Abstract: An aircraft having an airframe including a hollow structure referred to as a “storage” structure, the storage structure having an opening that is open to the outside of the aircraft. A sealing device extends around the opening, the sealing device including at least one compressible gasket. A plurality of non-removable fittings are fastened to the storage structure. At least one removable storage shell comprises at least a covering configured to close the opening while compressing each gasket. Removable fittings of the storage shell are attached in reversible manner to the non-removable fittings by respective elongate fasteners passing through each removable fitting and the non-removable fitting.

Abstract: A pneumatic deicer includes a base layer, a forming layer, a first chamber, and a first sensor. The base layer has an inlet, a first side, and a second side. The forming layer is connected to the base layer along at least two seams and has inner side and an outer side with the outer side being distant from the base layer. The first chamber is formed between the base layer and the forming layer and configured to be inflated by air passing into the first chamber through the inlet in the base layer. The first sensor is situated within the first chamber.

Abstract: In an on-orbit configuration, a spacecraft having a center of mass and a pitch axis passing through the center of mass includes a main body, a first solar array, and a first thruster is operable in a geostationary orbit with the first solar array deployed, proximate to a first north or south surface of the main body, such that a rotational axis of the deployed first solar array is substantially parallel to the pitch axis. The first thruster is disposed proximate to a second north or south surface of the main body, the first thruster having a thrust vector that is approximately coaligned with the pitch axis, the second surface being opposite to the first north or south surface. No solar array is proximate to the second surface.

Abstract: An evacuation slide assembly for an aircraft may comprise a main body configured to extend from a sill of the aircraft toward a surface within a range of angles relative to vertical when deployed so as to allow persons to safely slide down the main body to the surface. The main body may include a head end configured to attached to the sill of the aircraft, and a toe end opposite the head end. A first extendable portion may be coupled to the head end of the main body and may be in operable communication with a height sensor. The first extendable portion may be configured to deploy to adjust for a variation in a positional relationship between the surface and the sill to maintain the main body within the range of angles.

Abstract: An unmanned aerial vehicle for determining geolocation exclusion zones of animals. The unmanned aerial vehicle includes a processor-based monitoring device to track geolocation information associated with an animal from the unmanned aerial vehicle, an identification device mounted on the unmanned aerial vehicle to identify the animal and to track a position of the animal over time, and a mapping device coupled to the monitoring device to determine locations where the animal has traversed and to identify where an encounter with the animal is reduced.

Abstract: Provided are flight control mechanisms, such as omnidirectional thrust mechanisms (OTMs), and methods of using such mechanisms. These mechanisms may be positioned in wings, tails, or other components of aircraft. A mechanism may comprise a center member and top and bottom panels. The center member may comprise two curved segments joint at a center edge. The top and bottom panels may be independently pivotable relative to the center member. At high speeds, the top panel and/or the bottom panel may be pivoted outward to change the lift, drag, roll, and/or other flight conditions. The mechanism may also include a gas nozzle to direct compressed gas to the center member. The center member and/or the top and bottom panels redirect this gas resulting in forces in one of four directions, which are used for controlling the aircraft at low speeds, down to hover.

Abstract: An overhead aircraft passenger service unit, which is configured to be placed above the passenger seats within an aircraft cabin, comprises at least one cavity for housing at least one oxygen mask and at least one removable cover, which at least partially covers an opening of the cavity. The removable cover houses and/or supports at least one functional component.

Abstract: A jet engine support structure includes an inboard support fitting that is configured to be operatively attached to the jet engine, an outboard support fitting that is configured to be operatively attached to the jet engine, an inboard longeron that is configured to be attached to the inboard support fitting and an exterior underside surface of an aircraft wing, an outboard longeron that is configured to be attached to the outboard support fitting and the exterior underside surface of the wing, and a drag brace fitting that is configured to be attached to the inboard longeron and the outboard longeron and operatively attached to the jet engine. These component parts are employed in operatively attaching the jet engine to the aircraft wing. The same set of component parts is employed in operatively attaching the jet engine to either a left side or port side wing or to operatively attach a jet engine to a right side or starboard side wing.

Abstract: An aircraft includes a fuselage and first and second pairs of aerofoils, the aerofoils of each pair extend from opposing sides of the fuselage. Each aerofoil includes a first lift body and a second lift body which is arranged behind the first lift body in a direction of flow of the aerofoil. The second lift body is pivotable relative to the first lift body between a cruising flight position in which both lift bodies together define an elongate and substantially continuous cross section of the aerofoil in the direction of flow, and a take-off/landing position in which the second lift body is angled downwards relative to the first lift body in order to increase a lift of the aerofoil. At least one engine is arranged on the second lift body of at least one of the first and second pairs of aerofoils.

Abstract: An aircraft includes a fuselage, having a crown section and a keel, a first passenger cabin, having a first floor, located in an aft portion the fuselage, and a first cargo deck, located below at least a portion of the first passenger cabin. A forward split level cabin including an upper second cabin having a second floor above the level of the first floor, and a lower third cabin beneath the upper second cabin and having a third floor below the level of the first floor. A second cargo deck is located in the forward portion of the fuselage and beneath at least a portion of the lower third cabin. The crown section has a substantially constant cross-sectional shape fore-to-aft above the first passenger cabin and the split level cabin.

Abstract: A control method for controlling aerodynamic means of an aircraft having mechanically decoupled flight controls enabling the aircraft to be piloted by at least two pilots. The aircraft has at least two control members operated by respective ones of the at least two pilots and each enabling control signals to be generated for causing the aerodynamic means to move relative to an incident air stream. The control method includes piloting logic (“operational” logic). The operational logic includes a dual operating mode in which each control member can control the aerodynamic means. In the dual operating mode, only one of the at least two control members, (the “activated” member), has exclusive control over a full travel amplitude of the aerodynamic means. The other control member, (the “deactivated” member), then is temporarily inoperative on the aerodynamic means.

Abstract: A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.

Abstract: An aircraft monument comprising a desk and a movable part that is mounted to the aircraft monument by means of an attachment device. The movable part is pivotable about an axis between a first position in which the movable part covers a first area of the desk and is essentially arranged inside of the aircraft monument such that its front faces in a first direction towards the back of the aircraft monument, and a second position in which the movable part is at least partially arranged outside of the aircraft monument and its front faces in a second direction that crosses the first direction. The movable part, in its second position, covers a second area of the desk that is less than the first area.

Abstract: An aircraft windshield that improves pilot and co-pilot's perception of the outside world. The windshield includes a transparent panel held inside a structure of the aircraft, in which the upper part and the lower part are bridged so that the loads applied to the panel are (at least partially) diverted. Due to part of the loads applied on the panel being diverted, it is possible to provide a larger window panel than currently available that offers better visibility to the outside.

Abstract: An airbag assembly for leg flail protection and associated systems and methods are described herein. An airbag system configured in accordance with an embodiment of the present technology can include, for example, a housing having a cavity and an opening in communication with the cavity, an airbag stowed within the cavity, and an inflator operably coupled to the airbag. The airbag can be configured to deploy through the opening of the housing during a crash or other significant dynamic event. The airbag can deploy outwardly from the side-facing seat to reduce occupant leg rotation during the crash or other significant dynamic event. The airbag can be pushed out of the housing before it is fully inflated. The airbag can be stowed and include folded first and second opposing side portions such that when the airbag is deployed, the portion nearest the occupant unfurls toward the occupant prior to the other portion farthest from the occupant unfurling in a direction away from the occupant.

Abstract: An aerial vehicle includes a body having a longitudinal axis, a plurality of movable members emanating connected to the body, at least one motor, and at least three aerodynamic propulsors driven by the at least one motor. The movable members are connected to the body and extend away from the body.

Abstract: A zone is provided between the forward pressure bulkhead in an aircraft and the floor. The nose section of the aircraft in which the flat surface pressure bulkhead including at least one transverse frame comprises at least two rods, of which one of the front ends is attached to the bulkhead and/or the frame and the other rear end is attached to a structural element, the two rods further apart from the front to the rear, thus providing a work space. Therefore, the rods provide a more comfortable work area while picking up part of the loads from the bulkhead to the floor.

Abstract: The present invention is directed to reducing noise resulting from a wing tip vortex of a wing such as a flap. A flap of an aircraft includes a flap main body provided to a parent wing in a deployable manner, and a vortex generation portion including a protruding member, the protruding member being provided to protrude from an upper surface at least at an end of the flap main body on an outboard side in a span direction and forming a predetermined angle to an axial direction of the aircraft. A rear end of the protruding member is located on the side adjacent to a side-end edge at the end of the flap main body in the span direction relative to a virtual line passing through a front end of the protruding member and being parallel to the axial direction.

Abstract: An insulation component to be attached to a fuselage structure of an aircraft. The insulation component extends in a planar manner, and at least one peripheral recess, running transversely to the at least one longitudinal recess, is formed in a first surface of the insulation component configured to receive a respective associated peripheral support of the fuselage structure.

Abstract: An aircraft landing gear structure includes a strut assembly configured to transition between a compressed configuration, an extended configuration, and a retracted configuration. The strut assembly has a compressed length, an extended length, and a retracted length, such that the compressed length and retracted length are less than the extended length. The strut assembly includes an upper tubular housing, an upper bulkhead configured to be translated between a lower position and an upper position, a lower tubular housing operatively coupled to the upper tubular housing, a lower bulkhead supported by the lower tubular housing, and a pressure chamber defined between the lower bulkhead and the upper bulkhead. A volume of strut liquid and a mass of strut gas are positioned within the pressure chamber. A method of retracting a strut assembly includes longitudinally translating an upper bulkhead within an upper tubular housing from a lower position to an upper position.