A composite structure manufacturing method comprising: a lamination step in which a plurality of fiber-reinforced resin sheets are laminated to form a plate-shaped laminate; a pressing deformation step in which a third roller or similar, which rolls along a plate surface of the laminate, is used to press the plate surface of the laminate, thereby forming a recessed section or a protruding section in a prescribed section of the laminate; a short direction deformation step in which, after the pressing deformation step, the laminate is deformed in the short direction to make the long direction cross-section into a prescribed shape; and a long direction deformation step in which, after the pressing deformation step, the laminate is deformed in the long direction to make the short direction cross-section into a prescribed shape.

An aircraft flooring system is provided, made up of a low-weight carpet tile which functions both as a moisture barrier and as the loop part of a hook-and-loop system, for coupling to a hook part of a hook-and-loop system, which is bound to an aircraft floor. Specifically, a barrier backing within the carpet tile, comprising a nonwoven fabric portion, is able to act as the moisture barrier and the loop part, which allows for coupling of the carpet tile with the floor, without the need to add additional loops to the carpet tile, thereby realizing savings in material cost and weight.

An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

An air separation module includes a canister extending between a first end and an opposite second end, a separator fixed within the canister to separate a compressed air flow into an oxygen-enriched air flow fraction and an oxygen-depleted air flow fraction, and a one-piece cap. The one-piece cap is connected to the first end of the canister and has a filter module mount portion on a side of the one-piece cap opposite the separator to support a filter module with the air separation module. Nitrogen generation systems and methods of making air separation modules are also described.

A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.

Systems and methods relate to a vertical takeoff and landing (VTOL) platform that can include a stator and a rotor magnetically levitated by the stator. The rotor and stator can be annular, such that the rotor rotates about a rotational axis. The stator can include magnets that provide guidance, levitation, and drive forces to drive the rotor, as well as to control operation of rotor blades of the rotor that can be independently rotated to specific pitch angles to control at least one of lift, pitch, roll, or yaw of the VTOL platform. Various controllers can be used to enable independent and redundant control of components of the VTOL platform.

A thermal energy system for use with an aircraft includes a cooling loop and a cooler. The cooling loop includes a fluid conduit and a pump configured to move fluid through the fluid conduit to transfer heat from a heat source to the fluid in the fluid conduit to cool the heat source. The cooler includes an air-stream heat exchanger located in a duct and is in thermal communication with the fluid conduit to transfer heat between the fluid in the cooling loop and the air passing through the duct.

Various embodiments provide a method for installing a seat suspension on a seat frame having a first side frame member and a second side frame member opposed to and spaced apart from each other. The method may include moving a retainer on a first side of the seat suspension in a direction substantially perpendicular to a plane defined by the first and second side frame members for fastening onto a support member on the first side frame member; and moving a retainer on a second side of the seat suspension in the direction substantially perpendicular to the plane defined by the first and second side frame members for fastening onto a support member on the second side frame member. The second side of the seat suspension is opposed to and spaced apart from the first side of the seat suspension.

Methods and systems for a full-scale vertical takeoff and landing manned or unmanned aircraft, having an all-electric, low-emission or zero-emission lift and propulsion system, an integrated ‘highway in the sky’ avionics system for navigation and guidance, a tablet-based motion command, or mission planning system to provide the operator with drive-by-wire style direction control, and automatic on-board-capability to provide traffic awareness, weather display and collision avoidance. Automatic computer monitoring by a programmed triple-redundant digital autopilot computer controls each motor-controller and motor to produce pitch, bank, yaw and elevation, while simultaneously restricting the flight regime that the pilot can command, to protect the pilot from inadvertent potentially harmful acts that might lead to loss of control or loss of vehicle stability. By using the results of the state measurements to inform motor control commands, the methods and systems contribute to the operational simplicity, reliability and safety of the vehicle.

Embodiments of the present disclosure relate generally to the use of the fuel cell systems on board aircraft and other passenger transportation vehicles and to methods of using heat, air, and water generated by such fuel cell systems. The heat may be used to address condensation within the aircraft. The heat may be used to help evaporate excess water that would otherwise condense in the aircraft skin. The excess water collected may be used to create humidification for cabin air. In other examples, the heat, warmed air, or warmed water may be delivered to other locations or heating systems for beneficial use.