Abstract: An aerodynamic lift structure comprises unbalanced composite skin that couples twist and bending.

Abstract: A method is presented. The method comprises identifying a desired shape of a ply on a tool, in which the ply has a fiber orientation; identifying a cut shape for the ply, in which the cut shape is different than the desired shape; cutting a composite prepreg ply to have the cut shape, the composite prepreg ply having the fiber orientation; using a deformable carrier to apply the composite prepreg ply having the cut shape to the tool such that the composite prepreg ply has the desired shape on the tool.

Abstract: A wheel having a longitudinal plane normal to an axis of rotation. The wheel has a rim with side surfaces on opposite sides of the longitudinal plane. A hub is concentrically disposed relative to the rim. Two unitary side elements are disposed on opposite sides of the longitudinal plane and are coupled to the rim and to end portions of the hub. Each of the unitary side elements has an annular sidewall, a flange portion, and a plurality of spokes that do not cross the longitudinal plane and that integrally interconnect the annular sidewall and the flange portion. An end portion of each spoke of the one side element is tied to the end portion of an aligned spoke of the other side element adjacent to the sidewall to restrict the tied end portions from moving away from each other.

Abstract: An aircraft fuselage may include a barrel section having a side region. The fuselage may include a first cutout and a second cutout formed in the side region in side-by-side relation to one another. The fuselage may provide a direct load path extending along the barrel section. The load path may extend substantially continuously from a lower portion of the side region generally under the first cutout to an upper portion of the side region generally over the second cutout.

Abstract: A composite laminate has a primary axis of loading and comprises a plurality resin plies each reinforced with unidirectional fibers. The laminate includes cross-plies with fiber orientations optimized to resist bending and torsional loads along the primary axis of loading.

Abstract: An aircraft passenger seat configured in accordance with an embodiment of the invention utilizes composite materials to achieve significant weight savings relative to conventional seat designs. The seat includes one or more lightweight composite support legs, a lightweight composite seat pan, and a lightweight composite seat back structure. The support legs are coupled to the seat pan, which is in turn coupled to the seat back structure. The support legs utilize composite frame elements that are formed as continuous compression molded composite extrusions. The seat pan includes composite fore and aft cross beams that are also formed as continuous compression molded composite extrusions. The aft cross beam includes a rear flange that serves as a flexible “hinge” for the seat back structure. The seat can leverage producible and relatively inexpensive composite manufacturing techniques such that the seat can be economically produced for use as an economy class seat.

Abstract: A composite seat pan for a lightweight aircraft passenger seat includes an open-section fore cross beam, an open-section aft cross beam and a seat pan membrane carried by the fore cross beam and the aft cross beam.

Abstract: Composite prepreg is laid up over a tool by placing prepreg material on a carrier film and using the carrier film to apply the prepreg material to the tool. The prepreg is conformed to contours of the tool by deforming the carrier film.

Abstract: A composite leg for a landing gear assembly includes a composite compression cap including reinforcing fibers that provide strength in compression, and a tension cap including reinforcing fibers that provide strength in tension. At least some of the fibers are oriented at +? and ?? with respect to a longitudinal axis of the leg, where ? is between 2 and 8 degrees.

Abstract: Composite stringer and skin structures and methods for forming the same are disclosed. In one embodiment, a composite stringer and skin structure includes a polymer-based elongated stringer portion having reinforcing fibers positioned in a plurality of adjacent plies, a first portion of the reinforcing fibers being oriented at a relatively shallow angle relative to a selected reference direction, and a second portion of the reinforcing fibers being oriented at a relatively broad angle relative to the selected reference direction. A polymer-based and fiber reinforced skin member adjoins the stringer portion, and an adhesive material is interposed between the stringer portion and the skin member.

Abstract: The invention relates to aircraft floor assemblies and to methods for their assembly. In one embodiment, an aircraft comprises at least one fuselage section and at least one floor section. At least one system component is installed to the floor section prior to installation of the floor section in the fuselage of the aircraft. In another embodiment, a floor section adapted to be installed in an aircraft includes at least one system component installed to the floor section while it is outside of the aircraft. In yet another embodiment, a method is disclosed for assembling an aircraft. The method comprises installing at least one system component to a floor section, and installing the floor section into a fuselage section of the aircraft.

Abstract: An aircraft passenger seat configured in accordance with an embodiment of the invention utilizes composite materials to achieve significant weight savings relative to conventional seat designs. The seat includes one or more lightweight composite support legs, a lightweight composite seat pan, and a lightweight composite seat back structure. The support legs are coupled to the seat pan, which is in turn coupled to the seat back structure. The support legs utilize composite frame elements that are formed as continuous compression molded composite extrusions. The seat pan includes composite fore and aft cross beams that are also formed as continuous compression molded composite extrusions. The aft cross beam includes a rear flange that serves as a flexible “hinge” for the seat back structure. The seat can leverage producible and relatively inexpensive composite manufacturing techniques such that the seat can be economically produced for use as an economy class seat.

Abstract: A composite leg for a landing gear assembly includes a composite compression cap including reinforcing fibers that provide strength in compression, and a tension cap including reinforcing fibers that provide strength in tension. At least some of the fibers are oriented at +? and ?? with respect to a longitudinal axis of the leg, where ? is between 2 and 8 degrees.

Abstract: An aircraft fuselage may include a barrel section having a side region. The fuselage may include a first cutout and a second cutout formed in the side region in side-by-side relation to one another. The fuselage may provide a direct load path extending along the barrel section. The load path may extend substantially continuously from a lower portion of the side region generally under the first cutout to an upper portion of the side region generally over the second cutout.

Abstract: An aircraft passenger seat configured in accordance with an embodiment of the invention utilizes composite materials to achieve significant weight savings relative to conventional seat designs. The seat includes one or more lightweight composite support legs, a lightweight composite seat pan, and a lightweight composite seat back structure. The support legs are coupled to the seat pan, which is in turn coupled to the seat back structure. The support legs utilize composite frame elements that are formed as continuous compression molded composite extrusions. The seat pan includes composite fore and aft cross beams that are also formed as continuous compression molded composite extrusions. The aft cross beam includes a rear flange that serves as a flexible “hinge” for the seat back structure. The seat can leverage producible and relatively inexpensive composite manufacturing techniques such that the seat can be economically produced for use as an economy class seat.

Abstract: A composite beam chord is between first and second reinforcement plates. The beam chord includes a first ply of reinforcing fibers with a fiber orientation of +? degrees with respect to a longitudinal axis of the beam chord and a second ply of reinforcing fibers with a fiber orientation of ?? degrees with respect to the longitudinal axis. The angle ? is between 2 and 12 degrees for suppression or delay of ply splitting.

Abstract: Composite prepreg is laid up over a tool by placing prepreg material on a carrier film and using the carrier film to apply the prepreg material to the tool. The prepreg is conformed to contours of the tool by deforming the carrier film.

Abstract: A composite leg for a landing gear assembly includes a composite compression cap including reinforcing fibers that provide strength in compression, and a tension cap including reinforcing fibers that provide strength in tension. The composite leg further includes a torque box including carbon reinforcing fibers for providing torsional rigidity of the leg and carrying shear flow between the caps. The carbon fibers in the torque box are oriented at +? and ?? with respect to a longitudinal axis of the leg, where ? is between 35 and 55 degrees.

Abstract: An aircraft seat assembly configured in accordance with an example embodiment of the invention offers a light weight and comfortable seat cushioning system that also provides energy-absorption and enhanced passenger maneuverability in extreme conditions such as may be experienced in a hard landing situation. The cushioning system includes a crushable, energy-absorbing layer, a main cushioning layer, a smaller ishial insert layer which may be the same as the main cushioning material and a semi-dynamic pneumatic cell which uses a dual action breather valve to vary its inflation with changes in cabin pressure. The seat cushion may be finished with a covering of cloth or upholstery.