Abstract: 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.

Abstract: A pressure deck system for a fuselage of an aircraft. The pressure deck system comprises a first sloping outboard pressure panel, a first longitudinal stiffener connected to the first sloping outboard pressure panel, a second sloping outboard pressure panel opposite the first sloping outboard pressure panel, a second longitudinal stiffener connected to the second sloping outboard pressure panel, pressure panels between the first sloping outboard pressure panel and the second sloping outboard pressure panel and forming the an upper barrier of a wheel well, longitudinal beams connected to the pressure panels and supporting a cabin floor of the fuselage, and a sloping pressure deck connecting a number of these components to the rear spar of the center wing box. A waterline of the pressure deck system is de-coupled from a side-of-body waterline in the fuselage.

Abstract: Disclosed herein is a body of a mobile vehicle. The body includes skin, a stringer, and a frame. The skin comprises a first tab and a second tab, opposite the first tab. The first tab is fixed directly onto the skin and the second tab is fixed directly onto the skin. The frame comprises a cut-out, a first foot, and a second foot. The second foot is spaced apart from the first foot by the cut-out. The first foot is fixed directly onto the first tab of the stringer, such that the first tab of the stringer is immediately interposed between the first foot of the frame and the skin. The second foot is fixed directly onto the skin, such that no portion of the frame is fixed directly onto the second tab of the stringer.

Abstract: A vehicle, such as an aircraft, structural architecture for supporting a horizontal stabilizer with a back up beam having an upper longeron fitting connected to the front side and secured with a back up fitting on the back side, a lower longeron fitting connected to the front side and secured with a back up fitting on the back side, and a pivot fitting connected to the front side of the first back up beam in between the upper longeron fitting and the lower longeron fitting and secured with a third back up fitting on the back side of the back up beam.

Abstract: A pressure deck system for a fuselage of an aircraft. The pressure deck system comprises a first sloping outboard pressure panel, a first longitudinal stiffener connected to the first sloping outboard pressure panel, a second sloping outboard pressure panel opposite the first sloping outboard pressure panel, a second longitudinal stiffener connected to the second sloping outboard pressure panel, pressure panels between the first sloping outboard pressure panel and the second sloping outboard pressure panel and forming the an upper barrier of a wheel well, longitudinal beams connected to the pressure panels and supporting a cabin floor of the fuselage, and a sloping pressure deck connecting a number of these components to the rear spar of the center wing box. A waterline of the pressure deck system is de-coupled from a side-of-body waterline in the fuselage.

Abstract: A twisted strap transfers loads generated by an aircraft passenger floor from the floor to an aircraft fuselage. The twisted strap may be formed of carbon fiber reinforced plastic, fiberglass reinforced plastic, or metal, such as aluminum, stainless steel, or titanium alloy. The twisted strap has first and second ends configured to be twisted between 40 to 120 degrees relative to the other whenever connected to a seat track and a forward-aft extending fuselage stiffener, respectively. In at least one form, the twisted strap has a length ranging from 15 to 30 inches, a width of 1 to 2 inches, and thickness of 0.1 to 0.5 inch. Each end incorporates apertures for accommodating separate connectors spaced at least four-to six diameters apart along the length of the twisted strap, and the twisted strap is configured to accommodate minimums of 9 G's of force in tension and 1.5 G's in compression.

Abstract: A vehicle, such as an aircraft, structural architecture for supporting a horizontal stabilizer with a back up beam having an upper longeron fitting connected to the front side and secured with a back up fitting on the back side, a lower longeron fitting connected to the front side and secured with a back up fitting on the back side, and a pivot fitting connected to the front side of the first back up beam in between the upper longeron fitting and the lower longeron fitting and secured with a third back up fitting on the back side of the back up beam.

Abstract: The illustrative embodiments disclose a pressure bulkhead system comprising an aft pressure bulkhead, skin splice angles, and stringer splice angles. The aft pressure bulkhead has an outer compression ring. The skin splice angles are positioned adjacent to one another and joined to the outer compression ring. The skin splice angles form a joint between a first section of a fuselage, a second section of the fuselage, and the aft pressure bulkhead. The stringer splice angles join the skin splice angles to a stringer in the second section of the fuselage.

Abstract: 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.

Abstract: A bulkhead joint assembly that includes a strap section configured to secure to an aft section of a fuselage and forward section of the fuselage and extend past a bulkhead of the fuselage. The bulkhead joint assembly also includes a chord engaging and secured to the strap section, wherein the chord is configured to extend along the bulkhead to transfer a force from the bulkhead in shear between the chord and the strap section.

Abstract: An assembly of thermoplastic parts for forming a final composite part is presented where the assembly includes at least two prefabricated shells fabricated of thermoplastic. Each prefabricated shell has substantially the same shape as the final composite part and where the shapes of the prefabricated shells have dimensions that allow the prefabricated shells to be assembled into a nest for placement into a mold.

Abstract: A pressure bulkhead for a vehicle disclosed. The pressure bulkhead is configured to separate a pressurized interior from an unpressurized interior of the vehicle. The pressure bulkhead includes a bulkhead wall having a radially inner disk and a radially outer compression ring. The radially inner disk has a surface and a first thickness and the radially outer compression ring having a second thickness that is greater than the first thickness. The radially outer compression ring defines a periphery of the bulkhead wall and the second thickness of the radially outer compression ring is effective to provide a strength to oppose meridional and hoop stresses across the surface of the radially inner disk in response to a pressure differential across the bulkhead wall. The pressure bulkhead also includes an attachment ring that is affixed to the periphery of the bulkhead wall.

Abstract: A twisted strap transfers loads generated by an aircraft passenger floor from the floor to an aircraft fuselage. The twisted strap may be formed of carbon fiber reinforced plastic, fiberglass reinforced plastic, or metal, such as aluminum, stainless steel, or titanium alloy. The twisted strap has first and second ends configured to be twisted between 40 to 120 degrees relative to the other whenever connected to a seat track and a forward-aft extending fuselage stiffener, respectively. In at least one form, the twisted strap has a length ranging from 15 to 30 inches, a width of 1 to 2 inches, and thickness of 0.1 to 0.5 inch. Each end incorporates apertures for accommodating separate connectors spaced at least four-to six diameters apart along the length of the twisted strap, and the twisted strap is configured to accommodate minimums of 9 G's of force in tension and 1.5 G's in compression.

Abstract: A pressure bulkhead for a vehicle disclosed. The pressure bulkhead is configured to separate a pressurized interior from an unpressurized interior of the vehicle. The pressure bulkhead includes a bulkhead wall having a radially inner disk and a radially outer compression ring. The radially inner disk has a surface and a first thickness and the radially outer compression ring having a second thickness that is greater than the first thickness. The radially outer compression ring defines a periphery of the bulkhead wall and the second thickness of the radially outer compression ring is effective to provide a strength to oppose meridional and hoop stresses across the surface of the radially inner disk in response to a pressure differential across the bulkhead wall. The pressure bulkhead also includes an attachment ring that is affixed to the periphery of the bulkhead wall.

Abstract: The illustrative embodiments disclose a pressure bulkhead system comprising an aft pressure bulkhead, skin splice angles, and stringer splice angles. The aft pressure bulkhead has an outer compression ring. The skin splice angles are positioned adjacent to one another and joined to the outer compression ring. The skin splice angles form a joint between a first section of a fuselage, a second section of the fuselage, and the aft pressure bulkhead. The stringer splice angles join the skin splice angles to a stringer in the second section of the fuselage.

Abstract: A pressure bulkhead may include a bulkhead wall having a radially inner disk and a radially outer compression ring, the outer compression ring being reinforced to balance meridional and hoop stresses sustained by the bulkhead wall in response to a pressure differential across the pressure bulkhead; and the radially inner disk being unitary with the outer compression ring and being made of the same material as the outer compression ring.

Abstract: A method of constructing a large, complex composite panel involves connecting smaller compression molded thermoplastic subpanels, edge to edge using a thermoplastic co-consolidation method. The edges of adjacent subpanels are given complementary surface configurations. The surface configurations are overlapped and heat and pressure are applied to the overlapping surface constructions to co-consolidate the surface constructions in forming a large, composite panel of two or more subpanels.

Abstract: A method of forming a direct bearing joint includes coupling a first load-bearing structure to a second load-bearing structure. The second load-bearing structure includes a first structural feature comprising a first arcuate shape. The method also includes coupling a composite skin including a second structural feature comprising a second arcuate shape to the second load-bearing structure. The composite skin is coupled to the second load-bearing structure such that the first and second structural features are mated against each other to facilitate distributing compressive loads from the second load-bearing structure into the composite skin.

Abstract: Disclosed herein is a body of a mobile vehicle. The body includes skin, a stringer, and a frame. The skin comprises a first tab and a second tab, opposite the first tab. The first tab is fixed directly onto the skin and the second tab is fixed directly onto the skin. The frame comprises a cut-out, a first foot, and a second foot. The second foot is spaced apart from the first foot by the cut-out. The first foot is fixed directly onto the first tab of the stringer, such that the first tab of the stringer is immediately interposed between the first foot of the frame and the skin. The second foot is fixed directly onto the skin, such that no portion of the frame is fixed directly onto the second tab of the stringer.

Abstract: An assembly of thermoplastic parts for forming a final composite part is presented where the assembly includes at least two prefabricated shells fabricated of thermoplastic. Each prefabricated shell has substantially the same shape as the final composite part and where the shapes of the prefabricated shells have dimensions that allow the prefabricated shells to be assembled into a nest for placement into a mold.