Abstract: According to one embodiment, a flight control system includes a pilot control assembly and a flight control computer. The pilot control assembly can receive commands from a pilot. The flight control computer can receive, from the pilot control assembly, a pilot command to change a first flight characteristic, wherein changing the first flight characteristic would result in an expected change to a second flight characteristic. The flight control computer can instruct, in response to the received pilot command, the flight control system to change a first operating condition of the flight control system based on an inherently-coupled relationship between the first flight characteristic and the second flight characteristic. The flight control computer can instruct, in response to the expected change to the second flight characteristic, the flight control system to change a second operating condition of the flight control system.

Abstract: The present disclosure provides a USB connection system for an open cab vehicle such as a golf car, turf-care vehicle, small maintenance vehicle, shuttle vehicle, cargo vehicle, all-terrain vehicle, utility terrain vehicle, motorcycle, and/or other utility vehicle, and/or other outdoor/off-road vehicle. The USB connection system comprises a module structured and operable to receive and retain at least one USB port, a water protected circuit board located remotely from the USB port(s) and electrically and communicatively connected to the USB port(s). The USB connection system additionally comprises a laterally rotatable slide-away cover that is pivotally connected to the module via a pivot pin longitudinally disposed within a module housing such that the cover can be laterally rotated, between an opened and a closed position about the pivot pin. Furthermore, in various implementations, the module includes at least one water drainage channel structured and operable to drain water away from the USB port(s).

Abstract: In some embodiments, an aircraft may include a retractable or extendable landing gear. The landing gear may include a wheel connected to an axle, a strut configured to resist longitudinal compression, and a linear actuator that is partially disposed within an opening of the strut.

Abstract: A method for making a fuselage section comprises the steps of assembling a support system. The support system comprises fiber reinforced composite material and includes at least three frames and six stringers. The support system is partially cured such that the support system attains about eighty percent of its fully cured strength. A skin comprising fiber reinforced composite material is globally positioned such that an inner surface of the skin corresponds to an outer surface of the support system. The skin and the support system are fully cured together. The support system is assembled on a skeleton assembly tool having a bonding surface corresponding to an inner surface of the skin.

Abstract: Methods, systems, and apparatus, including computer programs encoded on a computer storage medium, for landing aircrafts with optimal landing spot selection. In one aspect, a method includes initiating an autorotation of an aircraft in response to detecting all engine failure, determining a plurality of flight characteristics and conditions of the aircraft at a time of initiating the autorotation, the plurality of flight characteristics and conditions comprising an aircraft altitude, an aircraft velocity, and wind direction, determining total air-time for glideslope and flare control, and a geographic area within which to land the aircraft by autorotation based on the plurality of flight characteristics and conditions, and controlling the aircraft to land the aircraft by autorotation within the geographic area.

Abstract: According to one embodiment, a flight control device includes a grip, a stick associated with the grip, and a gimbal. The stick defines a first axis. The gimbal includes a first platform, a second platform, a first electro- rheological elastomeric bearing, and a second electro-rheological elastomeric bearing. The first platform is coupled to the stick and configured to rotate on a second axis that is perpendicular to the first axis. The second platform is in mechanical communication with the first platform and configured to rotate on a third axis that is perpendicular to the second axis. The first electro-rheological elastomeric bearing defines the second axis, and the second electro-rheological elastomeric bearing defines the third axis. The first and second electro-rheological elastomeric bearing being configured to each have a variable stiffness.

Abstract: A system includes a first mast torque transfer system, a second mast torque transfer system coupled to the first mast torque transfer system, and a torque limiting system. The torque limiting system includes a first sensor configured to determine a torque of the first mast torque transfer system, a second sensor configured to determine a torque of the second mast torque transfer system, and a processor configured to determine a differential torque between the torque of the first mast torque transfer system and the torque of the second mast torque transfer system and configured to control at least one of a torque input and a torque output to at least one of the first and second mast torque transfer systems as a function of the determined differential torque.

Abstract: Embodiments of the present invention relate to a winglet for an end or tip of an aircraft wing. The winglet includes an inner portion that curves upward having a large radius of curvature near the wing, a middle portion having a small radius of curvature forming a bend, and an outer portion having a large radius of curvature extending to a tip of the winglet. The winglet lowers induced drag of the wing and improves aircraft performance especially for wing tip extensions that extend upwards about equal to or slightly more than outwards.

Abstract: A system for controlling a grass cutting reel assembly of a turf-care vehicle. The system includes: a reel cylinder motor operable to rotate a reel cylinder of a grass cutting reel assembly of a turf-care vehicle at a desired rotational rate of speed to provide a controllable frequency of clip for the reel assembly; an automated height of cut control system operable to control a position of a front roller of the reel assembly to provide a controllable height of cut for the reel assembly; and a controller system operable to control the reel cylinder motor and the height of cut control system to provide a particular frequency of clip and a particular height of cut stipulated by one of a plurality of cutting scenarios programmed into the controller system and selected via a user interface of the controller system that is accessible by an operator onboard the turf-care vehicle.

Abstract: A method of constructing a cured composite assembly includes positioning a composite assembly within a bonding tool, wherein the composite assembly comprises an uncured composite spar and a skin and performing a curing cycle on the composite assembly to simultaneously cure the uncured composite spar and bond the skin to the cured composite spar.

Abstract: The invention relates to a method of determining the retention capacity of fuel vapor filters for motor vehicles, wherein a temperature profile of the fuel is recorded on a motor vehicle in a SHED chamber during a temperature cycle. A fuel vapor volumetric flow for a temperature change is calculated from the temperature profile. In a measurement arrangement (1) fuel is evaporated by means of an evaporator (2) and is output by means of a charging pump (9) to a fuel vapor filter (4) disposed in an oven (5). The bleed emissions of the fuel vapor filter (4) are measured at least during the charging.

Abstract: According to one embodiment, an aircraft component is manufactured from a plurality of separate materials comprising a first material. The first material is physically associated with a tracking device comprising a first storage medium featuring line-of-sight accessible information and a second storage medium featuring non-line-of-sight accessible information. The line-of-sight accessible information and the non-line-of-sight accessible information each comprise information regarding the first material physically associated with the tracking device.

Abstract: According to one embodiment, a gauge display prioritization system comprises a priority engine and an output engine. The priority engine is operable to receive a measurement from a first sensor associated with a first aircraft component and a measurement from a second sensor associated with a second aircraft component, select a prioritization criterion based on the received measurements, and select one priority measurement from the received measurements based on the prioritization criterion. The output engine is operable to instruct a gauge disposed within a cockpit to display information representative of the one priority measurement to a pilot.

Abstract: According to one example embodiment, a method of assessing use of an aircraft component installed on an aircraft includes receiving, from one or more sensors installed on the aircraft, one or more measurements representative of at least one load applied against the aircraft component; selecting at least one usage model from a plurality of usage models, each usage model of the plurality of usage models relating aircraft loads with received sensor data; determining at least one load value based on the selected at least one usage model and the received one or more measurements; and calculating, based on the determined at least one load value, an amount of change in probability of failure caused by application of the at least one load against the aircraft component.

Abstract: The invention relates to a container (1) of thermoplastic material with at least one support (4), which is arranged in the interior of the container, extends between opposing container walls (2) and is anchored at each end to the container walls with a positive engagement and/or a material bond, the support (4) comprising at least one supporting strut (5) and the supporting strut (5) substantially absorbing a supporting load on the container walls (2) induced by negative pressure in the container, and a tensile force that is induced by positive pressure being absorbed by at least one tension-resistant bracing element in the form of a tension-resistant band (8) which extends between the container walls (2).

Abstract: A clamping assembly includes a first jaw having a plurality of alternating grooves and lands formed thereon, a second jaw having a plurality of alternating grooves and lands formed thereon, and a spring provided between the first and second jaws. The jaws are pivotable relative to each other. The jaws are attached to a draw stud. The draw stud is formed from an elongated cylinder which has a conventional thread form formed on one end thereof and a plurality of alternating grooves and lands formed on the other end thereof. The alternating grooves and lands formed on the jaws mesh with the alternating grooves and lands formed on the draw stud to mate the jaws with the draw stud.

Abstract: A vibration control system for a rotorcraft includes at least one of an integrated actuator and an intermediate actuator associated with a first source of vibration, a sensor configured to sense vibration from the first source of vibration, a dedicated actuator configured for association with a fuselage, and a controller configured to receive information from the sensor and configured to control the dedicated actuator and the at least one of the integrated actuator and the intermediate actuator.

Abstract: An emergency lighting system (ELS) for an aircraft has a capacitor, a light emitting diode (LED) selectively powered by the capacitor, and at least one of a photoluminescent sign and a photoluminescent panel configured to receive light emitted from the LED.

Abstract: In some embodiments, a gear includes a toothed portion that has a plurality of teeth, an inner wall that defines a cavity, and a lubricant feed aperture. The lubricant feed aperture extends from the inner wall portion to the toothed portion. The lubricant feed aperture can deliver lubricant from the cavity to the toothed portion.

Abstract: An emergency lighting system (ELS) for an aircraft has a capacitor, at least one of an onboard power system and a ground power unit configured to charge the capacitor, and a light emitting diode (LED) selectively powered by the capacitor.