Abstract: A method including providing power to an aircraft probe anti-ice system, monitoring an actual power demand of the aircraft probe anti-ice system, monitoring an air data parameter and atmospheric conditions surrounding an aircraft and calculating an expected power demand of the aircraft probe anti-ice system based on the air data parameters and the atmospheric conditions, comparing the actual power demand of the aircraft probe anti-ice system to the expected power demand, and performing a corrective action if the actual power demand and the expected power demand are different by more than an acceptable amount.

Abstract: A variable camber wing for mounting to a vehicle chassis has an actuator shaft and a static pin extending from the chassis. The wing's nose segment defines a proximal edge and a distal edge and has a channel therethrough between the proximal and distal edges, an arcuate aperture therethrough aft of the channel, and a second aperture therethrough aft of the arcuate aperture. The wing has a first linkage defining a clevis on a proximal end and hingeably connected to the nose segment. The clevis can rotatably engage with the static pin extending through the arcuate aperture. A second linkage defines a second clevis on a proximal end and a distal edge. The second linkage is configured to hingeably connect to the first linkage.

Abstract: An aircraft wing (2) including a main wing (3) and a wing tip device (4) at the tip of the main wing (3), wherein the wing tip device (4) has a variation of leading edge droop with respect to unrolled span-wise position such that flow separation on the wing tip device (4) first occurs in an outboard region (O) of the wing tip device (4). The leading edge droop of the wing tip device (4) may be a maximum in an outboard region (O) of the wing tip device.

Abstract: An autonomous cargo container retrieval and delivery system locates a select cargo container and maneuvers an unmanned aerial vehicle proximate to the container for retrieval. The vehicle positions itself to engage the cargo container using a grasping mechanism, and, responsive to engaging the cargo container, retracts the cargo container toward the vehicle. As the cargo container is retracted toward the vehicle, weight sensors within the retrieval mechanism sense the weight and the weight distribution of the cargo container, and, can modify the cargo container's location on the vehicle to optimize vehicle flight operations or replace the container on the ground and alert the operator that the cargo container is too heavy or has an improper weight distribution. Upon mating the cargo container with the vehicle, a coupling mechanism latches or secures the cargo container to the vehicle for further flight and/or ground operations.

Abstract: An assembly is provided for active laminar flow control. This assembly includes a panel, which panel includes an outer skin, an inner skin and a plurality of plenums between the outer skin and the inner skin. Each of the plurality of plenums is fluidly coupled with a respective array of perforations through the outer skin. The panel is constructed from fiber-reinforced composite material.

Abstract: An exemplary electric distributed propulsion system includes two or more rotors that are individually controlled by the rotational speed of associated motors, an input control connected to the associated motors to provide rotational speed control to the two or more rotors to produce a desired net thrust, and a logic connected to the input control and the associated motors, the logic for controlling speed and direction of the two or more rotors to achieve the desired net thrust and to avoid a motor speed condition.

Abstract: An aircraft undercarriage comprising a top portion (2) secured to the aircraft and a steerable bottom portion (3) carrying wheels and suitable for being steered by a steering control system (4) fitted to the undercarriage or else by an external towing device, the undercarriage being fitted with visual warning means (9) for indicating an angular overstroke. The visual warning means comprising at least one visual indicator (14) mounted to move between a retracted position that is invisible and an extended position that is visible. An aircraft provided with an undercarriage.

Abstract: A door system for an aircraft includes a door frame defining a door opening with a first perimeter strut and a second perimeter strut spaced apart from the first perimeter strut, at least one first frame stopper attached to the first perimeter strut and at least one second frame stopper attached to the second perimeter strut. The frame stoppers each comprise a first contact portion projecting into the door opening and having a first toothing. The first toothings are each formed on an inner surface of the first abutment portion. Further, the door system comprises a door mounted movably relative to the door frame and disposed in the door opening in a closed state, and a number of door stoppers corresponding to the number of frame stoppers disposed on opposite sides of the door and connected to the door, each door stopper having a second abutment portion. The second abutment portion comprises a second toothing formed complementary to the first toothing.

Abstract: A trimmable horizontal stabiliser actuator (THSA) control system includes least one main THSA motor for driving the THSA in response to inputs from a flight control computer (FCC), a pilot trim control system for manual control of the THSA by a pilot overriding the FCC. The pilot trim control system comprises a trim control for receiving an input from the pilot, the trim control including a trim control sensor for detecting the input from the pilot and providing a pilot trim control signal; a THSA trim control motor for driving the THSA in response to the pilot trim control signal; and an electronic override system for giving inputs from the pilot priority over inputs from the FCC.

Abstract: A method of detecting that ice has been shed from an external surface of a component is provided, the method comprising applying power to a heating means to provide heat to said external surface. The method further comprises sensing the temperature of the component and calculating the rate of change of temperature increase of the external surface over time. Further, the method comprises detecting a change in said rate of change of temperature increase over time, wherein said detected change in rate of change of temperature increase indicates that said ice has been shed from said external surface of said component.

Abstract: A vehicle body may have an internal skeleton forming a wing shape, and a skin formed over the internal skeleton. The skin may include a matrix material, and a plurality of continuous fibers encased within the matrix material. The plurality of continuous fibers may curve from a base end near a fore/aft center of the wing shape outward toward leading and trailing edges of the wing shape at a tip end.

Abstract: A turbofan engine may comprise an inlet and a fan case coupled to the inlet. An engine case may be coupled to the fan case via a vane extending between the fan case and the engine case. A strut apparatus may extend from the fan case and limit deflection of the fan case. The strut apparatus may comprise a first end proximate the fan case, and a second end coupled to at least one of the engine case or a structure for mounting the turbofan engine to an aircraft.

Abstract: Examples include an apparatus for providing a point of attachment to a structural component, the apparatus including: a first grommet comprising: a head; and a shaft that extends from a first side of the head, where the shaft comprises a first attachment component opposite the head; a gasket bonded to a second side of the head that is opposite the first side, where the gasket, the head, and the shaft are aligned and a hole is formed through the gasket, the head, and the shaft; and a second grommet comprising a second attachment component that is configured to engage the first attachment component of the first grommet.

Abstract: A device for deicing a wall of an aircraft, comprising a closed circuit. The closed circuit comprises at least one condenser, positioned in the environment of the wall that is to be deiced, and in which a heat-transfer fluid condenses, generating energy in the form of latent heat which is transmitted to the wall that is to be deiced, at least one evaporator positioned in the environment of a heat source sited remotely with respect to the wall, and in which the heat-transfer fluid evaporates, absorbing energy in the form of latent heat coming from the heat source. At least part of the closed circuit is facing, in contact with, or positioned in, the wall that is to be deiced, being made of a material transparent to electromagnetic fields.

Abstract: A dispersement system for a UAV is provided. The dispersement system may include a plurality of dispersement nozzles operable to dispense an agricultural product at variable flowrates, a flow controller responsive to instructions and operable to regulate a volume of the agricultural product dispensed by the dispersement nozzles, and a control system. The control system may include a plurality of sensors operable to monitor a plurality of flight parameters and a processing unit configured to model an effect of the plurality of flight parameters on first flow control instructions corresponding to a prescription coverage of the agricultural product and calculate and output modulated flow control instructions to the flow controller. The control system may modulate the first control instructions to change a flowrate of one or more of the plurality of dispersement nozzles to achieve an actual coverage of the agricultural product that is closer to the prescription coverage.

Abstract: A multi-rotor unmanned aerial vehicle (UAV) includes a central body, a plurality of branch members connected to the central body, each branch member configured to support a corresponding actuator assembly, a communication module disposed within the central body and configured to establish a communication channel between the UAV and a remote device, and an indicator light disposed on one of the plurality of branch members. The indicator light is configured to indicate whether the communication channel is established.

Abstract: A force limiting system and method are provided for limiting loads in aircraft nose or main landing gear having wheels powered by taxi drive systems mounted within the landing gear wheels to drive aircraft on the ground. The force limiting system may include mechanical components selected to limit or minimize spin-up mass and to releasably connect the taxi drive system to a landing gear wheel section so that operation of the taxi drive system to drive a landing gear wheel is prevented in the presence of a predetermined maximum load. The load limiting system employs mechanical components engineered to securely connect the taxi drive system to the landing gear wheel during operation and to release the taxi drive system from connection to the wheel when loads applied to system components exceed an established or recommended maximum load.

Abstract: A system for communicating between passenger seats and an aircraft galley. The system may include a control unit including a display area for interfacing with a crew member. The system may include a plurality of devices, each positioned at a respective passenger seat. The control unit may be adapted to display on the display area data related to a particular order, including a location of an associated passenger seat. The control unit may be further adapted to transmit to a particular device associated with the order notifications concerning a status of the particular order.

Abstract: Aircraft capable of vertical takeoff and landing, hovering, and efficient forward flight are described. An aircraft includes two side mounted tiltable proprotors and a central rotor disposed above the proprotors. The proprotors are tiltable between at least a horizontal position for forward flight and a vertical position for vertical or hovering flight. The central rotor may be powered for vertical and transitional flight modes and may turn by free autorotation during forward flight. The proprotors may be differentially tilted during vertical or hovering flight to counter torque effects of the central rotor. The central rotor may be foldable and/or easily detachable from the aircraft to facilitate storage and transportation. Left and right proprotors may provide both forward thrust and attitude control. Control inputs to left and right proprotors may be connected directly to an autopilot creating closed loop actuation using motor RPM feedback.

Abstract: A powertrain including an engine; a main drive shaft assembly; a primary clutch mechanism coupled to the engine and the a main drive shaft assembly, the primary clutch mechanism being operable to connect or disconnect the main drive shaft assembly and the engine; an axle shaft coupled transversely to the main drive shaft assembly; a secondary clutch mechanism having a driving member coupled to an end of the axle shaft; a drive wheel coupled to a first driven member of the secondary clutch mechanism; and an air propulsion unit coupled to a second driven member of the secondary clutch mechanism. The secondary clutch mechanism being operable to engage or disengage the first driven member and/or the second driven member to the driving member so as to connect or disconnect the drive wheel and/or the air propulsion unit to the axle shaft. A vehicle including the powertrain.