Abstract: One-piece molded thermoplastic L-shaped and Z-shaped support brackets are described for supporting wiring and/or tubing. The support brackets will include a lower support flange, a backing flange, and a junction region having a concave inner surface and a convex outer surface which integrally joins the lower support flange and the backing flange to one another at a substantially right angle. The support brackets may be provided with a unitarily molded nut plate boss and a metal threaded nut cylinder which is embedded within and overmolded with the nut plate boss. Alternatively, a wire, cable or tubing mount unitarily formed as a one-piece molded unit with one of the support flanges so as to dependently extend therefrom.

Abstract: Thermo-pneumatic anti-icing systems include port and starboard anti-icing subsystems operatively interconnecting heated engine bleed air discharged from port side and starboard side turboprop engines with port and starboard airfoils, respectively, associated with an aircraft to thereby provide in-flight anti-icing protection to the port and starboard airfoils, and an auxiliary power unit (APU) capable of discharging a supply of heated APU bleed air to the port and starboard anti-icing subsystems during an abnormal single engine or a single pneumatic bleed air operational condition. A controller may command respective port and starboard cross bleed valves to open and thereby allow the APU bleed air to be supplied to the one port or starboard anti-icing subsystem that is incapable of delivering heated engine bleed air from the port side turboprop engine or the starboard side turboprop engine, respectively.

Abstract: Thermally configurable structural elements (e.g., aircraft components such as an aircraft winglet spar) capable of assuming at least first and second structural configurations are provided whereby the structural element includes an integral actuation mechanism may be formed of sintered shape memory alloy (SMA) particles and sintered non-SMA particles formed by an additive layer manufacturing (ALM) process, such as 3D printing. The ALM process thereby provides by at least one thermally configurable region, and at least one non-thermally configurable region which is unitarily contiguous with the at least one thermally configurable region. The at least one thermally configurable region is capable of assuming at least first and second positional orientations in response to the presence or absence of a thermal input to thereby cause the structural element to assume the at least first and second structural configurations, respectively.

Abstract: Vertical short takeoff and landing (VSTOL) aircraft include primary airfoils extending outwardly from a forward region of the aircraft fuselage, and secondary empennage airfoils extending outwardly from an aft region of the aircraft fuselage so as to be separated from the forward primary airfoils and thereby define a space therebetween which accommodates non-cyclic controllable propellers operably driven by a respective engine of a propulsion unit. The propulsion units are mounted for pivotal movement within the defined space between the primary airfoil and the secondary empennage airfoils so as to achieve a first operational position wherein the thrust line of the propellers is orientated substantially parallel to the longitudinal axis of the fuselage and a second operational position wherein the thrust line of the propellers is oriented substantially perpendicular to the longitudinal axis of the aircraft. The propulsion units may be mounted aft of the aircraft center of gravity (CG).

Abstract: One example non-limiting example provides a full representative part 25 commercial aircraft flight deck with a visual system integrated with a robotic manipulator to provide an immersive simulation environment for training and research purposes. Such technology provides an architecture that provides visual blending-warp adjustment along with visual system integration, including for example Spherical screen design, Structural design and Projectors allocation.

Abstract: A network of computing devices connected to the central AOG management server execute the process of collecting data from a crew with a maintenance controller, supporting the creation of an unique electronic data package to record the data, submitting a maintenance requests from the server to independent mechanics mobile devices and/or maintenance repair and overhaul (MRO) computing systems for maintenance using the collect data, supporting maintenance control center controller to identify the needed materials for the events, providing visibility of the case solution progress to all parties involved and/or effected and providing ways to retrieve all data related to specific cases and creating analyses and reports to support Vehicles Operators (e.g., Airlines), independent mechanics, MROs (maintenance repair overhaulers), material providers and OEMs to improve their processes to solve events.

Abstract: Aircraft air data is estimated using a neural network trained to be independent of any signals from air data sensors whose values are based on air flow pressure measurements.

Abstract: An aircraft wing is provided having a wing leading edge, a cut-out opening in the wing leading edge, a telescopic tube extending through the cut-out opening and connected to an internal duct of a wing leading edge slat to establish fluid communication with heated air associated with an aircraft anti-icing system, wherein the telescopic tube is moveable between retracted and extended conditions in response to the wing leading edge slat being moved between slat retraction and deployment positions, respectively, and a cover assembly comprising a cover member operatively connected to the telescopic tube to close the cut-out opening and allow synchronous movement of the cover member with the telescopic tube in response to the telescopic tube being moved between the retracted and extended conditions thereof.

Abstract: Installation of powered actuators in the leading edge of a control surface in order to have a better weight distribution. The systems described herein propose an actuation system with a static ground structure used to move a control surface of an aircraft. The actuation system, and the ground structure are aligned with the center of rotation of the control surface, providing the aircraft with flutter suppression. This proposal is an approach to use the actuator in a place favorable to the mass balancing and reducing or even dismissing the usage of mass balancing, saving weight and cost.

Abstract: Seal cap devices are provided as an integral (one-piece) structure comprising an open-ended cylindrical body member sized so as to surround a threaded shaft of a fastener, the body member including an upper wall having (i) an arcuate interior edge which defines an aperture to allow threaded engagement with distalmost threads of the threaded shaft of the fastener, and (ii) at least one slot radially extending from the aperture. The upper wall may include opposed slots radially extending from the aperture, e.g., a pair of opposed slots radially extending from the aperture that are separated from one another by an angle of about 90°. A sealant material within the cap may therefore envelope the threaded shaft of the fastener and any collar nut associated therewith to provide a reliable seal.

Abstract: For aircraft taxiing, an aircraft is equipped with an electric machine installed in a propulsor gearbox (PGB), in parallel to the gas turbine, working in motor mode during taxi, and in generator mode during flight phases (such as take-off, climb, cruise, descent, approach and landing). Typical current systems which use an electric machine in the PGB do not use the electric machine in motor mode for taxi operations (i.e., it is only an additional generator). An optimized power supply providing a combination of a thermal engine such as an Auxiliary Power Unit (APU) and an electric energy storage system such as a battery provides power to the PGB electric machine even when the gas turbine is off.

Abstract: Unmanned aircraft have aligned forward and aft propulsion systems possessing different performance and/or noise characteristics. According to some embodiments, unmanned aircraft have a forward engine and a forward tractor propeller and an aft engine and an aft pusher propeller. Selected ones of forward and aft propulsion systems will thus be provided to have greater and lesser operational flight performance characteristics and greater and lesser noise signature characteristics, respectively, as compared to the other. For example, the forward propulsion system may be provided with the greater operational flight performance and higher signature characteristics as compared to the aft propulsion system, while conversely the aft propulsion system may be provided with a lesser flight performance and lower noise signature characteristics as compared to the forward propulsion system.

Abstract: Automatic system management is provided by controlling/managing part or all of the system operation through the predefined properties embedded in the components of the management system itself. The creation of Quanta with properties allow the programming of the rules for the system management in a way that any user, client, provider or any other type of participant can interact with the system without the need of an intermediary or approver.

Abstract: An aircraft with the capability of taxiing with main engines off uses the energy stored in a mechanical flywheel to power a propulsor(s) providing taxiing thrust. The flywheel can store energy generated by the propulsor operating as a wind turbine and/or by a power turbine in fluid coupling with the exhaust of a gas turbine engine and/or an expansion turbine operating with bleed and/or APU air.

Abstract: Noise-abatement for a leading edge wing slat is provided by a noise-abatement airflow shield integral with the lower trailing edge of the slat, wherein the shield is reciprocally autonomously curveable from a substantially planar configuration when the slat is in a retracted position thereof and into a convexly curved configuration when the slat is in a deployed position thereof.

Abstract: The example non-limiting technology herein provides a Synthetic Aperture Radar (SAR) solution on board a micro-satellite that provides global revisit within 1 month; a cost below US$ 10 million; and satellite mass lower than 100 kg. One solution uses an inflatable Cassegrain type antenna with a phased beam steering array in the 1.2 GHz band.

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.