causes the nut to cock relative to the collar. As a result, the nut does not easily come loose on the arbor, even during aggressive use.

Abstract: A variable stiffness liquid inertia vibration isolation device includes a liquid inertia vibration elimination isolator and a variable stiffness spring operably associated with the liquid inertia vibration elimination isolator for varying the stiffness of the liquid inertia vibration isolator. The variable stiffness spring may include an elastomeric pad exhibiting a first stiffness along a first axis and a second stiffness, significantly greater than the first stiffness, along a second axis that is perpendicular to the first axis.

Abstract: A method of managing aircraft exhaust includes providing hot air at a hot air mass flow rate, providing cold air at a cold air mass flow rate, and mixing the hot air and the cold air at a variable hot air mass flow rate to cold air mass flow rate ratio, wherein the variable hot air mass flow rate to cold air mass flow rate ratio is selectively maintained independent of at least one of (1) a variation in the hot air mass flow rate and (2) a variation in a translational speed of the aircraft.

Abstract: A console for aircraft that is located between two seats which face each other. The console includes an open ledge with a cup holder arrangement. The cup holder arrangement includes two removable holder dividers which can be flipped up or down and held into position by a spring-loaded cam arrangement. The console also includes two inwardly facing surfaces which provide connectors for electronic devices resting on the ledge. A light-emitting face is provided on a back wall of the ledge so that any articles resting on the ledge can be seen in dark environments.

Abstract: An acoustic baffle for reducing noise of a centrifugal fan includes a base for mounting with a fan outlet and a projection extending from the length of the base at a back side of the base and curving away from a top surface of the base. The projection continuously tapers along at least one side from an area proximate the base to an apex. The apex aligns with a fan tangency point, and the apex or a trough of the projection aligns with a midpoint of the outlet, when the acoustic baffle is installed in the outlet. The acoustic baffle effects a gradual variation in radial and tangential airflow at the blower outlet, to reduce fan blade passage tone.

Abstract: The invention relates to a fuel tank (1) consisting of thermoplastic, with at least one continuous seam (3), with a filler orifice, with means for aeration and venting and with means for the conveyance and extraction of fuel which are in the form of at least one fuel conveying unit (11) arranged inside the fuel tank (1). In the fuel tank (1) according to the invention, with the exception of the filler orifice, no orifices or perforations which are substantially larger than the diameter of the line to be led through are provided in the tank wall, instead the fluid lines and/or electrical lines led out of or into the fuel tank (1) pass through the seam (3) of the fuel tank (1) so as to extend at an angle with respect to the profile of the seam (3), and/or are led partially through the filler orifice and, if appropriate, a filler neck adjoining the filler orifice.

Abstract: An aircraft and method to control flat yawing turns of the aircraft while maintaining a constant vector heading across a ground surface. The aircraft includes a control system in data communication with a model, a lateral control architecture, a longitudinal control architecture, and an initialization command logic. The model decouples the directional movement of the aircraft into a lateral equation of motion and a longitudinal equation of motion. The lateral control architecture utilizes the lateral equation of motion to control the aircraft in the lateral direction, while the longitudinal control architecture utilizes the longitudinal equation of motion to control the aircraft in the longitudinal direction. The initialization command logic selectively activates the lateral control architecture and the longitudinal control architecture.

Abstract: According to one embodiment, a landing point indication system includes an image provider, a rotorcraft position provider, a pilot image generation system, and a display device. The image provider is operable to provide a visual representation of an area underneath a rotorcraft. The rotorcraft position provider is operable to provide information indicating a position of the rotorcraft. The pilot image generation system is operable to generate a supplemented visual representation. The supplemented visual representation includes the visual representation of the area underneath the aircraft and information indicating a position of the rotorcraft relative to the visual representation. The display device is operable to display the supplemented visual representation within the rotorcraft.

Abstract: A vertical support system includes a first articulated leg assembly configured to carry a first load, the first articulated leg assembly being selectively movable between a first retracted configuration and a first loaded configuration and a second articulated leg assembly configured to carry a second load substantially kinematically identical to the first articulated leg assembly, the second articulated leg assembly being selectively movable between a second retracted configuration and a second loaded configuration, wherein a lateral width ratio is equal to a value of less than about 0.6, the lateral width ratio being defined as a ratio of (1) a maximum lateral width when the first articulated leg assembly and the second articulated leg assembly are in a retracted configuration to (2) a maximum lateral width when the first articulated leg assembly and the second articulated leg assembly are in a loaded configuration.

Abstract: According to one embodiment, a method of adjusting an aircraft pedal assembly includes providing a pedal linkage coupled between a pedal and an attachment assembly situated proximate to an aircraft instrument panel. A brake cylinder is provided coupled between the pedal and the attachment assembly. The pedal linkage is rotated in response to an adjustment input. The pedal linkage is maintained approximately parallel to the brake cylinder during rotation of the pedal linkage.

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: According to one embodiment, a structural electrical system includes an electrical power source operable to provide electrical current, a structural composite, and a plurality of output devices. The structural composite includes alternating layers of conductive layers and insulative layers. Each conductive layer is less than or equal to 500 nanometers thick and each conductive layer is in electrical communication with the electrical power source. The plurality of output devices are in electrical communication with each conductive layer and are operable to receive electrical current from the electrical power source through the conductive layers.