Abstract: In an example, an overhead payload module is described. The overhead payload module comprises a ceiling assembly, an aisle floor assembly, a first payload assembly attached to the ceiling assembly and the aisle floor assembly to form a first side of the overhead payload module, and a second payload assembly attached to the ceiling assembly and the aisle floor assembly to form a second side of the overhead payload module. The first payload assembly comprises a first payload module and a first overhead stowbin module structurally integrated with the first payload module and having a first stowage area configured to receive stowbins. The second payload assembly is positioned opposite the first payload assembly to form an aisle therebetween and comprises a second payload module and a second overhead stowbin module structurally integrated with the second payload module and having a second stowage area configured to receive stowbins.

Abstract: An aircraft wing has a wing body with a span and a chord. A skin of the wing body has a leading edge portion with an inner surface delimiting a cavity of the wing body. A wing ice protection system includes a curved flow guide disposed within the cavity and spaced apart from the leading edge portion to define a fluid channel, A bleed air supply is operable to convey bleed air to the fluid channel. Turbulence-generating members are positioned within the leading edge portion to engage the bleed air in the fluid channel. The members are spaced apart along the fluid channel in a chordwise direction and/or in a spanwise direction. A thermal barrier may be disposed on the curved flow guide to thermally insulate the leading edge interior from the fluid channel.

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: A storage system for a flying object is equipped with a landing portion having a landing surface on which the flying object can land, and a storage main body for storing the flying object that has landed on the landing surface. The storage main body includes opening and closing portions that cover the landing surface. The storage system is further equipped with retaining mechanisms adapted to retain the flying object in a state of having landed on the landing surface from a direction perpendicular to the landing surface.

Abstract: A propulsion unit for an aircraft, including an engine and a propeller shaft and further a propeller with airfoils which is coupled to the propeller shaft and having electrical members consuming electrical power, sealing between a case and the propeller shaft being ensured by a dynamic seal housed between a rotating dynamic seal support secured to the propeller shaft and a dynamic seal support flange secured to an end portion of the case, the rotating dynamic seal support being secured to the propeller shaft and abutted against a bearing for supporting this propeller shaft, it is provided that the propulsion unit, in order to deliver electrical power to the electrical members, having a rotating transformer rotated by the propeller shaft and including a stator, a casing of which is secured to the dynamic seal support flange and a rotor, a casing of which is secured to this propeller shaft.

Abstract: A pivot connection part for a flying machine includes an inner body, an outer body radially surrounding the inner body, and a set of connection elements configured to connect the inner body to the outer body. Breaking the connection elements detaches the inner body from the outer body. A first blocking assembly having a cam and a stop is configured to block relative rotation between the inner and outer bodies in a first rotational direction. A second blocking assembly having a pawl and a resilient stop blade is configured to block relative rotation between the inner and outer bodies in a second rotational direction.

Abstract: A ground station for aerial vehicles including a protective casing; at least one charging mechanism; and an extendable landing pad. The extended landing pad is operable to transition between a closed configuration having dimensions suitable to be contained within said protective casing, and an open configuration having dimensions suitable to land the aerial vehicle.

Abstract: A propulsion system for small artificial satellites comprises a plurality of engines (2) fixable to a frame (101) of a satellite (100); a control unit (3) connected functionally to the engines (2) for sending at least one activation signal (AS) for activating at least one engine (2); the system is selectively configurable at least between a first configuration in which at least one of the engines (2) is activated for correcting the orbit of the satellite (100) and a second configuration in which at least one of the engines (2) is activated for dispersing said satellite (100) relative to another adjacent satellite.

Abstract: A control system (50) for an electro-hydraulic servo-actuator (26) envisages: a controller (55), to generate a control current (Ic), designed to control actuation of the electro-hydraulic servo-actuator (26), implementing a position control loop based on a position error (ep), the position error (ep) being a difference between a reference position (Posref) and a measured position (Posmeas) of the electro-hydraulic servo-actuator (26); and a limitation stage (58), coupled to the controller (55) to provide a limitation of the actuator speed of the electro-hydraulic servo-actuator (26); the limitation stage (58) limits a rate of change of a driving current (Id) to be supplied to the electro-hydraulic servo-actuator (26), in order to limit the actuator speed.

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: A ducted fan assembly for generating thrust during edgewise forward flight. The ducted fan assembly includes a duct having an inlet with a leading portion and a diffuser with a trailing portion during the edgewise forward flight. A fan disposed within the duct is configured to rotate relative to the duct about a fan axis to generate an airflow through the duct from the inlet to the diffuser. An active flow control system includes a plurality of injectors including a first injector configured to inject pressurized air substantially tangential with the leading portion of the inlet and a second injector configured to inject pressurized air substantially tangential with the trailing portion of the diffuser such that when the injectors are injecting pressurized air, flow separation of the airflow at the leading portion of the inlet and the trailing portion of the diffuser is reduced.

Abstract: A rotor system has a mast axis, a first rotor rotatable about the mast axis in a first direction and the first rotor has a first number of first rotor blades, and a second rotor rotatable about the mast axis in a second direction and the second rotor has a second number of second rotor blades that is different than the first number. The second direction is opposite the first direction.

Abstract: This disclosure describes a configuration of an unmanned aerial vehicle (“UAV”) that will facilitate extended flight duration. The UAV may have any number of lifting motors. For example, the UAV may include four lifting motors (also known as a quad-copter), eight lifting motors (also known as an octo-copter), etc. Likewise, to improve the efficiency of horizontal flight, the UAV also includes a pivot assembly that may rotate about an axis from a lifting position to a thrusting position. The pivot assembly may include two or more offset motors that generate a differential force that will cause the pivot assembly to rotate between the lifting position and the thrusting position without the need for any additional motors or gears.

Abstract: In an embodiment, a rotorcraft includes: a flight control computer configured to: receive a first sensor signal from a first aircraft sensor of the rotorcraft; receive a second sensor signal from a second aircraft sensor of the rotorcraft, the second aircraft sensor being different from the first aircraft sensor; combine the first sensor signal and the second sensor signal with a complementary filter to determine an estimated vertical speed of the rotorcraft; adjust flight control devices of the rotorcraft according to the estimated vertical speed of the rotorcraft, thereby changing flight characteristics of the rotorcraft; and reset the complementary filter in response to detecting the rotorcraft is grounded.

Abstract: In one aspect the present subject matter is directed to a gas-electric propulsion system for an aircraft. The system may include a turbofan jet engine, an electric powered boundary layer ingestion fan that is coupled to a fuselage portion of the aircraft aft of the turbofan jet engine, and an electric generator that is electronically coupled to the turbofan jet engine and to the boundary layer ingestion fan. The electric generator converts rotational energy from the turbofan jet engine to electrical energy and provides at least a portion of the electrical energy to the boundary layer ingestion fan. In another aspect of the present subject matter, a method for propelling an aircraft via the gas-electric propulsion system is disclosed.

Abstract: An aircraft has an airframe with first and second wings having first and second pylons extending therebetween. A distributed propulsion system attached to the airframe includes at least first, second, third and fourth propulsion assemblies that are independently controlled by a flight control system. A pod assembly is coupled to the airframe. In a VTOL flight mode, the first and second propulsion assemblies are forward of the pod assembly and the third and fourth propulsion assemblies are aft of the pod assembly. In a forward flight mode, the first and second propulsion assemblies are below the pod assembly and the third and fourth propulsion assemblies are above the pod assembly. In both the VTOL and forward flight modes, the first and fourth propulsion assemblies generate thrust having a first direction while the second and third propulsion assemblies generate thrust having a second direction that is different from the first direction.

Abstract: A joint joining an aircraft wing to an aircraft body employs a splice panel that is engaged in surface engagement with a skin panel on a side of the aircraft body and is engaged in surface engagement with a leg panel extending upwardly from the aircraft wing. A plurality of fasteners extend through the splice panel and the leg panel and extend through the splice panel and the skin panel. The plurality of fasteners attach the splice panel to the skin panel and attach the splice panel to the leg panel and thereby attach the skin panel to the leg panel. After fastener holes have been drilled through the splice panel and the leg panel to attach the splice panel to the leg panel, the splice panel can be removed from the leg panel. This provides easy access to the fastener holes drilled through the leg panel for deburring of the fastener holes.

Abstract: An arrangement of a structural element for an aerospace vehicle and a battery set. The structural element extends along a longitudinal direction and has a main web, a first flange and a second flange. The flanges extend away from the main web and are defined by flange edges extending along the longitudinal direction. The first flange, the second flange and the main web form a U-shaped profile defining a cavity. The battery set includes a baseplate and at least one battery on the baseplate. The structural element and the battery set are formed such that the baseplate can be releasably attached to the structural element. The baseplate extends between flange edges and the battery is received in the cavity when the battery set is mounted to the structural element. Further, an aerospace vehicle including such an arrangement, a structural element for an aerospace vehicle and a battery set are disclosed.

Abstract: Aspects relate to systems and methods for orienting a thrust propulsor in response to a failure event of a vertical take-off and landing (VTOL) aircraft. An exemplary system includes a plurality of lift propulsors mechanically connected to a VTOL aircraft, wherein each of the plurality of lift propulsors are configured to produce lift, a plurality of sensors, wherein at least a sensor is configured to detect a failure of at least a lift propulsor, and transmit a failure datum, a thrust propulsor mechanically attached to the VTOL aircraft with an orientable joint, wherein the thrust propulsor is configured to produce thrust and orient the thrust propulsor as a function of a thrust orientation datum, and a flight controller configured to receive the failure datum, generate a thrust orientation datum as a function of the failure datum, and transmit the thrust orientation datum to the orientable joint.