Abstract: A tandem-wing unmanned aircraft system (UAS) includes forward and aft wings mounted to the fuselage by frangible spar elements, the forward wings in a shoulder-wing configuration and the aft wings in a low-wing configuration. The forward and aft wings may incorporate fill-span multifunctional control surfaces on their trailing edges. The wing design prevents interference with airflow over the fuselage into a tail-mounted ducted propeller assembly, which pivots to provide vectored thrust. A nose compartment at the nose end of the fuselage may include a forward-mounted camera with a hemispherical field of view, the nose camera protected by transparent exterior panels. A ventral cargo compartment mounted amidships may include a ventral camera gimbal-mounted to provide an overhead perspective; the ventral camera may be gimbal-mounted for articulation along multiple rotational axes to provide additional views of the UAS exterior.

Abstract: Disclosed herein are technologies for a WYSIWYG user interface (UI) design tool that enables runtime behaviors (e.g., content update and user interaction) with UI controls during design time of such controls. That is, using a UI design tool in accordance with the technology described herein, the human designer can see and experience the runtime behavior of the UI controls while designing those controls. This Abstract is submitted with the understanding that it will not be used to interpret or limit the scope or meaning of the claims.

Abstract: In one set of embodiments, methods, systems, and apparatus are provided that include presenting, by a computer system, a task flow in a popup component of an application user interface executing in a user interface layer, where the task flow executes in an application layer of the computer system, and also include communicating, by the computer system, a first notification from the application layer to the user interface layer in response to normal completion of the task flow, and updating, e.g., closing, the component in the application user interface based upon the first notification. A second notification may be communicated from the user interface layer to the application layer in response to a user interface event that is associated with the popup component and causes an abnormal termination of the task flow. Presenting may include displaying the task flow in a region component in the popup component.

Abstract: A media recommendation system may score media items according to user recommendations, popularity, and/or recency. The scores may be weighted to produce an overall score for each media item. Media items may be added to a pool for a specific user, from which media items are selected for playback. The contents of the pool may be modified based upon user feedback and other data. The pool may be modified dynamically and/or in real time as media items are consumed or rated by the user.

Abstract: A heater of a piece of aeronautic equipment is intended to be arranged at the skin of an aircraft. The equipment includes a part intended to be arranged at the skin of the aircraft and elements for heating the part. The heating element include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it. Outside the evaporator, the circuit in which the fluid circulates is formed by a tubular channel with an empty section. At least part of the equipment is made from a material with a low heat conductivity.

Abstract: The invention relates to an overhead luggage compartment for an aircraft, comprising an upper luggage compartment element, a lower luggage compartment element movable between a locked and an open position, a holding device for holding the lower luggage compartment element in the closed position, a lifting spring for supporting the movement of the lower luggage compartment element from the open position to the closed position, and a retaining device for fixing the lifting spring in the tensioned state in the open position of the lower luggage compartment element. An operating handle for releasing the retaining device in the open position of the lower luggage compartment element is provided, wherein the lower luggage compartment element is movable, optionally with support by the lifting spring or with the lifting spring fixed in a tensioned state, from the open position to the closed position.

Abstract: Disclosed herein is a method of repairing damage to a fuselage barrel, having a one-piece construction, of an aircraft. The method includes determining at least a first virtual splice line and a second virtual splice line along the fuselage barrel in a direction parallel to a longitudinal axis of the fuselage barrel. The method also includes detecting damage in a first section of the fuselage barrel between the first virtual splice line and the second virtual splice line. The method further includes cutting through the fuselage barrel along the first virtual splice line and the second virtual splice line to physically separate the first section from a main section of the fuselage barrel. The method also includes removing the first section from the main section of the fuselage barrel, and splicing a new section to the main section of the fuselage barrel in place of the first section.

Abstract: In some embodiments, systems, apparatuses and methods are provided to enhance delivery of packages. Some embodiments provide an unmanned delivery system comprising: a rotational drive shaft; a crane motor cooperated with the drive shaft that is rotated by the crane motor; a first crane system with a first cord fixed with the first crane system, wherein the first crane system is configured to cooperate with the drive shaft to control the first crane system in controlling the spooling and retraction of the first cord; a control circuit coupled with the crane motor; and a stop switch electrically coupled with the control circuit and positioned to be contacted by a package release hanger secured with the first cord when the first cord is retracted to a first threshold; wherein the control circuit is configured to stop the crane motor in response to receiving a signal from the stop switch.

Abstract: An aircraft hand controller is disclosed. The hand controller includes a set of finger controls on a single hand grip structure, the set of finger controls including a first finger control configured to control throttle of the aircraft and a second finger control, separate from the first, configured to control rotation about a first rotational axis of the aircraft.

Abstract: In some embodiments, systems, apparatuses and methods are provided to enhance delivery of packages and/or cargo through the use of unmanned delivery aircraft. In some embodiments, a mechanical package release system is provided that comprises: a package release hanger configured to couple with and suspend from an unmanned delivery aircraft; and one or more tension supports each configured to secure with a package and to releasably couple with the package release hanger wherein a decrease of at least a threshold amount of a force being applied by the weight of the package on the one or more tension supports induces a mechanical release of the coupling between the one or more tension supports and the package release hanger resulting in a release of the package from the unmanned delivery aircraft.

Abstract: Systems, methods, and computer program products for directional force weighting of an active vibration control system involve arranging a plurality of force generators in an array, identifying individual component forces corresponding to force outputs of each of the plurality of force generators, determining a combination of the individual component forces that will produce a desired total force vector, and adjusting the outputs of each of the plurality of force generators such that the combination of the individual component forces are at least substantially similar to the desired force vector.

Abstract: An improved fin retention and release mechanism (15) comprising an elongated body (16), at least one fin (18a) mounted to the body and capable of moving from a stowed position (30) to a deployed position (32), an actuator (20a) connected to the fin and arranged to rotate the fin about a first axis (33), a fin retention member (19a) connected to the body and configured and arranged to rotate about a second axis (34) from a locked position (36) to a release position (38), the fin and the fin retention member configured and arranged such that the fin is held in the stowed position by the fin retention member when being in the locked position and the fin is not held in the stowed position by the fin retention member when being in the release position, and wherein actuation of the fin about the first axis by the actuator rotates the fin about the first axis in a first direction (39) and correspondingly rotates the fin retention member about the second axis in a second direction (40) opposite to the first direction

Abstract: A vortex generator arrangement for an aircraft comprising a surface section forming a flow surface interacting with a flow surrounding the aircraft in operation, wherein the surface section comprises an opening, a vortex generator movable between a retracted position and an extended position, a retainer for holding the vortex generator in the retracted position, a biasing structure for biasing the vortex generator towards the extended position and a release for releasing the vortex generator from the retainer such that the vortex generator can be moved towards the extended position. Further, a sealing membrane is provided completely sealing the opening when the vortex generator is in the retracted position. The vortex generator is movable through the membrane from the retracted position to the extended position. Furthermore, a flow control system, an aircraft and a method of controlling flow are described and claimed.

Abstract: A heavy-lift UAV frame includes a central frame portion having a symmetrical shape and forming a pocket area for receiving an avionics package. Top and bottom plates are secured to the central frame portion and include four corner members that extend diagonally outward therefrom. A plurality of boom arms are pivotally connected to the corner members and transition between an extended position for flight and a retracted position for storage and transport. Each boom arm includes a complementary dimension to one side of the central frame portion and is arranged parallel thereto when in the retracted position.

Abstract: A method of engaging a drive system with a rotating wheel of an aircraft landing gear is disclosed. A motor is operated to apply torque to a pinion so the pinion rotates. An engagement command is issued to an actuator at an engagement time, and the actuator operates the actuator in response to the engagement command to move the pinion from a neutral position to a contact position in which it contacts a rotating driven gear at an initial contact time, the rotating driven gear being mounted to a rotating wheel of an aircraft landing gear; then after the initial contact time operating the actuator to move the pinion further to a meshing position where the pinion meshes with the driven gear. A centre-to-centre distance between the pinion and the driven gear reduces as the pinion moves to the contact position and to the meshing position.

Abstract: An electrical connector is provided for both power and data transmission. The electrical connector comprises an electrical plug (100) having a plurality of pins (131˜138) and an electrical socket (200) having a plurality of passageways (220) which are arranged corresponding to the plurality of pins (131˜138). The pins (131˜138) of the plug comprise at least one signal pin (131, 136), two or more positive power pins (133, 134) and two or more negative power pins (132, 135). The pins (131˜138) of the plug can be disposed such that the positive power pins (133, 134) and the at least one signal pin (131, 136) are positioned on opposite sides of the negative power pins (132, 135).

Abstract: The invention relates to an aircraft landing gear (2) comprising:—a leg (6) having a first leg portion (8) that can be pivotably connected to a load-bearing structure of the aircraft (1) in order for the landing gear (2) to be deployed and retracted, and a second leg portion (9) that is rotatable in relation to the first leg portion (8);—a wheel (13, 14) that is rotatable in relation to the second leg portion (9), and an electric motor (15, 16) that can rotate the wheel (13, 14) in relation to the second leg portion (9);—a transmission mechanism (17) designed to selectively transmit torque generated by the electric motor (15, 16) to the wheel (13, 14) in order to rotate the wheel in relation to the second leg portion (9) or to the second leg portion (9) in order to rotate the second leg portion (9) in relation to the first leg portion (8).

Abstract: A modular payload system for an aircraft includes a modular bay recessed within the aircraft. The modular bay includes a modular bay interface. The modular payload system includes a plurality of payload modules each having a respective function and a payload interface adapted to connect to at least a portion of the modular bay interface. The plurality of payload modules are interchangeably insertable into the modular bay to enable the modular bay to support the functions of the plurality of payload modules.

Abstract: An auxiliary power unit for an aircraft includes a turbine engine. An inlet includes an opening and a passageway between the opening and the turbine engine. An acoustic splitter is supported within the passageway for attenuating noise within the inlet. An inlet door is movable between a closed position and a fully open position. A portion of the inlet door aligns with a part of the passageway in at least a first position and divides the passageway to deflect ice and noise in at least a second position. An air inlet and a method are also disclosed.

Abstract: An evacuation slide may comprise an arched tube configured to extend between a first side tube and a second side tube of the evacuation slide and a strap configured to be coupled between the arched tube and a center tube of the evacuation slide. The arched tube may be configured to provide vertical support to the first side tube and to the second side tube in response to a tension in the strap. The evacuation slide may comprise a dual lane slide, the first side tube and the center tube defining a first lane and the second side tube and the center tube defining a second lane.