A blank panel assembly comprising a skin panel configured to define a brace region and an accessory region and a brace assembly operatively connected to the skin panel within the brace region of the skin panel. The brace assembly comprises first and second main members, a plurality of cross members, and plurality of brace members. The first and second main members are riveted to the skin panel within at least a portion of the brace region. The plurality of cross members are riveted to the skin panel within at least a portion of the brace region. The third cross member portions are riveted to the third main member portions. The at least one accessory is adapted to be supported by the skin panel in the accessory region.

A method of manufacturing a structural component for a vehicle, in particular an aircraft or spacecraft, includes additively manufacturing a reinforcing plate of a metal material having on a joining surface a plurality of joining arms projecting from the joining surface; and joining the reinforcing plate at the joining surface to a structural element to form the structural component by inserting the joining arms into the structural element such that the joining arms permanently hold the structural element together with the reinforcing plate.

A method of fabricating a panel for a helicopter airframe configurable in a plurality of helicopter configurations comprises the following steps. Operational characteristics of the helicopter airframe are defined. A skin panel is provided, where the skin panel is configured according to the operational characteristics of the helicopter airframe. A brace region is defined relative to the skin panel based on the operational characteristics of the helicopter airframe and the plurality of helicopter configurations. A brace assembly is operatively connected to the skin panel within the brace region to form a blank panel assembly. Accessories are arranged relative to the blank panel assembly according on one of the helicopter configurations to obtain a configured panel assembly.

Pressure panel assemblies have a high-pressure side and a low-pressure side and comprise panels, one or more splicing members, and one or more beams. The panels comprise a first panel and a second panel that is positioned laterally adjacent to the first panel. Each of the first panel and the second panel have a longitudinal panel length. A first splicing member is welded to the first panel and to the second panel along the longitudinal panel length of the first and second panels. A first beam is joined directly to the first splicing member or is joined directly to the first panel and to the second panel.

An auxiliary power unit enclosure of an aircraft includes a space frame configured to carry a load and defining an auxiliary power unit compartment. The space frame includes a plurality of frame elements coupled together at a plurality of nodes. The auxiliary power unit enclosure also includes a fairing coupled to and surrounding the space frame.

The present invention is directed to an apparatus for managing thermal energy of an electric aircraft energy source. Apparatus may include fins, which extend from a skin of electric aircraft. The energy source may bias or be adjacent to the fins so that heat energy may dissipate from the energy source and through the fins and, thus, the skin. A coolant may also be run through the apparatus, where the coolant may flow through channels that are disposed between the fins.

The present invention is directed to an apparatus for managing thermal energy of an electric aircraft energy source. Apparatus may include fins, which extend from a skin of electric aircraft. The energy source may bias or be adjacent to the fins so that heat energy may dissipate from the energy source and through the fins and, thus, the skin. A coolant may also be run through the apparatus, where the coolant may flow through channels that are disposed between the fins.

Described herein are novel 7xxx series aluminum alloys. The alloys exhibit high strength. The alloys can be used in a variety of applications, including automotive, transportation, electronics, aerospace, and industrial applications. Also described herein are methods of making and processing the alloys. Further described herein are methods of producing a metal sheet, which include casting an aluminum alloy as described herein to form an ingot, homogenizing the ingot, hot rolling the ingot to produce a hot band, and cold rolling the hot band to a metal sheet of final gauge.

Described herein are novel 7xxx series aluminum alloys. The alloys exhibit high strength. The alloys can be used in a variety of applications, including automotive, transportation, electronics, aerospace, and industrial applications. Also described herein are methods of making and processing the alloys. Further described herein are methods of producing a metal sheet, which include casting an aluminum alloy as described herein to form an ingot, homogenizing the ingot, hot rolling the ingot to produce a hot band, and cold rolling the hot band to a metal sheet of final gauge.

A joint for a metallic skin structure includes a first end portion and a second end portion positioned in an overlying relationship with each other. A first row of a first plurality of bores, within the first end portion, have adjacent bores spaced apart from one another. A second row of a second plurality of bores, within the second end portion have adjacent bores spaced apart from one another. First common central axis is defined by a first bore of each of the first and second plurality of bores. Second common central axis is defined by a second bore of each of the first and second plurality of bores. A line of securement extends between the first and second common central axes. At least one reinforcement fiber embedded within one of the first or second end portion extending orthogonal to and on either side of the line of securement.