A method for printing three-dimensional parts with an additive manufacturing system, comprising printing successive layers having increasing cross-sectional areas, and printing layers of a three-dimensional part onto the previously printed layers, where a last layer of the previously printed successive layers has a cross-sectional area that is at least as large as a footprint area of the three-dimensional part.

A single piece pulsed flow wing assembly method providing for horizontal wing manufacture is accomplished using synchronized automated vehicles guided in a predetermined manner to move and, locate wing structure in a plurality of assembly positions. Multi-axis assembly positioning systems (MAPS) are used at each assembly position to support and index components in the wing structure and determinant assembly techniques are used for indexing of the components. Modular automated manufacturing processes employing magnetic assembly clamping, drilling, fastener insertion, and sealant application are employed.

A device to absorb kinetic energy caused by an exceptional load includes an outer casing configured to maintain integrity after the exceptional load. A core of the device is made of a compactable material at least partially filling the outer casing. The core material is compacted under an exceptional load and absorbs some of the kinetic energy caused by the load. At least one stiffness element is incorporated into the core. A distribution element includes each stiffness element. An aircraft, a vehicle, an item of equipment and an installation includes such a device.

A device to absorb kinetic energy caused by an exceptional load includes an outer casing configured to maintain integrity after the exceptional load. A core of the device is made of a compactable material at least partially filling the outer casing. The core material is compacted under an exceptional load and absorbs some of the kinetic energy caused by the load. At least one stiffness element is incorporated into the core. A distribution element includes each stiffness element. An aircraft, a vehicle, an item of equipment and an installation includes such a device.

A fixed wing aircraft has a wing with an aerofoil cross-section defining an upper and lower geometric surfaces which meet at a geometric leading edge of the wing. The wing has an upper and lower aerodynamic surfaces while in flight. The upper aerodynamic surface and the lower aerodynamic surface meet at an aerodynamic leading edge at the intersection with an attachment line dividing the air that passes over the upper aerodynamic surface from the air that passes over the lower aerodynamic surface. The lower geometric surface adjacent the geometric leading edge has a roughness strip with a step height of at least 50 microns over the lower geometric surface. The roughness strip is located on the lower aerodynamic surface of the wing when the aircraft is flown at a load factor of 1 g and is located on the upper aerodynamic surface when the load factor is above 1.2 g.

A fixed wing aircraft has a wing with an aerofoil cross-section defining an upper and lower geometric surfaces which meet at a geometric leading edge of the wing. The wing has an upper and lower aerodynamic surfaces while in flight. The upper aerodynamic surface and the lower aerodynamic surface meet at an aerodynamic leading edge at the intersection with an attachment line dividing the air that passes over the upper aerodynamic surface from the air that passes over the lower aerodynamic surface. The lower geometric surface adjacent the geometric leading edge has a roughness strip with a step height of at least 50 microns over the lower geometric surface. The roughness strip is located on the lower aerodynamic surface of the wing when the aircraft is flown at a load factor of 1 g and is located on the upper aerodynamic surface when the load factor is above 1.2 g.

An aerial device is provided. The aerial device includes a processor and a memory that includes instructions configured to cause the processor to perform certain operations when the processor executes the instructions. The operations may include receiving a first signal indicative of a first position of the aerial device. The operations may also include generating, based on the first signal and based on a randomly generated sequence, a second signal configured to actuate flight hardware of the aerial device to a second position.

An aerial device is provided. The aerial device includes a processor and a memory that includes instructions configured to cause the processor to perform certain operations when the processor executes the instructions. The operations may include receiving a first signal indicative of a first position of the aerial device. The operations may also include generating, based on the first signal and based on a randomly generated sequence, a second signal configured to actuate flight hardware of the aerial device to a second position.

A temperature monitoring unit may be removably installed inside an aircraft wing structure for monitoring temperature conditions along the span of the wing. The wing structure has a temperature-sensitive device (162) for monitoring a temperature condition, which is attached to a support frame (173). The support frame and attached temperature-sensitive device may be installed as a unit within the wing structure. The support frame may be configured for sliding engagement inside the wing structure, for example, with a set of tracks.

An aerodynamic structure incorporated in an aircraft control surface (10) provides a spar (16) extending along at least a portion of the control surface in a direction and the spar includes a plurality of bends along the direction of extension along the control surface to provide space to accommodate actuator fittings or other structural or operational requirements.