Abstract: A payload retrieval apparatus is provided including a stand or base, wherein the base or stand has an upper end and a lower end, a first sloped surface positioned over the upper end of the stand or base, a second sloped surface positioned over the upper end of the stand or base and adjacent the first sloped surface, a tether slot positioned in a channel having a first end and a second end, the channel positioned under or near the first sloped surface, and a payload holder positioned at the second end of the channel, wherein the payload holder is adapted to secure a payload.

Abstract: An armrest assembly for a passenger seat may include an armrest and an attendant step assembly. The armrest may include a top side and a bottom side, and the attendant step assembly may be connected to the bottom of the armrest. The attendant step assembly is movable between a stowed position and a deployed position relative to the bottom side of the armrest.

Abstract: Embodiments are directed to releasing smaller unmanned aerial vehicles from larger unmanned aerial vehicles. Apparatus and system embodiments are disclosed for physically retaining and ejecting the smaller unmanned aerial vehicles, including the communication networks associated with the command and control of both the smaller unmanned aerial vehicles and the larger unmanned aerial vehicles.

Abstract: An embodiment is a system including an external passenger seating unit comprising at least one seat; and a translation mechanism for translating the external passenger seating unit between a first position in which the external passenger seating unit is stowed in a payload bay of an aircraft and a second position in which the external passenger seating unit is deployed external to the aircraft for accommodating at least one passenger.

Abstract: An aircraft portion includes a fuselage oriented in a longitudinal direction, an airfoil made up of at least one pair of wings arranged on either side of the fuselage in a transverse direction orthogonal to the longitudinal direction, and an airfoil-fuselage junction fairing at the interface between the airfoil and the fuselage. The junction fairing has, in a vertical plane, a lower profile and, in a horizontal plane, a horizontal profile at the junction of the outer surface of the junction fairing with the convex side of each wing. The horizontal profile and/or the lower profile successively has, in the longitudinal direction, a convex front segment, a concave intermediate segment, and a convex rear segment.

Abstract: The aircraft (10) comprises a fuselage (11) and a rhombohedral wing structure (12) comprising front wings (13, 14) mounted on a front wing-root support (17) and rear wings (15, 16) mounted on a rear wing-root support (18). At least two wings (13, 14) support an engine (24, 26) provided with a propeller (25, 27). The rear end of the fuselage supports an engine (21) provided with a propeller (22). The aircraft comprises means (28 to 35) for tilting said engines, the rotary shaft of each of the propellers being tilted between an orientation parallel to the main axis of the fuselage and an orientation perpendicular to the main axis of the fuselage and to an axis extending through the ends of the front wings.

Abstract: The present invention includes a hybrid propulsion system for an aircraft comprising: one or more turboshaft engines that provide shaft power and are capable of providing thrust; at least one of: one or more electrical generators or one or more hydraulic pumps connected to a shaft of the one or more turboshaft engines; and at least two rotatable nacelles, each nacelle housing at least one of: one or more electric motors or one or more hydraulic motors each connected to a proprotor, wherein the electric motor is electrically connected to the electric generator, or the hydraulic motor is connected to the hydraulic pump, respectively, wherein the proprotors provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight, and provide thrust whenever the aircraft is in forward flight.

Abstract: Vertical take-off and landing (VTOL) aircraft can provide opportunities to incorporate aerial transportation into transportation networks for cities and metropolitan areas. However, VTOL aircraft can be sensitive to uneven weight distributions, e.g., the payload of an aircraft is primarily loaded in the front, back, left, or right. When the aircraft is loaded unevenly, the center of mass of the aircraft may shift substantially enough to negatively impact performance of the aircraft. Thus, in turn, there is an opportunity that the VTOL may be loaded unevenly if seating, luggage placement, and/or positions of internal components are not coordinated. Among other advantages, dynamically assigning the payloads and adjusting components of the VTOL aircraft can increase VTOL safety by ensuring the VTOL aircraft is loaded evenly and meets all weight requirements; can increase transportation efficiency by increasing rider throughput; and can increase the availability of the VTOL services to all potential riders.

Abstract: A system for restraining a cargo container in a cabin of an aircraft is disclosed. The system may include a guide rail, a rail and a plurality of rollers. The guide rail spans a length of a seat track and is releasably coupled to the seat track at one or more locations on a bottom surface of the guide rail. The rail is attached to a surface of the cargo container. The rail engages with the guide rail. The plurality of roller are coupled to the guide rail. The rollers engage a surface of the rail. The rail has two side surfaces that partially enclose two side surfaces of the rollers. When the cargo container deviates from a path defined by the guide rail, one of the side surfaces of the rollers abuts one of the side surfaces of the rail.

Abstract: Embodiments are directed to systems and methods for deploying an outboard rotor blade of proprotor pylon to act as an extended lifting surface. Blade control actuators may provide primary rotor flight control as well as providing fold linkage actuation when fold locks are disengaged. During cruise flight, the blade control actuator may provide feathering inputs to the extended rotor blade, wherein the amplitude and frequency of feathering inputs are tuned to mitigate undesirable wing and fuselage dynamic modes thereby enhancing aircraft stability. The deployed rotor blades also improve the total lifting area of the aircraft, which may increase aircraft range and efficiency.

Abstract: Tail boom drive systems for helicopters are described which utilize a fan internal to the tail boom to provide yaw control, and an external propulsor to provide forward thrust. In one embodiment, the tail boom drive system includes a shaft, a fan, and a propulsor. The shaft is disposed lengthwise within an interior space of the tail boom, and the shaft has a first end and a second end. The fan is mechanically coupled coaxially to the shaft within the interior space between the first end and the second end, and the fan generates a variable airflow directed towards the second end that is ejected from the interior space substantially perpendicular to the tail boom. The propulsor is external to the tail boom and is mechanically coupled coaxially to the shaft at the second end, and the propulsor generates a variable thrust directed towards the first end.

Abstract: Provided are various spacecraft propulsion systems, and associated methods of operation. A spacecraft comprises an ion propulsion system and an ion blocker suspended from the spacecraft via one or more electrically insulated tethers. The ion propulsion system is configured to generate a first propulsive force by emitting a charged ion beam in a direction with an ion velocity vector comprising an ion vector component that is perpendicular to a magnetic field of a planet, such as Earth. The magnetic field causes the ion beam to curve toward the ion blocker at a trajectory such that ions within the ion beam are blocked by the ion blocker to generate a second propulsive force on the ion blocker. The ion blocker blocks the ions by contacting or deflecting the ions. The ion blocker is positioned approximately twice the gyroradius of the ion beam trajectory.

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: A wing for an aircraft, including a main wing, a slat, and a connection assembly movably connecting the slat to the main wing, such that the slat is movable between a retracted position and at least one extended position. The connection assembly includes a first connection station and a second connection station spaced apart from the first connection station in a wing span direction. The object, to prevent the slat from skewing, is achieved in that the connection assembly includes a sync shaft coupling the first connection station to the second connection station for sync movement of the first and second connection stations.

Abstract: An orientation assembly includes a platform and a locking assembly engageable with the platform and positionable in a first state in which the platform is permitted to rotate about a lateral axis and inhibited from rotating about a longitudinal axis perpendicular to the lateral axis, and a second state in which the platform is permitted to rotate about the longitudinal axis and inhibited from rotating about the lateral axis.

Abstract: According to one implementation, a rotorcraft includes a first rotorcraft and at least one second rotorcraft. The first rotorcraft has a first main rotor and a first tail rotor. The at least one second rotorcraft has a second main rotor and a second tail rotor. The at least one second rotorcraft are attachable and detachable to and from the first rotorcraft. Further, according to one implementation, a method of controlling the above-mentioned rotorcraft includes: flying the first rotorcraft, to which the at least one second rotorcraft has been attached, to a destination; and separating the at least one second rotorcraft from the first rotorcraft at the destination.

Abstract: Passenger seat assemblies may be used in vehicles such as aircraft. The passenger seat assembly includes a first wall, a second wall opposite from the first wall, and a passenger seat having a first side and a second side opposite from the first side. The passenger seat is positioned between the first wall and the second wall. The passenger seat assembly is positionable between a forward-facing configuration and an aft-facing configuration. In both the forward-facing configuration and the aft-facing configuration, the first wall is proximate to the first side of the passenger seat and the second wall is proximate to the second side of the passenger seat.

Abstract: Embodiments are directed to an aircraft fuselage comprises two keel beams and two roof beams. Each keel beam is formed as a single component having no joints. Each keel beam comprises a first portion that is configured to define a floor of an aircraft and a second portion that is configured to define a tail section of an aircraft. The second portion is positioned at an angle relative to the first portion. Each roof beam is coupled to the second portion of a corresponding keel beam at a point remote from the first portion. Each roof beam and a corresponding keel beam are positioned along a single butt line relative to an aircraft fuselage centerline. Frame members are coupled to both keel beams and both roof beams.

Abstract: A seat base includes a plurality of linear actuators each having a first end pivotally mounted to a base member and a second end pivotally mounted to a seat member. A controller is adapted for controlling an extension length of each of the plurality of linear actuators in a coordinated manner for adjusting a position of the seat member with six degrees-of-freedom and for damping vibration of the seat member. An active vibration mitigation method for reducing vibrations of an aircraft seat includes receiving vibration data from one or more accelerometers mounted to the aircraft seat and determining a vibration profile based on the vibration data. When vibration mitigation is warranted, control signals for damping vibration are determined and transmitted to a plurality of linear actuators adapted to support the aircraft seat.

Abstract: An arrangement of individual seats for installation in an aeroplane cabin having a first set of two seats and a second set of two seats, each seat having an axis and being convertible between a sitting position and an extended position, said arrangement having a longitudinal axis. The arrangement also includes (i) a first central console having a first foot area and a second foot area open in two opposite directions relative to each other and respectively associated with the first seat of the first set and the first seat of the second set and (ii) a second central console having a first foot area and a second foot area open in two opposite directions relative to each other and respectively associated with the second seat of the first set and the second seat of the second set.