Abstract: A system includes a mandrel contoured to define a tapering tubular shape of a workpiece cured on the mandrel and a demolding tool. The demolding tool is configured to remove the workpiece from the mandrel after the workpiece is cured on the mandrel and cut longitudinally. The demolding tool is configured to remove the workpiece from the mandrel by deforming a first end of the workpiece to at least partially disengage the first end of the workpiece from a first end of the mandrel, and subsequently, deforming a second end of the workpiece to at least partially disengage the second end of the workpiece from a second end of the mandrel. The first end of the workpiece may have a first cross-sectional area that is smaller than a second cross-sectional area of the second end of the workpiece.

Abstract: An aircraft tail assembly includes an aft fuselage section secured to a forward fuselage section, and includes a stiffener-reinforced pivot bulkhead defined by separate parts secured together by a first set of splices. A longeron extends longitudinally along the aft and forward fuselage sections, and includes a discontinuity adjacent a peripheral edge of the pivot bulkhead. The aircraft tail assembly includes a second set of splices that overlie the discontinuity. One of the second set of splices extends laterally over the longeron to bridge the discontinuity adjacent the peripheral edge of the pivot bulkhead, and another of the second set of splices extends longitudinally along the longeron to secure the longeron to the pivot bulkhead adjacent the discontinuity. A chord engages the peripheral edge of the pivot bulkhead to facilitate transfers of force loads from the bulkhead along a load path that includes the longerons and the splices.

Abstract: A system includes a mandrel contoured to define a tapering tubular shape of a workpiece cured on the mandrel and a demolding tool. The demolding tool is configured to remove the workpiece from the mandrel after the workpiece is cured on the mandrel and cut longitudinally. The demolding tool is configured to remove the workpiece from the mandrel by deforming a first end of the workpiece to at least partially disengage the first end of the workpiece from a first end of the mandrel, and subsequently, deforming a second end of the workpiece to at least partially disengage the second end of the workpiece from a second end of the mandrel. The first end of the workpiece may have a first cross-sectional area that is smaller than a second cross-sectional area of the second end of the workpiece.

Abstract: A securement assembly for securing a vertical tail fin assembly to an aircraft includes a first lug member secured to the vertical tail fin assembly. The securement assembly further includes a first clevis member. The first clevis member includes a first end portion of the first clevis member is engaged to the first lug member. A second end portion of the first clevis member is secured to a first fuselage frame constructed of a composite material with a first fastener which extends through the second end portion and the first fuselage frame in a first direction transverse to the first fuselage frame.

Abstract: An aircraft tail assembly includes an aft fuselage section secured to a forward fuselage section, and includes a stiffener-reinforced pivot bulkhead defined by separate parts secured together by a first set of splices. A longeron extends longitudinally along the aft and forward fuselage sections, and includes a discontinuity adjacent a peripheral edge of the pivot bulkhead. The aircraft tail assembly includes a second set of splices that overlie the discontinuity. One of the second set of splices extends laterally over the longeron to bridge the discontinuity adjacent the peripheral edge of the pivot bulkhead, and another of the second set of splices extends longitudinally along the longeron to secure the longeron to the pivot bulkhead adjacent the discontinuity. A chord engages the peripheral edge of the pivot bulkhead to facilitate transfers of force loads from the bulkhead along a load path that includes the longerons and the splices.

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: 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 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 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: The disclosed shell structure splice and method may include a first panel having a first edge, a second panel having a second edge, the second edge being positioned in edgewise alignment with the first edge to form a splice joint, a strap bridging the splice joint and attached to the first panel and the second panel, the strap having a first tapered region and a second tapered region, a first fitting having a tapered section and a flat section, the tapered section being attached to the first tapered region of the strap, and a second fitting having a tapered section and a flat section, the tapered section being attached to the second tapered region of the strap.

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.