Abstract: Noise-abatement systems provide noise abatement to a wing assembly provided with a forward edge slat and include an elongate shield element which is unconnected but positionable adjacent to a lower trailing edge of the edge slat along a lengthwise extent thereof, and a support web having a distal end fixed to the shield element and a proximal end capable of fixation to an interior cove surface of the edge slat adjacent an upper trailing edge thereof. The support web will therefore allow movement of the shield element towards and away from the lower trailing edge of the edge slat between an operative position wherein the shield element is positioned adjacent to the lower trailing edge of the edge slat along the lengthwise extent thereof and an inoperative position wherein the edge slat is spaced from the trailing edge of the edge slat and positioned in the cove region thereof, respectively.

Abstract: A system and method provides noninvasive mental state diagnostics and brain stimulation via consensual transcranial stimulation. The method utilizes face recognition associated with known physiologic measures to identify an emotional state-of-mind of a human subject and then provides or at least suggests a transcranial stimulation treatment for enhancing mental focus or for alleviating discomfort or anxiety by inducing a feeling of well-being. An example system arrangement utilizes a camera to scan a subject's facial expressions and, if the subject desires, provides a transcranial stimulation to the subject based upon an analysis of the facial expression. In one example environment, the system is used in the office or other workplace. In another example environment, the system is used in conjunction with a vehicle seat, such as for example a seat in a car, train, aircraft or other vehicle.

Abstract: Cargo load platform assemblies are especially adapted to provide support for a variety of cargo, such as auxiliary aircraft fuel tanks. According to certain embodiments herein, a load platform is provided which is adapted to being positioned onto a cargo deck of a cargo aircraft. At least one anti-rattle device is operatively associated with the load platform for positionally fixing the load platform to a tie-down ring of the cargo deck of a cargo aircraft. The cargo load platform may support a rigid fuel tank thereon so that auxiliary fuel tankage systems can be provided as may be needed.

Abstract: Retractable guide assemblies are provided to guide cargo load pallets onto a cargo deck of a cargo aircraft, the guide assembly having a support subassembly comprising a recessed housing box, a moveable guide subassembly pivotally connected to the support subassembly so as to be pivotally moveable relative thereto, and an actuator subassembly operatively interconnecting the moveable guide subassembly and the support subassembly. The actuator subassembly may thereby allow the moveable guide subassembly to be pivotally moveable between (i) a releasably locked stowed condition, (ii) a releasably locked deployed condition and (iii) a freely moveable unlocked maintenance condition.

Abstract: Seat assemblies are provided which include a seat base structure, a seat cushion supported by the seat base structure and at least a lateral outboard seat lip positioned relative to the seat cushion so as to assist a passenger during seat entry and exit. The lateral outboard seat lip is preferably attached relative to the seat cushion for manual movements between an extended position wherein the outboard seat lip extends outwardly thereby increasing effective surface area of the seat cushion and a deflected position wherein the outboard seat lip extends upwardly or downwardly relative to the seat cushion so as to thereby decrease the effective surface area of the seat cushion.

Abstract: Aircraft takeoff trajectory is automatically optimized to minimize Perceived Noise Level. A flight computer automatically performs all the actions to takeoff the airplane and assure that its real takeoff trajectory is compliant with the takeoff trajectory optimized. Variability of trajectory is eliminated through automation of pilot's actions during takeoff and assurance of an optimum trajectory. The system also provides for simultaneity of actions and the changing of aerodynamic configuration during takeoff.

Abstract: Methodologies to deal with electrical systems and power source failures for electric vertical takeoff and landing aircraft (eVTOL) design with distributed propulsion using multiple electric motors minimize required power source energy to perform an emergency landing procedure. Interconnecting electric loads and power sources in the “Ring Topology” concept considers combination of electric loads and power sources in order to reduce the impact on the loss of a power source, as well as to better utilize the remaining energy of the remaining power sources if any load becomes unavailable.

Abstract: Methods and system for locating an event on an aircraft using augmented-reality content, an array of ultrasonic devices configured in mesh topology, and deep learning.

Abstract: The present invention relates to a device for storing tires, particularly large tires, said tire storage device comprising a plurality of storage niches (10) and at least one elevator disposed in a front portion (31) of the device and engaging the plurality of storage niches (10), each storage niche (10) consisting of an inclined upper platform (II), a lower inclined platform (12), and a connecting platform (13) associating the upper platform (11) with the lower platform (12), the upper platform (11) comprising an inlet end of the tire (111) engaging the elevator and a second end (112) opposite the inlet end of the tire (111) engaging the connecting platform (13), the lower platform (12) comprising a first end (121) engaging the connecting platform and an outlet end of the tire (122) opposite the first end (121).

Abstract: Systems and methods are provided for storage in at least one on-board fuel tank of aircraft fuel under a predetermined pressure and at an internal ambient tank temperature. A passive heat exchanger having an exchanger inlet is fluid-connected to a propulsion engine of the aircraft to receive heated pressurized bleed air therefrom while an exchanger outlet is fluid connected to the fuel tank. The passive heat exchanger is configured to cool the heated pressurized bleed air from the engine by heat transfer to a surrounding environment by radiation and convection so as to supply pressurization air to the fuel tank at the predetermined internal tank pressure and the internal ambient tank temperature. A system controller is provided to provide the fuel tank with pressurized air at a predetermined temperature during various aircraft flight phases.

Abstract: Cargo aircraft having a cargo ramp and cargo door oppositely hinged relative to one another to allow access to the aircraft's cargo space may be provided with a flying boom mast that is physically mounted at the aft portion of the fuselage so as to configure such cargo aircraft for aerial refueling operations. The flying boom mast may therefore be operably associated with the aft portion of the fuselage and moveable between a stowed and deployed conditions relative to the aft portion of the fuselage, while a fuel supply line fluid-interconnects the flying boom mast with an on-board fuel supply of the aircraft so as to allow aerial refueling of a receiver aircraft when the flying boom mast is in the deployed condition thereof.

Abstract: A flexible distributed multi-system architecture for aircraft control integrates electronic computers comprising plural types of high integrity, dissimilar, generic and reconfigurable controllers (GECs) that can assume different purposes. GECs are configured as actuator controllers (able to control up to three channels including hydraulic or electro-mechanical actuators) or as Control Law Computers (able to calculate more sophisticated and processor demanding control laws). The multi-system architecture is built around a backbone of high performance, high integrity digital protocols and three hubs with dual connection to two different GECs.

Abstract: A no/low visibility automatic takeoff system for an aircraft obtains a runway reference centerline and aircraft pointing direction (via the aircraft's sensors) and automatically controls the aircraft pointing direction to track the runway reference centerline. An initial vector is obtained based on the initial position of the aircraft the first piloted initiation of the takeoff roll. After the system obtains a centerline, it automatically tracks the centerline and corrects aircraft trajectory so the aircraft heading closely matches the runway centerline as the aircraft proceeds down the runway.

Abstract: Aircraft cargo lock assemblies are capable of positionally restraining movement of a cargo load pallet in both vertical and horizontal planes relative to the cargo deck of the aircraft. According to certain embodiments, the lock assemblies will include an actuator case and a restraint element which comprises at least one restraint plate and restraint detent, the restraint element being connected to the actuator case for pivotal movements between locked and released conditions relative to an edge of a cargo load pallet positioned on a cargo deck of an aircraft so as to positionally restrain the cargo load pallet against movement in both vertical and horizontal planes relative to the cargo deck. An actuator assembly is operably connected to the restraint element for moving the restraint element between the locked and released conditions thereof.

Abstract: Separable partition assemblies provide privacy between adjoining aircraft cabin sections, e.g., between a main passenger cabin section and a section having an emergency exit and a belted toilet seat such as may be provided in executive aircraft. The separable partition assembly includes a bulkhead structure defining a bulkhead passageway opening to allow passenger egress from one vehicle cabin section to an adjoining vehicle cabin section that is provided with at least one panel sized and configured to close the bulkhead passageway. A nonpermanent mounting system mounts the panel to an inboard edge of the bulkhead structure to allow the at least one panel to be separably uncoupled from the bulkhead structure in response to exertion of a force of predetermined magnitude thereagainst to thereby allow unimpeded passenger egress between the adjoining vehicle cabin sections.

Abstract: Describes a deflection mechanism of the flap panels of an aircraft, the aforesaid deflection mechanism being connected to a wing of an aircraft by means of a first fixed structure and to the flap panels by linkage points, in order to support and deflect the flap panels in desired positions, the deflection mechanism of the flap panels of an aircraft comprises of a set of moving hinged links pivotally connected with each other and linked to a first fixed structure, and a hinged drive link connected to the flap panel and to a second fixed structure, the set of moving hinged links being linked to the flap panel by at least one linkage point in order to pivot jointly the moving hinged links deploying the flap panels in an initially predominantly rectilinear and subsequently deflected trajectory and at the same time aligned with a longitudinal direction of the aircraft, without the use of tracks and rollers, the hinged drive link being pivoted from the movement of the flap panels by the set of moving hinged links.